| 发明名称 | Vane assembly for a gas turbine engine | ||
| 摘要 | A vane assembly for a gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible features, a first platform, a second platform spaced from the first platform, and a first variable airfoil that extends radially across an annulus between the first platform and the second platform. One of a radial outer portion and a radial inner portion of the variable airfoil includes a rotational shaft and the other of the radial outer portion and the radial inner portion includes a ball and socket joint that rotationally connect the first variable airfoil relative to the first platform and the second platform. | ||
| 申请公布号 | US9273565(B2) | 申请公布日期 | 2016.03.01 |
| 申请号 | US201213401872 | 申请日期 | 2012.02.22 |
| 申请人 | United Technologies Corporation | 发明人 | Propheter-Hinckley Tracy A. |
| 分类号 | F01D9/04;F01D17/16 | 主分类号 | F01D9/04 |
| 代理机构 | Carlson, Gaskey & Olds | 代理人 | Carlson, Gaskey & Olds |
| 主权项 | 1. A vane assembly for a gas turbine engine, comprising: a first platform; a second platform spaced from said first platform; and said first platform is skewed relative to said second platform; and a first variable airfoil that extends radially across an annulus between said first platform and said second platform, wherein one of a radial outer portion and a radial inner portion of said variable airfoil includes a rotational shaft and the other of said radial outer portion and said radial inner portion includes a ball and socket joint that rotationally connect said first variable airfoil relative to said first platform and said second platform. | ||
| 地址 | Hartford CT US | ||