GAS TURBINE BURNER AND METHOD FOR COOLING LINER OF GAS TURBINE BURNER BY USING AIR COLLISION

摘要

PURPOSE: A gas turbine burner and a method for cooling a liner of the gas turbine burner are provided to lengthen the life span of the liner by cooling the liner using air such that the temperature is uniformly distributed on the liner and to reduce nitrogen oxide concentration by supplying air into a main combustion area. CONSTITUTION: A gas turbine burner comprises a casing(20) including an air inlet(20a) at one end. A fuel injection nozzle(30) is installed at the other end of the casing(20) so as to inject fuel into a combustion area. A liner(40) is positioned in the casing(20) in order to introduce main combustion air and diluted air. An air collision inducer(50) is installed between the liner(40) and the casing so as to allow air introduced into the casing to contact with a sidewall of a combustion chamber liner(40), thereby uniformly cooling the combustion chamber. A pivoting device(60) is provided to introduce air having the high temperature into an injection side of the fuel injection nozzle(30).