Film Cooling from Two Staggered Rows of Compound Angle Holes at High Blowing Ratios

International Journal of Rotating Machinery

Phillip M. Ligrani¹  Joon Sik Lee² 

[1] Convective Heat Transfer Laboratory, Department of Mechanical Engineering, University of Utah, Salt Lake City 84112, Utah, USA;Turbo and Power Machinery Research Center, Department of Mechanical Engineering, Seoul National University, Seoul 151-742, Korea;

关键词: Gas turbines;    film cooling;    compound angle holes;    turbine blades;    film effectiveness.;   

DOI  :  10.1155/S1023621X96000073

来源: DOAJ

【 摘 要 】

Experimental results are presented which describe the development and structure of flow downstream of two staggered rows of film-cooling holes with compound angle orientations at high blowing ratios. These film cooling configurations are important because they are frequently employed on the first stage of rotating blades of operating gas turbine engines. With this configuration, holes are spaced 3d apart in the spanwise direction, with inclination angles of 24 degrees, and angles of orientation of 50.5 degrees. Blowing ratios range from 0.5 to 4.0 and the ratio of injectant to freestream density is near 1.0. Results show that spanwise averaged adiabatic effectiveness, spanwise-averaged iso-energetic Stanton number ratios, surveys of streamwise mean velocity, and surveys of injectant distributions change by important amounts as the blowing ratio increases. This is due to injectant lift-off from the test surface just downstream of the holes which becomes more pronounced as blowing ratio increases.

【 授权许可】

Unknown