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156 results on '"Shamshin, I."'

11. A Detonation Afterburner

Author

Frolov, S. M., Ivanov, V. S., Shamshin, I. O., Aksenov, V. S., Vovk, M. Yu., Mokrynskij, I. V., Bruskov, V. A., Igonkin, D. V., Moskvitin, S. N., Illarionov, A. A., and Marchukov, E. Yu.

Published
2020
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12. Pulse-Detonation Hydrojet

Author

Frolov, S. M., Avdeev, K. A., Aksenov, V. S., Frolov, F. S., Sadykov, I. A., Shamshin, I. O., Tukhvatullina, R. R., Anisimov, K. V., editor, Dub, A. V., editor, Kolpakov, S. K., editor, Lisitsa, A. V., editor, Petrov, A. N., editor, Polukarov, V. P., editor, Popel, O. S., editor, and Vinokurov, V. A., editor

Published
2018
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26. Pulse-Detonation Hydrojet

Author

Frolov, S. M., primary, Avdeev, K. A., additional, Aksenov, V. S., additional, Frolov, F. S., additional, Sadykov, I. A., additional, Shamshin, I. O., additional, and Tukhvatullina, R. R., additional

Published
2017
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27. Features of Ignition of Mixtures of Hydrogen With Hydrocarbons (C2, C3, C5) Over Rhodium and Palladium at Pressures of 1–2 atm.

Author

Troshin, K. Ya., Rubtsov, N. M., Tsvetkov, G. I., Chernysh, V. I., and Shamshin, I. O.

Abstract

It is found that the determining factor for the catalytic ignition of mixtures of hydrogen with ethane and ethylene is not only the material of the catalyst but also the chemical nature of the C2 hydrocarbon in the mixture with H2. It is shown that the limits of the catalytic ignition of the synthesis gas over metallic rhodium (Rh) are qualitatively different from the dependences for a hydrogen–hydrocarbon mixed fuel. The dependence of the lower limit of catalytic ignition on temperature has a distinct maximum, which indicates a more complex mechanism of the catalytic process than in the case of hydrogen–methane mixtures; the Arrhenius dependence of ln [H2]lim on 1/T does not hold. Therefore, the interpretation of the upper and lower limits of catalytic ignition (ULCI, LLCI) used in the literature, taking into account catalyst poisoning by CO molecules, needs to be clarified. The relatively long delay periods of the catalytic ignition of hydrogen–n-pentane mixtures (tens of seconds) and the absence of dependence of the delays on the initial temperature allow us to conclude that the catalytic ignition of hydrogen–propane/n-pentane mixtures is determined by the rate of transfer of hydrocarbon molecules to the surface of the catalytic wire. Thus, in the oxidation of hydrogen–hydrocarbon mixtures for "short" hydrocarbons, the main factor determining the catalytic ignition is the oxidation reaction of hydrogen on the catalytic surface. With an increase in the number of carbon atoms in the hydrocarbon, the factors associated with the chemical structure, i.e., the reactivity of the hydrocarbon in catalytic oxidation, begin to play a significant role; and then the rate of oxidation is determined by the rate of transfer of the hydrocarbon molecules to (or within) the catalyst surface. [ABSTRACT FROM AUTHOR]

Published
2023
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40. Deflagration-to-detonation Transition in Stratified Oxygen – Liquid Fuel Film Systems.

Author

Frolov, S. M., Shamshin, I. O., and Aksenov, V. S.

Subjects
LIQUID films, FUEL systems, MACH number, SHOCK waves, LIQUID fuels, P-waves (Seismology)
Abstract

Deflagration-to-detonation transition (DDT) in gas (oxygen)–liquid n-heptane film and gas (oxygen)–liquid n-decane film systems is registered experimentally using a fused or exploding wire as a weak ignition source that generates a primary shock wave with a Mach number ranging from 1.02 to 1.6. In a straight smooth-walled channel of rectangular cross section 54 × 24 mm, 3 and 6 m long with one open end, the DDT is obtained at distances 900 to 4000 mm from the ignition source 3 to 1700 ms after ignition. The DDT is obtained for n-heptane and n-decane films 0.2 to 0.7 mm thick, which corresponds to the overall fuel-to-oxygen equivalence ratios of 15 to 40. The registered detonation velocities range from 1400 to 2000 m/s. In several experiments, a high-velocity quasi-stationary deflagration front propagating at an average velocity of 700–1100 m/s is recorded. The structure of this front includes the leading shock wave followed by the reaction zone separated from each other by a time delay of 90 to 190 μs. The results obtained are important for explosion safety and for better understanding of the operation process in the continuous-detonation and pulse-detonation combustors of advanced rocket and air-breathing engines with the supply of liquid fuel in the form of a wall film. [ABSTRACT FROM AUTHOR]

Published
2022
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