The Effect of Different Clapboards Structure in Turbine Blade Trailing Edge Complex Passages on Heat Transfer Characteristics
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The Effect of Different Clapboards Structure in Turbine Blade Trailing Edge Complex Passages on Heat Transfer Characteristics
Vol. 21, Issue 3, (2006)
作者机构:
北京航空航天大学 能源与动力工程学院 航空发动机气动热力重点实验室,北京,100083
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Published:2006
稿件说明:
移动端阅览
DING Shui-ting, LIU Li-yan, LI Li, et al. The Effect of Different Clapboards Structure in Turbine Blade Trailing Edge Complex Passages on Heat Transfer Characteristics[J]. 2006, 21(3).
DOI:
DING Shui-ting, LIU Li-yan, LI Li, et al. The Effect of Different Clapboards Structure in Turbine Blade Trailing Edge Complex Passages on Heat Transfer Characteristics[J]. 2006, 21(3).DOI:
The Effect of Different Clapboards Structure in Turbine Blade Trailing Edge Complex Passages on Heat Transfer Characteristics
The experiment mainly aimed at to investigate the effect of different aperture in different clapboard structure in the turbine blade trailing edge complex passages on heat transfer and pressure drop characteristics.A thermochromic liquid crystal method was used to measure the detailed heat transfer coefficients on the end wall surfaces.Comparison of end wall heat transfer and pressure drop characteristics was made between two kinds of rectangular clapboards and two kinds of waved clapboard in the turbine blade trailing edge complex passages.It was found that the rectangular clapboard with aperture of 2.5 millimeter produces higher heat transfer with relatively less pressure drop than that of the rectangular clapboard with aperture of 1.8 millimeter;the heat transfer of the waved clapboard with aperture 1.5 millimeter in trough and aperture 2.1 millimeter on ridge was higher than that of the waved clapboard with aperture 2.1 millimeter in trough and aperture 3.0 millimeter on ridge.Comparing the four structures
the two waved clapboards performed the higher endwall-averaged heat transfer and in the meanwhile pay the lower pressure drop penalty than the two rectangular clapboards.
Experimental study on heat transfer in rotor-stator cavity with high-positioned pre-swirl inflow
Experimental investigation on heat transfer in complex internal cooling blade channel with leading-edge
Heat transfer characteristics of axi-symmetrical nozzle and RS nozzle
Heat transfer characteristics of expander cycle thrust chamber
Experimental investigations on the local heat transfer coefficient of rotating single circular impingement in a half-limited space
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XU Guo-qiang
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Related Institution
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics
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College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics