Abstract

The invention is directed to a method for cleaning a component from powder residues of an additive layering method using a cleaning device, wherein a machine plate and the component arranged thereon are excited during a cleaning process by a vibration actuator of the cleaning device with a set resonance frequency of the machine plate to carry out a mechanical vibration. It is provided that the machine plate is excited by predefined vibration movements of the at least one vibration actuator to the predefined mechanical vibration, wherein the predefined vibration movements of the at least one vibration actuator occur in parallel to a main plane of the machine plate. The invention also relates to a cleaning device for cleaning an at least partially additively manufactured component, in particular a component of a turbomachine.

IPC Classes  ?

• B22F 10/68 - Cleaning or washing
• B08B 7/02 - Cleaning by methods not provided for in a single other subclass or a single group in this subclass by distortion, beating, or vibration of the surface to be cleaned
• B08B 13/00 - Accessories or details of general applicability for machines or apparatus for cleaning
• B29C 64/35 - Cleaning
• B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
• B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing

Abstract

The present invention relates to a method of calibrating a thermal FEM-model of a turbomachine, the method comprising: i) creating a meta-model of the thermal FEM-model; ii) feeding, for a set of thermal variables, a set of input values to the meta-model for a calculation in the meta-model; iii) obtaining a set of output values from the calculation in the meta-model for the set of input values; iv) comparing the set of output values to measurement data of the turbomachine.

IPC Classes  ?

• G06F 30/15 - Vehicle, aircraft or watercraft design

Abstract

A module for a turbomachine, including a guide blade arrangement, a seal carrier that is situated radially within an inner platform of the guide blade arrangement, seal carrier walls, namely, a first seal carrier wall and a second seal carrier wall, and a sliding body as well as a connecting element. The seal carrier walls have a multipart design with respect to one another, and the second seal carrier wall is fastened to the first seal carrier wall and to the seal carrier via the connecting element. The sliding body holds the seal carrier walls at a distance from one another in such a way that they mutually axially delimit a clearance in which the guide blade arrangement engages via a radially inwardly extending guide pin. A radially inner section of the second seal carrier wall has frictional contact relative to the seal carrier.

IPC Classes  ?

• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F01D 9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits

Goods & Services

Separator membranes for hydrogen fuel cells, namely, polymeric membranes in chemical form for the separation of gas Hydrogen storage systems consisting of metal containers for storing gases Generators of electricity and emergency electricity, in particular for aircraft; Fuel cell energy converters, namely, electric power generators; electric power generators based on integrated fuel cell hybrid energy converters; Parts of machines, namely, Heat exchangers and conduits for fluid and heat transfer for integrated fuel cell power generation systems and subsystems, namely, power generators; Integrated hydrogen-fuel systems comprised of heat exchangers being parts of aircraft engines, containers, valves, pumps and lines, namely, parts of machines, for propulsion systems for aircraft; Hydrogen dispensing pumps for filling stations; Parts for electrolysis machines for generating hydrogen, namely, separators and membranes for generators, circulation frames for generators, baffle plates and containers for generators, rectifier droplet separators for generators, and gas-liquid separators; Parts of machines, namely, Gas lines for discharging and discharging gas mixtures, hydrogen and water from drives for aircraft Microprocessor-based, control system comprised of microprocessors and downloadable computer software for controlling fuel cell operation; Hydrogen fuel cells; Control system, for power generating fuel cell generator modules, comprised of computer hardware and embedded operating software, valves, switches and circuits; Test stations for fuel cells; Automatic test stations for fuel cells; downloadable computer software for use in operating test stations for fuel cells; downloadable computer software for use in operating automatic test stations for fuel cells; downloadable computer software for use in operating hydrogen test stations; Fuel cells; Fuel cell stacks; Integrated fuel cell systems comprised of fuel cells; Anodes, sensor devices being temperature, humidity and pressure sensors; cathodes; Fuel cell stacks, heat and pressure sensors and electronic controls, all for integrated fuel cell power generation systems and subsystems; pressure, heat and temperature sensors; computer hardware and downloadable software for controlling the integrated hydrogen fuel system in propulsion systems for aircraft Hydrogen cleaning devices, namely, gas scrubbers; Air filters for fuel cell systems Refueling aircraft with hydrogen; Construction of power generation plants; construction project management and construction supervision in the field of energy generation equipment Electronic transmission of data for use in regulating the fuel system and the fuel cell system and distributing the relevant data to the aircraft, a ground station or an internal memory Storage of hydrogen, for example with an integrated fuel system; Distribution of hydrogen and air as fuel for fuel cells; Electricity supply through distribution of electricity; Distribution of energy; Information, advice and consultancy in relation to all of the aforesaid Power generation; Power generation services; Custom manufacture, for others, of industrial and commercial hydrogen fuel and propulsion systems; Custom manufacture, for others, of fuel cell systems and hydrogen fuel and propulsion systems; Generation of hydrogen; Custom manufacture of fuel cell systems and hydrogen fuel and propulsion systems for others; Information, advice and consultancy in relation to all of the aforesaid Engineering services in the field of the refueling, storage and use of hydrogen as fuel, the conversion of hydrogen to electricity with fuel cells and the installation and integration of such systems, including their control by means of hardware and software; Consultancy in the field of design and development of test stations for fuel cells, fuel cells, integrated hydrogen fuel and propulsion systems, and ancillary equipment; Design of industrial and commercial hydrogen fuel and propulsion systems; Technical advice, research and development and testing services in relation to electricity, propulsion energy from hydrogen and hydrogen-fueled products; Testing services in relation to fuel cells, fuel cell systems, aerospace propulsion systems and hydrogen; Design and testing of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aerospace propulsion systems based on fuel cell technologies; Design of alternative energy systems; Technical consultancy, engineering services and project development in the field of hydrogen fuel and drive systems and fuel cells, fuel cell systems, aviation drive systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation engineering services and project development in the field of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aviation propulsion systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation engineering services and project development in the field of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aviation propulsion systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation

Goods & Services

Separator membranes for hydrogen fuel cells, namely, polymeric membranes in chemical form for the separation of gas Hydrogen storage systems consisting of metal containers for storing gases Generators of electricity and emergency electricity, in particular for aircraft; Fuel cell energy converters, namely, electric power generators; electric power generators based on integrated fuel cell hybrid energy converters; Parts of machines, namely, Heat exchangers and conduits for fluid and heat transfer for integrated fuel cell power generation systems and subsystems, namely, power generators; Integrated hydrogen-fuel systems comprised of heat exchangers being parts of aircraft engines, containers, valves, pumps and lines, namely, parts of machines, for propulsion systems for aircraft; Hydrogen dispensing pumps for filling stations; Parts for electrolysis machines for generating hydrogen, namely, separators and membranes for generators, circulation frames for generators, baffle plates and containers for generators, rectifier droplet separators for generators, and gas-liquid separators; Parts of machines, namely, Gas lines for discharging and discharging gas mixtures, hydrogen and water from drives for aircraft Microprocessor-based, control system comprised of microprocessors and downloadable computer software for controlling fuel cell operation; Hydrogen fuel cells; Control system, for power generating fuel cell generator modules, comprised of computer hardware and embedded operating software, valves, switches and circuits; Test stations for fuel cells; Automatic test stations for fuel cells; downloadable computer software for use in operating test stations for fuel cells; downloadable computer software for use in operating automatic test stations for fuel cells; downloadable computer software for use in operating hydrogen test stations; Fuel cells; Fuel cell stacks; Integrated fuel cell systems comprised of fuel cells; Anodes, sensor devices being temperature, humidity and pressure sensors; cathodes; Fuel cell stacks, heat and pressure sensors and electronic controls, all for integrated fuel cell power generation systems and subsystems; pressure, heat and temperature sensors; computer hardware and downloadable software for controlling the integrated hydrogen fuel system in propulsion systems for aircraft Hydrogen cleaning devices, namely, gas scrubbers; Air filters for fuel cell systems Refueling aircraft with hydrogen; Construction of power generation plants; construction project management and construction supervision in the field of energy generation equipment Electronic transmission of data for use in regulating the fuel system and the fuel cell system and distributing the relevant data to the aircraft, a ground station or an internal memory Storage of hydrogen, for example with an integrated fuel system; Distribution of hydrogen and air as fuel for fuel cells; Electricity supply through distribution of electricity; Distribution of energy; Information, advice and consultancy in relation to all of the aforesaid Power generation; Power generation services; Custom manufacture, for others, of industrial and commercial hydrogen fuel and propulsion systems; Custom manufacture, for others, of fuel cell systems and hydrogen fuel and propulsion systems; Generation of hydrogen; Custom manufacture of fuel cell systems and hydrogen fuel and propulsion systems for others; Information, advice and consultancy in relation to all of the aforesaid Engineering services in the field of the refueling, storage and use of hydrogen as fuel, the conversion of hydrogen to electricity with fuel cells and the installation and integration of such systems, including their control by means of hardware and software; Consultancy in the field of design and development of test stations for fuel cells, fuel cells, integrated hydrogen fuel and propulsion systems, and ancillary equipment; Design of industrial and commercial hydrogen fuel and propulsion systems; Technical advice, research and development and testing services in relation to electricity, propulsion energy from hydrogen and hydrogen-fueled products; Testing services in relation to fuel cells, fuel cell systems, aerospace propulsion systems and hydrogen; Design and testing of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aerospace propulsion systems based on fuel cell technologies; Design of alternative energy systems; Technical consultancy, engineering services and project development in the field of hydrogen fuel and drive systems and fuel cells, fuel cell systems, aviation drive systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation engineering services and project development in the field of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aviation propulsion systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation engineering services and project development in the field of hydrogen fuel and propulsion systems and fuel cells, fuel cell systems, aviation propulsion systems based on fuel cell technologies; Information, advice and consultancy relating to all of the aforesaid; Technical project management in the field of energy generation

Abstract

The invention is directed to a method for cleaning powder residues of an additive layer build-up method away from an at least partly additively manufactured component by a cleaning device, wherein a machine plate and the component arranged thereon are excited to mechanical oscillation during a cleaning process by a vibration actuator of the cleaning device with a set resonant frequency of the machine plate. According to the invention, before the cleaning process is carried out, a resonant frequency of the machine plate is set to the set resonant frequency by an arrangement of a mass element on a securing element of the machine plate.

IPC Classes  ?

• B22F 10/68 - Cleaning or washing
• B29C 64/35 - Cleaning
• B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
• B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes

Abstract

The present invention relates to a method for inspecting a component, in particular a component of a turbomachine (1), including the steps of: capturing (S2) at least one X-ray or CT image of the component (10) using an image-capturing device (20); providing (S21) metadata about the component (10), the metadata including, in particular, a component type, a running time of the component (10), a number of remaining life cycles, and/or a repair history; classifying, by a machine learning system (30), the component (10) into a “serviceable” category or a “non-serviceable” category based on the image captured by the image-capturing device (20) and the provided metadata.

