An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: commanding, via the processor, a first scan of a bladed rotor; generating, via the processor, a three-dimensional model based on a first set of data received from the first scan; comparing, via the processor, the three-dimensional model to an acceptable three-dimensional model of the bladed rotor; determining, via the processor, areas of interest based on the comparison; commanding, via the processor, a second scan of the areas of interest of the bladed rotor; and generating a final three-dimensional model based on the first scan and the second scan.
A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier and a ring gear including first and second portions. The first and second portions have axially opposed faces abutting one another at a radial interface.
An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by a processor, cause the processor to perform operations comprising: commanding, via the processor, a first scan of a bladed rotor; generating, via the processor, a three-dimensional model based on a first set of data received from a first scanner; comparing, via the processor, the three-dimensional model to an acceptable three-dimensional model of the bladed rotor; determining, via the processor, areas of interest based on the comparison; and commanding, via the processor, a contact probe to perform a non-destructive inspection on the areas of interest.
G01N 21/95 - Investigating the presence of flaws, defects or contamination characterised by the material or shape of the object to be examined
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)
G01B 5/008 - Measuring arrangements characterised by the use of mechanical techniques for measuring coordinates of points using coordinate measuring machines
G01N 21/91 - Investigating the presence of flaws, defects or contamination using penetration of dyes, e.g. fluorescent ink
4.
FIBER HAVING INTEGRAL WEAK INTERFACE COATING, METHOD OF MAKING AND COMPOSITE INCORPORATING THE FIBER
Disclosed is a method of coating a high temperature fiber including depositing a base material on the high temperature fiber using atomic layer deposition, depositing an intermediate material precursor on the base material using molecular layer deposition, depositing a top material on the intermediate material precursor or the intermediate layer using atomic layer deposition, and heat treating the intermediate precursor. The intermediate material in the final coating includes a structural defect, has lower density than the top material or a combination thereof. Also disclosed are the coated high temperature fiber and a composite including the high temperature fiber.
D01F 11/00 - Chemical after-treatment of man-made filaments or the like during manufacture
C03C 14/00 - Glass compositions containing a non-glass component, e.g. compositions containing fibres, filaments, whiskers, platelets, or the like, dispersed in a glass matrix
C08K 9/02 - Ingredients treated with inorganic substances
C23C 16/455 - 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 introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
A retention ring for a gas turbine engine according to an example of the present disclosure includes, among other things, a main body extending in a circumferential direction about an axis to establish a continuous hoop having a first diameter and a second diameter. The main body includes first and second circumferential faces along opposite sides of the main body. The first circumferential face is dimensioned to abut a gas turbine engine component. The main body includes at least one removal feature dimensioned to sever in response to engagement with a cutting tool. A method of assembly is also disclosed.
A turbomachine has a bearing in a bearing compartment. A first seal system isolates the bearing compartment and has: a first runner; a second runner; an inner seal encircling the first runner; and an outer seal encircling the second runner. The inner seal has a static clearance with the first runner. The outer seal has a static clearance with the second runner, greater than the inner seal static clearance. The first runner has an inner portion cantilevered inward. The second runner has an outer portion cantilevered outward.
A method for coating a fiber tow includes moving a fiber tow across a wedge to separate the fiber tow into a plurality of sub-tows, and coating the plurality of sub-tows.
C23C 16/455 - 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 introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
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.
A method is disclosed herein. In various embodiments, the method comprises: coupling a sheath to an airfoil of an integrally bladed rotor, the sheath comprising a plurality of apertures disposed therein; and coupling a plurality of locators to the integrally bladed rotor, each locator in the plurality of locators disposed through a corresponding aperture in the plurality of apertures.
