Abstract

A vane assembly includes vanes, an actuator assembly, and a controller. The vanes are configured to rotate about their pitch axes. The actuator assembly includes an annular ring arranged radially outward of the vanes and coupled to the vanes, a magnet arranged on the annular ring, and a stator arranged adjacent the magnet. The ring is configured to rotate the vanes about the pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and annular ring about the central axis. The controller controls movement of the ring via the stator and magnets in response to at least one of (i) at least one operating condition of the gas turbine engine, or (ii) at least one operating parameter of the at least one first vane.

IPC Classes  ?

• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

A vane assembly includes a casing, vanes, and an actuator assembly. The vanes are arranged within the casing and are rotatably coupled to the casing for rotation relative thereto and configured to rotate about their pitch axes. The actuator assembly is arranged radially outward of the casing and includes an annular ring surrounding the casing and coupled to the vanes, a magnet arranged on the ring, and a stator spaced apart from the magnet. The ring is configured to rotate the vanes about their pitch axes in response to rotation of the ring about the central axis and the stator is configured to selectively rotate the magnet and ring about the central axis. The stator is configured to create a magnetic field which causes annular movement of the ring via interaction with the magnet.

IPC Classes  ?

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

Abstract

A fan case assembly adapted for use with a gas turbine engine includes a case at extends circumferentially at least partway about an axis of the gas turbine engine and a plurality of vanes. The case is formed to define a plenum that extends circumferentially at least partway about the axis. The plurality of vanes are arranged in the plenum and spaced apart circumferentially about the axis to define a plurality of inlet openings in fluid communication with the plenum.

IPC Classes  ?

• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
• F04D 29/52 - Casings; Connections for working fluid for axial pumps
• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the like; Balancing by influencing boundary layers

Abstract

A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

IPC Classes  ?

• B64D 33/10 - Radiator arrangement
• B64D 37/34 - Conditioning fuel, e.g. heating
• F02C 7/12 - Cooling of plants
• F02C 7/224 - Heating fuel before feeding to the burner
• F02K 7/10 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines

Abstract

A cooling apparatus includes a first fluid flowpath and a second fluid flowpath. The first fluid flowpath includes a subcooler having a first side in fluid communication with the first fluid flowpath; a flow control valve; a primary evaporator assembly including at least one evaporator configured to be disposed in thermal communication with a heat load; and a pressure regulator operable to control a saturation pressure within the at least one evaporator. The second fluid flowpath is in fluid communication with a second side of the subcooler.

IPC Classes  ?

• F25B 40/00 - Subcoolers, desuperheaters or superheaters
• F25B 6/00 - Compression machines, plants or systems, with several condenser circuits
• F25B 40/02 - Subcoolers
• F25B 41/20 - Disposition of valves, e.g. of on-off valves or flow control valves

Abstract

A turbine engine may include a compressor section of the turbine engine. The turbine engine may include a combustion section of the turbine engine. The combustion section may be downstream of the compressor section. The turbine engine may include a turbine section of the turbine engine. The turbine section may be downstream of the combustion section. The turbine engine may include a sensor for speed detection. The sensor may be disposed at an upstream segment of the turbine section. The sensor may include a cooling jacket. The cooling jacket may encase at least a portion of the sensor. A cooling fluid may be in fluid communication with the cooling jacket and an outer surface of the sensor. The cooling jacket may be shaped to direct cooling fluid around the sensor.

IPC Classes  ?

• F02C 7/12 - Cooling of plants
• F01D 17/02 - Arrangement of sensing elements
• F01D 25/12 - Cooling

Abstract

A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

IPC Classes  ?

• F01D 9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits
• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel

Abstract

An example system includes a power electronics system; a starter electrically connected to the power electronics system and configured to start a gas-turbine engine of an aircraft; and an energy storage system electrically connected to the power electronics system and configured to provide direct current (DC) electrical energy to the power electronics system, wherein the power electronics system is configured to deliver alternating current (AC) electrical energy to the starter to start the gas-turbine engine using the DC electrical energy from the energy storage system and AC electrical energy sourced from an AC electrical bus of the aircraft.

IPC Classes  ?

• H02P 9/08 - Control of generator circuit during starting or stopping of driving means, e.g. for initiating excitation
• F02C 7/268 - Starting drives for the rotor

Abstract

An example system includes an electrical machine electrically configured to generate electrical energy used by one or more components of a gas-turbine engine; an energy storage system; and a controller electrically connected to the energy storage system and configured to receive electrical energy from the energy storage system, wherein, in response to the gas-turbine engine being shut off, the controller is configured to cause the electrical machine to rotate a rotor of the gas-turbine engine using the energy received from the energy storage system.

IPC Classes  ?

• H02K 11/33 - Drive circuits, e.g. power electronics
• H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
• H02K 7/00 - Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
• B64D 31/00 - Power plant control; Arrangement thereof
• B60L 50/52 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells characterised by DC-motors

Abstract

A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine.

IPC Classes  ?

• F02K 1/60 - Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
• B23P 15/00 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
• F02K 1/56 - Reversing jet main flow

Abstract

A gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the compressor and a fan, shaft, or propeller.

IPC Classes  ?

• F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
• F01D 25/12 - Cooling
• F02C 3/08 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
• 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

Abstract

A compressor assembly for a gas turbine engine includes an outer band, a plurality of variable pitch vanes, and an inner band. The plurality of variable pitch vanes extend radially between the outer band and the inner band. The inner band extends circumferentially partway about an axis and includes a first ring segment and a second ring segment that cooperate to receive the plurality of variable pitch vanes.

IPC Classes  ?

• F04D 29/56 - Fluid-guiding means, e.g. diffusers adjustable
• F04D 29/54 - Fluid-guiding means, e.g. diffusers
• F04D 29/02 - Selection of particular materials
• F04D 19/00 - Axial-flow pumps specially adapted for elastic fluids

Abstract

A gas turbine engine system includes a gas turbine engine, an accessory gearbox, and a flywheel powered barring engine system. The gas turbine engine includes a rotor and a turbine. The accessory gearbox is connected with the rotor. The flywheel powered barring engine system is connected with the accessory gearbox and configured to rotate the rotor after shut down of the gas turbine engine.

IPC Classes  ?

• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 6/14 - Gas-turbine plants having means for storing energy, e.g. for meeting peak loads

Abstract

A cooling system includes a nozzle guide vane endwall. The nozzle guide vane endwall includes a first wall and a second wall. The first wall includes a first opening that extends completely through the first wall into a primary flow path of a high-pressure turbine. The second wall includes a second opening and a third opening that extend completely through the second wall into an inner passageway of the nozzle guide vane endwall. The inner passageway is configured to direct a cooling fluid to the first opening and/or the second opening via at least the third opening. The first and second opening are configured to receive a plug or a probe.

IPC Classes  ?

• F01D 25/12 - Cooling
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.

IPC Classes  ?

• F01D 9/02 - Nozzles; Nozzle boxes; Stator blades; Guide conduits
• F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
• F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel

Abstract

A power-generation system for a nuclear reactor includes a power unit, a heat exchanger, and a temperature control system. The power unit produces compressed air that is heated by the nuclear reactor via the heat exchanger. The temperature control system includes a heat transfer fluid and a heat exchanger fluidly connected with the compressed air to transfer heat between the compressed air and heat transfer fluid to control the power level of the power unit.

IPC Classes  ?

