Critical Plane Approach to Analysis of Failure Criteria for Anisotropic Geomaterials

In this work the biaxial behavior of 316 stainless steel is studied under the lens of critical plane approach. A series of ten experiments were developed on dog bone shape hollow cylindrical specimens made of type 316 stainless steel. Five different loading conditions were assessed, with (i) only axial stress, (ii) only hoop stress, (iii) proportional combination of axial and hoop stresses, (iv) non-proportional combination of axial and hoop stresses with square shape and (v) non-proportional combination of axial and hoop stresses with L-shape. The fatigue analysis is performed following four different critical plane theories, namely Wang-Brown, Fatemi-Socie, Liu I and Liu II. The efficiency of all four theories is studied in terms of the accuracy of their life predictions.

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Damage Assessment in Fretting Fatigue Specimens with Micro-voids Using Critical Plane Approach

Lecture Notes in Mechanical Engineering - Proceedings of the 13th International Conference on Damage Assessment of Structures ◽

10.1007/978-981-13-8331-1_51 ◽

2019 ◽

pp. 666-671 ◽

Cited By ~ 1

Author(s):

D. Infante-García ◽

H. Miguelez ◽

E. Giner ◽

M. Abdel Wahab

Keyword(s):

Damage Assessment ◽

Fretting Fatigue ◽

Critical Plane ◽

Critical Plane Approach

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On the application of a critical plane approach to the life assessment of welded joints

Procedia Engineering ◽

10.1016/j.proeng.2018.02.044 ◽

2018 ◽

Vol 213 ◽

pp. 448-458 ◽

Cited By ~ 3

Author(s):

Giuseppe Marulo ◽

Francesco Frendo ◽

Leonardo Bertini ◽

Ali Fatemi

Keyword(s):

Welded Joints ◽

Life Assessment ◽

Critical Plane ◽

Critical Plane Approach

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Configurational Mechanics and Critical Plane Approach: Concept and application to fatigue failure analysis of rubberlike materials

International Journal of Fatigue ◽

10.1016/j.ijfatigue.2010.03.004 ◽

2010 ◽

Vol 32 (10) ◽

pp. 1627-1638 ◽

Cited By ~ 27

Author(s):

A. Andriyana ◽

N. Saintier ◽

E. Verron

Keyword(s):

Failure Analysis ◽

Fatigue Failure ◽

Critical Plane ◽

Configurational Mechanics ◽

Critical Plane Approach ◽

Rubberlike Materials

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Assessment of Degrees of Cumulative Fatigue Crack Initiation Damage at Guyed Mast Earplate Joint

Key Engineering Materials ◽

10.4028/www.scientific.net/kem.467-469.776 ◽

2011 ◽

Vol 467-469 ◽

pp. 776-781

Author(s):

Wen Li Wang ◽

Wei Lian Qu ◽

Jie He

Keyword(s):

Residual Stress ◽

Fatigue Crack ◽

Crack Initiation ◽

Fatigue Crack Initiation ◽

Welding Residual Stress ◽

Critical Plane ◽

Multi Scale ◽

Cumulative Strain ◽

Critical Plane Approach ◽

Guyed Mast

This paper proposes a new method for assessing the degree of the cumulative fatigue crack initiation damage of the joint welds at the guyed mast earplate. Based on the multi-scale wind-induced stress analysis of the guyed mast earplate joint, and considering the welding residual stress in earplate joint, the critical plane approach is used for the calculation of cumulative strain fatigue damage due to the combined actions of the welding residual stress and the wind load.

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Dominant Damage Factors Determining for Single Crystal Nickel Superalloys Under Cyclic Loading Based on Principal Component Analysis

Volume 7A: Structures and Dynamics ◽

10.1115/gt2015-42156 ◽

2015 ◽

Author(s):

Rongqiao Wang ◽

Kanghe Jiang ◽

Fulei Jing ◽

Dianyin Hu ◽

Jun Song

Keyword(s):

Principal Component Analysis ◽

Single Crystal ◽

Slip Rate ◽

Principal Component ◽

Component Analysis ◽

Nickel Superalloys ◽

Strong Correlations ◽

Critical Plane ◽

Critical Plane Approach ◽

Life Model

A critical plane approach in combination with principal component analysis (PCA) for determining dominant damage factors (DDFs) was developed for single crystal nickel superalloys at elevated temperature. Maximum resolved shear stress (RSS), maximum slip rate and other 2 mesoscopic parameters on the critical plane, defined as the preferential slip plane, were selected as damage parameters. Correlation analysis results indicated that there were strong correlations (i.e. multicollinearity) among the selected parameters. To address this issue, PCA was performed to eliminate the effect of multicollinearity and the DDFs were determined as well. Based on the DDFs a life model was proposed and then validated by the fatigue experimental results. Most of the experimental lives are within the factor three of the predicted ones. The life model has a relatively simple form with reliable constants which facilitates the application in industry design.