B23P 15/02 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine engine further includes a means for selectively releasing a cooling fluid flow produced at a cryogenic temperature and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section and the turbine section.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
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 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
F25B 9/14 - Compression machines, plants or systems, in which the refrigerant is air or other gas of low boiling point characterised by the cycle used, e.g. Stirling cycle
F25J 3/04 - Processes or apparatus for separating the constituents of gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream for air
B01D 45/08 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by utilising inertia by impingement against baffle separators
B01D 53/00 - Separation of gases or vapours; Recovering vapours of volatile solvents from gases; Chemical or biological purification of waste gases, e.g. engine exhaust gases, smoke, fumes, flue gases or aerosols
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 7/143 - Cooling of plants of fluids in the plant of working fluid before or between the compressor stages
F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
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
B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned
An inspection system for a bladed rotor is disclosed herein. In various embodiments, the inspection system comprises: a support structure; a first scanner moveably coupled to the support structure; a second scanner moveably coupled to the support structure; a motor operably coupled to a shaft, the shaft rotatably coupled to the support structure, the shaft configured to be coupled to the bladed rotor; and a controller in electronic communication with the first scanner, the second scanner, and the motor, the controller configured to: command the first scanner to scan the bladed rotor; command the second scanner to scan the bladed rotor; and generate a point cloud for the bladed rotor based on scanning data received from the first scanner and the second scanner.
G01S 17/89 - Lidar systems, specially adapted for specific applications for mapping or imaging
F02C 7/00 - Features, component parts, details or accessories, not provided for in, or of interest apart from, groups ; Air intakes for jet-propulsion plants
G01S 7/481 - Constructional features, e.g. arrangements of optical elements
A vane arm connection system for a gas turbine engine includes a vane stem having a head with flat contact surfaces; a vane arm having a claw, the claw having opposed arms having inwardly facing surfaces engaging the flat contact surfaces of the head; and a torque transfer member having a body defining an opening for engaging the flat contact surfaces of the head of the vane stem, and at least one arm extending from the body to contact the claw, whereby load from torque is transferred away from the inwardly facing surfaces.
A component for a gas turbine engine includes an airfoil section including a free end and an abrasive coating sprayed onto the free end, the abrasive coating including a polymer matrix and an abrasive filler, the abraisive filler between about 50%-75% by volume of the abrasive coating.
F01D 5/28 - Selecting particular materials; Measures against erosion or corrosion
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 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
F04D 29/32 - Rotors specially adapted for elastic fluids for axial-flow pumps
F01D 5/20 - Specially-shaped blade tips to seal space between tips and stator
B05B 7/14 - Spraying apparatus for discharge of liquids or other fluent materials from two or more sources, e.g. of liquid and air, of powder and gas designed for spraying particulate materials
B05D 1/02 - Processes for applying liquids or other fluent materials performed by spraying
B05D 3/00 - 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
Vane assemblies for gas turbine engines are described. The vane assemblies include a platform having an interior platform surface, a forward rail, and an aft rail, wherein the interior platform surface, the forward rail, and the aft rail define a plenum, an airfoil extending radially inward from the platform on a side opposite the forward and aft rails, the airfoil having a leading edge cavity and a baffle installed within the leading edge cavity, and platform feed structure arranged on the platform in the plenum and defining a fluid path through the forward rail and into the baffle of the leading edge cavity.
A ceramic matrix composite blade includes a central core surrounded by an outer profile, the central core comprising layers of unidirectional layup having two dimension and three dimension fiber weaves; the outer profile comprises a biased weave layup that radiates toward a leading edge and a trailing edge of the blade; wherein the biased weave layup includes fibers that extend proximate an attachment region of the blade radially and axially along an airfoil portion of the blade toward the leading edge and trailing edge.
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.
In accordance with at least one aspect of this disclosure, a transition structure for a heat exchanger can include a body defining a dome cavity. The dome cavity can be configured to transition flow between at least one first channel and a plurality of second channels having a different number than the at least one first channel.
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.
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
26.
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
27.
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.
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
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.
33.
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.
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
37.
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.
40 - Treatment of materials; recycling, air and water treatment,
Goods & Services
Parts molding; Manufacturing services for others in the field of radiation detector components, mold components, and structural components for marine and aerospace applications
39.
END EFFECTOR, WELDING SYSTEM, AND METHOD FOR WELDING COMPOSITE COMPONENTS
An end effector for welding composite components includes an end effector housing and a welding member mounted to the end effector housing. The end effector further includes a leading roller mounted to the end effector housing forward of the welding member and at least one follower roller mounted to the end effector housing aft of the welding member. The end effector further includes at least one first cooling air jet positioned to direct a first stream of cooling air toward the at least one follower roller.
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 flow battery includes an electrochemical cell that has a first electrode, a second electrode spaced apart from the first electrode, and a separator layer arranged between the first electrode and the second electrode. The separator layer is formed of a polymer that has a polymer backbone with cyclic groups that are free of unsaturated nitrogen and one or more polar groups bonded between the cyclic groups.
