Simulated turbine blades were subjected to transient and steady-state heating and spanwise loading in a Mach 1 burner rig. Leading-edge cracks were produced which were similar to thermal-fatigue cracks observed during engine service. Crack initiation and propagation data were obtained for a variety of test conditions.The simulated turbine blades consisted of coated and uncoated IN 100 and B 1900 cambered airfoils with grips for application of spanwise load to simulate centrifugal stress. Test variables were blade temperature, spanwise load, and steady-state (hold) time. The Mach 1 gas velocity substantially reduced conventional creep rupture life. This caused a substantial reduction in thermal fatigue life. Coating effectiveness was below that for low velocity tests.


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    Title :

    Thermal Fatigue Testing of Simulated Turbine Blades


    Additional title:

    Sae Technical Papers


    Contributors:
    Spera, D. A. (author) / Calfo, F. D. (author) / Bizon, P. T. (author)

    Conference:

    National Air Transportation Meeting ; 1971



    Publication date :

    1971-02-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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