Finned seal assembly for gas turbine engines
US9121298B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 27, 2012 |
| Grant date | Sep 1, 2015 |
| Priority date | — |
| Expiry date | Mar 27, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D11/001
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.