Published in: International Journal of Engineering Research & Technology
License: This work is licensed under a Creative Commons Attribution 4.0 International License.
Volume/Issue: Vol.1 - Issue 10 (December - 2012)
In this research paper is mainly apprehensive with aircraft gas turbine engine. Turbine blade is an important part of aircraft gas turbine engine. The research focus of 10 C4 / 60 C 50 turbine blade model, because of its common use in all types of aircraft engines. Investigate used, Pro-e model and ANSYS tools. Present research was focused on using Finite element methods (FEM) to predict the location of possible temperature areas on turbine blades. The conventional alloys such as titanium, zirconium, molybdenum, super alloys are chosen for analysis. Initially the model is created with the help of Pro-e and then it is imported to Ansys.The static analysis of solid model is carried out by applying temperature from external circumference tip of turbine blade to root of the blade and the temperature distribution is plotted. At that time measured the maximum temperature withstood capacity in gas turbine blade. Finally the entire four alloy materials are compared with respect to temperature distribution to found out of the best one. Then suggested to which material is better performing in gas turbine engine applications.
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