Gas turbine combustor
This patent describes a gas turbine combustor including burner units arranged around an axis of a compressor. Each burner unit has an inner tube provided with air ports formed in the wall thereof, an outer tube surrounding the inner tube, a fuel nozzle for supplying a fuel into a head portion of the inner tube, a tail tube for guiding combustion gases produced in the inner tube to stationary blades of an associated gas turbine, an annular air passage formed between the inner tube and the outer tube, an annular chamber formed around the tail tube, and means for providing communication between an air outlet of the compressor and the annular chamber. The communication means are nearer to the compressor axis, radially thereof, than the inner tube. The air inlet includes first and second areas. The first area is more remote from the axis, radially thereof, than the second area, and a flow-uniformalizing tube is disposed adjacent to the air inlet to the annular passage and around the inner tube and extending into the annular chamber. The flow-uniformalizing tube has an end extremity disposed in the annular chamber. The end extremity is generally oblique relative to the axis of the inner tube and arranged such that flow-uniformalizing tube extends deeper into the annular chamber in the first area of the air inlet than in the second area thereof to impart a greater flow resistance to the flow of air in the first area of the air inlet than in the second area of the air inlet.
- Assignee:
- Hitachi, Ltd., Tokyo
- Patent Number(s):
- US 4704869
- OSTI ID:
- 5901380
- Resource Relation:
- Patent File Date: Filed date 17 Sep 1986
- Country of Publication:
- United States
- Language:
- English
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