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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。
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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.
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Patent Agency Ranking
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.
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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).
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公开(公告)号：US20200180771A1
公开(公告)日：2020-06-11
申请号：US16211972
申请日：2018-12-06
Applicant: General Electric Company
Inventor： Nicholas Taylor Moore , Andrew James Fleming
Abstract: An aircraft includes an aircraft heat source; a propulsion system including an electric propulsion engine, the electric propulsion engine including an electric motor and a fan rotatable by the electric motor, the electric propulsion engine further defining a fan air flowpath; a thermal management system including a heat source exchanger in thermal communication with the aircraft heat source, a heat sink exchanger in thermal communication with the fan air flowpath of the electric propulsion engine, and a thermal distribution bus extending from the heat source exchanger to the heat sink exchanger; and a control system operably connected to the thermal management system for selectively thermally coupling the heat sink exchanger with the heat source exchanger.
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公开(公告)号：US20230365264A1
公开(公告)日：2023-11-16
申请号：US18102977
申请日：2023-01-30
Applicant: General Electric Company
Inventor： Nicholas Taylor Moore , Andrew James Fleming
CPC classification number: B64D13/08 , B64D27/24 , B64D29/00 , B64D13/06 , B64D31/00 , B64D2013/0625 , B64D2013/0618
Abstract: An aircraft includes an aircraft heat source; a propulsion system including an electric propulsion engine, the electric propulsion engine including an electric motor and a fan rotatable by the electric motor, the electric propulsion engine further defining a fan air flowpath; a thermal management system including a heat source exchanger in thermal communication with the aircraft heat source, a heat sink exchanger in thermal communication with the fan air flowpath of the electric propulsion engine, and a thermal distribution bus extending from the heat source exchanger to the heat sink exchanger; and a control system operably connected to the thermal management system for selectively thermally coupling the heat sink exchanger with the heat source exchanger.
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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.
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