Can combustor for a gas turbine engine
AssigneeSiemens Westinghouse Power Corporation
InventorRobert Bland
Life of this patent
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Abstract
A gas turbine engine (10) includes a plurality of can combustors (19). Each can combustor includes a first stage of burners (46) located at a first radius about the combustor centerline (42) and a second stage of burners (50) located at a second radius greater than the first radius. The second stage of burners may be clocked to an angular position that is not midway between respective neighboring burners of the first stage. Combustion instabilities may be controlled by exploiting variations in combustion parameters created by differential fueling of the two stages.
Claims18
A can combustor for a gas turbine engine comprising:
- a first stage comprising a first plurality of burners arranged symmetrically around a longitudinal centerline of a combustion chamber at a first radial distance from the centerline;
- and
- a second stage comprising a second plurality of burners arranged symmetrically around the centerline of the combustion chamber at a second radial distance different than the first radial distance.
A can combustor for a gas turbine engine comprising:
- a first stage comprising a first plurality of burners arranged symmetrically around a longitudinal centerline of a combustion chamber and angularly separated from each other by an angle of 360/N degrees;
- a second stage comprising a second plurality of burners arranged symmetrically around the longitudinal centerline of the combustion chamber and angularly separated from each other by an angle of 360/N degrees;
- wherein the burners of the second stage are positioned at respective angular locations other than midway between respective neighboring burners of the first stage.
A gas turbine engine comprising:
- a compressor for supplying compressed air;
- a can annular combustor for burning fuel in the compressed air to produce a hot gas;
- and
- a turbine for expanding the hot gas;
- wherein the can annular combustor further comprises a plurality of can combustors each comprising:
- an annular member defining a combustion chamber having a longitudinal centerline;
- a first plurality of burners fueled by a first fuel supply and disposed in a symmetrical ring around the centerline at a first radial distance;
- and
- a second plurality of burners fueled by a second fuel supply separately controllable from the first fuel supply, the second plurality of burners being disposed in a symmetrical ring around the centerline at a second radial distance greater than the first radial distance.
A gas turbine engine comprising:
- a compressor for supplying compressed air;
- a can annular combustor for burning fuel in the compressed air to produce a hot gas;
- and
- a turbine for expanding the hot gas;
- wherein the can annular combustor further comprises a plurality of can combustors each comprising:
- a first stage of burners disposed in a symmetrical circular pattern about a centerline, N being the number of burners in the first stage of burners and 360/N° being an angle of separation between burners of the first stage of burners;
- a second stage of burners disposed in a symmetrical circular pattern about the centerline, the burners of the second stage of burners being singularly disposed between respective neighboring burners of the first stage of burners, N being the number of burners in the second stage of burners and 360/N° being an angle of separation between burners of the second stage of burners;
- and
- an angular separation between burners of the first stage of burners and neighboring burners of the second stage of burners being an angle not equal to 360/2N°.
Dependencies are inferred from the claim text.