An airfoil includes a high pressure surface and a low pressure surface that are connected at a leading edge and a trailing edge. The high pressure surface and the low pressure surface extend from a first end to a second end. A camber line extends between the leading edge and the trailing edge and a camber angle is defined as a plurality of camber-angle distributions that extend between the leading edge end and the trailing edge. The plurality of camber-angle distributions include a uniform portion that extends from the leading edge to a forced non-equilibrium boundary layer diffusion (FNBD) feature. The uniform portion includes a non-dimensionalized camber-angle unit that is constant the FNBD feature includes a rapidly increasing camber-angle that is 0.2 non-dimensional camber-angle units higher than the non-dimensionalized camber-angle of the uniform portion.
A method can comprise dividing a heat exchanger design into a plurality of modules, the plurality of modules arranged in a grid, each module in the plurality of modules including: a first fluid conduit defining an inlet, an outlet, and a heat-transfer surface, and a first flow direction, and a second fluid conduit defining a second inlet, a second outlet, a second heat-transfer surface, and a second flow direction, the second flow direction different from the first flow direction; and determining a heat-transfer augmenter arrangement for the first fluid conduit and the second fluid conduit of each module in the plurality of modules based on a stress threshold of the module in the plurality of modules.
An integrally bladed rotor for a gas turbine engine, including: a plurality of blades integrally formed with a hub as a single component, each of the plurality of blades having a blade body extending from the hub to an opposing blade tip surface along a longitudinal axis, each blade body having a pressure side and a suction side each extending between a leading edge and a trailing edge of the blade body; and each of the plurality of blades including a leading edge shield secured to the leading edge of the blade body.
A component for a gas turbine engine, including: at least one internal channel extending through a first portion of the component, the at least one internal channel having at least one inlet opening and at least one outlet opening each being in fluid communication with the at least one internal channel; a plurality of cooling features extending from a surface of the at least one internal channel; and at least one internal channel extending through a second portion of the component, the at least one internal channel extending through the second portion of the component is in fluid communication with the at least one internal channel extending through the first portion of the component, the second portion being located on top of the first portion, the at least one internal channel extending through the second portion of the component having a plurality of openings extending from the least one internal channel extending through the second portion of the component through the plurality of cooling features to an outer surface of the component.
A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.
A turbine engine assembly includes a turbine section including at plurality of turbine stages through which the gas flow expands to generate a mechanical power output. An inter-turbine burner between at least two of the plurality of turbine stages reheats the gas flow. A condenser extracts water from the gas flow exhausted from the turbine section, and an evaporator heats the water extracted by the condenser to generate a steam flow with the steam flow communicated to the inter-turbine burner and added to the gas flow expanded through the turbine section.
A gas turbine engine assembly including a tap that is at a location up stream of the combustor section for drawing a bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow and communicate the heated bleed airflow into the turbine section where it is expanded to drive the turbine section.
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F02G 5/00 - Profiting from waste heat of combustion engines, not otherwise provided for
F02K 3/02 - 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
Direct pin-fin cooling assemblies are disclosed for a high-power printed circuit boards (PCBs). The disclosure can solve the classical coldplate problem associated with liquid cooling of high-power PCBs namely: (1) Inhomogeneous cooling due to the calorimetric heating up of the coolant, (2) thermal interface material (TIM) related quality issues such as dry-out effects, (3) high cost due to complicated metal coldplate structure, and (4) low thermal conductivity due to multi-layer structure. This includes incorporating pin-fin direct cooling into high-power PCB structures without additional coldplate structure or TIM. In this approach, a TIM and a top plate of coldplate can be removed. Thus, the cooling performance can be improved because the thermal conductivity between a liquid coolant and a power device is increased.
A chemical vapor deposition system comprises a reactor including at least one wall extending between an inlet end and an outlet end, and an internal volume defined by the at least one wall, the inlet end, and the outlet end. The reactor further comprises a heat source in thermal communication with the internal volume, and a solid precursor container removably placed within the internal volume. The solid precursor container includes at least one internal cavity for holding an amount of the solid precursor, and an opening fluidly connecting the at least one internal cavity to the internal volume of the reactor. The solid precursor comprises at least one of aluminum, zirconium, hafnium, and a rare earth metallic element.
C23C 16/448 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the method of coating characterised by the method used for generating reactive gas streams, e.g. by evaporation or sublimation of precursor materials
A coating for an article includes a seal coat comprising self-healing particles disposed in a seal coat matrix and a bond coat disposed on the seal coat. The bond coat includes a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix. A coating for an article and a method of applying a coating to an article are also disclosed.
A system for deep rolling a fan blade including a shaft assembly disposed along a first axis; a hub connected to a distal end of the shaft assembly, the hub having an upper hub portion and a lower hub portion extending along a second axis, the second axis forming an angle relative to a first axis; a roller disk joined to the lower portion of the hub, the roller disk configured to contact a fan blade; a fixture supporting the fan blade; the fixture comprising a body supporting a pivot clamp attached to the body with a pivot; a support attached to the body, the support is configured to engage an airfoil portion of the fan blade; a receiver formed in the body for supporting a root of the fan blade; and a shoulder attached to the body configured to support a platform portion of the fan blade.
C22F 1/04 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
Various examples of methods and systems are provided for improved predictive analytics. In one example, a method of managing operation of an asset or group of assets of interest includes comparing a generated prediction with one or more prediction range associated with a risk profile assigned to an operational outcome of interest, presenting a notification to an operator in response to the comparison, and incorporating operator-generated input as updated source data for the generation of subsequent predictions. The operator-generated input can comprise an operator-defined selection such as, e.g.,.; acceptance of the notification, or rejection of the notification. The operator-generated input can provide real time or near real time information based upon context-specific knowledge that the operator holds that is substantially independent of historical source data.
An energy supply system includes an electrolysis system to perform electrolysis on a first source of water, and break the water into hydrogen and oxygen components. The hydrogen and oxygen components are supplied to a power generation system. The power generation system includes a combustor receiving the hydrogen and oxygen components and is operable to combust the hydrogen and oxygen components. The combustor also receives a source of steam. Products of combustion downstream of the combustor pass over a top turbine rotor, driving the top turbine rotor to rotate. A first generator generates electricity from the rotation of the top turbine rotor.
