| 发明名称 |
GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT |
| 摘要 |
A gas turbine engine has a fan section, including a fan, a gear arrangement configured to drive the fan section, the geared arrangement defining a gear reduction ratio greater than or equal to about 2.6. A compressor section includes both a first compressor and a second compressor. A turbine section is configured to drive the compressor section and the gear arrangement. An overall pressure ratio is provided by the combination of the first compressor and the second compressor. |
| 申请公布号 |
US2014157756(A1) |
申请公布日期 |
2014.06.12 |
| 申请号 |
US201414179771 |
申请日期 |
2014.02.13 |
| 申请人 |
United Technologies Corporation |
发明人 |
Hasel Karl L.;Staubach Joseph B.;Merry Brian D.;Suciu Gabriel L.;Dye Christopher M. |
| 分类号 |
F02K3/06 |
主分类号 |
F02K3/06 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a fan section including a fan; a gear arrangement configured to drive the fan section, the geared arrangement defining a gear reduction ratio greater than or equal to about 2.6; a compressor section, including both a first compressor and a second compressor; a turbine section configured to drive the compressor section and the gear arrangement; wherein an overall pressure ratio is:
provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor; andgreater than or equal to about 35; and wherein the pressure ratio across the first compressor is greater than or equal to about 7.
|
| 地址 |
Hartford CT US |
