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公开(公告)号：US11794912B2
公开(公告)日：2023-10-24
申请号：US17568254
申请日：2022-01-04
IPC分类号： B64D27/10 , H01M8/04111 , H01M8/04746 , H01M8/04992 , H01M8/04701 , F02C9/00 , B64D27/02
CPC分类号： B64D27/10 , F02C9/00 , H01M8/04111 , H01M8/04738 , H01M8/04776 , H01M8/04992 , B64D2027/026 , H01M2250/20
摘要： A gas turbine engine includes a fuel cell assembly including a fuel cell stack and defining a fuel cell assembly operating parameter, a fuel source, and a turbomachine. The turbomachine includes a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel from the fuel source and further configured to receive output products from the fuel cell stack. A controller is configured to perform operations including receiving data indicative of system operation conditions, determining a set of fuel cell operating conditions to move the system emission output into or maintain the system emission output within an emissions range, and controlling the fuel cell assembly operating parameter according to the determined set of fuel cell operating conditions.
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公开(公告)号：US11780597B2
公开(公告)日：2023-10-10
申请号：US17853332
申请日：2022-06-29
申请人： ROLLS-ROYCE plc
摘要： A propulsion system for an aircraft comprises a gas turbine engine; a plurality of fuel tanks arranged to contain different fuels to be used to power the gas turbine engine, wherein the fuels have different calorific values; and a fuel manager. The fuel manager is arranged to store information on the fuel contained in each fuel tank and to control fuel input to the gas turbine engine in operation by selection of a specific fuel or fuel combination from one or more of the plurality of fuel tanks based on thrust demand of the gas turbine engine such that a fuel with a lower calorific value is supplied to the gas turbine engine at lower thrust demand.
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公开(公告)号：US11777370B2
公开(公告)日：2023-10-03
申请号：US17597786
申请日：2020-07-24
申请人： SAFRAN HELICOPTER ENGINES , SAFRAN
CPC分类号： H02K7/1823 , B64D27/02 , B64D27/10 , B64D27/24 , F02C6/20 , H02K21/14 , B64D2027/026 , F05D2220/76
摘要： An aeronautical turbogenerator for hybrid electric propulsion includes a heat engine and an electrical generator coupled mechanically to the heat engine and including a rotor and a stator, the rotor extending in an axial direction and including a common magnetized rotor yoke comprising a plurality of permanent magnets defining at least three axially distributed movable annular rings, the stator including a magnetic stator yoke comprising a plurality of electrical windings defining axially and/or circumferentially distributed stationary sectors, at least two stationary sectors, one of which covers axially at least two movable annular rings, being arranged angularly so as not to mutually coincide and thus deliver at least two distinct and independent voltage levels.
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公开(公告)号：US11772788B1
公开(公告)日：2023-10-03
申请号：US17900474
申请日：2022-08-31
发明人： Uwe Waltrich , Stanley Buchert
IPC分类号： B64C29/00 , H05K7/20 , H02M7/537 , H05K7/14 , H02M7/00 , B64D35/04 , B64D27/10 , B60L15/02 , B64D27/24 , B64D27/02
CPC分类号： B64C29/0033 , B60L15/02 , B64D27/10 , B64D27/24 , B64D35/04 , H02M7/003 , H02M7/537 , H05K7/1427 , H05K7/209 , B60L2200/10 , B60L2210/30 , B64D2027/026
摘要： An electrical vertical takeoff and landing (eVTOL) aircraft includes an electrical propulsion unit that has a propeller or a fan configured to be driven to rotate by an electric motor arranged to receive electrical power from an inverter. The inverter includes a carrier substrate, and a converter commutation cell including a power circuit. The power circuit includes at least one power semiconductor switching element. Each power semiconductor switching element is comprised in a power semiconductor prepackage. A heat sink is arranged to remove heat from the respective power semiconductor prepackage. The heat sink is spaced apart from the carrier substrate to define a heat sink gap between the carrier substrate and the heat sink. A converter parameter φ, which is defined as a size of the heat sink gap divided by a maximum electric field strength in the heat sink gap, is less than or equal to 20 nm2/V.
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公开(公告)号：US20230278714A1
公开(公告)日：2023-09-07
申请号：US17684677
申请日：2022-03-02
IPC分类号： B64D27/24 , H01M8/2475 , H01M8/248 , B64D27/10 , F02C9/44
CPC分类号： B64D27/24 , H01M8/2475 , H01M8/248 , B64D27/10 , F02C9/44 , H01M2250/20 , B64D2027/026
摘要： An anti-stall system for an aircraft may be provided, where the aircraft includes a propulsion system including a fuel cell assembly and a combustion engine, the combustion engine including a compressor section having a compressor. The anti-stall system may include at least one sensor configured to sense data indicative of at least one operating parameter indicative of a compressor stall condition of the compressor; and a controller including a processor and a memory storing instructions that when executed by the processor cause the controller to determine that the at least one operating parameter has achieved a compressor stall condition threshold and execute an anti-stall action responsive to determining that the at least one operating parameter has achieved the compression stall condition threshold. The anti-stall action may be configured to adjust at least one fuel cell parameter.