Baffles (126) for installation within airfoils include a baffle body (1004, 704, 804) defining a feed cavity (420) and extending between inner and outer diameter (316) ends. A forward standoff shelf (812) is formed along an exterior surface of the baffle (126, 302) and defined by a depression, bend, or channel in a material of the baffle body (1004, 704, 804) extending between the inner and outer diameter (316) ends. The forward standoff shelf (812) is configured to engage with a forward rail (502) of the airfoil body (402, 702, 704, 802), and an aft standoff shelf (814) is formed along an exterior surface of the baffle body (1004, 704, 804) and configured to engage with an aft rail (504) of the airfoil body (402, 702, 704, 802). A surface of the baffle body (1004, 704, 804) between the forward standoff shelf (812) and the aft standoff shelf (814) defines a side channel surface extending in a radial direction along the baffle body (1004, 704, 804) between the outer diameter end (430, 506, 706, 914) and the inner diameter end (432, 508, 708, 916).
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix; a topcoat; and a porous interlayer disposed between the topcoat and the bond coat. The porous interlayer has a porosity that is greater than a porosity of the topcoat. A slurry composition for applying an interlayer to an article and method of applying a top coat to an article are also disclosed.
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix. At least about 10 % of the gettering particles are in a crystalline phase. The article also includes a top coat. An article is also disclosed.
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
C04B 35/14 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silica
C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C04B 41/50 - Coating or impregnating with inorganic materials
An article according to an exemplary embodiment of this disclosure, among other possible things includes a substrate and a barrier layer on the substrate. The barrier layer includes a bond coat comprising a matrix, diffusive particles disposed in the matrix, and gettering particles disposed in the matrix; and a topcoat including a constituent that is reactive with calcium-magnesium-alumino-silicate (CMAS). An article and a method applying a calciummagnesium- alumino-silicate (CMAS)-resistant topcoat are also disclosed.
A bearing compartment seal for a gas turbine engine includes a seal ring that defines an axis and has a radially inward facing sealing surface. A seal runner is configured to rotate relative to the seal ring. The seal runner has a runner surface facing the radially inward facing sealing surface. A plurality of grooves are spaced circumferentially along the runner surface. The plurality of grooves have a length in an axial direction that is at least 50% of an axial length of the runner surface.
A gas turbine engine has a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction, and includes a lubricant pump to supply an air/oil mixture to an inlet of a deaerator. The deaerator includes a separator for separating oil and air, delivering separated air to an air outlet, and delivering separated oil back into an oil tank. The separated oil is first delivered into a pipe outwardly of the oil tank, and then into a location beneath a minimum oil level in the tank. Air within the oil tank moves outwardly through an air exit into the deaerator. A method of designing a gas turbine engine is also disclosed.
A gas turbine engine article includes a silicon-containing ceramic wall that has an external combustion gaspath side and an internal side that borders a cooling air cavity. The external combustion gaspath side has an associated combustion gas flow direction there along. An array of cooling holes extends through the silicon-containing ceramic wall and connects the internal side with the external combustion gaspath side. The cooling holes are oriented to discharge cooling air to the external gaspath side in a direction counter to the combustion gas flow direction.
A redox flow battery includes a cell that has first and second electrodes and an ion-exchange layer there between, first and second circulation loops that are fluidly connected with, respectively, the first and second electrodes, first and second electrolyte storage tanks in, respectively, the first and second circulation loops, first and second electrolytes contained in, respectively, the first and second circulation loops, and a Raman spectrometer on at least one of the first or second circulation loops for determining a state-of-charge of at least one of the first or second electrolytes. The Raman spectrometer includes a laser source that is rated to emit a laser of a wavelength of 694 nanometers to 1444 nanometers.
H01M 8/18 - Regenerative fuel cells, e.g. redox flow batteries or secondary fuel cells
G01R 31/382 - Arrangements for monitoring battery or accumulator variables, e.g. SoC
G01R 31/378 - Arrangements for testing, measuring or monitoring the electrical condition of accumulators or electric batteries, e.g. capacity or state of charge [SoC] specially adapted for the type of battery or accumulator
A redox flow battery includes a cell that has first and second electrodes and an ion-exchange layer there between, first and second circulation loops that are fluidly connected with, respectively, the first and second electrodes, first and second electrolyte storage tanks in, respectively, the first and second circulation loops, first and second electrolytes contained in, respectively, the first and second circulation loops, and a Raman spectrometer on at least one of the first or second circulation loops for determining a state-of-charge of at least one of the first or second electrolytes. The Raman spectrometer includes a laser source that is rated to emit a laser of a wavelength of 694 nanometers to 1444 nanometers.
Aircraft engines and methods of operation include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section. A core condenser is arranged downstream of the turbine section of the core assembly along the core flow path, the core condenser being configured to condense water from the core flow path. A refrigeration system is operably coupled to the core condenser and configured to direct a cold stream flow path into thermal interaction with the core flow path at the core condenser and configured to control a delta temperature at which heat exchange occurs between the core flow path and the cold stream flow path.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/141 - Cooling of plants of fluids in the plant of working fluid
F02C 7/16 - Cooling of plants characterised by cooling medium
F02C 7/224 - Heating fuel before feeding to the burner
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
A method of damping vibrations in a seal includes inserting a first wave spring between a first beam and a second beam of the seal. The seal can be for a gas turbine engine and can include a full hoop outer ring, a shoe coupled to the full hoop outer ring via the first beam (e.g., an outer beam) and the second beam (e.g., an inner beam), and the first wave spring in contact with the first beam and the second beam.
F16F 15/06 - Suppression of vibrations of non-rotating, e.g. reciprocating, systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating system using elastic means with metal springs
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.
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
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
Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to engage with the baffle and define radially extending channels therebetween. First and second forward radially extending rails are segmented in the radial direction and a showerhead radial channel is defined along the leading edge. Pressure and suction side radial flow channels are defined between an interior surface of the airfoil body, an exterior surface of the baffle, and radially extending rails. An aft channel is defined between an interior surface of the airfoil body along pressure and suction side walls, an interior rib, exterior surfaces of the baffle, and the radially extending rails.
Vane assemblies for gas turbine engines are described. The vane assemblies 400 include a platform 404 having an interior platform surface, a forward rail 420, and an aft rail 422 defining a plenum 424. An airfoil 402 extends radially inward from the platform on a side opposite the forward and aft rails and includes a leading edge cavity 412 that is open at the platform. A platform feed structure 426 is arranged on the platform about the leading edge cavity 412 and in the plenum 424 and defines a fluid path through the forward rail 420 and into the leading edge cavity 412. A cover plate 726 is arranged on a top surface of the platform feed structure 426 and configured to fluidly separate the plenum of the platform from the leading edge cavity and define a turning plenum. The cover plate 726 defines a turning contour surface that is shaped to turn an airflow from an axial flow direction to a radial flow direction.
