GAS TURBINE DRIVE OF LIQUID-PROPELLANT ROCKET ENGINE

摘要

aircraft engineering. SUBSTANCE: gas turbine drive of liquid propellant rocket engine has generator and nozzle assembly installed before turbine and including outer shell. Nozzle assembly has hollow fairing connected with outer shell by radial posts. It is arranged inside housing of gas generator along its longitudinal axis and is secured in housing by means of splines and threaded ring. Gas generator has cooling jacket. Ring space is formed between outer shell and gas generator housing. EFFECT: reduced overall dimensions and weight of gas generator, improved reliability in operation and stability of burning process in gas flow. 2 cl, 1 dwg