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US 2009/0151358 A1Published application
Turbine Engine Combustor
AssigneeUnited Technologies Corporation
InventorCurtis C. Cowan
Life of this patent
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Abstract
A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.
Claims11
A combustor system for a gas turbine engine comprising:
- a combustion chamber having at least one air inlet for receiving air;
- at least a first source of a gaseous first fuel;
- at least a second source of an essentially liquid second fuel;
- and
- at least one fuel injector positioned to introduce the first and second fuels to the air.
2 more elements
Dependencies are inferred from the claim text.