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公开(公告)号：US12104530B2
公开(公告)日：2024-10-01
申请号：US17940035
申请日：2022-09-08
申请人： ROLLS-ROYCE plc
CPC分类号： F02C7/12 , F02C3/06 , F05D2220/323 , F05D2260/213 , F05D2260/40
摘要： An aircraft turbofan gas turbine engine includes a fan assembly, a compressor module, and a turbine module. An electric machine positioned downstream of the fan assembly is rotationally connected to the turbine module. The fan assembly is in fluid communication with the compressor module by an intermediate duct and includes a highest pressure fan stage having a plurality of fan blades defining a fan diameter. The compressor module includes a lowest pressure compressor stage having a row of rotor blades. An intermediate flow axis is defined joining a radially outer tip of a trailing edge of one of the fan blades of the highest pressure fan stage, and a radially outer tip of a leading edge of one of the rotor blades of a leading edge of a lowest-pressure compressor blade. An intermediate flow axis angle and the intermediate flow axis angle is from −20 to −30 degrees.
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公开(公告)号：US12104499B2
公开(公告)日：2024-10-01
申请号：US18330000
申请日：2023-06-06
CPC分类号： F01D25/10 , F01D25/12 , F02C7/12 , F05D2220/32 , F05D2260/20 , F05D2260/213
摘要： A method of regulating pressure in a thermal transport bus of a gas turbine engine, the method including: operating the gas turbine engine with the thermal transport bus having an intermediary heat exchange fluid flowing therethrough, the thermal transport bus including one or more heat source heat exchangers and one or more heat sink heat exchangers in thermal communication through the intermediary heat exchanger fluid; and adjusting a flow volume of the thermal transport bus using a variable volume device in fluid communication with the thermal transport bus in response to a pressure change associated with the thermal transport bus.
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公开(公告)号：US12092035B2
公开(公告)日：2024-09-17
申请号：US18148199
申请日：2022-12-29
发明人： Rajan Prakash , Shivani Agarwal
CPC分类号： F02C7/25 , F02C7/057 , F02C7/12 , F23N5/022 , F23N5/242 , F23N2231/06 , F23N2241/20
摘要： A fire detection system for a gas turbine system including fire risk zones is provided. The system includes a pipe intake port proximate to each of the fire risk zones within a gas turbine system enclosure, and a manifold in fluid communication with the pipe intake port. A temperature sensor is positioned in the manifold upstream of a cooling system. The cooling system reduces a temperature of a gas flow in the manifold, allowing use of an aspirating smoke detector. An aspirating smoke detector, which is downstream of the cooling system, draws in the gas flow and detects smoke in the gas flow. A controller generates a first alarm in response to the temperature sensor detecting a temperature of the gas flow exceeding a temperature threshold, or a second alarm in response to the aspirating smoke detector detecting smoke in the gas flow.
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公开(公告)号：US12092030B2
公开(公告)日：2024-09-17
申请号：US17940055
申请日：2022-09-08
申请人： ROLLS-ROYCE plc
发明人： Natalie C Wong , Jonathan A Cherry , Paul R Davies , David A Jones , Andrew J Newman , Benjamin J Sellers , Stephen J Bradbrook
CPC分类号： F02C7/12 , F02C6/20 , F02C7/32 , F05D2220/323 , F05D2220/76 , F05D2260/213
摘要： An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.
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公开(公告)号：US20240301827A1
公开(公告)日：2024-09-12
申请号：US18179660
申请日：2023-03-07
发明人： Alan W. Smith , Sara Karaffa
CPC分类号： F02C7/12 , F02C6/20 , F05D2220/323 , F05D2220/76 , F05D2230/60 , F05D2260/20
摘要： Gas turbine engines include an engine frame defining an inner radial surface, a shaft rotatably mounted in the engine frame along a longitudinal axis, and an electric machine that includes a rotor coupled to the shaft and a stator coupled to the engine frame and defining an outer radial surface. In some gas turbine engines, the engine frame includes inlet and outlet fluid passages, each extending to a portion of the inner radial surface. The portion of the inner radial surface of the engine frame is spaced from the outer radial surface of the stator to form an annular fluid passage around the stator of an electric machine. The annular fluid passage is configured to direct a cooling fluid around the stator to remove heat from the stator. Some gas turbine engines include two or more positioning keys configured to fix the stator relative to the engine frame.
