Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Mathematical simulation of coolant flow in the cooling channel of a liquid rocket engine combustion chamber featuring an extremely high degree of ribbing

Published: 18.11.2019

Authors: Aleksandrenkov V.P., Kovalev K.E., Yagodnikov D.A.

Published in issue: #11(95)/2019

DOI: 10.18698/2308-6033-2019-11-1933

Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts

The paper presents a computational analysis of coolant distribution in the cooling channel of a liquid rocket engine combustion chamber, performed in order to develop a set of practical guidelines towards increasing efficiency of a cooling system featuring an extremely high degree of ribbing. We created a three-dimensional mathematical model comprising a closed system of hydrodynamic equations as well as initial and boundary conditions for an element of the liquid rocket engine chamber we modelled, the chamber featuring longitudinal cooling channel arrangement manufactured via additive technology. We computed velocity and pressure fields in characteristic cooling channel regions for various levels of coolant mass flow rate, which confirmed the feasibility of the layout proposed in terms of uniform coolant distribution in the cooling channel of the liquid rocket engine modelled. We obtained the friction loss ξ as a function of coolant mass flow rate and particle size of the powder used in the additive technology to manufacture the combustion chamber wall and cooling channel.

[1] Aleksandrenkov V.P. Vestnik MGTU im. N.E. Baumana. Ser. Mashinostroenie — Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, 2013, no. 3, pp. 111–121.
[2] Aleksandrenkov V.P., Zubkov N.N., Yagodnikov D.A., Iryanov N.Ya. Inzhenernyy zhurnal: nauka i innovatsii — Engineering Journal: Science and Innovation, 2016, iss. 10.
[3] Artemov A.L., Dyadchenko V.Yu., Lukyashko A.V., et al. Kosmicheskaya tekhnika i tekhnologii — Space Engineering and Technology, 2017, no. 1, pp. 50–62.
[4] Solodovnikov A.V., Akinshin I.A., Golubyatnik V.V., Krivonogov A.V. Vestnik Samarskogo universiteta. Aerokosmicheskaya tekhnika, tekhnologii i mashinostroenie — VESTNIK of Samara University. Aerospace and Mechanical Engineering, 2017, vol. 16, no. 2, pp. 127–134. DOI: 10.18287/2541-7533-2017-16-2-127-134
[5] Kudryavtsev V.M., ed. Osnovy teorii i rascheta zhidkostnykh raketnykh dvigateley [Foundations of liquid rocket engine theory and parameter calculation]. Vol. 2. 4th ed. Moscow, Vysshaya Shkola Publ., 1993, 703 p.
[6] Anfimov M.V. Politekhnicheskiy molodezhnyy zhurnal — Politechnical student journal, 2017, no. 10. DOI: 10.18698/2541-8009-2017-10-188
[7] Grigoryants A.G., Kolchanov D.S., Drenin A.A., Denezhkin A.O. Izvestiya vysshikh uchebnykh zavedeniy. Mashinostroenie — Proceedings of Higher Educational Institutions. Маchine Building, 2019, no. 6, pp. 20–29. DOI: 10.18698/0536-1044-2019-6-20-2
[8] Fedorova D.K., Ivolga D.V., Alekseev V.P., Balyakin A.V. Izvestiya Samarskogo nauchnogo tsentra Rossiyskoy akademii nauk — Proceedings of the Samara Scientific Center of the Russian Academy of Sciences, 2016, no. 4 (6), pp. 1186–1190.
[9] Spalart P.R., Shur M. Aerospace Science and Technology, 1997, no. 1 (5), pp. 297–366.
[10] Redchits D.A. Nauchnye vedomosti BelGU — Belgorod State University Scientific Bulletin, 2009, no. 13 (68), pp. 118–146.