• G21C 15/12 - Arrangement or disposition of passages in which heat is transferred to the coolant, e.g. for coolant circulation through the supports of the fuel elements from containment vessel
• G21C 15/253 - Promoting flow of the coolant for gases, e.g. blowers
• G21C 15/243 - Promoting flow of the coolant for liquids

Abstract

A gas turbine engine comprises an engine core and an electric fan array. The engine core includes a compressor, a combustor, and a turbine. The compressor compresses and delivers air to the combustor. The combustor mixes fuel with the compressed air received from the compressor and ignites the fuel. The hot, high-pressure products of the combustion reaction in the combustor are directed into the turbine to cause the turbine to rotate about an axis and drive the compressor. The electric fan array may include at least two non-concentric fans having parallel shafts.

IPC Classes  ?

• F04D 29/66 - Combating cavitation, whirls, noise, vibration, or the like; Balancing
• F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
• F02C 6/00 - Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• F04D 25/06 - Units comprising pumps and their driving means the pump being electrically driven
• F04D 27/00 - Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
• F02C 9/16 - Control of working fluid flow

Abstract

A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment assembly. The ring adjustment assembly includes a shim plate having a first shim surface removably arranged on an axially facing surface of the annular ring, a carrier plate having a first carrier surface removably arranged on a second shim surface of the shim plate opposite the first shim surface, and a roller pin coupled to a second carrier surface of the carrier plate opposite the first carrier surface. The shim plate is sized so as to locate the roller pin at a predetermined distance from the annular ring so as to adjust a position of the plurality of variable vanes relative to the roller pin.

IPC Classes  ?

• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

An inlet duct for a gas turbine engine includes a particle separator, a scavenge duct, and a layer of material having a low coefficient of restitution. The particle separator including an outer wall spaced, an inner wall, and a splitter located radially between the outer wall and the inner wall. The scavenge duct is coupled with particle separator. The layer of material is located on at least one of the outer wall, the splitter, and the scavenge duct.

IPC Classes  ?

• F02C 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices

Abstract

A propulsion system includes two gas turbine engines and an air-provisioning system. The air-provisioning system includes a first ejector, a second ejector, a plenum fluidically connected with the first ejector and the second ejector, and a first propulsor. The air-provisioning system is configured to bleed and mix air from each gas turbine engine in the ejectors so as to provide selectively a flow of plenum air from the plenum to the first propulsor at a desired pressure and a desired flow rate to power the first propulsor.

IPC Classes  ?

• 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
• 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

Abstract

A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

IPC Classes  ?

• F02C 7/224 - Heating fuel before feeding to the burner
• B64D 37/02 - Tanks
• B64D 37/34 - Conditioning fuel, e.g. heating
• F28D 20/00 - Heat storage plants or apparatus in general; Regenerative heat-exchange apparatus not covered by groups or

Abstract

A gas turbine engine includes a compressor, a combustor, and a turbine. The compressor compresses gases entering the gas turbine engine. The combustor receives the compressed gases from the compressor and mixes fuel with the compressed gases. The turbine receives the hot, high pressure combustion products created by the combustor by igniting the fuel mixed with the compressed gases. The turbine extracts mechanical work from the hot, high pressure combustion products to drive the compressor and a fan, shaft, or propeller.

IPC Classes  ?

• F02C 3/14 - Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
• F02C 3/08 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
• 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
• F01D 25/12 - Cooling

Abstract

A system including a turbine engine configured to generate rotor power and produce an engine air flow. The system is configured to provide rotor power to one of more shaft-driven lift fans to generate a first thrust on an aircraft body and provide a gas flow to one or more gas-driven lift fans to generate a second thrust on the aircraft body. The gas flow may be at least a portion of the engine air flow produced by the turbine engine. The turbine engine may be configured to exhaust another portion of the engine air flow through a jet nozzle to generate an engine thrust. In examples, the system includes at least a second turbine engine. The one of more shaft-driven lift fans and/or one of more gas-driven lift fans be powered by the turbine engine, the second turbine engine, or both the turbine engine and the second turbine engine.

IPC Classes  ?

• F02C 6/04 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
• 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
• F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber

Abstract

A method of assembling a gas turbine engine is disclosed herein. The method comprises providing a set of standard turbine stages. Each turbine stage included in the set of standard turbine stages includes a single turbine rotor having a plurality of blades configured to rotate about an axis and a subset of standard turbine vane rings associated with the single turbine rotor.

IPC Classes  ?

• 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
• F04D 19/02 - Multi-stage pumps
• F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
• F02C 3/067 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
• F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user

Abstract

Techniques for abrasively blasting (e.g., grit blasting) components, such as ceramic or CMC components. In some examples, based on a comparison of component geometry to a target geometry, a blasting path over the surface of the component may be generated for a selected traverse speed. A computing device may control a blasting device to blast the component according to the generated blasting path with the selected traverse speed. In some examples, based on a comparison of a component geometry to a target geometry, a respective traverse speed for a blasting device relative the component for each section of a plurality of sections over a surface of the component may be generated. A computing device controls the blasting device to blast the component according to the respective traverse speeds relative over a surface of the component to remove material from the surface of the component.

IPC Classes  ?

• B24C 7/00 - Equipment for feeding abrasive material; Controlling the flowability, constitution, or other physical characteristics of abrasive blasts

Abstract

A fan case assembly extend along and around a center axis. The fan case assembly may comprise a barrel extending along and around the center axis, the barrel configured to fasten to a flange of an engine case. The fan case assembly may comprise a fan track liner disposed radially inward of the barrel and a containment hook, wherein the containment hook is a discrete component separate from the barrel. The containment hook may include a front segment configured to fasten to the flange, and an axial segment disposed radially inward of the barrel. The axial segment may extend between the flange and the fan track liner and the front segment may extend radially outward from an end of the axial segment. The containment hook may also include a protruding segment extending radially inward from the axial segment.

IPC Classes  ?

• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
• 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 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part

Abstract

An engine section stator for a gas turbine engine having a compressor, a combustor, and a turbine. The engine section stator includes an inner band, an outer band spaced radially outwardly from the inner band, and a series of spaced apart aerofoils extending the inner and outer bands. The engine section stator includes a stiffness feature that extends away from one of the inner and outer bands of the engine section stator. The stiffness feature configured to increase the high cycle fatigue strength of the aerofoils without impeding airflow passing between the inner and outer bands.

IPC Classes  ?

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

Abstract

In some examples, a system including a gas turbine engine, the engine including a high-pressure (HP) shaft; HP compressor; HP turbine, second shaft; second compressor; second turbine, the second turbine being coupled to the second compressor via the second shaft (e.g., LP shaft); and a generator coupled to the LP shaft. The generator is configured to generate electrical power from rotation of the LP shaft, and increase electrical power generated by the generator to increase a torque applied to the LP shaft by the generator, e.g., in combination with reduction in engine thrust, or in response to the detection of a stall and/or surge of the engine. The increase in torque applied to the second shaft is configured to increase a rate at which a rotational speed of the second shaft decreases, e.g., in combination with the reduction in engine thrust or during the stall/surge of the engine.

IPC Classes  ?

• F02C 9/48 - Control of fuel supply conjointly with another control of the plant
• F02C 6/00 - Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines

Abstract

An airfoil for use in a gas turbine engine is formed to define a cavity formed in the airfoil. The airfoil further includes at least one obstructing member arranged within the cavity and a shear-thickening fluid disposed in the cavity. A viscosity of the shear-thickening fluid increases in response to the airfoil experiencing an aeromechanic response or vibrations such that the obstruction of the movement of the thicker fluid by the obstructing member dampens the vibrations of the airfoil and reduces negative effects of a dynamic response of the airfoil.

