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Optimization of the Multi-Stage Compressor Design by Developing a Software for 2D Axial-Flow Compressor Analysis

Khodabakhshi, Alireza | 2015

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 47393 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Mazaheri, Karim
  7. Abstract:
  8. Streamline Curvature method is one of the most commonly used methods by industry for prediction of axial flow compressors. This method analyze axial compressor by solving radial equations in the meridional plane to locate streamlines and also by using empirical models to predict total pressure loss. Despite growth of CFD models, Streamline Curvature method has been considered as most practical method for compressor preliminary design and performance assessment because of it’s high speed and good precision. In the current work a C++ code (SLC) has been developed using streamline curvature for axial flow compressor performance analysis. This code receives compressor geometry, properties of blades and radial distribution of inlet flow at a specific operation point as inputs and predicts compressor performance and gives radial distribution of flow at compressor and blades outlets. This code was validated by design and experimental data of NASA 2-stage axial compressor and results of a similar work. This code was used to develop an Axial flow compressor optimization tool. For this purpose Differential Evolutionary method was used as optimization method which is a global method and is useful for continuous spaces. Finally a C++ code (SLCDE) was developed for axial flow compressor optimization. This code was used to optimize NASA 2-stage axial compressor. Several different scenarios were presented to optimize this compressor. Following the selected scenario setting angels of blades choose as optimization variables and total pressure ratio at original design operating point as objective function also constraint of optimization was not to decrease the adiabatic efficiency at original design operating point. The result of 2-stage compressor optimization was 15% increase in total pressure ratio without decreasing the adiabatic efficiency (the adiabatic efficiency increased 0.5%)
  9. Keywords:
  10. Optimization ; Axial Compressor ; Streamline Carvature Method ; Differential Evolution Algorithm ; Axial-flow Compressor ; NASA Two-stage Compressor

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