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公开(公告)号：US12110820B2
公开(公告)日：2024-10-08
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：US20240280052A1
公开(公告)日：2024-08-22
申请号：US18649607
申请日：2024-04-29
IPC分类号： F02C7/06 , F01D25/16 , F01D25/24 , F02C3/14 , F02C7/18 , F02C7/20 , F04D29/053 , F04D29/056 , F04D29/32 , F04D29/54
CPC分类号： F02C7/06 , F01D25/162 , F01D25/246 , F02C3/14 , F02C7/18 , F02C7/20 , F04D29/053 , F04D29/056 , F04D29/321 , F04D29/541 , F05D2220/32 , F05D2240/35
摘要： The present disclosure generally relates to monolithic superstructures for supporting a rotating shaft coupled to a rotor relative to a stator. An integral superstructure supports the rotating component. The superstructure includes a bearing portion that contacts the shaft. A stator portion, is spaced a critical dimension radially outward, from the rotor. A first annular transfer portion extends axially forward from the bearing to the stator portion. A second annular transfer portion extends axially aft from the stator portion to a mounting flange. The mounting flange connects the superstructure to a frame. The superstructure maintains a critical dimension between the rotor and the stator as the temperature of the superstructure increases. The rotor may be a compressor impeller in a gas turbine engine and the stator may be an aero component that transfers air into a combustor.
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公开(公告)号：US11994296B2
公开(公告)日：2024-05-28
申请号：US18034119
申请日：2021-09-13
CPC分类号： F23R3/16 , F02C3/14 , F23R3/54 , F05D2250/82
摘要： A combustion device for an electricity production or energy cogeneration apparatus, the apparatus comprising a gas turbine supplied by the device, the device being suitable for a combustion regime of a “flameless” type, the device including: an outer tube; and a combustion tube forming a combustion zone for flameless combustion of a mixture of oxidizing air and fuel, the combustion tube being concentric with the outer tube, in communication with fuel-injection means, and with air-injection means arranged at a first end of the combustion tube, referred to as a front end, and which is closed by an end wall at a second end of the combustion tube, referred to as a rear end, the end wall being secured to the combustion tube and fluidtight, the fuel-injection means including at least a first orifice, referred to as a fuel-injection orifice, the air-injection means including at least a second orifice.
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公开(公告)号：US20230399996A1
公开(公告)日：2023-12-14
申请号：US17838167
申请日：2022-06-11
申请人： Isaac Erik Anderson
发明人： Isaac Erik Anderson
CPC分类号： F02K1/38 , F05D2220/323 , F02C7/04 , F02C3/14
摘要： The engine described herein utilizes an internal low pressure near the nozzle to draw fluid through a center section/duct of the engine and therefore through an upstream, cold, turbine. The fluid moving through this center duct-section experiences a pressure differential between the zone of the incoming fluid (which raises pressure upstream) and the low pressure zone generated near the nozzle. With fast-moving fluid around each side of this cold turbine duct, inducing a Venturi effect on the fluid passing through the duct, a low pressure is generated and therefore enacts work on the turbine. Using this method, turbine blades are not down stream of the hot combustion section and therefore can be made with light weight and low melting temperature material. With a cold section turbine, the engine can therefore be considerably lighter and cheaper to manufacture and maintain.
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公开(公告)号：US11841141B2
公开(公告)日：2023-12-12
申请号：US17072465
申请日：2020-10-16
CPC分类号： F23R3/54 , F02C3/145 , F02C7/18 , F23R3/06 , F23R3/46 , F01D9/023 , F05D2220/323 , F05D2240/35 , F23R3/50 , F23R2900/00017
摘要： An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.
