Volume 36 Issue 4
Apr.  2010
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Du Zhenggang, Li Mao, Jin Ping, et al. Large mass flowrate gas-gas injector optimization design with response surface methodology[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(4): 395-398. (in Chinese)
Citation: Du Zhenggang, Li Mao, Jin Ping, et al. Large mass flowrate gas-gas injector optimization design with response surface methodology[J]. Journal of Beijing University of Aeronautics and Astronautics, 2010, 36(4): 395-398. (in Chinese)

Large mass flowrate gas-gas injector optimization design with response surface methodology

  • Received Date: 27 Mar 2009
  • Publish Date: 30 Apr 2010
  • In order to investigate the effect of design parameters of dual shear coaxial injector that utilizes gaseous oxygen and hydrogen as propellants on the combustion location, the numerical simulation efforts were performed to simulate the flow field of combustor with orthogonal array applied to guide the injector design. The results display that dual shear coaxial injector made propellants combusted efficiently at the condition of large mass flowrate which was close to eight times greater than that of space shuttle main engine (SSME) single element injector. The range analysis and variance analysis indicate that the velocity ratio of hydrogen to oxygen has significant effect on the combustion location, while the ratio of center hydrogen mass fraction and oxygen wall thickness have not influenced the combustion location significantly. The response surface methodology based on orthogonal-polynomial is employed to get the optimized parameters of the dual shear coaxial injector.

     

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