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Modeling stable growth of fatigue cracks in aero engine turbine discs under simple and complex loading cycles
- Authors: Tumanov N.V.1, Lavrentyeva M.A.1, Cherkasova S.A.1, Servetnik A.N.1
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Affiliations:
- Central Institute of Aviation Motors
- Issue: Vol 8, No 3-1 (2009): Special Issue
- Pages: 188-199
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/695
- DOI: https://doi.org/10.18287/2541-7533-2009-0-3-1(19)-188-199
- ID: 695
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Abstract
Techniques for modeling stable fatigue crack growth in highly stressed structural parts under simple and complex loading cycles have been developed which are based on the theory of local high-energy-type fracture mechanism acting at a crack front in the second stage of fatigue crack kinetics. The techniques have been verified with the use of 3D finite element modeling and microfractographic reconstitution of fatigue crack growth in aero engine turbine discs.
About the authors
N. V. Tumanov
Central Institute of Aviation Motors
Author for correspondence.
Email: vest@ssau.ru
Russian Federation
M. A. Lavrentyeva
Central Institute of Aviation Motors
Email: vest@ssau.ru
Russian Federation
S. A. Cherkasova
Central Institute of Aviation Motors
Email: vest@ssau.ru
Russian Federation
A. N. Servetnik
Central Institute of Aviation Motors
Email: vest@ssau.ru
Russian Federation
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