The 3D Computational Investigation of Film Cooling Effectiveness for Turbine Nozzle Vanes with “Meridian Constriction” and Shaped Film-Cooling Holes

Yu. G. Gorelov; K. V. Tyul’kov

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The 3D Computational Investigation of Film Cooling Effectiveness for Turbine Nozzle Vanes with “Meridian Constriction” and Shaped Film-Cooling Holes

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

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Active influence dimension of film cooling along the blade profile is investigated with using the Spalart–Allmaras turbulence model. The cooling effectiveness of vane platforms and vane fillets is studied with the use of perforation holes on the leading edge.

机译：使用Spalart-Allmaras湍流模型研究了沿着叶片轮廓的薄膜冷却的主动影响尺寸。在前缘上使用穿孔孔来研究叶片平台和叶片内圆角的冷却效果。

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来源
《Russian Aeronautics》 |2018年第1期|共7页
作者
Yu. G. Gorelov; K. V. Tyul’kov;
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作者单位

Salyut Gas Turbine Engineering Research and Production Centre;

Salyut Gas Turbine Engineering Research and Production Centre;

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原文格式 PDF
正文语种 eng
中图分类航空;
关键词
rocket engine nozzle; chemical kinetics; mathematical modeling; eigenvalue; Jacobian matrix;

机译：火箭发动机喷嘴;化学动力学;数学建模;特征值;雅各比亚矩阵;

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专利

1. 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
2. Film-Cooling Performance of a Turbine Vane Suction Side: The Showerhead Effect on Film-Cooling Hole Placement for Cylindrical and Fan-Shaped Holes [J] . Hossein Nadali Najafabadi, Matts Karlsson, Mats Kinell, Journal of turbomachinery . 2015,第9期

机译：涡轮叶片吸入侧的薄膜冷却性能：莲蓬头对圆柱孔和扇形孔薄膜冷却孔位置的影响
3. Aerodynamic and Endwall Film-Cooling Investigations of a Gas Turbine Nozzle Guide Vane Applying Temperature-Sensitive Paint [J] . Martin Kunze, Konrad Vogeler, Glenn Brown, Journal of turbomachinery . 2011,第3期

机译：涂有温度敏感涂料的燃气轮机喷嘴导流叶片的空气动力学和端壁薄膜冷却研究
4. FILM-COOLING EFFECTIVENESS FROM SHAPED FILM COOLING HOLES FOR A GAS TURBINE BLADE [C] . Shantanu Mhetras, Je-Chin Han, Ron Rudolph ASME turbo expo . 2008

机译：燃气轮机叶片的异形冷却孔的膜冷却效率
5. A detailed study of fan-shaped film-cooling for a nozzle guide vane for an industrial gas turbine. [D] . Colban, William F., IV. 2005

机译：对用于工业燃气轮机的喷嘴导向叶片的扇形薄膜冷却的详细研究。
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. The Influence of Film-Cooling on the Aerodynamic Performance of a Turbine Nozzle Guide Vane [O] . C. Osnaghi, A. Perdichizzi, M. Savini, 1997

机译：薄膜冷却对涡轮喷嘴导向叶片空气动力学性能的影响

The 3D Computational Investigation of Film Cooling Effectiveness for Turbine Nozzle Vanes with “Meridian Constriction” and Shaped Film-Cooling Holes

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