| 发明名称 |
GAS TURBINE ENGINE WITH LOW STAGE COUNT LOW PRESSURE TURBINE |
| 摘要 |
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, a low spool that includes a low pressure compressor section, the low pressure compressor section including three (3) or more stages, and a high spool including a high pressure compressor section. The high pressure compressor section includes between eight to thirteen (8-13) stages. A gear train is defined along an engine axis. The low spool is operable to drive the fan section through the gear train. |
| 申请公布号 |
US2016024958(A1) |
申请公布日期 |
2016.01.28 |
| 申请号 |
US201514872508 |
申请日期 |
2015.10.01 |
| 申请人 |
United Technologies Corporation |
发明人 |
Suciu Gabriel L.;Merry Brian D.;Dye Christopher M.;Johnson Steven B. |
| 分类号 |
F01D15/12;F01D1/02;F01D17/10;F01D17/14;F01D25/24;F01D5/02;F01D9/02 |
主分类号 |
F01D15/12 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a fan section; a low spool that includes a low pressure compressor section, said low pressure compressor section includes three (3) or more stages; a high spool that includes a high pressure compressor section, said high pressure compressor section including between eight to thirteen (8-13) stages; and a gear train defined along an engine axis, said low spool operable to drive said fan section through said gear train. |
| 地址 |
Hartford CT US |