IPC Classes  ?

• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• G06T 7/00 - Image analysis
• G06V 10/82 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using neural networks

Goods & Services

aus metallischen Behältern zur Speicherung von Gasen bestehende Speichersysteme für Wasserstoff. Generatoren [Strom-, Notstrom-], insbesondere für Luftfahrzeuge; Brennstoffzellen-Energiewandler [Stromgeneratoren]; Stromgeneratoren basierend auf Integrierten Brennstoffzellen- Hybrid-Energiewandlern; Wärmetauscher und Leitungen zur Flüssigkeits- und Wärmeübertragung [Maschinenteile] für Integrierte Brennstoffzellen-Energieerzeugungssysteme und - subsysteme [Stromgeneratoren]; Teile und Zusatzteile für alle vorstehend genannten Waren; aus Behältern, Wärmetauschern, Ventilen, Pumpen, Leitungen [Maschinenteile] bestehende integrierte Wasserstofftreibstoffsysteme für Antriebe von Luftfahrzeugen; Wasserstoffzapfsäulen für Tankstellen; Teile für Wasserstoffgeneratoren, nämlich Abscheider und Membranen für Generatoren, Zirkulationsgerüste für Generatoren, Prallbleche und Behälter für Generatoren, Gleichrichter- Tropfenabscheider für Generatoren, Gas-Flüssigkeitsabscheider; Gasleitungen [Maschinenteile] zum Abführen und Ablassen von Gasgemischen, Wasserstoff und Wasser aus Antrieben für Luftfahrzeuge. Integrierte Brennstoffzellen-Energieerzeugungs- und -subsysteme, insbesondere für Luftfahrtantriebe; Wasserstoff- Brennstoffzellen; Stromerzeugende Brennstoffzellengeneratormodule; Steuerungen einschließlich Hardware und Software, Ventile, Schalter und Schaltungen für die vorstehend genannten Waren; Prüfstationen für Brennstoffzellen; Automatische Prüfstationen für Brennstoffzellen; Computersoftware zur Verwendung in Prüfstationen für Brennstoffzellen; Computersoftware für automatische Prüfstationen für Brennstoffzellen; Computersoftware für Wasserstoffprüfstationen; Brennstoffzellen; Brennstoffzellen-Stromsysteme; Brennstoffzellenstapel; Integrierte Brennstoffzellensysteme; Anoden, Sensorik-Geräte, Kathoden, Abscheider Membranen für Wasserstoffbrennstoffzellen; Wasserstoff-Stromspeichersysteme; Teile und Zubehör für alle vorgenannten Waren; Brennstoffzellenstapel, Sensoren und elektronische Steuerungen für Integrierte Brennstoffzellen-Energieerzeugungssysteme und -subsysteme; Sensoren, Hardware und Software zur Regelung des integrierten Wasserstofftreibstoffsystems in Antrieben für Luftfahrzeuge. Wasserstoffreinigungsgeräte; Gleichrichter-Tropfenabscheider; Teile und Bestandteile aller vorstehend genannten Waren; Luftfilter für Brennstoffzellensysteme. Betanken von Luftfahrzeugen mit Wasserstoff; Bau von Energieerzeugungsanlagen; Projektmanagement im Bauwesen [Bauaufsicht] im Bereich von Anlagen zur Energieerzeugung. Elektronische Übermittlung von Daten mit dem Ziel, das Treibstoffsystem und das Brennstoffzellensystem zu Regeln und die relevanten Daten an das Flugzeug, eine Bodenstation oder einen internen Speicher zu verteilen. Befüllen von Behältern zur Verwendung in Wasserstofftreibstoffsystemen für Luftfahrzeuge; Speicherung von Wasserstoff, beispielsweise mit einem integrierten Treibstoffsystem; Verteilung von Wasserstoff und Luft als Treibstoff für Brennstoffzellen; Verteilung von Fluiden zur Verteilung und Ableitung von Wärme; Stromversorgung durch Verteilung von Elektrizität; Verteilung von Energie; Information und Beratung in Bezug auf alles vorstehend Genannte. Stromerzeugung; Energieerzeugungsdienste; Kundenspezifische Fertigung von industriellen und kommerziellen Wasserstofftreibstoff- und -antriebssystemen; Kundenspezifische Fertigung von Brennstoffzellensystemen und Wasserstofftreibstoff- und -antriebssystemen; Erzeugung von Wasserstoff; Kundenspezifische Anfertigung von Brennstoffzellensystemen und Wasserstofftreibstoff- und -antriebssystemen für Dritte; Information und Beratung in Bezug auf alles vorstehend Genannte. Ingenieurtechnische Dienstleistungen auf dem Gebiet der Betankung, Speicherung und Verwendung von Wasserstoff als Treibstoff, der Wandlung von Wasserstoff zu Strom mit Brennstoffzellen und die Installation und Integration solcher Systeme einschließlich deren Regelung durch Hardware und Software; Beratung auf dem Gebiet Entwurf und Entwicklung von Prüfstationen für Brennstoffzellen, Brennstoffzellen, integrierten Wasserstofftreibstoff- und -antriebssystemen und Zusatzausrüstung; Entwurf von industriellen und kommerziellen Wasserstofftreibstoff- und -antriebssystemen; Technische Beratung, Forschung und Entwicklung und Prüfungsleistungen in Bezug auf Strom/Antriebsenergie aus Wasserstoff und mit Wasserstoff betriebene Erzeugnisse; Prüfleistungen in Bezug auf Brennstoffzellen, Brennstoffzellensysteme, [Luftfahrt-] Antriebssysteme und Wasserstoff; Entwurf, Prüfung von Wasserstofftreibstoff- und -antriebssystemen und Brennstoffzellen, Brennstoffzellensysteme, [Luftfahrt-] Antriebssysteme basierend auf Brennstoffzelltechnologien; Entwurf von alternativen Energiesystemen; Technische Beratung, ingenieurtechnische Dienstleistungen und Projektentwicklung im Bereich Wasserstofftreibstoff- und -antriebssystemen und Brennstoffzellen, Brennstoffzellensysteme, [Luftfahrt-]Antriebssysteme basierend auf Brennstoffzelltechnologien; Information und Beratung in Bezug auf alles vorstehend Genannte; Technisches Projektmanagement im Bereich Energieerzeugung.

Goods & Services

aus metallischen Behältern zur Speicherung von Gasen bestehende Speichersysteme für Wasserstoff. Generatoren [Strom-, Notstrom-], insbesondere für Luftfahrzeuge; Brennstoffzellen-Energiewandler [Stromgeneratoren]; Stromgeneratoren basierend auf Integrierten Brennstoffzellen- Hybrid-Energiewandlern; Wärmetauscher und Leitungen zur Flüssigkeits- und Wärmeübertragung [Maschinenteile] für Integrierte Brennstoffzellen-Energieerzeugungssysteme und - subsysteme [Stromgeneratoren]; Teile und Zusatzteile für alle vorstehend genannten Waren; aus Behältern, Wärmetauschern, Ventilen, Pumpen, Leitungen [Maschinenteile] bestehende integrierte Wasserstofftreibstoffsysteme für Antriebe von Luftfahrzeugen; Wasserstoffzapfsäulen für Tankstellen; Teile für Wasserstoffgeneratoren, nämlich Abscheider und Membranen für Generatoren, Zirkulationsgerüste für Generatoren, Prallbleche und Behälter für Generatoren, Gleichrichter- Tropfenabscheider für Generatoren, Gas-Flüssigkeitsabscheider; Gasleitungen [Maschinenteile] zum Abführen und Ablassen von Gasgemischen, Wasserstoff und Wasser aus Antrieben für Luftfahrzeuge. Integrierte Brennstoffzellen-Energieerzeugungs- und -subsysteme, insbesondere für Luftfahrtantriebe; Wasserstoff- Brennstoffzellen; Stromerzeugende Brennstoffzellengeneratormodule; Steuerungen einschließlich Hardware und Software, Ventile, Schalter und Schaltungen für die vorstehend genannten Waren; Prüfstationen für Brennstoffzellen; Automatische Prüfstationen für Brennstoffzellen; Computersoftware zur Verwendung in Prüfstationen für Brennstoffzellen; Computersoftware für automatische Prüfstationen für Brennstoffzellen; Computersoftware für Wasserstoffprüfstationen; Brennstoffzellen; Brennstoffzellen-Stromsysteme; Brennstoffzellenstapel; Integrierte Brennstoffzellensysteme; Anoden, Sensorik-Geräte, Kathoden, Abscheider Membranen für Wasserstoffbrennstoffzellen; Wasserstoff-Stromspeichersysteme; Teile und Zubehör für alle vorgenannten Waren; Brennstoffzellenstapel, Sensoren und elektronische Steuerungen für Integrierte Brennstoffzellen-Energieerzeugungssysteme und -subsysteme; Sensoren, Hardware und Software zur Regelung des integrierten Wasserstofftreibstoffsystems in Antrieben für Luftfahrzeuge. Wasserstoffreinigungsgeräte; Gleichrichter-Tropfenabscheider; Teile und Bestandteile aller vorstehend genannten Waren; Luftfilter für Brennstoffzellensysteme. Betanken von Luftfahrzeugen mit Wasserstoff; Bau von Energieerzeugungsanlagen; Projektmanagement im Bauwesen [Bauaufsicht] im Bereich von Anlagen zur Energieerzeugung. Elektronische Übermittlung von Daten mit dem Ziel, das Treibstoffsystem und das Brennstoffzellensystem zu Regeln und die relevanten Daten an das Flugzeug, eine Bodenstation oder einen internen Speicher zu verteilen. Befüllen von Behältern zur Verwendung in Wasserstofftreibstoffsystemen für Luftfahrzeuge; Speicherung von Wasserstoff, beispielsweise mit einem integrierten Treibstoffsystem; Verteilung von Wasserstoff und Luft als Treibstoff für Brennstoffzellen; Verteilung von Fluiden zur Verteilung und Ableitung von Wärme; Stromversorgung durch Verteilung von Elektrizität; Verteilung von Energie; Information und Beratung in Bezug auf alles vorstehend Genannte. Stromerzeugung; Energieerzeugungsdienste; Kundenspezifische Fertigung von industriellen und kommerziellen Wasserstofftreibstoff- und -antriebssystemen; Kundenspezifische Fertigung von Brennstoffzellensystemen und Wasserstofftreibstoff- und -antriebssystemen; Erzeugung von Wasserstoff; Kundenspezifische Anfertigung von Brennstoffzellensystemen und Wasserstofftreibstoff- und -antriebssystemen für Dritte; Information und Beratung in Bezug auf alles vorstehend Genannte. Ingenieurtechnische Dienstleistungen auf dem Gebiet der Betankung, Speicherung und Verwendung von Wasserstoff als Treibstoff, der Wandlung von Wasserstoff zu Strom mit Brennstoffzellen und die Installation und Integration solcher Systeme einschließlich deren Regelung durch Hardware und Software; Beratung auf dem Gebiet Entwurf und Entwicklung von Prüfstationen für Brennstoffzellen, Brennstoffzellen, integrierten Wasserstofftreibstoff- und -antriebssystemen und Zusatzausrüstung; Entwurf von industriellen und kommerziellen Wasserstofftreibstoff- und -antriebssystemen; Technische Beratung, Forschung und Entwicklung und Prüfungsleistungen in Bezug auf Strom/Antriebsenergie aus Wasserstoff und mit Wasserstoff betriebene Erzeugnisse; Prüfleistungen in Bezug auf Brennstoffzellen, Brennstoffzellensysteme, [Luftfahrt-] Antriebssysteme und Wasserstoff; Entwurf, Prüfung von Wasserstofftreibstoff- und -antriebssystemen und Brennstoffzellen, Brennstoffzellensysteme, [Luftfahrt-] Antriebssysteme basierend auf Brennstoffzelltechnologien; Entwurf von alternativen Energiesystemen; Technische Beratung, ingenieurtechnische Dienstleistungen und Projektentwicklung im Bereich Wasserstofftreibstoff- und -antriebssystemen und Brennstoffzellen, Brennstoffzellensysteme, [Luftfahrt-] Antriebssysteme basierend auf Brennstoffzelltechnologien; Information und Beratung in Bezug auf alles vorstehend Genannte; Technisches Projektmanagement im Bereich Energieerzeugung.

