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Research Papers: Gas Turbines: Structures and Dynamics

Modeling of Crack Growth With Dwell Time for Aero-Engine Spectra Loadings in a Ni-Based Superalloy

[+] Author and Article Information
Erik Storgärds

Division of Solid Mechanics,
Linköping University,
Linköping SE-58183, Sweden
e-mail: erik.storgards@liu.se

Kjell Simonsson, Sören Sjöström

Division of Solid Mechanics,
Linköping University,
Linköping SE-58183, Sweden

David Gustafsson

Siemens Industrial Turbomachinery AB,
Finspång SE-61283, Sweden

Tomas Månsson

GKN Aerospace Engine Systems,
Trollhättan SE-46181, Sweden

1Corresponding author.

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 15, 2015; final manuscript received July 20, 2015; published online August 12, 2015. Editor: David Wisler.

J. Eng. Gas Turbines Power 138(1), 012501 (Aug 12, 2015) (6 pages) Paper No: GTP-15-1327; doi: 10.1115/1.4031155 History: Received July 15, 2015

Testing and simulation of aero-engine spectra with dwell times are reported in this paper. The modeling concept used is built on linear elastic fracture mechanics (LEFM) and provides a history-dependent evolution description of dwell damage and its interaction with cyclic load. The simulations have been carried out for three spectra: (1) cyclic loads, (2) combined sustained load and cyclic loads, and (3) slow load ramps and cyclic loads, all for surface cracks at 550 °C for Inconel 718. All simulations show reasonable good agreement with experimental results. Prediction of multiple tests of several batches is also provided to show statistical scatter.

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References

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Figures

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Fig. 1

Flight spectra tested: (a) cyclic spectrum, (b) sustained load spectrum, and (c) ramp spectrum

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Fig. 2

The ramp spectrum applied with the history-dependent load counting technique

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Fig. 3

The ramp spectrum with the crack closure function, where σ open  mem.c is the stored opening value

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Fig. 4

Results for model prediction versus test

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Fig. 5

Scatter including 95% confidence interval for (a) the damaged zone concept and (b) the superposition model

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