NUMERICAL SIMULATION OF COMBUSTION PROCESS IN A LIQUID H<SUB>2</SUB>/O<SUB>2</SUB> ROCKET ENGINE

Liu Weidong; Wang Zhenguo; Zhou Jin

Volume 13 Issue 3

Jul. 1998

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Article Navigation > Journal of Aerospace Power > 1998 > 13(3): 337-338,352

Liu Weidong, Wang Zhenguo, Zhou Jin. NUMERICAL SIMULATION OF COMBUSTION PROCESS IN A LIQUID H2/O2 ROCKET ENGINE[J]. Journal of Aerospace Power, 1998, 13(3): 337-338,352.

Citation:

Liu Weidong, Wang Zhenguo, Zhou Jin. NUMERICAL SIMULATION OF COMBUSTION PROCESS IN A LIQUID H₂/O₂ ROCKET ENGINE[J]. Journal of Aerospace Power, 1998, 13(3): 337-338,352.

Liu Weidong, Wang Zhenguo, Zhou Jin. NUMERICAL SIMULATION OF COMBUSTION PROCESS IN A LIQUID H2/O2 ROCKET ENGINE[J]. Journal of Aerospace Power, 1998, 13(3): 337-338,352.

Citation:

Liu Weidong, Wang Zhenguo, Zhou Jin. NUMERICAL SIMULATION OF COMBUSTION PROCESS IN A LIQUID H₂/O₂ ROCKET ENGINE[J]. Journal of Aerospace Power, 1998, 13(3): 337-338,352.

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NUMERICAL SIMULATION OF COMBUSTION PROCESS IN A LIQUID H₂/O₂ ROCKET ENGINE

2nd Dept.Nanjing University of Aeronautics and Astronautics,Nanjing 210016

Received Date: 1997-12-01
Rev Recd Date: 1998-02-01
Publish Date: 1998-07-28

Abstract

Abstract

Numerical simulation is employed in calculation of the combustion processes in the rocket engine which uses liquid hydrogen and oxygen as propellants.A random spray model is used to describe the initial conditions of oxygen droplets.The evaporation rate of the oxygen droplets at high pressure is calculated by ZKS model.The Arrehnius model is adopted to compute the chemical reaction rates.PISO algorithm extended by the authors is used to calculate the spray combustion flow.The convection terms of the governing equations are discretized by a second-order upwind scheme.
- Spray combustion,
- Algorithms,
- Hydrogen/oxygen engines