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公开(公告)号：US20170089205A1
公开(公告)日：2017-03-30
申请号：US14870853
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Christian Lee Vandervort , Krishan Lal Luthra , Ronald Scott Bunker , Joel Meier Haynes , Venkat Eswarlu Tangirala
CPC classification number: F01D5/186 , F01D25/32 , F02C3/34 , F02C6/003 , F02C7/185 , F05D2260/213 , F05D2260/61 , F05D2300/6033 , F23C9/08 , F23M2900/05004 , F23N2021/12 , F23R3/002 , F23R2900/03041 , F23R2900/03341 , Y02E20/14 , Y02E20/16
Abstract: A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.
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公开(公告)号：US20160252019A1
公开(公告)日：2016-09-01
申请号：US15041710
申请日：2016-02-11
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Krishan Lal Luthra
IPC: F02C9/20
CPC classification number: F02C9/20 , F05D2270/11 , F05D2270/303
Abstract: 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.
Abstract translation: 一种操作燃气涡轮发动机的方法包括测量燃气涡轮发动机的排气温度。 燃气涡轮发动机的第一级涡轮喷嘴组件被调节到第一位置。 基于排气温度来确定燃气轮机的燃烧温度。 将烧制温度与阈值进行比较，并从其确定差值。 如果差值超过阈值，则将第一级涡轮喷嘴组件调节到第二位置，使得点火温度基本上等于阈值。
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公开(公告)号：US20150380999A1
公开(公告)日：2015-12-31
申请号：US14317294
申请日：2014-06-27
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Manoj Ramprasad Shah , James William Bray , Randy Marinus Vondrell , Kurt David Murrow , Jeffrey Anthony Hamel , Samuel Jacob Martin
CPC classification number: H02K1/28 , H02K1/182 , H02K1/278 , H02K1/30 , H02K21/026 , H02K21/24 , H02K49/108 , Y02E10/725
Abstract: A permanent magnet machine and a rotor assembly for the permanent magnet machine. The permanent magnet machine includes a stator assembly including a stator core configured to generate a magnetic field and extending along a longitudinal axis with an inner surface defining a cavity and a rotor assembly including a rotor core and a rotor shaft. The rotor core is disposed inside the stator cavity and configured to rotate about the longitudinal axis. The rotor assembly further including a plurality of permanent magnets for generating a magnetic field which interacts with the stator magnetic field to produce torque. The permanent magnets are disposed within one or more cavities formed in a sleeve component. The sleeve component configured to include a plurality of cavities or voids therein and thus provide minimal weight to the permanent magnet machine. The permanent magnet machine providing increased centrifugal load capacity, increased power density and improved electrical performance.
Abstract translation: 永磁机和用于永磁机的转子组件。 永磁体机器包括定子组件，该定子组件包括定子铁心，该定子铁心构造成产生磁场并且沿纵向轴线延伸，内表面限定空腔，转子组件包括转子芯和转子轴。 转子芯设置在定子腔内部并且构造成围绕纵向轴线旋转。 转子组件还包括多个永磁体，用于产生与定子磁场相互作用以产生转矩的磁场。 永磁体设置在形成在套筒部件中的一个或多个空腔内。 套筒部件构造成在其中包括多个空腔或空隙，从而为永磁机提供最小的重量。 永磁机提供增加的离心负载能力，增加功率密度和改善的电气性能。
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公开(公告)号：US20150275762A1
公开(公告)日：2015-10-01
申请号：US14663871
申请日：2015-03-20
Applicant: General Electric Company
Inventor： Ross Hartley Kenyon , Narendra Digamber Joshi
CPC classification number: F02C7/14 , F01D13/003 , F01D13/02 , F01D25/12 , F02C3/305 , F02C6/00 , F02C7/143 , F02C7/16 , F02C9/18 , F02K3/075 , F02K3/10 , F02K3/11 , F02K7/14 , F05D2220/323 , F05D2220/80 , F05D2260/213 , Y02T50/675
Abstract: A cooling system for a turbine engine including a heat exchanger in fluid communication with a first fluid inlet stream and disposed upstream and in fluid communication with a core engine. The heat exchanger operative to cool the first fluid inlet stream. The heat exchanger including a heat exchanger inlet for input of a heat exchanging medium for exchange of heat from the first fluid inlet stream to the heat exchanging medium. The heat exchanger further including a heat exchanger outlet for discharge of a heated output stream into one of a turbine of a downstream engine, an augmentor or a combustor of the core engine. The heated output stream provides an additional flow to the downstream engine. A turbine engine including the cooling system is disclosed.
