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公开(公告)号：US20240360784A1
公开(公告)日：2024-10-31
申请号：US18309023
申请日：2023-04-28
IPC分类号： F02C3/04
CPC分类号： F02C3/04
摘要： A propulsion system for an aircraft includes a fan that is rotatable about a fan axis, a core engine that is configured for generating a gas flow utilized to generate shaft power for driving the fan, a nacelle that surrounds the core engine and the fan, a condenser where water in the gas flow is condensed into a liquid form, an exhaust duct assembly where the gas flow exhausted from the core engine is directed to the condenser, an ejector duct where a portion of a bypass airflow is thermally communicated with the condenser to cool the gas flow, and an evaporator assembly that is in thermal communication with the exhaust duct where water recovered by the condenser is heated to generate a steam flow that is subsequently communicated to the core engine.
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公开(公告)号：US11781478B2
公开(公告)日：2023-10-10
申请号：US17571720
申请日：2022-01-10
摘要： An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.
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公开(公告)号：US20240271567A1
公开(公告)日：2024-08-15
申请号：US18108532
申请日：2023-02-10
发明人： Jesse M. Chandler
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F05D2260/213
摘要： An intercooler for a gas turbine engine can include a shell having a partial annular shape, the shell defining a duct comprising an inlet and an outlet, the shell defining a first flow path between the inlet and the outlet; a supply manifold disposed proximate the outlet of the duct and extending circumferentially around the shell; and an outlet manifold disposed proximate the inlet of the duct and extending circumferentially around the shell, the supply manifold in fluid communication with the outlet manifold through a heat transfer region in the duct.
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公开(公告)号：US11215197B2
公开(公告)日：2022-01-04
申请号：US16251133
申请日：2019-01-18
摘要： A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.
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公开(公告)号：US11970974B2
公开(公告)日：2024-04-30
申请号：US17570764
申请日：2022-01-07
CPC分类号： F02C7/20 , B64C7/02 , B64D27/12 , B64D29/06 , B64D29/08 , F02C7/06 , F02C7/14 , F02C7/32 , F05D2220/323 , F05D2230/72 , F05D2260/213 , F05D2260/4031 , F05D2260/98
摘要： A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.
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公开(公告)号：US20220403774A1
公开(公告)日：2022-12-22
申请号：US17716290
申请日：2022-04-08
摘要： A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.
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公开(公告)号：US20220349656A1
公开(公告)日：2022-11-03
申请号：US17854655
申请日：2022-06-30
摘要： A heat exchanger has arcuate inlet and outlet manifolds and a plurality of tube banks, each tube bank coupling one of the inlet manifold outlets to an associated one of the outlet manifold inlets. Each tube bank partially nests with one or more others of the tube banks and has: a first header coupled to the associated inlet manifold outlet and the associated the outlet manifold inlet; a second header; and a plurality of tube bundles each having a first end coupled to the associated first header and a second end coupled to the associated second header. A flowpath from the each inlet manifold outlet passes sequentially through flowpath legs formed by each of the tube bundles in the associated tube bank to exit the tube bank to the associated outlet manifold inlet.
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公开(公告)号：US20220136441A1
公开(公告)日：2022-05-05
申请号：US17570764
申请日：2022-01-07
摘要： A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.
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公开(公告)号：US12044171B1
公开(公告)日：2024-07-23
申请号：US18108532
申请日：2023-02-10
发明人： Jesse M. Chandler
IPC分类号： F02C7/18
CPC分类号： F02C7/18 , F05D2260/213
摘要： An intercooler for a gas turbine engine can include a shell having a partial annular shape, the shell defining a duct comprising an inlet and an outlet, the shell defining a first flow path between the inlet and the outlet; a supply manifold disposed proximate the outlet of the duct and extending circumferentially around the shell; and an outlet manifold disposed proximate the inlet of the duct and extending circumferentially around the shell, the supply manifold in fluid communication with the outlet manifold through a heat transfer region in the duct.
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10.发明授权公开(公告)号：US12000334B1
公开(公告)日：2024-06-04
申请号：US18119169
申请日：2023-03-08
发明人： Jon E. Sobanski , Jesse M. Chandler
CPC分类号： F02C3/30 , F02C7/12 , F05D2220/32 , F05D2260/213 , F05D2270/08
摘要： A turbine engine is provided that includes a fan section, a turbine engine core and a recovery system. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. A centerline axis of the turbine engine core is offset from a centerline axis of the turbine engine. The recovery system includes an evaporator module and a condenser module. A core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module from an inlet into the core flowpath to an exhaust from the core flowpath.
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