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Mathematical Modeling of Electrization of Particles of Acondensing Phase in High-Temperature Flow of Combustion Products of Rocket Engine

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Abstract

A mathematical model has been developed and the electrophysical characteristics of combustion products in the flow path of a liquid-propellant rocket engine have been calculated taking into account the electrification of combustion products and solid metal particles resulting from the combustion of engine structural elements. Numerical methods have been used to calculate the trajectories, speed, and temperature of the metal particles and the total electric charge acquired by the particles as a result of interaction with electrons present in the combustion products. The influence of particle size on the electric charge is analyzed. The results can be used to develop an early diagnosis system for the ignition of heat-stressed structural elements of power plants.

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Authors and Affiliations

  1. Bauman Moscow State Technical University, 105005, Moscow, Russia

    A. V. Rudinsky & D. A. Yagodnikov

  2. Baranov Central Institute of Aviation Motors, Moscow, Russia

    A. V. Rudinsky

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  1. A. V. Rudinsky
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  2. D. A. Yagodnikov
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Correspondence to A. V. Rudinsky.

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Rudinsky, A.V., Yagodnikov, D.A. Mathematical Modeling of Electrization of Particles of Acondensing Phase in High-Temperature Flow of Combustion Products of Rocket Engine. High Temp 57, 753–760 (2019). https://doi.org/10.1134/S0018151X19050134

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  • DOI: https://doi.org/10.1134/S0018151X19050134

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