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首页> 外文学位 >An investigation on the effects of the high maximum-thickness-to-chord ratio on the performance of nozzle guide vanes in a transonic planar cascade.
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An investigation on the effects of the high maximum-thickness-to-chord ratio on the performance of nozzle guide vanes in a transonic planar cascade.

机译：研究高音高和弦比对跨音速平面叶栅中喷嘴导叶性能的影响。

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摘要

The performance of turbine airfoils is usually predicted by empirical correlations. However, these correlations are inadequate to predict the performance of airfoils with maximum-thickness-to-chord ratio of higher than 25%.;A planar cascade consisting of four airfoils was constructed to allow the investigation of the effect of the maximum-thickness-to-chord ratio on the airfoil performance. Three airfoil sets with maximum-thickness-to-chord ratio of 15.2% (baseline), 26.6% (27% airfoil) and 48.2% (48% airfoil) were used. Measurements included surface Mach number distributions for the baseline airfoil, total pressure loss coefficients and deviation angles of isentropic exit Mach numbers of 0.7 (design), 0.9 and 1.1. Also the effect of varying the inlet boundary layer thickness and free-stream turbulence level was investigated. The results showed that the 27% airfoil produced lower losses as predicted by the Kacker and Okapuu correlation (1982). The introduction of turbulence produced a significant redistribution of the losses in the exit place. The secondary loss decreased as the leading edge diameter was increased. Except for the baseline blade where high under-turning in exit flow angle was observed, the 27% and 48% airfoils showed a decrease in over-turning with increasing exit Mach number, as predicted by Ainley and Mathieson (1951).;To create a data base from which the performance of turbine airfoils with the maximum-thickness-to-chord ratio of higher than 25% could be predicted, a collaborative work between Pratt & Whitney Canada, National Research Council and Carleton University was initiated.
机译：涡轮机翼的性能通常通过经验相关性进行预测。但是，这些相关性不足以预测最大厚度与弦的比率大于25％的机翼的性能。；构造了由四个机翼组成的平面叶栅，以研究最大厚度的影响。弦比对翼型性能的影响。使用了三个翼型套件，最大厚度与弦的比例分别为15.2％（基线），26.6％（27％翼型）和48.2％（48％翼型）。测量包括基准翼型的表面马赫数分布，总压力损失系数和等熵出口马赫数的偏差角（设计）为0.7、0.9和1.1。还研究了改变入口边界层厚度和自由流湍流水平的影响。结果表明，根据Kacker和Okapuu相关性（1982）的预测，机翼的27％产生的损失较小。湍流的引入对出口处的损失进行了重新分配。二次损耗随着前缘直径的增加而降低。正如Ainley和Mathieson（1951）所预测的那样，除了基线叶片上观察到出口流向角有很大的下弯之外，随着出口马赫数的增加，27％和48％的机翼的上倾角减小。通过一个数据库，可以预测最大厚度与弦比大于25％的涡轮机翼的性能，加拿大普惠公司，国家研究委员会和卡尔顿大学之间开展了一项合作研究。

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  • 作者

    Radmard, Rama.;

  • 作者单位

    Carleton University (Canada).;

  • 授予单位 Carleton University (Canada).;
  • 学科 Engineering Aerospace.
  • 学位 M.Eng.
  • 年度 1993
  • 页码 210 p.
  • 总页数 210
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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