Cavitating Venturi as a Mass Flow Controller in a Deep Throttling Liquid Rocket Engine

نویسندگان

چکیده

Abstract The most common solutions for rocket engines are the single operation point (thrust level) units. Oxidiser and fuel mass flow rates oxidiser-to-fuel rate ratio (OFR) some of determinants thrust level. Based on these, planetary ascent descent; space rendezvous; orbital manoeuvring, including orientation stabilisation in space; hovering, hazard avoidance during landing; ballistic missile trajectory control propulsion systems could use throttleable liquid engines. Several engine throttling methods, such as supply pressure variation variable injector area, can be applied. Among others, a cavitating venturi propellant regulatory valve is one promising method. This type provide steady flow, despite downstream disturbance (i.e. from combustion chamber), which sustains stable kept. article presents sizing method, design prototype test results that has potential utilisation deep engine. Mass stability repeatability presented operating points 10%–110% nominal range. Valve optimisation, based CFD, to sustain cavitation higher downstream-to-upstream shown.

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ژورنال

عنوان ژورنال: Prace Instytutu Lotnictwa

سال: 2023

ISSN: ['2545-2835', '2300-5408', '0509-6669']

DOI: https://doi.org/10.2478/tar-2023-0018