H01M 8/18 - Regenerative fuel cells, e.g. redox flow batteries or secondary fuel cells
H01M 8/20 - Indirect fuel cells, e.g. fuel cells with redox couple being irreversible
H01M 8/1025 - Polymeric electrolyte materials characterised by the chemical structure of the main chain of the ion-conducting polymer having only carbon and oxygen, e.g. polyethers, sulfonated polyetheretherketones [S-PEEK], sulfonated polysaccharides, sulfonated celluloses or sulfonated polyesters
H01M 8/1027 - Polymeric electrolyte materials characterised by the chemical structure of the main chain of the ion-conducting polymer having carbon, oxygen and other atoms, e.g. sulfonated polyethersulfones [S-PES]
H01M 8/1032 - Polymeric electrolyte materials characterised by the chemical structure of the main chain of the ion-conducting polymer having sulfur, e.g. sulfonated-polyethersulfones [S-PES]
H01M 8/103 - Polymeric electrolyte materials characterised by the chemical structure of the main chain of the ion-conducting polymer having nitrogen, e.g. sulfonated polybenzimidazoles [S-PBI], polybenzimidazoles with phosphoric acid, sulfonated polyamides [S-PA] or sulfonated polyphosphazenes [S-PPh]
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
An energy extraction system according to an exemplary embodiment of this disclosure, among other possible things includes an ammonia fuel storage tank assembly that is configured to store a liquid ammonia fuel, a thermal transfer assembly that is configured to transform the liquid ammonia fuel into a vaporized ammonia based fuel, a turbo-expander that is configured to expand the vaporized ammonia based fuel to extract work, and an energy conversion device that is configured to use the vaporized ammonia based fuel from the turbo-expander to generate a work output.
F02C 7/224 - Heating fuel before feeding to the burner
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
F02C 3/24 - 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 liquid at standard temperature and pressure
F23R 3/30 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
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.
An energy storage assembly includes an energy storage unit. A supervisor is operable to determine a power reference set point based upon a cost function. A storage unit controller is configured to control the energy storage unit to provide electric energy to at least one load based upon a power reference input that is based upon the power reference set point and at least one dynamically changing power profile from the at least one load.
B66B 1/30 - Control systems with regulation, i.e. with retroactive action, for influencing travelling speed, acceleration, or deceleration electrical effective on driving gear
B66B 1/24 - Control systems with regulation, i.e. with retroactive action, for influencing travelling speed, acceleration, or deceleration
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
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
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 3/30 - Windings characterised by the insulating material
H02K 3/32 - Windings characterised by the shape, form or construction of the insulation
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
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
58.
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
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
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
62.
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 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
71.
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.%.
09 - Scientific and electric apparatus and instruments
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Downloadable and recorded software for tracking the geographic location of aircraft engines; Downloadable and recorded computer search engine software Aircraft engine repair and maintenance Providing temporary use of on-line non-downloadable software for tracking the geographic location of aircraft engines; Computer services, namely, providing a search engine for obtaining data on a global computer network; Providing a website featuring a search engine for information on and tracking of aircraft engines; Electronic monitoring, recording and reporting the life usage of engines, engine components, engine assemblies, and engine support equipment using computers and sensors
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
77.
PYLON SHAPE WITH GEARED TURBOFAN FOR STRUCTURAL STIFFNESS
A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives the geared architecture. A turbine to fan diameter ratio is substantially less than 45%.
B64D 27/12 - Aircraft characterised by the type or position of power plant of gas-turbine type within, or attached to, wing
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
F02C 7/20 - Mounting or supporting of plant; Accommodating heat expansion or creep
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
A method of in-situ electrolyte preparation in a flow battery includes providing a vanadium-based electrolyte solution having vanadium ions of predominantly vanadium V4+ to a first electrode and a second electrode of at least one cell of a flow battery. The vanadium V4+ at the first electrode is converted to vanadium V3+ and the vanadium V4+ at the second electrode is converted to vanadium V5+ by providing electrical energy to the electrodes. A reducing agent is then provided to the vanadium V5+ at the second electrode to reduce the V5+ to vanadium V4+. The vanadium V3+ at the first electrode is then converted to vanadium V2+ and the vanadium V4+ at the second electrode is then converted to vanadium V5+ by providing electrical energy to the electrodes. A simple method to produce predominantly vanadium V4+ electrolyte from a V5+ source, such as V2O5, is also taught.
