| 发明名称 | Asymmetrically slotted rotor for a gas turbine engine | ||
| 摘要 | A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface. | ||
| 申请公布号 | US8784062(B2) | 申请公布日期 | 2014.07.22 |
| 申请号 | US201113283710 | 申请日期 | 2011.10.28 |
| 申请人 | United Technologies Corporation | 发明人 | Suciu Gabriel L.;Muron Stephen P.;Dye Christopher M.;Alvanos Ioannis;Merry Brian D. |
| 分类号 | F01D11/00;F01D5/02 | 主分类号 | F01D11/00 |
| 代理机构 | Carlson, Gaskey & Olds, PC | 代理人 | Carlson, Gaskey & Olds, PC |
| 主权项 | 1. A spacer for a gas turbine engine comprising: a rotor ring defined along an axis of rotation, said rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, said first thickness different than said second thickness; and a plurality of core gas path seals which extend from said rotor ring opposite an interface, each of said plurality of core gas path seals extend from said rotor ring at said interface, said interface defined along a spoke. | ||
| 地址 | Hartford CT US | ||