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公开(公告)号：US12104539B2
公开(公告)日：2024-10-01
申请号：US17972720
申请日：2022-10-25
摘要： A gas turbine engine defines an axial direction and a radial direction and comprises a turbomachine having an unducted primary fan, a core engine a combustor casing enclosing a combustor and defining an outer surface, a core cowl surrounding at least a portion of the core engine. The outer surface of the core cowl defines a peak cowl diameter (D) in the radial direction, and the outer surface of the combustor casing defines a maximum combustor casing diameter (d) along the radial direction. The core engine defines an overall core axial length (L) along the axial direction and an under-core cowl axial length (L1) along the axial direction. The gas turbine engine defines a core cowl diameter ratio (CDR) equal to the peak cowl diameter (D) divided by the maximum combustor casing diameter (d) and a core cowl length ratio (CLR) equal to the under-core cowl axial length (L1) divided by the overall core axial length (L). The CDR is between 2.7 and 3.5 and the CLR is between 0.25 and 0.50.
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2.发明公开公开(公告)号：US20240287933A1
公开(公告)日：2024-08-29
申请号：US18114656
申请日：2023-02-27
发明人： Adam Gallagher
CPC分类号： F02C7/06 , B64D27/10 , B64D27/24 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/98
摘要： A hybrid electric propulsion system is provided that includes a thermal engine, at least one electric generator, at least one lubrication fluid pump, at least one electric motor, and a controller. The electric generator is driven by the thermal engine, and is configured to produce electrical power. The lubrication fluid pump is configured to provide a volumetric flow rate of lubrication fluid to at least one component of the thermal engine. The electric motor is configured to drive the lubrication fluid pump using electrical power from the electric generator. The controller is in communication with the electric motor and a memory device storing instructions, which instructions when executed cause the controller to control the electric motor to drive the lubrication fluid pump to produce lubrication fluid at a determined volumetric fluid flow rate to the at least one component of the thermal engine.
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公开(公告)号：US20240287917A1
公开(公告)日：2024-08-29
申请号：US18568168
申请日：2022-05-27
摘要： An assembly for an aircraft turbomachine (20), comprising an intermediate casing hub (30), an equipment support (40) having an upstream face (42) located downstream of the intermediate casing hub (30), and a transfer gear box (50) driving a power transmission shaft (54) configured to transmit mechanical power, taken off an engine shaft (17) of the turbomachine, to at least one upstream equipment item (46) mounted on the upstream face (42) of the equipment support (40), the upstream equipment item (46) comprising a structural element (462) attaching the equipment support (40) to the intermediate casing hub (30).
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公开(公告)号：US12071891B1
公开(公告)日：2024-08-27
申请号：US17899326
申请日：2022-08-30
申请人： ADG POWER, LLC
IPC分类号： F02C6/00 , F02C1/02 , F02C6/14 , F02C6/16 , F02C7/32 , F03B1/02 , F03B7/00 , F03B11/06 , F03B13/06 , F03B15/16 , F03B17/00 , H02K7/14 , H02K7/18 , H02K21/14 , H02K21/24 , H02P9/04 , H02P101/10
CPC分类号： F02C6/00 , F02C1/02 , F02C6/14 , F02C6/16 , F02C7/32 , F03B1/02 , F03B7/003 , F03B11/06 , F03B13/06 , F03B15/16 , F03B17/00 , F03B17/005 , H02K7/14 , H02K7/18 , H02K7/1823 , H02K7/183 , H02K21/14 , H02K21/24 , H02P9/04 , F05B2260/504 , H02P2101/10 , Y02E10/20
摘要： A buoyancy powered electrical generator. A source of compressed gas is provided. The gas, which may be air, is compressed using a conventional compressor. In one embodiment, the compressor is powered by a windmill, turbine, or other conventional means. The compressed gas may be stored in a tank for an indefinite period. If necessary, the tank may be transported to the generator via truck, train or other conventional transportation means. During generation, compressed gas is released into a series of hollow, flooded drums mounted on a wheel in a liquid filled chamber. Introducing gas into the drums closes a valve in the drums and evacuates liquid from the drums, causing the drums to become buoyant. The buoyant drums exert a buoyant force on the wheel, causing it to rotate. The wheel is connected to a rotor in a magnetic generator. Rotating the wheel turns the rotor, thereby generating electricity.
