Premixed pilot burner for a combustion turbine engine
US6848260B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Sep 23, 2002 |
| Grant date | Feb 1, 2005 |
| Priority date | — |
| Expiry date | Jan 23, 2023 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/343
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor (40) for a gas turbine engine is provided with a premix pilot fuel stage (42) in order to reduce the emission of oxides of nitrogen from the engine. An in-service engine may be modified to add the premix pilot fuel stage by delivering premix pilot fuel to a ring manifold (42) for tip-feeding a premix pilot fuel outlet member such as a swirler vane (78) or fuel peg (124). In this manner, complex and expensive components such as the top hat (46), support housing (48) and diffusion pilot burner assembly (44) may be used without modification. Thermal stresses caused by the differential cooling of the ring manifold by the premix pilot fuel (96) are reduced by a heat shield (94) installed within the manifold.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.