RESEARCH COMMONS
LIBRARY

Aerodynamic Shape Optimization Of 3D Gas Turbine Blade Using Differerential Evolution Method

ResearchCommons/Manakin Repository

Aerodynamic Shape Optimization Of 3D Gas Turbine Blade Using Differerential Evolution Method

Show simple item record

dc.contributor.author Joshi, Darshak en_US
dc.date.accessioned 2010-07-19T19:54:58Z
dc.date.available 2010-07-19T19:54:58Z
dc.date.issued 2010-07-19
dc.date.submitted January 2010 en_US
dc.identifier.other DISS-10666 en_US
dc.identifier.uri http://hdl.handle.net/10106/4936
dc.description.abstract This paper outlines the aerodynamics shape optimization process of a 3D VKI gas turbine blade using Computational Fluid Dynamics (CFD) and differential evolution optimization method. The main objective of this work is to improve outlet total pressure for better aerodynamic performance. This benefit is achieved by optimizing the stacking line path of the turbine blade in 3D annular cascade for which higher exit total pressure is achieved. The optimization process starts with generating a 3D annular cascade with a boundary domain and meshing it using GAMBIT and is then solved in FLUENT using viscous flow analysis. The original stacking line is defined as a B -spline with its end points fixed and middle points free to move in translational direction. These middle points work as design variables whose position needs to be changed for improved exit total pressure which is a desired parameter.. The turbine blade cascade is analyzed for only aerodynamic performance. The optimization analysis is an iterative process using a parallel computing system. The shape optimization process runs iteratively with the CFD and DE code until the higher total pressure at outlet is achieved by optimizing the stacking line path of the turbine blade cascade. Here the optimization process of the 3D turbine blade cascade is presented en_US
dc.description.sponsorship Dennis, Brian en_US
dc.language.iso EN en_US
dc.publisher Aerospace Engineering en_US
dc.title Aerodynamic Shape Optimization Of 3D Gas Turbine Blade Using Differerential Evolution Method en_US
dc.type M.S. en_US
dc.contributor.committeeChair Dennis, Brian en_US
dc.degree.department Aerospace Engineering en_US
dc.degree.discipline Aerospace Engineering en_US
dc.degree.grantor University of Texas at Arlington en_US
dc.degree.level masters en_US
dc.degree.name M.S. en_US
dc.identifier.externalLink https://www.uta.edu/ra/real/editprofile.php?onlyview=1&pid=234
dc.identifier.externalLinkDescription Link to Research Profiles

Files in this item

Files Size Format View
Joshi_uta_2502M_10666.pdf 1.528Mb PDF View/Open

This item appears in the following Collection(s)

Show simple item record

Browse

My Account

Statistics

About Us