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首页> 外文期刊>Journal of Aerospace Sciences and Technologies >COMPUTATIONAL INVESTIGATION OF EFFECT OF TIP CLEARANCE IN AN ANNULAR TURBINE ROTOR IMPULSE CASCADE
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COMPUTATIONAL INVESTIGATION OF EFFECT OF TIP CLEARANCE IN AN ANNULAR TURBINE ROTOR IMPULSE CASCADE

机译：环形涡轮转子脉冲级联中尖端间隙影响的计算研究

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摘要

This paper describes three dimensional computational investigations of the effect of the tip clearance on the secondary and tip clearance flows in an annular turbine rotor cascade with non uniform inlet flow. In the actual turbine, the flow at inlet of the rotor is non uniform due to radial pressure gradient acting from the hub to casing. To provide non uniformity at the rotor cascade inlet, an annular nozzle cascade is provided at the upstream. The studies are carried out with the help of a commercially available CFD package. The studies have been carried out for four values of clearance, i.e. 0%, 1%, 3% and 5% of chord. Detailed comparison of the leakage flow direction, pressure gradient, and leakage vortex size, losses, location and interaction with other flow features is carried out. The results are presented in terms of static pressure coefficient distribution on the blade surfaces and total pressure loss coefficient contours in the passage. Spanwise distributions of the circumferentially averaged loss coefficient and flow angle are presented. The extent of losses in the circumferential direction is increased with the increase in the height of the tip clearance but reduced in the spanwise direction. The mass averaged loss coefficient increases rapidly from 0.24 at zero clearance to 0.42 at 1% tip clearance. As the tip clearance is further increased, the losses increase slowly (0.54 at 3% tip clearance to 0.58 at 5% tip clearance). The mass averagedflow angle decreases from 66.3° at zero clearance to 63.7° at 1% clearance to 60.1° at 3% clearance and to 57.3° at 5% clearance.
机译：本文描述了在入口流量不均匀的环形涡轮转子叶栅中，叶尖间隙对次级和叶尖间隙流动的影响的三维计算研究。在实际的涡轮机中，由于从轮毂到壳体的径向压力梯度，转子进口处的流量是不均匀的。为了在转子叶栅入口处提供不均匀性，在上游提供了环形喷嘴叶栅。借助可商购的CFD软件包进行研究。已针对间隙的四个值（即弦的0％，1％，3％和5％）进行了研究。进行了泄漏流方向，压力梯度和泄漏涡流大小，损失，位置以及与其他流动特征的相互作用的详细比较。结果以叶片表面上的静压力系数分布和通道中的总压力损失系数轮廓表示。给出了周向平均损耗系数和流动角的横向分布。沿圆周方向的损失程度随刀尖间隙高度的增加而增加，但沿翼展方向减小。质量平均损失系数从零间隙处的0.24迅速增加到尖端间隙为1％时的0.42。随着尖端间隙的进一步增加，损耗会缓慢增加（尖端间隙为3％时为0.54，尖端间隙为5％时为0.58）。质量平均流角从零间隙处的66.3°减小到1％间隙处的63.7°到3％间隙处的60.1°和5％间隙处的57.3°。

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