37 - Construction and mining; installation and repair services
Goods & Services
Maintenance, repair and overhaul services for gas turbine engines and parts thereof; providing technical support, namely, technical advice and predictive analysis concerning maintenance and repair of individual aircraft engines and fleets of aircraft engines utilizing operational data; technical support services, namely, providing technical advice in the field of aircraft engine overhaul and repair
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
87.
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.
A method of manufacturing a composite vessel assembly (20) includes the steps of filling a first chamber defined by a first liner (28,30,32) with a first granulated material (96) through a first orifice (98) in the first liner. A vacuum is then applied to the first chamber, and the first orifice is plugged. The first liner may then be enveloped with a first layer (84) for structural rigidity followed by relief of the vacuum.
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or 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
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
B29C 33/52 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles soluble or fusible
B29C 33/54 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles made of powdered or granular material
F17C 1/06 - Protecting sheatings built-up from wound-on bands or filamentary material, e.g. wires
F17C 1/16 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge constructed of plastics materials
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
A heat exchanger for a gas turbine engine includes a first plate for a coolant medium, and the first plate includes a first cool portion, a second cool portion, a coolant inlet and a coolant outlet. The coolant inlet and the coolant outlet are disposed on a common side and the first cool portion includes more passages than the second cool portion. A second plate is in thermal communication with the first plate. The second plate includes a first hot portion including a first inlet and a first outlet and a second hot portion includes a second inlet and a second outlet. The first cool portion is in thermal communication with the first hot portion and the second cool portion is in thermal communication with the second hot portion.
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 fuel system for a gas turbine engine includes an accessory gearbox driven by a mechanical link to the gas turbine engine, a primary fuel pump providing a first fuel flow during engine operation, and a secondary fuel pump providing a second fuel flow. The primary fuel pump and the secondary fuel pump are driven by an output of the accessory gearbox.
04 - Industrial oils and greases; lubricants; fuels
06 - Common metals and ores; objects made of metal
07 - Machines and machine tools
09 - Scientific and electric apparatus and instruments
11 - Environmental control apparatus
12 - Land, air and water vehicles; parts of land vehicles
13 - Firearms; explosives
15 - Musical instruments
16 - Paper, cardboard and goods made from these materials
17 - Rubber and plastic; packing and insulating materials
35 - Advertising and business services
36 - Financial, insurance and real estate services
37 - Construction and mining; installation and repair services
38 - Telecommunications services
39 - Transport, packaging, storage and travel services
41 - Education, entertainment, sporting and cultural services
42 - Scientific, technological and industrial services, research and design
45 - Legal and security services; personal services for individuals.
Goods & Services
Optical coatings Fuel propellants for use in rocket motors Metal ball mats for aerospace vehicles; metal roller tracks for loading cargo; metal hydraulic and pneumatic valves not for machines, adaptors, couplings, manifolds for aerospace construction Impact machines for breaching concrete; rocket motors for use in spacecraft and missiles, structural parts therefor and controls sold as a unit; aircraft jet and marine engines and replacement and structural parts therefor; electric roller devices, namely, roller conveyors used to transport and place portable storage containers; power winches and lifts and hoists for aerospace vehicles; cargo winches; aerospace vehicle parts, namely, transmissions, blowers, starters; turbine power systems comprised of a hot gas turbine and a pump for auxiliary and hydraulic power not for land vehicles; ram air turbines not for land vehicles; hydromechanical actuators for aircraft flight controls; air cycle machines and water separators for aircraft; fuel pumps for rocket engines and replacement parts and controls sold as a unit; auxiliary power units for supplying electrical power other than for land vehicles; electric vibratory drilling and/or abrading machines for applying vibration to an object to remove portions of said object or another object therefrom; Generators of electricity, namely, wind-powered electricity generators and hydroelectric generators; machine cylinder; engine starters; couplings and belts and transmissions for machines except for vehicles; machines for vulcanization of tires; compressors for machines involved in temperature control; industrial machines, namely, electric motors; resistance welding machines; machine parts, namely, dust filters in the nature of dust separators; valves, namely, hydraulic and pneumatic valves being parts of machines for aircraft and spacecraft construction and gas turbine engines; hydraulic and pneumatic valves as machine components; valves for pumps; exhaust nozzles for gas turbine engines, not for land vehicles aerospace vehicle sensors; photo-electric cells; television lamps; military computer mobile systems comprised of computer central processing units and displays, electronic and