NDLI: Experimental Investigation on the Leading Edge Film Cooling of Cylindrical and Laid-Back Holes With Different Hole Pitches

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Liu, Cun-Liang Zhu, Hui-Ren Zhang, Zong-Wei
Copyright Year	2012
Abstract	Experimental investigation has been performed to study the film cooling performance of cylindrical and laid-back film holes on the turbine blade leading edge. Four test models are measured for four blowing ratios to investigate the influence of film hole shape and hole pitch on the film cooling performance. Film cooling effectiveness and heat transfer coefficient are obtained using transient heat transfer measurement technique with double thermochromic liquid crystals. As the blowing ratio increases, the trajectory of jets deviates to the spanwise direction and lifts off gradually. However, more area can benefit from the film protection under large blowing ratio, while the heat transfer coefficient is also higher. The basic distribution features of heat transfer coefficient are similar for all the four models. Heat transfer coefficient in the region where the jet core flows through is relatively lower, while heat transfer coefficient in the jet edge region is relatively higher. For the models with small hole pitch, the laid-back holes only give better film coverage performance than the cylindrical holes under large blowing ratio. For the models with large hole pitch, the advantage of laid-back holes in film cooling effectiveness is more obvious in the upstream region relative to the cylindrical holes. For the cylindrical hole model and the laid-back hole model with the same hole pitch, the laterally averaged heat transfer coefficients are nearly the same with each other under the same blowing ratios. Compared with the models with large hole pitch, the laterally averaged film cooling effectiveness and the laterally averaged heat transfer coefficient are larger for the models with small hole pitch because of larger proportion of film covering area and strong heat transfer region.
Sponsorship	International Gas Turbine Institute
Starting Page	1139
Ending Page	1150
Page Count	12
File Format	PDF
ISBN	9780791844700
DOI	10.1115/GT2012-68027
Volume Number	Volume 4: Heat Transfer, Parts A and B
Conference Proceedings	ASME Turbo Expo 2012: Turbine Technical Conference and Exposition
Language	English
Publisher Date	2012-06-11
Publisher Place	Copenhagen, Denmark
Access Restriction	Subscribed
Subject Keyword	Turbine blades Trajectories (physics) Jets Transient heat transfer Film cooling Shapes Heat transfer coefficients Flow (dynamics) Liquid crystals Heat transfer
Content Type	Text
Resource Type	Article

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