Plug resistant effusion holes for gas turbine engine
US11519604B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jul 1, 2021 |
| Grant date | Dec 6, 2022 |
| Priority date | — |
| Expiry date | Jul 1, 2041 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor for a gas turbine engine includes a liner having a first surface, a second surface opposite the first surface, and defining a plurality of effusion cooling holes. At least one of the effusion cooling holes includes an inlet section and a converging section downstream of the inlet section. The at least one of the effusion cooling holes includes a metering section downstream of the converging section. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface. The inlet section, the converging section, the metering section and the outlet section extend along a longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.