| 发明名称 | Hybrid rotor disk assembly for a gas turbine engine | ||
| 摘要 | A rotor disk assembly for a gas turbine engine includes a rotor hub defined about an axis of rotation, the rotor hub includes a blade mount section with a first radial flange having a multiple of first apertures and a second radial flange with a multiple of second apertures. | ||
| 申请公布号 | US8851853(B2) | 申请公布日期 | 2014.10.07 |
| 申请号 | US201113116199 | 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;F01D5/28;F01D5/30;F01D5/22 | 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 rotor disk assembly for a gas turbine engine comprising: a rotor hub defined about an axis of rotation, said rotor hub includes a blade mount section with an axially foremost radial flange having a multiple of first circumferentially-spaced apertures and an axial aftmost radial flange with a multiple of second circumferentially-spaced apertures, each of said first circumferentially-spaced apertures being paired, with respect to receiving a common pin, with a circumferentially offset one of said second circumferentially-spaced apertures. | ||
| 地址 | Hartford CT US | ||