System and method for cooling a wall of a gas turbine combustor
US8397511B2 · kind B2 · utility
7Cited by
11References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 19, 2009 |
| Grant date | Mar 19, 2013 |
| Priority date | — |
| Expiry date | Jan 3, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A system, in one embodiment, includes an engine wall. The engine wall includes a cold-side and a hot-side. The engine wall includes one or more dilution holes, wherein each of the one or more dilution holes includes a first opening on the cold-side, a second opening on a hot-side, and a section of thermal barrier coating (TBC) applied on the cold-side and having an opening that generally circumscribes the first opening.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.