Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
270 words
In a gas turbine combustor including a plurality of burner units arranged around an axis of a compressor, each burner unit having an inner tube provided with air ports formed in the wall thereof, an outer tube surrounding said inner tube, a fuel nozzle for supplying a fuel into a head portion of said inner tube, a tail tube for guiding combustion gases produced in said inner tube to stationary blades of an associated gas turbine, an annular air passage formed between said inner tube and said outer tube, an annular chamber formed around said tail tube and communicating with said annular air passage through a substantially circular air inlet, and means for providing communication between an air outlet of said compressor and said annular chamber, said communication means being nearer to the compressor axis, radially thereof, then said inner tube, said air inlet including first and second areas, said first area being more remote from said axis, radially thereof, than said second area, and a flow-uniformalizing tube disposed adjacent to said air inlet to said annular passage and around said inner tube and extending into said annular chamber, said flow-uniformalizing tube having an end extremity disposed in said annular chamber, said end extremity being generally oblique relative to the axis of said inner tube and arranged such that said flow-uniformalizing tube extends deeper into said annular chamber in said first area of said air inlet than in said second area thereof to impart a greater flow resistance to the flow of air in said first area of said air inlet than in said second area of said air inlet.
Claim 2
Dependent Claim
270 words
In a gas turbine combustor including a plurality of burner units arranged around an axis of a compressor, each burner unit having an inner tube provided with air ports formed in the wall thereof, an outer tube surrounding said inner tube, a fuel nozzle for supplying a fuel into a head portion of said inner tube, a tail tube for guiding combustion gases produced in said inner tube to stationary blades of an associated gas turbine, an annular air passage formed between said inner tube and said outer tube, an annular chamber formed around said tail tube and communicating with said annular air passage through a substantially circular air inlet, and means for providing communication between an air outlet of said compressor and said annular chamber, said communication means being nearer to the compressor axis, radially thereof, then said inner tube, said air inlet including first and second areas, said first area being more remote from said axis, radially thereof, than said second area, and a flow-uniformalizing tube disposed adjacent to said air inlet to said annular passage and around said inner tube and extending into said annular chamber, said flow-uniformalizing tube having an end extremity disposed in said annular chamber, said end extremity being generally oblique relative to the axis of said inner tube and arranged such that said flow-uniformalizing tube extends deeper into said annular chamber in said first area of said air inlet than in said second area thereof to impart a greater flow resistance to the flow of air in said first area of said air inlet than in said second area of said air inlet.