Study Over Thermal State of Gas Turbine Engine Metal-ceramic Rotor Blades and Nozzle Guide Vanes Under Thermal Shock and Thermal-cyclic Loading Conditions

Toensureareliableoperationofthe2.5MWgasturbineengine(GTE-2.5)withtheinletgastemperatureTIT=1623K,studieswereperformedoverthethermalstateofthenozzleguidevanesandrotorbladeswiththetemperatures,ratesandflowsoftheworkingmediaandcoolingairsimulatingallthepotentialturbinestageoperatingduties.Thesteadystateandthermal-cyclictestshavingbeenaccomplished,therewasnovisibledefectontherotorbladesandthenozzlevanes.Afterwards,theysurvivedtheendurancetestsattheratedcooling.Therefore,thefunctionalityoftheshellthin-wallhybridnozzlevanesandrotorbladesunderthevariableoperatingdutiesofthegasturbineatthe'shock'and'cyclic'loadsoftheworkingmediatemperaturevariationshasbeendemonstrated.