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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.3 pt.A; 20050606-09; Reno-Tahoe,NV(US) >Investigation of Velocity Profiles for Effusion Cooling of a Combustor Liner
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Investigation of Velocity Profiles for Effusion Cooling of a Combustor Liner

机译：燃烧室衬里喷流冷却速度分布的研究

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摘要

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：燃气涡轮发动机的燃烧器衬套的喷射冷却是非常有挑战性的，并且对于防止燃烧器衬套壁的热损伤是必要的。冷却层中的流动和热模式会受到紧密间隔的薄膜冷却孔的影响。重要的是，要充分记录薄膜层在全覆盖冷却方案下的行为，以了解表面冷却现象。本文讨论了在低速风洞中测试的燃烧室模拟器的实验结果。对发动机代表性的无量纲冷却液流量进行了全覆盖积水板测试。激光多普勒测速仪用于测量冷却层的流动特性。这些实验表明，全覆盖薄膜的冷却流具有独特且可缩放的速度分布，这是由紧密间隔的出水孔产生的。对冷却流动行为的参数研究表明了薄膜流动的复杂性及其对冷却性能的影响。

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