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Aerodynamic Experimental and Numerical Investigations of the Gas Turbine Lab Axial Flow Compressor Blades for Performance Prediction

Marali, Mehrdad | 2022

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 55381 (08)
  4. University: Sharif University of Technology
  5. Department: Mechanical Engineering
  6. Advisor(s): Hajilouy Benisi, Ali
  7. Abstract:
  8. Axial compressors play an important role in industry and aerial and land-based engines. Hence their design and optimization is of great importance. Due to the high costs associated with design and manufacturing of axial compressors, developing a sophisticated, rapid, low-cost and reliable methods for machine performance prediction is imperative. In this study, an attempt was made at introducing such a method. In this method, isolated airfoils were built in two different scales based on medium radius cross section of stator and rotor blades of the axial compressor of Sharif University of Technology gas turbine laboratory. Using the existing wind tunnel set-up at the aforementioned laboratory, numerous experimental tests at different angles of attack and speeds were conducted and in each case the pressure distribution on the blade was obtained. By integrating the pressure distribution along the length of the airfoil, lift and drag coefficients were evaluated. Comprehensive performance data of these airfoils were produced which were in good agreement with existing general airfoil data. In order to analyze more carefully the flow around the airfoil, especially in regions where measurement was not possible, computational methods were utilized. To this end, numerical simulation using computational fluid dynamics methods was adopted. K-ω SST and Generalized k-ω computational models accompanied by C-type and channel-type geometries were used in the numerical simulation. The results of simulations using aforementioned models and geometries were compared to the experimental data and their accuracy was assessed. The simulations had high accuracy in predicting fluid behavior at pressure side and channel-type geometry was shown to be more accurate with less than 10% difference at angles of attack up to 10 degrees. At suction side channel-type geometry exhibited high agreement with experimental data in angles of attack up to 5 for rotor and 10 for stator. Ultimately, a new method was introduced for performance prediction using experimental lift and drag coefficients. The results yielded by its implementation were compared with existing performance data of the axial compressor, which demonstrated partial success. It appears more effort is needed in order to apply this method for accurate compressor performance prediction
  9. Keywords:
  10. Performance Prediction ; Computational Fluid Dynamics (CFD) ; Axial Compressor ; One-Dimentional Modeling ; Isolated Airfoil Test

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