AIRCRAFT BYPASS GAS TURBINE ENGINE FURNISHED WITH PRECOOLER Russian patent published in 2010 - IPC F02K3/06 

FIELD: engines and pumps.

SUBSTANCE: aircraft bypass gas turbine engine comprises hollow nacelle with front air inlet and rear air outlet. Central hot air generator is arranged axially in said nacelle and fan is mounted ahead of it to generate cold airflow for gas turbine engine. Outer and inner fairings are arranged inside nacelle to embrace central generator and to constrict cold air flow fan duct with circular cross section. Inner fairing with central generator constrict intermediate chamber with circular cross section that embraces central generator and is furnished with at least one rear bore at hot air periphery. Precooler comprises inlet to take in hot air from central generator and outlet of cooled hot air produced using cold air. Precooler is arranged intermediate chamber in thermal contact with rear part of inner fairing to form intermediate channel between precooler and central generator. There is at least one air intake arranged ahead of precooler that passes through inner fairing to bleed cooling air flow from cold flow to at least partially cool hot air flow coming into precooler.

EFFECT: ruling out aerodynamic disturbances in fan duct.

10 cl, 11 dwg