Email this article Design of the cooling system of a reasuble liquid rocket engine with three-component fuel
- Authors: Belyakov V.A.1, Vasilevsky D.O.2,1, Ermashkevich A.A.1, Kolomentsev A.I.1, Farizanov I.R.3
-
Affiliations:
- Moscow Aviation Institute (National research university)
- Federal State Enterprise “Research and Testing Center of the Rocket and Space Industry”
- AO “Ural Civil Aviation Plant”
- Issue: Vol 22, No 2 (2021)
- Pages: 316-327
- Section: Section 2. Aviation and Space Technology
- URL: https://journals.eco-vector.com/2712-8970/article/view/562882
- DOI: https://doi.org/10.31772/2712-8970-2021-22-2-316-327
- ID: 562882
Cite item
Abstract
Currently, in the field of engine building, the 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 a vapor of 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 the 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 the cooling path in order to further use the refrigerant 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 – liquid oxygen, fuel – RG-1 kerosene and liquid hydrogen. Cooling of the chamber – combined: it consists of regenerative and internal. The regenerative cooling path is formed by longitudinal milled fins. Supercritical hydrogen is used as the engine coolant. Internal cooling includes a tantalum coating applied to the fire wall of the chamber in the critical section.
The article examines the problems of organizing the cooling system (CO) and the implementation of effective heat removal from the firing wall of a three-component rocket engine. Basing on the existing liquid-propellant engine cooling systems, optimal circuit solutions and measures are proposed in the RESEARCH to remove the thermal load in the most stressed places.
A mathematical model has been developed for calculating the CO of a three-component LPRE. The results of the design calculation of cooling using several calculation methods are presented.
About the authors
Vladislav A. Belyakov
Moscow Aviation Institute (National research university)
Email: titflavii@rambler.ru
post-graduate student, engineer of the Department 202 “Rocket Engines”
Russian Federation, 4, Volokolamskoe Higway, A-80, GSP-3, Moscow, 125993Dmitry O. Vasilevsky
Federal State Enterprise “Research and Testing Center of the Rocket and Space Industry”; Moscow Aviation Institute (National research university)
Author for correspondence.
Email: zudwa_dwesti_dwa@rambler.ru
post-graduate student, engineer of the Department 202 “Rocket Engines”, engineer of the 1st category
Russian Federation, 9, Babushkina St., Peresvet, 141320; 4, Volokolamskoe Higway, A-80, GSP-3, Moscow, 125993Alexey A. Ermashkevich
Moscow Aviation Institute (National research university)
Email: alex.ermashkevich@yandex.ru
post-graduate student of the Department 202 “Rocket Engines”
Russian Federation, 4, Volokolamskoe Higway, A-80, GSP-3, Moscow, 125993Alexander I. Kolomentsev
Moscow Aviation Institute (National research university)
Email: a.i.kolomentsev@yandex.ru
Cand. Sc., Professor, Professor of Department 202 “Rocket Engines”
Russian Federation, 4, Volokolamskoe Higway, A-80, GSP-3, Moscow, 125993Ilnur R. Farizanov
AO “Ural Civil Aviation Plant”
Email: chelsea.physic@gmail.com
design engineer 1 categories
Russian Federation, 1/1, Marshal Zhukov Av., Moscow, 123308References
- 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.
Supplementary files
