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公开(公告)号：US12066188B2
公开(公告)日：2024-08-20
申请号：US17214730
申请日：2021-03-26
IPC分类号： F23R3/28
CPC分类号： F23R3/283 , F23R2900/00012
摘要： An assembly is provided for an engine. This engine assembly includes an engine structure and a fuel injector. The engine structure includes an injector aperture and a fuel supply passage. The injector aperture extends longitudinally through the engine structure along a centerline. The fuel supply passage extends laterally within the engine structure to the injector aperture. The fuel injector is mated with the injector aperture. The fuel injector includes a nozzle passage and a nozzle orifice. The nozzle passage extends longitudinally along the centerline within the fuel injector to the nozzle orifice. The nozzle passage is fluidly coupled with the fuel supply passage.
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公开(公告)号：US11754287B2
公开(公告)日：2023-09-12
申请号：US17018561
申请日：2020-09-11
CPC分类号： F23R3/30 , F23R3/045 , F05D2220/323
摘要： An apparatus is provided for a turbine engine. This apparatus includes a fuel conduit and a fuel nozzle. The fuel conduit includes a supply passage. The fuel nozzle includes a nozzle passage, an end wall and a nozzle orifice. The nozzle passage has a longitudinal centerline and extends longitudinally through the fuel nozzle along the longitudinal centerline from the end wall to the nozzle orifice. The nozzle passage is configured with a convergent portion and a throat portion. The nozzle passage converges radially inward towards the longitudinal centerline as the convergent portion extends longitudinally along the longitudinal centerline away from the end wall and towards the throat portion. The supply passage is fluidly coupled to the nozzle passage by a fuel aperture in the end wall. A centerline of the fuel aperture is angularly and laterally offset from the longitudinal centerline.
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公开(公告)号：US11753994B2
公开(公告)日：2023-09-12
申请号：US17962059
申请日：2022-10-07
CPC分类号： F02C7/222 , B23P15/26 , F28F9/0265 , B33Y80/00 , F28D2021/0021 , F28D2021/0026
摘要： An additively manufactured attritable engine includes a compressor section, a combustion section, a turbine section, and an engine case wall, which surrounds the compressor section, the combustion section, and the turbine section. The engine case wall includes a first cavity embedded in the engine case wall that defines an injector that is in fluid communication with the combustion section. The engine case wall includes a second cavity embedded within the engine case wall and defines a fuel feed passage that is in thermal communication through the exterior surface of the engine case wall.
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公开(公告)号：US20230265761A1
公开(公告)日：2023-08-24
申请号：US17675564
申请日：2022-02-18
CPC分类号： F01D5/18 , F01D25/12 , F02C7/12 , F05D2220/32 , F05D2260/20
摘要： An assembly is provided for a gas turbine engine. This assembly includes a compressor rotor, a turbine rotor and a cooling circuit. The compressor rotor includes a gas path surface. The turbine rotor is rotatable with the compressor rotor about a rotational axis. The cooling circuit includes an inlet in the gas path surface. The cooling circuit extends from the inlet, through the compressor rotor and into the turbine rotor.
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公开(公告)号：US11732656B2
公开(公告)日：2023-08-22
申请号：US17219207
申请日：2021-03-31
摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes a case structure and an air conduit. The case structure extends circumferentially about and axially along an axis. The air conduit has a conduit centerline, a conduit first end and a conduit second end. The air conduit extends longitudinally along the conduit centerline between the conduit first end and the conduit second end. The conduit first end is connected to the case structure at a first location. The conduit second end is connected to the case structure at a second location. The air conduit is displaced from the case structure longitudinally between the conduit first end and the conduit second end. At least a majority of the conduit centerline follows a non-straight trajectory.
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公开(公告)号：US20230041714A1
公开(公告)日：2023-02-09
申请号：US17962059
申请日：2022-10-07
摘要： An additively manufactured attritable engine includes a compressor section, a combustion section, a turbine section, and an engine case wall, which surrounds the compressor section, the combustion section, and the turbine section. The engine case wall includes a first cavity embedded in the engine case wall that defines an injector that is in fluid communication with the combustion section. The engine case wall includes a second cavity embedded within the engine case wall and defines a fuel feed passage that is in thermal communication through the exterior surface of the engine case wall.
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公开(公告)号：US11441451B2
公开(公告)日：2022-09-13
申请号：US17034854
申请日：2020-09-28
发明人： Lawrence A. Binek , Sean R. Jackson
摘要： An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine case, a first transceiver and a second transceiver. The turbine engine case includes a case wall and a waveguide. The waveguide is formed integral with the case wall. The waveguide includes a waveguide channel. The second transceiver is configured to be in signal communication with the first transceiver through the waveguide channel.
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公开(公告)号：US11421883B2
公开(公告)日：2022-08-23
申请号：US17019009
申请日：2020-09-11
摘要： An apparatus is provided for a turbine engine. This turbine engine apparatus includes a fuel nozzle. The fuel nozzle includes an airflow inlet, a nozzle orifice, a fuel passage and a swirler passage. The fuel passage is fluidly coupled with the swirler passage through a first fuel aperture in a wall between the fuel passage and the swirler passage. The swirler passage extends along a helical trajectory away from the airflow inlet and towards the nozzle orifice.
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公开(公告)号：US20220136409A1
公开(公告)日：2022-05-05
申请号：US17085494
申请日：2020-10-30
IPC分类号： F01D25/26
摘要： An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint.
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公开(公告)号：US11268404B2
公开(公告)日：2022-03-08
申请号：US16881781
申请日：2020-05-22
摘要： A hot section of a gas turbine engine includes a stator housing wall and an at least one insulating standoff attached to the stator housing wall, extending radially away from the stator housing wall. The hot section includes an accessory module attached to an opposite end of the at least one insulating standoff away from the stator housing wall.
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