Burner arrangement for a gas turbine including an inlet-air impingement plate
US6209327A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Aug 9, 1999 |
| Grant date | Apr 3, 2001 |
| Priority date | — |
| Expiry date | Aug 9, 2019 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23M9/02
- WIPO fieldThermal processes and apparatus
- WIPO sectorMechanical engineering
Abstract
A burner arrangement (20) for a gas turbine comprises an interior space (22) enclosed by a casing (23), in which interior space (22) at least one burner (21) is arranged, and into which interior space (22) in each case a jet (26, 27) of a gaseous medium, in particular air, is sprayed through at least two nozzle openings (24, 25) against the direction of flow of the burner (21) and along the inner wall (23a) of the casing (23) which jets (26, 27), guided by the inner wall (23a), meet one another from opposite directions and combine to form a secondary flow (28) flowing off perpendicularly from the inner wall (23a). In such a burner arrangement, the flow is stabilized and evened out by virtue of the fact that, to establish the impingement point of the jets (26, 27), a dividing plate (29) arranged in the flow path of the jets (26, 27) and disposed essentially perpendicularly to the inner wall (23a) is provided.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.