Combustion apparatus for a gas turbine engine
US4693074A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | May 16, 1986 |
| Grant date | Sep 15, 1987 |
| Priority date | — |
| Expiry date | May 16, 2006 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/14
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
The present invention relates to combustion apparatus for gas turbine engines. An annular combustion chamber of a gas turbine engine comprises an upstream wall formed from a single metal skin. The upstream wall has a plurality of equi-spaced apertures, and a convergent/divergent pot is positioned coaxially with each aperture and extends in an upstream direction therefrom. Each convergent/divergent pot has a radial swirler assembly positioned a its upstream end to supply air into the convergent/divergent pot. A fuel injector is aligned with each convergent/divergent pot and radial swirler assembly to supply fuel into the convergent/divergent pot. A plurality of annular air scoops extend in an upstream direction from the upstream wall, and each annular air scoop is positioned coaxially around a convergent/divergent pot to supply air to the radial swirler assembly. The downstream end of each convergent/divergent pot has apertures for supplying cooling air over the downstream face of the upstream wall.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.