METHOD OF OPERATION OF GAS TURBINE ENGINE Russian patent published in 1995 - IPC

FIELD: mechanical engineering. SUBSTANCE: housing 3 is positioned in engine bonnet with a spaced relation. The main multi-stage compressor is mounted in housing 3. The compressor has rotor 4 with front deflector 5. Combustion chamber 9 has controller 10 of auxiliary air flow rate. Space 2 is in communication with flowing part 16 of an axial compressor, and outlet of the main compressor is in communication with combustion chamber 9 and cooling paths. Auxiliary compressor 8 is made up of radial blades 18 secured to disk 13 of the turbine. Guide blades 6 of the first stage of the main compressor and deflector 5 are provided with cooling passages 19,20. Additional cooling paths are made in nozzle and working blades 12 of turbine 11. Heat exchanger 17 is in communication with space 2 by coolant. The heat exchanger is also connected to the outlet of the main compressor by heating fluid and to inlets of passages 19 of guide blades 6 outlets of which are in communication with inlets of passages 20. The inlet and outlet of compressor 8 are in communication with outlets of passages 20 and inlet of the additional cooling path of blade 12 correspondingly. The outlet of the additional path is in communication with controller 10. EFFECT: enhanced efficiency. 4 dwg