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公开(公告)号：US12071895B2
公开(公告)日：2024-08-27
申请号：US17228794
申请日：2021-04-13
发明人： Gerardo Plata , Jorge Mario Rochin Machado , Ravinder Yerram , Balakrishnan Ponnuraj , Tho Vankhanh Nguyen
CPC分类号： F02C7/18 , F01D25/12 , F01D25/14 , F01D25/30 , F05D2260/201
摘要： A system for cooling a load coupling coupled to a gas turbine and disposed within an exhaust housing is provided. The system includes a shroud configured to be mounted about the load coupling, the shroud defining an inlet passage between the shroud and the load coupling and an outlet passage between the exhaust housing and the shroud. The system also includes a set of blades configured to couple to the load coupling. The set of blades are angled to draw air into the inlet passage as the set of blades rotate with the load coupling.
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公开(公告)号：US12044172B2
公开(公告)日：2024-07-23
申请号：US18148559
申请日：2022-12-30
发明人： Vaishnav Raghuvaran , Sesha Subramanian , Hari Krishna Meka , Vishnu Vardhan Venkata Tatiparthi , Raghuveer Chinta , Daniel O'Brien , Sai Raju Ippili , Michael Thomas Hogan
CPC分类号： F02C7/18 , F01D25/12 , F01D25/14 , F02C7/28 , F05D2220/32 , F05D2240/55 , F05D2260/201
摘要： A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.
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公开(公告)号：US12044136B2
公开(公告)日：2024-07-23
申请号：US17663507
申请日：2022-05-16
发明人： Louis Kobielski , Baris Uygun , Adam C. Felton
CPC分类号： F01D25/145 , F04D17/10 , F05D2220/40 , F05D2240/15
摘要： A rotary assembly is provided that may be operably connected to an engine. The rotary assembly may include a rotary device comprising a turbine wheel, a shaft connected to the turbine wheel, and a case that houses the shaft and the turbine wheel. The turbine wheel may receive exhaust gas from the engine which causes rotation of the turbine wheel and the shaft. The case may include an interior surface that defines a hollow volume in which the turbine wheel and the shaft are located. The case has a radial thickness extending from the interior surface to an exterior surface of the case. The case may include a lattice structure integrated within the radial thickness of the case. The lattice structure may include a repeating three-dimensional array of frame segments connected to one another at junctions and defining interstitial spaces between the frame segments.
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公开(公告)号：US12025016B2
公开(公告)日：2024-07-02
申请号：US18195446
申请日：2023-05-10
申请人： BorgWarner Inc.
发明人： Wolfram Schaefer
CPC分类号： F01D25/14 , F01D25/125 , F02C6/12 , F04D29/584 , F05D2220/40 , F05D2240/55
摘要： A housing includes a seal, a first portion for receiving a first axial portion of a rotor, and a second portion for receiving a second axial portion of the rotor. The first portion includes a first cooling system having a cooling channel through which cooling medium flows and a first cooling channel intake, and a first abutment face which surrounds the first cooling channel intake. The second portion includes a second cooling system having a cooling channel through which cooling medium flows and a second cooling channel intake, and a second abutment face which surrounds the second cooling channel intake. The housing portions are connected so that the abutment faces rest on each other and the cooling channel intakes form a transition surrounded by the abutment faces. The seal is arranged between the abutment faces and extends around the transition and is spaced apart from the cooling channel intakes.
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公开(公告)号：US20240191638A1
公开(公告)日：2024-06-13
申请号：US18581225
申请日：2024-02-19
发明人： Ashish Sharma , Tomasz Edward Berdowski , Maciej Czerwinski , Katarzyna Anna Mikolajczyk , Raymond Floyd Martell , Tomasz Jan Bulsiewicz
CPC分类号： F01D25/26 , F01D11/00 , F01D25/04 , F01D25/12 , F01D25/14 , B33Y80/00 , F05D2240/126 , F05D2240/14 , F05D2240/55 , F05D2250/182 , F05D2260/20 , F05D2260/96
摘要： Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example airfoil includes an outer wall having a first rib spaced apart from a second rib on a surface of the outer wall, and an inner wall surrounded by the outer wall, the inner wall having a third rib protruding from the inner wall towards the surface of the outer wall, an end of the third rib detachably coupled to a portion of the surface of the outer wall, the portion of the surface positioned between the first rib and the second rib, the third rib and at least one of the first rib or the second rib to at least partially seal a flow passage between the inner and outer walls.
