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为了研究液体火箭发动机涡轮内流场,发展了一种基于相对流面理论和流线曲率法的多级跨声速叶轮机械流场计算方法.首先使用流线曲率法求解流面内的流场,再采用全三维流面迭代的方法得到三维流场.计算过程中通过临界流量的对比确定跨声速流道内的喉部位置,采用混合平面法将动、静叶间的非定常流动转化为定常流动.激波和黏性等损失通过相应的损失模型进行计算.对于多级流道内不同的超声速/亚声速流动状态则采用穷举法计算所有可能情况并用出口参数筛选最接近真实情况的结果.该方法准确地计算出了多级跨声速涡轮流场中的流动参数分布和性能参数,为进一步改进涡轮设计、提高涡轮性能提供了理论依据.
In order to study the flow field in the liquid rocket engine turbomachinery, a multi-level transonic impeller mechanical flowfield calculation method based on the theory of relative flow surface and the method of flow curvature is developed.Firstly, the flow field curvature method is used to solve the flow field, Then the 3D flow field is obtained by using the full three-dimensional flow surface iteration method, and the throat position in the transonic flow channel is determined by comparing the critical flow rates in the calculation process. The mixed plane method is used to transform the unsteady flow between the moving and stationary vanes into a steady flow Shock and viscosity losses are calculated using the corresponding loss model.For all the different supersonic / subsonic flows in a multistage flowpath, exhaustive methods are used to calculate all possible cases and the exit parameters are used to screen the results that are closest to the real situation. The method can accurately calculate the flow parameter distribution and performance parameters in the multi-stage transonic turbine flow field, providing a theoretical basis for further improving the turbine design and improving the turbine performance.