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。

公开(公告)号：US20160025339A1

公开(公告)日：2016-01-28

申请号：US14774917

申请日：2014-03-12

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Deepak Manohar KAMATH ,  Adon DELGADO, JR. ,  Michael Jay EPSTEIN

IPC: F23K5/22 ,  F23R3/36 ,  F23K5/00 ,  F02C9/40 ,  F02C3/04

CPC classification number: F23K5/22 ,  B64D37/30 ,  B64D37/34 ,  F02C3/04 ,  F02C3/22 ,  F02C7/224 ,  F02C9/40 ,  F05D2220/32 ,  F23K5/002 ,  F23R3/36 ,  Y02T50/44 ,  Y02T50/672 ,  Y02T90/44

Abstract: A method and apparatus of using cryogenic fuel in an engine for an aircraft wherein the cryogenic fuel is supplied to the engine for combustion.

Abstract translation: 一种在用于飞机的发动机中使用低温燃料的方法和装置，其中将低温燃料供应到发动机用于燃烧。

公开(公告)号：US20150321767A1

公开(公告)日：2015-11-12

申请号：US14651583

申请日：2013-11-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Deepak Manohar KAMATH ,  Mehdi Milani BALADI ,  Sergei A. JEREBETS ,  Robert Lawrence MAYER ,  Scott Chandler MORTON ,  Alejandro Yatzail PEREZ VALADEZ

IPC: B64D37/34

CPC classification number: B64D37/30 ,  B64D37/34 ,  F02C3/22 ,  F02C7/222 ,  F02C7/224 ,  F02C9/40 ,  F05D2260/207 ,  Y02T50/44 ,  Y02T50/672 ,  Y02T50/676

Abstract: A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels. The system includes a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tank fluidly coupled to the engine, with the second fuel being different from the first fuel and having a different temperature than the first fuel, a fuel distribution unit (FDU) fluidly coupled to the first fuel tank of the first fuel system, and a fuel-to-fuel cooler (FFC) configured to transfer heat between the first fuel in the first fuel system and the second fuel in the second fuel system.

Abstract translation: 用于由双重燃料燃料的飞机发动机的流体温度控制和致动控制的系统。 该系统包括具有流体地联接到发动机的第一燃料箱的第一燃料系统，具有与发动机流体耦合的第二燃料箱的第二燃料系统，其中第二燃料与第一燃料不同，并且具有与 第一燃料，流体耦合到第一燃料系统的第一燃料箱的燃料分配单元（FDU）和燃料 - 燃料冷却器（FFC），其被配置为在第一燃料系统中的第一燃料和第二燃料系统之间传递热量 第二燃料系统中的燃料。