IPC Classes  ?

• F01D 5/16 - Form or construction for counteracting blade vibration
• F01D 5/14 - Form or construction

Abstract

A fluid storage tank can be configured to store a cooling fluid in a liquid state and a gas state. A first heat exchanger can be configured to release heat into the fluid storage tank. A second heat exchanger can be disposed fluidly downstream of the fluid storage tank and configured to exchange heat between the cooling fluid and a heat load. A pressure control device can be disposed fluidly downstream of the second heat exchanger. One of the first cooling fluid that has been heated by the second heat exchanger or a second cooling fluid different than the first cooling fluid can pass through the first heat exchanger and thereby heat upstream first cooling fluid resident in the fluid storage tank.

IPC Classes  ?

• F01K 25/10 - Plants or engines characterised by use of special working fluids, not otherwise provided for; Plants operating in closed cycles and not otherwise provided for using special vapours the vapours being cold, e.g. ammonia, carbon dioxide, ether
• F01K 3/02 - Use of accumulators and specific engine types; Control thereof
• F01K 3/16 - Mutual arrangement of accumulator and heater
• F17C 7/04 - Discharging liquefied gases with change of state, e.g. vaporisation
• F01K 9/02 - Arrangements or modifications of condensate or air pumps
• F01K 27/00 - Plants for converting heat or fluid energy into mechanical energy, not otherwise provided for

Abstract

In some examples, a system including a gas turbine engine, the engine including a high-pressure (HP) shaft; HP compressor; HP turbine, second shaft; second compressor; second turbine, the second turbine being coupled to the second compressor via the second shaft (e.g., LP shaft); and a generator coupled to the LP shaft. The generator is configured to generate electrical power from rotation of the LP shaft, and increase electrical power generated by the generator to increase a torque applied to the LP shaft by the generator, e.g., in combination with reduction in engine thrust, or in response to the detection of a stall and/or surge of the engine. The increase in torque applied to the second shaft is configured to increase a rate at which a rotational speed of the second shaft decreases, e.g., in combination with the reduction in engine thrust or during the stall/surge of the engine.

IPC Classes  ?

• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
• F02C 6/00 - Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
• H02K 11/00 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection

Abstract

Methods for forming a blade for a gas turbine engine include altering the crystallographic texture of the blade in a discrete region relative to the surrounding locations of the blade to minimize flutter and/or mistune the blade by changing the natural frequency response of at least one mode of the blade.

IPC Classes  ?

• F01D 5/16 - Form or construction for counteracting blade vibration

Abstract

A rotor assembly for a gas turbine engine includes a rotor extending circumferentially about a central axis. The rotor includes a ring that extends around the central axis and a mount that extends axially away from the ring. The ring includes an axially facing engagement surface. A blade extends radially outward from the ring of the rotor. A damper is coupled with the mount of the rotor and engaged with the engagement surface to minimize vibrations of the rotor assembly.

IPC Classes  ?

• F01D 5/10 - Antivibration means

Abstract

A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

IPC Classes  ?

• F01D 25/26 - Double casings; Measures against temperature strain in casings
• F01D 9/06 - Fluid supply conduits to nozzles or the like

Abstract

A cooling system includes a nozzle guide vane endwall. The nozzle guide vane endwall includes a first wall and a second wall. The first wall includes a first opening that extends completely through the first wall into a primary flow path of a high-pressure turbine. The second wall includes a second opening that extends completely through the second wall into an inner passageway of the nozzle guide vane endwall. The inner passageway is configured to direct a cooling fluid to the first opening and/or the second opening. The first and second opening are configured to receive a plug or a probe.

IPC Classes  ?

• F01D 25/12 - Cooling
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

A gas turbine nozzle guide vane structure includes a vane shaped as an airfoil and having a vane trailing edge, an endwall including an opening to receive an end of the vane, and an element securing the endwall and the vane to each other. Clearance remaining between the endwall and the vane defines a plenum to feed cooling air to the vane at a location adjacent the vane trailing edge. Certain arrangements may have a purge groove defined in at least one of the endwall and the vane and located between the endwall and the vane to receive cooling fluid supplied. In certain arrangements, the structure may include a cover sheet on the endwall defining a gap with the vane, the purge groove configured to receive cooling fluid that exits through the gap.

IPC Classes  ?

• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
• F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades

Abstract

A bleed air control system is configured to vary the air pressure at the inlet of a gas turbine engine. The bleed air control system includes a first gas turbine engine configured to provide bleed air, a second gas turbine engine acting as an auxiliary power unit, and a bleed air control system configured to selectively provide bleed air from the first gas turbine engine to the second gas turbine engine.

IPC Classes  ?

• 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
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• 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

Abstract

A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

IPC Classes  ?

• F04D 29/52 - Casings; Connections for working fluid for axial pumps
• F01D 25/26 - Double casings; Measures against temperature strain in casings
• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
• F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the like; Balancing by influencing boundary layers
• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position

Abstract

A fan case assembly adapted for use with a gas turbine engine includes a fan track liner and an annular case. The fan track liner extends circumferentially at least partway about a central axis of the gas turbine engine. The annular case is configured to support the fan track liner at a radial position relative to the central axis. The fan case assembly further includes an air recirculation duct configured to redirect air around the fan track liner.

IPC Classes  ?

• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan

Abstract

An acoustic panel for a gas turbine engine, includes a panel body, a panel-body cover, and a support bracket. The panel body is configured to dampen vibrations caused by the gas turbine engine. The forward support bracket is configured to mount the acoustic panel to portions of the gas turbine engine.

IPC Classes  ?

• F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
• F02K 1/82 - Jet pipe walls, e.g. liners
• G10K 11/168 - Plural layers of different materials, e.g. sandwiches
• G10K 11/172 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using resonance effects

Abstract

A gas turbine engine includes a fan case assembly adapted to extend around blades of a fan rotor included in the gas turbine engine. The fan case assembly includes an annular case that extends around an axis, an acoustic panel coupled to the annular case and configured to dampen vibrations and a bolting arrangement that couples the acoustic panel to the annular case.

IPC Classes  ?

• F02C 7/24 - Heat or noise insulation
• F02C 7/045 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings

Abstract

A guide vane assembly includes a fan case, a vane, and a retention ring. The fan case extends circumferentially partway about an axis. The vane extends radially inward away from the fan case and is coupled to the fan case. The retention ring extends circumferentially partway about the axis and is coupled with the fan case and supports the vane.

IPC Classes  ?

• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings

Abstract

An example system includes one or more battery modules, a battery module of the one or more battery modules comprising: a cylindrical pressure vessel; a cooling channel extending axially through the cylindrical pressure vessel; and one or more battery packs within the cylindrical pressure vessel, a battery pack of the one or more battery packs comprising a plurality of battery cells radially distributed about the cooling channel.

IPC Classes  ?

• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries

Abstract

Airfoils and methods of cooling an airfoil are provided. The airfoil may comprise a spar; a coversheet on the spar; and a dual feed circuit between the spar and the coversheet. The dual feed circuit may include a first dam, a second dam spaced apart from the first dam along the chord axis of the spar, a first inlet disposed adjacent to the first dam, a second inlet disposed adjacent to the second dam, a circuit outlet disposed between the first inlet and the second inlet, and a plurality of diamond and/or hexagonal pedestals disposed on an outer surface of the spar. The diamond and/or hexagonal pedestals may form a plurality of cooling channels between the first inlet, the second inlet, and the circuit outlet. There may be no other circuit inlets are located between the first inlet and the second inlet.

IPC Classes  ?

• F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
• F01D 5/14 - Form or construction

Abstract

A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A blade splitter (shroud) on the fan partially spans the fan blade thus separating the core and bypass streams downstream while leaving a gap upstream for communication between the flows. The communication gap expands the operational range of the fan over fans without the communication gap.

IPC Classes  ?

• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
• F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan

Abstract

An endwall may be disposed at one end of a vane assembly. The endwall may comprise an endwall spar and a coversheet on the hot surface of the endwall spar. The endwall may further comprise a cooling fluid channel between the hot surface of the endwall spar and the cold surface of the coversheet. The cooling fluid channel may include a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The cooling fluid outlet may be formed at an angle with the axis of the endwall spar. A plurality of pedestals may be disposed on the hot surface of the endwall spar extending into the cooling channel. The pedestals may be formed at an angle with the axis of the endwall spar to direct a cooling fluid.

IPC Classes  ?

• F01D 9/00 - Stators
• F01D 25/12 - Cooling
• F01D 9/04 - Nozzles; Nozzle boxes; Stator blades; Guide conduits forming ring or sector

Abstract

A gas turbine engine includes a centrifugal compressor, a combustor, a radial turbine, and a cooling air metering system. The centrifugal compressor is configured to rotate about an axis to produce compressed air. The combustor is fluidly connected downstream of the centrifugal compressor to receive the compressed air from the centrifugal compressor. The radial turbine is fluidly connected with the combustor and is axially spaced apart from the centrifugal compressor. The cooling air metering system is configured to selectively block or allow a portion of the compressed air flowing radially between the centrifugal compressor and the radial turbine, bypassing the combustor, and through a heat exchanger for cooling the radial turbine and other components.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• 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 3/08 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
• 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

Abstract

A method for forming a component for a gas turbine engine may include forming a first portion of the component that includes a cast metal or metal alloy, forming a second portion of the component that includes presintered preform defining at least one support structure, positioning the second portion on the first portion to define an assembly such that the first portion and the second portion define at least one cooling channel therebetween, and heating the assembly to join the first portion and the second portion and form the component.

IPC Classes  ?

• B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
• F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
• B23K 1/00 - Soldering, e.g. brazing, or unsoldering
• B22F 10/22 - Direct deposition of molten metal
• B33Y 80/00 - Products made by additive manufacturing
• B22F 5/00 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
• B22F 7/00 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting
• B23K 101/00 - Articles made by soldering, welding or cutting

Abstract

A redundant oil and fuel pumping system for use with a gas turbine engine. The pumping system includes a plurality of power sources, a fuel system and an oil system. The fuel system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources. The oil system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources.

IPC Classes  ?

• F02C 7/236 - Fuel delivery systems comprising two or more pumps

Abstract

A heat transfer system for controlling two or more heat loads, including a high transient heat load, is provided. The heat transfer system may include sensible-heat thermal energy storage. A method of transferring heat from two or more heat loads to an ambient environment is further provided.

IPC Classes  ?

• F25B 5/04 - Compression machines, plants or systems, with several evaporator circuits, e.g. for varying refrigerating capacity arranged in series
• F25B 6/04 - Compression machines, plants or systems, with several condenser circuits arranged in series
• F25B 31/00 - Compressor arrangements
• F25B 40/02 - Subcoolers
• F25B 49/02 - Arrangement or mounting of control or safety devices for compression type machines, plants or systems
• F25B 43/00 - Arrangements for separating or purifying gases or liquids; Arrangements for vaporising the residuum of liquid refrigerant, e.g. by heat

Abstract

A redundant oil and fuel pumping system for use with a gas turbine engine. The pumping system includes a plurality of power supplies, a fuel system and an oil system. The fuel system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power supplies. The oil system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power supplies.

IPC Classes  ?

• F02C 7/236 - Fuel delivery systems comprising two or more pumps
• F02C 7/06 - Arrangement of bearings; Lubricating
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 9/30 - Control of fuel supply characterised by variable fuel pump output

Abstract

A redundant oil and fuel pumping system for use with a gas turbine engine. The pumping system includes a plurality of power sources, a fuel system and an oil system. The fuel system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources. The oil system pump being driven by electric motors controlled via variable frequency drives powered by the plurality of power sources.

IPC Classes  ?

• F02C 7/236 - Fuel delivery systems comprising two or more pumps
• F02C 7/06 - Arrangement of bearings; Lubricating
• F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
• F02C 9/30 - Control of fuel supply characterised by variable fuel pump output
• F02C 7/232 - Fuel valves; Draining valves or systems

Abstract

An oil pumping system for use with a gas turbine engine includes an electric machine, an oil pump assembly, and a variable frequency drive controller. The variable frequency drive is connected with the electric machine and the oil pump assembly. The variable frequency drive controller is programmed to control a torque and speed of the pump motor independent of the gas turbine engine speed so that a flow of oil moved by the oil pump assembly is controlled to cool or lubricate components of the gas turbine engine independent of the gas turbine engine speed.

IPC Classes  ?

• F02C 7/06 - Arrangement of bearings; Lubricating
• F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
• F02C 7/16 - Cooling of plants characterised by cooling medium

Abstract

A fan case assembly is adapted to extend around blades of a fan rotor included in a gas turbine engine. The fan case assembly includes an annular case that extends around an axis, a fan track liner coupled to the annular case and extending circumferentially at least partway about the axis, and a bolting arrangement that couples the fan track liner to the annular case.

IPC Classes  ?

• F01D 21/04 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
• F01D 25/24 - Casings; Casing parts, e.g. diaphragms, casing fastenings
• 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
• F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part

Abstract

In some examples, a gas turbine engine including a high-pressure (HP) spool assembly including a HP shaft, a HP compressor and HP turbine; a lower pressure (LP) spool assembly including a LP shaft and LP turbine; a motor-generator coupled to the LP shaft; and a controller. The controller is configured to control the motor-generator to operate in a motor mode to apply torque the LP shaft during a starting of the HP spool assembly, and control the motor-generator to operate in a generator mode for a least a period of time following the starting of the HP spool assembly.

IPC Classes  ?

• F02C 7/268 - Starting drives for the rotor
• F02C 6/20 - Adaptations of gas-turbine plants for driving vehicles
• F02C 6/00 - Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
• F02C 9/00 - Controlling gas-turbine plants; Controlling fuel supply in air-breathing jet-propulsion plants

Abstract

A method of assembling a gas turbine engine is disclosed herein. The method comprises providing a set of standard axial compressor stages. Each axial compressor stage included in the set of standard axial compressor stages includes a rotor having a plurality of blades configured to rotate about an axis and a stator having a plurality of stator vanes.

IPC Classes  ?

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

Abstract

A method of maintaining at least one gas turbine engine includes monitoring a compressor of the gas turbine engine. The compressor includes a compressor case at least partially defining a flow path, a plurality of stages and a vane actuator system configured to move at least one of the stages. The vane actuator system includes a vane mover having one or more slots formed therein and configured to actuate the at least one stage. The vane mover may be replaced after the gas turbine engine has experienced engine degradation.

