| 发明名称 | Hybrid rotor disk assembly with ceramic matrix composites platform for a gas turbine engine | ||
| 摘要 | A Ceramic Matrix Composite (CMC) platform for an airfoil of a gas turbine engine includes a CMC platform segment which at least partially defines an airfoil profile. | ||
| 申请公布号 | US8936440(B2) | 申请公布日期 | 2015.01.20 |
| 申请号 | US201113116173 | 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 | F01D5/32;F01D25/24;F01D5/14;F01D5/22;F01D5/28;F01D11/00 | 主分类号 | F01D5/32 |
| 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) platform assembly for an airfoil of a gas turbine engine comprising: a CMC platform segment which defines an airfoil leading or trailing edge profile, wherein said CMC platform segment defines a CMC forward platform segment with a first platform inner surface which defines said airfoil leading edge profile. | ||
| 地址 | Hartford CT US | ||