Gas turbine combustor
US4704869A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Sep 17, 1986 |
| Grant date | Nov 10, 1987 |
| Priority date | — |
| Expiry date | Sep 17, 2006 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/02
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine combustor has a plurality of burner units each having an inner tube defining a combustion chamber therein and an outer tube surrounding the inner tube coaxially therewith. A fuel is injected into the head portion of the inner tube and is burnt in the combustion chamber to produce hot combustion gases which are guided through a tail tube to stationary blades of a gas turbine. Combustion air is supplied through an annular passage between the inner and outer tubes from the area around the tail tube to the head portion of the inner tube. A flow-uniformalizing tube is disposed between the inner and outer tubes to cooperate with the inner tube to define therebetween an air passage. The flow-uniformalizing tube imparts a greater flow resistance to air flow from the back side of the tail tube than to the air flow from the side thereof diametrically remote from the back side, so that the flow velocity of the air flowing through the air passage is substantially uniformalized in the circumferential direction of the inner tube.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.