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公开(公告)号：US20240175364A1
公开(公告)日：2024-05-30
申请号：US18432818
申请日：2024-02-05
CPC分类号： F01D5/147 , F01D25/12 , F01D25/14 , F23C7/02 , F05D2300/60 , F05D2300/70
摘要： A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.
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公开(公告)号：US20240117754A1
公开(公告)日：2024-04-11
申请号：US17961987
申请日：2022-10-07
发明人： Connor C. Perry , Xiaomei Fang , Bradley L. Paquin , Jacob Yochimowitz , Sushruth G. Kamath , Jun Cao
CPC分类号： F01D25/005 , F01D9/02 , F01D25/08 , F01D25/145 , F05D2220/32 , F05D2230/31 , F05D2240/10 , F05D2240/128 , F05D2240/14 , F05D2240/15 , F05D2260/231 , F05D2300/211
摘要： A gas turbine engine component includes a structural component having a surface, the structural component having an organic matrix composite material; and a cured thermal barrier layer on the surface, wherein the cured thermal barrier layer is a pre-ceramic layer including inorganic matrix containing silicon oxides reinforced with glass or quartz fibers.
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公开(公告)号：US11905842B2
公开(公告)日：2024-02-20
申请号：US17553513
申请日：2021-12-16
发明人： Ashish Sharma , Tomasz Edward Berdowski , Maciej Czerwiński , Katarzyna Anna Mikolajczyk , Raymond Floyd Martell , Tomasz Jan Bulsiewicz
IPC分类号： F01D25/26 , F01D11/00 , F01D25/04 , F01D25/12 , F01D25/14 , B33Y80/00 , F01D5/16 , F01D5/26 , F01D9/04 , F01D5/14 , F01D9/06 , F01D25/24
CPC分类号： F01D25/26 , F01D11/00 , F01D25/04 , F01D25/12 , F01D25/14 , B33Y80/00 , F05D2240/126 , F05D2240/14 , F05D2240/55 , F05D2250/182 , F05D2260/20 , F05D2260/96
摘要： Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.
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公开(公告)号：US11898517B2
公开(公告)日：2024-02-13
申请号：US17297079
申请日：2019-11-21
CPC分类号： F02K1/822 , F01D9/065 , F02C7/06 , F02K1/04 , F01D25/14 , F01D25/26 , F05D2220/323 , F05D2250/232 , F05D2260/205
摘要： A turbofan engine including an exhaust casing traversed by a primary flow and surrounded by a secondary flow and an outlet cone carried by this exhaust casing, the exhaust casing and the outlet cone together defining an internal space. The exhaust casing includes a hollow radial arm traversing the primary flow in order to convey part of the secondary flow so as to form a cooling flow for supplying the internal space, and the outlet cone is terminated by an opening for discharging the cooling flow.
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公开(公告)号：US11879347B2
公开(公告)日：2024-01-23
申请号：US17919184
申请日：2021-04-13
发明人： Benoit Guillaume Silet , Stéphane Pierre Guillaume Blanchard , Fabien Stéphane Garnier , Thibaud Louis Zaia
CPC分类号： F01D25/14 , F01D25/12 , F05D2260/60
摘要： A turbomachine turbine casing that extend around an axis and includes an annular wall and a cooling device. The annular wall is provided with a casing hook which extends in radial protrusion from an inside of the annular wall. The casing hook allows a mounting, on the turbomachine turbine casing, of ring segments disposed circumferentially end to end around the axis. The cooling device includes a collector duct intended to convey cooling air, the collector duct extending circumferentially around the annular wall. The collector duct has a cooling air inlet and a cooling air outlet. The collector duct and the annular wall have a common portion, which delimits the collector duct and from which the corresponding casing hook extends.
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