Method for operating a lean premix burner of an aircraft gas turbine and device for carrying out the method

Abstract

The present invention relates to a method for operating a lean premix burner of an aircraft gas turbine, where fuel and primary supporting air are supplied by means of a supporting burner (pilot burner) arranged centrically to the burner axis, where secondary air surrounding the supporting burner is supplied, and where fuel and air are supplied by means of a main burner, characterized in that the primary supporting air is supplied in an amount of 5 vol % to 10 vol % of the total air quantity, that the secondary supporting air is supplied in an amount of 5 vol % to 20 vol % and that 35 vol % to 75 vol % of the total air quantity are supplied via the main burner in the partial load range and in the full load range.

1 . Method for operating a lean premix burner of an aircraft gas turbine, where fuel and primary supporting air are supplied by means of a supporting burner (pilot burner) arranged centrically to the burner axis, where secondary air surrounding the supporting burner is supplied, and where fuel and air are supplied by means of a main burner, characterized in that the primary supporting air is supplied in an amount of 5 vol % to 10 vol % of the total air quantity, that the secondary supporting air is supplied in an amount of 5 vol % to 20 vol % and that 35 vol % to 75 vol % of the total air quantity are supplied via the main burner in the partial load range and in the full load range. 
     
     
         2 . Method in accordance with  claim 1 , characterized in that adjacent to the supporting burner a rich zone is formed, that the rich zone is enclosed by an intermediate admixing zone, that the intermediate admixing zone is enclosed and that the intermediate admixing zone is enclosed by a lean zone. 
     
     
         3 . Aircraft gas turbine lean premix burner for carrying out the method in accordance with  claim 1 , characterized in that a flame stabilizer concentrically surrounding the supporting burner is provided with secondary air recesses. 
     
     
         4 . Premix burner in accordance with  claim 3 , characterized in that the secondary air supply recesses are provided in the form of straight or V-shaped slots. 
     
     
         5 . Premix burner in accordance with  claim 3 , characterized in that the secondary air supply recesses are provided in the form of tubes (chutes).