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首页> 外文会议>ASME international conference on nanochannels, microchannels and minichannels >INFLUENCE OF THE GROOVE-PATTERNED COOLING TUBE ON THE FILM COOLING PERFORMANCE OF GAS TURBINE
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INFLUENCE OF THE GROOVE-PATTERNED COOLING TUBE ON THE FILM COOLING PERFORMANCE OF GAS TURBINE

机译：沟槽型冷却管对燃气轮机膜冷却性能的影响

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The gas turbine performance significantly depends on the temperature of working fluid. In order to improve the efficiency of gas turbine, it is required to increase turbine inlet temperature. However, the working fluid in high temperature conditions causes thermal stress which could damage turbine blades. One of the methods to require turbine blades by controlling the temperature of working fluid is a film-cooling method. In this study, cooling tubes with various aspect ratios of groove length (L/L_t) with groove diameter of d=1.2 mm were considered to enhance the film cooling efficiency. In addition, effects of blowing ratios (M) and diffuser angles (δ) of the cooling tube were considered. Numerical investigations were conducted using ANSYS ver. 17.1, and film cooling efficiencies of each case were obtained. Especially, the case with groove length aspect ratio of L/L_t=0.4 at blowing ratio M =1.4 and diffuser angle δ=3.5° showed the highest cooling efficiency of 18% among all model cases.
机译：燃气轮机的性能在很大程度上取决于工作流体的温度。为了提高燃气轮机的效率，需要提高燃气轮机的入口温度。但是，高温条件下的工作流体会引起热应力，从而可能损坏涡轮机叶片。通过控制工作流体的温度来需要涡轮叶片的方法之一是膜冷却方法。在这项研究中，考虑使用具有d = 1.2 mm凹槽直径的凹槽长度（L / L_t）的各种纵横比的冷却管来提高薄膜冷却效率。另外，考虑了冷却管的吹风比（M）和扩散角（δ）的影响。数值研究是使用ANSYS ver。按照图17.1，得到每种情况的薄膜冷却效率。特别是，在所有模型情况下，在吹风比M = 1.4且凹槽角δ= 3.5°的情况下，槽长纵横比为L / L_t = 0.4的情况显示出最高的冷却效率，为18％。

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