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首页> 外文期刊>International Journal of Turbo and Jet Engines >Large Eddy Simulation of Secondary Flows in an Ultra-High Lift Low Pressure Turbine Cascade at Various Inlet Incidences
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Large Eddy Simulation of Secondary Flows in an Ultra-High Lift Low Pressure Turbine Cascade at Various Inlet Incidences

机译：在各种入口通道的超高升降机低压涡轮机级联中次流的大型涡流模拟

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摘要

Increasing the blade loading of a low pressure turbine blade decreases the number of blades, thus improving the aero-engine performance in terms of the weight and manufacture cost. Many studies focused on the blade-to-blade flow field of ultra-high lift low pressure turbines. The secondary flows of ultra-high lift low pressure turbines received much less attention. This paper investigates the secondary flows in an ultra-high lift low pressure turbine cascade T106C by large eddy simulation at a Reynolds number of 100,000. Both time-averaged and instantaneous flow fields of this ultrahigh lift low pressure turbine are presented. To understand the effects of the inlet angle, five incidences of -10°, -5°, 0, +5° and +10° are investigated. The case at the design incidence is analyzed first. Detailed data is used to illustrate the how the fluids in boundary layers develops into secondary flows. Then, the cases with different inlet incidences are discussed. The aerodynamic performances are compared. The effect of blade loading on the vortex structures is investigated. The horseshoe vortex, passage vortex and the suction side corner vortex are very sensitive to the loading of the front part of the blade.
机译：增加低压涡轮叶片的刀片加载减小了叶片的数量，从而在重量和制造成本方面提高了航空发动机性能。许多研究专注于超高升降机低压涡轮机的刀片到叶片流场。超高升降机低压涡轮机的二次流量受到更少的关注。本文通过在雷诺数为100,000的雷诺数，调查超高提升低压涡轮机级联T106C中的二次流动。提出了这种超高提升低压涡轮机的时间平均和瞬时流动场。要了解入口角的效果，研究了-10°，-5°，0，+ 5°和+ 10°的五种发射。首先分析设计入射的情况。详细数据用于说明边界层中的流体如何发展成二次流动。然后，讨论了具有不同入口发夹的案例。比较空气动力学性能。研究了叶片加载对涡旋结构的影响。马蹄形涡旋，通道涡流和吸入侧旋转涡流对刀片的前部的装载非常敏感。

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