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公开(公告)号：US20230257128A1
公开(公告)日：2023-08-17
申请号：US17670031
申请日：2022-02-11
发明人： Richard Freer , Dominik Quillet , David Rancourt
摘要： A method of operating a hybrid-electric propulsion system for an aircraft and a hybrid-electric propulsion system is provided. The method includes: a) providing at least one thermal engine sized to provide sufficient thrust to the aircraft for at least one flight mission independent of a second non-thermal engine source of thrust for the at least one flight mission; b) providing at least one electric motor powered by a non-hydrocarbon fuel burning electrical energy source, the at least one electric motor configured to provide thrust to the aircraft for the at least one flight mission; and c) selectively providing thrust during one or more segments of the at least one flight mission using the electric motor.
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公开(公告)号：US11724815B2
公开(公告)日：2023-08-15
申请号：US17575086
申请日：2022-01-13
申请人： The Boeing Company
IPC分类号： F02C7/36 , B64D27/24 , B64D27/10 , B64D41/00 , B64C13/28 , B64D47/00 , F02C6/20 , B64C21/08 , B64D27/02
CPC分类号： B64D27/24 , B64C13/28 , B64C21/08 , B64D27/10 , B64D41/00 , B64D47/00 , F02C6/20 , F02C7/36 , B64D2027/026 , B64D2041/005
摘要： A hybrid engine including features to meet aircraft thrust, passenger airflow, and fuel cell requirements. The engine includes a combustor burning the same fuel as the fuel cell. The engine has electric motors to utilize the power output of the fuel cell. The engine shafts have sprags to allow motors to drive the compressors and over run the turbines. The engine has variable flowpath geometry to bypass the combustor.
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公开(公告)号：US20230212988A1
公开(公告)日：2023-07-06
申请号：US17568099
申请日：2022-01-04
IPC分类号： B64D31/00 , B64D27/24 , H01M8/04701 , H01M8/04858 , B64D37/00 , B64D27/10 , B60L58/30 , B64D27/02
CPC分类号： B64D31/00 , B64D27/24 , H01M8/04701 , H01M8/04895 , B64D37/00 , H01M8/04925 , B64D27/10 , B60L58/30 , B64D2027/026 , H01M2250/20 , B60L2200/10
摘要： A propulsion system for an aircraft includes a fuel cell assembly, the fuel cell assembly including a fuel cell, and a turbomachine, the turbomachine including a compressor section, a combustor, and a turbine section arranged in serial flow order. The combustor is configured to receive a flow of fuel and further configured to receive output products from the fuel cell. A controller is configured to receive data indicative of an engine constraint of the turbomachine, determine that the engine constraint has achieved a fuel cell trim threshold; and perform a fuel cell corrective action with the fuel cell assembly in response to determining that the engine constraint has achieved the fuel cell trim threshold.
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公开(公告)号：US11685542B2
公开(公告)日：2023-06-27
申请号：US16891337
申请日：2020-06-03
发明人： Daniel Alan Niergarth , Randy M. Vondrell , Brandon Wayne Miller , Patrick Michael Marrinan , Lawrence Chih-Hui Cheung , Nikolai N. Pastouchenko
IPC分类号： B64D27/10 , B64D27/24 , B64D33/08 , F02K5/00 , F02C7/14 , F02C6/20 , B64C11/00 , B64C21/06 , F01D15/10 , F01D15/12 , F02K3/062 , F04D29/056 , F04D29/063 , F04D29/32 , F04D29/58 , B64D27/02
CPC分类号： B64D33/08 , B64C11/001 , B64C21/06 , B64D27/10 , B64D27/24 , F01D15/10 , F01D15/12 , F02C6/206 , F02C7/14 , F02K3/062 , F02K5/00 , F04D29/056 , F04D29/063 , F04D29/325 , F04D29/582 , B64D2027/026 , F05D2220/323 , F05D2260/213 , F05D2260/98 , Y02T50/60
摘要： A propulsion system for an aircraft having an aft end is provided herein. The propulsion system can include an electric propulsion engine defining a central axis. The electric propulsion engine can include an electric motor, a fan rotatable about the central axis of the electric propulsion engine by the electric motor, a bearing supporting rotation of the fan, and a thermal management system. The thermal management system can include a lubrication oil circulation assembly for providing the bearing with lubrication oil. The lubrication oil circulation assembly can be driven independently of a shaft of the electric propulsion engine.
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公开(公告)号：US11685539B2
公开(公告)日：2023-06-27
申请号：US17032154
申请日：2020-09-25
申请人： Rohr, Inc.
发明人： Brian A. Sherman
CPC分类号： B64D29/00 , B64D33/04 , F01D25/24 , F02K1/822 , B64D27/10 , B64D29/08 , F01D25/30 , F02C9/16
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inner structure that extends axially along and circumferentially about an axial centerline. The nacelle inner structure includes an internal compartment and a cowl. The internal compartment is configured to house a core of a gas turbine engine. The cowl is configured to form an outer radial periphery of the internal compartment. An aft end portion of the cowl is also configured to form an outer radial periphery of a compartment exhaust to the internal compartment. The aft end portion of the cowl includes a plurality of axial fingers arranged circumferentially about the axial centerline in an array.
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