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Optimization of Aerodynamic Performance of a Transonic Axial Compressor Rotor Blade Using Shock Control Bump

Fouladi, Mojtaba | 2016

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 48358 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Mazaheri, Karim
  7. Abstract:
  8. Nowadays, the axial transonic compressors are used widely in aircraft engines, oil and gas industry and etc. because of higher pressure ratio and more efficiency than the other compressors. The Major part of losses in transonic compressors is due to shock waves. In this study the idea of using Shock Control Bump as a passive flow control method has been used for weakening the shock waves. The Shock Control Bump is modeled with the Hicks-Henne function and added to the suction side of a section of the NASA rotor 67 blade. Validation of flow solver is done in both two and three dimensions. Single-point and multi-point optimizations are performed in the design condition and in two off-design conditions. It is shown that the single point optimized shapes have more total pressure loss reduction for their respective operating conditions, but the multi-point optimized shape has an overall better performance over the whole operating range. Single point optimized shapes improved 10.7%, 6.9% and 8.8% of total pressure loss in off-design1, design and off-design2 conditions respectively compared with the same condition without bump. Also, multi point optimized shape improved 7.6%, 5.5% and 8.6% of total pressure loss in off-design1, design and off-design2 conditions respectively compared to the same condition without bump. In addition to total pressure loss, isentropic entropy increased in all cases. Entropy improved 5% and 2/5% for single point and three point optimized blades respectively compared with the same condition without bump in off design 2. At last an analysis is given for improvement of the wave structure by the Shock Control Bump and interactions of the boundary layer of it and the wave structure
  9. Keywords:
  10. Shock Control Bump ; Differential Evolution Algorithm ; Optimization ; Transonic Axial Compressor Blade ; Total Pressure Loss ; Mulfi-Point Optimization

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