Combustor for a gas turbine engine
US8726626B2 · kind B2 · utility
5Cited by
7References
17Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Dec 17, 2012 |
| Grant date | May 20, 2014 |
| Priority date | — |
| Expiry date | Dec 17, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02E20/34
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustor in a gas turbine engine has a wall which forms a gap with an outer nozzle guide vane platform. A closure mechanism is operable to open or close the gap. Opening of the gap, for example during cruise conditions, reduces the mass flow rate of air through an open end of the combustor, so enriching the air fuel ratio and improving flame stability and combustion efficiency. Under high power conditions, the gap is closed, causing an increase in air flow rate through the open end to achieve a lean burn air fuel ratio when the fuel flow rate is increased.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.