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1.发明公开公开(公告)号：US20240141833A1
公开(公告)日：2024-05-02
申请号：US17977680
申请日：2022-10-31
摘要： An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, and a flow control device. The air inlet duct includes an intake inlet of the air intake. The core flow duct includes a core flow outlet. The core flow duct extends between and to the air inlet duct and the core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct extends between and to the air inlet duct and the bypass flow outlet. The bypass flow duct includes an interior surface forming and surrounding a bypass flow passage through the bypass flow duct. The flow control device is disposed on the interior surface. The flow control device is configured to variably control an area of a cross-sectional flow area of the bypass flow passage.
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公开(公告)号：US10883414B2
公开(公告)日：2021-01-05
申请号：US16707362
申请日：2019-12-09
发明人： Jean Thomassin , Sebastien Bolduc , Bruno Villeneuve , Stephane Berube , Mike Fontaine , David Gagnon-Martin , Andre Julien , Mark Cunningham , Serge Lafortune , Pierre-Yves Legare
IPC分类号： F02B29/04 , F02C6/12 , F02C7/047 , F02C7/052 , F02C7/055 , F02C7/14 , F02C7/36 , F01C11/00 , F02B33/40 , F02B39/04 , F01C21/18 , F02M31/04 , F02M31/10 , F02B37/12 , F02B53/08 , F02B53/14 , F01C1/22
摘要： An engine assembly including an engine core including at least one internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, a compressor having an outlet in fluid communication with an inlet of the engine core, a first intake conduit in fluid communication with an inlet of the compressor and with a first source of air, a second intake conduit in fluid communication with the inlet of the compressor and with a second source of air warmer than the first source of air, and a selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit. A method of supplying air to a compressor is also discussed.
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公开(公告)号：US10533489B2
公开(公告)日：2020-01-14
申请号：US15708442
申请日：2017-09-19
发明人： Jean Thomassin , Sebastien Bolduc , Bruno Villeneuve , Stephane Berube , Mike Fontaine , David Gagnon-Martin , Andre Julien , Mark Cunningham , Serge Lafortune , Pierre-Yves Legare
IPC分类号： F02B29/04 , F01C1/22 , F01C11/00 , F01D13/00 , F02K5/00 , F02C6/12 , F02B33/34 , F02B41/10 , F02B53/00 , F02B61/04
摘要： A compound engine assembly including a common air conduit having an inlet in fluid communication with ambient air, a compressor, at least one internal combustion engine having an inlet in fluid communication with an outlet of the compressor, a turbine section having an inlet in fluid communication with an outlet of the at least one internal combustion engine, the turbine section configured to compound power with the at least one internal combustion engine, and at least one heat exchanger in fluid communication with the common air conduit, each of the at least one heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the common air conduit circulating therethrough. The compressor has an inlet in fluid communication with the common air conduit upstream of the at least one heat exchanger. The internal combustion engine may be a reciprocating engine.
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公开(公告)号：US10030581B2
公开(公告)日：2018-07-24
申请号：US15052189
申请日：2016-02-24
摘要： An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The air intake may comprise a scroll portion and a strutted portion configured to receive the flow of air from the intake duct and channel the flow of air toward the intake outlet. The strutted portion may comprise one or more vanes for interacting with the flow of air. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.
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公开(公告)号：US20240254942A1
公开(公告)日：2024-08-01
申请号：US18593232
申请日：2024-03-01
发明人： Eray Akcayoz , Mark Cunningham
IPC分类号： F02K1/40
CPC分类号： F02K1/40 , F05D2220/323 , F05D2250/51 , F05D2250/52 , F05D2250/71 , F05D2250/73
摘要： An exhaust duct of an aircraft engine includes an annular inlet conduit having an inlet central axis, and at least two outlet conduits in flow communication with the inlet conduit. The at least two outlet conduits are located non-parallel to the inlet central axis. Each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits. At least one of the outlet ports is non-circular in cross-sectional shape.
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公开(公告)号：US12000358B1
公开(公告)日：2024-06-04
申请号：US18109428
申请日：2023-02-14
发明人： Mark Cunningham , Eray Akcayoz
CPC分类号： F02K1/62 , F02K1/58 , F05D2220/323
摘要： An engine nacelle assembly includes a nacelle that defines a flow path between an intake end and an exhaust end, and a nozzle that is disposed at the exhaust end of the nacelle about a central axis. The nozzle includes opposing thrust reverser openings and thrust reverser doors. A cross-sectional area transverse to the central axis proximate a forward side of each of the opposing thrust reverser openings is oval shaped with an offset radius within offset arc segments that are aligned with the opposing thrust reverser openings and a first radius outside of the offset arc segment. The first radius is less than the offset radius.
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7.发明授权公开(公告)号：US11994064B2
公开(公告)日：2024-05-28
申请号：US17977722
申请日：2022-10-31
IPC分类号： F02C7/042
CPC分类号： F02C7/042 , F05D2220/323 , F05D2270/60
摘要： An air intake for an aircraft propulsion system includes an air inlet duct and a flow control device. The air inlet duct includes an interior surface and an intake inlet. The interior surface extends from the intake inlet. The interior surface forms and surrounds an inlet flow passage through the air inlet duct. The intake inlet includes a top side, a bottom side, a first lateral side, and a second lateral side. Each of the first lateral side and the second lateral side extend between and to the top side and the bottom side. The flow control device is disposed inside the air inlet duct at the first lateral side. The flow control device is configured to form an asymmetrical shape of the intake inlet at the first lateral side relative to the second lateral side.
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公开(公告)号：US11965460B1
公开(公告)日：2024-04-23
申请号：US17977737
申请日：2022-10-31
CPC分类号： F02C7/05 , F02C7/042 , F02C7/057 , F02C9/18 , F05D2220/323
摘要： An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, a splitter, and a flow control device. The air inlet duct includes an intake inlet and a gas path floor. The core flow duct includes a core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct includes the gas path floor. The splitter separates the core flow duct and the bypass flow duct. The flow control device is disposed on a portion of the gas path floor. The flow control device is configured to be selectively positioned to control an air flow path for air flowing through the air inlet duct, the core flow duct, and the bypass flow duct.
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公开(公告)号：US20240035393A1
公开(公告)日：2024-02-01
申请号：US17876854
申请日：2022-07-29
发明人： Damien Le Pape , Mark Cunningham
IPC分类号： F01D21/00
CPC分类号： F01D21/003 , F05D2220/323 , F05D2260/30 , F05D2270/3011
摘要： A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.
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公开(公告)号：US11867070B1
公开(公告)日：2024-01-09
申请号：US17876854
申请日：2022-07-29
发明人： Damien Le Pape , Mark Cunningham
IPC分类号： F01D21/00
CPC分类号： F01D21/003 , F05D2220/323 , F05D2260/30 , F05D2270/3011
摘要： A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.
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