IPC Classes  ?

• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes

Abstract

An airfoil for use in a gas turbine engine is formed to define a cavity formed in the airfoil. The airfoil further includes at least one obstructing member arranged within the cavity and a magnetorheological fluid disposed in the cavity. A viscosity of the magnetorheological fluid increases in response to a magnetic field being generated proximate to the fluid in response to the airfoil experiencing an aeromechanic response or vibrations. As such, the obstruction of the movement of the thicker fluid by the obstructing member dampens the vibrations of the airfoil and reduces negative effects of a dynamic response of the airfoil.

IPC Classes  ?

• F01D 5/16 - Form or construction for counteracting blade vibration
• F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades

Abstract

An instrumentation assembly configured to measure properties of an engine exhaust stream is disclosed in this paper. The instrumentation assembly may include an outer support ring that extends around a central axis, an inner support ring arranged radially inward of the outer support ring around the central axis, and a plurality of instrumentation rake assemblies. The plurality of instrumentation rake assemblies extends from the outer support ring to the inner support ring across an annular passageway defined between the outer support ring and the inner support ring configured to carry the engine exhaust stream.

IPC Classes  ?

• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
• F01D 17/24 - Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical electrical
• F01D 17/02 - Arrangement of sensing elements

Abstract

A system includes a flow battery and a temperature control system. The flow battery is configured to thermally manage a thermal load. In some embodiments, the flow battery is also configured to electrically power the thermal load. The temperature control system is configured to cool electrolyte in the flow battery in response to the thermal load being inactive.

IPC Classes  ?

• H01M 8/04029 - Heat exchange using liquids
• H01M 8/18 - Regenerative fuel cells, e.g. redox flow batteries or secondary fuel cells

Abstract

An instrumentation assembly configured to measure properties of an engine exhaust stream is disclosed in this paper. The instrumentation assembly may include an outer support ring that extends around a central axis, an inner support ring arranged radially inward of the outer support ring around the central axis, and a plurality of instrumentation rake assemblies. The plurality of instrumentation rake assemblies extends from the outer support ring to the inner support ring across an annular passageway defined between the outer support ring and the inner support ring configured to carry the engine exhaust stream.

IPC Classes  ?

• G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
• F01D 17/24 - Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted the operation or power assistance being predominantly non-mechanical electrical
• G01M 17/02 - Tyres
• F01D 21/00 - Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
• F01D 25/28 - Supporting or mounting arrangements, e.g. for turbine casing
• G01M 15/02 - Testing of engines - Details or accessories of testing apparatus

Abstract

An endwall assembly disposed at one end of a vane assembly may comprise an endwall spar that includes an cold side, an hot side, a leading edge, a trailing edge, and an axis extending from the leading edge to the trailing edge perpendicular to the leading edge. The endwall assembly may include a coversheet on the hot side of the endwall spar and a cooling channel that includes a cooling fluid inlet disposed in the endwall spar, and a cooling fluid outlet. The endwall assembly may include a structure protruding from the cold side of the endwall spar, wherein the structure is located between the cooling fluid inlet and the cooling fluid outlet along the axis; and a cooling fluid source cavity on the cold side of the wall, the cooling fluid source cavity in fluid communication with the cooling fluid channel via the cooling fluid inlet.

IPC Classes  ?

• F01D 5/18 - Hollow blades; Heating, heat-insulating, or cooling means on blades
• F01D 9/06 - Fluid supply conduits to nozzles or the like
• F01D 25/12 - Cooling

Abstract

A rotating machine including a thrust bearing configured to receive an axial thrust exerted by a rotor. The thrust bearing may be configured to transfer the axial thrust from the rotor to a housing or other structural component of the rotating machine using a plurality of ball bearings. The rotating machine includes a magnetic apparatus configured to cause the rotating machine to exert an axial force on the thrust bearing in the direction of the axial thrust of the rotor, such that the magnetic apparatus loads the ball bearings in the direction of the axial thrust. The magnetic apparatus may be configured to generate a magnetic field causing a first magnetic component of the magnetic apparatus to repel or attract a second magnetic component of the apparatus. The first magnetic component may be configured to rotate relative to the second magnetic component.

IPC Classes  ?

• F16C 25/08 - Ball or roller bearings self-adjusting
• F01D 25/16 - Arrangement of bearings; Supporting or mounting bearings in casings
• F16C 39/06 - Relieving load on bearings using magnetic means
• F16C 32/04 - Bearings not otherwise provided for using magnetic or electric supporting means
• F16C 27/04 - Ball or roller bearings, e.g. with resilient rolling bodies
• F16C 19/16 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls

Abstract

A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.

IPC Classes  ?

• F04D 29/44 - Fluid-guiding means, e.g. diffusers
• F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F01D 15/00 - Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
• F04D 1/00 - Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
• F01D 5/00 - Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members

Abstract

An article may include a substrate, such as a silicon-containing ceramic matrix composite, an environmental barrier coating (EBC) layer on the substrate, and a CMAS-resistant EBC layer on the EBC layer. The EBC layer may include at least one rare-earth disilicate (REDS). The CMAS-resistant EBC layer may include at least one rare-earth monosilicate (REMS) configured to react with CMAS to form crystalline reaction products. The CMAS-resistant EBC layer may include a plurality of vertical cracks extending from a surface of the CMAS-resistant EBC layer at least partially into the CMAS-resistant EBC layer. Additionally, or alternatively, the EBC layer may include a plurality of vertical cracks extending from a surface of the EBC layer into at least a portion of the EBC layer.

IPC Classes  ?

• C04B 41/52 - Multiple coating or impregnating
• C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
• C04B 41/00 - After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
• C04B 41/50 - Coating or impregnating with inorganic materials
• C04B 41/89 - Coating or impregnating for obtaining at least two superposed coatings having different compositions
• C04B 41/87 - Ceramics

Abstract

Fuel injectors having a fuel-air heat exchange system and methods thereof for use in a gas turbine engine. The fuel-air heat exchanger allows heat transfer between a flow of cooling air used to cool components of the engine and a flow of fuel used to drive the engine to transfer heat to the flow of fuel and cool the cooling air.

IPC Classes  ?

• F02C 7/224 - Heating fuel before feeding to the burner
• F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Abstract

Cooling systems and methods of operation are provided. The cooling system may include a two-phase pumped loop (TPPL). The two-phase pumped loop may include, a receiver, a pump downstream from the receiver, a heat load downstream from the pump, a TPPL tee downstream from the heat load, a TPPL check valve downstream from the TPPL tee, and a heat exchanger downstream from the TPPL check valve and upstream from the receiver. The cooling system may further include a vapor cycle system (VCS) loop. The vapor cycle system loop may include the receiver, a compressor downstream from a vapor outlet of the receiver, a compressor check valve downstream from the compressor and upstream of the heat exchanger, the heat exchanger, and the heat load downstream from a liquid outlet of the receiver.

IPC Classes  ?