Abstract

A geared turbofan engine includes a plurality of turbine stages, wherein for each stage (i) of the turbine, an inner radius Ri has a maximum deviation between +1.5% and −3% as compared to the average inner radius of the inner blade platforms of the plurality of stages. The engine further includes a fan, the fan coupled to the turbine stages via a gear.

IPC Classes  ?

• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan

Abstract

The invention relates to an aircraft fuel cell propulsion unit (10) comprising a fuel cell system (12) that includes at least one anode (14), at least one cathode (15) and a process gas device (17) for supplying fuel and ambient air to the anode (14) and the cathode (15) and evacuating spent process gases, further comprising a ram air duct (21) through which compressed ram air (22) flows, and a heat exchanger (20) which is located in the ram air duct (21) and is designed to give off heat generated by the fuel cell system (12) to the environment.

IPC Classes  ?

• H01M 8/04029 - Heat exchange using liquids
• H01M 8/04119 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants with simultaneous supply or evacuation of electrolyte; Humidifying or dehumidifying

Abstract

The invention relates to a braze alloy mix for application in a method for brazing a component that has a nickel-based superalloy as base material, wherein the braze alloy mix comprises the following powders in a predetermined mixing ratio: a powder of a first braze alloy, a powder of a second braze alloy, a powder of a third braze alloy, and a powder of an additive alloy.

IPC Classes  ?

• B23K 35/30 - Selection of soldering or welding materials proper with the principal constituent melting at less than 1550°C
• C22C 19/07 - Alloys based on nickel or cobalt based on cobalt
• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• B23K 35/02 - Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape
• B23K 1/00 - Soldering, e.g. brazing, or unsoldering

Abstract

A cooling system (10) for an aircraft is provided, in particular for cooling at least one element of an electric propulsion system (24) of the aircraft, the cooling system (10) being at least partially disposed within a wing (12) of the aircraft and including at least two heat exchangers (16, 42) interconnected via at least one cooling circuit (11), the first heat exchanger (16) being operatively connected to the at least one element to be cooled of the electric propulsion system (24), and the second heat exchanger (42) being disposed within at least one wing (12) and being operatively connected to an upper and/or lower wing shell (46, 48) of the wing (12). A method for cooling at least one element of an electric propulsion system (24) of an aircraft is also provided.

IPC Classes  ?

• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• B60L 58/33 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling fuel cells for controlling the temperature of fuel cells, e.g. by controlling the electric load by cooling
• H01M 8/04029 - Heat exchange using liquids

Abstract

The present invention relates to a propulsion system (1) for an aircraft (50), having a first propulsion unit (11) which has a first power generator (21) for outputting a first electric power (P1) and a first thrust unit (31) connected to the first power generator (21) to generate thrust from the first electric power (P1), and a second propulsion unit (12) which has a second power generator (22) for outputting a second electric power (P2) and a second thrust unit (32) connected to the second power generator (22) to generate thrust from the second electric power (P2), and a connecting device (40), which, in the event of a fault of the first propulsion unit (11), is designed to connect the first thrust unit (31) or the first power generator (21) to the second propulsion unit (12) for supply.

IPC Classes  ?

• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• B64D 27/02 - Aircraft characterised by the type or position of power plant

Abstract

The invention relates to a housing flange (1) for an electric motor housing (2) of an electric motor (3), in particular for an aircraft engine, the housing flange (1) comprising a forged and/or cast round base plate (4), the base plate (4) comprising a through-opening (5) in its centre for the passage of a shaft (6) of a rotor (8) of the electric motor (3). According to the invention, a housing coolant distribution body (10), which is additively manufactured at least in some regions, is located on a first base plate main surface (9) of the base plate (4), the housing coolant distribution body (10) being in the form of a hollow cylinder, the cylinder axis (11) of which is oriented so as to be centred with respect to the through-opening (5), and the housing coolant distribution body (10) comprising one or more coolant channels (16) for the passage of a coolant.

IPC Classes  ?

• B33Y 80/00 - Products made by additive manufacturing
• H02K 5/06 - Cast metal casings
• H02K 5/20 - Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
• H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
• H02K 15/14 - Casings; Enclosures; Supports
• H02K 1/20 - Stationary parts of the magnetic circuit with channels or ducts for flow of cooling medium

Abstract

A method for automatically generating an optimized maintenance plan for a fleet of aircraft engines, includes the steps of: acquiring input data on a plurality of engines and providing an existing initial maintenance plan or creating an initial maintenance plan based on the acquired input data. A total maintenance effort for the fleet resulting in an application of the initial maintenance plan is then determined. Next, the engines are sorted into a defined order according to at least one criterion and at least one optimization strategy or heuristic stored as an algorithm in a computer program is applied to each of the engines in the defined order. Next, an optimized maintenance plan for the engines or output data comprising an estimated total maintenance effort of the optimized maintenance plan is output.

IPC Classes  ?

• G06Q 10/20 - Administration of product repair or maintenance

Abstract

A rotor blade (20) for a rotor blade assembly (10) of a turbomachine (1) is provided, having an inner rotor blade platform (40) which extends axially from the rotor blade (20) with respect to a longitudinal turbomachine axis (2) and has two opposite circumferential end faces (41) and a free axial end (42) whose cross section is radially inwardly and radially outwardly bounded by circular arcs of two concentric circles. The inner rotor blade platform (40) has a cross section of connection (45) with the rotor blade (20) which is bounded radially inwardly by an inner connecting line (46) and radially outwardly by an outer connecting line (47). Each of the connecting lines (46, 47) has a central portion (61) having a convex curvature.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots

Abstract

The present invention relates to a fuel cell stack (1), having fuel cells (2) arranged successively in a stacking direction (3), an inner covering element (11) which follows the fuel cells (2) in the stacking direction (3), and an outer covering element (12) which follows the inner covering element (11) in the stacking direction (3) and holds the inner covering element and the fuel cells (2) together in a braced state, wherein the outer covering element (12) forms at least a first and a second spring element (15.1, 15.2) perpendicularly to the stacking direction (3), wherein each of the spring elements (15.1, 15.2) forms an arc profile (16.1, 16.2) which is convexly curved in the direction of the inner covering element (11), and the respective arc profile (16.1, 16.2) is separately suspended, and wherein the inner covering element (11) forms a respective receptacle (40.1, 40.2) for the spring elements (15.1, 15.2), each receptacle being concavely curved in the direction of the outer covering element (12) and accommodating the respective convexly curved arc profile (16.1, 16.2).

IPC Classes  ?

• H01M 8/2465 - Grouping of fuel cells, e.g. stacking of fuel cells - Details of groupings of fuel cells
• H01M 8/2475 - Enclosures, casings or containers of fuel cell stacks
• H01M 8/248 - Means for compression of the fuel cell stacks
• B64D 27/355 - using fuel cells

Abstract

The invention relates to a fuel cell stack (1) with fuel cells (2) arranged one after another in a stacking direction (3), a cover element (5) and a hydraulic compensation element (6), wherein the hydraulic compensation element (6) and the cover element (5) are arranged following the fuel cells (2) in the stacking direction (3), wherein the cover element (5) holds the fuel cells (2) together in a state (21) in which it is tensioned against the fuel cells (2), and is curved towards the fuel cells (2) in an untensioned state (20), and wherein the hydraulic compensation element (6) is/can be applied with a fluid (11) in order to adjust a pressing force (8) transferred to the fuel cells (2) in the tensioned state (21).

Abstract

The invention is directed to an engine that has a fan, a compressor with a high-pressure compressor, and a combustion chamber. The high-pressure compressor of the engine has a mean stage pressure ratio and an overall pressure ratio formed between the fan and the combustion chamber.

IPC Classes  ?

• F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages

Abstract

The invention relates to a compressor for an engine, wherein the compressor has compressor stages arranged in succession in a flow direction of the compressor and each compressor stage has a rotating blade cascade and a guide vane cascade arranged downstream of the rotating blade cascade and the rotating blade cascade and the guide vane cascade each have an aspect ratio.

IPC Classes  ?

• F04D 19/02 - Multi-stage pumps
• F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages

Abstract

A method (100) for operating an aircraft-engine turbomachine (1) having a compressor (3), through which a gas flow (6) passes in a flow direction, a combustion chamber (4), a turbine (5) and a heat exchanger (8) downstream of the turbine (5), wherein the heat exchanger (8) generates steam from water by means of energy from the gas flow (6) and the steam is fed, in particular together with fuel, into the gas flow (6) for burning in the combustion chamber (4).

IPC Classes  ?

• F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid

Abstract

The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) having a core flow channel (10), wherein a compressor (12), a combustion chamber (13), a first turbine, in particular a high-pressure turbine (14), for driving the compressor (12), and a second turbine, in particular a low-pressure turbine (15) are arranged in the core flow channel (10) in the flow direction, and comprising a water system (30) for providing water via recovery from an exhaust gas from the core flow channel (10).

IPC Classes  ?

• F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
• F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange

Abstract

The invention relates to a heat exchanger (10) for cooling a hot fluid, in particular an exhaust gas or a fuel-cell cooling fluid, by means of a cooling fluid which is at a lower temperature than the hot fluid and which has a high flow velocity, comprising a high-temperature grille (30) for guiding the hot fluid and a low-temperature grille (20) for guiding the cooling fluid. According to the invention, a heat exchanger which can improve a transfer of heat despite a high-velocity inflowing fluid and/or which can reduce the required installation space is created in that a diffuser region (24) for decelerating the cooling fluid is arranged in at least one first low-temperature channel (21), through which the cooling fluid flows, of the low-temperature grille (20), and in that the diffuser region (24) and a first high-temperature channel (31), through which the hot fluid flows, of the high-temperature grille (30) have at least one shared wall (40) for heat transfer.

