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首页> 外文期刊>The Aeronautical Journal >An unsteady numerical analysis of a generic non-axisymmetric turbine endwall in a 1 1/2 stage turbine test rig
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An unsteady numerical analysis of a generic non-axisymmetric turbine endwall in a 1 1/2 stage turbine test rig

机译：1 1/2级涡轮试验台中通用非轴对称涡轮端壁的非定常数值分析

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摘要

As concern for the environment increases, so does the desire to reduce emissions and improve fuel efficiency. One avenue being investigated in the aerospace industry is the reduction in losses in a gas turbine engine through endwall contouring, which has shown some promise in improving efficiency. The current investigation was aimed at investigating the unsteady effects downstream of a rotor with a non-axisymmetric endwall contour originally designed for a cascade. Previous investigations (numerical and experimental) have shown that the endwall contour improved the turbine efficiency by reducing the cross passage secondary flows. The contour however had a detrimental effect on the tip flow. The current investigation found that there were negligible unsteady differences between the annular and contoured rotor, with the average comparing well to the steady state results. It was also found that the effects at the tip were due to the experimental blades untwisting during operation.
机译：随着人们对环境的关注增加，减少排放和提高燃油效率的愿望也在增加。航空航天业正在研究的一种途径是通过端壁轮廓减少燃气涡轮发动机的损失，这在提高效率方面已显示出一定的希望。当前的研究旨在调查具有非轴对称端壁轮廓的转子下游的不稳定影响，该轮廓最初是为级联设计的。先前的研究（数值和实验）表明，端壁轮廓通过减少交叉通道的二次流而提高了涡轮效率。然而，轮廓对尖端流动有不利影响。当前的研究发现，环形转子和异形转子之间的非稳态差异可忽略不计，其平均值与稳态结果相比较。还发现尖端的影响是由于实验刀片在操作过程中未扭转。

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  • 来源
    《The Aeronautical Journal》 |2015年第1211期|109-119|共11页
  • 作者

    D. Dunn; T. W. von Backstroem; G. Snedden;

  • 作者单位

    Department of Mechanical and Mechatronic Engineering University of Stellenbosch Pretoria South Africa;

    Department of Mechanical and Mechatronic Engineering University of Stellenbosch Pretoria South Africa;

    CSIR Pretoria South Africa;

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