Turbine stage shroud segment
US8714918B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 6, 2011 |
| Grant date | May 6, 2014 |
| Priority date | — |
| Expiry date | Dec 18, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49323
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A shroud segment for a turbine stage of a gas turbine engine forms an endwall for the working gas annulus of the stage. The segment also provides a close clearance to the tips of a row of turbine blades which sweep across the segment. In use a leakage flow of the working gas passes through the clearance gap between the blade tips and the segment. The segment has a plurality of cooling holes and respective air feed passages for the cooling holes. The cooling holes are distributed over that part of the gas-washed surface of the segment which is swept by the blade tips. The cooling holes deliver, in use, cooling air which spreads over the gas-washed surface. The feed passages are configured such that the delivered air opposes the leakage flow of the working gas.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.