| 发明名称 |
FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE |
| 摘要 |
A geared architecture for a gas turbine engine includes a fan shaft and a frame which supports said fan shaft. The frame defines a frame stiffness. A plurality of gears drives the fan shaft and includes a gear mesh that defines a gear mesh stiffness. A stiffness of a ring gear of the plurality of gears is less than about 20% of the gear mesh stiffness. A flexible support supports the geared architecture and defines a flexible support stiffness. An input coupling to the plurality of gears defines an input coupling stiffness. The flexible support stiffness and the input coupling stiffness are each less than about 11% of the frame stiffness. |
| 申请公布号 |
US2016319829(A1) |
申请公布日期 |
2016.11.03 |
| 申请号 |
US201615185292 |
申请日期 |
2016.06.17 |
| 申请人 |
United Technologies Corporation |
发明人 |
McCune Michael E.;Husband Jason |
| 分类号 |
F04D29/056;F16H1/28;F02K3/06;F16H57/028;F04D29/053;F04D25/02 |
主分类号 |
F04D29/056 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A geared architecture for a gas turbine engine comprising:
a fan shaft; a frame which supports said fan shaft, said frame defines a frame stiffness; a plurality of gears which drives said fan shaft, said plurality of gears includes a gear mesh that defines a gear mesh stiffness, wherein a stiffness of a ring gear of said plurality of gears is less than about 20% of said gear mesh stiffness; a flexible support which supports said geared architecture and defines a flexible support stiffness; and an input coupling to said plurality of gears, said input coupling defines an input coupling stiffness, wherein said flexible support stiffness and said input coupling stiffness are each less than about 11% of said frame stiffness. |
| 地址 |
Farmington CT US |
