Engeneering of a cooling system for a reusable liquid-propellant rocket engine opereting on tripropellant fuel
Автор: Belyakov V. A., Vasilevsky D. O., Ermashkevich A. A., Kolomentsev A. I., Farizanov I. R.
Журнал: Siberian Aerospace Journal @vestnik-sibsau-en
Рубрика: Aviation and spacecraft engineering
Статья в выпуске: 2 vol.22, 2021 года.
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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.
LPRE on three-component fuel, thermal protection of an engine body, mathematical model of LPRE, heat and mass transfer of three-component combustion products.
Короткий адрес: https://sciup.org/148321807
IDR: 148321807 | DOI: 10.31772/2712-8970-2021-22-2-316-327
Список литературы Engeneering of a cooling system for a reusable liquid-propellant rocket engine opereting on tripropellant fuel
- Gakhun G. G., Alekseev I. G., Berezanskaya E. L. et al. Atlas konstruktsiy ZHRD [ATLAS of LPRE design, Part 1]. Moscow, MAI Publ., 1969, 286 p.
- Berezhinsky R. A., Sokolov S. A., Gudkova S. R. et al. Modelirovanie rabochih processov i konstruktsiya elementov kamerj ZHRD [Modeling of working processes and construction of elements of the LPRE chamber]. Voronezh, VGTU Publ., 2002, 169 p.
- Dobrovolsky M. V. Zhidkostnye raketnye dvigateli, Osnovy proektirovaniya [Liquid rocket engines, Fundamentals of design]. Moscow, Bauman Moscow state technical University Publ., 2016, 461 p.
- Shevchenko Yu. N., Kishkin A. A., Tanasiyenko F. V. et al. [Calculation of complex heat transfer in the liquid circuit of the spacecraft thermal control system based on real topology and thermal properties]. Siberian journal of science and technology. 2019, Vol. 20, No. 3, P. 375–382 (In Russ.). Doi: 10.31772 / 2587-6066-2019-20-3-375-382.
- Seryakov A.V. [Investigation of flows in the steam channel of short linear heat pipes]. Siberian journal of science and technology. 2017, Vol. 18, No. 3, P. 592–603. (In Russ.)
- Ponomarenko A. RPA: Tool for Rocket Propulsion Analysis. Available at: http://propulsion-analysis.com (accessed: 10.10.2020).
- Ievlev V. M. Turbulenthoye dvizheniye vysokotemperaturnykh sploshnykh sred [Turbulent motion of high-temperature continuous media]. Moscow, Nauka Publ., 1975, 255 p.
- Ponomarenko A. RPA: Tool for Rocket Propulsion Analysis, Thermal Analysis of Thrust Chambers.Available at: http://propulsion‑analysis.com/downloads/2/docs/RPA_ThermalAnalysis. pdf (accessed: 10.10.2020).
- Kudryavtsev V. M., Vasiliev A. P. et al. Osnovy teorii i rascheta zhidkostyh raketnyh dvigatelej [Fundamentals of the theory and calculation of liquid rocket engines]. Moscow, Higher school Publ., 1975, 656 p.
- Salakhutdinov G. M. Razvitie metodov teplozashity v zhidkosntnyh rakentyh dvigatelyah [Development of methods of thermal protection in liquid rocket engines]. Moscow, Nauka Publ., 1984, 256 p.
- Elliot D. G., Bartz, D. R., Silver S. Culculation of turbulent boundary-layer grouth and heat transfer in axi-symmetric nozzles. Tech. Rep. JPL. 1963, No. 32-387, 45 p.
- Dewey M. S. A comparison of experimental heat-transfer coefficients in a nozzle with analytical predictions from Bartz’s methods for various combustion chamber pressures in a solid propellant rocket motor. A thesis submitted to the Graduate Faculty of North Carolina State University Raleigh in partial fulfillment of the requirements for the Degree DEPARTMENT OF Master of Science: Department of mechanical and aerospace engineering. Releigh, 1970. 99 p.
- Hobler T. Teploperedacha i teploombenniki [Heat transfer and heat exchangers]. Leningrad, Goskhimizdat Publ., 1961, 821 p.
- Shevchenko Yu. N., Kishkin A. A., Tanasiyenko F. V. et al. [Determining thermal resistances in the model of the liquid circuit of the spacecraft thermal control system]. Siberian journal of science and technology. 2019, Vol. 20, No. 3, P. 366–374. (In Russ.)Doi: 10.31772 / 2587-6066-2019-20-3-366-374.
- Zimin A. Yu. Razrabotka stenda ognevyh ispytanij zhidkostnogo raketnogo dvigatelya na toplive zhidkij kislorod I zhidkiy vodorod tyagoj 100 kN . Diplom specialista.[Development of a stand for fire tests of a liquid rocket engine powered by liquid oxygen and liquid hydrogen with 100kn thrust. Diploma of a specialist]. Moscow, MAI Publ., 2017, 106 p.
- Lebedinsky E. V. et al. Rabochie processy v zhidkostnom raketnom dvigatele i ih modelirovanie [Working processes in a liquid rocket engine and their modeling]. Moscow, Mashinostroenie Publ., 2008, 512 p.
