DESIGN OPTIMIZATION AND ANALYTICAL INVESTIGATIONS OF MICRO GAS TURBINE

Dr. P. Srinivasulu, Mr. P. Raju, P.S. Raja Bhanu Prakash

Abstract


A turbine blade is the person aspect which makes up the turbine phase of a gas turbine. The blades are answerable for extracting strength from the high temperature, high strain gas produced with the aid of the combustor. The turbine blades are frequently the restricting factor of gas turbines. To survive in this difficult environment, turbine blades regularly use distinctive materials like notable alloys and lots of exceptional methods of cooling, which includes inner air channels, boundary layer cooling, and thermal barrier coatings. In this mission, a turbine blade is designed and modeled in 3-D modeling software program CREO. The design is changed with the aid of changing the base of the blade to boom the cooling efficiency. Since the design of faster equipment is complicated, and efficiency is immediately associated with cloth performance, material selection is of top significance. In this project,  materials are considered for turbine blade titanium alloy and nickel alloy. Optimization is achieved by using varying the materials Titanium alloy and Super Alloy by using acting coupled discipline evaluation (thermal+structural) at the turbine blade for each the designs.


Keywords


Micro Gas Turbine ; Static Analysis; Thermal Analysis; CREO Parametric; ANSYS;

References


O.E. Balje, Turbo machinery: A Guide to Design, Selection and Theory, Wileys, April 1981.

S.M. Yahya, Turbines, Compressors and Fans, Tata McGraw Hill Education Private Limited, New Delhi, 2005

A.H. Epstein, Micro-Heat Engines, Gas Turbines, and Rocket Engines - The MIT Micro engine Project, American Institute of Aeronautics and Astronautics, 1997, pp. 1-12.

Available from http:// www.Powermems.Com.

Available from http://www.Planet-energy.Org


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