Aerodynamic Design Methodology for Changing Axial Compressor Capacity

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Mofrad, Ehsan | 2012

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 44274 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Ghorbanian, Kaveh
Abstract:
Axial compressor design is a very complex and expensive process. In general, for design and development of a new axial compressor, manufacturing companies usually intend to employ an existing and successful axial compressor as an starting point and modify and upgrade it. In this regard, dimensional scaling is a common method for derivative axial compressors. The goal of dimensional scaling is to get a different capacitywhile minimizing the development time and cost. In this thesis, theNASA eight stage transonic axial flow compressor is chosen as the base model for dimensional scaling to lower and upper size of its original dimension. The scaled compressor is analyzed with a quasi 2-D code. Further, the tip clearance, the boundary layer growth, and the maintenance of the leading and trailing edge thickness are of prime aerodynamic concern. Furthermore, the changes in the Reynolds number, that could be detrimental to aerodynamic performance, are investigated
Keywords:
Gas Turbines ; Compressor ; Capacity Enhancement ; One-Dimentional Modeling ; Axial Compressor ; Tip Clearance ; Loss Model

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