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首页> 外文期刊>Journal of turbomachinery >Boundary Conditions for Compressor Cascade Ice Crystal Icing Testing
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Boundary Conditions for Compressor Cascade Ice Crystal Icing Testing

机译：压缩机级联冰晶锦冰测试的边界条件

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摘要

At the Altitude Test Facility (ATF) of the University of Stuttgart, a linear compressor cascade test rig serves the investigation of ice crystal icing (ICI) under engine realistic conditions. A numerical model of the first stage of National Aeronautics and Space Administration (NASA) Stage 67 is validated with experimental data taken from the literature and used to investigate the respective ice crystal icing conditions for prospective cascade experiments. Eleven operating points simulating climb conditions with constant non-dimensional power setting through ascending parcels of moist air are selected for analysis. Only the melting-dominated regime is considered. The three-dimensional flow field is obtained using a Reynolds-averaged Navier-Stokes (RANS) approach in combination with a Spalart-Allmaras one-equation turbulence model. The droplet and ice crystal trajectories are calculated based on an Eulerian framework. The computation of the surface energy balance is adapted from the Messinger model taking into account unsteady phenomena. Four of 11 selected operating points indicate the onset of substantial ice accretion. A static wet-bulb temperature of freezing constitutes in general the lower icing limit for rig experiments. The upper icing limit depends on the ice water content impinging and sticking to the target surface.
机译：在斯图加特大学的高度测试设施（ATF），一个线性压缩机级联试验台在发动机现实条件下对冰晶冰（ICI）进行了研究。通过从文献中取出的实验数据，验证了国家航空航天局（NASA）第67阶段67的第一阶段的数值模型，并用于研究预期级联实验的各自的冰晶锦冰条件。选择通过升高的潮湿空气的升高的包裹来模拟具有恒定非尺寸功率设定的爬升条件进行分析。只考虑熔化主导的制度。使用Reynolds平均的Navier-Stokes（RAN）方法与Spalart-Allmaras单一方程湍流模型组合获得三维流场。基于欧拉框架计算液滴和冰晶轨迹。表面能量平衡的计算从Messinger模型调整，考虑到不稳定的现象。 11个选定的操作点中的四个表明了大量冰积极的开始。凝固湿灯泡温度一般是钻机实验的较低僵硬极限。上冰限取决于撞击并粘附到目标表面的冰水含量。

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