• F25B 41/22 - Disposition of valves, e.g. of on-off valves or flow control valves between evaporator and compressor
• F25B 25/00 - Machines, plants or systems, using a combination of modes of operation covered by two or more of the groups
• F25B 49/02 - Arrangement or mounting of control or safety devices for compression type machines, plants or systems
• B64D 13/06 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned

Abstract

An electronics cabinet cooling system may include multiple cabinet heat exchangers mounted at an air discharge of respective different electronic cabinets. Heat from a flow of air heated by electronic components in the electronic cabinets may be received by respective cabinet heat exchangers. A liquid refrigerant flowing through the heat exchangers in parallel may be at least partially changed from liquid to gas and absorb the heat from the flow of air. A three-way tee in a common outlet header downstream from the cabinet heat exchangers may direct the gas refrigerant to a condenser and the liquid refrigerant to a receiver. The condenser may condense the gas refrigerant to liquid refrigerant, which may be routed to the receiver.

IPC Classes  ?

• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating

Abstract

A turbine wheel for a gas turbine engine including a compressor impeller and a radial inflow turbine integral to or attached to the compressor impeller is provided. A compressor turbine wheel including features to increase surface area of a surface of the compressor impeller and/or the radial inflow turbine and/or a passage to flow air between the compressor impeller and the radial inflow turbine is further provided. Methods for cooling radial inflow turbines integral to compressor impellers are further provided.

IPC Classes  ?

• F01D 5/04 - Blade-carrying members, e.g. rotors for radial-flow machines or engines
• F01D 5/02 - Blade-carrying members, e.g. rotors
• F01D 25/12 - Cooling

Abstract

A bearing lubrication system includes a bearing assembly comprising a duplex bearing including an outer ring, an inner ring positioned radially inward from the outer ring, and two sets of circumferentially distributed rolling elements between the inner and outer rings. The bearing assembly further includes a housing radially surrounding the duplex bearing and including a lubricant flow passage in fluid communication with a source of lubricant. A flow orifice is located downstream of the lubricant flow passage for jetting the lubricant into the duplex bearing. The flow orifice has an axial location between the two sets of rolling elements.

IPC Classes  ?

• F16C 33/66 - Special parts or details in view of lubrication
• F16C 33/60 - Raceways; Race rings divided
• F16C 19/18 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with two or more rows of balls

Abstract

A gas turbine engine includes a sump housing, an electric generator, and a shaft assembly and includes features for directing lubrication fluid away from the electric generator. The sump housing is configured to collect the lubrication fluid and air used in the gas turbine engine. The electric generator is located in the sump housing and configured to produce electric energy during use of the gas turbine engine. The shaft assembly extends through the electric generator and may be coupled with the electric generator.

IPC Classes  ?

• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• F02C 7/06 - Arrangement of bearings; Lubricating
• F02C 7/26 - Starting; Ignition

Abstract

An example hybrid aircraft propulsion system includes one or more power units configured to output electrical energy onto one or more electrical busses; a plurality of propulsors; and a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from at least one of the one or more electrical busses.

IPC Classes  ?

• B64D 27/02 - Aircraft characterised by the type or position of power plant
• B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
• F01D 15/10 - Adaptations for driving, or combinations with, electric generators
• 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

Abstract

A power-generation system for a nuclear reactor includes a power unit, a reactor heat exchanger, and an auxiliary combustion system. The power unit produces compressed air that is heated by the reactor heat exchanger. The auxiliary combustion system includes an auxiliary combustor located external to the power unit and fluidly connected with the compressed air to increase the temperature of the compressed air.

IPC Classes  ?

• F02C 1/05 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy
• F02C 6/18 - Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
• F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases
• G21D 1/02 - Arrangements of auxiliary equipment
• G21D 3/02 - Manual control
• G21D 1/00 - NUCLEAR POWER PLANT - Details of nuclear power plant
• F02C 6/16 - Gas-turbine plants having means for storing energy, e.g. for meeting peak loads for storing compressed air

Abstract

A power-generation system for a nuclear reactor includes a power unit, a heat exchanger, and a temperature control system. The power unit produces compressed air that is heated by the nuclear reactor via the heat exchanger. The temperature control system includes a heat transfer fluid and a heat exchanger fluidly connected with the compressed air to transfer heat between the compressed air and heat transfer fluid to control the power level of the power unit.

IPC Classes  ?

• G21D 3/00 - Control of nuclear power plant
• G21C 15/12 - Arrangement or disposition of passages in which heat is transferred to the coolant, e.g. for coolant circulation through the supports of the fuel elements from containment vessel
• G21C 15/253 - Promoting flow of the coolant for gases, e.g. blowers
• G21C 15/243 - Promoting flow of the coolant for liquids

Abstract

A power generation system for a nuclear reactor includes an externally-heated turbine engine, a reactor heat exchanger, and a heat recuperating system. The externally-heated turbine engine produces compressed air that is heated by the reactor heat exchanger. The heat recuperating system includes a heat exchanger thermally connected to the externally-heated turbine engine to transfer heat to the compressed air to supplement the reactor heat exchanger.

IPC Classes  ?

• F02C 1/05 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly characterised by the type or source of heat, e.g. using nuclear or solar energy
• F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases
• F02C 6/18 - Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
• F02C 1/04 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid the working fluid being heated indirectly
• F01K 3/18 - Plants characterised by the use of steam or heat accumulators, or intermediate steam heaters, therein having heaters
• F02C 6/16 - Gas-turbine plants having means for storing energy, e.g. for meeting peak loads for storing compressed air
• F22B 1/18 - Methods of steam generation characterised by form of heating method by exploitation of the heat content of hot heat carriers the heat carrier being a hot gas, e.g. waste gas such as exhaust gas of internal-combustion engines

Abstract

A weapons system includes a high-energy beam unit and a power and thermal management system. The high-energy beam unit is configured to discharge high-energy beams. The power and thermal management system is configured to supply power to the high-energy beam unit and to manage the temperature of the high-energy beam unit.

IPC Classes  ?

• H01S 3/04 - Arrangements for thermal management
• F41H 13/00 - Means of attack or defence not otherwise provided for
• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating

Abstract

A variable exhaust nozzle for use with a gas turbine engine includes an outer shroud and an inner plug that can move relative to the outer shroud. The relative movement of the inner plug and the outer shroud changes the shape of the variable exhaust nozzle from one that converges in area to one that converges and then diverges in area.

IPC Classes  ?

• F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• F02K 1/08 - Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone

Abstract

The disclosure describes an example technique that includes cold spraying first particles and second particles of a metal alloy on at least a portion of a surface of a substrate to form a deposit on the surface of the substrate. The first and second particles have been subjected to different heat treatments prior to cold spraying. Cold spraying involves accelerating the first particles and the second particles toward the surface of the substrate without melting or creating other thermally induced changes to a microstructure of the first and second particles. As a result, the first particles form a first, heat-treated component and the second particles form a second non-heat-treated or differently-heat-treated component, and the particles and substrate are not subject to a heat treatment during the cold spray process that may further modify their thermomechanical properties.

IPC Classes  ?

• C23C 24/04 - Impact or kinetic deposition of particles
• B22F 7/04 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite layers with one or more layers not made from powder, e.g. made from solid metal
• C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
• B22F 1/142 - Thermal or thermo-mechanical treatment

Abstract

A cooling system is provided including a two-phase pump loop and a vapor compression system. The two-phase pump loop cools a thermal load with a first coolant. The vapor compression system is configured to circulate a second coolant. The vapor compression system includes a liquid vapor separator which separates the second coolant into a liquid portion and a gaseous portion. The liquid vapor separator is a thermal energy storage for the two-phase pump loop. A condenser of the two-phase pump loop transfers heat from the first coolant to the liquid portion of the second coolant in the liquid-vapor separator.

