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NUMERICAL SIMULATION OF TRANSIENT FLOWS IN A ROCKET PROPULSION NOZZLE

Suryakant P. Nagdewe
School of Mechanical Engineering, Andong National University 388 Songchun-dong, Andong, Gyeongbuk, 760-749, Korea

Heuy Dong Kim
Department of Mechanical Engineering, Andong National University, Andong 760-749, Korea

Toshiaki Setoguchi
Institute of Ocean Energy (IOES), Saga University, 1, Honjo-machi, Saga 840-8502, Japan

Abstract

A numerical investigation of transient flows in an axisymmetric over-expanded thrust optimized contour nozzle is presented. These nozzles experience side-loads during start-up and shut-down operations, because of the flow separation at nozzle walls. Two types of flow separation such as FSS and RSS shock structure occur. A two-dimension numerical simulation has been carried out over an axisymmetric TOC nozzle to validate present results and investigate transient flow characteristics for start-up processes. Reynolds Averaged Navier−Stokes equations are numerically solved using a fully implicit finite volume scheme. Governing equations are solved by coupled implicit scheme. Reynolds Stress turbulence model is selected. Present computed pressure at the nozzle wall closely matched with experiment data. A hysteresis phenomenon has been observed between these two shock structures. The transition from FSS to RSS pattern during start-up process has shown maximum nozzle wall pressure. Nozzle wall pressure values have shown fluctuations during the FSS to RSS transition. The end-effect has been observed at high pressure ratio, when the recirculation bubble opens to the atmosphere.