| 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 has a fan section including a fan rotatable about an axis. A speed reduction device is in communication with the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.6. A fan blade tip speed of the fan is less than 1400 fps. A low pressure turbine section is in communication with the speed reduction device. The low pressure turbine section includes three or four stages. A bypass ratio is between 11.0 and about 22.0. A method of improving performance of a gas turbine engine comprising |
| 申请公布号 |
US2015308335(A1) |
申请公布日期 |
2015.10.29 |
| 申请号 |
US201514746910 |
申请日期 |
2015.06.23 |
| 申请人 |
United Technologies Corporation |
发明人 |
Sheridan William G.;Hasel Karl L. |
| 分类号 |
F02C3/113;F02C7/36;F16H1/36;F02C3/06 |
主分类号 |
F02C3/113 |
| 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; a speed reduction device in communication with the fan, wherein the speed reduction device includes an epicyclic gear system with a gear ratio of at least 2.6, wherein a fan blade tip speed of the fan is less than 1400 fps; and a low pressure turbine section in communication with the speed reduction device, wherein the low pressure turbine section includes three or four stages; and a bypass ratio that is between 11.0 and about 22.0. |
| 地址 |
Hartford CT US |
