-
公开(公告)号：US10415897B2
公开(公告)日：2019-09-17
申请号：US15037432
申请日：2014-11-17
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas Kupiszewski , Mehdi Milani Baladi , John Andrew Kemme , Christopher Charles Glynn , Steven Douglas Johnson , Michael Jay Epstein
Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.
-
公开(公告)号：US09188285B2
公开(公告)日：2015-11-17
申请号：US13726480
申请日：2012-12-24
Applicant: General Electric Company
Inventor： Chiranjeev Kalra , William Dwight Gerstler , Laura Michele Hudy , Michael Jay Epstein , Vaibhav Bahadur
CPC classification number: F17C5/02 , B64D37/30 , B64D37/32 , F23G7/066 , F23G7/07 , F23G2206/10 , F23J15/06 , F23M2900/13003 , Y02E20/12 , Y02E20/363
Abstract: A system in one embodiment includes a mixing module, an oxidation module, and a heat exchanger. The mixing module is configured to receive and mix a boil-off gas stream from a cryotank. The oxidation module is configured to receive the mixed stream, and to oxidize the boil-off gas in the mixed stream to produce an exhaust stream. The heat exchanger is configured to exchange heat between streams passing through a first passage configured to receive at least a portion of the exhaust stream, and a second passage configured to receive a fluid including the boil-off gas. The heat exchanger is configured to heat the fluid including the boil-off gas and cool the at least a portion of the exhaust stream. The fluid including the boil-off gas is heated by the heat exchanger upstream of the oxidation module.
Abstract translation: 一个实施例中的系统包括混合模块，氧化模块和热交换器。 混合模块被配置为接收和混合来自低温罐的蒸发气流。 氧化模块被配置为接收混合流，并且使混合流中的蒸发气体氧化以产生排气流。 热交换器被配置为在通过构造成接收排气流的至少一部分的第一通道的流之间交换热量，以及构造成接收包括该蒸发气体的流体的第二通道。 热交换器被配置为加热包括蒸发气体的流体并且冷却排气流的至少一部分。 包括蒸发气体的流体被氧化模块上游的热交换器加热。
-
公开(公告)号：US20160153359A1
公开(公告)日：2016-06-02
申请号：US14755398
申请日：2015-06-30
Applicant: General Electric Company
Inventor： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming
CPC classification number: B64D13/08 , B64D13/006 , B64D13/06 , B64D2013/0618 , B64D2013/0648 , B64D2013/0688 , F01D13/02 , F01D17/08 , F01D17/10 , F01D17/14 , F01D25/12 , F02C6/08 , F02C7/185 , F02C7/32 , F02C9/18 , F05D2220/3216 , F05D2220/323 , F05D2260/211 , F05D2260/213 , F05D2260/232 , F05D2260/606 , F05D2270/301 , F05D2270/303 , Y02T50/56 , Y02T50/675 , Y02T50/676
Abstract: Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.
Abstract translation: 提供飞机和喷气发动机，其包括发动机压缩机; 与发动机压缩机流动连通的燃烧器; 与所述燃烧器流动连通以从所述燃烧器接收燃烧产物的发动机涡轮机; 以及与来自发动机压缩机的排出空气流体连通的排气冷却系统。 排气冷却系统可以包括与来自发动机压缩机的排出空气流体连通的第一预冷器; 与第一预冷器相流体连通和下游的冷却系统涡轮机; 以及来自冷却系统涡轮机的排放管道，其构造成与飞机热管理系统和飞行器环境控制系统中的至少一个流体连通。 还描述了用于从喷气发动机提供冷却流体的方法。
-
公开(公告)号：US20140174103A1
公开(公告)日：2014-06-26
申请号：US13726480
申请日：2012-12-24
Applicant: General Electric Company
Inventor： Chiranjeev Kalra , William Dwight Gerstler , Laura Michele Hudy , Michael Jay Epstein , Vaibhav Bahadur
IPC: F17C5/02
CPC classification number: F17C5/02 , B64D37/30 , B64D37/32 , F23G7/066 , F23G7/07 , F23G2206/10 , F23J15/06 , F23M2900/13003 , Y02E20/12 , Y02E20/363
Abstract: A system in one embodiment includes a mixing module, an oxidation module, and a heat exchanger. The mixing module is configured to receive and mix a boil-off gas stream from a cryotank. The oxidation module is configured to receive the mixed stream, and to oxidize the boil-off gas in the mixed stream to produce an exhaust stream. The heat exchanger is configured to exchange heat between streams passing through a first passage configured to receive at least a portion of the exhaust stream, and a second passage configured to receive a fluid including the boil-off gas. The heat exchanger is configured to heat the fluid including the boil-off gas and cool the at least a portion of the exhaust stream. The fluid including the boil-off gas is heated by the heat exchanger upstream of the oxidation module.
