Labyrinth seal device for gas turbine engine
US7296415B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 21, 2004 |
| Grant date | Nov 20, 2007 |
| Priority date | — |
| Expiry date | Jan 5, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D11/025
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element. The means of intervention offers a means of controlling the clearance of the labyrinth seal clearance.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.