IPC Classes  ?

• F28F 1/02 - Tubular elements of cross-section which is non-circular
• F28F 13/08 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
• F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
• F28F 9/02 - Header boxes; End plates

Abstract

A propulsion system (1) for an aircraft, comprising a gas turbine (2), with a main flow duct (10) and a bypass flow duct (20), wherein the gas turbine (2) has an outer housing (5) which surrounds the bypass flow duct (20) on the outside. The core flow of the gas turbine (2) is routed radially to the outside and at least in portions through the outer housing (5) or along the outer housing (5).

IPC Classes  ?

• F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange

Abstract

The invention relates to a propulsion system (1) for an aircraft, comprising a gas turbine (2) with a main flow channel (10) and a bypass flow channel (20), a water system (30) and a steam system (40), wherein the water system (30) comprises at least one water separation unit (31) and a condenser (21) with at least one condenser module (23), wherein the gas turbine (2) has a housing (5, 6), in particular an outer housing (5) bordering the bypass flow channel (20) on the outside, and/or an inner housing (6) comprising the main flow channel (10). A propulsion system, with a water and steam system that is better integrated into the gas turbine, is achieved in that the water separation unit (13) is arranged in and/or on the outer housing (5), in particular in the cowling, and/or the at least one condenser module (23) is arranged in the bypass flow channel (20) and has exhaust gas channels (26) which direct an exhaust gas from the main flow channel (10), via the the bypass flow channel (20) and in and/or through the outer housing (5).

IPC Classes  ?

• F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
• F02K 3/115 - Heating the by-pass flow by means of indirect heat exchange
• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan

Abstract

The invention relates to an exhaust gas treatment apparatus (1) for an aircraft engine (2), the exhaust gas treatment apparatus comprising an exhaust gas channel (7), through which an exhaust gas of the aircraft engine (2) can flow, a first cooling device (8) and a second cooling device (13) for cooling an exhaust gas flow (6) flowing through the exhaust gas channel (7), the second cooling device (13) being located downstream of the first cooling device (8) with respect to the exhaust gas flow (6). The invention also relates to a method for operating such a cooling device.

IPC Classes  ?

• F02C 7/16 - Cooling of plants characterised by cooling medium
• F01D 25/30 - Exhaust heads, chambers, or the like
• F01N 3/04 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust by means of liquids

Abstract

The invention is directed to a guide vane device for a guide vane adjustment of a turbomachine, comprising a guide vane, which has a shaft extending along an adjustment axis of the guide vane, as well as an adjusting lever, which forms a connecting element for connection to an outer end of the shaft, wherein, at its outer end, the shaft has a three-dimensional front surface with at least one beveled region, the connecting element surrounds, at least in sections, the outer end of the shaft in a sleeve-like manner and is joined to the outer end in a form-fitting manner, and the guide vane device forms an interference fit between the connecting element and the outer end of the shaft.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes

Abstract

An airfoil array segment for an airfoil array of a turbomachine including a platform having a platform surface and an upstream-side platform edge, as well as at least two airfoils, whose leading and trailing edges define an inter-airfoil strip, the platform surface having a trough with a bottom configured such that the bottom is a global minimum and a radial position of the trough decreases relative to a reference surface in the circumferential direction from a suction side of one of the airfoils toward the pressure side of the adjacent other airfoil toward the bottom and from there increases in the circumferential direction, at most up to the radial position of the reference surface, and a radial position of the trough decreasing relative to a reference surface axially in the downstream direction toward the bottom and from there increasing axially in the downstream direction, at most up to the radial position of the reference surface, and the platform surface reaching at most a radial position of the reference surface, the reference surface corresponding to an uncontoured platform surface.

IPC Classes  ?

• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

A heat engine, in particular an aircraft engine, having a first compressor for supplying a combustion chamber of the heat engine with air and a first turbine arranged downstream of the combustion chamber for driving the first compressor, wherein the heat engine also has at least one steam supply line for supplying steam from a steam source into the combustion chamber. The heat engine also has a steam supply device, which has a second compressor and is designed to compress the working gas further by the second compressor as a function of a mass flow conducted through the steam supply line, before the working gas flows into the combustion chamber.

IPC Classes  ?

• F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Abstract

The invention relates to a device and a method for cooling a heat exchanger of a fuel cell of a flight propulsion drive outside of a flight phase of an aircraft. The flight propulsion drive has an air line with at least one compressor for feeding compressed air for the operation of the fuel cell. A flow amplifier is arranged in the region of the heat exchanger, and is configured to guide air onto a cooling surface of the heat exchanger, whereby thermal energy is diverted from the cooling surface of the heat exchanger.

IPC Classes  ?

• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
• H01M 8/04007 - Auxiliary arrangements, e.g. for control of pressure or for circulation of fluids related to heat exchange
• H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly

Abstract

blade for a turbomachine is provided. The blade at its blade tip (4) includes blade tip armor (5), and an erosion protection layer (11) above the blade tip armor. For the blade, the erosion protection layer in the area of the blade tip has a layer thickness in the range of 5 µm to 100 µm, in particular 10 µm to 50 µm.

IPC Classes  ?

• C23C 14/06 - Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
• C25D 15/00 - Electrolytic or electrophoretic production of coatings containing embedded materials, e.g. particles, whiskers, wires
• C25D 3/12 - Electroplating; Baths therefor from solutions of nickel or cobalt
• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
• C23C 14/54 - Controlling or regulating the coating process

Abstract

The invention relates to a masking device (1) for producing a masking structure (2) on a turbomachine component (3) to be machined by means of a surface finishing method. The masking device (1) operates in an automated and adaptive manner and is configured to move at least one metering unit (8) of the masking device (1) along a predetermined masking zone of the component (3) by an application robot arm (14) of the masking device (1) in an application method step (S3), and thereby apply a first masking layer (37) of a masking agent (11) in the masking zone by means of the metering unit (8), and in a curing method step (S4) after completion of the application method step (S3), to irradiate the applied first masking layer at least in areas by an irradiation means of the masking device (1) in order to cure the masking agent (11) of the masking layer, and to repeat the application method step (S3) and the curing method step (S4) in order to produce further masking layers of the masking structure (2) until the masking structure (2) is completed.

IPC Classes  ?

• B05C 5/02 - Apparatus in which liquid or other fluent material is projected, poured or allowed to flow on to the surface of the work from an outlet device in contact, or almost in contact, with the work
• B05C 9/12 - Apparatus or plant for applying liquid or other fluent material to surfaces by means not covered by groups , or in which the means of applying the liquid or other fluent material is not important for applying liquid or other fluent material and performing an auxiliary operation the auxiliary operation being performed after the application
• B05B 12/20 - Masking elements, i.e. elements defining uncoated areas on an object to be coated
• B05B 13/04 - Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work the spray heads being moved during operation
• B05D 1/32 - Processes for applying liquids or other fluent materials using means for protecting parts of a surface not to be coated, e.g. using stencils, resists

Abstract

The present invention relates to an exhaust-gas treatment device for an aircraft engine, comprising an exhaust-gas channel, through which an exhaust gas of the aircraft engine flows, and a first cooling unit for cooling with ambient air, characterized by a second cooling unit, which is downstream of the first cooling unit with respect to an exhaust-gas flow in the exhaust-gas channel.

IPC Classes  ?

• F01N 3/02 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust
• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
• F02C 7/16 - Cooling of plants characterised by cooling medium

Abstract

A guide vane ring and/or a rotor blade ring for a low-pressure turbine of an aircraft gas turbine of a turbofan engine includes a plurality of airfoils disposed consecutively in a direction of rotation. The plurality of airfoils includes a first airfoil and a second airfoil adjacent to the first airfoil in the direction of rotation. The first and second airfoils are disposed relative to each other such that a ratio e/t, viewed in a conical section, results from a smallest free flow cross-section e taken on the pressure side of the first airfoil from its trailing edge to a suction side of the second airfoil, and a pitch t of the airfoils, such that e/t is less than 0.31, (e/t<0.31).

IPC Classes  ?

• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan

Abstract

The invention relates to a guide vane assembly for a turbomachine, comprising a guide vane, which has a guide vane airfoil; and a guide vane holder. The guide vane is mounted in the guide vane holder such that the guide vane can be moved about an axis of rotation. For this purpose, the guide vane has at least one axle element, which is inserted into the guide vane holder in such a way that an outer lateral surface of the axle element faces an inner lateral surface of the guide vane holder. A protective coating is applied to at least parts of the guide vane airfoil. A protective coating is applied to at least one of the lateral surfaces. The invention also relates to a compressor module, a turbomachine, and a method for producing a guide vane assembly.

IPC Classes  ?

• F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion

Abstract

The present invention relates to a method for testing a component by a penetrant test, in which a penetrant is introduced onto a surface of the component; at least one portion of the penetrant is removed from the surface by blasting the surface with a solid blasting material; the surface is optically detected after the blasting.

IPC Classes  ?

• G01N 21/91 - Investigating the presence of flaws, defects or contamination using penetration of dyes, e.g. fluorescent ink
• G01N 1/28 - Preparing specimens for investigation

Abstract

The invention relates to a machining machine (10) having at least one rotatable shaft (11), said machining machine comprising: an excitation device (13) having an actuator (14) which is designed to apply an impact excitation (α) to the rotating shaft (11); a detection device (21); an evaluation device (22); and a control device (20). According to the invention, the shaft (11) is rotated and an impact excitation (α) is applied to the rotating shaft (11) in order to generate a response vibration (γ) of the shaft (11).

IPC Classes  ?

• B23Q 17/00 - Arrangements for indicating or measuring on machine tools
• G01M 7/08 - Shock-testing

Abstract

An aircraft system includes, among other things, an aircraft and a gas turbine engine coupled to the aircraft. The gas turbine engine includes a propulsor section including a propulsor, a compressor section, a turbine section including a first turbine and a second turbine, and a gear reduction between the propulsor and the second turbine. The second turbine includes a number of turbine blades in each of a plurality of rows of the second turbine. The second turbine blades operating at least some of the time at a rotational speed. The number of blades and the rotational speed being such that the following formula holds true for a majority of the blade rows of the second turbine: 5500 Hz≤(number of blades×speed)/60 sec≤10000 Hz. The gas turbine engine is rated to produce 15,000 pounds of thrust or more.

IPC Classes  ?