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公开(公告)号：US20240263561A1
公开(公告)日：2024-08-08
申请号：US18567254
申请日：2022-06-23
发明人： Tomoko Morikawa , Satoshi Hada
CPC分类号： F01D9/041 , F01D25/12 , F02C7/12 , F05D2240/12 , F05D2260/20
摘要： A turbine stator vane comprising: a vane body; a shroud formed at an end of the vane body in a vane height direction; a fillet portion joining the vane body and the shroud; and a plurality of cooling holes in a bottom plate contacting a combustion gas flow path. The plurality of cooling holes connect to entry openings and downstream exit openings formed in the bottom plate. The entry openings and the exit openings are connected by cooling hole center lines having the same inclination with respect to an axial direction. The plurality of cooling holes constitute a set of cooling hole rows in which a linear first opening center line connecting the centers of the exit openings and a linear second opening center line connecting the centers of the entry openings are formed parallel to each other.
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7.发明公开公开(公告)号：US20240229718A9
公开(公告)日：2024-07-11
申请号：US18148199
申请日：2022-12-29
发明人： Rajan Prakash , Shivani Agarwal
CPC分类号： F02C7/25 , F02C7/057 , F02C7/12 , F23N5/022 , F23N5/242 , F23N2231/06 , F23N2241/20
摘要： A fire detection system for a gas turbine system including fire risk zones is provided. The system includes a pipe intake port proximate to each of the fire risk zones within a gas turbine system enclosure, and a manifold in fluid communication with the pipe intake port. A temperature sensor is positioned in the manifold upstream of a cooling system. The cooling system reduces a temperature of a gas flow in the manifold, allowing use of an aspirating smoke detector. An aspirating smoke detector, which is downstream of the cooling system, draws in the gas flow and detects smoke in the gas flow. A controller generates a first alarm in response to the temperature sensor detecting a temperature of the gas flow exceeding a temperature threshold, or a second alarm in response to the aspirating smoke detector detecting smoke in the gas flow.
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公开(公告)号：US12025029B1
公开(公告)日：2024-07-02
申请号：US18452922
申请日：2023-08-21
申请人： RTX CORPORATION
发明人： Thomas S. Heylmun , Cheng Gao , David J. Wasserman
CPC分类号： F01D5/18 , F01D5/282 , F01D11/00 , F02C3/04 , F02C7/12 , F05D2260/20 , F05D2300/6033
摘要： A vane assembly includes a vane having an outer platform with mount structure and an airfoil extending inwardly from the outer platform and formed of ceramic matrix composites (“CMC”). The vane having an internal cooling chamber. A metal baffle is received within the internal cooling chamber and extends beyond the outer platform. A bathtub seal has a central portion receiving the metal baffle. The metal baffle has a central chamber and cooling air holes to deliver cooling air into the internal cooling chamber. The bathtub seal having an inner wall and an outer wall outward of the metal baffle. The inner wall, the outer wall and a base wall define a bathtub seal chamber. The base wall is in contact with the outer platform. The vane is connected to the outer wall. The static structure is received within the bathtub seal chamber. A connection is configured to deliver pressurized air to the bathtub seal chamber. A gas turbine engine is also disclosed.
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公开(公告)号：US12025023B2
公开(公告)日：2024-07-02
申请号：US17968784
申请日：2022-10-18
发明人： Ravinder Yerram , Balakrishnan Ponnuraj , Vineet Sethi , Jose Emmanuel Guillen , Tho Vankhanh Nguyen , Douglas Alan Jones , Abhinash Reddy Konatham
CPC分类号： F01D25/305 , F01D9/06 , F01D25/30 , F01D9/065 , F02C7/12 , F05D2240/60 , F05D2260/608
摘要： One or more cooling systems for ventilating a turbine and rotary shaft of a gas turbine system is provided. The gas turbine system includes a gas turbine engine and a turbine exhaust collector in separate enclosures. A first cooling system includes an educator that sucks exhaust gas through a diffuser and directs it out of the turbine exhaust collector enclosure based on suction pressure created from the high velocity of exhaust gas. A second cooling system include struts that enable the exhaust gas to flow from the diffusers to a ventilation flow stack. A third cooling system includes exhaust gas sucked from an opening to a top duct based on suction pressure created from the rotation of the rotary shaft disposed about a coupling. A guideway associated with the third cooling system also directs the exhaust gas to flow to the top duct.
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公开(公告)号：US12006869B2
公开(公告)日：2024-06-11
申请号：US17959534
申请日：2022-10-04
CPC分类号： F02C7/12 , F02C9/18 , F05D2260/20
摘要： A heat exchanger includes an inlet plenum chamber, an outlet plenum chamber fluidly coupled to the inlet plenum chamber, and a plurality of intermediate plenum chambers disposed downstream from the inlet plenum chamber and upstream from the outlet plenum chamber. The plurality of intermediate plenum chambers includes a first intermediate plenum chamber, at least one tube bundle, and a first bypass valve fluidly coupled to the first intermediate plenum chamber. The first bypass valve is configured to control fluid flow rate from the first intermediate plenum chamber to the outlet plenum chamber.
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