| 发明名称 |
COMPRESSOR BLEED AIR SUPPLY FOR AN AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM |
| 摘要 |
A gas turbine engine includes a fan, a compressor section having at least two sequential compressors, a combustor section fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. The turbine section includes at least a first turbine, a second turbine and a third turbine. One of the first turbine, the second turbine and the third turbine is a fan-drive turbine. An environmental control system air supply includes at least a first compressor bleed and a second compressor bleed. Each of the first compressor bleed and the second compressor bleed are positioned upstream of a highest pressure compressor of the at least two compressors. |
| 申请公布号 |
US2016114894(A1) |
申请公布日期 |
2016.04.28 |
| 申请号 |
US201514887932 |
申请日期 |
2015.10.20 |
| 申请人 |
United Technologies Corporation |
发明人 |
Schwarz Frederick M.;Suciu Gabriel L. |
| 分类号 |
B64D13/06;F02C9/18;F02C7/12;F02C3/107;F02C3/06 |
主分类号 |
B64D13/06 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a fan; a compressor section having at least two sequential compressors; a combustor section fluidly connected to the compressor section;a turbine section fluidly connected to the combustor section, the turbine section including at least a first turbine, a second turbine and a third turbine, and wherein one of said first turbine, said second turbine and said third turbine is a fan-drive turbine;
an environmental control system air supply including at least a first compressor bleed and a second compressor bleed, wherein each of said first compressor bleed and said second compressor bleed are positioned upstream of a highest pressure compressor of said at least two compressors. |
| 地址 |
Hartford CT US |
