15479

1553 دكتري

دكتري

تبديل انرژي

اصفهان : دانشگاه صنعتي اصفهان

1398

هفت،130ص.: مصور، جدول، نمودار

مهدي نيلي احمدابادي

فرهاد قدك

علي مددي، حسين احمدي كيا،ابراهيم شيراني،احمد سوهانكار

1398/11/29

كتابنامه

مكانيك

پرديس

1398/11/30

2602671

Upgrade and Development of Elastic Surface Inverse Design Method for a Cascade with Sharp edged Blades in order toImprove the Performance of the Rotor Cascade of the First Stage in One Axial Compressor Sayed Hossein Nasrazadani h nasrazadani@pa iut ac ir Date of Submission 2020 01 19 Mechanical Engineering group Pardis College Isfahan University of Technology Isfahan 84156 83111 IranDegree PhD Language FarsiSupervisor Mahdi Nili Ahmadabadi m nili@cc iut ac irAdvisor Farhad GhadakAbstractThe aim of an inverse design method is to calculate the geometry corresponding to a targetpressure distribution along the walls Recently Upgraded Elastic Surface Algorithm UESA as a residual corrective inverse design method was developed for the compressor cascade withsharp edged blades in subsonic flow regimes In this method the blade walls were modeled asan elastic Timoshenko beam that smoothly deforms due to the difference between the targetand current pressure distribution without any geometrical filtration Nevertheless the UESA issubjected to oscillation instability or divergence for a cascade of sharp edged blades intransonic flow regimes due to the high pressure difference near the shock This study developsthe UESA for the shape design of transonic sharp edged blades with shock occurrence In thenew version of this method a distribution for the elastic module along the Timoshenko beamwas chosen to increase the stiffness of the beam near the shock and to control the highdeformation at this region Furthermore the nodes were constrained to move along the spinesperpendicular to the chord line By this modification the instability and oscillation wereremoved through the shape modification process Finally two design cases were carried out toevaluate the new developed method for sharp edged blades in transonic flow regimes Keywords inverse design upgraded ESA Shock cascade sharp edged blades transonic compressor cascade 1 IntroductionIn the past in order to aerodynamically optimize a flow passing over a body the aerodynamicperformance of the existing body was evaluated by examining the fluid flow around it and thegeometry was corrected based on empirical rules and the designer s experience in a trial anderror process This method was time consuming and inefficient 1

مهدي نيلي احمدابادي

فرهاد قدك

علي مددي، حسين احمدي كيا،ابراهيم شيراني،احمد سوهانكار