The thermal stresses in a turbine stator vane of a turbojet engine were measured by means of static high-temperature resistance-wire strain gages. The temperature variations existing in the engine were duplicated in the vane in a test setup at a reduced average temperature. Stress measurements at the leading and trailing edges indicated maximum principal values in compression of 18,100 and 27,200 psi, respectively. In the mid-chord region on the suction surface, the maximum principal stress was 19,600 psi in compression and in the midchord region on the pressure surface, 26,200 psi in tension.
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