SIMULATION OF OXYGEN STEAM JET CONDENSATION IN LIQUID OXYGEN
DOI:
https://doi.org/10.32782/KNTU2618-0340/2020.3.2-2.14Ключові слова:
condensation, gaseous oxygen stream, liquid oxygen flow, length of the condensation region, phase transition criterion, oxygen gas velocity, liquid oxygen velocity, generalization of experimental data, regression analysisАнотація
The results of numerical calculations of the length of the condensation region of a gaseous oxygen jet in a liquid oxygen flow are presented.
Condensation of superheated steam jet of a low-temperature substances has its own characteristics in comparison with condensation of a water vapor jet. When modeling flows of various substances, the following dimensionless parameters and criteria can be used: density ratio of liquid and vapor, velocity ratio liquid to vapor, and the phase transition criterion. The oxygen gas temperature can be significantly higher than the saturation temperature, which leads to different condensation conditions.
Experimental data with visualization of the condensation process of a stream of gaseous oxygen in a stream of liquid oxygen, namely, photographs are used. In the photographs, the condensation area is predominantly in the shape of a torch; in the early studies of jet condensation of water vapor in water, the jet was shaped like a cone.
As a result of generalization of the experimental data, a formula was obtained for determining the length of the condensation region. As a result of applying the methods of nonlinear regression analysis, the values of the parameters for the function, which are used to determine the length of the condensation region of gaseous oxygen in the flow of liquid oxygen, have been refined. We calculated the standard deviations of the experimental data from the theoretical data, which were obtained on the basis of an analytical dependence with two sets of parameter values: new and proposed in [2]. Comparative analysis of the accuracy of the constructed approximating functions is carried out. New function is more accurate and can be used for mathematical modeling of the dynamics of the pumping system of a liquid propellant rocket engine.
Посилання
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