Abstract translation: 一种用于涡轮发动机的冷却系统，其包括与第一流体入口流流体连通并且设置在上游并与核心发动机流体连通的热交换器。 热交换器用于冷却第一流体入口流。 热交换器包括用于输入热交换介质的热交换器入口，用于将热量从第一流体入口流传递到热交换介质。 热交换器还包括用于将加热的输出流排放到核心发动机的下游发动机，增压器或燃烧器的涡轮机之一的热交换器出口。 加热的输出流为下游发动机提供额外的流量。 公开了一种包括冷却系统的涡轮发动机。
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公开(公告)号：US20240309830A1
公开(公告)日：2024-09-19
申请号：US18672379
申请日：2024-05-23
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Timothy John Sommerer , Narendra Digamber Joshi , Venkat Eswarlu Tangirala
CPC classification number: F02K7/10 , F02K7/14 , F23R3/12 , F23R2900/00009 , F23R2900/00015
Abstract: An engine includes an inlet tube introducing air to a combustion process and a first plurality of fuel injectors disposed in the inlet tube and used for scram-jet engine operation. The engine includes a second plurality of fuel injectors used for ram-jet engine operation. The second plurality of fuel injectors is upstream from the first plurality of fuel injectors and is disposed in the inlet tube. The engine includes a combustor swirl zone downstream of and adjacent to the first plurality of fuel injectors.
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Patent Agency Ranking
公开(公告)号：US12092336B2
公开(公告)日：2024-09-17
申请号：US17195131
申请日：2021-03-08
Applicant: General Electric Company
Inventor： Owen James Sullivan Rickey , Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Shashank Yellapantula
Abstract: 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：US11859820B1
公开(公告)日：2024-01-02
申请号：US17984669
申请日：2022-11-10
Applicant: General Electric Company
Inventor： Seung-Hyuck Hong , Richard L. Hart , Honggang Wang , Anil Raj Duggal , Michael Anthony Benjamin , Andrew Wickersham , Narendra Digamber Joshi
IPC: F23R3/00 , H01M8/04089 , H01M8/2457 , F23R3/28 , H01M8/04007
CPC classification number: F23R3/002 , F23R3/28 , H01M8/04074 , H01M8/04089 , H01M8/2457 , H01M2250/20
Abstract: A combustion section defines an axial direction, a radial direction, and a circumferential direction. The combustion section includes a casing that defines a diffusion chamber. A combustion liner is disposed within the diffusion chamber and 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. A fuel cell assembly is disposed in the passageway. The fuel cell assembly includes a fuel cell stack that has a plurality of fuel cells each extending between an inlet end and an outlet end. The inlet end receives a flow of air and fuel and the outlet end provides output products to the combustion chamber. The outlet end of the plurality of fuel cells extends through the combustion liner and partially defines the combustion chamber.
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公开(公告)号：US11371711B2
公开(公告)日：2022-06-28
申请号：US16203335
申请日：2018-11-28
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Narendra Digamber Joshi
Abstract: A combustion system includes an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end; at least one annulus inlet disposed in the annular tube proximate the inlet end, the annulus inlet providing a conduit through which fluid flows into the annular tube; at least one outlet disposed in the annular tube proximate the outlet end; at least one inlet fluid plenum disposed upstream of the annulus inlet; and at least one fluid inlet disposed upstream of the inlet fluid plenum. The fluid inlet is linearly offset from the annulus inlet.
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公开(公告)号：US11260953B2
公开(公告)日：2022-03-01
申请号：US16685527
申请日：2019-11-15
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Brian Magann Rush , Narendra Digamber Joshi , Timothy John Sommerer , Gregory Alexander Natsui , Brian Gene Brzek , Douglas Carl Hofer
Abstract: A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.
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公开(公告)号：US11149954B2
公开(公告)日：2021-10-19
申请号：US15795894
申请日：2017-10-27
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Narendra Digamber Joshi
Abstract: A rotating detonation combustion system is generally provided. The rotating detonation combustion system includes an outer wall, an upstream wall, and a radial wall. The outer wall is defined circumferentially around a combustor centerline extended along a lengthwise direction. The outer wall defines a first radius portion generally upstream along the outer wall. A second radius portion is defined generally downstream along the outer wall and a transition portion is defined between the first and second radius portions. The first radius portion defines a first radius greater than a second radius at the second radius portion. The transition portion defines a generally decreasing radius from the first radius portion to the second radius portion. The upstream wall is defined circumferentially around the combustor centerline and is extended along the lengthwise direction and inward radially of the first radius portion of the outer wall. An oxidizer passage is defined within the upstream wall. A combustion chamber is defined downstream of the upstream wall and radially inward of the outer wall. The radial wall is coupled to the outer wall and the upstream wall. A fluid injection opening is defined through at least one of the radial wall or the outer wall adjacent to the combustion chamber.
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