| 发明名称 |
Finned seal assembly for gas turbine engines |
| 摘要 |
A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly. |
| 申请公布号 |
US9121298(B2) |
申请公布日期 |
2015.09.01 |
| 申请号 |
US201213534060 |
申请日期 |
2012.06.27 |
| 申请人 |
SIEMENS AKTIENGESELLSCHAFT |
发明人 |
Lee Ching-Pang;Tham Kok-Mun;Owen John M.;Lock Gary D.;Sangan Carl M.;Laurello Vincent P. |
| 分类号 |
F04D11/00;F01D11/00 |
主分类号 |
F04D11/00 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A seal assembly between a hot gas path and a disc cavity in a turbine engine including a rotor structure supporting a plurality of blades for rotation with a turbine rotor, the seal assembly comprising:
an annular outer wing member extending from an axially facing side of the rotor structure toward an adjacent non-rotating vane assembly; and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly, the fins being arranged such that a space having a component in a circumferential direction is defined between adjacent fins. |
| 地址 |
München DE |
