Film Cooling Characteristic on Trailing Edge Cutback of Gas Turbine Airfoils with Dimple/Protrusion Structure

doi:10.13675/j.cnki.tjjs.190233

Journal of Propulsion Technology ›› 2020, Vol. 41 ›› Issue (2): 372-381.DOI: 10.13675/j.cnki.tjjs.190233

• Combustion and Heat Transfer • Previous Articles Next Articles

Film Cooling Characteristic on Trailing Edge Cutback of Gas Turbine Airfoils with Dimple/Protrusion Structure

College of Energy Resource and Mechanical Engineering，Northeast Electric Power University， Jilin 132012， China

Published:2021-08-15

涡轮叶片尾缘凹坑 /凸起结构气膜冷却特性研究

张玲¹,史梦颖¹,原峥¹,洪文鹏¹

东北电力大学能源与动力工程学院，吉林吉林 132012

基金资助:
国家自然科学基金（51576036）。

Abstract

Abstract: In order to investigate the effects of the dimple and protrusion structures of suction surface on film cooling characteristics of turbine blade trailing edge, the cooling performance and flow mechanism of turbine blade trailing edge were analyzed in detail by numerical simulation method when the blowing ratio M=1.1 ( Re=2.5×10 ⁵). The results show that，compared with the original one， the dimple and protrusion structure on trailing edge can improve the film cooling efficiency in the region of X/ H > 6 （the split width of H is 4.8mm）downstream of the split outlet , while have little effect on the film cooling efficiency in the region of X/H< 6 downstream. Along the direction of flow, these three kinds of trailing edge structures will produce a process from two-dimensional spread vortices to hairpin vortices, then to flow vortices. By restraining fluid disturbance and changing the fluid flow, the dimple and protrusion structures can improve the film cooling efficiency at the far downstream of the split outlet.

Key words: Turbine;Blade;Film cooling;Blowing ratio;Numerical simulation;Dimple-protrusion structure

摘要： 为探究吸力面凹坑和凸起结构对涡轮叶片尾缘气膜冷却特性的影响，在吹风比 M=1.1时（雷诺数 Re=2.5×10 ⁵），采用数值模拟方法，通过在叶片尾缘吸力面上加入凹坑或凸起，对涡轮叶片尾缘的冷却性能和流动机理进行了详细分析。结果表明：与原始结构相比，叶片尾缘凹坑和凸起结构提高了劈缝出口下游远距离端 X/H>6（ H为劈缝宽度，为4.8mm）区域气膜冷却效率，对下游的 X/H<6区域气膜冷却效率影响较小；三种叶片尾缘结构，沿着流向方向会产生由二维展向涡到发卡涡，再到流向涡的变化过程，凹坑和凸起结构通过抑制流体的扰动，改变流体流动情况，提高了劈缝出口下游远距离端气膜冷却效率。

关键词: 涡轮;叶片;气膜冷却;吹风比;数值模拟;凹坑-凸起结构

ZHANG Ling¹,SHI Meng-ying¹,YUAN Zheng¹,HONG Wen-peng¹. Film Cooling Characteristic on Trailing Edge Cutback of Gas Turbine Airfoils with Dimple/Protrusion Structure[J]. Journal of Propulsion Technology, 2020, 41(2): 372-381.

张玲,史梦颖,原峥,洪文鹏. 涡轮叶片尾缘凹坑 /凸起结构气膜冷却特性研究[J]. 推进技术, 2020, 41(2): 372-381.

