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公开(公告)号：US12078102B2
公开(公告)日：2024-09-03
申请号：US17951972
申请日：2022-09-23
IPC分类号： F02C6/08 , F02C3/13 , F02C7/08 , F02C7/10 , F02C7/32 , F02C9/18 , F02C9/52 , F02G5/00 , F02K3/02
CPC分类号： F02C6/08 , F02C3/13 , F02C7/08 , F02C7/10 , F02C7/32 , F02C9/18 , F02C9/52 , F02G5/00 , F02K3/02
摘要： A gas turbine engine assembly including a tap that is at a location up stream of the combustor section for drawing a bleed airflow. An exhaust heat exchanger is configured to transfer thermal energy from the exhaust gas flow into the bleed airflow and communicate the heated bleed airflow into the turbine section where it is expanded to drive the turbine section.
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公开(公告)号：US12031478B2
公开(公告)日：2024-07-09
申请号：US17951991
申请日：2022-09-23
CPC分类号： F02C6/08 , F02C3/10 , F02C7/18 , F02C7/32 , F02C7/36 , F02C9/18 , F05D2220/323 , F05D2220/36
摘要： An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that is expanded through a turbine section for powering a primary propulsor. The aircraft propulsion system further includes a tap that is at a location upstream of the combustor section where a bleed airflow is drawn, a heat exchanger where the bleed airflow is heated by the gas flow, a power turbine through which heated bleed airflow is expanded to generate a work output, and a secondary propulsor that is driven by the work output that is generated by the power turbine.
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公开(公告)号：US20240109662A1
公开(公告)日：2024-04-04
申请号：US18538129
申请日：2023-12-13
发明人： Tony Ho , Louis J. Bruno , Aiden Coutin
CPC分类号： B64D13/06 , B60H1/3211 , F02C6/08 , B64D2013/0618 , F05D2220/32
摘要： An environmental control system includes an environmental control system pack having a trim outlet and a primary outlet. A trim medium is output from the trim outlet and a first medium is output from the primary outlet. An inlet of a mixing manifold is connected to the primary outlet of the at least one environmental control system pack. A trim heat exchanger is connected to the trim outlet and the at least one inlet of the environmental control system pack. Within the trim heat exchanger, the trim medium is arranged in a heat exchange relationship with a second medium. From the trim heat exchanger, the second medium is provided to an inlet of the least one environmental control system pack and the trim medium is mixed with a flow output from an outlet of the mixing manifold.
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公开(公告)号：US20240076034A1
公开(公告)日：2024-03-07
申请号：US17902261
申请日：2022-09-02
CPC分类号： B64C21/08 , F02C6/08 , B64C2230/06 , F05D2220/323 , F05D2260/605 , F05D2260/606
摘要： An assembly is provided that includes a regulator manifold and a regulator element. The regulator manifold includes an inlet passage, a first outlet passage and a second outlet passage. The inlet passage is configured to receive bleed gas from a core flowpath. The regulator element is within the regulator manifold and configured to pivot to a first position, a second position and an intermediate position between the first position and the second position. The regulator element is configured to fluidly couple the inlet passage with the first outlet passage in the first position. The regulator element is configured to fluidly couple the inlet passage with the second outlet passage in the second position. The regulator element is configured to fluidly decouple the inlet passage from the first outlet passage and the second outlet passage in the intermediate position.
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公开(公告)号：US20240035414A1
公开(公告)日：2024-02-01
申请号：US18241447
申请日：2023-09-01
发明人： Steven Mazur , Rex M. Little
摘要： 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.
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公开(公告)号：US11878810B2
公开(公告)日：2024-01-23
申请号：US17698525
申请日：2022-03-18
申请人： The Boeing Company
发明人： Scott Schorn , John Carl Szillat , David Scott Krug , Paul R. Tretow , Keith Douglas Choyke , Royal E. Boggs , Angela O'Gorman
CPC分类号： B64D41/00 , B64D13/06 , F02C6/08 , F02C7/32 , B64D2013/0611 , B64D2013/0618 , B64D2033/0213 , F05D2220/50
摘要： Auxiliary power systems, aircraft including the same, and related methods are disclosed herein. In one embodiment, the aircraft includes an airframe and an auxiliary power system that includes an auxiliary power unit (APU), an APU controller, and a bleed air temperature (BAT) sensor. The APU defines a bleed air outlet and is configured to regulate a BAT of a bleed air flow generated by the auxiliary power unit. The BAT sensor is positioned at a remote BAT location that is outside the bleed air outlet of the APU. In another embodiment, the auxiliary power system includes an APU configured to generate a bleed air flow, an APU controller configured to receive and transmit signals, and a BAT sensor suite configured to measure the BAT of the bleed air flow and to generate a BAT signal that is based, at least in part, on the BAT.
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公开(公告)号：US11852025B2
公开(公告)日：2023-12-26
申请号：US17760173
申请日：2021-03-15
CPC分类号： F01D25/12 , F01D5/081 , F01D9/065 , F01D17/141 , F01D17/145 , F02C6/08 , F02C9/18 , F02C3/13 , F05D2260/20 , F05D2270/3015 , F05D2300/50212
摘要： A turbo machine including a device for ventilating and pressurising a turbine rotor of a turbomachine having an axis, the device including at least one collection pipe suitable for collecting a fraction of the air circulating in a high-pressure compressor of the turbomachine and conveying it to a first inner chamber inside the turbomachine that communicates with a second inner chamber delimited by the turbine rotor, the first and second chambers being at least partially separated by a stationary shroud having the axis, wherein it includes at least one injector passing through the stationary shroud and having a cross-section that varies in response to a pressure difference between the first and second chambers.
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公开(公告)号：US11807379B2
公开(公告)日：2023-11-07
申请号：US16774778
申请日：2020-01-28
CPC分类号： B64D33/02 , B64D15/04 , F02C6/08 , B64D2033/0206 , B64D2033/0233 , B64D2033/0286 , F02C7/047 , F02K3/06 , F05D2220/323 , F05D2220/36
摘要： The nacelle can have an inlet portion having a duct wall and an outer skin, the duct wall being annular around an axis and having a surface forming a radially-outer delimitation to a gas path upstream of a fan area, the duct wall extending from a rounded inlet edge of the nacelle to the fan area, a cavity located inside the inlet portion, a compressed air inlet leading into the cavity, and an outlet fluidly connecting the cavity to the gas path, the outlet having a plurality of apertures disposed circumferentially around the duct wall, the apertures sloping circumferentially.
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公开(公告)号：US20230323810A1
公开(公告)日：2023-10-12
申请号：US18184008
申请日：2023-03-15
申请人： ROLLS-ROYCE plc
CPC分类号： F02C6/08 , B64D13/06 , B64D2013/0618 , F05D2260/205 , F05D2220/323
摘要： There is provided a gas turbine engine comprising a blower system for supplying pressurised air to an airframe via an airframe port. The blower system comprises a compressor configured to receive air from a bypass duct or a core of the gas turbine engine and to discharge compressed air into a delivery line extending from the compressor to the airframe port. The blower system also comprises a heat exchanger configured to transfer heat from the compressed air to a coolant and a valve arrangement configured to switch between operation of the blower system in a baseline mode and a cooling mode, the valve arrangement being configured to: selectively divert the compressed air within the delivery line to the heat exchanger for operation in the cooling mode; and/or selectively provide the coolant to the heat exchanger for operation in the cooling mode.
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公开(公告)号：US11773773B1
公开(公告)日：2023-10-03
申请号：US17874213
申请日：2022-07-26
发明人： Steven Mazur , Rex M. Little
摘要： 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.
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