Gas turbine combustion chamber
US5426943A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Nov 14, 1994 |
| Grant date | Jun 27, 1995 |
| Priority date | — |
| Expiry date | Nov 14, 2014 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05B2260/2241
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
In a gas turbine combustion chamber (1)--having environment-friendly burners (5) which consist of at least two hollow partial conical bodies which are positioned one upon the other in the flow direction and whose longitudinal axes of symmetry extend radially offset relative to one another, by which means tangential opposed-flow air inlet slots are produced for a combustion air flow, at least one nozzle for spraying in the fuel being placed in the hollow conical space formed by the cone-shaped partial conical bodies, and having a cooling duct (4), which is bounded by the combustion chamber inner wall (2) and the combustion chamber outer wall (3), along which the cooling air flows and in which longitudinal and transverse ribs (8) can be arranged--the cooling duct (4) has a continuously decreasing height and/or increasing surface roughness in the flow direction of the cooling air. The total mass flow coming from the compressor (7) is used for pure convective cooling of the combustion chamber inner wall (2) and takes part in the combustion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.