Method of Calculating Carbon Ablation in the Jet of Liquid Rocket Engine Combustion Products

Nowadays carbon materials are widely used as ablating thermal protection for high-temperature structural elements in aerospace technology. Prediction of changes in the shape of the external surfaces of these elements, due to the burning of thermal protection, is closely related to the use of computational-theoretical methods describing the flow of various physicochemical and mechanical processes associated with the occurrence of the phenomenon under consideration. At the same time, it is crucial to test such methods on the results of experimental studies conducted under conditions which are implemented during the process of testing thermal protection in jets of aerodynamic units. The main elements of ablation of carbon materials include their erosion, i.e., mechanical ablation of mass, observed in high-pressure gas flows. In the process of experimental development, it is necessary to carry out research on large-scale models, which has led to widespread use of underexpanded jets of combustion products of liquid rocket engine combustion products for modeling the erosion process of thermal protection. The theoretical model of ablation of thermal protection in such jets requires taking into account the complex chemical composition of the gas mixture flowing into the model; physical and chemical interaction of this gas with thermal protection, which causes gasification of the latter; use of mathematical models describing the process of material erosion due to mechanical impact of high-pressure gas flow. The paper describes the development of the carbon material ablation calculating and theoretical methodology which could be used to determine the material erosion characteristics on the basis of solving a complex problem of circumfluence, heating, heat penetration and ablation of thermal protection

This work was supported by RFBR (grant no. 17-08-01467a)

References

[1] Polezhaev Yu.V., Yurevich F.B. Teplovaya zashchita [Thermal protection]. Moscow, Energiya Publ., 1976.

[2] Nikitin P.V. Teplovaya zashchita [Thermal protection]. Moscow, MAI Publ., 2006.

[3] Gorskiy V.V. Teoreticheskie osnovy rascheta ablyatsionnoy teplovoy zashchity [Theoretical foundations for calculating ablative thermal protection]. Moscow, Nauchnyy mir Publ., 2015.

[4] Anfimov N.A. Graphite combustion in air flow at high temperatures. Izv. AN SSSR. OTN. Mekhanika i mashinostroenie, 1964, no. 5, pp. 3--11 (in Russ.).

[5] Pchelkin Yu.D. Approximate method for calculating the mass loss of carbon materials in the high-temperature air. Kosmonavtika i raketostroenie, 2014, no. 2, pp. 19--24 (in Russ.).

[6] Mur Dzh.A, Zlotnik M. Carbon combustion in air flow. Raketnaya tekhnika, 1961, vol. 1, no. 10, pp. 35--45 (in Russ.).

[7] Rozner D.E., Allendorf G.D. Comparative analysis of oxidation of pyrolithic and isotropic graphite exposed to atomic and molecular oxygen at high temperatures. Raketnaya tekhnika i kosmonavtika, 1968, vol. 6, no. 4, pp. 91--96 (in Russ.).

[8] Polezhaev Yu.V. Sublimatsiya [Sublimation]. Fizicheskiy entsiklopedicheskiy slovar’. T. 5 [Physical encyclopedical dictionary. Vol. 5.]. Moscow, Sovetskaya entsiklopediya Publ., 1966, pp. 101.

[9] Vlasov V.I., Zalogin G.N. Numerical modeling of thermochemical destruction of carbon materials for thermal protection. Kosmonavtika i raketostroenie, 2015, no. 2, pp. 84--90 (in Russ.).

[10] Boyarintsev V.I., Zvyagin Yu.V. Study on destruction of carbon-graphite materials at high temperatures. AN SSSR. Teplofizika vysokikh temperatur, 1975, vol. 4, no. 5, pp. 1045 (in Russ.).

[11] Gorskiy V.V., Koval’skiy M.N., Olenicheva A.A. Determination of the kinetic oxidation constants of carbon materials on the basis of analysis of experiments on their ablation. Inzhenerno-fizicheskiy zhurnal, 2017, vol. 90, no. 1, pp. 133--141 (in Russ.). (Eng. version: J. Eng. Phys. Thermophy., 2017 vol. 90, no. 1, pp. 126--133). DOI: 10.1007/s10891-017-1547-4

[12] Gorskiy V.V., Gordeev A.N., Dmitrieva A.A., et al. Methods of solving inverse problems of mathematical physics to determine effective physical properties of carbon ablators for thermal protection. Inzhenernyy zhurnal: nauka i innovatsii [Engineering Journal: Science and Innovation], 2018, № 8 (in Russ.). DOI: 10.18698/2308-6033-2018-8-1789

[13] Gorskiy V.V., Dmitrieva A.A. Defining the kinetic constants of heterogeneous carbon oxidation under the sublimational condition of its ablation according to the results of the combined ablative experiments. Inzhenernyy zhurnal: nauka i innovatsii [Engineering Journal: Science and Innovation], 2017, № 12 (in Russ.). DOI: 10.18698/2308-6033-2017-12-1708

[14] Gorskiy V.V., Gordeev A.N., Dmitrieva A.A., et al. HF-Plasmatron IPG-4 in IPMech RAS as an instrument for determination of kinetics of heterogeneous chemical reactions on the surface of carbon material. Fiziko-khimicheskaya kinetika v gazovoy dinamike [Physical-Chemical Kinetics in Gas Dynamics], 2017, vol. 18, no. 2 (in Russ.).

[15] Maas Kh.G., Shrayder D.R. Particle entrainment at the ablation of artificial graphite. Raketnaya tekhnika i kosmonavtika, 1969, vol. 7, no. 11, pp. 155--160 (in Russ.).

[16] Gorsky V.V., Resh V.G. The study of carbon matherial’s aerothermochemical destruction in combustion products of liquid-propellant rocket engines. 29-th Cong. Of the Int. Council of the AeronauticalSciences. Available at: http://www.icas.org/ICAS_ARCHIVE/ICAS2014/data/papers/2014_0619_paper.pdf

[17] Gorskiy V.V., Koval’skiy M.G. Techniques for numerical simulation flow around an axisymmetric blunt body in an underexpanded jet of liquid rocket engine combustion products. Matematicheskoe modelirovanie i chislennye metody [Mathematical Modeling and Computational Methods], 2017, no. 2, pp. 65--80 (in Russ.).DOI: 10.18698/2309-3684-2017-2-6580

[18] Glushko V.P., ed. Termodinamicheskie svoystva individual’nykh veshchestv. T. II. Kn. 2 [Thermodynamic properties of individual substances. Vol. II. P. 2]. Moscow, Nauka Publ., 1979.