Turbine blade analysis using different alloy

Abstract

Gas turbines play a serious role in aviation due to their high power-to-weight ratios and compactness in comparison to other conventional power generating units. The principal characteristic of the turbine blade is imparting power to or extracting it from numerous fluid streams. Turbine blades are exposed to a mix of high operating temperatures, centrifugal and bending loads due to shock loads as well as erosive/corrosive effects during operation. These operating conditions make the blades most vulnerable to failure and demand periodic inspection which adversely affects the general operational costs. In this paper, we present a study of problems related to gas turbine blades and by taking fatigue into consideration, we present a framework that successfully uses a combination of Reverse Engineering (RE) and finite element analysis (FEA) to model, analyses and optimizes different material properties which has an optimal performance of gas turbine blades for aircraft engines. Thermal fatigue and stress analysis are carried out and fatigue life cycles of different alloys are calculated