Vane assemblies for gas turbine engines are described. The vane assemblies 400 include a platform 404 having an interior platform surface, a forward rail 420, and an aft rail 422, wherein the interior platform surface, the forward rail, and the aft rail define a plenum 424, an airfoil 402 extending radially inward from the platform on a side opposite the forward and aft rails, the airfoil having a leading edge cavity 412 and a baffle 416 installed within the leading edge cavity, and a platform feed structure 426 arranged on the platform 404 in the plenum 424 and defining a fluid path through the forward rail 420 and into the baffle 416 of the leading edge cavity 412.
Aircraft propulsion systems and aircraft are described. The aircraft propulsion systems include aircraft systems having at least one hydrogen tank and an aircraft-systems heat exchanger and engine systems having at least a main engine core, a high pressure pump, a hydrogen-air heat exchanger, and an expander, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section. Hydrogen is supplied from the at least one hydrogen tank through a hydrogen flow path, passing through the aircraft-systems heat exchanger, the high pressure pump, the hydrogen-air heat exchanger, and the expander, prior to being injected into the burner for combustion.
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/224 - Heating fuel before feeding to the burner
An apparatus has: a first member (120); a shaft (40; 50) rotatable relative to the first member about an axis; and a seal system (100). The seal system has a seal carrier (150) having: an axially-extending wall (156) having an inner diameter (ID) surface (160); and a radially-extending wall (154) having a first surface (158). A seal (102) is carried by the first member and has: an outer diameter (OD) surface (206); and a seal face (106). A seat (104) is carried by the shaft and has a seat face (108) in sliding sealing engagement with the seal face. One or more springs (132) bias the seal carrier relative to the first member so as to bias the seal face against the seat face. A key (240; 280; 300; 338) spans an interface between the seal carrier and the seal.
A method for producing a ceramic matrix composite component is disclosed. The method includes providing a plurality of first ceramic fiber plies including a plurality of interconnected tows and a plurality of first pores positioned between adjacent tows. The method includes applying a plurality of first ceramic particles within the plurality of first pores. Next, the method includes applying a plurality of second ceramic fiber plies onto an outer surface of the plurality of first ceramic fiber plies. The second ceramic fiber plies include a plurality of interconnected tows and a plurality of second pores positioned between adjacent tows. The method then includes applying a plurality of second ceramic particles within the plurality of second pores. Further, the plurality of second ceramic particles are larger than the plurality of first ceramic particles. Lastly, the method includes densifying the ceramic matrix composite preform to form the ceramic matrix composite component.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
Disclosed herein is a composite co-fiber comprising a plurality of ceramic tows; one or more sacrificial yarns; where the sacrificial yarns are operative to undergo dissolution, decomposition or melting upon being subjected to an elevated temperature; and wherein the sacrificial yarns leave open spaces in the co-fiber upon being subjected to decomposition, dissolution or melting.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 35/565 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides based on silicon carbide
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C04B 38/06 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof by burning-out added substances
C22C 49/02 - Alloys containing metallic or non-metallic fibres or filaments characterised by the matrix material
C22C 49/14 - Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
33.
POLYMER YARNS FOR FABRIC STABILITY AND UNIFORMITY, PLIES MANUFACTURED THEREFROM AND ARTICLES COMPRISING THE SAME
Disclosed herein is a composite ply comprising fill and warp tows; or optional axial and bias tows; wherein one or more of the fill tows and/or the warp tows or wherein one or more of the optional axial and/or bias tows comprise a polymer yarn while the remaining portion of the fill tows and/or the warp tows or the remaining portion of the bias and/or optional axial tows comprise the polymer yarn; and wherein the polymer yarn is melted to bond to the fill or warp tows to prevent removal from the ply.
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 35/622 - Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
C04B 35/01 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides
C04B 35/515 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides
34.
SACRIFICAL YARN FILAMENT FOR USE IN CERAMIC MATRIX COMPOSITES AND METHODS OF MANUFACTURE THEREOF
Disclosed herein is a composite tow comprising a plurality of ceramic filaments; one or more sacrificial yam filaments; where the sacrificial yarn filaments are operative to undergo decomposition or melting upon being subjected to an elevated temperature; and wherein the sacrificial yarn filaments leave open spaces in the tow upon being subjected to decomposition, dissolution or melting; where the filaments have an average filament diameter of 5 to 15 micrometers.
Disclosed herein is a ceramic matrix composite comprising a preform comprising a plurality of plies; a ceramic matrix encompassing the plies and distributed through the plies; and thermally conducting particles distributed through the ceramic matrix. Disclosed herein is a method comprising distributing thermally conducting particles between plies in a preform; infiltrating chemical vapors of a ceramic precursor into the plies; and reacting the ceramic precursor to form a matrix.
B05D 3/10 - Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by other chemical means
B23B 7/02 - Automatic or semi-automatic machines for turning of stock
37 - Construction and mining; installation and repair services
Goods & Services
Maintenance and repair of aircraft, satellite, and weapon systems and components thereof; Information with relation to aircraft repair and maintenance; Aerospace vehicle maintenance, repair and overhaul, including parts and components thereof.
42 - Scientific, technological and industrial services, research and design
Goods & Services
Research, development, design, and testing services relating to aerospace including aeronautics systems and vehicles, electronic systems, information systems, energy systems, materials technology, environmental enhancement, satellite and weapons technology; Technology consultation and research in the field of aerospace engineering; Engineering and computer programming services for aircraft and aerospace vehicles, parts, and components; Aircraft product development, including parts and components thereof.
38.
METHOD FOR MACHINING CERAMIC WORKPIECE WITH COMPOSITE VIBRATION
A method for machining a ceramic workpiece includes providing a sonotrode that has a transducer and a horn arranged along an axis, and the horn has helical slots and terminates at a tip, bringing the tip into proximity of the ceramic workpiece and providing an abrasive media to a work zone around the tip, using the transducer to produce ultrasonic vibration that axially propagates down the horn and causes axial vibration at the tip, and the helical slots convert a portion of the axial vibration to torsional vibration at the tip, and the axial vibration and the torsional vibration causing the abrasive media to abrade the ceramic workpiece in the work zone and thereby remove a localized portion of the ceramic workpiece.
B06B 3/04 - Processes or apparatus specially adapted for transmitting mechanical vibrations of infrasonic, sonic or ultrasonic frequency involving focusing or reflecting
In a redox flow battery (RFB), the base solvent of the electrolytes tends to migrate across the barrier layer from one electrode toward the other. This can result in a volume and concentration imbalance between the electrolytes that is detrimental to battery efficiency and capacity. Compatible electrolytes can be mixed to rebalance the system, but for incompatible electrolytes mixing is not a viable option. To this end, the RFB herein includes a separator that recovers base solvent from the vapor phase of one of the electrolytes and returns the recovered base solvent to the other electrolyte to thereby reverse the imbalance.
