Details
| Original language | English |
|---|---|
| Pages (from-to) | 1880-1892 |
| Number of pages | 13 |
| Journal | Fatigue and Fracture of Engineering Materials and Structures |
| Volume | 43 |
| Issue number | 8 |
| Publication status | Published - 1 Jun 2020 |
Abstract
Rotor components of an aircraft engine in service are usually subjected to combined high and low cycle fatigue (CCF) loadings. In this work, combining with the load spectrum of CCF, a modified damage accumulation model for CCF life prediction of turbine blades is first put forward to take into account the effects of load consequence and load interaction caused by high-cycle fatigue (HCF) loads and low-cycle fatigue (LCF) loads under CCF loading conditions. The predicted results demonstrate that the proposed model presents a higher prediction accuracy than Miner, Manson-Halford model does. Moreover, to evaluate the fatigue reliability of rotor components, reliability model with the failure mode of CCF is proposed on the basis of the stress-strength interference method when considering the strength degeneration, and its results show that the reliability model with CCF is more suitable for aero-engine components than that with the failure mode of single fatigue.
Keywords
- combined cycle fatigue, fatigue damage accumulation, life prediction, reliability analysis, turbine blades
ASJC Scopus subject areas
- Materials Science(all)
- Engineering(all)
- Mechanics of Materials
- Engineering(all)
- Mechanical Engineering
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In: Fatigue and Fracture of Engineering Materials and Structures, Vol. 43, No. 8, 01.06.2020, p. 1880-1892.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - A fatigue damage accumulation model for reliability analysis of engine components under combined cycle loadings
AU - Yue, Peng
AU - Ma, Juan
AU - Zhou, Changhu
AU - Jiang, Hao
AU - Wriggers, Peter
N1 - Funding Information: The authors gratefully acknowledge the support of Natural Science Foundation of China (Grant No.11572233), Pre‐research Foundation (Grant No.61400020106), and Advance Research Fund (Grant No. FY15018040001) to the projects.
PY - 2020/6/1
Y1 - 2020/6/1
N2 - Rotor components of an aircraft engine in service are usually subjected to combined high and low cycle fatigue (CCF) loadings. In this work, combining with the load spectrum of CCF, a modified damage accumulation model for CCF life prediction of turbine blades is first put forward to take into account the effects of load consequence and load interaction caused by high-cycle fatigue (HCF) loads and low-cycle fatigue (LCF) loads under CCF loading conditions. The predicted results demonstrate that the proposed model presents a higher prediction accuracy than Miner, Manson-Halford model does. Moreover, to evaluate the fatigue reliability of rotor components, reliability model with the failure mode of CCF is proposed on the basis of the stress-strength interference method when considering the strength degeneration, and its results show that the reliability model with CCF is more suitable for aero-engine components than that with the failure mode of single fatigue.
AB - Rotor components of an aircraft engine in service are usually subjected to combined high and low cycle fatigue (CCF) loadings. In this work, combining with the load spectrum of CCF, a modified damage accumulation model for CCF life prediction of turbine blades is first put forward to take into account the effects of load consequence and load interaction caused by high-cycle fatigue (HCF) loads and low-cycle fatigue (LCF) loads under CCF loading conditions. The predicted results demonstrate that the proposed model presents a higher prediction accuracy than Miner, Manson-Halford model does. Moreover, to evaluate the fatigue reliability of rotor components, reliability model with the failure mode of CCF is proposed on the basis of the stress-strength interference method when considering the strength degeneration, and its results show that the reliability model with CCF is more suitable for aero-engine components than that with the failure mode of single fatigue.
KW - combined cycle fatigue
KW - fatigue damage accumulation
KW - life prediction
KW - reliability analysis
KW - turbine blades
UR - http://www.scopus.com/inward/record.url?scp=85085709056&partnerID=8YFLogxK
U2 - 10.1111/ffe.13246
DO - 10.1111/ffe.13246
M3 - Article
AN - SCOPUS:85085709056
VL - 43
SP - 1880
EP - 1892
JO - Fatigue and Fracture of Engineering Materials and Structures
JF - Fatigue and Fracture of Engineering Materials and Structures
SN - 8756-758X
IS - 8
ER -