Accession Number:

ADA218555

Title:

Advanced Cumulative Damage Modeling

Descriptive Note:

Final rept. 13 Dec 84-31 Sep 86,

Corporate Author:

GE AIRCRAFT ENGINES CINCINNATI OH ADVANCED TECHNOLOGY OPERATION

Report Date:

1988-09-01

Pagination or Media Count:

343.0

Abstract:

Crack growth in the near-threshold and Paris regimes Regions I and II, were measured in single edge notch specimens of Rene 95 and Alloy 718 as a function of test temperature, R-ratio, hold time, frequency, and overpeak ratio. The results obtained at 649 deg. C were modeled using an interpolation and interpolation superposition model. Both models accurately predicted the time dependent crack growth of these materials. The interpolation superposition model appeared to be a better model because the interpolation model made unrealistic predictions outside the range of data obtained in this investigation. The overpeak retardation was predicted using a modified Willenborg model. A residual life computer code ACDCYCLE, which can be run on an IBM personal computer, was written to make predictions of crack growth rates and residual lives. Metal fatigue Metal life prediction Time-dependent Metal cracks Fatigue Metal crack growth Cycle-dependent metal fatigue Interpolative model Metal fracture mechanics Superposition model.

Subject Categories:

  • Metallurgy and Metallography

Distribution Statement:

APPROVED FOR PUBLIC RELEASE