Temperature Calculation in an Uncooled Low-pressure Stage of a Heavy-duty Gas Turbine Using Conjugate Heat Transfer Analysis
Author:
Affiliation:
1. Engineering and R&D Department, MAPNA Turbine Engineering and Manufacturing Co. (TUGA)
2. Engineering and R&D Department, MAPNA Turbine Blade Engineering and manufacturing Co. (PARTO)
Publisher
Gas Turbine Society of Japan
Subject
Mechanical Engineering
Link
https://www.jstage.jst.go.jp/article/jgpp/9/2/9_11/_pdf
Reference9 articles.
1. Facchini, B., Magi, A., Scotti Del Greco, A., 2004, ”Conjugate Heat Transfer Simulation of A Radially Cooled Gas Turbine Vane,” Proceedings, ASME Turbo Expo 2004, Land, Sea, and Air, GT2004-54213.
2. E., Takehashi, T., Sato, M., Koyama, M., Ninomiya, T., 2005, ”Conceptual Design and Cooling Blade Development of 1700°C Class High-Temperature Gas Turbine,” Journal of Engineer- ing for Gas Turbines and Power, Vol. 127, pp 358-368.
3. Barringer, M. D.,Thole, K. A., Polanka, M. D., 2009, ” Effects of Combustor Exit Profiles on Vane Aerodynamic Loading and Heat Transfer in a High Pressure Turbine,” Journal of Turbomachinery, Vol. 131, pp....
4. Ni, R., Humber, W., Fan, G., Johnson, P., Downs, Jim., Clark, J.P., Koch, P.J., 2011, ”Conjugate Heat Transfer Analysis Of A Film-Cooled Turbine Vane,” Proceedings, ASME Turbo Expo 2011, Vancouver, British Columbia, Canada, GT2011-45920.
5. Ho, K., Urwiller, C., Konan, S., Liu, J., Aguilar, B., 2012, ”Conjugate Heat Transfer Analysis For Gas Turbine Cooled Stator,” Proceedings, ASME Turbo Expo 2012, Copenhagen, Denmark, GT2012-68196.
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