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http://dx.doi.org/10.6108/KSPE.2020.24.1.047

Numerical Analysis on the Effect of Hole Arrangement on the Film Cooling Effectiveness on the Vane Endwall  

Kim, TaeWoo (Department of mechanical Engineering, Yonsei University)
Kim, JeongJu (Department of mechanical Engineering, Yonsei University)
Park, Hee Seung (Department of mechanical Engineering, Yonsei University)
Ju, Won-Gu (Department of mechanical Engineering, Yonsei University)
Im, Ju Hyun (Agency for Defense Development)
Cho, Hyung Hee (Department of mechanical Engineering, Yonsei University)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.24, no.1, 2020 , pp. 47-57 More about this Journal
Abstract
The present study investigates to improve the film cooling performance on the vane endwall. Numerical simulation was conducted to analyze film cooling characteristics on the vane endwall. Six different hole arrangements were designed considering flow characteristics on the endwall. The results showed that the film cooling effectiveness was low on the pressure side and nozzle throat in the base case, because coolant was deflected from the pressure side to the suction side. On the other hand, when the holes were installed near the pressure side, the film cooling effectiveness was enhanced on the pressure side and nozzle throat, because the coolant was less affected by cross flow. Therefore, the film cooling effectiveness increases about 16% compared to the base hole arrangement.
Keywords
Gas Turbine; Endwall; Film Cooling Hole;
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  • Reference
1 Lakshminarayana, Budugur. Fluid dynamics and heat transfer of turbomachinery. John Wiley & Sons, 1995.
2 Friedrichs, S., H.P. Hodson, and W.N. Dawes. "Distribution of film-cooling effectiveness on a turbine endwall measured using the ammonia and diazo technique." ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995.
3 Friedrichs, S., Hodson, H.P., and Dawes, W.N., "The Design of an Improved Endwall Film-Cooling Configuration." ASME. J. Turbomach 121(4): 772-780, October 1999.   DOI
4 Satta, Francesca, and Giovanni Tanda. "Effect of discrete-hole arrangement on film- cooling effectiveness for the endwall of a turbine blade cascade." Applied Thermal Engineering 91, 507-514, 2015.   DOI
5 Jung Shin Park, Jin Young Jeong, Jae Su Kwak, Ki Don Lee, "Film cooling effectiveness for a first-stage cooled vane and endwall of gas turbine with fanshaped holes", KSME, 309-310, 2016
6 Sehjin Park, Ho-Seong Sohn, Seon Ho Kim, Jeong Ju Kim, Taehyun Kim, Hyung Hee Cho, "Effect of Inclined Holes of blade platform on Endwall Film Cooling Effcetivess", KSME, 11-12, 2018
7 Ho-Seong Sohn, Sehjin Park, Seok Min Choi, Minjae Park, Seungyun Kim, Hyung Hee Cho, "Flow Characteristics in Endwall with Front Blade Wake by DES method", KSME, 1420-1422, 2017.
8 Choi, S. M., Park, J. S., Chung, H., Park, S., & Cho, H. H. "Upstream wake effect on flow and heat transfer characteristics at an endwall of first-stage blade of a gas turbine." Experimental Thermal and Fluid Science, 86, 23-36, 2017.   DOI
9 Burd, Steven W., and Terrence W. Simon. "Effects of Slot Bleed Injection Over a Contoured Endwall on Nozzle Guide Vane Cooling Performance: Part I-Flow Field Measurements." ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000.
10 Thole, Karen A., and Daniel G. Knost. "Heat transfer and film-cooling for the endwall of a first stage turbine vane." International Journal of Heat and Mass Transfer 48.25-26, 5255-5269, 2005.   DOI
11 Chung, H., Hong, C.W., Kim, S.H., Cho, H.H., and Moon, H.K.. Heat transfer measurement near endwall region of first stage gas turbine nozzle having platform misalignment at combustor-turbine interface. International Communications in Heat and Mass Transfer, 78, 101-111, 2016.   DOI