mechanical shock absorbers and shock isolators; active and passive countermeasure equipment comprising signal transmitters and receivers, and computer central processing units for generating communication data for aircraft and vehicles; electronic data communicators for aircraft and vehicles; Electronic transmitters for jamming signals for aircraft and ground vehicles; aerials, namely, radio aerials and satellite aerials; laser perimeter awareness systems comprised of lasers, optical receivers and associated controls; aerospace ice detectors; aerospace sensors for monitoring angle of sideslip, gas path engine pressure, current-to-heater system interruptions, brake temperatures, air data, altitude, pitot pressure, static pressure, angle of attack, temperature, engine exhaust, inlet pressure, engine temperature, fuel and oil temperature, navigation; aerospace sensors for flight crew safety and security; air traffic control systems comprised of radio equipment, radar transmitters and receivers, global positioning systems, and computer central processing units for image display and analysis; radar transmitters, detectors, receivers; global positioning systems; aircraft navigation and landing systems, namely, automatic direction finders, radio altimeters, distance measuring equipment, global position sensors, navigation receivers, multimode receivers, VHF omni-directional range marker beacon receivers; aerospace communication systems comprised of receivers and transmitters, and computer central processing units for processing communication information; aircraft interior products, namely, emergency oxygen systems for aircraft passengers and flight crews comprised of oxygen masks not for medical use, chemical oxygen generators, empty oxygen storage vessels, gas pressure regulators, oxygen distribution circuits and controls, and protective breathing equipment being oxygen breathing units; aircraft navigation and landing systems comprised of high frequency signal transmitters and receivers, global positioning units and central computer processing units for image display and analysis; aircraft alarm systems comprised of sensors, sound emitting devices and circuitry for aircraft; ally or enemy identification systems comprised of signal transmitters and receivers, data processing equipment for signal identification, coding and decoding of signals, and hardware and downloadable software to process images and sound; antenna tuning apparatus; microwave communications transmitter; battery accumulators; optical fiber; downloadable analysis software for computer software and computer networks; modulators for wireless networks and cellular communication and monolithic microwave integrated circuits; space suits; antennas; downloadable computer programs for the management of battlefields; computerized aircraft engine analyzers; fuel controllers; avionics systems for aircraft and aerospace vehicles consisting of communication and navigation hardware for use in airborne applications comprising computer hardware, software and displays for communications and navigation for aircraft and aerospace vehicles and for head-up display guidance systems, namely, flight situational awareness; batteries; battery eliminators; cabin pressure control systems comprised of cabin pressure controller, control panel, pressure relief valve, outflow valve and structural and replacement parts therefor; calculating machines; data processing equipment and computers; cameras; climate and weather monitoring and forecasting systems comprised of radar transmitters and receivers and computer central processing units for processing climate and weather data; climate control systems for aerospace vehicles consisting of thermostats, air conditioning, heating, ventilation and drying control devices; climatological surveillance systems comprised of radar transmitters and receivers; collective radio communication apparatus for ships, aircraft, vehicles; portable communications equipment, namely, modems, receivers, transceivers, and waveforms for use in air-to-ground secure communication networks; wireless appliances downloadable computer software for tracking, or disturbing / confusing communication; digital information downloadable computer software for securing storage and use of the computer; global positioning system (GPS); missile launch systems comprising downloadable software for analyzing a target's location and actuating warheads, motors and propulsion systems for deploying warheads, and warheads for destroying targets; communications computers and systems for aircraft, namely, receivers, transmitters, amplifiers, transceivers, jammers, couplers, audio distribution units, satellite communication units, automatic control computer central processing unit for gas turbine engines, radar and GPS systems used for the transmission of interrogation signals and the reception of response signals, and downloadable software for analyzing such signals to enable communication between aircraft; electric compensating cables; computer hardware for telecommunications; downloadable computer programs for military surveillance; downloadable computer programs for organizing and viewing digital images and photos; downloadable computer programs for analyzing computer software and networks; downloadable computer programs for wireless content transfer; downloadable computer programs for integrated bridge control systems; downloadable computer software used in oxygen delivery systems for aircraft; downloadable software for military mobile computers; computerized condition analyzers for life support equipment; computers; Electric motor speed and direction controls; electronic controls for engines for aerospace vehicles; electronic throttle controllers; electronic brake monitoring controls and fuel controls for aerospace vehicles; Electrical and electronic