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
41.
CELL FOR ELECTROCHEMICALLY DETERMINING ACTIVE SPECIES CONCENTRATIONS IN REDOX FLOW BATTERIES
A redox flow battery system with a redox flow battery includes a redox flow cell, and a supply/storage system external of the redox flow cell. The supply/storage system includes first and second electrolytes for circulation through the redox flow cell. At least the first electrolyte is a liquid electrolyte that has electrochemically active species with multiple, reversible oxidation states. A secondary cell is fluidly connected with the first electrolyte and is operable to monitor concentration of one or more of the electrochemically active species. The secondary cell includes a counter electrode, a working microelectrode, and an ionically conductive path formed by the first electrolyte between the counter electrode and the working microelectrode.
Disclosed is a coated composite comprising a seal coat disposed on a composite material wherein the seal coat comprises protective particles and a matrix.
A turbine engine system includes an aircraft systems including at least one hydrogen fuel tank, engine systems comprising a compressor section, a combustor section having a burner, and a turbine section, and a hydrogen fuel flow supply line configured to supply hydrogen fuel from the at least one hydrogen fuel tank into the burner for combustion. The turbine engine system has a bypass ratio between 5 to 20.
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
F02C 3/22 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being gaseous at standard temperature and pressure
F02C 7/16 - Cooling of plants characterised by cooling medium
A method is provided for treating a fuel system of a turbine engine. During this method, a treatment system is connected to the turbine engine. Preservation fluid is drawn out of the fuel system using the treatment system.
F02M 63/00 - SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF - Details, component parts or accessories of fuel-injection apparatus, not provided for in, or of interest apart from, the apparatus of groups or
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
F01D 25/32 - Collecting of condensation water; Drainage
A preform comprising a first sub-laminate comprising a plurality of layers and a second sub-laminate comprising a plurality of layers. The first sub-laminate comprises a first unit cell comprising a first volume fraction of tows, where the first volume fraction of tows comprise first tows having a first tow spacing between successive first tows. The second sub-laminate comprises a second unit cell comprising a second volume fraction of tows, where the second volume fraction of tows comprise second tows having a second tow spacing between successive second tows. The first volume fraction of tows in the first unit cell is equal to the second volume fraction of tows in the second unit cell. The second tow spacing is less than the first tow spacing.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 19/06 - Layered products essentially comprising natural mineral fibres or particles, e.g. asbestos, mica next to a fibrous or filamentary layer
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
A ceramic matrix composite laminate comprises a ceramic matrix that encapsulates a plurality of layers. Each layer comprises fibers. Each layer comprises a plurality of fill fibers and a plurality of warp fibers or a plurality of bias fibers. The outermost layer contains a different concentration of fibers per unit volume than a layer located near an interior of the ceramic matrix composite laminate. A gradient in the number of fibers exists between the outermost layer and the layer located at the interior of the ceramic matrix composite laminate, or a combination thereof. A combined ceramic matrix composite comprises a plurality of composite laminates; wherein each laminate has a different fiber concentration gradient from another laminate that it is in contact with.
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 19/06 - Layered products essentially comprising natural mineral fibres or particles, e.g. asbestos, mica next to a fibrous or filamentary layer
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 38/00 - Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool, a high speed spool, and a combustor; a lubrication circuit comprising a bearing compartment, a supply pump, and a scavenger pump; an electric motor configured to augment rotational power of the low speed spool or the high speed spool; and a controller operable to: control the electric motor based upon a pressure differential between an interior of the bearing compartment and an exterior of the bearing compartment and to drive rotation of the low speed spool and/or the high speed spool via the electric motor responsive to a thrust command while fuel flow to the combustor is inhibited.
A system and method for automatically assessing pilot readiness via a plurality of biometric sensors includes continuously receiving biometric data including vision-based data; the biometric vision-based data is compared to a task specific set of movements and facial expressions as defined by known anchor points. A deviation is calculated based on the vision-based data and task specific set of movements and expressions, and the deviation is compared to an acceptable threshold for pilot readiness. Other biometric data may be included to refine the readiness assessment.
A61B 5/308 - Input circuits therefor specially adapted for particular uses for electrocardiography [ECG]
A61B 5/31 - Input circuits therefor specially adapted for particular uses for electroencephalography [EEG]
A61B 5/00 - Measuring for diagnostic purposes ; Identification of persons
G10L 13/02 - Methods for producing synthetic speech; Speech synthesisers
G10L 25/57 - Speech or voice analysis techniques not restricted to a single one of groups specially adapted for particular use for comparison or discrimination for processing of video signals
G06V 20/40 - Scenes; Scene-specific elements in video content
G06V 20/59 - Context or environment of the image inside of a vehicle, e.g. relating to seat occupancy, driver state or inner lighting conditions
G06V 40/18 - Eye characteristics, e.g. of the iris
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
49.
ENVIRONMENTAL BARRIER COATING AND METHOD OF FORMING THE SAME
A method of applying a coating to a substrate includes forming a slurry by mixing elemental precursors of gettering particles, diffusive particles, matrix material, and a carrier fluid; applying the slurry to a substrate; and sintering the slurry to form a composite material. The sintering causes the elemental precursors to react with one another to form gettering particles. An article is also disclosed.
C23C 16/22 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition (CVD) processes characterised by the deposition of inorganic material, other than metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
A redox flow battery includes a redox flow cell and a supply and storage system external of the redox flow cell. The supply and storage system includes first and second electrolytes for circulation through the redox flow cell. The first electrolyte is a liquid electrolyte having electrochemically active manganese species with multiple, reversible oxidation states in the redox flow cell. The electrochemically active manganese species may undergo reactions that cause precipitation of manganese oxide solids. The first electrolyte includes an inhibitor that limits the self-discharge reactions. The inhibitor includes an oxoanion compound.
A redox flow battery includes a redox flow cell and a supply and storage system external of the redox flow cell. The supply and storage system includes first and second electrolytes for circulation through the redox flow cell. The first electrolyte is a liquid electrolyte having electrochemically active manganese species with multiple, reversible oxidation states in the redox flow cell. The electrochemically active manganese species may undergo reactions that cause precipitation of manganese oxide solids. The first electrolyte includes an inhibitor that limits the self-discharge reactions. The inhibitor includes an oxoanion compound.
