Gas turbine combustor endcover with adjustable flow restrictor and related method
US9188340B2 · kind B2 · utility
1Cited by
3References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 18, 2011 |
| Grant date | Nov 17, 2015 |
| Priority date | — |
| Expiry date | Sep 17, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49238
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An endcover for a turbine combustor adapted to support one or more combustor nozzles, includes a plate having one side which in use, faces a combustion chamber and an opposite side which, in use, faces away from the combustion chamber. At least one fuel cavity is formed in the plate; and a fuel restrictor insert is formed with at least one flow orifice located within the fuel cavity for supplying fuel to at least one combustor nozzle. The fuel restrictor insert is adjustable along a length dimension of the fuel cavity.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.