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The effect of the density ratio of injectant and main stream on film cooling effectiveness on a gas turbine blade.

机译：注射剂和主流密度比对燃气轮机叶片薄膜冷却效果的影响。

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Shinzo KIKKAWA; Keiichi OZAKI;
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年度 1987
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1. Effect of main stream turbulence on the film cooling effectiveness of a circular and a fan-shaped film cooling hole [J] . Kenichiro TAKEISHI, Yutaka ODA, Shohei MORI, Mechanical Engineering Journal . 2020,第4期

机译：主流湍流对圆形和扇形薄膜冷却孔膜冷却效果的影响
2. Trailing Edge Film Cooling of Gas Turbine Airfoils - Effects of Ejection Lip Geometry on Film Cooling Effectiveness and Heat Transfer [J] . TIM HORBACH, ACHMED SCHULZ, HANS-JOERG BAUER Heat Transfer Research . 2010,第8期

机译：燃气轮机机翼的后缘膜冷却-喷射唇几何形状对膜冷却效率和传热的影响
3. Film Cooling on Highly Loaded Blades With Main Flow Separation-Part Ⅱ: Overall Film Cooling Effectiveness [J] . Reinaldo A. Gomes, Reinhard Niehuis Journal of turbomachinery . 2013,第1期

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4. EXPERIMENTAL AND NUMERICAL INVESTIGATION OF EFFECT OF BLOWING RATIO ON FILM COOLING EFFECTIVENESS AND HEAT TRANSFER COEFFICIENT OVER A GAS TURBINE BLADE LEADING EDGE FILM COOLING CONFIGURATIONS [C] . Giridhara Babu Yepuri, Gururaj Lalgi, Ashok Babu Talanki Puttarangasetty, ASME gas turbine India conference . 2014

机译：吹气比对燃气轮机前缘膜冷却结构的膜冷却效率和传热系数的影响的实验和数值研究
5. Experimental Investigation of Advanced Film Cooling Schemes for a Gas Turbine Blade. [D] . Ghorab, Mohamed Gaber. 2010

机译：燃气轮机叶片高级冷却方案的实验研究。
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. Experimental and Numerical Investigation of Effect of Blowing Ratio on Film Cooling Effectiveness and Heat Transfer Coefficient over a Gas Turbine Blade Leading Edge Film Cooling Configurations [O] . Giridhar Babu Y, Gururaj L, Ashok Babu TP, 2013

机译：吹气比对燃气轮机叶片前缘薄膜冷却结构中薄膜冷却效率和传热系数影响的实验和数值研究
8. Heat Transfer Near the Entrance to a Film Cooling Hole in a Gas Turbine Blade. [R] . Byerley, A. R. 1989

机译：燃气轮机叶片薄膜冷却孔入口附近的传热。

The effect of the density ratio of injectant and main stream on film cooling effectiveness on a gas turbine blade.

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