DUAL-FLOW TURBOJET ENGINE Russian patent published in 2017 - IPC F01D5/18 F02C7/18 

FIELD: engines and pumps.

SUBSTANCE: dual-flow turbojet engine contains a compressor with a dummy cavity, a combustion chamber, a turbine, a turbine swirl flow device communicated with both the transit cavities of the turbine nozzle blades, and the high-pressure air supply channels, rotating deflector and the low-pressure air supply channels communicated with internal cavities of the cooled turbine blades. The cooled turbine rotor blades are made in the form of a profile limited by the inlet and outlet edges, the trough and the back with a partition separating the inner cavity of each turbine rotor blade adjacent to the input edge from the rest of the cavity. The internal cavity of each turbine rotor blade adjacent to the input edge is communicated with both the high-pressure air supply system and with the wheelspace through the perforations at the inlet edge. The rest of the cavity is communicated with the low pressure air supply system. The remaining cavity of each turbine rotor blade is divided along the middle line of the profile by a longitudinal partition and forms a channel adjacent to the profile trough and a channel adjacent to the profile back. In the upper part of each blade, air channels are made, connected on one side through the internal cavity of each turbine rotor blade adjacent to the inlet edge, with the high-pressure air supply system, and on the other side with the channel adjacent to the profile trough. The channel adjacent to the profile back is connected to the low pressure air supply system. In this case, the channels adjacent to the trough and back of the profile, through the perforations on the trough and back of the profile, are respectively connected to the wheelspace.

EFFECT: invention improves the engine efficiency, the life and reliability of the turbine blade.

8 cl, 7 dwg