基于动态边界的跨声速压气机过渡态三维模拟方法

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.