Gas turbine combustor with liner air admission holes associated with interpersed main and pilot swirler assemblies
US8789374B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Feb 7, 2013 |
| Grant date | Jul 29, 2014 |
| Priority date | — |
| Expiry date | Feb 7, 2033 |
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 having an annular combustion chamber includes a plurality of main fuel injection and air swirler assemblies and a plurality of pilot fuel injection and air swirler assemblies disposed in a circumferential ring extending about the circumferential expanse of a forward bulkhead. The plurality of pilot fuel injection and air swirler assemblies are interspersed amongst and disposed in the circumferential ring of main fuel injection and air swirler assemblies. Fuel being supplied to the combustor is selectively distributed between the plurality of main fuel injection and air swirler assemblies and the plurality of pilot fuel injection and air swirler assemblies in response to the level of power demand on the gas turbine engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.