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首页> 外文期刊>International Journal of Heat and Mass Transfer >High pressure turbine blade internal cooling in a realistic rib roughened two-pass channel
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High pressure turbine blade internal cooling in a realistic rib roughened two-pass channel

机译：高压涡轮叶片内部冷却在现实肋骨粗糙的双通道

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摘要

Simplified rectangular or square channels are commonly adopted for studying turbine blade internal cooling characteristics under constant temperature or constant heat flux boundary conditions, but the effects caused by those simplifications have not been considered in detail. This paper used a numerical method to study blade internal cooling in a realistic rib roughened two-pass channel of a Pratt & Whitney Energy Efficient Engine high-pressure turbine blade under turbine design conditions. The purposes are two-fold: 1) to investigate the effects of the types of wall boundary condition on blade internal heat transfer, including coupled wall, constant temperature wall, and constant heat flux wall; 2) to present the internal heat transfer and pressure losses in the channel with two types of rib roughened walls, i.e., Model A with 60-degree inclined ribs and Model B with 60-degree V-shaped ribs. Both stationary and two rotating conditions with rotation number Ro= 0.1 and 0.2 are considered. The turbulence model is Shear Stress Transport k-ω model. The results revealed that: 1) The types of wall boundary conditions have large effects on blade internal cooling performance. At the stationary condition, the maximum difference in local normalized Nusselt number (Nu/Nu_0) on the trailing surface can be as large as 44.4% between the coupled wall and constant temperature at the inlet pass, and 50% between the coupled wall and constant heat flux at the outlet pass. Under blade rotations, the large difference in Nu/Nu_0 remains on the trailing surface, while on the leading surface only minor difference exists. 2) At the stationary condition, the maximum difference in Nu/Nu_0 between the trailing surface and leading surface for Model A 51.3%, and Model B 40.7%. 3) At the stationary condition, in the inlet pass, the results of Mode A and B are close to the simplified channels. In the outlet pass, a relatively large discrepancy exists between the two ribbed models and their corresponding simplified channel results. 4) Blade rotation results in a large increase in Nu/Nuo on the trailing surface in the inlet pass and bend regions of the three models. The maximum change in Nu/Nu_0 reaches over 100% for each model, which is significantly higher than that of the simplified channels. 5) The friction factor of the two ribbed models decreases with the rotation number. The difference in pressure drop and friction factor between the two ribbed models also decreases with the rotation number.
机译：通常采用简化的矩形或方形通道用于在恒定温度或恒定的热通量边界条件下研究涡轮机叶片内部冷却特性，但是未详细考虑由这些简化引起的效果。本文采用了一种在涡轮设计条件下的普通＆惠特尼节能发动机高压涡轮叶片的实际肋骨粗糙通道中研究叶片内部冷却。目的是两倍：1）为了研究壁边界条件类型对叶片内部传热，包括耦合壁，恒温壁和恒温焊剂的影响; 2）以具有两种类型的肋粗糙壁，即型号A的沟道内的内部传热和压力损失，其中具有60度倾斜肋和模型B，具有60度V形肋。考虑静止和两个旋转条件，旋转数量RO = 0.1和0.2。湍流模型是剪切应力传输K-ω模型。结果表明：1）墙边界条件的类型对叶片内部冷却性能具有很大的影响。在静止条件下，尾后表面上的局部归一化篮板（Nu / Nu_0）的最大差异可以在耦合壁和入口通道的恒定温度之间大至44.4％，并且在耦合壁和恒定之间的50％出口通量在出口通量。在刀片旋转下，Nu / Nu_0的较大差异保持在尾部表面上，而在前面的表面上仅存在轻微差异。 2）在静止状态下，尾表面和前导表面之间的Nu / Nu_0的最大差异为51.3％，B 2 40.7％。 3）在静止状态下，在入口通行证中，模式A和B的结果接近简化通道。在出口通过中，两个罗纹模型之间存在相对较大的差异及其相应的简化信道结果。 4）刀片旋转导致在入口通行证和三种型号的弯曲区域中的尾部表面上的nu / nuo大幅增加。 Nu / Nu_0的最大变化对于每个型号超过100％，其显着高于简化通道。 5）两个罗纹模型的摩擦系数随旋转数而降低。两个罗纹模型之间的压降和摩擦系数的差异也随着旋转数而降低。

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  • 来源
    《International Journal of Heat and Mass Transfer》 |2021年第5期|121019.1-121019.14|共14页
  • 作者

    Xu Wang; Huazhao Xu; Jianhua Wang; Wei Song; Lei Wang;

  • 作者单位

    CAS Key Laboratory of Mechanical Behavior and Design of Materials Department of Thermal Science and Energy Engineering University of Science and Technology of China Jinzhai Road No. 96 Hefei 230027 Anhui PR China;

    CAS Key Laboratory of Mechanical Behavior and Design of Materials Department of Thermal Science and Energy Engineering University of Science and Technology of China Jinzhai Road No. 96 Hefei 230027 Anhui PR China;

    CAS Key Laboratory of Mechanical Behavior and Design of Materials Department of Thermal Science and Energy Engineering University of Science and Technology of China Jinzhai Road No. 96 Hefei 230027 Anhui PR China;

    Research Institute of Aero-engine Corporation of China Shenyang Liaoning PR China;

    Research Institute of Aero-engine Corporation of China Shenyang Liaoning PR China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Internal cooling; Numerical simulation; Conjugate heat transfer; High pressure turbine; Coupled wall;

    机译：内部冷却;数值模拟;共轭传热;高压涡轮机;耦合墙;

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