液体火箭发动机氧腔流动分析及均流板设计研究

采用Navier-Stokes方程数值模拟了某型火箭发动机推力室氧腔流动，计算分析了节流板表面的总、静压分布及其畸变指数。依据压力畸变提出了氧腔均流孔板改进方法，并通过多次分析-设计循环得到了新的均流板。最后对所设计的均流板进行了详细地计算分析和实验验证。分析和验证表明新设计的均流板使氧腔出口节流板表面压力畸变降低了30．4％，显著提高了氧腔压力均匀性，进而可以大大提高燃烧效率。

Flow Analysis and Orifice Plate Design for Oxygen Chamber of a Liquid Propellant Rocket Engine

The oxygen-chamber flow in thrust chamber of a liquid propellant rocket engine is numerically simulated using Navier-Stokes solver. The total/static pressure distributions and pressure distortion on the throttle plate are analyzed. A method to improve the flow-uniforming orifice-plate design is developed based on the calculated pressure distortion, and the new orifice plate is designed via several analysis-design cycles. Finally numerical and experimental validations are performed for the newly designed case, the analysis and validation show that the pressure distortion on the throttle plate is reduced 30.4% in new design. This improves the uniformity evidently, thus the combustion efficiency can be significantly improved.