Thermal stresses in nozzle vanes with deflector cooling system

1. The combined theoretical and experimental investigation of the thermal and stress state of the nozzle vane of a gas turbine confirmed the possibility of using the newly devised experimental strain gauges in the range of working temperatures 293–973°K. 2. In modeling the pin system of the outlet channel by thin continuous baffles we obtained satisfactory agreement of calculation and experiment at all points of measurement uniformly distributed over the surface of the vane.