CFD Investigation of the Flow of Trailing Edge Cooling Slots

Yuewen Jiang, Niharika Gurram, E. Romero, P. Ireland, L. Mare
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Abstract

Slot film cooling is a popular choice for trailing edge cooling in high pressure (HP) turbine blades because it can provide more uniform film coverage compared to discrete film cooling holes. The slot geometry consists of a cut back in the blade pressure side connected through rectangular openings to the internal coolant feed passage. The numerical simulation of this kind of film cooling flows is challenging due to the presence of flow interactions like step flow separation, coolant-mainstream mixing and heat transfer. The geometry under consideration is a cutback surface at the trailing edge of a constant cross-section aerofoil. The cutback surface is divided into three sections separated by narrow lands. The experiments are conducted in a high speed cascade in Oxford Osney Thermo-Fluids Laboratory at Reynolds and Mach number distributions representative of engine conditions. The capability of CFD methods to capture these flow phenomena is investigated in this paper. The isentropic Mach number and film effectiveness are compared between CFD and pressure sensitive paint (PSP) data. Compared to steady k–ω SST method, Scale Adaptive Simulation (SAS) can agree better with the measurement. Furthermore, the profiles of kinetic energy, production and shear stress obtained by the steady and SAS methods are compared to identify the main source of inaccuracy in RANS simulations. The SAS method is better to capture the unsteady coolant-hot gas mixing and vortex shedding at the slot lip. The cross flow is found to affect the film significantly as it triggers flow separation near the lands and reduces the effectiveness. The film is non-symmetric with respect to the half-span plane and different flow features are present in each slot. The effect of mass flow ratio (MFR) on flow pattern and coolant distribution is also studied. The profiles of velocity, kinetic energy and production of turbulent energy are compared among the slots in detail. The MFR not only affects the magnitude but also changes the sign of production.
后缘冷却槽流动的CFD研究
槽膜冷却是高压(HP)涡轮叶片尾缘冷却的流行选择,因为与离散膜冷却孔相比,它可以提供更均匀的膜覆盖。槽的几何形状由叶片压力侧的一个切口组成,通过矩形开口连接到内部冷却剂进料通道。由于存在阶梯流分离、冷却液主流混合和换热等流动相互作用,这类气膜冷却流动的数值模拟具有挑战性。所考虑的几何形状是在一个恒定截面翼型的后缘切割表面。切割表面被狭窄的土地分成三个部分。实验在牛津奥斯尼热流体实验室的高速叶栅中进行,雷诺数和代表发动机条件的马赫数分布。本文研究了CFD方法捕捉这些流动现象的能力。比较了CFD和压敏涂料(PSP)数据的等熵马赫数和膜效。与稳态k ω海表温度法相比,尺度自适应模拟(SAS)能更好地与实测结果吻合。此外,通过比较稳态和SAS方法得到的动能、生产和剪应力分布,找出了RANS模拟不准确的主要原因。SAS方法能较好地捕捉槽唇处的非定常冷热气体混合和旋涡脱落。交叉流对膜的影响很大,因为它触发了陆地附近的流动分离,降低了膜的有效性。膜相对于半跨平面是非对称的,并且在每个狭缝中存在不同的流动特征。研究了质量流量比(MFR)对流型和冷却剂分布的影响。详细比较了各槽的速度分布、动能分布和湍流能产生情况。MFR不仅影响震级,而且改变生产符号。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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