Measurement Errors Analysis And Correction In Gas Turbine Engine Pyrometer System

In recent years, people’s need in more powerful engine is increasing fast with highdevelopment speed of industry. Engine as the main power source of machine has alreadyupgraded for many generations from steam engine to combustion engine, and to gas turbineengine which is applied for its high power and efficiency. Therefore, there are manytechniques which are researching and developing related to gas turbine engine.For practical application of gas turbine engine, to increase the heat efficiency is toarchiving the highest turbine entry temperature. However the gas turbine blade has its owntemperature limit. The gas turbine blades are usually made of special alloy which must beworking under highest temperature limit. Once the gas turbine blades’ temperature exceedsthe limit, the blade’s mechanical strength will decrease rapidly. That will shorten the maintainperiod of gas turbine, and also increase the cost of maintaining. In more critical conditions,the gas turbine blade may break to harm the whole gas turbine and cause serious accident. So,we must find a method to measure the temperature of gas turbine blade to prevent it fromworking beyond limit.The infrared radiation temperature measurement is a chosen method among many for itis an un-contact measurement method. But the infrared radiation temperature measurement iseasy to be effected by many errors. These errors should be analyzed and corrected beforepractical application.This thesis firstly analyzed the theoretical basis of infrared radiation measurement andthe errors of emissivity. Then analyzed the practical environment of gas turbine engine to findout the possible errors. At the end of this thesis some algorisms are came out to correct thesepossible errors.