Gas turbine burner
US4012904A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Jul 17, 1975 |
| Grant date | Mar 22, 1977 |
| Priority date | — |
| Expiry date | Jul 17, 1995 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2270/31
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
NOx formation in a fixed geometry burner is minimized during steady state operation of a gas turbine engine by burning homogenous gaseous fuel and air mixtures in successive combustion stages of controlled duration and temperature determined by fuel to air ratios proximate the lean limit for combustion. When combustion is substantially complete in each stage NOx, formation is further inhibited by quenching the combustion temperature with comparatively cool air or the lean mixture for the next successive stage. Nox formation is effectively minimized during acceleration by supplying fuel to the combustion stages in sufficiently rich mixtures to consume all the available oxygen and to effect comparatively cool combustion temperatures. Adjacent the downstream end of the final combustion stage and appreciably upstream of the turbine rotor stages, the combustion temperature is again cooled by introducing a large excess of comparatively cool air which affects substantially complete oxidation of unburned HC and CO and a resulting maximum temperature approximating 2700.degree.F. as the gaseous combustion products enter the rotor stages.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.