3D Investigations of the High Pressure Turbine Vane Platform Convection Cooling and Convection-Film Cooling

Yu. G. Gorelov; V. V. Anan’ev

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3D Investigations of the High Pressure Turbine Vane Platform Convection Cooling and Convection-Film Cooling

机译：高压涡轮叶片平台对流冷却和对流膜冷却的3D研究

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摘要

3D ANSYS CFX conjugate calculation was carried out to compare cooling effectiveness of the high pressure turbine vane platforms with the film cooling and the convection-film cooling.

机译：进行3D ANSYS CFX共轭计算，以比较高压涡轮叶片平台与薄膜冷却和对流膜冷却的冷却效能。

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来源
《Russian Aeronautics》 |2018年第3期|共8页
作者
Yu. G. Gorelov; V. V. Anan’ev;
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作者单位

Salyut Gas Turbine Engineering Research and Production Center;

Salyut Gas Turbine Engineering Research and Production Center;

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原文格式 PDF
正文语种 eng
中图分类航空;
关键词
vane platform; cooling effectiveness; set of nozzles; high pressure turbine; gas turbine engine;

机译：叶片平台;冷却效果;套喷嘴;高压涡轮机;燃气轮机发动机;

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专利

1. 3D Investigations of the High Pressure Turbine Vane Platform Convection Cooling and Convection-Film Cooling [J] . Yu. G. Gorelov, V. V. Anan’ev Russian Aeronautics . 2018,第3期

机译：高压涡轮叶片平台对流冷却和对流膜冷却的3D研究
2. The 3D Computational Investigation of Film Cooling Effectiveness for Turbine Nozzle Vanes with “Meridian Constriction” and Shaped Film-Cooling Holes [J] . Yu. G. Gorelov, K. V. Tyul’kov Russian Aeronautics . 2018,第1期

机译：涡轮喷嘴叶片薄膜冷却效能的3D计算研究，“经络收缩”和成型薄膜冷却孔
3. Heat Transfer for the Film-Cooled Vane of a 1-1/2 Stage High-Pressure Transonic Turbine-Part Ⅱ: Effect of Cooling Variation on the Vane Airfoil and Inner End Wall [J] . Harika S. Kahveci, Charles W. Haldeman, Randall M. Mathison, Journal of turbomachinery . 2013,第2期

机译：1-1 / 2级高压跨音速涡轮的薄膜冷却叶片的传热-第二部分：冷却变化对叶片翼型和内端壁的影响
4. NUMERICAL 3-D CONJUGATE FLOW AND HEAT TRANSFER INVESTIGATION OF A TRANSONIC CONVECTION-COOLED THERMAL BARRIER COATED TURBINE GUIDE VANE WITH REDUCED COOLING FLUID MASS FLOW [C] . Dieter E. Bohn, Christian Tuemmers Heat Transfer . 2003

机译：降低了冷却液流的超音速对流冷却式壁垒透平涡轮导流叶片的3维共轭流动和传热研究
5. Experimental Investigation of Particulate Deposition on a Simulated Film-Cooled Turbine Vane Pressure Surface in a High Pressure Combustion Facility. [D] . Murphy, Robert G. 2012

机译：高压燃烧设备中模拟膜冷式涡轮叶片压力表面上颗粒沉积的实验研究。
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. PRESSURE-LOSS AND FLOW COEFFICIENTS INSIDE A CHORDWISE-FINNED, IMPINGEMENT, CONVECTION, AND FILM AIR-COOLED TURBINE VANE [R] . Steven A. Hippensteele 1974

机译：压力，冲击，对流和薄膜空气冷却涡轮叶片内的压力损失和流量系数

3D Investigations of the High Pressure Turbine Vane Platform Convection Cooling and Convection-Film Cooling

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