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Aerodynamic Optimization of Axial Transonic Compressor Blade by Adjoint Method Using Bump/ Local Blowing

Khatibi Rad, Saeedeh | 2017

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  1. Type of Document: Ph.D. Dissertation
  2. Language: Farsi
  3. Document No: 54040 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Mazaheri, Karim
  7. Abstract:
  8. Transonic flow compressors are widely used today. In these systems, the occurrence of shock waves, interaction of the shock and the boundary layer, thickening of the boundary layer and separation are some challenges which can severely affect the aerodynamic performance. Here we use a numerical analysis and an optimization algorithm to optimize the aerodynamic shape of a transonic axial compressor blade section. The total pressure loss through a cascade of blade sections is selected as the cost function. A continuous adjoint optimization method is used along with a RANS solver to find the new blade section shape. Application of three different geometric modelling of a compressor blade section in an inverse design problem are compared and it is shown that the Bezier method has a better convergence rate and also is accurate enough. Here, we introduce the shock control bump (SCB) to improve the performance of axial compressor blade sections, and optimize its shape and location. Three single point and one multi-point optimizations were performed in the design condition and in two off-design conditions. Also we optimize the use of flow blowing to improve the performance of a compressor blade section. An analysis is given regarding how the SCB and the blowing change the wave structure between blade sections resulting in a more favorable flow pattern. Results show that using the optimized SCB and using the optimized blowing improve the performance of a tansonic axial compressor blade section
  9. Keywords:
  10. Axial Compressor ; Geometric Modeling ; Flow Control ; Shock Control Bump ; Optimization ; Transonic Flow ; Local Blowing

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