| 发明名称 |
METHOD FOR SETTING A GEAR RATIO OF A FAN DRIVE GEAR SYSTEM OF A GAS TURBINE ENGINE |
| 摘要 |
A gas turbine engine includes a fan section including a fan rotatable about an axis of rotation of the gas turbine engine. A speed reduction device is in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps. A bypass ratio is between about 11.0 and about 22.0. |
| 申请公布号 |
US2015233301(A1) |
申请公布日期 |
2015.08.20 |
| 申请号 |
US201514705459 |
申请日期 |
2015.05.06 |
| 申请人 |
United Technologies Corporation |
发明人 |
Sheridan William G.;Hasel Karl L. |
| 分类号 |
F02C7/32;F02C3/107;F02C7/36 |
主分类号 |
F02C7/32 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a fan section including a fan rotatable about an axis of rotation of the gas turbine engine; a speed reduction device in communication with the fan, wherein the speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5, wherein a fan blade tip speed of the fan is less than 1400 fps; and a bypass ratio is between about 11.0 and about 22.0. |
| 地址 |
Hartford CT US |
