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首页> 外文期刊>International Journal of Heat and Mass Transfer >Investigation on aerothermal performance of a rib-slot scheme on the multi-cavity tip of a gas turbine blade
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Investigation on aerothermal performance of a rib-slot scheme on the multi-cavity tip of a gas turbine blade

机译：燃气轮机叶片多腔尖端肋槽方案的空气性能研究

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摘要

A rib-slot blade tip is proposed to improve the film cooling performance of an unshrouded gas turbine blade tip in the current paper. The rib-slot blade tip is formed by arranging the slot into ribs of the multi-cavity squealer tip. The film cooling performance of the rib-slot blade tip is experimentally studied by using the Pressure Sensitive Paint (PSP) technique in transonic flows. The inlet Reynolds number is 370,000 based on the blade axial chord length. The exit Mach numbers is 1.05. Effects of density ratios and mass flow ratios on the film cooling characteristics are investigated, and the experiments are carried out at four mass flow ratios and three density ratios. The numerical simulation is used to predict the flow field and analyze the film cooling characteristics. The multi-cavity squealer tip consists of cavity 1-4. The results indicate that at the high mass flow ratio, the film can cover the whole squealer tip bottom surface downstream of rib-slots at three density ratios. Increasing the mass flow ratio has a slight effect on the film cooling effectiveness (η) near the tip pressure side upstream of the cavity 3. There is a low η region near the suction side of the cavity 2 and cavity 3 at low mass flow ratios, particularly for the high-density jet due to the leakage flow reattachment. A low η region is formed in the middle region of the cavity 4 at the low mass flow ratio. The blade tip with the jet shrinks the high aerodynamic loss coefficient region formed by the counter vortex, whereas, it expands the high aerodynamic loss coefficient region formed by the leakage vortex in the blade span-wise direction. The pitch-wise averaged aerodynamic loss coefficient of the blade tip with the jet is lower than that of the no film case near the shroud.
机译：提出了一种肋槽刀片尖端，以改善当前纸张中的未体验的燃气涡轮叶片尖端的薄膜冷却性能。通过将槽布置成多腔耳子尖端的肋来形成肋槽叶片尖端。通过使用跨音速流动的压敏涂料（PSP）技术通过使用压敏涂料（PSP）技术进行实验研究了肋槽叶片尖端的膜冷却性能。入口雷诺数为370,000，基于叶片轴向弦长。出口马赫号为1.05。研究了密度比和质量流量比对薄膜冷却特性的影响，并在四种质量流量比和三个密度比例下进行实验。数值模拟用于预测流场并分析薄膜冷却特性。多腔耳声尖端由腔1-4组成。结果表明，在高质量流量比下，薄膜可以在三个密度比下覆盖肋槽下游的整个静脉尖端底表面。增加质量流量对腔3上游的尖端压力侧附近的膜冷却效果（η）具有轻微影响。在腔2的吸入侧附近存在低质量流量比的腔3附近的低η区域，特别是由于泄漏流动重新附着的高密度射流。低质量流量比在腔4的中间区域中形成低η区。具有喷射器的叶片尖端收缩了由计数器涡流形成的高空气动力学损耗系数区域，而它扩展了由叶片跨度方向上的泄漏涡流形成的高空气动力损耗系数区域。具有射流的叶片尖端的俯仰平均空气动力学损耗系数低于护罩附近的薄膜壳的叶片尖端。

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