پديد آورنده :
نيك نژاد، فرهود
عنوان :
ارزيابي مشخصات عملكردي موتور توربوشفت با استفاده از شبيه سازي عددي اجزاء دوار
مقطع تحصيلي :
كارشناسي ارشد
گرايش تحصيلي :
تبديل انرژي
محل تحصيل :
اصفهان: دانشگاه صنعتي اصفهان، دانشكده مكانيك
صفحه شمار :
هفت،127ص.: مصور،جدول،نمودار
يادداشت :
ص.ع.به فارسي و انگليسي
استاد راهنما :
مهدي نيلي احمد آبادي
استاد مشاور :
احمدرضا پيشه ور
توصيفگر ها :
كمپرسور محوري , كمپرسور گريز از مركز , توربين محوري , نمودار عملكردي
تاريخ نمايه سازي :
24/1/92
استاد داور :
احمد سوهانكار، محسن ثقفيان
چكيده فارسي :
به فارسي و انگليسي: قابل رويت در نسخه ديجيتالي
چكيده انگليسي :
Evaluation of Performance Characteristic of Turbo shaft Engine Using Numerical Simulation of Rotary Component Farhoud NickNezhad f nikenezhad@me iut ac ir Date of Submission 2012 12 24 Department of Mechanical Engineering Isfahan University of Technology Isfahan 84156 83111 Iran Degree M Sc Language Persian Supervisor Mahdi Nili AhmadAbadi m nili@cc iut ac ir Abstract In the last decade three dimensional numerical simulation of gas turbine components has been studied intensely One of the most important issues in design and analysis of gas turbine components is flow field insight losses and instabilities prediction These losses and instabilities include return flows rotational stall local shocks surge and local and global instabilities reducing life and performance of system components severely On the other hand predicting the performance characteristics of turbine and compressor without costly experimental tests is a significant advantage for gas turbine design Hence In the last decade with upgrade of computers numerical study of effective parameters on the performance of turbine and compressor such as axial distance between stages end wall contouring methods of turbine passage effects of roughness and airfoils on losses and effects of clearance between the rotor blades and casing have been considered to be studied Therefore in the present study three dimensional numerical analysis of rotating components of a turbo shaft engine involving 3 stage axial compressor one stage centrifugal compressor and one stage high pressure axial turbine is done for its recognition Also feasibility study of its promotion to a turbojet engine is done by adding a nozzle at the end of high pressure turbine 3D Numerical analysis of flow inside the compressor and turbine is done separately by CFX software Compressible flow equations are solved by using pressure based method with second order accuracy and SST turbulence model Performance characteristic curves of compressor and turbine are obtained separately by changing inlet and outlet boundary conditions of the compressor and turbine Also internal flow field and local losses in various components are studied in design and off design conditions Finally by design of nozzle at the end of the motor and its numerical simulations with high pressure turbine possibility of changing this engine into a turbojet engine is assessed The results of simulations show that in the first stage of axial compressor a secondary flow is created from hub to tip because of high axial chord of rotor blade Also flow in this rotor is transonic Flow in the turbine nozzle is chocked earlier than in rotor showing upstream flow of the turbine is not affected by downstream flow Moreover change of rotor speed does not affect in nozzle flow pattern Also flow chocking occurs in the nozzle hub earlier The feasibility study for promotion of this engine to a turbo jet engine shows that change of the current engine to a turbofan engine is more suitable because of its low mass flow rate Keywords Numerical Simulation Axial Compressor Centrifugal Compressor Axial Turbine Performance Curve
استاد راهنما :
مهدي نيلي احمد آبادي
استاد مشاور :
احمدرضا پيشه ور
استاد داور :
احمد سوهانكار، محسن ثقفيان
