MODELING OF PROCESSES IN THE COMBUSTION CHAMBER OF A JET ENGINE
Heading:
| Katrenko, MО, Strelnikov, GO, Pryadko, NS, Vasilyv, SS |
| Space Sci. & Technol. 2026, 32 ;(2):11-21 |
| https://doi.org/10.15407/knit2026.02.011 |
| Publication Language: Українська |
Abstract: An important design component of the heat engine process used in an aircraft is the selection and study of the main energy-
fuel characteristics, namely the combustion product temperature, the thermal eff ect of the chemical reaction, the components of the combustion products, etc. Th e search for a universal simulation approach to fuel combustion processes that would provide comprehensive, valid information to achieve the jet engine design parameters is relevant. Th e method’s universality should consist of the ability to calculate the fuel combustion characteristics in any aggregation state, determine the combustion product composition and obtain data to determine the main engine parameters. Th e use of modern mathematical modeling methods, for example, the ANSYS package, is characterized by complexity, a need for suffi cient hardware resources, and a lot of time. Th ere is an alternative method for modeling thermogasodynamic processes of thermal energy supply of jet engines. Comparison of modeling methods requires an analytical assessment of results against the criteria of minimum time and resources, with the highest possible accuracy. Th is task determines the relevance of this work. Th e existing theoretical foundations and methods for designing jet engines for various purposes, along with the world experience used in their creation, show and characterize many features in modeling thermogasodynamic processes inherent to engines with heat supply at constant pressure. Th e main results of using the method for modeling combustion processes in chemically reacting, multicomponent, heterogeneous thermodynamic systems, based on the principle of maximum entropy, are presented for calculating thermogasodynamic parameters of various fuels used in jet engines. Comparative results of mathematical modeling of the fuel combustion process in jet engines, along with trends in their change, are presented. Th e correctness of the methodological approaches to the conducted study is verifi ed by the results of other authors. Th e need for clarifi cation, addition, and ordering of the selected method of mathematical modeling is shown. Th e novelty of the study lies in the collection of new and comparative data on the characteristics of fuel combustion processes in thermal jet engines. Th e results obtained allow us to establish trends in the characteristics of the fuel combustion process. Th e practical signifi cance of the presented results lies in the possibility of using the obtained data to calculate the main parameters in jet engine design. |
| Keywords: characteristics, combustion chamber, fuel components, jet engine, model, system, thermodynamic parameters |
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design bureau of the State Enterprise «Design Bureau «Yuzhnoye». /Under the scientifi c editorship of Academician of
the NAS of Ukraine S.N. Konyukhov, Candidate of Technical Sciences V. N. Shnyakin. Dnepropetrovsk: State Enterprise
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index. Chemistry, Physical organic. ISBN 0–06–044082–1. https://www.academia.edu/51718697/Mechanism_and_theory_
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Ed. L. V. Pron, G. A. Gorbenko, M. A. Katrenko. Dnepropetrovsk: ART-PRESS, 560 p., ill. ISBN 978-966-348-437-2 [in
Russian].
McBride B. J., Gordon S. (1996). Computer Program for Calculation of Complex Chemical Equilibrium Compositions and
Applications. II. Users Manual and Program Description. NASA Reference Publication, 1311, 167 p.
McBride B. J., Zehe M. J., Gordon S. (2002). NASA Glenn Coeffi cients for Calculating Th ermodynamic Properties of Individual
Species. NASA/TP–2002-211556. Glenn Research Center, 287 p.
Ponomarenko A. (2010). RPA: Tool for Liquid Propellant Rocket Engine Analysis. C++ Implementation. URL: http://soft ware.
lpre.de
Shevtsova E. et al. (2009). Autonomous and Backup Gas Supply Systems. Reference Guide. St. Petersburg: Published by “Drops
of Rain”, 264 p. [in Russian].
Shriver D. F., Atkins P. W. (1999). Inorganic Chemistry. Th ird edition. Oxford: University Press. ISBN 0-19-850331-8.
Siebenhaar A., Bulman M. J., Bonnar D. K. (1998). Th e Strutjet rocket based combined cycle engine. NASA Technology Report.
Sinyarev G. B., Vatolin N. A., Trusov B. G., Moiseev G. K. (1982). Application of computers for thermodynamic calculations of
metallurgical processes. M.: Nauka, 263 р. [in Russian].
Smith S. D. (1963). Engineering design handbook. Military pyrotechnics series. Part three. Properties of materials used in
pyrotechnic compositions. Headquarters united states army materiel command Washington, D. C. 20315. AM CP 706–187,
337.
Staskevich N. L., Severinets G. N., Vigdorchik D. Ya. (1990). Handbook of gas supply and gas use. L.: Nedra, 762 p. [in Russian].
Turner M. J. L. (2006). Rocket and Spacecraft Propulsion: Principles, Practice and New Developments. 3rd ed. Springer-Praxis
Books, 314.
Wark K. Th ermodynamics, 4th ed. New York: McGraw-Hill, 1983. 896. https://www.scribd.com/document/407123837/
Kenneth-Wark-Th ermodynamics.
Zeleznik F. J., Gordon S. (1960). Technical Note D-473 An analytical investigation of three general methods of calculating
chemical-equilibrium compositions. Lewis Research Center, № 62-71047, 35.
Zuev V. S., Makaron V. S. (1971). Th eory of ramjet and rocket-ramjet engines. M.: Mechanical Engineering, 368 p. [in Russian].