Combustion control system
US4255927A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jun 29, 1978 |
| Grant date | Mar 17, 1981 |
| Priority date | — |
| Expiry date | Jun 29, 1998 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05B2200/15
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion system for gas turbines is disclosed which is capable of burning gaseous and liquid fuels. Excess air injected into the reaction zone of the combustor produces either a fuel-lean or fuel-rich mixture which lowers the temperature at which combustion occurs and thereby reduces the amount of nitrogen oxides in the turbine exhaust. Efficient combustion is maintained across a wide range of turbine loads by means of a control mechanism disposed externally of the combustor, which directs the airflow from the compressor to the reaction zone and to the downstream dilution zone respectively in a manner which permits variable, inverse proportioning of the air supplied to these zones. The variation in the pressure drop across the combustor is maintained within acceptable limits throughout the full load range.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.