Abstract We present a technique and results of calculating the cooling air pressure and flowrate in the turbine nozzle deflector vane duct, coefficients of heat transfer through air and from gas taking into account the influence of an air film heated in the perforation holes as well as temperature and thermal stresses in the vane elements and its thermal barrier coating in the GTE takeoff operational conditions. The effect of oval grooves in the coating behind the holes in the gas flow downstream direction and possible cracking of material on the thermal stress distribution in metal is considered.
Calculation of the thermostressed state of a turbine nozzle vane
Russian Aeronautics (Iz VUZ) ; 52 , 3 ; 368-371
2009-09-01
4 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch