Calculation-Based Study of the Influence of the Coandă Effect on the Formation of Long-Range Gas Curtains in a Rocket Engine Combustion Chamber
Authors: Taran K.A., Novikov A.V.
Published in issue: #7(175)/2026
Category: Aviation and Rocket-Space Engineering | Chapter: Thermal, Electric Jet Engines, and Power Plants of Aircrafts
A numerical study of the operating process in a model low-thrust rocket engine using gaseous oxygen and gaseous methane as propellants was carried out. A physical and mathematical model describing the interaction between a jet flowing around a step and the wall was considered. This phenomenon is known as the Coandă effect. The influence of the Coandă effect on the organization of film cooling was investigated by varying the operating parameters, namely the oxidizer injection slot width and the combustion chamber diameter. The effects of these parameters on the wall temperature and chamber efficiency coefficient were studied. Dependences of the chamber efficiency coefficient on the oxidizer injection slot width and combustion chamber diameter were obtained, on the basis of which the optimal dimensions providing a chamber efficiency coefficient of 0.883 were determined. In addition, distributions of wall temperature versus the axial coordinate x for different values of the oxidizer injection slot width and combustion chamber diameter were obtained, confirming that the selected parameters ensure a maximum wall temperature not exceeding the allowable value of 1800 K. Based on the obtained temperature fields, the physics of the process was analyzed, and the factors responsible for the observed behavior of the chamber efficiency coefficient and wall temperature were identified, namely the opposite effects of flow turbulence in the combustion chamber and base pressure.
EDN ILOQIJ
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