Catalytic combustor having fuel flow control responsive to measured combustion parameters
US7421843B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 15, 2005 |
| Grant date | Sep 9, 2008 |
| Priority date | — |
| Expiry date | Jul 28, 2026 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00002
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustor (23) includes a catalytic combustion stage (22) receiving a first portion (18) of a total oxidizer flow (16) and a first portion (30) of a total fuel flow (29) and discharging a partially oxidized fuel/oxidizer mixture (40) into a post catalytic combustion stage (24) defined by a combustion liner (58). The combustor further includes an injector scoop (54) having an injector scoop inlet (56) in fluid communication with an opening (56) in the combustion liner for receiving a second portion (20) of the oxidizer flow. A fuel outlet (e.g. 64) selectively supplies a second portion (42) of the total fuel flow into the second portion of the oxidizer flow. The injector scoop includes an injector scoop outlet (66) in fluid communication with the post catalytic combustion stage and discharges a fuel/oxidizer mixture (44) into the partially combusted fuel/oxidizer mixture at an angle relative to the flow axis to impart a swirl to the fuel/oxidizer mixture as it enters the post catalytic combustion stage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.