controls, namely, electro-hydraulic transducers and electrical sensors and replacement parts therefor; data collection and data processing systems comprised of computer central processing units and antennas for military information; deep ocean control systems comprised of sonar; gyroscopes for maritime use; oceanic depth finding systems comprised of pressure sensors, temperature sensors and computer processing unit for signal analysis and image display; digital weapon system interface device for tactical training; echo sounders; electric power distribution units, power supplies, power switches and power distribution and generation sensors for power generation and power distribution for aerospace vehicles; electric power distribution systems comprised of automatic power management apparatus, solid state power controllers and secondary power distribution assemblies; electric power distribution unit for aircraft; electrical circuits; electronic compass for navigation; emergency signal transmitters; weapons locators, namely, acoustic detection and computer-based signal processing unit for sensing and determining the location of weapon detonation; fire extinguishers; laser warning receivers for use in detecting, analyzing and locating the direction of laser; optical communication instruments and components, namely, optical and digital transmitters and receivers; satellite connection systems comprising downloadable security-enhanced software establishing secure connections between ground stations and satellites; satellite navigation devices, namely, GPS receivers for communicating with GPS satellites, and downloadable anti-jamming software providing uninterrupted signal communications; satellite receiver; military training systems, namely, battlefield and flight simulation; submarine surveillance systems, namely, radar systems used for detection, imaging and classification of underwater submarines; thermal imaging sensors and equipment, namely, sensors for detecting infrared radiation to enable vision in darkness, dust or inclement weather, and sensors used for imaging, targeting and tracking of guided missiles; torpedo components and systems, namely, power supply, namely, batteries, electronic controls, electronic sensors, electronic navigational and positioning apparatus; electronic aircraft touchdown protectors; undersea surveillance systems, namely, systems comprised of hydrophones, optical telemetry devices, and computer central processing unit for image display and analysis; optical telemetry devices for image display and analysis; wireless communications devices for recording, organizing, transmitting, receiving, manipulating, and reviewing voice, text, data, image, and audio files; digital forensics, namely, electronic aircraft integrated data acquisition units for collecting, integrating and recording data for monitoring, diagnosing and prognosticating aircraft subsystems, overall aircraft performance and performance of the aircraft crew; downloadable software for predictive analysis concerning maintenance and repair of individual aircraft engines and fleets of aircraft engines using operational data downloadable computer software for cybersecurity; video modulators; video tape recorders; compass systems, namely, gyroscopes; global positioning systems; imaging and targeting systems for military vehicles and weapon systems comprised of radar transmitters and receivers, and computer central processing unit for image display and analysis; ground-based radar sensors; infrared sensors and infrared sensoring systems comprised of infrared transmitters and detectors, optical lenses, video monitors, and computer central processing unit for image display and analysis; thermal vision systems for vehicles comprised of signal transmitters and detectors, cameras, and computer central processing unit for image display and analysis; radar systems comprised of antennas and computer central processing unit; weapon locating systems comprising electro-optical sensors, radar transmitters and receivers, and computer central processing unit for image display and analysis; laser warning systems comprised of laser sensors, computer central processing unit for sensor signal analysis, and alarms; remote sensing and surveillance instruments for aircraft and space applications comprised of satellite receivers and transmitters, optical sensors, spectral filters, and computer central processing unit for image display and analysis; active and passive countermeasure equipment comprising signal transmitters and receivers, and computer central processing unit for generating communication data for aircraft and vehicles; mobile military computer systems comprised of computer central processing unit and displays, electronic and mechanical shock absorbers and shock isolators; satellite communication systems comprised of satellite receivers and transmitters, and computer central processing unit for processing communication information; sonar systems comprised of sonar transducers, and computer central processing unit for sonar signal analysis and image display; undersea surveillance systems comprised of hydrophones, optical telemetry devices, and computer central processing unit for image display and analysis; global positioning systems; air traffic control systems comprised of radar transmitters and receivers, global positioning systems, and computer central processing unit for image display and analysis; aircraft navigation and landing systems comprised of high frequency signal transmitters and receivers, global positioning systems, and computer central processing unit for image display and analysis; aircraft communication systems comprised of high frequency signal transmitters and receivers, and computer central processing unit for generating communication information; multi-party radio communication systems comprised of radio frequency