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Meccanica
Erschienen in: Meccanica 2/2015

01.02.2015 | Experimental Solid Mechanics

A study into the interaction of intergranular cracking and cracking at a fastener hole

verfasst von: R. Jones, M. Lo, D. Peng, A. Bowler, M. Dorman, M. Janardhana, N. S. Iyyer

Erschienen in: Meccanica | Ausgabe 2/2015

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Abstract

This paper describes the results of a study into a new class of multi-site damage problems, viz: the interaction between multi-layer intergranular cracks and cracks that grow from small naturally occurring material discontinuities at a hole. The nature of the intergranular cracks, which are perhaps better thought of as delaminations rather than cracks, are chosen so as to approximate those found at fastener holes in RAAF AP3C (Orion) aircraft which arise due to ingress of the environment down the holes in the wing structure. The particular form of the multi-site damage studied involves two intergranular cracks (delaminations) that (in the vicinity of the hole) divide the plate thickness into thirds) interacting with cracks that emanate from the bore of the hole in a 7075-T6 aluminium plate.
We first determine the effect of the intergranular cracks (delaminations) on the stress field at the hole. We then evaluate the effect of these intergranular cracks on the stress intensity factors associated with cracks that emanate from small naturally occurring material discontinuities at the hole and then on the reduction in the time for a crack at a hole, with multi-layer intergranular cracking, to grow to a size where it will be readily detectable.
Vorheriger Artikel A combined analytic and experimental study of the displacement field in a circular ring
Nächster Artikel Novel optoelectronic laser interferometric microscope (OELIM) methodology for NDE of microsystems

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Fußnoten
1
Australian P3C aircraft are now referred to as AP3C.
 
2
This equation can be considered as a special case of the Nasgro equation [12], see Appendix.
 
3
FCA-301 corresponds to a location at the lower front spar adjacent to the wing root of the P-3C aircraft and FCA-351 and FCA-361 represent locations at the lower front spar inboard and outboard areas near the inboard engine respectively, see [1, 2] for more details. Location FCA-301 experiences mainly tension-dominated loading with a mean R≈0.11, whilst FCA-351 and FCA-361 experience a high degree of compressive loading. For FCA-361 the mean value of the R ratio is less than −0.55, see [3] for more details.
 
4
The link between Eq. (1) and the Nasgro equation [12] is discussed in the Appendix.
 
5
The crack growth equations presented in [20‐24] are similar in that they relate da/dN to (ΔK−ΔK th)2, see [5] for more details.
 
6
In [5, 7, 9, 17] it was explained that the term ΔK thr should not be confused with the term ΔK th, which the ASTM 647 test standard suggests (somewhat arbitrarily) to be the value of ΔK at a crack growth rate, da/dN, of 10−10 m/cycle.
 
7
Here the term small is defined as in ASTM E647 and the term long is as per the USAF Damage Tolerance Design Handbook [25].
 
8
An advantage of the weight function approach, which is also used in the crack growth program AFGROW, is that to obtain accurate solutions we only need to have an accurate stress solution.
 
9
This (initiating defect) size is consistent with the work of Merati [29], where it was found that the size of initial defects in civil transport aircraft lie in the range 0.009 to 0.029 mm and with the paper by Schijve [30] where it was reported that the size of initial defects in civil transport aircraft lie in the range 0.007 to 0.030 mm.
 
10
As previously mentioned fatigue critical locations FCA-351 and FCA-361 represent locations at the lower front spar inboard and outboard areas near the inboard engine respectively, see [1, 2].
 
11
The purpose of introducing the term ΔK eff was to collapse the various R ratio da/dN versus ΔK curves onto a single da/dN versus ΔK eff curve.
 
12
The value of p is often approximately 2 [5, 7‐10, 13‐15].
 
13
A value of λ=11 mm−1 is reported by Berretta et al. [16] for the growth of small cracks in a mild steel. A similar value was used in [9] for the growth of cracks from small naturally occurring material discontinuities in 7050-T7451.
 
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Metadaten
Titel
A study into the interaction of intergranular cracking and cracking at a fastener hole
verfasst von
R. Jones
M. Lo
D. Peng
A. Bowler
M. Dorman
M. Janardhana
N. S. Iyyer
Publikationsdatum
01.02.2015
Verlag
Springer Netherlands
Erschienen in
Meccanica / Ausgabe 2/2015
Print ISSN: 0025-6455
Elektronische ISSN: 1572-9648
DOI
https://doi.org/10.1007/s11012-013-9849-x

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