基于流固耦合的部分进气涡轮数值模拟研究

Numerical simulation method of partial admission turbine based on fluid-structure coupling

发展了三维线性插值算法用于CSD/CFD耦合计算数据交换,对某型液体火箭发动机部分进气涡轮进行了气/热/固多学科耦合数值仿真。结果表明,发展的三维线性插值程序对网格类型限制性小,计算简单,计算量小,插值结果能够满足耦合计算要求。仿真结果表明,某型火箭发动机涡轮由于其部分进气结构设计和叶轮高速旋转,设计工况下在涡轮转子入口处产生了较强的激波,激波与边界层干涉不仅使涡轮转子叶片的载荷分布出现了强烈的不均匀性,同时在叶轮的高速旋转下,该涡轮转子受到强烈的气动、热交变力冲击,其结构强度问题变得尤为突出。耦合计算分析认为设计工况下,该型涡轮结构设计,转子强度能够满足要求。

A three-dimensional linear interpolation method is developed for the exchange of CSD/CFD coupling calculation data to execute numerical simulation of air/thermal/liquid-structure coupling for a partial admission turbine in liquid rocket engine. The results show that the developed three- dimensional linear interpolation program relies on grid type weakly, has the characteristics of simple calculation and less calculated quantity, and can meet the requirements of coupling calculation. The results of the coupling simulation show that a serious shock wave is generated at inlet of turbine rotor, which makes the blade load distribution asymmetrical which has an important impact on the turbine rotor. The coupling calculation and analysis shows that the strength of the turbine rotor with the designed structure can satisfy the requirements. The design can provide a reference for designand engineering application of the partial admission turbine in a certain type of liquid rocket engine.