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US 6,314,716 B1Granted
Serial cooling of a combustor for a gas turbine engine
AssigneeSolar Turbines Incorporated
InventorsMario E. Abreu, Janusz J. Kielczyk
Life of this patent
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Abstract
A combustor for a gas turbine engine uses compressed air to cool a combustor liner and uses at least a portion of the same compressed air for combustion air. A flow diverting mechanism regulates compressed air flow entering a combustion air plenum feeding combustion air to a plurality of fuel nozzles. The flow diverting mechanism adjusts combustion air according to engine loading.
Claims10
A combustor for a gas turbine engine comprising:
- a combustor liner, said combustor liner having an inlet end portion and an exit end portion, said combustor liner defining a combustion zone therein;
- cooling air passage being defined by a cooling shield and said combustor liner, said cooling air passage having a plurality convection enhancing devices being disposed on said combustor liner;
- an air passage being fluidly connected with said cooling air passage proximate said exit end portion;
- a combustion air plenum being fluidly connected with said cooling air passage proximate said inlet end portion, said combustion air plenum being fluidly connected with said combustion zone;
- a flow diverting mechanism being positioned intermediate said cooling air passage and said combustion air plenum, said flow diverting mechanism being movable between a first and second position, said first position allowing fluid communication between said cooling air passage and said combustion air plenum, said second position preventing fluid communication between said combustion air plenum and said cooling air passage.
2 more elements
Dependencies are inferred from the claim text.