Isotherm Identification on the Surface of Gas Turbine Engine Hot Components using Temperature Indicating Paint through Image Processing Algorithm

Abstract

iv newlineABSTRACT newlineGas Turbines has been used in the applications of the aircraft newlinepropulsion system and land-based power generating systems in more newlineeffective way. Optimization of the individual component temperature of newlinethe gas turbine engine is mandatory by the manufacturers of aeronautical newlinecomponents in order to enhance the life span of the turbo shaft and the newlinethermal efficiency of an aircraft propulsion system. Thermal efficiency newlineand power output of the gas turbine system can be increased if the newlinetemperature of flue gases entering the turbine increased from 1500 newline0 newlineC to newline19500 newlineC. Combustion Chamber and Turbine are to be considered as the newlineessential sections of gas turbine engine for maximizing the energy newlineoutput. The flame produced due to combustion of air and fuel propagates newlinethrough these two components of the gas turbine system. As the hot newlinecombustible gases flows through these components, high thermal newlinestresses are imposed on these components. The maximum exposure newlinetemperature leads to thermal stress, fatigue and creep of the components. newlineThe exposure temperature and the temperature gradient on the surface of newlinethese components should be kept to an acceptable level for better health newlinemonitoring. newlineThe current research work concentrates on the identification of newlineisotherms on the components of a gas turbine engine exposed to high newlinetemperature. The prime objective of surface temperature detection is newlineachieved by using a novel method called as Temperature Indicating newlinepaint (TIP). A Multi Colour Change (MC) 350-8, Temperature newlineIndicating Paint (TIP) was chosen to achieve this objective. A newlinev newlinecalibration data base has been framed based on the colour change of MC newline350-8 with temperature variation. The behavior of MC 350-8 with newlinechange in temperature, time, cross sectional area and flame distribution newlinehas been observed with a bow-tie specimen. The experimental research newlinealso comprises the calibration of temperature detected using MC 350-8 newlinealong with the temperature recorded by K type thermocouple. newlineThe colour attributes has been found for each colour change and newlinea relation between temperature and colour attributes has been newlineestablished. Based on the relation, an image processing algorithm has newlinebeen formed for detection of surface temperature using colour attributes. newlineThe temperature gradient on the surface of fabricated combustion newlinechamber and turbine blades has been detected using the proposed newlinealgorithm. A steady state thermal analysis also has been carried out on newlinethe miniature of the experimental specimens for the numerical validation newlineof MC 350-8 results. newlineAn optimum configuration and the suitable material for the newlinecombustion chamber and turbine blade has been identified based on newlinesurface temperature profiling of MC 350-8. The observed results from newlinethe research work reveals that the proposed image processing algorithm newlineusing the colour change of MC 350-8 is an simple and cost-effective newlinemethod in the surface temperature detection of gas turbine engine newlinecomponents. newline