A method for configuring a fixture for use in machining of sequential parts via a machine tool, for a planned machining movement of the machining element, uses a model of the part and fixture. Respective reaction forces at the plurality of part contact references are computed. Responsive to computation of a negative reaction force at a said part contact reference, a modification is made to a machining parameter.
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)
In a method for forming an abradable material (36), the abradable material has at least 20% by volume rutile titania (44) and hBN (46). The method includes: blending a first titania powder having an oxygen debit of at least 5.0% with a second titania powder having an oxygen debit, if any, of less than 1.0%. The blend is thermal sprayed. The sprayed blend is then oxidized.
C04B 35/46 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on titanium oxides or titanates
C04B 35/20 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in magnesium oxide
C04B 35/22 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in calcium oxide
C04B 35/462 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on titanium oxides or titanates based on titanates
C04B 35/583 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides based on boron nitride
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
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
Disclosed is a heat exchanger having: an inlet manifold configured to receive a cooling fluid; a reservoir; first and second condenser arms connected between and that respectively fluidly couple the inlet manifold to the reservoir, so that fluid received at the inlet manifold travels from the inlet manifold into the reservoir; and an outlet pump having a pump inlet port coupled to the reservoir and having a pump outlet port, wherein the inlet manifold, the reservoir, the first and second condensers, in combination, form a continuous shape.
F28D 7/00 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
55.
HEADER GUIDING FLUID FLOW TO AND FROM COOLING CHANNELS IN A HIGH DENSITY MOTOR
A header for an electric machine that include a stator core and one or more windings that include coolant passages formed therein. The header includes an inlet to receive a coolant, an outlet though which the coolant exits the header, an inlet plenum fluidly connected to the inlet, and an outlet plenum fluidly separated from the inlet plenum and fluidly connected to the outlet. The inlet and outlet plenums each have a varying cross section that varies from a top of the header as compared to a bottom of the header.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
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
A stator includes a stator hub, a plurality of stator teeth extending from stator hub that define a stator slot and at least one winding disposed in the stator slot, the winding including a cooling passage formed therein through. The cooling passage is connected to an inlet plenum and an outlet plenum. The stator can also include coil separators that include cooling passages.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 3/34 - Windings characterised by the shape, form or construction of the insulation between conductors or between conductor and core, e.g. slot insulation
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
Electric motors and stators thereof are described. The stators of the electric motors include a first header, a second header fluidly connected to the first header, a plurality of windings fluidly connected to the first header and the second header to receive a cooling fluid passing from the first header to the second header along one or more flow channels, and one or more phase-change material elements arranged to thermally interact with at least one of the first header, the second header, the one or more flow channels, and the plurality of windings.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
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 9/20 - Arrangements for cooling or ventilating for machines with closed casing and closed-circuit cooling using a liquid cooling medium, e.g. oil wherein the cooling medium vaporises within the machine casing
H02K 9/22 - Arrangements for cooling or ventilating by solid heat conducting material embedded in, or arranged in contact with, the stator or rotor, e.g. heat bridges
58.
Three-dimensional diffuser-fin heat sink with integrated blower
A heat exchanger system is provided and includes a heat sink, fins arrayed on a central region of the heat sink to form channels between adjacent fins and an integrated blower. Each of the fins extends radially outwardly from the central region and has a height that increases with increasing distance from the central region. The integrated blower is disposed at the central region to generate flows of coolant directed into and through the channels.
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
H01L 23/467 - Arrangements for cooling, heating, ventilating or temperature compensation involving the transfer of heat by flowing fluids by flowing gases, e.g. air
F28F 13/06 - Arrangements for modifying heat transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
A method for maintaining a redox flow includes draining a first battery electrolyte solution from a redox flow battery cell, the cell including a separator layer arranged between a first electrode and a second electrode, a first circulation loop configured to provide the first battery electrolyte solution to the first electrode and a second circulation loop configured to provide a second battery electrolyte solution to the second electrode; and flowing a non-battery electrolyte solution through the first electrode. The non-battery electrolyte removes at least a portion of the solid precipitates from at least one of the first electrode and the separator layer. The method also includes draining the non-battery electrolyte solution from the cell and returning the first battery electrolyte solution to the cell. A method for a redox flow battery and a redox flow battery are also disclosed.
A method for a redox flow battery includes using a cell of a redox flow battery to store electrical energy and discharge the stored electrical energy. The using includes circulating a first electrolyte solution through a first circulation loop in fluid connection with the first electrode of the cell; circulating a second electrolyte solution through a second circulation loop in fluid connection with the second electrode of the cell; and at least one of a first element from the first electrolyte solution in the first electrode permeates through the separator layer and precipitates as a first solid product in the second electrode and a second element from the second electrolyte solution permeates through the separator layer and precipitates a second solid product in the first electrode. The method also includes removing at least a portion of the first solid product or the second solid product from the first electrode and the second electrode, respectively.
A method for a redox flow battery includes using a cell of a redox flow battery to store electrical energy and discharge the stored electrical energy. The using includes circulating a first electrolyte solution through a first circulation loop in fluid connection with the first electrode of the cell; circulating a second electrolyte solution through a second circulation loop in fluid connection with the second electrode of the cell; and at least one of a first element from the first electrolyte solution in the first electrode permeates through the separator layer and precipitates as a first solid product in the second electrode and a second element from the second electrolyte solution permeates through the separator layer and precipitates a second solid product in the first electrode. The method also includes removing at least a portion of the first solid product or the second solid product from the first electrode and the second electrode, respectively.
C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
A coated substrate has a substrate and a coating system having one or more ceramic layers. At least a first layer of one of the one or more ceramic layers is a columnar layer having as-deposited columns and intercolumn gaps. The intercolumn gaps have a mean width at least one of: at least 4.0 micrometers; and at least 1.5% of a thickness of said first layer.
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
C04B 35/50 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare earth compounds
C22C 19/03 - Alloys based on nickel or cobalt based on nickel
C23C 28/04 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of inorganic non-metallic material
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
The presently disclosed embodiments utilize an ice separator vessel to trap ice particles in a non-homogeneous ice/fuel mixture flowing in a fuel system. A source of heat, such as heated fuel provided to the ice separator vessel, is used to melt at least a portion of the ice particles so that they do not enter the fuel system downstream of the ice separator vessel.
A metal-supported electrolyzer includes an electrolysis cell that has, in stacked order, an electrode unit having a first solid oxide electrode layer, a solid oxide electrolyte layer that is proton-conductive in a temperature range of 650° C. or lower, and a second solid oxide electrode layer. A porous metal sheet in contact with the second solid oxide electrode layer supports the electrode unit, a metal separator sheet bonded to the porous metal sheet, and a metal interconnect backing the metal separator sheet.
