STUDY OF THERMAL MAPPING FOR HEALTH MONITORING OF GAS TURBINE BLADE

Thermal mapping for health monitoring of gas turbine is essential as modern day gas turbine subjected to very high temperature applications, gas turbines are used extensively for aircraft propulsion, land -based power generation, and industrial applications. Developments in turbine cooling technology play a critical role in increasing the thermal efficiency and power output of advanced gas turbines. Gas turbine blades are cooled internally by passing the coolant through several rib-enhanced Some tine passages to remove heat conducted from the outside surface. External cooling of turbine blades by film cooling is achieved by injecting relatively cooler air from the internal coolant passages out of the blade surface in order to form a protective layer between the blade surface and hot gas-path flow. For health monitoring of gas turbine blade, this presentation focuses on the effect of critical zone and hot spot along temperature distribution by using thermal paint. The comp utational flow and heat transfer results are also presented. This presentation includes unsteady high free -stream turbulence effects on film cooling performance with a discussion of detailed heat transfer coefficient and filmcooling effectiveness distributions for standard and shaped film-hole geometry using the newly developed transient liquid crystal image method.