Numerical Investigation of Tip Clearance Effects in an Axial Transonic Compressor

查看全文 作　　者：R. [1]Ciorciari;A. [1]Lesser;F. [1]Blaim;R. [1]Niehuis

机构地区：[1]Institute for Jet Propulsion, University of Federal Armed Forces Munich, Werner-Heisenberg-Weg 39, D-85577 Neubiberg

出　　处：《Journal of Thermal Science》索引2012年第21卷第2期,共11页

基　　金：a part of the Deutsche Forschungsgemeinschaft Joint Research Project FOR-1066 摘　　要：Numerical investigations of the Darmstadt transonic single stage compressor (DTC), in the Rotor1-Stator1 configuration, aimed at advancing the understanding of the effect of different rotor tip gaps and transition modelling on the blade surfaces are presented. Steady three dimensional Reynolds Averaged Navier Stokes (RANS) simulations were performed to obtain the flow fields for the different configurations at different operating conditions using the RANS-Solver TRACE. The stage geometry and the multi-block structured grid were generated by G3DMESH and a grid sensitivity analysis was conducted. For the clearance gap region, a fully gridded special H-grid was chosen. Comparisons were made between the flow characteristic at design speed, representative for a transonic flow regime, and at 65% speed, representative for a subsonic flow regime. The computations were used to analyse the flow phenomena through the tip clearance region for the different configurations and their impact on the performance of the compressor stage. 关键词：跨音速流动轴流压缩机数值研究间隙 STOKES方程结构网格雷诺平均设计速度

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Numerical Investigation of Tip Clearance Effects in an Axial Transonic Compressor

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