Email this article 
Choosing the mixing pattern for oxygen-hydrogen low-thrust rocket engines
- Authors: Ryzhkov V.V.1, Morozov I.I.1
-
Affiliations:
- Samara National Research University
- Issue: Vol 17, No 3 (2018)
- Pages: 103-115
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/6333
- DOI: https://doi.org/10.18287/2541-7533-2018-17-3-103-115
- ID: 6333
Cite item
Full Text
Abstract
The article presents the results of comparison of computation data on the energy parameters of the working process of engines and the thermal condition of the structure obtained for low-thrust rocket engines fueled by gaseous oxygen-hydrogen, using various schemes of mixture formation. The analysis of the efficiency of the working process is carried out on the basis of the patterns of distribution of combustion products temperature in the cross sections of combustion chambers, temperature diagrams, their values in the area of the engine chamber wall and the specific thrust impulse. It is shown that the chosen tools fully characterize the efficiency of the working process implemented in various schemes of mixing in engines and make it possible to assess the quality of a particular scheme. It was found that for most of the parameters used and additional criteria for evaluating the efficiency of the mixture formation scheme for low-thrust rocket engines, the scheme implementing a rotational coaxial multistage flow of gaseous fuel components in the chamber is preferable.
About the authors
V. V. Ryzhkov
Samara National Research University
Author for correspondence.
Email: ke_src@ssau.ru
Candidate of Science (Engineering)
Head of the Research Center of Space Power
I. I. Morozov
Samara National Research University
Email: ke_src@ssau.ru
Junior Researcher, Research Center of Space Power
Russian FederationReferences
- Gupta A.K., Lilley L.G., Syred N. Swirl flows. Tunbridge Wells: Abacus Press, 1984. 475 p.
- GOST 21980-76. Gas centrifugal burners with tangential iniet basic indexes nomenklature and methods of computation. Moscow: Izdatel'stvo Standartov Publ., 1976. 22 p.
- Palatnik I.B., Temirbaev D.Zh. Zakonomernosti rasprostraneniya osesimmetrichnoy vozdushnoy strui v snosyashchem odnorodnom potoke. V knige: «Problemy teploenergetiki i prikladnoy teplofiziki». Iss. 4. Alma-Ata: Nauka Publ., 1967. P. 68-82. (In Russ.)
- Howard S.P. Characteristics of heat transfer and hydraulic resistance of heat exchange surfaces with beveled channels and surfaces made of glass mica ceramics. Transactions of the ASME. Series A. 1967. V. 89, no. 1. P. 85-101.
- Volchkov E.P. Pristennye gazovye zavesy [Near-wall gas film]. Novosibirsk: Nauka Publ., 1983. 239 p.
- Gradov V.N., Ryzhkov V.V. Raketnyy dvigatel' maloy tyagi (RDMT) s mnogokaskadnoy kameroy sgoraniya na gazoobraznykh vodorode i kislorode [Hydrogen-oxygen low-thrust rocket engine with a multistage combustion chamber]. Patent RF, no. 2615883, 2017. (Publ. 11.04.2017, bull. no. 11)
- Gradov V.N., Ryzhkov V.V. Raketnyy dvigatel' maloy tyagi na gazoobraznykh vodorode i kislorode so shchelevoy forsunkoy [Hydrogen-oxygen low-thrust rocket engine with a slit injector]. Patent RF, no. 2624419, 2017. (Publ. 03.07.2017, bull. no. 19)
- Gradov V.N., Gulyaev Yu.I., Ryzhkov V.V. Vodorodno-kislorodnyy raketnyy dvigatel' maloy tyagi [Hydrogen-oxygen low-thrust rocket engine]. Patent RF, no. 2623610, 2017. (Publ. 28.06.2017, bull. no. 19).
- Gradov V.N., Gulyaev Yu.I., Ryzhkov V.V. Raketnyy dvigatel' maloy tyagi na gazoobraznom vodorode i kislorode s forsunkami tipa struya v snosyashchem potoke [Hydrogen-oxygen low-thrust rocket engine with injectors of the jet type in the cross flow]. Patent RF, no. 2641785, 2018. (Publ. 22.01.2018, bull. no. 3)
- Gradov V.N., Ryzhkov V.V. Raketnyy dvigatel' maloy tyagi na gazoobraznom vodorode i kislorode s predvaritel'nym smesheniem komponentov v smesitel'noy golovke [Hydrogen-oxygen low-thrust rocket engine with premixing in the mixing head]. Patent RF, no. 2648040, 2018. (Publ. 21.03.2018, bull. no. 2)
Supplementary files