C25B 9/73 - Assemblies comprising two or more cells of the filter-press type
C25B 9/23 - Cells comprising dimensionally-stable non-movable electrodes; Assemblies of constructional parts thereof with diaphragms comprising ion-exchange membranes in or on which electrode material is embedded
H01M 8/126 - Fuel cells with solid electrolytes operating at high temperature, e.g. with stabilised ZrO2 electrolyte characterised by the process of manufacturing or by the material of the electrolyte the electrolyte consisting of oxides the electrolyte containing cerium oxide
C25B 15/08 - Supplying or removing reactants or electrolytes; Regeneration of electrolytes
H01M 4/86 - Inert electrodes with catalytic activity, e.g. for fuel cells
66.
Redox flow battery with electrolyte balancing and compatibility enabling features
A redox flow battery includes first and second cells. Each cell has electrodes and a separator layer arranged between the electrodes. A first circulation loop is fluidly connected with the first electrode of the first cell. A polysulfide electrolyte solution has a pH 11.5 or greater and is contained in the first recirculation loop. A second circulation loop is fluidly connected with the second electrode of the second cell. An iron electrolyte solution has a pH 3 or less and is contained in the second circulation loop. A third circulation loop is fluidly connected with the second electrode of the first cell and the first electrode of the second cell. An intermediator electrolyte solution is contained in the third circulation loop. The cells are operable to undergo reversible reactions to store input electrical energy upon charging and discharge the stored electrical energy upon discharging.
A rotor assembly of a gas-turbine engine may comprise a first rotor blade, a second rotor blade, a third rotor blade, a first platform sealing assembly and a second platform sealing assembly. The first platform sealing assembly may be disposed between a first platform of the first rotor blade and a second platform of the second rotor blade. The second platform sealing assembly may be disposed between the second platform and a third platform of the third rotor blade.
A heat exchanger plate provides heat transfer between a first flow along a first flowpath and a second flow along a second flowpath. The heat exchanger plate has a substrate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal portion having a plurality of inlet ports along the first flowpath and a plurality of outlet ports along the first flowpath; and a plurality of passageways along the first flowpath. Each passageway extends between a respective associated said inlet port of the plate and a respective associated said outlet port of the plate.
F28F 3/02 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations
F28F 3/00 - Plate-like or laminated elements; Assemblies of plate-like or laminated elements
F28D 7/08 - Heat-exchange apparatus having stationary tubular conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall the conduits being otherwise bent, e.g. in a serpentine or zig-zag
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/12 - Elements constructed in the shape of a hollow panel, e.g. with channels
An alloy that may include nickel, aluminum from 4.8 wt.% to 5.15 wt.%;cobalt from 18 wt.% to 19 wt.%, chromium from 11.9 wt.% to 12.9 wt.%, molybdenum from 2.8 wt.% to 3.6 wt.%, and niobium from 0.05 wt.% to 0.1 wt.%. The alloy may further include tungsten from 0.05 wt.% to 0.1 wt.%. The alloy may further include tantalum from 0.05 wt.% to 0.1 wt.%.
A heat exchanger for providing thermal energy transfer between a first flow along a first flowpath and a second flow along a second flowpath has a plate bank having a plurality of plates, each plate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath. An inlet manifold has at least one inlet port and at least one outlet port. An outlet manifold has at least one outlet port and at least one inlet port. The first flowpath passes from the at least one inlet port of the inlet manifold, through the at least one passageway of each of the plurality of plates, and through the at least one outlet port of the outlet manifold.
F28D 9/00 - Heat-exchange apparatus having stationary plate-like or laminated conduit assemblies for both heat-exchange media, the media being in contact with different sides of a conduit wall
F28F 3/08 - Elements constructed for building-up into stacks, e.g. capable of being taken apart for cleaning
B21D 53/04 - Making other particular articles heat exchangers, e.g. radiators, condensers of sheet metal
F28F 1/26 - Tubular elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with projections, with recesses the means being only outside the tubular element and extending transversely the means being integral with the element
F28F 9/26 - Arrangements for connecting different sections of heat-exchange elements, e.g. of radiators
F28F 3/04 - Elements or assemblies thereof with means for increasing heat-transfer area, e.g. with fins, with recesses, with corrugations the means being integral with the element
A turbine engine has: a first member (22) having a surface bearing an abradable coating, the abradable coating (36) being at least 90% by weight ceramic; and a second member (24) having a surface bearing an abrasive coating. The abrasive coating (56) has a metallic matrix (64) and a ceramic oxide abrasive (66) held by the metallic matrix, the first member and second member mounted for relative rotation with the abrasive coating facing or contacting the abradable coating. At least 50% by weight of the ceramic abrasive has a melting point at least 400K higher than a melting point of at least 20% by weight of the ceramic of the abradable coating.
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
C23C 28/00 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and
B01J 21/06 - Silicon, titanium, zirconium or hafnium; Oxides or hydroxides thereof
C04B 35/20 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxides based on silicates other than clay rich in magnesium oxide
C04B 35/5831 - Shaped ceramic products characterised by their composition; Ceramic compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on borides, nitrides or silicides based on boron nitride based on cubic boron nitride
A redox flow battery includes a redox flow cell, a supply/storage system external of the redox flow cell, and a controller. The supply/storage system includes first and second electrolytes for circulation through the redox flow cell. The first electrolyte is a liquid electrolyte having electrochemically active species with multiple, reversible oxidation states. The electrochemically active species can form a solid precipitate blockage in the redox flow cell. The controller is configured to identify whether there is the solid precipitate blockage in the redox flow cell and, if so, initiate a regeneration mode that reduces the oxidation state of the electrochemically active species in the liquid electrolyte to dissolve, in situ, the solid precipitate blockage.
A turbine engine includes a duct defining an annular passage, at least two heat exchangers arranged within the annular passage and spaced circumferentially apart, a passage between the at least two heat exchangers, and a forward flow control device operable for controlling airflow through the passages.
A gas turbine engine article includes an article wall that has an inner portion at least partially defining a cavity and an outer portion. A plurality of first cooling passage networks each define first dimensions and are embedded in the article wall between the inner portion and the outer portion of the article wall. A plurality of second cooling passage networks each define second dimensions and are embedded into the article wall between the inner portion and the outer portions of the article wall. The plurality of first and second cooling passage networks are arranged in one of a first column of radially positioned networks and a second column of radially positioned networks. At least one cooling hole in the first column of radially positioned networks is located upstream of and radially aligned with at least one second mid-span wall between adjacent networks in the second column of networks.
