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首页> 外文会议>ASME gas turbine India conference >COMPUTATIONAL ANALYSIS OF EFFECT OF CIRCUMFERENTIAL GROOVE CASING TREATMENT WITH DIFFERENT AXIAL COVERAGE OVER ROTOR BLADE TIP CHORD ON THE PERFORMANCE OF A TRANSONIC AXIAL COMPRESSOR STAGE
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COMPUTATIONAL ANALYSIS OF EFFECT OF CIRCUMFERENTIAL GROOVE CASING TREATMENT WITH DIFFERENT AXIAL COVERAGE OVER ROTOR BLADE TIP CHORD ON THE PERFORMANCE OF A TRANSONIC AXIAL COMPRESSOR STAGE

机译：转子叶片尖端沿横轴尖端沿横桥梁尖端沿横桥梁桥面沿跨音轴压缩机阶段性能的计算分析

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Previous studies on circumferential groove casing treatments have shown that the effectiveness of casing Grooves highly depends on their axial location over blade tip. The present work aims to study the flow behavior and its impact on the performance of the compressor stage when the casing treatment grooves are placed to provide different axial coverage over rotor chord in each case. Geometry of a transonic compressor stage was modeled for this study. Flow field solutions for this model with smooth casing wall were obtained by solving steady state 3-D Reynolds-Averaged Navier-Stokes equations for three different grids to prove the grid independence of the solutions. Results obtained with the intermediate grid density were used as the baseline results to compare with results of casing treatment geometries. The basic casing treatment geometry has 10 circumferential groves of width 4mm, depth 16mm and axial spacing of 2mm between each groove. This casing treatment geometry was superimposed over the rotor domain with the grooves extending axially over the entire axial chord (58mm) of rotor blade tip and flow field solutions were again obtained. After that, for each case the grooves are removed from the rear side and axial coverage is shortened. Flow solutions for various axial coverage and hence for various number of grooves are thus obtained and compared. These results depict improvement in the operating range when compared to the Base-line results. Results also exhibit that as the grooves from the rear end are removed gradually, recovery in the overall efficiency is seen in compressor performance. Post processing of the flow solutions confirms the trend and shows that the grooves in the rear of the chord are almost idle not providing sufficient flow to pass over from pressure surface to suction surface of the blade and hence contributing very less towards performance enhancement.
机译：以前关于圆周槽壳体处理的研究表明，壳体槽高度依赖于叶片尖端的轴向位置。当前工作旨在研究流动行为及其对压缩机级的性能的影响，当套管处理槽放置在每种情况下在转子弦上提供不同的轴向覆盖。跨音速压缩机阶段的几何形状被建模用于本研究。通过求解稳态3-D Reynolds - 平均的Navier-Stokes方程，获得了三种不同网格的稳定状态3-D雷诺等，获得了具有光滑壳壁的该模型的流场解决方案，以证明溶液的网格独立性。使用中间栅极密度获得的结果用作基线结果，以与套管处理几何形状的结果进行比较。基本壳体处理几何形状具有10个宽度4mm的周向叶，深度16mm，在每个凹槽之间2mm的轴向间隔。该套管处理几何形状叠加在转子域上，轴向轴向沿转子叶片尖端（58mm）沿轴向延伸，再次获得流场溶液。之后，对于每种情况，凹槽从后侧移除，并且缩短轴向覆盖。因此获得了各种轴向覆盖的流动溶液，因此获得了各种数量的凹槽。这些结果描绘了与碱基结果相比的操作范围内的改善。结果还表明，随着从后端的凹槽逐渐去除，在压缩机性能中看到整体效率的恢复。流动解决方案的后处理确认了趋势，并表明弦中的后部的凹槽几乎不提供足够的流量以从压力表面传递到刀片的吸入表面，因此促进了对性能增强的影响非常少。

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