Fuel preheating in a gas turbine
AssigneeSiemens Aktiengesellschaft
InventorKlaus Werner
Life of this patent
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Abstract
A gas turbine and a method for operating a gas turbine includes a combustion chamber, a turbine having rows of blades, an air compressor, a combustion-air line for feeding compressed air into the combustion chamber, a fuel supply unit, at least one fuel line, at least one cooling-air line. Some of the blades have an interior defining cavities whereby first cavities direct at least a portion of fuel to the combustion chamber through the first cavities at least in a section of the blades, thereby preheating the fuel before being introduced into the combustion chamber. The system defined by the first cavities and the section of the blades is closed relative to an interior of the gas turbine. Second cavities fluidically connect to the air compressor and receive at least a portion of the cooling air for cooling the blades.
Claims13
A method of operating a gas turbine, which comprises:
- providing a gas turbine having:
- a combustion chamber;
- a turbine having at least two rows of blades, at least some of the blades having an interior defining first cavities and second cavities;
- and
- an air compressor;
- feeding compressed air and fuel to the combustion chamber;
- feeding cooling air to the turbine;
- directing at least a portion of fuel at least in a section of the blades through the first cavities and simultaneously preheating the portion of fuel before the portion of fuel is introduced into the combustion chamber;
- and
- directing cooling air fed to the turbine in a further section of the blades through the second cavities and discharging the cooling air at least partly at the blades.
A gas turbine, comprising:
- a combustion chamber;
- a turbine having at least two rows of blades, at least some of the blades having an interior defining first cavities and second cavities;
- an air compressor;
- a combustion-air line for feeding compressed air into said combustion chamber, said combustion-air line fluidically connected to said air compressor and said combustion chamber;
- a supply unit for supplying fuel;
- at least one fuel line for feeding fuel into said combustion chamber, said at least one fuel line fluidically connected to said combustion chamber and to said supply unit;
- at least one cooling-air line for feeding cooling air into said turbine, said at least one cooling-air line fluidically connected to said turbine and to said air compressor;
- said first cavities fluidically connected to said combustion chamber and to said supply unit for directing at least a portion of fuel to said combustion chamber from said supply unit through said first cavities at least in a section of said blades and, thereby, preheating said portion of fuel before being introduced into said combustion chamber, a system defined by said first cavities and said section of said blades being closed relative to an interior of the gas turbine;
- and
- said second cavities fluidically connected to said air compressor and receiving at least a portion of the cooling air through said second cavities for cooling said blades.
Dependencies are inferred from the claim text.