A turbine engine includes a core engine including a first spool and a second spool rotatable about a main engine longitudinal axis, a boost spool powered by a secondary drive system, and an accessory gearbox coupled to the core engine and the boost spool. A differential gear system is coupled between the core engine, the boost spool and the accessory gearbox for distributing power between the boost spool, the core engine and the accessory gearbox.
A redox flow battery system includes a redox flow battery that has a redox flow cell, and a supply/storage system external of the redox flow cell. The supply/storage system includes first and second electrolytes for circulation through the redox flow cell. At least the first electrolyte is an aqueous liquid electrolyte that has electrochemically active species with multiple, reversible oxidation states. There is a gas vent passage connected with the redox flow battery to receive water byproduct that evolves from side reaction of the first electrolyte. A bypass passage is connected with the supply/storage system to receive the aqueous electrolyte. An electrochemical recovery cell includes a first half-cell connected to the gas vent passage to receive as a reactant the water byproduct and a second half-cell connected to the bypass passage to receive as a reactant the first electrolyte.
A brake roller may comprise a brake shaft and a brake stack assembly located around the brake shaft. A one-way jaw clutch assembly may be configured to apply a force to the brake stack. A roller shell may be located radially outward of the brake stack. The one-way jaw clutch assembly may be configured to vary the force applied to the brake stack in response to a rotation of the roller shell in a circumferential direction.
F16D 11/10 - Clutches in which the members have interengaging parts actuated by moving a non-rotating part axially with clutching members movable only axially
F16D 41/18 - Freewheels or freewheel clutches with non-hinged detent
F16D 55/39 - Brakes with a plurality of rotating discs all lying side by side mechanically actuated by means of an intermediate leverage
78.
CMC COMPONENT ARRANGEMENT AND METHOD OF MANUFACTURE
A method of manufacturing a component includes forming an inner wrap about a mandrel. The inner wrap has first and second walls joined by a base portion and an outer wall. A rod is arranged at each of the first and second walls. An outer wrap is formed about the inner wrap and the rods to form a body. Features are formed in the first and second walls.
An acoustic liner for a gas turbine engine includes an acoustic panel that is curved about a central axis. The acoustic panel includes a support backing, a face sheet, and a cellular structure disposed between the support backing and the face sheet. The face sheet has elongated slots that extend along respective slot centerlines in the plane of the face sheet. The slot centerlines are sloped at oblique angles to the central axis.
An airfoil for a gas turbine engine includes an airfoil body extending between leading and trailing edges in a chordwise direction and extending from a root section in a spanwise direction, and the airfoil body defining pressure and suction sides separated in a thickness direction. The airfoil body defines a recessed region extending inwardly from at least one of the pressure and suction sides, and the airfoil body includes one or more ribs that define a plurality of pockets within a perimeter of the recessed region. A plurality of cover skins is welded to the airfoil body along the one or more ribs to enclose respective ones of the plurality of pockets.
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
F04D 29/26 - Rotors specially adapted for elastic fluids
B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
81.
Cell for electrochemically determining active species concentrations in redox flow batteries
A redox flow battery system includes a redox flow battery that has a redox flow cell and a supply/storage system. The supply/storage system has first and second electrolytes for circulation through the redox flow cell. At least the first electrolyte is a liquid electrolyte that has electrochemically active species with multiple, reversible oxidation states. A secondary cell is operable to monitor concentration of one or more of the electrochemically active species. The secondary cell has a counter electrode, a flow passage that connects the counter electrode with the redox flow battery to receive the first or second electrolyte, a working electrode, and a separator. The working electrode is isolated from receiving the electrochemically active species of the first and second electrolytes except for a transport passage connecting the flow passage and the working electrode. The transport passage limits movement of the electrochemically active species to the working electrode.
An occupant camera system for an aircraft ejection assembly may comprise a fixed structure and a camera mounted to the fixed structure. A digital video recorder may be mounted to the fixed structure and electrically coupled to the camera. A switch may be electrically coupled to the digital video recorder, and a battery may be electrically coupled to the switch.
A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the ECU being configured to determine whether the electric motor system and/or the heat engine system are in a normal mode such that the electric motor system and/or the heat engine can provide a predetermined amount of torque (e.g., full power). The ECU can be configured to receive a total torque setting and split output power between the electric motor system and the heat engine system in accordance with the normal mode as a function of the total torque setting. The ECU can be configured to detect and command recharging or regenerating of the battery system in some flight conditions.
A hybrid electric engine control module (ECU) can be configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system. The ECU can be configured to determine whether at least one of the electric motor system or the heat engine system are in a normal mode such that one of the electric motor system and/or the heat engine can provide a predetermined amount of torque. The ECU can be configured to switch to a degraded mode if either of the electric motor system or the heat engine system cannot provide the predetermined amount of torque. In the degraded mode the ECU can be configured to control the electric motor system and the heat engine system differently than in the normal mode or to not control one or both of the electric motor system or the heat engine system.
An electrical power system is disclosed for an aircraft having a hybrid-electric propulsion system, which includes a battery assembly for storing energy, an electric motor controller operatively connected to the battery assembly for conditioning and controlling power to an electric motor, and an electric motor receiving power through the motor controller for delivering torque to a shaft of the hybrid-electric propulsion system.
B60L 58/10 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
B60L 15/20 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performance; Adaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train for control of the vehicle or its driving motor to achieve a desired performance, e.g. speed, torque, programmed variation of speed
H02H 3/00 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection
H02J 1/00 - Circuit arrangements for dc mains or dc distribution networks
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H02P 7/00 - Arrangements for regulating or controlling the speed or torque of electric DC motors
H05K 10/00 - Arrangements for improving the operating reliability of electronic equipment, e.g. by providing a similar stand-by unit
B64D 27/35 - Arrangements for on-board electric energy production, distribution, recovery or storage
86.
Systems and methods for brake failure detection using retract braking
A system for detecting aircraft brake failure using retract braking may comprise a landing gear including a wheel, a brake coupled to the wheel, and a wheel sensor coupled to the wheel. A brake controller may be coupled to the brake and the wheel sensor. The brake controller may be configured to receive a begin retract braking signal, command the brake to apply a braking force to the wheel, calculate a wheel speed characteristic using data from the wheel sensor, and determine whether the wheel speed characteristic indicates a failure of the brake.