• F04D 29/66 - Combating cavitation, whirls, noise, vibration, or the like; Balancing
• F02C 3/107 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
• F02K 3/04 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type
• G06F 30/17 - Mechanical parametric or variational design
• F01D 15/12 - Combinations with mechanical gearing
• F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
• F01D 5/14 - Form or construction
• F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
• F01D 5/06 - Blade-carrying members, e.g. rotors - Details thereof, e.g. shafts, shaft connections
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
• F04D 25/04 - Units comprising pumps and their driving means the pump being fluid-driven
• F04D 29/053 - Shafts

Abstract

The invention relates to a method for processing a workpiece by means of electrochemical machining, in which i) the workpiece is introduced into a working chamber and the working chamber is closed, ii) in the working chamber, in an electrolyte fluid, material is removed from the workpiece, wherein, in addition, before the working chamber is reopened and the workpiece is taken out of the working chamber, iii) the working chamber is supplied with a fluid containing iron(II) ions as a reducing agent.

IPC Classes  ?

• B23H 3/10 - Supply or regeneration of working media
• C25F 3/02 - Etching
• C02F 1/467 - Treatment of water, waste water, or sewage by electrochemical methods by electrolysis by electrochemical disinfection
• B23H 9/10 - Working turbine blades or nozzles

Abstract

The present invention relates to an aircraft comprising at least one wing, at least one flight propulsion drive, and a retainer, particularly an engine pylon, which interconnects the wing and the flight propulsion drive. The aircraft comprises at least one heat exchanger for cooling exhaust gas of the fight propulsion drive and/or at least one water removal channel having at least one removal apparatus for removing water from exhaust gas of the flight propulsion drive, especially after the exhaust gas has flowed through the heat exchanger. The removal apparatus is disposed on, more particularly in, the retainer or is connected to the wing by means of the retainer, and/or the flight propulsion drive is fastened to the retainer by means of at least one flight propulsion drive suspension means, and the heat exchanger is fastened, independently thereof, to the retainer by means of at least one heat exchanger suspension means.

IPC Classes  ?

• B64D 27/18 - Aircraft characterised by the type or position of power plant of jet type within, or attached to, wing
• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• B64D 33/10 - Radiator arrangement
• B64D 29/06 - Attaching of nacelles, fairings, or cowlings
• F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
• F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine

Abstract

The invention relates to a blisk segment for a gas turbine, comprising at least one first blade having an airfoil, a leading edge, a trailing edge, a blade root, a suction side and a pressure side, a pedestal, and a first fillet having a device for influencing crack growth. The robustness of the gas turbine is improved in accordance with the invention in that, at the leading edge of the first blade, at least on the first fillet, a first surface structure is arranged and interacts with the crack-influencing device for influencing crack growth and for flow influencing.

IPC Classes  ?

• F01D 5/34 - Rotor-blade aggregates of unitary construction

Abstract

The invention relates to a method for determining individual vectors for open-loop and/or closed-loop control of at least one energy beam of a layering apparatus, comprising at least the steps of: providing layer data characterizing at least one component layer of a component to be additively manufactured, on the basis of the layer data, determining individual vectors, according to which at least one energy beam is to be moved relative to a construction and joining zone of the layering apparatus in order to solidify a material powder selectively to the component layer, determining at least one node point of a plurality of individual vectors, and adapting at least one property of at least one individual vector of the at least one node point, the at least one property being selected from a group comprising spatial orientation, radiation sequence in relation to at least one other individual vector, and vector length.

IPC Classes  ?

• B22F 10/85 - Data acquisition or data processing for controlling or regulating additive manufacturing processes
• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• G05B 19/4099 - Surface or curve machining, making 3D objects, e.g. desktop manufacturing

Abstract

A guide vane for arrangement in a gas duct of a turbomachine, including a guide vane blade and an outer platform which, relative to a longitudinal axis of the turbomachine, is arranged radially on an outside on the guide vane blade. The outer platform delimits the gas duct with an inner wall surface radially to the outside. The inner wall surface has a curved profile with an inflection point when viewed in an axial section, the inner wall surface having a concave curvature in a first axial section which is upstream from the inflection point with respect to a flow through the gas duct, and a convex curvature in a second axial section which is arranged downstream from the inflection point with respect to the flow through the gas duct.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F01D 5/14 - Form or construction
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable

Abstract

The present invention relates to a lever for adjusting an adjustable vane of a turbomachine, wherein the lever has a fulcrum for the rotatable mounting of the lever about an axis of rotation, a first load arm with a first adjusting connection point for at least indirect connection to an adjustable vane and a first force arm with a first actuating connection point for connection to an adjusting device, wherein the lever further has a first strut, which connects the first adjusting connection point and the first actuating connection point to each other and thereby extends in an arc-shaped manner about the axis of rotation.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F01D 17/12 - Final actuators arranged in stator parts
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

The invention relates to a nickel alloy (1), in particular for producing a component (3) for a thermal gas turbine, characterised by the following mass fractions of an alloy composition: 10% inclusive to 15% inclusive of chromium; 14% inclusive to 20% inclusive of cobalt; 3% inclusive to 8% inclusive of molybdenum; 2% inclusive to 6% inclusive of tungsten; 0.5% inclusive to 3% inclusive of niobium; 3% inclusive to 6% inclusive of aluminium; 3% inclusive to 6% inclusive of titanium; 0.1% inclusive to 0.2% inclusive of hafnium; 2% inclusive to 4% inclusive of tantalum; 0.01% inclusive to 0.1% inclusive of carbon; 0.02% inclusive to 0.1% inclusive of boron; 0.05% inclusive to 0.2% inclusive of zirconium; the remainder being formed by nickel.

IPC Classes  ?

• B22F 1/00 - Metallic powder; Treatment of metallic powder, e.g. to facilitate working or to improve properties
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium

Abstract

Provided is a method for detecting defects, in particular cracks and/or pores, in a component, in particular in a component of a turbomachine, preferably in a component of an engine, the method including the following steps: applying penetrant to at least a sub-region of the component such that the penetrant penetrates into any defects, in particular cracks and/or pores, present in the component; cleaning the surface of the component of penetrant that has not penetrated into defects, in particular cracks and/or pores, of the component; capturing an image, in particular a complete image, of the component; inputting the captured image into a machine learning system trained to detect defects, in particular cracks and/or pores; and detecting defects, in particular cracks and/or pores, in the component by machine learning system on the basis of light emitted and/or reflected by the penetrant in the defects, in particular cracks and/or pores.

IPC Classes  ?

• G01N 21/91 - Investigating the presence of flaws, defects or contamination using penetration of dyes, e.g. fluorescent ink
• G06T 7/00 - Image analysis

Abstract

A rotor blade for a gas turbine, in particular an aircraft gas turbine, including a blade root, a blade neck that adjoins the blade root in the radial direction, an airfoil that adjoins the blade neck in the radial direction, a radially outer partition wall that forms a radially inner delimiting section of an annular space of a gas turbine, an axially front partition wall and an axially rear partition wall that are connected to the radially outer partition wall so that the partition walls surround the blade neck on three sides, the partition walls protruding beyond the blade neck in the circumferential direction. For placement in a blade root receptacle of a rotor disk, the rotor blade is provided with a blade root protective plate that is situated between the blade root and the rotor disk. The blade root protective plate includes at least one sealing section that extends in the axial direction from the front partition wall to the rear partition wall, and whose radial outer side is situated opposite from the radially outer partition wall when the blade root protective plate is situated at the blade root. One or multiple ribs are situated at the blade neck for supporting the sealing section and are integrally joined to the blade neck.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

A stator vane for a turbomachine, including an airfoil having a leading edge and a trailing edge, which are interconnected by a suction side and a pressure side, the airfoil extending substantially in a radial direction between an inner platform and an outer platform, wherein, when viewed in an axial direction of the turbomachine toward the trailing edge, the trailing edge extends so as to be inclined at a first angle to the pressure side radially on an outside in relation to the radial direction at a circumferential position at which the trailing edge meets the outer platform, and wherein the first angle between the trailing edge and a tangent to the outer platform at a transition from the outer platform to the trailing edge is between 72° and 84°.

IPC Classes  ?

• F01D 5/14 - Form or construction
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

The invention relates to a fuel treatment device (10) for a combustion system of a turbomachine, having a vapour line (13) conducting water vapour (W), a fuel line (14) and a fuel supply device (15) by means of which fuel (B) can be supplied to water vapour (W) flowing in the vapour line (13) in order to produce a vapour-fuel mixture (G). The invention also relates to a method for operating a combustion system of a turbomachine.

IPC Classes  ?

• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
• F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
• F23R 3/32 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular

Abstract

The present invention relates to a guide vane assembly for a turbomachine, having an adjustable vane, which can be adjusted in order to alter an angle of attack, and an adjusting element, by way of which the adjustable vane can be adjusted, wherein the adjustable vane and the adjusting element are connected to each other in a connecting region, and wherein the adjustable vane and the adjusting element adjoin each other in the connecting region at a break edge.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes

Abstract

The invention relates to a fuel cell apparatus (1) for a main drive system of an aircraft, comprising at least one fuel cell device (2), and an air supply device (3) which is designed to feed a fluid (4) to the at least one fuel cell device (2), the air supply device (3) having a compressor device (6) which is designed to compress the fluid (4) to a predetermined mass flow and/or pressure. According to the invention, the compressor device (6) comprises a guide device (8), the guide device (8) having at least one adjustable guide element (9) which is designed to provide an aerodynamic narrowest cross section (10) of a main flow path (11) through the compressor device (6). The air supply device (3) has a control device (12) which is designed to control the guide device (8) in order to set the at least one narrowest cross section (10).

IPC Classes  ?

• H01M 8/04111 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants using a compressor turbine assembly
• F04D 17/02 - Radial-flow pumps specially adapted for elastic fluids, e.g. centrifugal pumps; Helico-centrifugal pumps specially adapted for elastic fluids having non-centrifugal stages, e.g. centripetal
• F04D 17/10 - Centrifugal pumps for compressing or evacuating
• F04D 17/12 - Multi-stage pumps
• F04D 19/02 - Multi-stage pumps
• F04D 27/02 - Surge control
• F04D 29/46 - Fluid-guiding means, e.g. diffusers adjustable
• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable

Abstract

The present invention relates to a flow field plate (4) for a fuel cell (3), having a plate core (20) and a metallic base layer (25.1) that is arranged on the plate core (20) and covers same, wherein the plate core (20) is made of an aluminium material, and wherein the metallic base layer has a thickness of at least 2 μm.

IPC Classes  ?

• H01M 8/0206 - Metals or alloys
• H01M 8/0213 - Gas-impermeable carbon-containing materials
• H01M 8/0228 - Composites in the form of layered or coated products
• H01M 8/0258 - Collectors; Separators, e.g. bipolar separators; Interconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant
• H01M 8/0215 - Glass; Ceramic materials

Abstract

An adjustable guide vane for a compressor, in particular a high-pressure compressor, of a gas turbine, in particular an aircraft gas turbine is described, the vane comprising a radially outer bearing section, a radially inner bearing section, and a vane section, which extends in the radial direction between the outer bearing section and the inner bearing section, wherein the outer and the inner bearing sections are designed in such a way that the adjustable guide vane can be taken up rotatably about a vane axis in the compressor, and wherein the radially inner bearing section is configured like a journal (cone-shaped) and has a lateral surface that is formed circumferentially about the vane axis, the lateral surface being of convex shape. In this way, it is provided that the radius of curvature of the convex lateral surface is at least double the maximum diameter of the bearing section.

