FIELD: engines.
SUBSTANCE: invention relates to gas turbine engines (GTE) of axial type and can be used in power plants to drive electric generators and in the field of transport as mechanical drive or turbojet propulsor. In a gas turbine engine, which includes a combustion chamber with the formed combustion products removal to the successively arranged stages of the cooled nozzle and working blades of the turbine, additional gaseous fuel is supplied to the flow part of the turbine of at least the second expansion stage. At the inlet between turbine nozzle blades there are additional guide vanes-nozzles with additional fuel supply channels, the fuel output from which is located in the zone of the narrowest section between adjacent nozzle blades. At that, in the additional guide blades there are additional air supply channels, the outlet from which is located near the fuel outlet, and in case of using regasified LNG as a source of gaseous fuel, cold natural gas is connected to closed cooling channels of nozzle blades before its combustion in the main combustion chamber and/or additional afterburning stages.
EFFECT: higher efficiency and power of GTE, as well as possibility of using existing GTE for their modernization or reconstruction.
3 cl, 3 dwg
