Patent ID: 6908303

Claim:
A premixed air-fuel mixture supply device combined with a combustor liner included in a combustor for a gas turbine or an aircraft engine, said premixed air-fuel mixture supply device comprising: a pilot fuel injection unit having an inner wall connected to a head part of the combustor liner; and a prevaporizing, premixing main fuel injection unit having an outer wall connected to the head part of the combustor liner and surrounding the inner wall; wherein the inner wall and the outer wall define a combustion air passage, an intermediate wall is disposed in the combustion air passage so as to divide an upstream part of the combustion air passage into an inner combustion air passage surrounding the inner wall, and an outer combustion air passage surrounding the intermediate wall, fuel injecting holes are formed in the intermediate wall to inject fuel radially outward so as to cross air currents flowing through the combustion air passage into the outer combustion air passage of the combustion air passage, and an atomization lip is formed in a tail part of the intermediate wall to promoting the atomization of fuel adhering to the tail part at a downstream edge of the intermediate wall.