Method of reducing the gap between a liner and a turbine distributor of a turbojet engine
US6163959A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Mar 19, 1999 |
| Grant date | Dec 26, 2000 |
| Priority date | — |
| Expiry date | Mar 19, 2019 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/4932
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of reducing the gap between a liner and a turbine distributor of a turbojet engine. The method allows for the improvement of the seal on the inside of the distributor of the high pressure turbine at the lower platform. The method includes the steps of: applying a protective deposit to the lower part of the external surface of the liner, before carrying out a filling by diffusion brazing between the liner and the distributor. The protective deposit, preferably a anti-adherent ceramic, makes it possible for the braze to avoid fixing the liner onto the distributor at the lower platform level. The method also has applications to turbojet engines.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.