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US 6,192,669 B1Granted
Combustion chamber of a gas turbine
AssigneeAsea Brown Boveri AG
InventorsJakob Keller, Roger Suter
Life of this patent
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Abstract
A combustion chamber in a gas-turbine, wherein the combustion chamber has an annular-toroidal-shaped interior space. A plurality of burners are arranged on the periphery of the combustion chamber, wherein the burners are operatively connected to the annular-toroidal-shaped interior space so as to initiate a swirl flow. The swirl flow forms a vortex core and the vortex core ensures the stability of the flame front.
Claims4
A combustion chamber of a gas-turbine, said combustion chamber comprising:
- at least one annular toroidal interior space of quasi-circular cross-section;
- a plurality of burners, wherein each burner of said plurality of burners is in operative connection with said at least one annular toroidal interior space so as to be tangentially arranged on a periphery of said combustion chamber and wherein each burner of said plurality of burners is a pre-mix burner;
- a hot-gas outlet duct defining an incident-flow plane of a downstream turbine of said gas-tuxbine, said hot-gas duct connected to said annular toroidal interior space, wherein said hot-gas duct is branched off in a peripheral tangential direction of said annular toroidal interior space;
- and
- wherein in cross-sectional of said annular toroidal interior space, the axis vector pointing out of any of said burners and the axis vector pointing into said hot-gas outlet duct, point in the same direction.
2 more elements
Dependencies are inferred from the claim text.