Computational study of the system efficiency of supplying components in the model low-thrust rocket engine on oxygen-methane
Authors: Kovalev K.E., Fedotova K.V., Vorozheeva O.A.
Published in issue: #10(130)/2022
DOI: 10.18698/2308-6033-2022-10-2217
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts
The paper considers a model low-thrust rocket engine using the environmentally friendly gaseous oxygen–methane components as a scientific and technical lead obtained by the authors in the course of preliminary experimental studies. The engine design makes it possible to investigate the influence of the mixing unit configuration, namely position of the supply holes and presence or absence of the components swirling on the mixing process efficiency. Numerical simulation was carried out in a three-dimensional stationary formulation of “cold” mixing of gaseous oxygen and methane and was based on the Favre-averaged Navier — Stokes equations solution closed by the k–ω-SST turbulence model and the ideal gas state equation. Calculation results are provided for various configurations of the mixing unit. It is shown that the most efficient method for the considered model low-thrust rocket engine is the method of supplying gaseous components with swirling in a single direction.
References
[1] Andreev E.A., Novikov A.V., Shatsky O.E. Raschetnoe i eksperimentalnoe issledovanie nadezhnosti zapuska i vykhoda na rezhim raketnogo dvigatelya maloy tyagi na gazoobraznykh komponentakh kislorod+metan s elektroiskrovym zazhiganiem [Calculation and experimental study of reliability of starting and reaching the mode of a low-thrust rocket engine on gaseous oxygen + methane components with the electric spark ignition]. Inzhenerny zhurnal: nauka i innovatsii — Engineering Journal: Science and Innovation, 2017, iss. 4 (64). https://doi.org/10.18698/2308-6033-2017-4-1606
[2] Novikov A.V., Yagodnikov D.A., Burkaltsev V.A., Lapitsky V.I. Matemati-cheskaya model i raschet kharakteristik rabochego protsessa v kamere sgoraniya ZhRD maloy tyagi na komponentakh topliva metan-kislorod [Mathematical model and calculation of the working process characteristics in the combustion chamber of a low-thrust LRE on the methane-oxygen fuel components]. Vestnik MGTU im. N.E. Baumana. Ser. Mashinostroenie. Spets. vyp. “Teoriya i praktika sovremennogo raketnogo dvigatelestroyeniya” — Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, special issue “Theory and practice of modern rocket propulsion engineering”, pp. 8–17.
[3] Vaulin S.D., Salich V.L. Metodika proektirovaniya vysokoeffektivnykh raketnykh dvigateley maloy tyagi na osnove chislennogo modelirovaniya vnutrikamernykh protsessov [Technique for designing high-efficiency low-thrust rocket engines based on numerical simulation of the inner chamber processes]. Vestnik YuUrGY. Ser. Mashinostroenie — Herald of the South Ural State University, Series Mechanical Engineering, 2012, no. 12, pp. 43–50.
[4] Salich V.L. Matematicheskoe modelirovanie rabochego protsessa kamery raketnogo dvigatelya maloy tyagi na kislirodno-vodorodnom toplive [Mathematical simulation of the working process in the chamber of a low-thrust rocket engine on oxygen-hydrogen fuel]. CAD/CAM/CAE Observer. Mashinostroyenie i smezhnye otrasli — Mechanical engineering and related fields, 2015, vol. 7, no. 99, pp. 31–36.
[5] Kochanov A.V., Klimenko A.G. Issledovanie problem sozdaniya raketnykh dvigateley maloy tyagi na ekologicheski chistykh gazoobraznykh toplivakh [Investigation of the problems in creating low-thrust rocket engines on environmentally friendly gaseous fuels]. Vestnik MGTU im. N.E. Baumana. Ser. Mashinostroenie — Herald of the Bauman Moscow State Technical University. Series Mechanical Engineering, 2006, no 3, pp. 64 73.
[6] Kutuev R.Kh., Lebedev I.N., Salich V.L. Razrabotka perspektivnykh RDMT na ekologicheski chistykh toplivnykh kompozitsiyakh [Development of promising LTRE on environmentally friendly fuel compositions]. Vestnik Samarskogo gosudarstvennogo aerokosmicheskogo universiteta — Herald of the Samara State Aerospace University, 2009, no. 3, pp. 101–109.
[7] Chudina Yu.S., Borovik I.N., Kozlov A.A. Konstruktsiya i ognevye ispytaniya kislorodno-metanovogo dvigatelya tyagoy 200 H [Design and firing tests of the oxygen-methane engine with a thrust of 200 N]. Vestnik PNIPU. Aerokosmicheskaya tekhnika — PNRPU Aerospace Engineering Bulletin, 2017, no. 51, pp. 26–38.
[8] Vorozheeva O.A., Yagodnikov D.A. Raschetnoe issledovanie teplovogo sostoyaniya raketnogo dvigatelya maloy tyagi na gazoobraznykh komponentakh topliva kislorod-metan, rabotayuschego v impulsnom rezhime [Computational study of the thermal state of a low-thrust rocket engine on gaseous components of oxygen-methane fuel operating in the pulsed mode]. Nauka i obrazovanie. MGTU im. N.E. Baumana. Elektr. Zhurnal — Science & Education, Bauman Moscow State Technical University, Electronic Journal, 2014, no. 11, pp. 330–344.
[9] Vorozheeva O.A., Yagodnikov D.A. Chislennoe issledovanie vliyaniya rezhimnykh parametrov na teplovoe sostoyanie konstruktsii raketnogo dvigatelya maloy tyagi na toplive kislorod-metan pri rabote v impulsnom rezhime [Numerical study of the influence of regime parameters on the thermal state of the low-thrust rocket engine design on the oxygen-methane fuel when operating in the pulsed mode]. Inzhenerny zhurnal: nauka i innovatsii — Engineering Journal: Science and Innovation, 2017, iss. 1. https://doi.org/10.18698/2308-6033-2017-1-1570
[10] Garbaruk A.V. Sovremennye podkhody k modelirovaniyu turbulentnosti [Modern approaches to turbulence simulation]. Saint Petersburg, Polytechnic University Publ., 2016, 234 p.