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Thermal Fatigue Testing of Simulated Turbine Blades
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1971 by SAE International in United States
Annotation ability available
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.
CitationSpera, D., Calfo, F., and Bizon, P., "Thermal Fatigue Testing of Simulated Turbine Blades," SAE Technical Paper 710459, 1971, https://doi.org/10.4271/710459.
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