A study of small-size thruster based on a bidirectional vortex combustor


Аuthors

Evdokimov O. A.1*, Piralishvili S. A.2**, Guryanov A. I.1, Veretennikov S. V.1

1. Rybinsk State Aviation Technical University named after P.A. Soloviev, RSATU, 53, Pushkin St., Rybinsk, Yaroslavl region, 152934, Russia
2. ,

*e-mail: yevdokimov_oleg@mail.ru
**e-mail: piral@list.ru

Abstract

The paper reports on the results of numerical simulation of a bidirectional vortex small-size thruster. The geometry of the thruster is based on the experience of studies of bidirectional vortex combustors of different applications. Additionally, Vitoshinsky’s outlet nozzle profile is used to provide supersonic flow at the combustor outlet. To calculate flow structure inside the device, the RANS approach is applied, 3 different models – k-ε, k-ω SST, and RSM BSL are used to simulate turbulence. Combustion is simulated by Eddy Dissipation Model with a 2-step reaction of oxidation and the reaction of thermal NO formation. Numerical simulation of the combustion process allowed us to obtain the values of the combustion efficiency and the thrust at the combustor outlet equal to 96% and 61.8 N, respectively. These values indicate higher operation efficiency in comparison with analogs. At the same time, combustor walls temperature is increased that requires the use of additional resources for cooling such as the latent heat of propellant evaporation. The value of the massflow averaged Mach number at the combustor outlet is equal to 2.24. The maximum unevenness of the Mach number distribution over the outlet cross-section is 29.0%. An additional geometrical improvement was based and variation of the inner diameter of the outlet nozzle. Its relative value obtained as a division by the combustion chamber inner diameter was changed from 0.5 to 0.7. The results show that the value 0.5 is optimal in terms of higher combustion efficiency and thrust as well as providing enhancement of vortical motion.

References

  1. Gupta A.K., Lilley D.G., Syred N. Swirl Flows. Abacus Press, 1984. 475 p.

  2. Biryuk V.V., Veretennikov S.V., Guryanov A.I., Piralishvili Sh.A. Vikhrevoj Effekt. Tekhnicheskie Prilozheniya. Ch. 2 [Vortex effect. Technical application. P. 2]. Mоscow: Nauchtechlitizdat, 2014. 288 p. In Russ.

  3. Syred N., Beér J.M. Combustion in swirling flows: A review. Combustion and Flame, 1974, vol. 23, pp. 142–201. DOI: 10.1016/0010-2180(74)90057-1

  4. Najim S.E., Styles A.C., Syred N. Flame movement mechanisms and characteristics of gas fired cyclone combustors. Symposium (International) on Combustion, 1981, vol. 18, pp. 1949–1957. DOI: 10.1016/S0082-0784(81)80201-9

  5. Dawson B. Feasibility Study on Vortex Combustion. Report RMD 1165-Q5, Contract DA-30-069-ORD-2772, 1960.

  6. Chiaverini M., Malecki M., Sauer J., Knuth W., Majdalani J. Vortex thrust chamber testing and analysis for O2-H2 propulsion applications. 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, American Institute of Aeronautics and Astronautics, Huntsville, Alabama. 2003. DOI: 10.2514/6.2003-4473

  7. Munson S., Sauer J., Rocholl J., Chiaverini M. Development of a low-cost vortex-cooled thrust chamber using hybrid fabrication techniques. 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, American Institute of Aeronautics and Astronautics, San Diego, California, 2011. DOI: 10.2514/6.2011-5835

  8. Majdalani J., Chiaverini M.J. Characterization of GO2-GH2 simulations of a miniature vortex combustion coldwall chamber. Journal of Propulsion and Powe, 2017, vol. 33, pp. 387–397. DOI: 10.2514/1.B36277

  9. Yu N., Zhao B., Li G., Wang J. Experimental and simulation study of a Gaseous oxygen/Gaseous hydrogen vortex cooling thrust chamber. Acta Astronautica, 2016, vol. 118, pp. 11–20. DOI: 10.1016/j.actaastro.2015.09.017

  10. Sun D., Liu S. Experimental research on bidirectional vortices in cold wall rocket thruster. Aerospace Science and Technology, 2012, vol. 18, pp. 56–62. DOI: 10.1016/j.ast.2011.04.002

  11. Rajesh T.N., Jothi T.J.S., Jayachandran T. Performance analysis of a vortex chamber under non-reacting and reacting conditions. Sādhanā, 2020, vol. 45, pp. 43. DOI: 10.1007/s12046-020-1271-1

  12. Besharat Shafiei S., Ghafourian A., Saidi M.H., Mozafari A.A. Theoretical and experimental modeling of vortex engine in ramjet application. 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, American Institute of Aeronautics and Astronautics, Denver, Colorado, 2009. DOI: 10.2514/6.2009-5433

  13. Augousti A.T., Baker A., Marlow J.-J. Design and test firing of a dual bidirectional double vortex bipropellant rocket engine. J. Phys.: Conf. Ser., 2018, vol. 1065, p. 262002. DOI: 10.1088/1742-6596/1065/26/262002

  14. Guryanov A.I., Piralishvili Sh.A., Guryanova M.M., Evdokimov O.A., Veretennikov S.V. Counter-current hydrogeneoxygen vortex combustion chamber. Thermal physics of processing. Journal of the Energy Institute, 2020, vol. 93, pp. 634–641. DOI: 10.1016/j.joei.2019.06.002

  15. Evdokimov O.A., Guryanov A.I., Mikhailov A.S., Veretennikov S.V. A numerical simulation of burning of pulverized peat fuel in a bidirectional vortex combustor. Thermal Science and Engineering Progress, 2020, vol. 17, p. 100510. DOI: 10.1016/j.tsep.2020.100510

  16. Evdokimov O.A., Guryanov A.I., Mikhailov A.S., Veretennikov S.V., Stepanov E.G. Experimental investigation of burning of pulverized peat in a bidirectional vortex combustor. Thermal Science and Engineering Progress, 2020, vol. 18, P. 100565. DOI: 10.1016/j.tsep.2020.100565

  17. Badernikov A.V., Piralishvily S.A., Guryanov A.I. Results of numerical modeling of combustion processes in a vortex chamber. MATEC Web Conf., 2018, vol 209, p. 00023. DOI: 10.1051/matecconf/201820900023

  18. Badernikov A.V. Modifitsirovannyj metod rascheta goreniya v vikhrevykh protivotochnykh gorelochnykh ustrojstvakh. Diss. cand. tekhn. nauk. [Modified method for calculating combustion in bidirectional vortex combustors. Cand. eng. sci. diss]. 2019. 168 p.

  19. ANSYS CFX-Solver Theory Guide, ANSYS Inc. 2011.

  20. Syred N. A review of oscillation mechanisms and the role of the precessing vortex core (PVC) in swirl combustion systems. Progress in Energy and Combustion Science, 2006, vol. 32, pp. 93–161. DOI: 10.1016/j.pecs.2005.10.002

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