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首页> 外文期刊>International Journal of Heat and Fluid Flow >Detached eddy simulation of blade trailing-edge cutback cooling performance at various ejection slot angles
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Detached eddy simulation of blade trailing-edge cutback cooling performance at various ejection slot angles

机译：叶片后缘切角冷却性能在不同喷射槽角度的分离涡流模拟

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摘要

Detached eddy simulation (DES) has been carded out to study a three-dimensional trailing-edge (TE) cutback turbine blade model with five rows of staggered circular pin-fin arrays inside the cooling passage, in order to evaluate the cooling performance in relation to coolant ejection slot angle. Simulations were performed by adopting a shear-stress transport k-omega turbulence model, and the effects of three different ejection slot angles 5 degrees, 10 degrees and 15 degrees were investigated in terms of the characteristics of adiabatic film-cooling effectiveness, coefficient of discharge, and vortex shedding frequencies, respectively. The results obtained have shown that the TE cutback blade cooling with a 5 degrees coolant ejection slot angle produced a better heat transfer coefficient than the other two ejection slot angles tested. The distributions of adiabatic film-cooling effectiveness along the cutback walls were found to be sensitive to the coolant ejection slot angle, e.g. the increase of ejection slot angle to 15 degrees yielded near unity of cooling effectiveness along the entire breakout walls, whereas the decrease of ejection slot angle caused a drastic decay of cooling effectiveness after the maximum effectiveness has been reached. Of the three angles studied, a TE cutback blade model with a 15 degrees ejection slot angle produced an optimum film-cooling effectiveness. In the breakout region, vortex shedding was observed along the shear layer between the hot gas and the coolant airflow. The shedding frequencies were evaluated to be 2.93, 2.21, and 2.18 kHz for the ejection slot angles of 5 degrees, 10 degrees and 15 degrees, respectively. The findings from this study could be useful to improve existing TE cutback turbine blade design to achieve optimum film-cooling performance.
机译：分离涡流仿真（DES）已被研究出来，以研究三维后缘（TE）缩减涡轮叶片模型，该模型在冷却通道内具有五排交错的圆形销-翅片阵列，以评估相关的冷却性能到冷却液喷射槽角度。采用剪切力传递k-ω湍流模型进行了模拟，并根据绝热膜冷却效率，放电系数等特性研究了5种，5度，10度和15度这三种不同的喷射槽角的影响。 ，和涡旋脱落频率。所获得的结果表明，以5度的冷却剂喷射缝隙角进行TE切刀冷却时，比其他两个测试的喷射缝隙角具有更好的传热系数。沿着绝热壁的绝热膜冷却效率的分布被发现对冷却剂的喷射槽角敏感。喷射缝隙角增加到15度可在整个突围壁上产生几乎相同的冷却效果，而喷射缝隙角的减小导致达到最大效率后冷却效率急剧下降。在研究的三个角度中，具有15度喷射槽角度的TE切边刀片模型产生了最佳的薄膜冷却效果。在突破区域中，沿着热气和冷却剂气流之间的剪切层观察到涡旋脱落。对于5度，10度和15度的喷射缝隙角，脱落频率被评估为分别为2.93、2.21和2.18kHz。这项研究的结果可能有助于改进现有的TE切回式涡轮机叶片设计，以实现最佳的薄膜冷却性能。

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