Sensitivity of laidback fan-shaped hole discharge coefficient under internal coolant crossflow conditions

IF 1.9 3区工程技术 Q3 ENGINEERING, MECHANICAL Journal of Turbomachinery-Transactions of the Asme Pub Date : 2023-09-07 DOI:10.1115/1.4063366

Haoyang Liu, Qiang Du, Qingzong Xu, Guangyao Xu, Hongye Li, Dawei Chen

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Abstract

An experimental study was performed on the discharge coefficients of laidback fan-shaped holes under different internal coolant crossflow orientations. The influence of the geometric and flow parameters on the discharge coefficient was investigated under flat plate conditions, where the pressure ratio ranged from 1–1.6. The results show that the film hole discharge coefficient is more sensitive to variations in the coolant crossflow under small pressure ratios. In comparison, the discharge coefficient is much less sensitive to the change of coolant crossflow under high pressure. Meanwhile, the length of the cylindrical section varied over the range of 1D–4D, and the length of the expansion section varied from 2D–6D, where D represents the diameter of the film hole. The results show that the discharge coefficient is much more sensitive to the length of the cylindrical section than to the length of the expansion section. To quantify the sensitivity of the internal crossflow effects on the discharge coefficient, a low-ordered reduced model is proposed for the discharge coefficient of laidback fan-shaped holes. Both the geometric and flow parameters are considered in the model and give prediction errors within 5%.

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内部冷却剂横流条件下回流扇形孔流量系数的灵敏度

对不同内部冷却剂横流方向下的回流扇形孔的流量系数进行了实验研究。在平板条件下，研究了几何参数和流量参数对流量系数的影响，其中压力比在1-1.6之间。结果表明，在小的压力比下，膜孔流量系数对冷却剂横流的变化更敏感。相比之下，流量系数对高压下冷却剂横流的变化不太敏感。同时，圆柱形截面的长度在1D–4D的范围内变化，膨胀截面的长度从2D–6D变化，其中D表示薄膜孔的直径。结果表明，流量系数对圆柱段长度比对膨胀段长度更敏感。为了量化内部横流效应对流量系数的敏感性，提出了一个低阶简化模型，用于计算悠闲扇形孔的流量系数。模型中同时考虑了几何参数和流量参数，预测误差在5%以内。

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来源期刊

Journal of Turbomachinery-Transactions of the Asme 工程技术-工程：机械

CiteScore

4.70

自引率

11.80%

发文量

168

审稿时长

9 months

期刊介绍： The Journal of Turbomachinery publishes archival-quality, peer-reviewed technical papers that advance the state-of-the-art of turbomachinery technology related to gas turbine engines. The broad scope of the subject matter includes the fluid dynamics, heat transfer, and aeromechanics technology associated with the design, analysis, modeling, testing, and performance of turbomachinery. Emphasis is placed on gas-path technologies associated with axial compressors, centrifugal compressors, and turbines. Topics: Aerodynamic design, analysis, and test of compressor and turbine blading; Compressor stall, surge, and operability issues; Heat transfer phenomena and film cooling design, analysis, and testing in turbines; Aeromechanical instabilities; Computational fluid dynamics (CFD) applied to turbomachinery, boundary layer development, measurement techniques, and cavity and leaking flows.