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‘Ibis paper presents a physically-based deterministic methodology for prediction of the crack growth resistance of supera.lloys within gas turbine engine environments. ?he model combines experimentally determined temperature and pressure dependent superalloy oxidation rates with crack growth rates obtained from thermal-mechanical fatigue (TMF) specimen testing to develop a crack growth rate law for oxidation assisted crack growth behavior. This information is then used in conjunction with standard linear elastic fracture mechanics (LEFM) methods to predict propagation lives. The propagation analysis procedure is combined with previously presented procedures for the prediction of coating cracking during TMF loading (Strangman [ 11). The combination results in an initiation plus propagation litimg strategy for superalloy gas turbine components subjected to thermal-mechanical fatigue. This analytical procedure has been found to predict the measured crack sizes obtained from superalloy components after engine testing with acceptable accuracy.

Prediction of Oxidation Assisted Crack Growth Behavior within Hot Section Gas Turbine Components