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Investigation of Velocity Profiles for Effusion Cooling of a Combustor Liner

机译：燃烧器衬里的积液冷却速度谱的研究

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Effusion cooling of combustor liners for gas turbine engines is quite challenging and necessary to prevent thermal distress of the combustor liner walls. The flow and thermal patterns in the cooling layer are affected by the closely spaced film-cooling holes. It is important to fully document how the film layer behaves with a full-coverage cooling scheme to gain an understanding into surface cooling phenomena. This paper discusses experimental results from a combustor simulator tested in a low-speed wind tunnel. Engine representative, non-dimensional coolant flows were tested for a full-coverage effusion plate. Laser Doppler velocimetry was used to measure the flow characteristics of the cooling layer. These experiments indicate that the full-coverage film cooling flow has unique and scaleable velocity profiles that result from the closely spaced effusion holes. A parametric study of the cooling flow behavior illustrates the complex nature of the film flow and how it affects cooling performance.
机译：用于燃气涡轮发动机的燃烧器衬里的电流冷却非常具有挑战性，以防止燃烧器衬里壁的热损坏。冷却层中的流动和热图案受到紧密间隔的薄膜冷却孔的影响。完全记录薄膜层的表现如何以完全覆盖的冷却方案的表现，以获得理解表面冷却现象。本文讨论了在低速风洞中测试的燃烧器模拟器的实验结果。发动机代表性，用于全覆盖积液板测试非尺寸冷却剂流。激光多普勒速度测量用于测量冷却层的流动特性。这些实验表明，全覆盖薄膜冷却流具有独特且可扩展的速度曲线，其由紧密间隔的积液孔产生。冷却流动行为的参数研究说明了膜流的复杂性以及它如何影响冷却性能。

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