Compact gas turbine engine
US5577380A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 6, 1995 |
| Grant date | Nov 26, 1996 |
| Priority date | — |
| Expiry date | Feb 6, 2015 |
Classification
- Technology area (CPC C)Chemistry; Metallurgy
- CPC primaryC08L2666/04
- WIPO fieldMacromolecular chemistry, polymers
- WIPO sectorChemistry
Abstract
A gas turbine engine 10 having a rotor 12 with turbine blades 14 and a nozzle 16 adjacent the turbine blades 14 for directing hot gases of combustion at the turbine blades 14. The engine 10 also includes an annular combustor 18 about the rotor 12 and an annular combustor housing 30 substantially surrounding the combustor 18 in generally concentric spaced relation. A fuel injection system is operatively associated with the combustor 18 for injecting fuel into a combustion space 28 to be combusted with air from a compressor 34. The fuel injection system may include a plurality of circumferentially spaced fuel injectors 68 disposed in an outer wall 20 of the combustor 18 together with a generally oval shaped manifold 70 in fluid communication with a primary fuel source and the fuel injectors 68. A turbine shroud 36 is provided to extend radially outward from the rotor to the outer wall of the combustor on the side of the nozzle 16 opposite the combustion space 28. The turbine shroud 36 is cooled by a film of air which passes through a plurality of circumferentially spaced orifices 40 in the outer wall 20 of the combustor 18. The engine 10 also includes an abutment member 38, 60 and a …
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.