BY-PASS TURBO-JET ENGINE Russian patent published in 1998 - IPC

FIELD: gas turbine engines with afterburner and heat exchanger of turbine cooling system in outer loop. SUBSTANCE: turbo-jet engine includes low-pressure compressor, hinge-pressure turbo-compressor and afterburner brought in communication with low-pressure compressor through corrugated wells of mixer and longitudinal passages of air-to-air heat exchanger located in outer loop. Ratio of outlet area of corrugated wells to area of outer loop before wells ranges from 0.20 to 0.35. Length of longitudinal passages of air-to-air heat exchanger ranges from 0.15 to 0.35 of length of wave of first tangential mode of oscillations of afterburner. EFFECT: reduced effect of afterburner on stable operation of low-pressure compressor and engine as a whole in dynamic modes of operation. 2 cl, 2 dwg