Combustion chamber for gas turbine engines, particularly an ignition device for such a combustion chamber
US4204404A · kind A · utility
1Cited by
2References
5Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 8, 1978 |
| Grant date | May 27, 1980 |
| Priority date | — |
| Expiry date | May 8, 1998 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/266
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion chamber for gas turbine engines, particularly aircraft turbojet engines, which is constituted of an outer casing, at least one flame tube inserted therein, and incorporating at least one ignition device for the produced, respectively, supplied fuel-air mixture. The ignition device comprises two high-capacity ignition or spark plugs which are presently arranged in series in a single axial plane in the flame tube, and further including an ignition fuel nozzle, whose fuel injection spray cone will simultaneously encompass the ignition spark zones of both high-capacity spark plugs.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.