Open AccessTechnology of computational analysis of the working process parameters of low-thrust rocket engines running on gaseous oxygen-hydrogen fuel with the use of ANSYS CFD
Author(s) -
В. В. Рыжков,
И Ю Морозов
Publication year - 2019
Publication title -
vestnik samarskogo universiteta. aèrokosmičeskaâ tehnika, tehnologii i mašinostroenie
Language(s) - English
Resource type - Journals
eISSN - 2541-7533
pISSN - 2542-0453
DOI - 10.18287/2541-7533-2019-18-2-62-74
Subject(s) - rocket engine , combustion chamber , rocket engine nozzle , nozzle , thrust , aerospace engineering , computational fluid dynamics , combustion , rocket (weapon) , mechanical engineering , automotive engineering , engineering , nuclear engineering , chemistry , organic chemistry
The paper presents the description of a mathematical model of the working process of a low-thrust rocket engine operating on gaseous oxygen-hydrogen fuel and some fragments of the technology of computational analysis of distribution of gas-dynamic parameters in the engine duct. We present the results of calculating the stream line distribution, the distribution of total temperature profile along the flow path of the engine chamber and at its characteristic cross sections, the axial component of (total) speed of combustion products in the Laval nozzle output section. The results of calculating the temperature in the area of the rocket engine’s inner wall are presented. It is shown that the distribution of the combustion products’ stagnation temperature has a significant impact on the efficiency of fuel conversion in the engine chamber, its thermal state and makes it possible to identify the ways of improving the workflow of the low-thrust rocket engine.