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Study of Film Cooling Effectiveness on a Flat Plate using CFD

机译：使用CFD研究平板上的薄膜冷却效果

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Film cooling is one effective way of cooling gas turbine hot internal components, which prevents the surface of base metal to get over-heated and hazardous effect of loosing its mechanical strength and operating life. It is forming thin layer of cool gases, which avoids direct contact between hot gases and surface. This paper presents the study of film cooling effectiveness with injection of air through a discrete hole into a turbulent boundary layer of air on a flat plate. The study includes effect of various blowing ratio with selected angle of coolant jet injection. A mesh on the flat plate was developed and tested for grid generation. CFD analysis was carried out using CFD solver FLUENT-6.3. In first section of the study, the CFD code used in this study has been validated with the experimental results obtained by Goldstein et al (1968). The effect of different turbulent models namely k-ε standard, k-ε RNG and k-ε Realizable has been studied and it is found that k-ε Realizable model gives good approximation and matching with experimental results of Goldstein et al (1968). In second section, simulations were carried out with k-ε Realizable turbulent model for various angles of jet protrusion namely 25°, 35° and 45°, blowing ratio is taken as 0.5. Among jet injection angles 25°, 35° and 45°, 25° is giving high cooling effectiveness. Further, simulations were carried out at 1 and 1.5 blowing ratios of coolant jet for 25° angle of jet protrusion. It shows that cooling effectiveness is decreases with increase in blowing ratio. It is also found that blowing ratio of 0.5 is giving good cooling effectiveness for all jet protrusion angles 25°, 35° and 45°.
机译：薄膜冷却是冷却燃气涡轮机热内部部件的一种有效方式，这防止了基础金属表面过度加热和危险效果，可失去其机械强度和经营寿命。它是形成薄薄的冷气体层，避免了热气体和表面之间的直接接触。本文介绍了通过离散孔注入空气中的薄膜冷却效能的研究进入平板上的湍流边界层。该研究包括与所选冷却剂喷射注射角度的各种吹吹比的影响。平板上的网格开发并测试了网格生成。使用CFD Solver Fluent-6.3进行CFD分析。在研究的第一部分中，本研究中使用的CFD代码已被验证，并通过Goldstein等（1968）获得的实验结果。已经研究了不同湍流模型的效果，即K-ε标准，K-εrng和k-ε可实现的，发现K-ε可实现的模型提供良好的近似和与Goldstein等人（1968）的实验结果匹配。在第二部分中，用K-ε可实现的湍流模型进行模拟，用于各种喷射突起的各个角度，即25°，35°和45°，吹出比例为0.5。喷射注射角25°，35°和45°，25°呈高冷却效果。此外，在射流射流的1和1.5吹气比的1和1.5的吹气比的射流突起中进行模拟。它表明，随着吹出比率的增加，冷却效果降低。还发现，对于所有喷射突起角度为25°，35°和45°，吹出比率为0.5为良好的冷却效果。

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