It is known that boundary layer transition and turbulent separation flow after transition can be influenced significantly by surface roughness. Since the traditional hybrid RANS/LES method cannot predict the boundary layer transition, and the RANS-based transition model cannot accurately simulate the massively separated flow, the present study sought to build an effective modeling strategy for the laminar, roughness-induced-transition and attached turbulence/massively separated flows that couples the Very-Large-Eddy-Simulation (VLES) model and a transition model considering roughness effects. Because the hybrid function between the transition model and VLES model constructed in the previous version still has some flaws, there is still a large laminar flow indication area in the turbulent flow region, which will reduce the simulation accuracy of the turbulent flow after transition. In this paper, the hybrid function is improved, which is examined in the simulation of the high-subsonic flow around the V103 compressor blade. Our analysis shows that the new hybrid model operates in the flow around the V103 compressor blade. The predictions of laminar separation bubble-induced transition, separation evolution, and reattachment are in accord with measurements and the LES results over both smooth and rough surfaces, indicating that the present transitional VLES method can achieve the simulation accuracy close to the LES method while reducing the computational cost.

众所周知，边界层转变和转变后的湍流分离流会受到表面粗糙度的显着影响。由于传统的混合RANS/LES方法无法预测边界层转变，并且基于RANS的转变模型无法准确模拟大规模分离流，因此本研究试图建立一种有效的层流、粗糙度诱导转变和边界层转变建模策略。附加湍流/大规模分离流，将超大涡模拟 (VLES) 模型和考虑粗糙度影响的过渡模型结合起来。由于之前版本构建的过渡模型和VLES模型的混合函数仍然存在一些缺陷，所以仍然存在较大的缺陷。层流指示区域位于湍流区域，这会降低过渡后湍流的模拟精度。本文对混合功能进行了改进，并在 V103压气机叶片周围高亚音速流动的模拟中进行了检验。我们的分析表明，新的混合模型在 V103 压缩机叶片周围的流动中运行。层流分离气泡引起的转变、分离演化和再附着的预测与光滑和粗糙表面上的测量和 LES 结果一致，表明当前的过渡 VLES 方法可以达到接近 LES 方法的模拟精度，同时减少计算成本。