Synthesis and characterization of thoria incorporated yttria ceriastabilized zirconia nano particles for high temperature thermal barrier coating application on turbine blades

Abstract

Nowadays the air transportation is the most sought after transportation mode Unlike the other mass rapid transportation means like rail transportation the aviation industry involves huge investment for establishing the infrastructure and maintenance of aircraft as well as its components Around 100 billion dollars every year would be spent by major airliners for the accomplishment of maintenance tasks of aircraft and its systems As these expenditures are huge the optimization or controlling of maintenance cost can be executed in all possible sections of a maintenance organization It can be said so the cost saved in maintenance is as good as cost earned The maintenance cost can be saved if and only if any part or component is utilized as much as possible within its service life This thesis proposes one possible technique to maximize the utilization of vital components like Turbine section of Gas turbine engines The combustion chamber and turbine section are most critical components of an aero engine as they are operated at extremely high pressure and temperature In general the failures or malfunctions in combustion chambers are not as significant as that of turbine The Turbine blades are exposed to high speed jets at high temperature and pressure As the turbine blades are continuously operated in non conducive atmosphere an increased amount of time and effort is needed to ensure the serviceability of these parts There are many potential failures found in turbine blades such as wear creep corrosion and fatigue failures These blades are provided with Thermal Barrier coating for protecting them from high temperature stresses and also to enhance their service life The service life of turbine blades is also limited and hence it is necessary to utilize them as much as possible newline