发明名称 |
JET ENGINE COLD AIR COOLING SYSTEM |
摘要 |
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. |
申请公布号 |
US2016153359(A1) |
申请公布日期 |
2016.06.02 |
申请号 |
US201514755398 |
申请日期 |
2015.06.30 |
申请人 |
General Electric Company |
发明人 |
Leamy Kevin Richard;Breig Benjamin Paul;Epstein Michael Jay;Parrilla Javier Armando;Hurt Matthew John;Brinson Thomas Edward;Fleming Andrew James |
分类号 |
F02C7/18;F02C9/18 |
主分类号 |
F02C7/18 |
代理机构 |
|
代理人 |
|
主权项 |
1. A jet engine comprising:
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, wherein the bleed air cooling system comprises:
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; andwherein a discharge conduit from the cooling system turbine is configured to be in fluid communication with at least one of an aircraft thermal management system and an aircraft environmental control system. |
地址 |
Schenectady NY US |