| 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, and a compressor section, including 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, with the overall pressure ratio being greater than or equal to about 35. A pressure ratio across the fan section is less than or equal to about 1.50. The fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct. |
| 申请公布号 |
US2014157754(A1) |
申请公布日期 |
2014.06.12 |
| 申请号 |
US201414179640 |
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; 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; wherein the pressure ratio across the first compressor is greater than or equal to about 7; wherein a pressure ratio across the fan section is less than or equal to about 1.50; and wherein the fan is configured to deliver a portion of air into the compressor section, and a portion of air into a bypass duct.
|
| 地址 |
Hartford CT US |
