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首页> 外文会议>ASME Turbo Expo vol.6 pt.A; 20050606-09; Reno-Tahoe,NV(US) >PERFORMANCE AND FLOW CHARACTERISTICS OF AN OPTIMIZED SUPERCRITICAL COMPRESSOR STATOR CASCADE
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PERFORMANCE AND FLOW CHARACTERISTICS OF AN OPTIMIZED SUPERCRITICAL COMPRESSOR STATOR CASCADE

机译：优化的超临界压缩机定子叶栅的性能和流动特性

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摘要

An experimental and numerical study was performed on an optimized compressor stator cascade designed to operate efficiently at high inlet Mach numbers (M_1) ranging from 0.83 to 0.93 (higher supercritical flow conditions). Linear cascade tests confirmed that low losses and high turning were achieved at normal supercritical flow conditions (0.7 < M_1 < 0.8), as well as higher supercritical flow conditions (0.83 < M_1 < 0.93), both at design and off-design incidences. The performance of this optimized stator cascade is better than those reported in the literature based on Double Circular Arc (DCA) and Controlled Diffusion Airfoil (CDA) blades, where losses increase rapidly for M_1 > 0.83. A 2-D Navier-Stokes solver was applied to the cascade to characterize the performance and flow behavior. Good agreement was obtained between the CFD and the experiment. Experimental loss characteristics, blade surface Mach numbers, shadowgraphs, along with CFD flowfield simulations, were presented to elucidate the flow physics. It is found that low losses are due to the well-controlled boundary layer, which is attributed to an optimum flow structure associated with the blade profile. The multi-shock pattern and the advantageous pressure gradient distribution on the blade are the key reasons of keeping the boundary layer from separating, which in turn accounts for the low losses at the higher supercritical flow conditions.
机译：对优化后的压缩机定子叶栅进行了实验和数值研究，该叶栅设计为在入口马赫数（M_1）为0.83至0.93（较高的超临界流动条件）时有效运行。线性级联测试证实，在设计和非设计入射时，在正常的超临界流动条件下（0.7 0.83迅速增加。将二维Navier-Stokes求解器应用于级联，以表征性能和流动行为。 CFD和实验之间获得了良好的一致性。提出了实验损失特性，叶片表面马赫数，阴影图以及CFD流场模拟，以阐明流场物理特性。发现低损耗归因于边界层控制得当，这归因于与叶片轮廓相关的最佳流动结构。多冲击模式和叶片上有利的压力梯度分布是保持边界层不分离的关键原因，这又导致了在较高超临界流动条件下的低损耗。

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