Gas turbine engines with plug resistant effusion cooling holes
US10101030B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 2, 2014 |
| Grant date | Oct 16, 2018 |
| Priority date | — |
| Expiry date | Jul 2, 2037 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a turbine engine is provided. A first liner has a first surface and a second surface. A second liner forms a combustion chamber with the second side of the first liner, and the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defines a plurality of effusion cooling holes configured to form a film of cooling air on the second surface of the first liner. The plurality of effusion cooling holes includes a first effusion cooling hole extending from the first surface to the second surface and including an inlet portion extending from the first surface, a metering portion fluidly coupled to the inlet portion, and an outlet portion fluidly coupled to the metering portion and extending to the second surface. The inlet portion is larger than the metering portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.