FIELD: rocket equipment.
SUBSTANCE: invention relates to rocket technology and can be used for experimental testing of liquid rocket propulsion systems, in particular, in order to imitate altitude conditions during their creation and modernization. Device is proposed for testing liquid-propellant rocket engines, which contains an exhaust diffuser consisting of a housing with a central body installed in it, including an input conical and output parts. Input conical part is made with the ability to partially move into the nozzle of the test engine. Ejector is installed inside the central body in the output part of it. Mixing chamber is located behind the central body in the diffuser housing.
EFFECT: technical result is that the present invention provides a continuous flow of combustion products in the nozzle and the absence of impact of shock waves on its wall during the entire operating time of the test engine.
4 cl, 1 dwg
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