High cycle fatigue limit prediction of foreign object damaged aerofoil samples by the theory of critical distance

Liucheng Zhou; Lingfeng Wang; Yibo Shang; Xiaosheng Zhang; Zhenhua Zhao; Kun Yu; Xue Zhao; Hong Liu; Bin Li

doi:10.1016/j.vacuum.2022.111220

High cycle fatigue limit prediction of foreign object damaged aerofoil samples by the theory of critical distance

Liucheng Zhou
, Lingfeng Wang
, Yibo Shang
, Xiaosheng Zhang
, Zhenhua Zhao
, Kun Yu
, Xue Zhao
, Hong Liu
, Bin Li

Research output: Contribution to journal › Article › peer-review

9 Scopus citations

Abstract

The fatigue limit at 3 × 10⁷ cycles predicted by the theory of critical distance (TCD) on Ti–6Al–4V aerofoil samples subjected to foreign object damage (FOD) was studied. First-order bending vibration fatigue experiments were carried out with 18 FOD samples after FOD tests. First-order bending vibration mode analysis of each notched sample with various semi-elliptical notch dimensions were carried out by finite element method and the critical distance is deduced by test results and numerical simulation. FOD and HCF tests were carried out on another 9 aerofoil samples, and fatigue limit predictions were carried out using the Peterson formula and the TCD model. The results showed that the TCD model has higher prediction accuracy.

Original language	English
Article number	111220
Journal	Vacuum
Volume	203
DOIs	https://doi.org/10.1016/j.vacuum.2022.111220
State	Published - Sep 2022
Externally published	Yes

Keywords

Aero-engine blade
Foreign object damage
High cycle fatigue limit
The theory of critical distance
Titanium alloy

Access to Document

10.1016/j.vacuum.2022.111220

Cite this

@article{15040a3da0204e72b7d95a03a158f1e8,

title = "High cycle fatigue limit prediction of foreign object damaged aerofoil samples by the theory of critical distance",

abstract = "The fatigue limit at 3 × 107 cycles predicted by the theory of critical distance (TCD) on Ti–6Al–4V aerofoil samples subjected to foreign object damage (FOD) was studied. First-order bending vibration fatigue experiments were carried out with 18 FOD samples after FOD tests. First-order bending vibration mode analysis of each notched sample with various semi-elliptical notch dimensions were carried out by finite element method and the critical distance is deduced by test results and numerical simulation. FOD and HCF tests were carried out on another 9 aerofoil samples, and fatigue limit predictions were carried out using the Peterson formula and the TCD model. The results showed that the TCD model has higher prediction accuracy.",

keywords = "Aero-engine blade, Foreign object damage, High cycle fatigue limit, The theory of critical distance, Titanium alloy",

author = "Liucheng Zhou and Lingfeng Wang and Yibo Shang and Xiaosheng Zhang and Zhenhua Zhao and Kun Yu and Xue Zhao and Hong Liu and Bin Li",

note = "Publisher Copyright: {\textcopyright} 2022 Elsevier Ltd",

year = "2022",

month = sep,

doi = "10.1016/j.vacuum.2022.111220",

language = "英语",

volume = "203",

journal = "Vacuum",

issn = "0042-207X",

publisher = "Elsevier Ltd",

}

TY - JOUR

T1 - High cycle fatigue limit prediction of foreign object damaged aerofoil samples by the theory of critical distance

AU - Zhou, Liucheng

AU - Wang, Lingfeng

AU - Shang, Yibo

AU - Zhang, Xiaosheng

AU - Zhao, Zhenhua

AU - Yu, Kun

AU - Zhao, Xue

AU - Liu, Hong

AU - Li, Bin

PY - 2022/9

Y1 - 2022/9

N2 - The fatigue limit at 3 × 107 cycles predicted by the theory of critical distance (TCD) on Ti–6Al–4V aerofoil samples subjected to foreign object damage (FOD) was studied. First-order bending vibration fatigue experiments were carried out with 18 FOD samples after FOD tests. First-order bending vibration mode analysis of each notched sample with various semi-elliptical notch dimensions were carried out by finite element method and the critical distance is deduced by test results and numerical simulation. FOD and HCF tests were carried out on another 9 aerofoil samples, and fatigue limit predictions were carried out using the Peterson formula and the TCD model. The results showed that the TCD model has higher prediction accuracy.

AB - The fatigue limit at 3 × 107 cycles predicted by the theory of critical distance (TCD) on Ti–6Al–4V aerofoil samples subjected to foreign object damage (FOD) was studied. First-order bending vibration fatigue experiments were carried out with 18 FOD samples after FOD tests. First-order bending vibration mode analysis of each notched sample with various semi-elliptical notch dimensions were carried out by finite element method and the critical distance is deduced by test results and numerical simulation. FOD and HCF tests were carried out on another 9 aerofoil samples, and fatigue limit predictions were carried out using the Peterson formula and the TCD model. The results showed that the TCD model has higher prediction accuracy.

KW - Aero-engine blade

KW - Foreign object damage

KW - High cycle fatigue limit

KW - The theory of critical distance

KW - Titanium alloy

UR - https://www.scopus.com/pages/publications/85132507649

U2 - 10.1016/j.vacuum.2022.111220

DO - 10.1016/j.vacuum.2022.111220

M3 - 文章

AN - SCOPUS:85132507649

SN - 0042-207X

VL - 203

JO - Vacuum

JF - Vacuum

M1 - 111220

ER -

High cycle fatigue limit prediction of foreign object damaged aerofoil samples by the theory of critical distance

Abstract

Keywords

Access to Document

Other files and links

Fingerprint

Cite this