B60T 8/32 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
B60T 8/88 - Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration with failure responsive means, i.e. means for detecting and indicating faulty operation of the speed responsive control means
B60T 17/22 - Devices for monitoring or checking brake systems; Signal devices
B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
A gas turbine engine includes a core engine, a fan section, and a superposition gearbox that includes a sun gear. A plurality of intermediate gears are engaged to the sun gear and supported in a carrier and a ring gear circumscribing the intermediate gears. The core engine drives the sun gear and an output from the superposition gearbox driving the fan section. An electric motor is coupled to a portion of the superposition gearbox to provide a portion of power to drive the fan section through the superposition gearbox.
F02C 3/113 - 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 with variable power transmission between rotors
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 35/02 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
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
88.
Redox flow battery with electrolyte balancing and compatibility enabling features
A redox flow battery includes first and second cells. Each cell has electrodes and a separator layer arranged between the electrodes. A first circulation loop is fluidly connected with the first electrode of the first cell. A polysulfide electrolyte solution has a pH 11.5 or greater and is contained in the first recirculation loop. A second circulation loop is fluidly connected with the second electrode of the second cell. An iron electrolyte solution has a pH 3 or less and is contained in the second circulation loop. A third circulation loop is fluidly connected with the second electrode of the first cell and the first electrode of the second cell. An intermediator electrolyte solution is contained in the third circulation loop. The cells are operable to undergo reversible reactions to store input electrical energy upon charging and discharge the stored electrical energy upon discharging.
A seat for an aircraft may comprise a seat pan and a back support coupled to the seat pan. An upper thoracic support may be located proximate an end of the back support opposite the seat pan. The upper thoracic support may be configured to rotate relative to the back support. A headrest may be coupled to the upper thoracic support.
A method of making an energy storage article having a metal nitride electrode is disclosed where metal nitride is made by nitriding particles of a metal or oxide of a metal selected from vanadium molybdenum, titanium, niobium, tungsten, or combinations including any of the foregoing by contacting the particles with a gas of nitrogen and hydrogen, or ammonia, in a fluidized bed reactor to form particles of metal nitride for the electrode.
Brake disks with integrated heat sink are provided. Brake disk includes a fiber-reinforced composite material and an encapsulated heat sink material impregnated into the fiber-reinforced composite material. The encapsulated heat sink material comprises a heat sink material encapsulated within a silicon-containing encapsulation layer. Methods for manufacturing the brake disk with integrated heat sink and methods for producing the encapsulated heat sink material are also provided.
A method includes detecting at least one region of interest in a frame of image data. One or more patches of interest are detected in the frame of image data based on detecting the at least one region of interest. A model including a deep convolutional neural network is applied to the one or more patches of interest. Post-processing of a result of applying the model is performed to produce a post-processing result for the one or more patches of interest. A visual indication of a classification of defects in a structure is output based on the result of the post-processing.
A pressure vessel assembly includes a vessel having a wall defining a chamber and a circumferentially continuous lip projecting into the chamber from the wall. The lip defines a through-bore that is in fluid communication with the chamber. A nozzle assembly of the pressure vessel assembly includes a tube projecting at least in-part into the through-bore, and an o-ring disposed between, and in sealing contact with, the tube and the lip.
A composite pressure vessel assembly includes a first vessel having a first inner layer and a second vessel having a second inner layer. An outer layer of the assembly is in contact with and substantially envelopes the first and second inner layers. A junction of the assembly has outer boundaries defined by segments of the first inner layer, the second inner layer and the outer layer. A cross-layered component of the assembly is disposed in the junction, the first and second inner layers and the outer layer for adding strength to the junction and restricting delamination.
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
A pressure vessel assembly includes a vessel including a wall defining a chamber and a circumferentially continuous lip projecting into the chamber from the wall. The lip defines a through-bore in fluid communication with the chamber. A nozzle assembly including a tube and a flange projecting radially outward from the tube. The tube includes a first portion projecting from the flange and through the through-bore and an opposite second portion projecting outward from the flange. The flange is in contact with the wall and the first portion includes an outer surface having a contour configured to produce sealing friction between the lip and the outer surface.
F17C 1/06 - Protecting sheatings built-up from wound-on bands or filamentary material, e.g. wires
F17C 11/00 - Use of gas-solvents or gas-sorbents in vessels
F17C 13/00 - VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES - Details of vessels or of the filling or discharging of vessels
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
96.
Oxidation resistant shot sleeve for high temperature die casting and method of making
Shot sleeves for high temperature die casting include a low modulus single crystal nickel-based alloy having less than 1 ppm sulfur, a low modulus single crystal nickel-based alloy doped with a sulfur active element, a low modulus single crystal nickel-based alloy having a protective oxide coating, or a combination of two or more of the foregoing.
A composite pressure vessel assembly includes a first and second vessels aligned side-by-side. Each vessel has a liner defining respective chambers. First and second mid-layers of the assembly cover the respective liners with portions of the respective mid-layers being in contact with one-another. An outer layer of the vessel assembly is in contact with and substantially envelops both mid-layers except for the mid-layer portions.
Various examples of methods and systems are provided for improved predictive analytics. In one example, a method of managing operation of an asset or group of assets of interest includes comparing a generated prediction with one or more prediction range associated with a risk profile assigned to an operational outcome of interest, presenting a notification to an operator in response to the comparison, and incorporating operator-generated input as updated source data for the generation of subsequent predictions. The operator-generated input can comprise an operator-defined selection such as, e.g., acceptance of the notification, or rejection of the notification. The operator-generated input can provide real time or near real time information based upon context-specific knowledge that the operator holds that is substantially independent of historical source data.
A composite vessel assembly includes a circumferentially continuous wall and an end cap. The wall includes a plurality of layers, and the end cap includes a plurality of steps. Each step of the plurality of steps is engaged to a respective layer of the plurality of layers.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
F17C 1/00 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge
F17C 1/06 - Protecting sheatings built-up from wound-on bands or filamentary material, e.g. wires
F17C 13/00 - VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES - Details of vessels or of the filling or discharging of vessels
B29K 105/08 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns
100.
Mold-less curing method of manufacturing a composite vessel assembly
A method of manufacturing a composite vessel assembly includes the step of placing the composite vessel assembly in a pliable containment prior to curing of a resin of the composite vessel assembly. With the composite vessel assembly in the pliable containment, a vacuum is applied through an orifice in the pliable containment to evacuate air and compact the composite vessel assembly.
B29C 65/02 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure
B29C 63/00 - Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor
B29C 65/00 - Joining of preformed parts; Apparatus therefor
B65B 3/02 - Machines characterised by the incorporation of means for making the containers or receptacles
B65B 31/00 - Packaging articles or materials under special atmospheric or gaseous conditions; Adding propellants to aerosol containers
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
B33Y 70/00 - Materials specially adapted for additive manufacturing
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