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公开(公告)号：US12060834B2
公开(公告)日：2024-08-13
申请号：US17314202
申请日：2021-05-07
申请人： RTX Corporation
CPC分类号： F02C7/32 , B64D27/16 , B64D27/24 , F01D15/10 , F01D19/02 , B64D27/026 , F05D2220/323 , F05D2220/76
摘要： An engine system of an aircraft includes an energy storage system, a gas turbine engine, and a controller. The gas turbine engine includes a low spool, a high spool, a low-spool generator operably coupled to the low spool, and a high-spool electric motor operably coupled to the high spool. The controller is configured to detect a braking condition of the aircraft, transfer power from the low-spool generator to the energy storage system based on the storage capacity state of the energy storage system, and transfer power to the high spool through the high-spool electric motor to support combustion in the gas turbine engine while a rotational speed of the low spool is reduced responsive to the low-spool generator extracting energy from the low spool.
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6.发明授权公开(公告)号：US12044181B1
公开(公告)日：2024-07-23
申请号：US18297589
申请日：2023-04-07
CPC分类号： F02C7/32 , F16M13/02 , F05D2260/30
摘要： An assembly for mounting an auxiliary component to an engine case for a gas turbine engine includes a support bracket and a locator. The locator includes a fusible guide pin extending at least partially into a first aperture disposed in the support bracket, and a catcher pin extending at least partially into a second aperture disposed in the support bracket. The fusible guide pin is configured to fracture to absorb energy while the catcher pin limits system displacement during and post an overload event, thus reducing the energy transmitted to the auxiliary component (e.g., a gearbox housing). The locator can further include an anti-rotation pin extending from the plate member and configured to be received by the auxiliary component. The anti-rotation pin prevents rotation of the locator, about a third pin of the locator, with respect to the auxiliary component when the fusible guide pin is broken.
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公开(公告)号：US20240228048A9
公开(公告)日：2024-07-11
申请号：US18493186
申请日：2023-10-24
摘要： An aircraft propulsion system having a variable airflow capture area is provided. The propulsion system includes a main propulsion source and an auxiliary propulsion source. In a first mode, the auxiliary propulsion source is stowed within an aerodynamic profile of the aircraft, and the main propulsion source provides all of the propulsion force for powering flight of the aircraft. In a second mode, the auxiliary propulsion source is deployed to augment the airflow capture area of the main propulsion source and increase an overall airflow capture area of the propulsion system. In the second mode, the auxiliary power source is operated by power extracted from the main propulsion source. The main propulsion source may include one or more low bypass ratio engines. The auxiliary power source may include one or more auxiliary thrust fans coupled at a plurality of locations on the aircraft.
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公开(公告)号：US12025061B2
公开(公告)日：2024-07-02
申请号：US17712747
申请日：2022-04-04
CPC分类号： F02C9/40 , F02C7/32 , F02C9/48 , F23R3/36 , F05D2220/323 , F05D2220/76 , F05D2270/304 , F05D2270/31
摘要： A method of operating a gas turbine engine is provided. The method includes: providing a flow of a primary fuel to a combustor of a turbomachine, the turbomachine including a compressor, a turbine, and a spool rotatable with the compressor and the turbine; receiving data indicative of a spool parameter of the spool; and modifying a flow of a secondary fuel to the combustor in response to the received data indicative of the spool parameter of the spool.
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公开(公告)号：US20240183314A1
公开(公告)日：2024-06-06
申请号：US18287745
申请日：2022-04-13
发明人： Philippe Jean René Marie BENEZECH , Alexis Thomas Valentin LONGIN , Pierre Anthony SICAIRE , Gabriel DARRIEUMERLOU
摘要： A liquid fuel supply system for an aircraft engine includes a fuel tank, a suction duct connected to the fuel tank and located higher than the fuel tank, an electric pump, a supply pump that is mechanically driven by an accessory gear box and an outlet of the supply pump being connected to a fuel supply circuit of the engine, and an air expulsion drain. The electric pump is in communication with the suction duct independently of the supply pump, the electric pump is in communication with the air expulsion drain, and the supply pump is in communication with the suction duct independently of the electric pump.
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公开(公告)号：US20240183283A1
公开(公告)日：2024-06-06
申请号：US18553819
申请日：2022-03-31
CPC分类号： F01D15/12 , B64D27/10 , F02C7/268 , F02C7/32 , F05D2220/76
摘要： A turbomachine including a gas generator endowed with a first shaft, a gear box, at least one reversible electric machine coupled to the gear box, and a free turbine endowed with a second shaft and rotationally driven by a gas stream of the gas generator and at least one accessory coupled to the accessory gear box, wherein the turbomachine includes a first mechanical coupling means configured to mechanically couple said first mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said first mechanical shaft from the accessory gear box in a second configuration, and a second mechanical coupling means configured to mechanically couple said second mechanical shaft to the accessory gear box in a first configuration and to mechanically uncouple said second mechanical shaft from the accessory gear box in a second configuration.
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