C222 ガスタービンの超高温化実現のためのタービン翼複合冷却技術に関する研究(ガスタービンその他,OS7 高温・高効率発電)

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This paper deals with detailed experimental studies, followed by the comparison with the corresponding numerical predictions, on integrated cooling technologies for turbine sections in ultra-high temperature gas turbines. Two types of the cooling technologies are investigated: one is an impingement cooling combined with pin-fin cooling and film cooling, and the other is film cooling applied to blade leading edge section. Large-scale acrylic-resin models are constructed for the measurement of heat transfer characteristics inside and outside of the those two cooling systems. A transient method based on thermochromic liquid crystal (TLC) is used to obtained film effectiveness and film-affected heat transfer coefficient simultaneously, while a comb-like multi-sensor thermoprobe is also applied to the film effective measurement on the test model surface and around the cooling holes. CFD (Computational Fluid Dynamics) analyses using RANS (Reynolds-Averaged Navier-Stokes Equations) and DES (Detached Eddy Simulation) methods are carried out in order to examine the capability of these methods to make a accurate prediction of the heat transfer characteristics of film-cooled flow field.
一般社団法人日本機械学会の論文
2009-06-28