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Outline of the Recent Consolidated Revision of EN13445-3, Clause 18 and Related Annexes: Detailed Assessment of Fatigue Life

Volume 1: Codes and Standards ◽

10.1115/pvp2019-93910 ◽

2019 ◽

Cited By ~ 1

Author(s):

Jürgen Rudolph ◽

Guy Baylac ◽

Ralf Trieglaff ◽

Rüdiger Gawlick ◽

Michael Krämer ◽

...

Keyword(s):

Finite Element ◽

Fatigue Life ◽

Assessment Method ◽

Structural Stress ◽

Critical Plane ◽

Fatigue Assessment ◽

European Working ◽

Critical Plane Approach ◽

Detailed Assessment

Abstract The European Pressure Vessel Standard EN 13445 (harmonized Standard acc. to PED 2014/68/EU) provides in its Part 3 (Design) a simplified method for fatigue assessment (Clause 17) and a detailed method of fatigue assessment (Clause 18). While the new revision of Clause 17 has already been adopted, Clause 18 “Detailed Assessment of Fatigue Life” is now available as a consolidated revision in inquiry phase. This major and comprehensive revision has been developed within the framework of the European working group CEN/TC 54/WG 53 – Design methods and constitutes a crucial step towards a modern and user-friendly engineering fatigue assessment method. The overall structure and amendments of Clause 18 are to be presented. All these amendments aim at a significant increase in user friendliness and clear guidelines for application. The following items are to be mentioned in that context: • Fatigue assessment of welded components based on structural stress and structural hot-spot stress approaches, • Detailed guidelines for determining relevant stresses and stress ranges, • Cycle counting proposals in the context of the fatigue assessment method including a critical plane approach. The fatigue assessment of welded components is separated from the fatigue assessment of un-welded parts as it has already been done in previous versions with respective methodological differences. Stress analyses for clause 18 are usually based on detailed finite element analyses (FEA). As an essential amendment for the user, the determination of structural stress ranges for the fatigue assessment of welds is further detailed in a new appropriate annex. Different applicable methods for the determination of structural stresses are explained in connection with the requirements of the finite element models and analyses. The cycle counting issue is comprehensively treated in the context of different design and operation situations (design transients, operational stress-time-histories). The description is detailed towards a critical plane approach. Detailed proposals for implementation in an algorithmic programming framework are given making the described methods ready to use.

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Multiaxial Fatigue Life Calculation Model for Engineering Components in Rolling-Sliding Contact

MATEC Web of Conferences ◽

10.1051/matecconf/201818802016 ◽

2018 ◽

Vol 188 ◽

pp. 02016

Author(s):

Robert Basan ◽

Tea Marohnić

Keyword(s):

Fatigue Life ◽

Complex Geometry ◽

Calculation Model ◽

Multiaxial Fatigue ◽

Sliding Contact ◽

Engineering Practice ◽

Critical Plane ◽

Principal Axes ◽

Critical Plane Approach ◽

Crack Initiation Criterion

Number of important engineering components and elements such as gears, rollers, bearings operate in conditions of rolling-sliding contact loading. Determination of fatigue lives of such components and elements is very important for engineering practice but remains quite chalenging task due to complex states of stress and strain in the material in the vicinity of contact (multiaxiality, non-proportionality, rotation of principal axes, mean compressive stress) as well as complex contact conditions such as loading amplitude, complex geometry of bodies in contact, type of lubrication, value of coefficient of friction, etc. Proposed fatigue life calculation model for cases of rolling-sliding contact is based on critical plane approach in the form of Fatemi-Socie crack initiation criterion. Developed model was implemented in the case of gears teeth flanks in mesh and compared with results and fatigue lives of gears reported in literature. Good agreement was determined confirming validity of developed model. Further advantage of presented approach and developed model is obtained information on critical location(s) and critical plane(s) orientation which can subsequently be used for estimation of crack shapes in initial phases of their growth and later damage type into which they can be expected to develop.

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