Abstract translation: 一个实施例中的系统包括混合模块，氧化模块和热交换器。 混合模块被配置为接收和混合来自低温罐的蒸发气流。 氧化模块被配置为接收混合流，并且使混合流中的蒸发气体氧化以产生排气流。 热交换器被配置为在通过构造成接收排气流的至少一部分的第一通道的流之间交换热量，以及构造成接收包括该蒸发气体的流体的第二通道。 热交换器被配置为加热包括蒸发气体的流体并且冷却排气流的至少一部分。 包括蒸发气体的流体被氧化模块上游的热交换器加热。
-
公开(公告)号：US10815890B2
公开(公告)日：2020-10-27
申请号：US15322842
申请日：2015-06-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming , George Eugene Wilmot
IPC: F02C7/18 , B64D13/00 , B64D13/06 , F01D13/02 , F02C6/08 , B64D13/08 , F01D17/08 , F01D17/10 , F01D25/12 , F02C9/18 , F02C7/32 , F01D17/14
Abstract: Methods and devices for cooling systems (700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can 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 VGT cooling system turbine (240) 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) for bypassing the turbine can also be included.
-
Patent Agency Ranking
公开(公告)号：US09676491B2
公开(公告)日：2017-06-13
申请号：US14654685
申请日：2013-11-26
Applicant: General Electric Company
Inventor： Michael Jay Epstein , Adon Delgado, Jr. , Robert Harold Weisgerber
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.
-
公开(公告)号：US10247100B2
公开(公告)日：2019-04-02
申请号：US14755398
申请日：2015-06-30
Applicant: General Electric Company
Inventor： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming
IPC: F02C1/00 , F02C7/18 , B64D13/00 , B64D13/06 , F01D13/02 , F01D17/08 , F01D17/10 , F01D25/12 , F02C6/08 , F02C9/18
Abstract: Airplanes and jet engines are provided that includes an engine compressor; a combustor in flow communication with the engine compressor; an engine turbine in flow communication with the combustor to receive combustion products from the combustor; and a bleed air cooling system in fluid communication with bleed air from the engine compressor. The bleed air cooling system can include a first precooler in fluid communication with the bleed air from the engine compressor; a cooling system turbine in fluid communication with and downstream from the first precooler; and a discharge conduit from the cooling system turbine that is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. Methods are also described for providing cooling fluid from a jet engine.
-
公开(公告)号：US20180194479A1
公开(公告)日：2018-07-12
申请号：US15322842
申请日：2015-06-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming , George Eugene Wilmot
Abstract: Methods and devices for cooling systems (700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can 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 VGT cooling system turbine (240) 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) for bypassing the turbine can also be included.
-
公开(公告)号：US09701416B2
公开(公告)日：2017-07-11
申请号：US14655761
申请日：2013-11-26
Applicant: General Electric Company
Inventor： Michael Jay Epstein , Paul Bernard Stumbo , Robert Harold Weisgerber
CPC classification number: B64D37/30 , B64D37/32 , F02C7/14 , F02C7/224 , F02C9/40 , F05D2260/213 , F05D2260/98 , F17C3/00 , Y02T50/44 , Y02T50/672 , Y02T50/676 , Y02T90/44
Abstract: An aircraft having a turbine engine having a bleed air output line, a cryogenic fuel system having a cryogenic fuel tank for storing cryogenic fuel and a supply line operably coupling the tank to the turbine engine, and an on board inert gas generating system (OBIGGS) fluidly coupled to the bleed air output and having a nitrogen rich stream output line and an oxygen rich stream output line.
-
公开(公告)号：US10808618B2
公开(公告)日：2020-10-20
申请号：US15322844
申请日：2015-06-30
Applicant: General Electric Company
Inventor： Kevin Richard Leamy , Benjamin Paul Breig , Michael Jay Epstein , Javier Armando Parrilla , Matthew John Hurt , Thomas Edward Brinson , Andrew James Fleming , George Eugene Wilmot, Jr.
IPC: F02C7/18 , B64D13/00 , B64D13/06 , F01D13/02 , F02C6/08 , B64D13/08 , F01D17/08 , F01D17/10 , F01D25/12 , F02C9/18 , F02C7/32 , 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).
-
-
-
-
-
-
-
-
-
Search Results
12
records
(took 0.016 seconds)
