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US 4,483,137 AGranted
Gas turbine engine construction and operation
AssigneeSolar Turbines Incorporated
InventorRobie L. Faulkner
Life of this patent
Estimating the term…
Abstract
Gas turbine engines in which provision is made for introducing a liquid coolant into the combustor of the engine. This reduces the flame temperature in the combustor, thereby discouraging the formation of thermal NO.sub.x.
Claims15
Combustion apparatus comprising the combination of:
- a combustor in which liquid fuel can be burned and means for reducing the emission of nitrogen oxides from said combustor, said last-mentioned means comprising means for;
- introducing a liquid coolant and the liquid fuel into said combustor;
- there mixing said coolant with said fuel;
- atomizing the fuel and coolant and forming a uniform mixture of fuel, coolant, and combustion air as the mixture enters the primary combustion zone in said combustor, said means for introducing a liquid coolant and the liquid fuel into said combustor comprising at least one fuel injection nozzle for introducing the liquid fuel into the combustor and means for introducing said liquid coolant into said combustor through said fuel injection nozzle, said fuel injection nozzle comprising a body having a centrally disposed combustion air passage extending through and opening onto one end thereof and an annular liquid fuel passage concentrically surrounding said air passage and opening onto the same end of the nozzle as said combustion air passage;
- said combustor further comprising means for introducing the liquid fuel into said annular passage;
- means for introducing the liquid coolant into the combustion air passage, and means for forming said liquid coolant into a film on the wall of said combustion air passage comprising means for introducing air into said centrally disposed passage and means for imparting a swirl to the air in said centrally disposed passage, thereby promoting the uniform mixing of said coolant and said fuel as they are discharged from said one end of said fuel injection nozzle.
3 more elements
A gas turbine engine comprising:
- a compressor;
- turbine means for driving said compressor and for providing kinetic energy in useful form;
- a combustor in which the liquid fuel can be burned with air discharged from said compressor to provide hot gases for driving said turbine means;
- and means for reducing the emission of nitrogen oxides from said engine, said last-mentioned means comprising:
- means for introducing a liquid coolant and the liquid fuel into said combustor;
- there mixing said coolant with said fuel;
- atomizing the fuel;
- and forming a uniform mixture of air, liquid coolant, and fuel as said mixture enters the primary combustion zone in said combustor, said means for introducing a liquid coolant and the liquid fuel into said combustor comprising at least one fuel injection nozzle for introducing the liquid fuel into the gas turbine engine combustor and means for introducing the liquid coolant into said combustor through said fuel injection nozzle, said fuel injection nozzle comprising a body having a centrally disposed, combustion air passage extending through and opening onto one end thereof and an annular liquid fuel passage concentrically surrounding said combustion air passage and opening onto the same end of said body as the latter;
- said gas turbine engine further comprising means for introducing the liquid fuel into said annular passage;
- means for introducing the liquid coolant into the combustion air passage;
- and means for forming said liquid coolant into a film on the wall of said combustion air passage comprising means for introducing air into said centrally disposed passage and means for imparting a swirl to the air in said centrally disposed passage, thereby promoting the uniform mixing of said coolant and said fuel as they are discharged from said one end of said fuel injection nozzle.
8 more elements
A gas turbine engine comprising:
- a compressor;
- turbine means for driving said compressor and for providing kinetic energy in useful form;
- a combustor in which the liquid fuel can be burned with air discharged from said compressor to provide hot gases for driving said turbine means;
- and means for reducing the emission of nitrogen oxides from said engine, said last-mentioned means for comprising means for:
- introducing a liquid coolant and the liquid fuel into said combustor;
- there mixing said coolant with said fuel;
- atomizing the fuel;
- and forming a uniform mixture of air, liquid coolant, and fuel as said mixture enters the primary combustion zone in said combustor, including means comprising a plurality of fuel injection nozzles for introducing the liquid fuel into the gas turbine engine combustor and means for introducing the liquid coolant into said combustor through said fuel injection nozzles, said fuel injection nozzles being equidistantly spaced in a circular array and the means for supplying the liquid fuel to the nozzles comprising upper and lower, arcuately shaped fuel manifolds having, together, an essentially circular configuration, the circular array of equiangularly spaced fuel injection nozzles being spaced concentrically within the circle formed by said manifolds;
- fuel lines connecting those fuel injectors girdled by each of the manifolds to that manifold at generally equidistantly spaced locations therealong;
- means for supplying fuel to the upper manifold at the opposite ends thereof;
- a fuel supply line connected between said fuel supplying means and said lower manifold approximately mid way between the ends of the latter;
- and means in said fuel supply line for creating a pressure drop that is effective to cause said fuel to be distributed at rates approaching equal through the upper and lower fuel manifolds.
9 more elements
Dependencies are inferred from the claim text.