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We contracted to improve combustion efficiency of SDM. Among several improvements, we felt that selecting a good jet rotational angle can increase combustion efficiency significantly. The actual result of our research is that combustion efficiency can be increased by from 10% to 20%. Section 1 reviews briefly the well known physical model. Section 2 describes the theoretical method we developed. Section 2 utilizes Reynolds averaged Navier Stokes governing equations, RNG(Renormalization Group Method) k-ε...

We contracted to improve combustion efficiency of SDM. Among several improvements, we felt that selecting a good jet rotational angle can increase combustion efficiency significantly. The actual result of our research is that combustion efficiency can be increased by from 10% to 20%. Section 1 reviews briefly the well known physical model. Section 2 describes the theoretical method we developed. Section 2 utilizes Reynolds averaged Navier Stokes governing equations, RNG(Renormalization Group Method) k-ε turbulence model, and finite rate chemical mechanism. Then section 2 describes how to carry out simulation involving three dimensional mixing, chemical reaction, and flow field with upwind difference scheme. Section 3 gives and discusses the results of numerical simulation. Figs.2 and 3 give the combustion efficiencies of 8 different rotational angles(typical ones out of over 80 different rotational angles).Each rotational angle is denoted by the angles made with x,y, and z axes respectively. When θ=θ 4=(10°,80°,90°) , the combustion efficiency can be 10% to 20% higher than the highest one of the test results obtained by Vanka .

在采用 N- S方程、RNG k-ε湍流模型和一步化学反应模型对固体火箭冲压发动机中有混合和化学反应的三维流场进行数值模拟的基础上 ,提出了一种提高固体火箭冲压发动机补燃室补燃效率的方法。讨论喷孔角度对管道火箭性能的影响并和 Vanka的试验结果进行了比较 ,结果表明 ,在同样的工况下选取适当的喷孔旋转角可以将补燃效率提高 1 0 %~ 2 0 %。

 
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