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    CRYOGENIC FUEL SYSTEM AND METHOD FOR DELIERING FUEL IN AN AIRCRAFT
    1.
    发明申请
    CRYOGENIC FUEL SYSTEM AND METHOD FOR DELIERING FUEL IN AN AIRCRAFT 有权
    低成本燃料系统和在飞机上调度燃料的方法

    公开(公告)号：US20150344144A1

    公开(公告)日：2015-12-03

    申请号：US14654925

    申请日：2013-11-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Deepak Manohar KAMATH ,  Todd James BUCHHOLZ ,  Mehdi Milani BALADI ,  Michael Jay EPSTEIN

    IPC: B64D37/30

    CPC classification number: B64D37/30 ,  F02C3/22 ,  F02C6/08 ,  F02C7/224 ,  F02C7/236 ,  F02C9/40 ,  Y02T50/672

    Abstract: A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine.

    Abstract translation: 一种用于飞行器的低温燃料系统，具有具有压缩机部分和燃烧室的涡轮发动机，包括用于存储低温燃料的罐，可操作地将罐连接到燃烧室的供应管和将罐耦合到供应管线的泵 在高压下泵送低温燃料通过供应管线，其中泵可操作地联接到压缩机，使得涡轮发动机的操作驱动泵以及将燃料系统中的燃料输送到涡轮发动机的方法。

    TURBINE ENGINE ASSEMBLIES
    4.
    发明申请
    TURBINE ENGINE ASSEMBLIES 审中-公开
    涡轮发动机总成

    公开(公告)号：US20150337730A1

    公开(公告)日：2015-11-26

    申请号：US14655769

    申请日：2013-11-26

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Thomas KUPISZEWSKI ,  Michael Jay EPSTEIN ,  Todd James BUCHHOLZ ,  Adon DELGADO ,  Christopher Dale MATHIAS ,  Deborah Ann OAKES

    IPC: F02C3/22 ,  F02C7/224

    CPC classification number: F02C3/22 ,  F02C7/16 ,  F02C7/224 ,  F05D2260/213 ,  F05D2260/232 ,  Y02T50/672 ,  Y02T50/676

    Abstract: Turbine engine assemblies including a turbine engine assembly having a turbine core comprising a compressor section, a combustion section, a turbine section, and a nozzle section, which are axially aligned, wherein the combustion section comprises a generally annular case having inner and outer walls, a heat exchanger comprising multiple passages in proximity to at least one of the inner and outer walls, with the passages arranged about at least a portion of the case and in fluid communication with each other such that fluid may flow through the passages and a cryogenic fuel system having a cryogenic fuel tank with a supply line coupled to one of the passages, wherein cryogenic fuel may be supplied from the cryogenic fuel tank, through the supply line, to the passages of the heat exchanger, where the fuel in the passages may be heated by the combustion section. The heat exchanger may be a single or multistage vaporizer.

    Abstract translation: 涡轮发动机组件，其包括涡轮发动机组件，涡轮发动机组件具有涡轮机芯，该涡轮机芯包括轴向对准的压缩机部分，燃烧部分，涡轮机部分和喷嘴部分，其中燃烧部分包括具有内壁和外壁的大致环形的壳体， 热交换器，其包括靠近内壁和外壁中的至少一个的多个通道，通道围绕壳体的至少一部分布置并且彼此流体连通，使得流体可以流过通道和低温燃料 系统具有一个低温燃料箱，其中一个通道连接有供应管线，其中低温燃料可以从低温燃料箱通过供应管路供应到热交换器的通道中，其中通道中的燃料可以是 由燃烧部分加热。 热交换器可以是单级或多级蒸发器。

    AIRCRAFT AND METHOD OF MANAGING EVAPORATED CRYOGENIC FUEL
    5.
    发明申请
    AIRCRAFT AND METHOD OF MANAGING EVAPORATED CRYOGENIC FUEL 有权
    飞机和蒸气冷冻燃料的管理方法

    公开(公告)号：US20150344143A1

    公开(公告)日：2015-12-03

    申请号：US14654685

    申请日：2013-11-26

    Applicant: General Electric Company

    Inventor： Michael Jay EPSTEIN ,  Adon DELGADO, Jr. ,  Robert Harold WEISGERBER

    IPC: B64D37/30 ,  B64D37/02

    CPC classification number: B64D37/30 ,  B64D37/02 ,  Y02T50/44 ,  Y02T90/44

    Abstract: A method of managing evaporated cryogenic fuel in a storage tank of a cryogenic fuel system of an aircraft and an aircraft having at least one turbine engine providing propulsive force for the aircraft and a cryogenic fuel system including a passively cooled cryogenic fuel storage tank located within the aircraft, a pressure vent fluidly coupled to the cryogenic fuel storage tank and exhausting evaporated gas from the cryogenic fuel to define a natural gas vent stream, and a catalytic converter fluidly coupled to the pressure vent.

    Abstract translation: 管理飞机和航空器的低温燃料系统的储罐中的蒸发的低温燃料的方法，该飞行器具有至少一个涡轮发动机为飞行器提供推进力，而低温燃料系统包括被动冷却的低温燃料储存箱 飞机，流体耦合到低温燃料储罐的压力通风口，并且从低温燃料排出蒸发的气体以限定天然气排放流，以及流体耦合到压力通风口的催化转化器。

    JET ENGINE COLD AIR COOLING SYSTEM
    7.
    发明申请
    JET ENGINE COLD AIR COOLING SYSTEM 审中-公开

    公开(公告)号：US20180194480A1

    公开(公告)日：2018-07-12

    申请号：US15322844

    申请日：2015-06-30

    Applicant: General Electric Company

    Inventor： Kevin Richard LEAMY ,  Benajamin Paul BREIG ,  Michael Jay EPSTEIN ,  Javier Armando PARRILLA ,  Matthew John Hurt ,  Thomas Edward BRINSON ,  Andrew James FLEMING ,  George Eugene WILMOT

    IPC: B64D13/08 ,  B64D13/00 ,  F02C6/08 ,  F01D17/14

    Abstract: Methods and devices for cooling systems (100, 700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a cooling system turbine (240) with variable guide vanes—VGT—and downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) can also be included that bypasses the cooling system turbine (240).

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