Gas turbine combustor liner cap assembly
US8572979B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 24, 2010 |
| Grant date | Nov 5, 2013 |
| Priority date | — |
| Expiry date | Jun 14, 2032 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00018
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.