BYPASS GAS TURBINE ENGINE Russian patent published in 2014 - IPC F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises compressor, combustion chamber, high-pressure turbine and low-pressure turbine with distributor. Distributor inner cavities abut on cooled nozzle vanes walls and are connected with cooling air bleed chamber and separated from disc space supercharge line with the help of transfer pipes. Transfer pipes are arranged inside nozzle vanes with clearance relative to their walls and connected by the inlet with feed manifold and the outlet with disc space supercharge line. Disc space supercharge line feed manifold is communicated with high-pressure compressor dummies chamber separated from compressor flow section outlet by moving seal. Combustion chamber cavity or that of one of compressor stages make the cooling air bleed chamber for its feed to the walls of low-pressure turbine nozzle vanes. Cooling air bleed chamber is connected to low-pressure nozzle vanes wall via connection line and extra feed manifolds. Regulating valve is fitted at connection line.

EFFECT: control over cooling air flow rate subjected to engine operating conditions.

4 cl, 2 dwg