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2-D Design and Optimization of Axial Flow Compressor Blade with 2-Objective Method

Naseripour Yazdi, Ali | 2015

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 46994 (08)
  4. University: Sharif University of Technology
  5. Department: Mechanical Engineering
  6. Advisor(s): Hajilouy Benisi, Ali
  7. Abstract:
  8. Axial compressors are utilized to increase compressible flow pressure in an efficient manner where mass flow rate is high, such as aviation engines and power generation gas turbines. The flow is compressed within this machine through several stages. Each stage consists of a rotor blade row followed by a stator blade row. Energy transfer to the air is performed on the rotor by changing its velocity vector. Then, pressure is recovered from velocity by diffusion, meanwhile turning the flow direction through stator blades. These blades have been designed and optimized with various methods evolved with developing computational and manufacturing facilities. In this thesis the aerodynamic design of blade is carried out in three steps: geometry representation, performance evaluation and then optimization. After reviewing common methods for each step proper orthogonal decomposition is chosen for representing the geometry. Two dimensional compressible Navier-Stocks equations as well as continuity and energy equations are solved to obtain flow field in blade to blade plane from which performance evaluated. At last the blade performance is optimized by adopting nondominated sorting genetic algorithm. Optimization of rotor blade is aimed to achieve maximum of blade work transfer with minimum entropy generation. For stator blades maximum of pressure recovery with minimum entropy generation is desired. After performing computations, some designs are obtained for stator and some for rotor blades. From these designs proper couple of rotor and stator blades could be choose to compromise between objects. The stator blades designed for the axial compressor of gas turbine of sharif university of technology gas turbine lab show 23 percent more pressure recovery with 9 percent lower total pressure loss. By the designed rotor blades, 17 percent higher pressure ratio is achievable with 3 percent increase in polytropic efficiency, considering Just profile loss. In next step blade cascade test rig is designed and constructed, for one of the designed stator blade examining performance experimentally. Comparing computational performance results with experimental results show good agreement in zero and negative incidence angles
  9. Keywords:
  10. Axial Compressor ; Multiobjective Optimization ; Rotor Blade ; Aerodynamic Design ; Stator Blade

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