Gas turbine engine combustor liner
US10107497B2 · kind B2 · utility
1Cited by
25References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 4, 2012 |
| Grant date | Oct 23, 2018 |
| Priority date | — |
| Expiry date | May 14, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A liner for a combustor of a turbine engine includes a cooling feature which projects from a backside and one or more effusion holes that communicate(s) through the liner. The effusion hole(s) surround an opening through said liner. The cooling feature may include a trip strip or a pyramid pin fin (e.g., a three-side pyramid pin fin, a conical pyramid pin fin). The effusion hole(s) may penetrate said cooling feature. The effusion hole(s) may define an angle less than or equal to ninety (90) degrees with respect to a face of said liner. The effusion hole(s) may be proximate an opening through said liner.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.