IPC Classes  ?

• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F04D 19/02 - Multi-stage pumps
• F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages

Abstract

A connecting structure (10) for load transfer, in particular in a gas turbine (1), including a strut (20) and at least one wall element (30) is provided. The strut (20) at one end is integrally joined to the wall element (30), and the strut (20) and the wall element (30) are enclosed by a fillet (40), at least in areas, and integrally joined to same. An elastic deformation of the involved elements of the structure during the load transfer and/or load absorption is improved in that a root section (50) that is formed by a ridge (56) and that extends from the strut (20) to the wall element (30) is situated on the fillet (40).

IPC Classes  ?

• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

The invention relates to a rotor for integration in a turbomachine, with a rotor base body, wherein, on the rotor base body in a rotor outer space of the rotor, at least one blade element or airfoil is mounted, wherein the rotor base body extends in an axial direction of the rotor and comprises a connecting section, which extends in an axial direction of the rotor for connection to at least one further rotor and separates the rotor outer space from a rotor inner space of the rotor, wherein the connecting section comprises, in the axial direction, at a front side, preferably in the axial direction at a downstream-lying front side, a balancing flange, wherein the balancing flange is configured for compensating an imbalance of the rotor and extends in the radial direction in the rotor outer space, at least in sections.

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors

Abstract

A method for checking at least one subregion of a component, in particular a component of a turbomachine, including at least the steps of a) providing a blank; b) producing at least the subregion from the blank by machining the blank using at least one tool and using at least one force sensor-to record at least one force curve of at least one force acting during machining on the at least one tool; c) checking whether there is at least one deviation-of the at least one force curve from at least one predetermined target curve-of the at least one force curve, the at least one deviation-characterizing at least one material defect-contained in an unmachined segment of the subregion. A checking device for checking at least a subregion of a component is also provided.

IPC Classes  ?

• B23Q 17/09 - Arrangements for indicating or measuring on machine tools for indicating or measuring cutting pressure or cutting-tool condition, e.g. cutting ability, load on tool
• G01N 3/40 - Investigating hardness or rebound hardness
• G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control (DNC), flexible manufacturing systems (FMS), integrated manufacturing systems (IMS), computer integrated manufacturing (CIM)

Abstract

A method for producing an impact-resistant component, in particular a component of a turbomachine, such as an aircraft engine, and a corresponding component. The component is produced at least partially by an additive manufacturing method from a powder material in such a way that the component is formed at least in a first region from a material with a first toughness and at least in a second region from a material with a second toughness, the second toughness being greater than the first toughness, and wherein the second region is formed, at least in a part of the component, as a continuous or interrupted layer, preferably parallel to the surface of the component, at a distance from the surface of the component.

IPC Classes  ?

• B22F 10/28 - Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
• B22F 3/24 - After-treatment of workpieces or articles
• C22C 14/00 - Alloys based on titanium
• C22C 21/00 - Alloys based on aluminium
• B22F 10/36 - Process control of energy beam parameters
• B22F 10/32 - Process control of the atmosphere, e.g. composition or pressure in a building chamber
• B22F 10/38 - Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures

Abstract

A method is provided including the steps: —first excitation of the object via a multifrequency signal; —detecting a first response signal of the object at one or multiple measuring points at the object; —transforming the first response signal from a time range into a frequency-dependent range; —selecting one or multiple frequencies, based on the frequency-dependent range; —second excitation of the object based on the selected frequencies; —detecting a second response signal of the object at one or multiple measuring points of the object; —ascertaining a mechanical parameter based on the second response signal.

IPC Classes  ?

• G01N 29/12 - Analysing solids by measuring frequency or resonance of acoustic waves
• F01D 5/34 - Rotor-blade aggregates of unitary construction
• G01H 9/00 - Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by using radiation-sensitive means, e.g. optical means
• G01M 13/00 - Testing of machine parts
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
• G01M 5/00 - Investigating the elasticity of structures, e.g. deflection of bridges or aircraft wings

Abstract

An intermediate duct (10) for disposition between an outlet of a low-pressure compressor and an inlet of a high-pressure compressor of a turbomachine, in particular of an aircraft engine is provided, the intermediate duct including an outer wall (2) and an inner wall (3) between which are disposed an optional exit stator ring (4) and at least one strut (12) extending radially with respect to a central axis of the intermediate duct (10). The intermediate duct (10) is at least partially manufactured by additive manufacturing. A method for manufacturing such an intermediate duct (10), and a turbomachine having such an intermediate duct (10) are also provided.

IPC Classes  ?

• F01D 9/06 - Fluid supply conduits to nozzles or the like

Abstract

A guide blade arrangement (20) for a turbomachine (1), including a guide blade airfoil (22) and a platform (21). The guide blade airfoil (22) is situated at a side (21.1) of the platform (21) facing the gas channel, an opposite side (21.2) of the platform (21) facing away from the gas channel being contoured at least in one area (30.1, 30.2) with elevations (25) and depressions (26) that follow one another in the circumferential direction (23) in relation to a longitudinal axis (2) of the turbomachine (1), and the elevations (25) and depressions (26) at the side (21.2) facing away from the gas channel being set via a platform thickness (31), taken radially in each case, that is variable in the circumferential direction (23) and that repeatedly increases and decreases with a continuous profile.

IPC Classes  ?

• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

The present invention relates to a method for testing a component, in particular an aircraft engine, comprising the steps of: determining (S40) a value of a first toleranced parameter (A1; A2) of the component; determining (S50) a value of a second toleranced parameter (E1; ...; E4) of the component; and classifying (S70) the component in a predefined quality class if this value pair lies outside of a predefined tolerance range, the upper and/or lower limit (G) of which for the second parameter depends on the first parameter, in particular linearly, in at least one first permissible value range (Ta1,1) of the first parameter.

IPC Classes  ?

• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

Abstract

Described is a heat-protection element (50) for a gas turbine (10), in particular an aircraft gas turbine, the heat-protection element (50) being adapted to at least partially surround a bearing chamber (60) of the gas turbine (10) and having at least one connecting portion (52) which is disposed in an axially forward region (VB) and connectable or connected by a material-to-material bond to a protective element (54) of a seal carrier, in particular a seal carrier with a carbon seal, at least one supporting portion (58) which is disposed in an axially central region (MB) and adapted to support the heat-protection element (50) radially on the bearing chamber (60), an end portion (64) which is disposed in an axially rearward region (HB) and forms a free end (66) of the heat-protection element (50) and which is configured such that the end portion surrounds (64) the bearing chamber (60) in a contactless manner.

IPC Classes  ?

• F01D 5/08 - Heating, heat-insulating, or cooling means

Abstract

Described is a rotor disk (40) for a compressor (29, 32) of a gas turbine, in particular an aircraft gas turbine (10), the rotor disk having a main body (42), at least one rotor arm (44) projecting from the main body (42) in the axial direction (AR), the rotor arm (44) having, in a sectional view taken in a sectional plane defined by the axial direction (AR) and the radial direction (RR) a beginning portion (44a) merging into the main body (42); an end (44e) portion remote from the main body (42) and forming a kind of free end in the axial direction (AR), the beginning portion (44a) and the end portion (44e) being interconnected by an intermediate portion (44z), characterized in that the intermediate portion (44z) is curved with at least one radius of curvature (Ri, Ra).

IPC Classes  ?

• F04D 29/38 - Blades
• B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type

Abstract

The invention relates to an airfoil as well as to a method for producing an airfoil for a turbomachine, comprising a leading edge and a trailing edge joined to each other by a suction side and a pressure side and which, in at least one region, extends in a curved manner from an airfoil root to an airfoil tip, wherein the airfoil tip has a squealer tip, which is arranged at the airfoil tip.

IPC Classes  ?

• F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator

Abstract

The invention relates to a compression system for a gas turbine, in particular for an aircraft gas turbine, wherein the compression system comprises a flow duct. The flow duct includes cross-sectional areas that are aligned perpendicular to the axial direction along the flow duct length and have the respective predetermined sizes, where the inlet cross-sectional area has a size that is 15.3 to 16.1 times a size of the outlet cross-sectional area, and/or a cross-sectional area arranged at a distance of 40% of the flow duct length from the inlet cross-sectional area has a size that is 5.0 to 5.2 times the size of the outlet cross-sectional area.

IPC Classes  ?

• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F04D 19/02 - Multi-stage pumps

Abstract

A blade has an internal blade profile, and a jet deflection portion adjoining the internal blade profile. Each blade profile of the jet deflection portion has a center of gravity. The centers of gravity are joined by a thread line, which is a space line, starting from the internal blade profile. A total deviation of the space line in relation to the reference line is described by an nth order polynomial based on radial distance from the blade profile to a reference point. The thread line is selected and designed such that a compressive stress is produced in the region of the leading edge of the blade during operation.

IPC Classes  ?

• F01D 5/14 - Form or construction

Abstract

A method (100) for classifying an etch indication (11) of a component (10), the method including the steps of: providing a captured image (13) of the at least one etch indication (11); detecting at least one criterion (15) of the etch indication (11) based on the captured image (13); comparing the determined criterion (15) to at least one criteria data set (16) of etch indications (11) that is stored in a database; and classifying the etch indication (11) into at least one predetermined defect class (D) based on the comparison.

IPC Classes  ?

• G06T 7/00 - Image analysis

Abstract

The invention relates to a method and to a device for determining how at least one engine module (15, 15a, 15b, 15c, 15d, 15e) impacts a deterioration in an engine performance, in particular for planning an engine maintenance. Firstly, at least one measurement value for at least one performance parameter of the at least one engine module (15, 15a, 15b, 15c, 15d, 15e) is recorded at a measurement time during a flight phase, as well as measurement values for flight parameters that characterise the engine load point at the measurement time. As a result of this, a change in at least one resulting module scaler (MS) relative to a default or model value of the module scaler (MS) is determined, wherein the at least one resulting module scaler (MS) is calculated based on a deviation of the at least one recorded measurement value for the at least one performance parameter from a default or model value of the at least one measurement value of the at least one performance parameter at an engine load point. The impact of the change of the at least one module scaler (MS) on the at least one predefined engine performance parameter (LP) is determined at the measurement time at a reference engine load point.

IPC Classes  ?

• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
• G07C 5/00 - Registering or indicating the working of vehicles

Abstract

The invention relates to a fuel cell (1) for a fuel cell stack (40) which has a first bipolar plate (11) and a catalyst membrane layer (2), the catalyst membrane layer (2) being subdivided into at least two segments (2.1-2.3), but the first bipolar plate (11) being formed continuously and extending beyond the at least two segments (2.1-2.3), thus the at least two segments (2.1-2.3) being electrically connected in parallel, and a first channel structure (21), which is intended to supply the catalyst membrane layer (2) with a reaction gas (35, 36), being subdivided into at least two segments congruently with the at least two segments (21.1-21.3) of the catalyst membrane layer.

IPC Classes  ?

• H01M 8/0258 - Collectors; Separators, e.g. bipolar separators; Interconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant
• H01M 8/0267 - Collectors; Separators, e.g. bipolar separators; Interconnectors having heating or cooling means, e.g. heaters or coolant flow channels
• H01M 8/0271 - Sealing or supporting means around electrodes, matrices or membranes
• H01M 8/2418 - Grouping by arranging unit cells in a plane
• H01M 8/249 - Grouping of fuel cells, e.g. stacking of fuel cells comprising two or more groupings of fuel cells, e.g. modular assemblies

Abstract

The present invention relates to a fuel cell stack (1), comprising: fuel cells (2) arranged successively in a stacking direction (5); a cover element (10) which follows the fuel cells (2) in the stacking direction (5) and holds them together; and a spring element (19) which is arranged between the fuel cells (2) and the cover element (10) in the stacking direction (5), wherein the spring element (19) is a constant force spring element (20).

IPC Classes  ?

• H01M 8/248 - Means for compression of the fuel cell stacks

Abstract

The invention relates to a rotor shaft (1) for an electric motor (2), in particular for an aircraft engine, wherein the rotor shaft (1) has a forged attachment flange (3), and the attachment flange (3) is designed to attach to another shaft (6) in order to transmit a force and/or a torque and comprises a first axial end (4) facing the other shaft (6) and a base (8) on a second axial end (7) opposite the first axial end (4). According to the invention, the rotor shaft (1) has a coolant distribution body (9) which is additively manufactured at least in some regions, wherein the additively manufactured coolant distribution body (9) is arranged on the base (9) of the forged attachment flange (3) in a radially centered manner, and the rotor shaft (1) has a rotor device (12), which radially surrounds the additively manufactured coolant distribution body (9) and is connected to the base (8) of the forged attachment flange (3) at least in a force-fitting manner.

IPC Classes  ?

• H02K 1/32 - Rotating parts of the magnetic circuit with channels or ducts for flow of cooling medium
• H02K 9/19 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil
• B33Y 80/00 - Products made by additive manufacturing
• H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
• H02K 1/30 - Means for mounting or fastening rotating magnetic parts on to, or to, the rotor structures using intermediate parts, e.g. spiders

Abstract

The present invention relates to an aircraft having at least one wing, on which at least one propulsion unit is arranged, comprising at least one heat engine, especially a gas turbine, as well as an exhaust gas passage for conducting exhaust gas of the heat engine into and inside the wing.

IPC Classes  ?

• B64D 27/12 - Aircraft characterised by the type or position of power plant of gas-turbine type within, or attached to, wing
• B64D 27/26 - Aircraft characterised by construction of power-plant mounting
• B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
• F01N 3/00 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust
• F01N 5/04 - Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy the devices using kinetic energy
• F01N 5/02 - Exhaust or silencing apparatus combined or associated with devices profiting by exhaust energy the devices using heat

Abstract

The invention relates to a guide vane assembly as well as to a method for mounting a guide vane assembly of a turbomachine, including a number of adjustable guide vanes, the guide vane platform of which has a guide vane journal that is mounted in a receiving opening of a housing of the turbomachine, wherein a guide vane head of the guide vane has a bearing pin, which is mounted on an inner ring arranged on a rotor of the turbomachine. In the method, a guide vane journal, which is arranged on a guide vane platform of a guide vane, is brought into a receiving opening of a housing, which is arranged radially with respect to a rotor axis of the turbomachine, and an inner ring is provided on a rotor of the turbomachine.

IPC Classes  ?

• F02C 9/20 - Control of working fluid flow by adjusting vanes
• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits

Abstract

A brush seal can be used for a gas turbine. The brush seal includes a support ring structure; and at least one bundle of bristles that is arranged in an axial direction on the support ring structure. The support ring structure has a basis portion arranged radially on the outside, and a supporting portion arranged radially on the inside. The supporting portion has a supporting surface that faces the bundle of bristles and supports the bundle of bristles in the axial direction. The supporting portion has a radially inner edge portion that faces a rotor portion of the gas turbine when the brush seal is in an assembled state. Starting from the radially inner edge portion, the supporting portion has a radial supporting-portion length together with a substantially constant axial supporting-portion width, the supporting-portion length being greater than the supporting-portion width by at least a factor of four.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings

Abstract

An adjustment lever adjusts a stator vane of a turbomachine. The adjustment lever has: a first connection site, of a plurality of connection sites, the first connection site being configured to join to an adjustment ring; a second connection site, of the connection sites, the second connection stie being configured to join to the stator vane; and a joining member arranged between the first connection site and the second connection site. The joining member is shaped having at least two struts which adjoin at least one of the connection sites.

IPC Classes  ?

• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits

Abstract

The invention relates to a fuel cell (1) having at least two bipolar plates (2) and at least one membrane-electrode arrangement (3) respectively arranged between two bipolar plates (2). Arranged between at least one bipolar plate (2) and a membrane-electrode arrangement (3) is a gas-diffusion layer (4), while at least one bipolar plate (2) has on the side facing the gas-diffusion layer (4) flow channels (4) for carrying a gas and/or a fluid, and the flow channels (5) are spaced apart from one another by webs (6). The invention also relates to a stack comprising two or more fuel cells (1).

IPC Classes  ?

• H01M 8/0232 - Metals or alloys
• H01M 8/0234 - Carbonaceous material
• H01M 8/026 - Collectors; Separators, e.g. bipolar separators; Interconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant characterised by grooves, e.g. their pitch or depth
• H01M 8/0258 - Collectors; Separators, e.g. bipolar separators; Interconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant
• H01M 8/0267 - Collectors; Separators, e.g. bipolar separators; Interconnectors having heating or cooling means, e.g. heaters or coolant flow channels
• H01M 8/1004 - Fuel cells with solid electrolytes characterised by membrane-electrode assemblies [MEA]
• H01M 8/24 - Grouping of fuel cells, e.g. stacking of fuel cells
• H01M 4/86 - Inert electrodes with catalytic activity, e.g. for fuel cells
• H01M 8/00 - Fuel cells; Manufacture thereof

Abstract

The present invention relates to a method for introducing a recess (3) into a workpiece (1), wherein the recess (3) is introduced by electrochemical removal by means of a processing cathode (2), wherein the removal exposes a flank (3.1) which bounds the recess (3) and extends from a first face (1.1) of the workpiece (1) in the direction of an opposite, second face (1.2) of the workpiece (1), wherein a protective anode (7.1, 7.2) is arranged on at least one of the faces (1.1, 1.2) during the removal, the protective anode being assigned to the flank (1.3) and lying against the at least one face (1.1, 1.2), in electrical contact with the workpiece (1), and wherein the protective anode (7.1, 7.2) is offset with respect to the flank (1.3) in the outward direction, that is to say away from the recess (3).

IPC Classes  ?

• B23H 3/04 - Electrodes specially adapted therefor or their manufacture
• B23H 9/10 - Working turbine blades or nozzles
• F01D 5/00 - Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
• B23H 9/00 - Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
• B23H 11/00 - Auxiliary apparatus or details, not otherwise provided for

Abstract

The invention relates to a method for detecting an anomaly in operating measurement values (3) of a turbomachine (1), in particular an aircraft turbine, comprising: recording operating measurement values (3) of respective operating parameters (4) of a turbomachine (1) several times during an operating period of the turbomachine (1) by means of sensors (2) of the turbomachine (1); determining quasi-stationary time periods (10) of the operating time by means of an analysis device (7); generating quasi-stationary operating data points (17) for the quasi-stationary time periods (10), the quasi-stationary operating data points (17) comprising averaged operating measurement values (14); determining respective expectation data points (20) which comprise respective operating expectation values (21) of the respective operating parameters (4); determining respective operating measurement value residues (23) of the respective operating parameters (4); checking the operating measurement value residues (23) of the respective quasi-stationary operating data points (17) for compliance with predetermined anomaly criteria (24B) with respect to predetermined nominal values (25) of the operating measurement value residues; and transmitting an anomaly indicator (26) comprising a violated anomaly criterion (27) of the anomaly criteria (24B) and the time (28) of the violation to a machine monitoring device (9).

IPC Classes  ?

• F01D 19/00 - Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines

Abstract

The invention relates to a rotor for a turbomachine, having at least one blade and having at least one rotor main part, which has at least one recess, in which a blade root of the least one blade is interlockingly received, wherein the blade root comprises at least one depression, in which at least one protrusion of the at least one rotor main part which protrusion delimits the at least one recess in regions is received, wherein the at least one depression is delimited by a first delimiting face on the blade root side and the at least one protrusion is delimited by a second delimiting face on the rotor main part side. At least the first delimiting face has at least one elevation which narrows a gap at least in regions, which extends between the first delimiting face and the second delimiting face.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages

Abstract

The invention relates to a monitoring system for a gas turbine, in particular for an aircraft engine. The monitoring system comprises at least one borescope device that is able to be mounted in a borescope opening of a gas turbine housing and has a housing, in which at least one optical sensor device for acquiring images of at least one inner region of the gas turbine is arranged, and an evaluation device that is able to be connected to the at least one borescope device in order to exchange data and is designed to inspect the at least one inner region for the presence of a fault on the basis of the at least one image acquired by way of the sensor device. The invention furthermore relates to a borescope device to an evaluation device and to a gas turbine.

IPC Classes  ?

• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
• G02B 23/24 - Instruments for viewing the inside of hollow bodies, e.g. fibrescopes

Abstract

A method for coating a component of an aircraft engine with a wear-resistant layer, wherein the component is first coated at least regionally with a nickel- or cobalt-based alloy and subsequently aluminized. Also disclosed is a method for producing a spray powder for producing a wear-resistant layer of a component of an aircraft engine.

IPC Classes  ?

• C23C 10/48 - Aluminising
• C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
• C22C 19/07 - Alloys based on nickel or cobalt based on cobalt
• C23C 10/04 - Diffusion into selected surface areas, e.g. using masks
• C23C 4/073 - Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements

Abstract

The invention relates to a seal carrier for a turbomachine, in particular a gas turbine, having a carrier base and at least one seal body, wherein the at least one seal body is connected to the carrier base, and wherein the at least one seal body is formed by a plurality of cavities arranged next to one another, in particular uniformly, in the peripheral direction and in the axial direction, wherein the cavities extend out from the carrier base in the radial direction and are delimited by a cavity wall. According to the invention, the seal body has a plurality of damping portions which are designed to locally damp or disrupt the flow of force in the seal body, wherein the carrier base is continuous in the region of the damping portions.

