Combustor apparatus for stoichiometric combustion

Abstract

Gas turbine combustor with a specific fuel and oxidizer flow arrangement which provides high combustion efficiency for stoichiometric diffusion combustion in gas turbine applications operating with oxygen deficient working fluids.

What is claimed is: 
     
         1 . A combustor comprising a housing having an inner surface, a nozzle and a liner assembly positioned within said housing, said liner having an interior volume and being spaced apart from the inner surface of the housing to define a path extending longitudinally along the combustor for transporting working fluid to said interior volume, said liner being provided with mixing holes and dilution holes positioned longitudinally along said liner as a function of the internal diameter of the liner. 
     
     
         2 . A combustor according to  claim 1 , wherein liner mixing holes are positioned at an axial distance from the nozzle of 0.65-1.05D, where D is the internal diameter of the liner. 
     
     
         3 . A combustor according to  claim 1 , wherein the liner mixing holes generate a jet penetration into the interior volume of the liner 1.05-1.4 D 1 , where D 1  is the diameter of the mixing hole. 
     
     
         4 . A combustor according to  claim 1  wherein the dilution holes and are positioned at an axial distance from the nozzle of 1.3-1.7 D, where D is the internal diameter of the liner. 
     
     
         5 . A combustor according to  claim 1 , wherein the dilution holes create a jet penetration into the interior volume of the liner of 1.4-1.6 D 2 , where D 2  is the diameter of the dilution hole. 
     
     
         6 . A combustor according to  claim 1 , wherein crown holes are provided which accommodate about 6-9% of the working fluid. 
     
     
         7 . A combustor according to  claim 5 , wherein the crown hole creates a recirculation bubble of length of 0.65-1.05 D, where D is the internal diameter of the liner. 
     
     
         8 . A combustor according to  claim 1 , wherein the dilution holes accommodate 8-11% of the total combustor flow. 
     
     
         9 . A combustor according to  claim 1 , wherein cooling holes are provided which accommodate 30-32% of the working fluid at compressor discharge. 
     
     
         10 . A combustor according to  claim 1 , wherein the outer passage flows 25-30% of the working fluid at compressor discharge. 
     
     
         11 . A combustor according to  claim 1 , wherein an integrated igniter is provided for igniting the working fluid. 
     
     
         12 . A combustor according to  claim 1  in which the nozzle passages are inclined such that they produce counter-rotating flow between the oxidizer and working fluid. 
     
     
         13 . A combustor according to  claim 1  in which the nozzle passages are inclined such that they produce co-rotating flow between the oxidizer and working fluid.