УСТРОЙСТВО ДЛЯ ОПРЕДЕЛЕНИЯ ХАРАКТЕРИСТИК И ГРАНИЦЫ УСТОЙЧИВОЙ РАБОТЫ КОМПРЕССОРА В СИСТЕМЕ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ (ГТД)

摘要

FIELD: aircraft engine and gas turbine manufacture. ^ SUBSTANCE: proposed method consists in introduction of vapor-and-gas mixture for shift of point of joint operation of compressor and turbine by compressor characteristic towards boundary of steady operation (surging) to combustion chamber of engine under test. Proposed device is provided with source for producing the working medium in form of vapor-and-gas mixture; this source is combustion chamber in form of combustion chamber of liquid propellant rocket engine with adjustable passages for delivery of fuel and oxidizer which are mounted in succession after combustion chamber, water supply section with adjustable water supply passage, evaporating chamber and section for distribution of vapor-and-gas flow among passages provided with adjustable throttle valves; one passage is connected with vapor-and-gas mixture inlet pipe lines. ^ EFFECT: enhanced efficiency; high compactness as compared with prototype; enhanced dynamic properties; no limitation in consumption of water being evaporated. ^ 1 dwg