The main intent of the project is to establish cyclic life of high pressure turbine rotor blade fitted on a twin spool turbojet engine meant for fighter class application. An attempt is made to identify the gas bending loads, centrifugal loads, and thermal gas loads due to various rpm conditions of the engine. To establish cyclic life of turbine blade, stress approach is followed. The three-dimensional model is generated using CATIA V5 R20 and the analysis of the model is carried out in ANSYS 12.1 by simulating pressure and thermal loads so that mean and alternating stresses and vibrational modes could be extracted. Material properties for room and operating temperature are obtained from literature and these are used for generating Goodman diagram and S-N diagram. Campbell diagram is used to obtain engine cross over for the blades in bending and torsional frequencies. Simulation of defects is another area explored in respect of a blade wherein notch is created and the same analysis as above is carried out on this blade also. The purpose is to identify the reduction in the frequency and variations in engine cross over points in the Campbell diagram and to compare with the serviceable and unserviceable blades. The loss of frequency and change in engine cross over locations has given an idea about the effect of unserviceability on blade and its manifestation during engine operation.
Cyclic Life Estimation of Turbine Rotor Blade Fitted in a Twin Spool Turbojet Engine
Lect.Notes Mechanical Engineering
Innovative Design, Analysis and Development Practices in Aerospace and Automotive Engineering ; Kapitel : 18 ; 135-143
2014-05-03
9 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch