Aerothermodynamic Design of Direct Coupled Turboexpander Compressor Radial Impellers

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Alizadeh, Saber | 2017

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 50216 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Ghorbanian, Kaveh
Abstract:
In this research, an attempt is made to obtain the geometrical and performance matching between a centrifugal compressor and a pre-designed radial inflow turbine. In this regard, constraints such as the same outer diameters, stagnation pressure, rotational speed, and power are considered. The impeller of the centrifugal compressor is designed by employing one-dimensional design method. The aerodynamic performance of the centrifugal compressor is 3-dimensionally evaluated by the commercial CFX software. A comparison of the 1D and 3D results reveals a maximum deviation of 7% indicating relatively good agreement. A sensitivity analysis on the flow coefficient and tip clearance shows a change of 0.02 and 2%, respectively. The final results indicate a power generation (consumption) of 2978 (2628) kilowatt for turbine (compressor) and a mechanical efficiency of 0.88 for equal rotational speeds of turbine and compressor
Keywords:
Centrifugal Compressor ; Aerodynamic Design ; Aerothermodynamics ; Geometrical Matching ; Performance Matching ; Radial Inflow Turbine

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