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首页> 外文会议>ASME Turbo Expo vol.3 pt.A; 20050606-09; Reno-Tahoe,NV(US) >Net Heat Flux Reduction and Overall Effectiveness for a Turbine Blade Leading Edge
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Net Heat Flux Reduction and Overall Effectiveness for a Turbine Blade Leading Edge

机译：净热通量减少和涡轮叶片前缘的整体效率

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摘要

The external cooling performance of a film cooled turbine airfoil can be quantified as a net reduction in heat transfer relative to the turbine airfoil without film cooling. This quantification is generally accomplished by using measurements of the adiabatic effectiveness and the change in heat transfer coefficients (h_f/h_0) for the film cooled surface to determine the net heat flux reduction (Δq_r). Although measurement of Δq_r for laboratory models give an indication of the ultimate film cooling performance, this does not show how much the surface temperature of the airfoil is reduced by film cooling. Measurement of scaled surface temperatures can be accomplished by using laboratory models constructed so that the Biot number is matched with that of the actual airfoil. These measurements provide a scaled temperature distribution on the airfoil that is referred to as the overall effectiveness, φ. For the current study, measurements of Δq_r and φ have been made for a simulated turbine blade leading edge. The simulated leading edge incorporated shaped coolant holes, and had three rows of coolant holes. Improvements due to the shaped holes were determined by comparisons with previously measured round hole configurations. Spatially distributed h_f/h_0 show increases of 5% to 15% for M= 1.0 and 10% to 30% for M= 2.0. Results show that local variation in Δq_r much greater than variation in φ, but laterally averaged Δq_r distributions are reasonable predictors of the laterally averaged φ distributions.
机译：薄膜冷却的涡轮机翼型的外部冷却性能可以量化为相对于没有薄膜冷却的涡轮机翼型的传热净减少。通常通过使用绝热效果的测量值和薄膜冷却表面的传热系数变化（h_f / h_0）来确定净热通量减少量（Δq_r）来完成此量化。尽管实验室模型的Δq_r的测量值表明了最终的薄膜冷却性能，但这并未显示出通过薄膜冷却将翼型件的表面温度降低了多少。可以通过使用实验室模型来完成按比例缩放的表面温度的测量，该实验室模型应构建为使Biot数与实际机翼的Biot数匹配。这些测量提供了翼型上成比例的温度分布，这被称为整体有效性。对于当前的研究，已经对模拟涡轮叶片前缘进行了Δq_r和φ的测量。模拟的前缘包含成形的冷却液孔，并具有三排冷却液孔。通过与先前测得的圆孔配置进行比较，确定了由于成形孔而导致的改进。空间分布的h_f / h_0显示，对于M = 1.0，增加5％至15％，对于M = 2.0，增加10％至30％。结果表明，Δq_r的局部变化远大于φ的变化，但横向平均Δq_r分布是横向平均φ分布的合理预测因子。

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