Method for controlling gas turbine combustor
US5319919A · kind A · utility
7Cited by
9References
29Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 2, 1992 |
| Grant date | Jun 14, 1994 |
| Priority date | — |
| Expiry date | Dec 2, 2012 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/26
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method for controlling a gas turbine combustor which comprises nozzles for injecting fuel into a combustor and which serves to combust the fuel with air in a combustion chamber so as to rotatively drive a gas turbine by combustion gas compressed as a result of combustion of a fuel, wherein the ratio of a flow rate of fuel supplied into the combustor to a flow rate of air supplied into the combustor is changed in accordance with at least one of the states of fuel, air and rotational frequency of the turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.