Abstract: A transient simulation method based on three-dimensional models of compressor components was developed, focusing on the transient state of aviation turbine engines components. The dynamic boundaries were used to set rotational speed and static pressure at outlet as the controlling parameters of transient process. The second-order backward Euler scheme was used to calculate the three-dimensional unsteady Reynolds average Navier-Stokes equations. The transient performance and internal unsteady flow field characteristics of a compressor were obtained through three-dimensional unsteady simulation. Using a transonic compressor rotor, NASA Rotor 67, as a model, this method was applied to simulate the transient process accelerating from 60% design rotational speed to 100% design rotational speed, and the transient performance of the compressor and detailed shock structure and its evolution process inside the compressor were obtained. The reliability of the method was verified by comparing with the results calculated by the general characteristic calculation method, as the maximal relative error of total pressure ratio was less than 6% and the maximal relative error of adiabatic efficiency was less than 2% on the whole transient line. The results show that the three-dimensional unsteady simulation method based on dynamic boundaries can accurately simulate the transient performance of compressors and reflect the detailed information of unsteady flow field in transient process.

Key words: Turbine engine;Dynamic boundaries;Transonic compressor;Transient performance

摘要： 针对航空涡轮发动机部件的过渡态，提出了一种基于压气机部件三维模型的过渡态性能计算方法，采用动态边界条件，以转速和出口静压为过渡过程的控制参数，二阶向后欧拉法求解三维非定常雷诺平均Navier-Stokes方程组，通过三维非定常模拟获得压气机的过渡态性能和内部非定常流场特征。以NASA跨声速压气机Rotor 67转子为模型，采用该方法模拟了压气机从60%设计转速加速至100%设计转速的过渡过程，获得了压气机过渡态性能及转子内部详细的激波结构与演变过程。对比通用特性结果，在整个过渡曲线上，总压比相对误差最大值小于6%，绝热效率相对误差最大值小于2%，验证了该方法的可靠性。结论表明：基于动态边界的三维非定常模拟方法能够准确模拟压气机的过渡态性能，并反映出过渡态的非定常流场详细信息。

关键词: 涡轮发动机;动态边界;跨声速压气机;过渡态性能