Investigation of the Effect of Using 3D Airfoils in the First Row Blades of v94.2 Gas Turbine Compressor Using CFX Software

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Mohebi, Zeinab | 2012

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 53889 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Ghorbanian, Kaveh
Abstract:
CDA and NACA65 airfoils, originally designed for aircraft engine applications so do not have the best possible performance for heavy-duty industrial gas turbines and should be optimized according to the operating conditions and requirements of these turbines. For example, due to the high mass flow in industrial gas turbines, the first rows of the compressor deal with the distribution of critical velocities and sound level, while in the middle and end rows of the flow, the flow is subsonic. In designing these airfoils, two parameters of wide performance drop and range should be considered. Since the diffusion of the suction surface causes a drop, the design of new airfoils should start with the change of this part and then be accompanied by changes in the pressure level
Keywords:
Gas Turbines ; Blade ; Compressor ; Airfoil Optimization ; Compressor Blade ; Controlled Diffusion Airfoil (CDA) ; NACA 65 Airfoil

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