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公开(公告)号：US11840958B2
公开(公告)日：2023-12-12
申请号：US17393508
申请日：2021-08-04
申请人： RTX Corporation
摘要： A gas turbine engine includes a fan positioned at an engine central longitudinal axis, and a fan drive turbine located at the engine central longitudinal axis and configured to drive rotation of the fan. A gas generator is non-coaxial with the fan drive turbine and operably connected to the fan drive turbine such that exhaust from the gas generator drives rotation of the fan drive turbine. An auxiliary power core is located at the engine central longitudinal axis, and one or more bleed passages connect the gas generator and the auxiliary power core. The one or more bleed passages are configured to selectably combine a bleed airflow from the gas generator and an auxiliary core airflow at the auxiliary power core to direct the combined airflow to the fan drive turbine to increase output of the fan drive turbine.
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公开(公告)号：US11834994B2
公开(公告)日：2023-12-05
申请号：US17623021
申请日：2020-08-06
发明人： Saki Matsuo , Satoshi Hada , Tomoko Morikawa , Hiroyuki Otomo
CPC分类号： F02C7/18 , F01D5/186 , F01D9/02 , F01D9/065 , F01D25/12 , F02C3/14 , F02C7/28 , F16J15/02 , F05D2220/32 , F05D2240/55 , F05D2240/81 , F05D2260/20 , F05D2260/201 , F05D2260/202
摘要： A turbine vane includes a blade body and a shroud. The shroud includes a gas path surface, a front end surface, a front end corner portion which is a corner portion between the gas path surface and the front end surface, a cavity defining surface which defines a cavity allowing cooling air to flow thereinto, a first air passage in which the cooling air flows, and a second air passage in which the cooling air flows. The first air passage includes a first inlet opened at the cavity defining surface and a first outlet opened at the front end corner portion. The second air passage includes a second inlet opened at the cavity defining surface and a second outlet opened at the front end surface.
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公开(公告)号：US20230313996A1
公开(公告)日：2023-10-05
申请号：US17811762
申请日：2022-07-11
摘要： An annular dome assembly for a combustor. The annular dome assembly includes an annular dome including one or more dome panels defining the annular dome. A first dome panel includes a dome upstream surface and a dome downstream surface opposite the dome upstream surface. One or more dome arms extend from the dome upstream surface. One or more apertures extend from the dome upstream surface to the dome downstream surface. The annular dome assembly also includes a deflector assembly including one or more deflector panels defining the deflector assembly. A first deflector panel includes a deflector upstream surface and a deflector downstream surface opposite the deflector upstream surface. One or more deflector arms extend from the deflector upstream surface. Each of the one or more deflector arms are mounted within a respective aperture of the annular dome.
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公开(公告)号：US11773772B2
公开(公告)日：2023-10-03
申请号：US17379052
申请日：2021-07-19
IPC分类号： F02C3/14
CPC分类号： F02C3/14 , F05D2220/32 , F05D2230/68
摘要： A system includes an annular track that surrounds the turbomachine. The annular track includes an upper rail portion and a lower rail portion removably coupled to one another. The system further includes a drive assembly operably coupled to the annular track. The drive assembly includes a drive chain that extends along the annular track. The system further includes a plurality of carts rotatably coupled to the annular track and connected to the drive chain such that operation of the drive assembly alters a circumferential position of the plurality of carts with respect to an axial centerline of the turbomachine. The system further includes a plurality of combustion can cradle assemblies each coupled to a respective cart of the plurality of carts. Each combustion can cradle assembly of the plurality of combustion can cradle assemblies is configured to removably couple to a combustion can of the one or more combustion cans.
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公开(公告)号：US11708973B2
公开(公告)日：2023-07-25
申请号：US16827284
申请日：2020-03-23
发明人： Michael J. O'Donnell
摘要： A fuel burner includes a tube extending from a first end to a second end and having an outer surface and an inner surface defining a central passage. The central passage is supplied at the first end with a mixture of air and combustible fuel pre-mixed upstream of the tube. The second end is closed by an end wall in a fluid-tight manner. The tube includes fluid directing structure for directing the pre-mixed mixture radially outward from the central passage to an exterior of the tube such that the pre-mixed mixture rotates radially about the central axis along the exterior of the tube.
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