期刊
INTERNATIONAL JOURNAL OF TURBO & JET-ENGINES
卷 29, 期 4, 页码 259-267出版社
WALTER DE GRUYTER GMBH
DOI: 10.1515/tjj-2012-0017
关键词
Fatigue life; linear damage rule; aircraft engine; load spectrum
资金
- National Natural Science Foundation of China [51075061]
- Specialized Research Fund for the Doctoral Program of Higher Education of China [20090185110019]
Aircraft engine components are subjected to variable amplitude load conditions usually they tend to experience fatigue damage. Many fatigue damage accumulation theories have been put forward to predict the fatigue lives of structure components. Under different load spectra, the aircraft engine has different working life. In this paper, based on the linear damage rule, the fatigue life of an aircraft engine was estimated by considering the load spectrum difference factor. According to one aircraft engine used for different load spectrums, the relationship between the load spectrum and the life is discussed. Moreover, the fatigue life of this engine used in A-type bomber is estimated based on the different load spectrum of the B-type bomber. A good agreement is found between the estimated results and real life data.
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