| 摘要 |
FIELD: mechanical engineering; gas-turbine engines. ^ SUBSTANCE: proposed combination double-flow gas-turbine propeller-fan engine contains propeller fan, high-pressure compressor, combustion chamber with ball-torus convector, two-stage active-reactive turbine connected through shaft with propeller fan and through step-up gear with high-pressure compressor, reaction nozzle, reheat unit, liquid-propellant rocket engine and air-hydrogen heat exchanger. Air-hydrogen heat exchanger installed after propeller fan serves to reduce enthalpy of air compressed by propeller fan. Part of air after air-hydrogen heat exchanger passes through screen-intake, hollow shaped posts, housing manifold of turboexpander and its hollow blades, into expansion centripetal stage of turboexpander and further into heat-mass exchange device. Liquid air in heat-mass exchange device is separated into gaseous nitrogen and liquid oxygen which is sucked out by centrifugal stage of turboexpander and is directed to empty tank of launch vehicle. Second air-hydrogen heat exchanger inscribed into passage part of first loop and serving for additional reduction of enthalpy of air of first loop is installed between middle support of engine and its high-pressure compressor. Step-up gear is installed under inner housing of second heat exchanger after middle support. Step-up hear is coupled through drive gear and planet pinions with driven gear installed on shaft of high-pressure compressor. ^ EFFECT: increased thrust and height of flight. ^ 1 dwg |
