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Flow-Field Modeling and Performance Prediction of Axial-Flow Compressors using Streamline Curvature Method

Kohandel, Hamed | 2009

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 39029 (08)
  4. University: Sharif University of Technology
  5. Department: Mechanical Engineering
  6. Advisor(s): Ghofrani, Mohammad Bagher; Nouri Borujerdi, Ali
  7. Abstract:
  8. Compressors are one of the most important components of gas turbines and turbomachinery processes. Thus some precise and quick tools are needed for design and analysis purposes. Despite of vast development of Computational Fluid Dynamics (CFD) tools, Through-Flow Streamline Curvature Methods (SCM) has retained their position. 2D and quasi-3D forms of SCM in combination with CFD results nowadays make more than 80% of turbomachinery design process of axial and radial compressors and turbines. In this thesis, the basics of developing a tool for axial-flow compressor analysis are introduced. As will be seen, this analysis tool can be used for design purposes too. The method that is chosen for analyzing the flow passing through the axial-flow compressors is Meridional Through-Flow Analysis. In this model, the ideal average flow passing through the compressor is analyzed two dimensionally or in other words quasi-three dimensionally on Meridional plane using Streamline Curvature Method (SCM). This analysis is a combination of non-viscous, potential flow analysis outside of boundary layers and adding viscous flow effects using empirical correlations and boundary layer analysis. In this analysis the blade effects are modeled by available empirical correlations for NACA 65-series, Double Circular Arc (DCA) and C4-series profiles. In addition, viscous effect on end-wall (hub and casing) boundary layers is imposed as blockage using boundary layer analysis. Validating the model, the subsonic flow through axial-flow NACA 10-Stage Compressor is analyzed and the results are presented as in blade row pressure ratio, stage pressure ratio, axial velocity and Mach number curves as well as performance maps. These results are compared with experimental data an show satisfying agreement, stating that the model can fulfill desired needs. Finally this model is employed to investigate performance and design improvement methods for axial flow compressors. This means that the effects of changing parameters like angle of IGV (Inlet Guide Vanes), blade stagger angle in first stage and tip clearance are examined as well as inlet distortion effects on performance maps
  9. Keywords:
  10. Axial Compressor ; Three Dimensional Modeling ; Two Dimentional Modeling ; Meridional Through-Flow Analysis ; Streamline Carvature Method ; NACA 10-Stage Compressor

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