signal transmitters and receivers, and computer central processing unit for analyzing and modulating frequency signals; roadway toll collection systems comprised of signal transmitters and receivers, cameras, video recorders, and computer central processing unit for performing toll collection; roadway vehicle tracking systems comprised of signal transmitters and receivers, cameras, video recorders, and computer central processing unit for processing and tracking vehicle license plates; identification of friend or foe systems comprised of signal transmitters and receivers, and computer central processing unit for performing signal encryption and decryption; environmental weather and climatological surveillance monitoring and forecasting systems comprised of radar transmitters and receivers, and computer central processing unit for signal analysis and image display; military intelligence data gathering and processing systems comprised of radar transmitters and receivers, and computer central processing unit for signal analysis; wireless network systems comprised of wireless modems and satellite communication receivers and transmitters; integrated circuit systems; oceanic depth finding systems comprised of pressure sensors, temperature sensors, and computer central processing unit for signal analysis and image display; electronic compasses for maritime use; transformers; power supplies; and electronic modulators for wireless networks and cellular communications equipment; monolithic microwave integrated circuits; computer hardware; downloadable computer software, namely, downloadable software for the creation of firewalls; downloadable software for security analytics; downloadable software for use by security analysts to facilitate the search and analysis of data related to cyber and real-world threats; downloadable software for network security, load balancing, and routing; downloadable software for web, hardware, network, computer and internet security; downloadable software for monitoring and/or controlling access to sites and locations on a global computer network; downloadable software that enables safe, secure and simultaneous data movement within and between computer networks; downloadable software that enables, controls and audits sharing of information across computer networks; downloadable software that enables users to enable and control access to computers, computer networks, data, documents and other software applications with multiple and differing access criteria; downloadable software that provides users with simultaneous access to multiple computer networks; downloadable computer software for security and protection, namely, downloadable software for providing web security and protection, providing e-mail messaging security and protection, and for data loss prevention; downloadable computer software for the security and protection of data, networks and communications; downloadable software for analyzing radar system inputs and directing interception of missiles; telecommunications apparatus, namely, radio transmitters, transceivers, and audio-frequency amplifiers; radio monitoring apparatus, namely, monitors for monitoring radio current and signals; electronic flight control surface actuators; machine, engine or motor control device, namely, electronic engine controls and full authority digital engine controls for aerospace vehicles; battery chargers, electric transformers, and electronic discharge tubes other than for lighting; Lights specifically made for protective tactical vests; missile defense systems, namely, radar systems detecting and analyzing incoming missiles and artillery launchers to deploy interceptors to destroy incoming missiles; automatic distribution machines, namely, electrical power distribution units; electronic fluid control valves for gas turbine engines and temperature and pressure sensors for gas turbine engines automatic valves; nozzles, namely, automatic nozzles for spraying fuel; automatic nozzles for water and liquids for use in the manufacturing or processing of goods electric lamps; lights for aircraft; lights for aerospace vehicles; aircraft interior products, namely, environmental control equipment in the nature of air cooling apparatus, heat exchangers not being parts of machines, cold plates in the nature of heat sinks for cooling electronic equipment; aircraft interior products, namely, food preparation structures, appliances and equipment in the nature of galley heating and cooling appliances, beverage makers, and galley chillers; Electric food and beverage equipment for airplane galleys, namely, coffee makers, water boilers, cooking and warming ovens, refrigerators and freezers, hot water dispensers, beverage dispensers, hot beverage makers, and food and beverage heating units; Aircraft toilets and associated systems and components, namely, toilet bowls, toilet seats, toilet frames, toilet flush valves, toilet rinse valves, electronic controllers for toilet valves, vacuum generators, wastewater storage tanks, and wastewater pipes and pipe fittings, sold together as a unit; Aircraft interior products, namely, lavatory compartments sold equipped with sanitary facilities in the nature of toilets and sinks; aircraft interior products, namely, aircraft potable water and vacuum waste systems comprised of lavatory compartments, toilets, sinks, plumbing fittings in the nature of valves and couplings and plumbing fixtures in the nature of sinks, sink traps and faucets; aircraft vacuum waste system consisting of a lavatory and waste holding tank; Aircraft interior products, namely, aircraft interior structures and monuments, namely, galleys sold equipped with food preparation apparatus in the nature of heating and cooling appliances Aircraft and structural parts for aircrafts, namely, seats, engines, brakes, wing, tail, rudder, aileron, elevators and