IPC Classes  ?

• F25B 25/00 - Machines, plants or systems, using a combination of modes of operation covered by two or more of the groups

Abstract

A shaft assembly for a gas turbine engine includes a shaft, a bearing, and an annular sump cover. The shaft is arranged along an axis and configured to rotate about the axis. The bearing is coupled to the shaft to facilitate rotation of the shaft about the axis. The annular sump cover is fixed relative to the axis and is configured to allow a lubrication fluid and a buffer air into an air chamber formed between the shaft, the bearing, and the annular sump cover.

IPC Classes  ?

• F02C 7/18 - Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• F02C 7/06 - Arrangement of bearings; Lubricating
• F02C 7/28 - Arrangement of seals

Abstract

A rotor assembly adapted for a gas turbine engine includes a shaft, a wheel, and a retaining nut. The shaft extends along an axis and includes a first tapered surface. The wheel is arranged circumferentially around the shaft and includes a second tapered surface. The retaining nut is fastened to the shaft and applies an axial force to the wheel to couple the wheel with the shaft.

IPC Classes  ?

• F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
• F01D 5/02 - Blade-carrying members, e.g. rotors

Abstract

A bi-directional direct current (DC) solid state power controller (SSPC) architecture and control method. The SSPC protects a DC distribution system by isolating both the positive and negative buses independently in case of short circuit or ground fault. The SSPC architecture includes two self-heal interleaved capacitors and includes a fast, soft-charging control technique that provides line-isolated charging of the DC bulk capacitor to avoid inrush current when powering up the DC distribution system. The soft-charging function alternately charges one of the two interleaved capacitors, while the other capacitor discharges to the DC bulk capacitor. Repetitive switching results in a charging and discharging process that increases the voltage of the DC bulk capacitor prior to powering up the DC distribution system, while keeping the DC power source isolated from the load.

IPC Classes  ?

• H02H 7/26 - Sectionalised protection of cable or line systems, e.g. for disconnecting a section on which a short-circuit, earth fault, or arc discharge has occurred
• H02H 7/12 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from norm for rectifiers for static converters or rectifiers
• H02H 1/04 - Arrangements for preventing response to transient abnormal conditions, e.g. to lightning

Abstract

A gas turbine engine includes a bypass duct, a compressor, and a pyrotechnic gas conduit. The bypass duct conducts bypass air between an outer bypass wall and an inner bypass wall. The compressor includes an impeller to compress engine air. The pyrotechnic gas conduit is configured to conduct a gas onto the impeller to start the gas turbine engine.

IPC Classes  ?

• F02C 7/272 - Fluid drives generated by cartridges
• F02C 7/27 - Fluid drives

Abstract

A thermal battery system may be provided comprising: a vessel comprising a phase change material and a gas; a heat exchanger configured to transfer heat to and/or from the phase change material; a temperature sensor configured to detect an indication of a temperature of the gas; a pressure sensor configured to detect an indication of a pressure of the gas; and a processor configured to determine a state of charge of the thermal battery system from the indication of the pressure and the indication of the temperature of the gas.

IPC Classes  ?

• F28D 20/02 - Heat storage plants or apparatus in general; Regenerative heat-exchange apparatus not covered by groups or using latent heat
• G01K 17/00 - Measuring quantity of heat

Abstract

In some examples, this disclosure describes a method for detecting a fault in an electrical power system comprising a bus connected between a first solid state power converter and a second solid state power converter. The method includes receiving, at a controller of the electrical power system, a first signal indicating a current at a source side of the first solid state power converter, wherein the source side of the first solid state power converter is connected to a power source of the electrical power system. The method also includes receiving, at the controller, a second signal indicating a current at the bus and determining, by the controller, that a fault occurred in the electrical power system based on the first signal and further based on the second signal. The method further includes controlling the first solid state power converter in response to determining that the fault occurred.

IPC Classes  ?

• H02H 7/12 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from norm for rectifiers for static converters or rectifiers
• H02H 7/125 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from norm for rectifiers for static converters or rectifiers for rectifiers
• H02H 1/00 - EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS - Details of emergency protective circuit arrangements
• H02M 3/07 - Conversion of dc power input into dc power output without intermediate conversion into ac by static converters using resistors or capacitors, e.g. potential divider using capacitors charged and discharged alternately by semiconductor devices with control electrode

Abstract

A dual flow path exhaust assembly for use with a combined turbofan and ramjet engine includes a turbofan engine exhaust duct, a ramjet engine exhaust duct, a combined outlet, and door configured to move between an open position and a closed position to selectively isolate the turbofan engine exhaust duct from the combined outlet.

IPC Classes  ?

• F02K 1/82 - Jet pipe walls, e.g. liners
• F02K 7/16 - Composite ram-jet/turbo-jet engines
• F02C 7/224 - Heating fuel before feeding to the burner
• B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
• F02K 1/06 - Varying effective area of jet pipe or nozzle
• F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants

Abstract

A dual flow path exhaust assembly for use with a combined turbofan and ramjet engine includes a turbofan engine exhaust duct, a ramjet engine exhaust duct, a combined outlet, and door configured to move between an open position and a closed position to selectively isolate the turbofan engine exhaust duct from the combined outlet.

IPC Classes  ?

• F02K 1/06 - Varying effective area of jet pipe or nozzle
• B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
• F02K 1/80 - Couplings or connections
• F02K 1/62 - Reversing jet main flow by blocking the rearward discharge by means of flaps
• F02K 3/075 - 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 controlling flow ratio between flows
• F02K 1/12 - Varying effective area of jet pipe or nozzle by means of pivoted flaps
• F02K 7/16 - Composite ram-jet/turbo-jet engines
• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes

Abstract

A shaft assembly for use with a turbine engine includes a shaft and a magnetic mode control unit. The shaft extends along an axis and is configured to rotate about the axis. The magnetic mode control unit is configured to control deflection of the shaft as the shaft rotates about the axis.

IPC Classes  ?

• F01D 25/04 - Antivibration arrangements
• F01D 5/02 - Blade-carrying members, e.g. rotors

Abstract

The disclosure describes an apparatus for sealing a rotating machine, such as an electric machine or gas turbine engine. The apparatus includes a brush seal. The brush seal includes a plurality of first filaments and a plurality of electrically conductive filaments. The first filaments are configured to seal a lubricant within a bearing chamber or sump of the rotating machine. The plurality of electrically conductive filaments is configured to contact a shaft of the rotating machine and discharge a shaft voltage-induced current from the shaft to an external ground of the rotating machine.

IPC Classes  ?

• F16J 15/3288 - Filamentary structures, e.g. brush seals
• H02K 5/124 - Sealing of shafts
• H02K 11/40 - Structural association with grounding devices

Abstract

In some examples, an electrical power system includes a solid state power converter including a first set of switches on a source side of the solid state power converter and a second set of switches on a load side of the solid state power converter. The electrical power system also includes a power source connected to the source side of the solid state power converter and also includes a differential bus connected to the load side of the solid state power converter. The electrical power system further includes a controller configured to receive a first signal indicating a current at the source side and receive a second signal indicating a current at the load side. The controller is further configured to detect, based on a time derivative of the first signal and a time derivative of the second signal, a fault in the electrical power system.

IPC Classes  ?

