An Experimental Investigation of Flow Characteristics Downstream of Discrete Film Cooling Holes on Turbine Blade Leading Edge

Abstract:

The gas turbine blade was studied on the condition that the mainstream velocity was 10m/s and the Renolds number based on the chord length of the blade was 160000.The Hot-film anemometer was used to measure the two-dimension speed distribution along the downstream of the film cooling holes on the suction side and the pressure side. The conclusions are as follows: When the blowing ratio of the suction side and the pressure side increasing, the the mainstream and the jet injection mixing center raising. Entrainment flow occurs at the position where the blade surface with great curvature gradient, simultaneously the mixing flow has a wicked adhere to the wall. The velocity gradient of the u direction that on the suction side increase obviously, also the level of the wall adherence is better than the pressure side. With the x/d increasing, the velocity u that on the pressure side gradually become irregularly, also the secondary flow emerged near the wall region where the curvature is great. The blowing ratio on the suction side has a little influence on velocity v than that on the pressure side.

• Periodical: Advanced Materials Research (Volumes 383-390)
• Pages: 5553-5560
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.383-390.5553
• Online since: November 2011
• Authors: Shao Hua Li, Hong Wei Qu, Mei Li Wang, Ting Ting Guo
• Keywords: Blade Curvature, Blowing Ratio, Experiment Investigation, Film Cooling

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