| 发明名称 | Hybrid rotor disk assembly with a ceramic matrix composite airfoil for a gas turbine engine | ||
| 摘要 | A Ceramic Matrix Composite (CMC) airfoil for a gas turbine engine includes a CMC root section which extends to form a CMC airfoil section, the CMC root section defines a bore along a non-linear axis. | ||
| 申请公布号 | US8834125(B2) | 申请公布日期 | 2014.09.16 |
| 申请号 | US201113116188 | 申请日期 | 2011.05.26 |
| 申请人 | United Technologies Corporation | 发明人 | Alvanos Ioannis;Suciu Gabriel L.;Dye Christopher M.;Levasseur Glenn |
| 分类号 | F01D5/30;F01D5/28;F01D5/22;C04B37/00 | 主分类号 | F01D5/30 |
| 代理机构 | Carlson, Gaskey & Olds, P.C. | 代理人 | Carlson, Gaskey & Olds, P.C. |
| 主权项 | 1. A Ceramic Matrix Composite (CMC) airfoil for a gas turbine engine comprising: a CMC root section which extends to form a CMC airfoil section; a forward platform segment and an aft platform segment capturing there between said CMC root section, said CMC root section, said forward platform segment, and said aft platform segment together defining a curved bore. | ||
| 地址 | Hartford CT US | ||