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求解了某型航空发动机的低压涡轮导向器内流场。采用的数值方法为具有 TVD性质的三阶精度GODU NOV格式 ,湍流模型为 B-L代数模型及 MML模型的混合修正模型。该涡轮导向器的一个显著特点是由于结构上的要求 ,静叶前子午流道在上端壁具有较大的扩张角。通过数值模拟及流场内涡系结构和损失的分析表明 ,由于子午扩张造成端壁附面层增厚并在静叶前形成较大的分离区。该分离区的存在不但使静叶前损失急剧增加而且使上端壁马蹄涡和通道涡尺度加大 ,强度增强 ,引起流道内损失增加。
The flow field in a low pressure turbine guide of aeroengine is solved. The numerical method adopted is the third-order accuracy GODU NOV with TVD property, and the turbulence model is a mixed modification model of B-L algebra model and MML model. A notable feature of the turbine guide is that due to structural requirements, the vortex of the vortex before the vane has a larger divergence angle at the upper end wall. Numerical simulation and analysis of eddy structure and loss in the flow field show that due to the meridional expansion, the thickening of the surface wall of the end wall and the formation of a larger separation zone in front of the vane. The existence of the separation zone not only increased the static loss of the vane but also increased the vortex scale of the horseshoe vortex and the channel on the upper end wall, increasing the strength and causing the loss in the runner to increase.