GAS-TURBINE ENGINE Russian patent published in 2004 - IPC

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed by-pass gas-turbine engine has outer circuit 1 and inner circuit including series mounted high-pressure 2, combustion chamber 3 and cooled turbine 4. Air space 14 of combustion chamber 3 is connected through multichannel air duct 15 with nozzle swirler 16. Dummy space 18 is found between compressor 2, inner casing 10 of combustion chamber 3, impeller 5 of high-pressure turbine and shaft 17 connecting compressor 2 with turbine 4, dummy space being separated from passage part of compressor 2 by labyrinth seal 19. Dummy space 18 communicates through supply air ducts 20 located in outer circuit 1 in direction of air flow with inter-disk space 9 and through holes 21, with inner space of swirler 16. By-pass gas turbine engine is furnished with heat exchanger 22 one part of whose section 23 communicates at inlet with air space 14 of combustion chamber 3, and at outlet it communicates through inner spaces of blades 7 of high-pressure turbine nozzle assembly with inlet of swirler 16. Other part of sections 24 is located on supply air ducts 20 being communicated at inlet with dummy space 18 of compressor 2, and at outlet, with inner space of blades 8 of low-pressure turbine nozzle assembly. At least one of sections 23 is located in heat exchanger 22 at both sides of one of sections 24. All outlets of hollow posts 12 connecting outer and inner casings of combustion chamber 3 are interconnected by distributing manifold 25 to which each section 24 of heat exchanger 22 is connected. Number of hollow posts 12 coincides with number of sections 24 of heat exchanger 22.

EFFECT: increased economy and reliability of engine.

4 cl, 5 dwg