stabilizers, engine bay doors, water tanks, chassis and enclosures, aeronaves; unmanned aircraft; aviation fuel truck joint; apparatus for locomotion by land, air or water, namely, gas turbine engines; aircraft landing gear; aircraft; aircraft propellers and structural parts for aircraft propellers Missiles, namely, cruise missiles, pyrotechnic missiles, ballistic missiles, guided missiles, ship-to-air missiles; firearms; ammunition and projectiles; explosives; fire flare; fireworks; torpedoes; weapons scopes and sights Drum machines Printed publications, namely, booklets, pamphlets and brochures featuring technical standards and specifications relating to avionics and aeronautics Rubber seals for aircrafts and gas turbine engines; weather stripping compositions, packing and insulation in the nature of non-metal weather strips for use in aircrafts Business management and operations consulting and advisory services; business consulting services in the field of cybersecurity; business consulting services in the field of data security Providing extended warranty services on aircraft engines; providing extended warranties on maintenance, repair, overhaul, conversion and servicing of aircraft engines Aerospace vehicle maintenance, repair and overhaul; maintenance, repair, and service of pumps, blowers, and compressors; installation of complex electronic equipment and systems Emergency and disaster communications services via telephone, wireless network and satellite; aeronautical communications services via telephone, wireless network and satellite; teleprocessing; railroad telecommunications via telephone, wireless network and satellite; satellite communications services; providing Internet services to airline passengers; aeronautical air-ground-air-radio service Providing airline travel databases, online interactive maps; rental of aircraft engines Training in servicing and repair of aircraft and systems and components, in use of electronic equipment/systems, pumps, blowers, and compressors; training on how to operate unmanned aircraft; training in the field of chemical and biological incident response; training of first responders on use of unmanned aerial vehicle equipment and distribution of service manuals and video materials therewith; training in the use of complex electronic equipment and systems Engineering and computer programming services for aircraft and aerospace vehicles, parts and components; aircraft product development; providing weather and meteorological information; providing Internet search engine services for retrieving data; research consultation services; engineering research services; engineering services; engineering counselling; providing online, non downloadable software to protect users from cyber intrusions; cybersecurity services in the nature of preventing unauthorized computer access; engineering services, namely, operation of complex electronic equipment and systems; cybersecurity services; providing online non-downloadable computer software services, namely, web, hardware, network, computer and internet security services by restricting and monitoring access to unauthorized areas in a global computer network or any other publicly accessible computer network for the purposes of promoting security and the computer user's productivity, by restricting access to and by computers to web sites, and by providing email messaging security and electronic data security; providing temporary use of non-downloadable computer software, namely, software for the creation of firewalls, software for security analytics, software for use by security analysts to facilitate the search and analysis of data related to cyber and real world threats, software for network security, load balancing, and routing, software for web, hardware, network, computer and internet security, software for monitoring and/or controlling access to sites and locations on a global computer network, software that enables safe, secure and simultaneous data movement within and between computer networks, software that enables, controls and audits sharing of information across computer networks, software that enables users to enable and control access to computers, computer networks, data, documents and other software applications with multiple and differing access criteria, and software that provides users with simultaneous access to multiple computer networks; providing temporary use of non-downloadable computer software for security and protection, namely, software for use in maintaining and monitoring web security, data security and e-mail security; Software as a Service (SaaS) services, namely, hosting cloud and datacenter infrastructure software for use by others in relation to security and protection computer software; cloud computing services featuring computer software for use in security and protection; providing online non-downloadable computer software services for the security and protection of data, networks, and communications Airport security control services for persons and luggage
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.
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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
B64D 31/00 - Power plant control; Arrangement thereof
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
36 - Financial, insurance and real estate services
39 - Transport, packaging, storage and travel services
Goods & Services
Aircraft engines, and structural and replacement parts therefor; gas turbine engines, not for land vehicles, and structural and replacement parts therefor; aircraft engine parts, namely, aircraft engine structural and replacement parts therefor Providing extended warranty services on aircraft engines; providing extended warranties on maintenance, repair, overhaul, conversion and servicing of aircraft engines Rental of aircraft engines
