Experimental Study of the Working Process in Liquid Rocket Engines by an Electrophysical Diagnostic Method

Bobrov, A. N.; Рудинский, А. В.; Пушкин, Н. М.; Safonova, D. B.; Yagodnikov, D. A.

doi:10.1134/s1063784220080034

Cited by 3 publications

(2 citation statements)

References 8 publications

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“…The spatial flame distribution in the combustion process of a liquid rocket engine mainly includes flame structures and flame characteristics. 36 As depicted in Figure 13, the flame expansion angle increases in both the low-frequency oscillation combustion subprocess and the shutdown subprocess due to the increase in LOx momentum (Figure 12), but the momentum of methane shows little change. The decrease in the momentum flux ratio…”

Section: Resultsmentioning

confidence: 97%

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Experimental Study on the Unsteady Spray Combustion Process of a Liquid Oxygen/Methane Swirl Coaxial Injector

Cao

Bai

et al. 2021

ACS Omega

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The present study experimentally investigated the dynamic spray combustion process of a liquid-centered swirl coaxial injector using liquid oxygen/ methane in an optically accessible liquid rocket engine. Data were obtained at combustor pressures from 0.4 to 1.8 MPa and the ratio of the oxidizer mass flow rate to the fuel rate between 1.32 and 1.55. Liquid oxygen was injected at 120 K, and the injection temperature of gaseous methane was about 285 K. Based on the obtained spatial distribution and oscillation characteristics of liquid oxygen/ methane flame, the combustion process was described by four subprocesses: ignition, low-frequency oscillation combustion, quasi-steady state combustion, and shutdown. In the quasi-steady state combustion subprocess, both the flame length and the normalized flame area are the largest, and the flame expansion angle is the smallest. At the initial stage of combustion, the instability of the liquid oxygen phase state leads to flame instability, which generates low-frequency unstable combustion with a dominant frequency of 93.74 Hz. In addition, the highfrequency (2500−3000 Hz) oscillation of the flame appeared in the whole combustion process. It has been confirmed to be caused by the self-pulsation of spray. Furthermore, with the increase in liquid oxygen manifold pressure, the liquid oxygen phase state changes from a two-phase mixture of liquid and gaseous oxygen to a liquid phase, which increases the mass flow rate of liquid oxygen entering into the combustor, thus generating the increase in the high oscillation frequency of the flame through the whole combustion process.

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Section: Resultsmentioning

confidence: 97%

“…The spatial flame distribution in the combustion process of a liquid rocket engine mainly includes flame structures and flame characteristics Figure presents the changing trend of the flame expansion angle, flame length, and normalized flame area ( A F /A C ).…”

Section: Results and Discussionmentioning

confidence: 99%

Experimental Study on the Unsteady Spray Combustion Process of a Liquid Oxygen/Methane Swirl Coaxial Injector

Cao

Bai

et al. 2021

ACS Omega

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Simulation of the Condensed Phase Particles Electrization in Combustion Products of the Model Hybrid Rocket Engine

Рудинский

Kravchenko

Evstigneeva

2023

2023 5th International Youth Conference on Radio Electronics, Electrical and Power Engineering (REEPE)

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Technique for Recording and Analysis of the Amplitude Spectrum of the Strength Oscillations of Magnetic and Electric Fields of Combustion Products in a Model Liquid Rocket Engine Fuel Depending on the Combustion Chamber Pressure

Yagodnikov

2022

High Temp

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Experimental Study of the Working Process in Liquid Rocket Engines by an Electrophysical Diagnostic Method

Cited by 3 publications

References 8 publications

Experimental Study on the Unsteady Spray Combustion Process of a Liquid Oxygen/Methane Swirl Coaxial Injector

Experimental Study on the Unsteady Spray Combustion Process of a Liquid Oxygen/Methane Swirl Coaxial Injector

Simulation of the Condensed Phase Particles Electrization in Combustion Products of the Model Hybrid Rocket Engine

Technique for Recording and Analysis of the Amplitude Spectrum of the Strength Oscillations of Magnetic and Electric Fields of Combustion Products in a Model Liquid Rocket Engine Fuel Depending on the Combustion Chamber Pressure

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