• G01R 31/56 - Testing of electric apparatus
• H02H 1/00 - EMERGENCY PROTECTIVE CIRCUIT ARRANGEMENTS - Details of emergency protective circuit arrangements
• H02H 7/12 - Emergency protective circuit arrangements specially adapted for specific types of electric machines or apparatus or for sectionalised protection of cable or line systems, and effecting automatic switching in the event of an undesired change from norm for rectifiers for static converters or rectifiers
• G01R 19/165 - Indicating that current or voltage is either above or below a predetermined value or within or outside a predetermined range of values

Abstract

A seal system may include a static housing, a carbon seal positioned in the static housing, a runner having a sealing surface aligned with the carbon seal, a number of electromagnets positioned in the static housing, and a controller circuitry. The controller circuitry may control a variable flow of electric current to control an electromagnetic field respectively generated by each of the electromagnets. The controller circuitry may variably apply the electromagnetic field to move at least one of the carbon seal or the runner and correspondingly adjust an applied force loading of an interface of the carbon seal and the sealing surface of the runner.

IPC Classes  ?

• F02C 7/28 - Arrangement of seals
• F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
• F16J 15/34 - Sealings between relatively-moving surfaces with slip-ring pressed against a more or less radial face on one member
• F01D 25/18 - Lubricating arrangements

Abstract

A cooling system comprising a cooling circuit connecting a heat exchanger and a heat load. The cooling system comprising a first velocity fuse upstream of the heat exchanger or heat load and a second velocity fuse or valve downstream of the heat exchanger or heat load. The heat exchanger or heat load is dynamically isolated from the rest of the cooling system by the first velocity fuse or the second velocity fuse in response to a velocity of a flow of cooling fluid exceeding a respective velocity setting of the first velocity fuse or the second velocity fuse.

IPC Classes  ?

• F25B 25/00 - Machines, plants or systems, using a combination of modes of operation covered by two or more of the groups
• F25B 13/00 - Compression machines, plants or systems, with reversible cycle

Abstract

Thermal management systems for cooling high-power, low-duty-cycle thermal loads by rejecting heat from the thermal loads to the ambient environment are provided. The thermal management systems include a two-phase pump loop in fluid communication with a vapor compression system loop, evaporators disposed in parallel between the two-phase pump loop and the vapor compression system loop, and a thermal energy storage loop including a cold-temperature tank and a warm-temperature tank thermally coupled to the two-phase pump loop and the vapor-compression system loop. Methods of transferring heat from one or more thermal loads to an ambient environment are also provided.

IPC Classes  ?

• F25B 25/00 - Machines, plants or systems, using a combination of modes of operation covered by two or more of the groups
• F25B 7/00 - Compression machines, plants or systems, with cascade operation, i.e. with two or more circuits, the heat from the condenser of one circuit being absorbed by the evaporator of the next circuit
• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating
• F25B 41/22 - Disposition of valves, e.g. of on-off valves or flow control valves between evaporator and compressor

Abstract

An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.

IPC Classes  ?

• F02K 1/04 - Mounting of an exhaust cone in the jet pipe
• F02K 1/80 - Couplings or connections
• F02K 1/08 - Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone

Abstract

A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

IPC Classes  ?

• F02C 7/224 - Heating fuel before feeding to the burner
• B64D 37/34 - Conditioning fuel, e.g. heating
• F02C 7/12 - Cooling of plants
• B64D 33/10 - Radiator arrangement
• F02K 7/10 - Plants in which the working-fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines

Abstract

A thermal energy system for use with an aircraft includes a cooling loop and a cooler. The cooling loop includes a fluid conduit and a pump configured to move fluid through the fluid conduit to transfer heat from a heat source to the fluid in the fluid conduit to cool the heat source. The cooler includes an air-stream heat exchanger located in a duct and is in thermal communication with the fluid conduit to transfer heat between the fluid in the cooling loop and the air passing through the duct.

IPC Classes  ?

• B64D 33/10 - Radiator arrangement
• B64D 37/34 - Conditioning fuel, e.g. heating
• F02C 7/224 - Heating fuel before feeding to the burner
• F02C 7/12 - Cooling of plants

Abstract

A heat transfer system for controlling two or more heat loads, including a high transient heat load, is provided. The heat transfer system may include sensible-heat thermal energy storage. A method of transferring heat from two or more heat loads to an ambient environment is further provided.

IPC Classes  ?

• F25B 43/00 - Arrangements for separating or purifying gases or liquids; Arrangements for vaporising the residuum of liquid refrigerant, e.g. by heat
• F25B 5/04 - Compression machines, plants or systems, with several evaporator circuits, e.g. for varying refrigerating capacity arranged in series
• F25B 6/04 - Compression machines, plants or systems, with several condenser circuits arranged in series
• F25B 31/00 - Compressor arrangements
• F25B 40/02 - Subcoolers
• F25B 49/02 - Arrangement or mounting of control or safety devices for compression type machines, plants or systems

Abstract

A cooling apparatus includes: a first fluid flowpath including the following elements, in downstream flow sequence: a subcooler having a first side in fluid communication with the first fluid flowpath and a second side configured to be disposed in thermal communication with a source of cooling fluid; a flow control valve; a primary evaporator assembly including at least one primary evaporator configured to be disposed in thermal communication with a primary heat load; and a pressure regulator operable to maintain a refrigerant saturation pressure within the primary evaporator at a predetermined set point.

IPC Classes  ?

• F25B 40/00 - Subcoolers, desuperheaters or superheaters
• F25B 41/20 - Disposition of valves, e.g. of on-off valves or flow control valves
• F25B 6/00 - Compression machines, plants or systems, with several condenser circuits
• F25B 40/02 - Subcoolers

Abstract

Methods are provided for controlling thermal energy storage in a thermal energy management system that may operate in response to a variable or high transient heat load. Thermal energy management systems are also provided for controlling thermal energy storage that may operate in response to a variable or high transient heat load.

IPC Classes  ?

• F28D 17/00 - Regenerative heat-exchange apparatus in which a stationary intermediate heat-transfer medium or body is contacted successively by each heat-exchange medium, e.g. using granular particles
• F28D 20/02 - Heat storage plants or apparatus in general; Regenerative heat-exchange apparatus not covered by groups or using latent heat
• F24F 5/00 - Air-conditioning systems or apparatus not covered by group or
• F28D 20/00 - Heat storage plants or apparatus in general; Regenerative heat-exchange apparatus not covered by groups or

Abstract

An integrated circuit thermal management system includes an enclosure, a heat exchanger, an integrated circuit, a slide having a moveable slide body, an electromagnetic coil, a magneto caloric material and controller circuitry. The heat exchanger is positioned on a first side of the enclosure, and the integrated circuit is positioned on a second side of the enclosure with a temperature sensor configured to generate a temperature signal indicative of a temperature of the integrated circuit. The slide is disposed in the enclosure extending between the heat exchanger and the integrated circuit. The electromagnetic coil and the magnetocaloric material are included on the slide body. The controller is configured to control energization of the magnetic coil and movement of the magnetocaloric material on the slide body between the heat exchanger and the integrated circuit based on the temperature signal.

IPC Classes  ?

• H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating
• F28D 15/02 - Heat-exchange apparatus with the intermediate heat-transfer medium in closed tubes passing into or through the conduit walls in which the medium condenses and evaporates, e.g. heat-pipes
• H01F 1/01 - Magnets or magnetic bodies characterised by the magnetic materials therefor; Selection of materials for their magnetic properties of inorganic materials
• H01F 7/06 - Electromagnets; Actuators including electromagnets