Научная электронная библиотека ULRICH'S Periodicals Directory

Сибирский государственный университет
науки и технологий имени академика М.Ф. Решетнева

Сибирский аэрокосмический журнал
ISSN 2712-8970 (Print) ISSN 2782-5760 (on-line)

Сведения об образовательной организации

UDK УДК 629.7.036.54 Doi: 10.31772/2712-8970-2021-22-2-316-327
Design of the cooling system of a reasuble liquid rocket engine with three-component fuel
Belyakov V. A., Vasilevsky D. O., Ermashkevich A. A., Kolomentsev A. I., Farizanov I. R.
Federal State Enterprise “Research and Testing Center of the Rocket and Space Industry”, 9, Babushkina St., Peresvet, 141320, Russian Federation; Moscow Aviation Institute (National research university), 4, Volokolamskoe Higway, A-80, GSP-3, Moscow, 125993, Russian Federation; AO “Ural Civil Aviation Plant”, 1, p. 1, Marshal Zhukov Av., Moscow, 123308, Russian Federation
Currently, in the field of engine building, development of three-component propulsion systems (PS) is a very promising task. Liquid-propellant rocket engines (LPRE) operating at the initial stage of launching a launch vehicle (LV) on liquid oxygen + kerosene fuel and at high-altitude launch sites using cryogenic fuel (liquid oxygen + liquid hydrogen) are in particular interest. LPRE that use three-component fuel have a high pressure level in a combustion chamber (CC) (up to 30 MPa) and temperatures (up to 4000 K). In this regard, arise questions related to reliable cooling of such engines, as well as ensuring minimal hydraulic fluid losses in a cooling passage in order to further use re-frigerant as a working fluid for driving the turbine of a booster turbo pump unit (BTP). The object of research is a two-mode single-chamber three-component liquid-propellant rocket engine, made in a closed circuit with generator gas afterburning. Oxidizing agent is liquid oxygen, fuel is RG-1 kerosene and liquid hydrogen. Cooling of the chamber is combined: it consists of regenerative and internal. Regenerative cooling passage is formed by longitudinal integral-machined fins. Hipercritical hydrogen is used as an engine coolant. Internal cooling includes a tantalum coating applied to a fire wall of the chamber in a critical section. The article examines the problems of organizing cooling system (CS) and implementation of effective heat removal from a firing wall of a three-component rocket engine. Basing on existing liquid-propellant engine cooling systems, optimal circuit solutions and measures to remove thermal load in the most stressed places are proposed. A mathematical model has been developed for calculating a CS of a three-component LPRE. The results of the design calculation of cooling using several calculation methods are presented.
Keywords: LPRE on three-component fuel, thermal protection of an engine body, mathematical model of LPRE, heat and mass transfer of three-component combustion products.
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Belyakov Vladislav Albertovich – post-graduate student, engineer of the Department 202 “Rocket Engines”, Moscow aviation Institute (National Research University). E-mail: titflavii@rambler.ru.

Vasilevsky Dmitry Olegovich – post-graduate student, engineer of the Department 202 “Rocket Engines”, Moscow aviation Institute (National Research University); engineer of the 1st category, Federal state enterprise “Research and testing center of the rocket and space industry”. E-mail: zudwa_dwesti_dwa@rambler.ru.

Ermashkevich Alexey Aleksadrovich – post-graduate student of the Department 202 “Rocket Engines”, Moscow aviation Institute (National Research University). E-mail: alex.ermashkevich@yandex.ru.

Kolomentsev Alexander Ivanovich – Cand. Sc., Professor, Professor of Department 202 “Rocket Engines”; Moscow aviation Institute (National Research University). E-mail: a.i.kolomentsev@yandex.ru.

Farizanov Ilnur Ravinatovich – design engineer 1 categories, JSC “Ural works of civil aviation”. E-mail: chelsea.physic@gmail.com.


  Design of the cooling system of a reasuble liquid rocket engine with three-component fuel