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Experimental investigation of wall thickness and hole shape variation effects on full-coverage film cooling performance for a gas turbine vane

机译：壁厚和孔形变形效应对燃气轮机叶片全覆盖薄膜冷却性能的实验研究

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Weihong Li; Xueying Li; Jing Ren; Hongde Jiang;
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1. Experimental investigation of wall thickness and hole shape variation effects on full-coverage film cooling performance for a gas turbine vane [J] . Li Weihong, Li Xueying, Ren Jing, Applied thermal engineering: Design, processes, equipment, economics . 2018,第期

机译：壁厚和孔形变形变化对燃气轮机叶片全覆盖薄膜冷却性能的实验研究
2. An experimental investigation on cooling characteristics of a vane laminated end-wall with axial-row layout of film-holes [J] . Wang Wei, Pu Jian, Wang Jian-hua, Applied thermal engineering: Design, processes, equipment, economics . 2019,第期

机译：薄膜孔轴排布局叶片层压端壁冷却特性的实验研究
3. 3D Investigation of Film Cooling Effectiveness for Nozzle Vane Platform of High Pressure Turbine with “Meridian Constriction” and Laidback Fan-Shaped Film-Cooling Holes [J] . Russian Aeronautics . 2019,第3期

机译：高压涡轮机带有“经络收缩”和“经络”和悠闲扇形薄膜冷却孔的喷嘴叶片平台薄膜冷却效能研究
4. SYSTEMATIC EXPERIMENTAL AND NUMERICAL INVESTIGATIONS ON THE AEROTHERMODYNAMICS OF A FILM COOLED TURBINE CASCADE WITH VARIATION OF THE COOLING HOLE SHAPE Part I Experimental [C] . Wolfgang Ganzert, Thomas Hildebrandt, Leonhard Fottner ASME TURBO EXPO . 2000

机译：薄膜冷却涡轮机级联的系统实验性和数值研究，其实验研究
5. Experimental Study of Film Cooling and Heat Transfer on a Gas Turbine Vane with Shaped Holes [D] . Elnady, Tarek 2010

机译：异形孔涡轮叶片冷却与传热的实验研究
6. Conjugate Heat Transfer Investigation on Swirl-Film Cooling at the Leading Edge of a Gas Turbine Vane [O] . Haifen Du, Ziyue Mei, Jiayao Zou, 2019

机译：燃气轮机叶片前缘旋流膜冷却的共轭传热研究
7. NUMERICAL INVESTIGATION OF THE EFFECT OF DIELECTRIC BARRIER DISCHARGE ACTUATOR (DBDA) ON FILM COOLING PERFORMANCE DOWNSTREAM A CIRCULAR HOLE SCHEME OVER A GAS TURBINE VANE PRESSURE SIDE [O] . M. Abdelhares, O. Hassan, M. El-Dosoky, 2018

机译：介电阻挡放电致动器（DBDA）对燃气轮机叶片压力侧下游圆孔方案膜冷却性能影响的数值研究
8. Investigations on an Experimental Air-Cooled Turbine Part Ⅲ.—the Effects of Cooling on the Overall Turbine Aerodynamic Performance and Initial Operation at an Inlet Gas Temperature of 140° deg K PartⅣ.—Examination of Sintered Vitallium Air-Cooled Turbine Blades Following 100 Hours' Operation at a Turbine Inlet Mean Gas Temperature of 1400 deg K [R] . N. E. WALDREN, C. J. HART, D. E. FRAY 1960

机译：实验风冷涡轮机的研究Ⅲ。冷却对整体涡轮气动性能和入口气体温度140°K时的初始运行的影响第四部分 - 100小时后烧结的Vitallium空冷涡轮叶片的检查'在涡轮机入口处的操作平均气体温度为1400度K.

Experimental investigation of wall thickness and hole shape variation effects on full-coverage film cooling performance for a gas turbine vane

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