References

[1] Wieghardt K . Hot-Air Discharge for Deicing[M]. Wright Field： Air Materiel Command， 1946： 1- 44.
[2] Martini P ， Schulz A ， Bauer H J . Film Cooling Effectiveness and Heat Transfer on the Trailing Edge Cutback of Gas Turbine Airfoils with Various Internal Cooling Designs[J]. Journal of Turbomachinery， 2005， 128( 1)： 87- 96.
[3] 孙瑞嘉，杨卫华，贺宜红，等 . 不同叶片尾缘结构对流换热特性实验[J]. 推进技术， 2011， 32( 4)： 485- 490.
[4] 朱惠人，原和朋，周志强，等 . 几何结构对后台阶缝隙气膜冷却效率的影响[J]. 推进技术， 2006， 27( 4)： 312- 315.
[5] Schneider H ， Terzi D V ， Bauer H J . Turbulent Heat Transfer and Large Coherent Structures in Trailing-Edge Cutback Film Cooling[J]. Flow Turbulence and Combustion， 2012， 88( 1-2)： 101- 120.
[6] Effendy M ， Yao Y ， Yao J ， et al . Predicting Film Cooling Performance of Trailing-Edge Cutback Turbine Blades by Detached-Eddy Simulation[C]. National Harbor： Aerospace Sciences Meeting， 2013.
[7] 贾静，王曦娟，王凯 . 涡轮叶片尾缘扰流柱对换热效果的影响[J]. 汽轮机技术， 2008， 50( 3)： 220- 222.
[8] Cheng L J ， Xu W J ， Zhu H R ， et al . Investigation of Heat Transfer and Pressure Field of Jet Impingement of the Side of a Dimpled Surface[C]. Charlotte： Turbomachinery Technical Conference and Exposition， 2017.
[9] Guo Z Q ， Zheng M ， Liu Y ， et al . Investigations of Single Jet Impinging on Plates with Circular Dimples[C]. Charlotte： Turbomachinery Technical Conference and Exposition， 2017.
[10] Shen Z Y ， Jing Q ， Xie Y H . Thermal Performance of Miniscale Heat Sink with Jet Impingement and Dimple/Protrusion Structure[J]. Journal of Heat Transfer， 2017， 139( 5)： 1- 7.
[11] Choi E Y ， Choi Y D ， Lee W S ， et al . Heat Transfer Augmentation Using a Rib-Dimple Compound Cooling Technique[J]. Applied Thermal Engineering， 2013， 51( 1-2)： 435- 441.
[12] Zhou W W ， Hu H ， Rao Y ， et al . An Experimental Investigation on the Flow Characteristics over[C]. Chicago： APS Division of Fluid Dynamics Meeting， 2014.
[13] Shen Z ， Qu H ， Zhang D ， et al . Effect of Bleed Hole on Flow and Heat Transfer Performance of U-Shaped Channel with Dimple Structure[J]. International Journal of Heat and Mass Transfer， 2013， 66( 11)： 10- 22.
[14] Xie Y ， Shi D ， Shen Z . Experimental and Numerical Investigation of Heat Transfer and Friction Performance for Turbine Blade Tip Cap with Combined Pin-Fin-Dimple/Protrusion Structure[J]. International Journal of Heat and Mass Transfer， 2017， 104： 1120- 1134.
[15] Luo L ， Wang C ， Wang L ， et al . Heat Transfer and Friction Factor in a Dimple-Pin Fin Wedge Duct with Various Dimple Depth and Converging Angle[J]. International Journal of Numerical Methods for Heat and Fluid Flow， 2016， 26( 6)： 1954- 1974.
[16] Rao Y ， Wan C Y ， Xie Y H . An Experimental and Numerical Study of Flow and Heat Transfer in Channels with Pin Fin-Dimple Combined Arrays of Different Configurations[J]. Journal of Heat Transfer， 2012， 134( 12)： 1- 11.
[17] Meena M G ， Anandakrishnan A ， Kavumcheril M A ， et al . Numerical Study on Heat Transfer and Fluid Flow in Pin Fin-Dimple Channels with Fillet on Dimple[C]. New Delhi： ASME Gas Turbines and Power： Gas Turbine India Conference， 2014.
[18] Martini P ， Schulz A ， Bauer H J ， et al . Detached Eddy Simulation of Film Cooling Performance on the Trailing Edge Cutback of Gas Turbine Airfoils[J]. Journal of Turbomachinery， 2005， 127( 2)： 292- 299.
[19] Schulz A ， Martini P . Experimental and Numerical Investigation of Trailing Edge Film Cooling by Circular Coolant Wall Jets Ejected from a Slot with Internal Rib Arrays (2003-GT-38157)[J]. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy， 2003， 217： 393- 401.
[20] Effendy M ， Yao Y F ， Yao J ， et al . DES Study of Blade Trailing Edge Cutback Cooling Performance with Various Lip Thicknesses[J]. Applied Thermal Engineering， 2016， 99： 434- 445.

Film Cooling Characteristic on Trailing Edge Cutback of Gas Turbine Airfoils with Dimple/Protrusion Structure

涡轮叶片尾缘凹坑 /凸起结构气膜冷却特性研究

PDF

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 0

Recommended Articles

Metrics

Comments