IPC Classes  ?

• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part

Abstract

The invention relates to a method for machining a workpiece (11) by means of an electrochemical machining process (51) in which material is removed from the workpiece (11) in an electrolyte liquid (15), wherein the electrolyte liquid (15) is then filtered (52) in a membrane filter system (20) which has a membrane (21) that undergoes a relative movement in the membrane filter system (20) during the filtering process, and the filtered electrolyte liquid (15) is reused for the electrochemical machining process (51).

IPC Classes  ?

• B23H 3/10 - Supply or regeneration of working media
• B01D 63/16 - Rotary, reciprocated or vibrated modules
• C25F 7/02 - Regeneration of process liquids

Abstract

A rotor assembly may be used in a gas turbine. The rotor assembly includes rotor segments arranged in succession in an axial direction and interconnected in the axial direction by a tie-rod, and a rotor segment disposed forwardly in the axial direction having a first contact surface and a rotor segment disposed rearwardly in the axial direction having a second contact surface. The first and second contact surfaces are at least partially in contact with each other, are substantially annular in shape, and extend in a radial direction and in a circumferential direction. The first contact surface and/or the second contact surface extend at least partially obliquely relative to the radial direction. An angle is formed between the first contact surface and the second contact surface when viewed in a sectional plane defined by the axial direction and the radial direction.

IPC Classes  ?

• F03D 5/06 - Other wind motors the wind-engaging parts swinging to-and-fro and not rotating
• F01D 5/06 - Blade-carrying members, e.g. rotors - Details thereof, e.g. shafts, shaft connections

Abstract

The invention relates to a method for operating a combustion system (2) of a turbomachine (1) for a flight propulsion system, comprising a compressor (11), a combustion chamber (4), a turbine (15), a heat exchanger (16, 17) arranged downstream of the turbine (15) and a fuel treatment system (3). According to the invention, steam is produced in the heat exchanger (17) and guided into a mixing chamber (33, 37) of the fuel treatment system (2), to which furthermore fuel is supplied. The invention further relates to a turbomachine (1) comprising a combustion system (2) in particular for using the method.

IPC Classes  ?

• F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Abstract

The present invention relates to an adjustment assembly for the adjustment of adjustable blades or vanes of a turbomachine, having an adjustment ring for coupling to the adjustable blades or vanes of a blade or vane ring and having an adjusting mechanism, which has a coupling rod for coupling to a further blade or vane ring as well as a lever and a push rod, wherein the lever is rotatably mounted at a pivot and has a load arm as well as a force arm, wherein the load arm of the lever is coupled to the push rod and its force arm is coupled to the coupling rod, on different sides of the lever, so that an offset of the coupling rod via the lever and the push rod is converted to a rotation of the adjustment ring around the ring axis thereof.

IPC Classes  ?

• F01D 7/00 - Rotors with blades adjustable in operation; Control thereof
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

The invention relates to a fuel cell device (1) which has a fuel cell stack (2). Respective end plates (5) are arranged on the opposite end surfaces (4) of the fuel cell stack (2), and the end plates (5) are connected by a tensioning device (17) of the fuel cell device (1) in order to clamp the fuel cell stack (2). According to the invention, at least one of the end plates (5) comprises a reinforcing device (8) which comprises at least one reinforcing element (7) with a fluid line (10).

IPC Classes  ?

• H01M 8/04089 - Arrangements for control of reactant parameters, e.g. pressure or concentration of gaseous reactants
• H01M 8/248 - Means for compression of the fuel cell stacks
• H01M 8/2484 - Grouping of fuel cells, e.g. stacking of fuel cells - Details of groupings of fuel cells characterised by external manifolds

Abstract

The invention relates to an airfoil for a compressor of a turbomachine, which extends starting from a blade root between a leading edge and a trailing edge to a blade tip, wherein the leading edge has a leading-edge thickness and the airfoil has a maximum profile thickness, the ratio of which to each other represents a relative leading-edge thickness, and the airfoil has a leading-edge wedge angle.

IPC Classes  ?

• F01D 5/14 - Form or construction

Abstract

The invention relates to a manufacturing device for the electrochemical machining of a component, in particular a turbine component, wherein the manufacturing device comprises at least one machining device, which is set up to remove material of the component in accordance with a predetermined electrochemical machining method. It is provided that the manufacturing device comprises at least one cleaning device, which is set up to spray jets of the electrolyte solution onto the component in accordance with a predetermined jet-spraying method in order to remove a residue layer formed on the component during the predetermined electrochemical machining method.

IPC Classes  ?

• B23H 3/10 - Supply or regeneration of working media
• B23H 9/10 - Working turbine blades or nozzles
• B23H 11/00 - Auxiliary apparatus or details, not otherwise provided for

Abstract

The disclosure is directed to a method comprising the steps: carrying out multiple measurements on a mechanical object, the measurements each differing by one or more parameters influencing the measurement; determining a spectrogram on the basis of the measurement data of the measurements and depending on a predefined parameter of the mechanical object; determining one or more excitations of the mechanical object; reproducing the excitations in the spectrogram.

IPC Classes  ?

• G01M 13/00 - Testing of machine parts
• G01M 15/12 - Testing internal-combustion engines by monitoring vibrations

Abstract

The invention relates to a machining apparatus for electrochemically removing component layers of a component, having at least one electrode, which is mounted so as to be movable along at least one infeed axis, and having at least one auxiliary electrode, which is mounted so as to be movable along an auxiliary infeed axis, wherein a gap for arranging the component for electrochemically removing the component layers extends between the at least one electrode and the at least one auxiliary electrode. At least the infeed axis and a longitudinal extension direction of the gap enclose an acute angle with each other. The machining apparatus comprises at least one oscillation device (40), which is set up at least to move the at least one electrode in an oscillating manner along the infeed axis and relative to the at least one auxiliary electrode.

IPC Classes  ?

• B23H 7/30 - Moving electrode in the feed direction
• B23H 3/10 - Supply or regeneration of working media

Abstract

The invention relates to an adjustable guide vane (1) for a gas turbine (2), more particularly an aircraft gas turbine (2), comprising a vane shaft (3), wherein the vane shaft (3) has a vane shaft screw thread (6) at least in a region of a radially outer vane shaft end (5). The adjustable guide vane (1) has a lever device (7), which is disposed on the vane shaft (3), and the vane shaft (3) runs through a level opening (8, 14, 23) in the lever device (7). According to the invention, an external screw thread radius (22) of the external screw thread of the vane shaft screw thread (6) corresponds to the radius (25) of the vane shaft (3), the vane shaft (3) has at least one longitudinal groove (16), which extends from the radially outer vane shaft end (5) and runs parallel to the adjustment axis (4) on the vane shaft (3) up to a longitudinal groove end (17) of the longitudinal groove (16), and the lever device (7) has at least one protrusion (18, 19), the protrusion (18, 19) being disposed in the longitudinal groove (16) and being seated at the longitudinal groove end (17) of the longitudinal groove (16).

IPC Classes  ?

• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F02C 9/22 - Control of working fluid flow by adjusting vanes by adjusting turbine vanes

Abstract

Blade root receptacle for receiving a blade root of a rotor blade of a turbomachine. The blade root receptacle, for radially bearing in a form-fitting manner on the blade root, has a supporting flank which, in terms of a rotation axis, at least in proportions faces radially inward, wherein the supporting flank is provided with a convexity which, when viewed in an axially perpendicular section, at least in portions has a convex shape and, also when viewed in an axially parallel section, at least in portions has a convex shape.

IPC Classes  ?

• F01D 5/30 - Fixing blades to rotors; Blade roots

Abstract

133), thus generating only a partial image (20.1-20.3) of the surface (21); - the imaging device (9) and the surface (21) are moved relative to each other such that different portions (31.1-31.3) of the surface (21) are captured over the course of time, thus generating different partial images (20.1-20.3), and wherein the partial images (20.1-20.3) are stitched (64) together to produce an image (40) of the surface (21).

IPC Classes  ?

• G06T 3/40 - Scaling of a whole image or part thereof
• G06T 7/00 - Image analysis

Abstract

The invention relates to a supply device (10) and to a method (100) for supplying an air bearing (11) by means of a fuel cell system (12), which comprises at least one anode (14) and at least one cathode (15) and a process gas device (17) for supplying the anode (14) and cathode (15) with fuel and ambient air and for discharging used process gases.

IPC Classes  ?

• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings
• F02C 7/06 - Arrangement of bearings; Lubricating
• F02C 6/00 - Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• F16C 29/02 - Sliding-contact bearings
• F16C 32/06 - Bearings not otherwise provided for with moving member supported by a fluid cushion formed, at least to a large extent, otherwise than by movement of the shaft, e.g. hydrostatic air-cushion bearings
• F16C 33/10 - Construction relative to lubrication

Abstract

The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, having a blade airfoil, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, the change in the stagger angle over the height does not decrease with increasing height at least over certain portions.

IPC Classes  ?

• F01D 5/14 - Form or construction

Abstract

The present invention relates to a rotor blade (20) for arrangement in a gas duct (2) of a turbomachine (1), having a rotor blade airfoil (23), which, viewed in a tangential section, has a blade airfoil profile (24) with a leading edge radius RVK and a rotor blade airfoil thickness d, wherein the blade airfoil profile (24) is thickened, at least in sections, specifically the blade airfoil thickness d is specified, in relation to the front edge radius RVK, such that (2d/Rvk2)−d≤5.5.

IPC Classes  ?

• F01D 5/14 - Form or construction

Abstract

A turbine module (2) for a turbomachine (1). The turbine module (2) includes a main channel (26) to guide a main flow (36) through the turbine module (2), a rotor blade (21) and a stator vane (22), the stator vane (22) including a stator airfoil (22) and a platform (23), with the stator airfoil (22) arranged downstream of the rotor blade (21) in the main channel (26), and a cavity (30) including an inlet (31) for injecting a part (36.2) of the main flow (36) into the cavity (30), an outlet (32) for a reinjection of the part (36.2) of the main flow (36) from the cavity (30) into the main channel (26), wherein the cavity (30) is arranged at an axial position of the stator vane (20) and is radially offset from the stator airfoil (22).

IPC Classes  ?

• F01D 17/10 - Final actuators
• F01D 11/14 - Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing

Abstract

The present invention relates to a rotating blade for a turbomachine, having a blade element and a shroud, wherein the shroud is profiled at a peripheral side, i.e., when observed in a tangential section, has a contact flank that is oriented axially, at least proportionally, and has a free flank that is also oriented axially, at least proportionally, and is in fact opposite the contact flank, wherein, when observed in the tangential section, an intermediate segment between the contact flank and the free flank has a first curvature in a first transition segment to the contact flank and has a second curvature in a second transition segment to the free flank, wherein the first curvature is greater than the second curvature.

IPC Classes  ?

• F01D 5/14 - Form or construction