Gas turbine with a concentric fuel line, and a connection to duplex burner head

摘要

The present invention relates to an aircraft gas turbine with a plurality of burners 25 which, in order to supply of fuel via burner heads 30 are connected with a fuel line 31, each burner 25 as a duplex burner with two separately switchable force material channels 32, 33 is provided, wherein the fuel line 31 two fuel channels 34, 35, which are concentrically formed, an inner fuel channel 34 for the temporary flow of fuel and an outer fuel channel 35 for the permanent flow are formed with fuel, wherein in the region of the connection of the fuel line 31 to the burner head 30 in each fuel channel 34, 35 a check valve 36, 37 is arranged.