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公开(公告)号：US20240162458A1
公开(公告)日：2024-05-16
申请号：US17984615
申请日：2022-11-10
发明人： Seung-Hyuck Hong , Richard L. Hart , Honggang Wang , Anil Raj Duggal , Michael Anthony Benjamin , Owen James Sullivan Rickey , Narendra Digamber Joshi , Hendrik Pieter Jacobus de Bock
IPC分类号： H01M8/04111 , F23R3/00
CPC分类号： H01M8/04111 , F23R3/002 , B64D2027/026
摘要： A combustion section includes a casing that defines a diffusion chamber. The combustion section further includes a combustion liner that is disposed within the diffusion chamber and that defines a combustion chamber. The combustion liner is spaced apart from the casing such that a passageway is defined between the combustion liner and the casing. The combustion section further includes a fuel cell assembly that is disposed in the passageway. The fuel cell assembly includes a fuel cell stack having a plurality of fuel cells. The plurality of fuel cells extend from an inlet end in fluid communication with the diffusion chamber to an outlet end extending through the combustion liner and in fluid communication with the combustion chamber.
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公开(公告)号：US11378277B2
公开(公告)日：2022-07-05
申请号：US15987070
申请日：2018-05-23
发明人： Narendra Digamber Joshi , Shawn David Wehe , ShihYang Hsieh , Changjin Yoon , Owen James Sullivan Rickey , Joseph Douglas Monty
摘要： A combustor includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.
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公开(公告)号：US20210190320A1
公开(公告)日：2021-06-24
申请号：US17195131
申请日：2021-03-08
发明人： Owen James Sullivan Rickey , Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Shashank Yellapantula
摘要： A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.
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公开(公告)号：US20210142921A1
公开(公告)日：2021-05-13
申请号：US16733497
申请日：2020-01-03
摘要： A turbine engine comprising a compressor section and a turbine section in serial flow arrangement defining a working air flow path with a heat exchanger in fluid communication the working air flow path, and a nuclear fuel in thermal communication with the heat exchanger and a release valve in fluid communication with the working air flow path.
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公开(公告)号：US20210039798A1
公开(公告)日：2021-02-11
申请号：US17078198
申请日：2020-10-23
IPC分类号： B64D27/24
摘要： Embodiments of a propulsion system are provided herein. In some embodiments, a propulsion system for an aircraft may include an electrical power supply; a motor coupled to the electrical power supply, wherein the electrical power supply provides power to the motor; and a fan disposed proximate a rear portion of an aircraft and rotatably coupled to the motor, wherein the fan is driven by the motor.
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公开(公告)号：US20200070961A1
公开(公告)日：2020-03-05
申请号：US16118878
申请日：2018-08-31
摘要： A flow control actuator includes a first side wall, a second side wall opposite and substantially parallel to the first side wall, an upstream wall mechanically coupled to upstream ends of the first and second side walls, and a downstream cap mechanically coupled to downstream ends of the first and second side walls. The first side wall, the second side wall, the upstream wall and the downstream cap collectively define an interior of the flow control actuator. An energy source is disposed in at least one of the first sidewall and the second sidewall. At least one fuel injector is disposed in the upstream wall, the first sidewall and/or the second sidewall for dispersing fuel into the flow control actuator. At least one air inlet is disposed in the upstream wall, the first sidewall and/or the second sidewall for introducing air into the flow control actuator. Fuel from fuel injector and air from the air inlet are ignited in the flow control actuator.
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公开(公告)号：US20200025216A1
公开(公告)日：2020-01-23
申请号：US16039621
申请日：2018-07-19
摘要： A combustion system includes at least one plasma actuator disposed along a substrate at a plasma location, and at least one fuel injector disposed along the substrate at an injection location. The fuel injector disperses fuel toward the plasma location. The plasma from plasma actuator ignites fuel from the fuel injector proximate the plasma location.
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公开(公告)号：US10480791B2
公开(公告)日：2019-11-19
申请号：US14447967
申请日：2014-07-31
发明人： Krishna Kumar Venkatesan , Joel Meier Haynes , Narendra Digamber Joshi , David James Walker , Junwoo Lim , Sarah Marie Monahan
摘要： A fuel injector to reduce NOx emissions in a combustor system. The fuel injector including a housing, at least one oxidizer flow path, extending axially through the fuel injector housing and defining therein one or more oxidizer flow paths for an oxidizer stream and a fuel manifold, extending axially through the fuel injector housing and defining therein one or more fuel flow path. The fuel manifold includes a forward portion and an aft portion including an aft face. A plurality of fuel injector outlets are defined in the aft portion, wherein the plurality of fuel injector outlets are configured to inject a fuel flow along a mid-plane of the fuel injector and away from a downstream wall. The fuel flow exiting the fuel manifold undergoes circumferential and radial mixing upon interaction with the oxidizer stream. Additionally disclosed is a combustor system including the fuel injector.
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公开(公告)号：US10371064B2
公开(公告)日：2019-08-06
申请号：US15041710
申请日：2016-02-11
IPC分类号： F02C9/20
摘要： A method of operating a gas turbine engine includes measuring an exhaust gas temperature of the gas turbine engine. A first stage turbine nozzle assembly of the gas turbine engine is adjusted to a first position. A firing temperature of the gas turbine engine is determined based on the exhaust gas temperature. The firing temperature is compared to a threshold value and a difference value is determined therefrom. If the difference value exceeds a threshold value, the first stage turbine nozzle assembly is adjusted to a second position such that the firing temperature is substantially equal to the threshold value.
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公开(公告)号：US10323532B2
公开(公告)日：2019-06-18
申请号：US15159678
申请日：2016-05-19
发明人： Nicholas Joseph Kray , Narendra Digamber Joshi , Samar Jyoti Kalita , Paul Marsland , Wayne Spence
摘要： The present disclosure generally relates to variable cellular structures, methods of making such cellular structures, and variable cellular flow discouragers for turbine engines for jet aircraft.
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