Temperature mixing enhancement with locally co-swirling quench jet pattern for gas turbine engine combustor
US9322554B2 · kind B2 · utility
5Cited by
9References
29Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 29, 2011 |
| Grant date | Apr 26, 2016 |
| Priority date | — |
| Expiry date | Mar 23, 2034 |
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 includes a first liner defined about an axis with a first row of first combustion air holes, one of the first combustion air holes is defined along each of a multiple of fuel injector zero pitch lines. A second liner defined about the axis with a second row of second combustion air holes, each of the second combustion air holes circumferentially offset relative to each of the multiple of fuel injector zero pitch lines.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.