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Transcript of Fracture Mechanics-Brittle Fracture Fracture at Atomic Level Solid / Vapour Interfaces Boundaries in...
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2a
2b
A
s
sAr
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Fracture Mechanics-Brittle Fracture
Fracture at Atomic Level
Solid / Vapour Interfaces
Boundaries in Single Phase Solids
Interphase Interfaces in Solids
Interface Migration
Fracture Mechanics-Brittle Fracture
Fracture at Atomic Level
Solid / Vapour Interfaces
Boundaries in Single Phase Solids
Interphase Interfaces in Solids
Interface Migration
TopicsTopics 1
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Fracture Mechanics-Brittle fracture
Fracture mechanics is used to formulate quantitatively • The degree of Safety of a structure against brittle fracture
• The conditions necessary for crack initiation, propagation and arrest
• The residual life in a component subjected to dynamic/fatigue loading
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Fracture mechanics identifies three primary factors that control the susceptibility of a structure to brittle failure.
1. Material Fracture Toughness. Material fracture toughness may be defined as the ability to carry loads or deform plastically in the presence of a notch. It may be described in terms of the critical stress intensity factor, KIc, under a variety of conditions. (These terms and conditions are fully discussed in the following chapters.)
2. Crack Size. Fractures initiate from discontinuities that can vary from
extremely small cracks to much larger weld or fatigue cracks. Furthermore, although good fabrication practice and inspection can minimize the size and number of cracks, most complex mechanical components cannot be fabricated without discontinuities of one type or another.
Fracture Mechanics-Brittle fracture
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3. Stress Level. For the most part, tensile stresses are necessary for brittle fracture to occur. These stresses are determined by a stress analysis of the particular component.
Other factors such as temperature, loading rate, stress concentrations, residual stresses, etc., influence these three primary factors.
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Fracture at the Atomic level
Two atoms or a set of atoms are bonded together by cohesive energy or bond energy. Two atoms (or sets of atoms) are said to be fractured if the bonds between the two atoms (or sets of atoms) are broken by externally applied tensile load
Theoretical Cohesive Stress
If a tensile force ‘T’ is applied to separate the two atoms, then bond or cohesive energy is
(2.1)Where is the equilibrium spacing between two atoms.Idealizing force-displacement relation as one half of sine wave
(2.2)
ox
Tdx
x
o
x
CT sin( )
+ +
xo
BondEnergy
CohesiveForce
EquilibriumDistance xo
Pot
ent
ialE
nerg
y
Distance
Repulsion
Attraction
Tension
Compression
App
lied
For
ce
k
BondEnergy
Distance
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Assuming that the origin is defined at and for small displacement relationship is assumed to be linear such that Hence force-displacement relationship is given by
(2.2)
Bond stiffness ‘k’ is given by
(2.3)
If there are n bonds acing per unit area and assuming as gage length and multiplying eq. 2.3 by n then ‘k’ becomes young’s modulus and becomes cohesive stress such that
(2.4)
Or (2.5)
If is assumed to be approximately equal to the atomic spacing
oxx
xsin( )
C
xT T
CT
k
ox
oxCTCs
co
Exs
c
Es
Theoretical Cohesive Stress (Contd.)
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Theoretical Cohesive Stress (Contd.)
The surface energy can be estimated as
(2.6)
The surface energy per unit area s equal to one half the fracture energy because two surfaces are created when a material fractures. Using eq. 2.4 in to eq.2.6
(2.7)
x12
s C C0
sin dx
s s
s
C
o
Exs
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Inglis (1913) analyzed for the flat plate with an elliptical hole with major axis 2a and minor axis 2b, subjected to far end stress The stress at the tip of the major axis (point A) is given by (2.8)
The ratio is defined as the stress concentration factor, When a = b, it is a circular hole, then When b is very very small, Inglis define radius of curvature as (2.9)
And the tip stress as
(2.10)
2a
2b
A
s
sAr
s
A
2a1
b s s
Ass
tk
tk 3.
2ba
r
A
a1 a s s r
Fracture stress for realistic material
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Fracture stress for realistic material (contd.)
When a >> b eq. 2.10 becomes
(2.11)
For a sharp crack, a >>> b, and stress at the crack tip tends to Assuming that for a metal, plastic deformation is zero and the sharpest crack may have root radius as atomic spacing then the stress is given by (2.12)
When far end stress reaches fracture stress , crack propagates and the stress at A reaches cohesive stress then using eq. 2.7
(2.13)
This would
A
a2
s s r
0r
oxr
Ao
a2
x
s s
A Cs sfs s
1/ 2
sf
E
4a
s
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Griffith’s Energy balance approach
•First documented paper on fracture (1920) Considered as father of Fracture Mechanics
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A A Griffith laid the foundations of modern fracture mechanics by designing
a criterion for fast fracture. He assumed that pre-existing flaws propagate
under the influence of an applied stress only if the total energy of the
system is thereby reduced. Thus, Griffith's theory is not concerned with
crack tip processes or the micromechanisms by which a crack advances.
Griffith’s Energy balance approach (Contd.)
2a
X
Y
B
s
s
Griffith proposed that ‘There is a simple energy
balance consisting of the decrease in potential
energy with in the stressed body due to crack
extension and this decrease is balanced by
increase in surface energy due to increased
crack surface’
Griffith theory establishes theoretical
strength of brittle material and relationship
between fracture strength and flaw size
‘a’
fs
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2a
X
Y
B
s
s
Griffith’s Energy balance approach (Contd.)
The initial strain energy for the uncracked plate per thickness is (2.14)
On creating a crack of size 2a, the tensile force on an element ds on elliptic hole is relaxed from to zero. The elastic strain energy released per unit width due to introduction of a crack of length 2a is given by
(2.15)
2
iA
U dA2E
s
a1
a 20
U 4 dx v s
dxs
where displacement
v a sinEs usin g x a cos
2 2
a
aU
Es
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Griffith’s Energy balance approach (Contd.)
2a
X
Y
B
s
s
External work = (2.16)
The potential or internal energy of the body is
Due to creation of new surface increase in surface energy is (2.17)
The total elastic energy of the cracked plate is
(2.18)
wU Fdy,
where F= resultant force = area
=total relative displacement
s
p i a w U =U +U -U
s U = 4a
2 2 2
t sA
aU dA Fdy 4a
2E E s s
P1
P2
(a)
(a+d
a)
Load
,P
Displacement, v
Crack beginsto grow from
length (a)
Crack islonger by anincrement (da)
2 2
aa
UE
s
v
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Griffith’s Energy balance approach (Contd.)
Ene
rgy,
U
Cracklength, a
Surface Energy
U =
4a s
2 2
aa
UE
s
Elastic Strainenergy released
Total energy
Rat
es,G
, s
Potential energyrelease rate G =
Syrface energy/unitextension =
U
a
¶ ¶
Cracklength, a
ac
UnstableStable
(a)
(b)
(a) Variation of Energy with Crack length(b) Variation of energy rates with crack length
The variation of with crack extension should be minimum
Denoting as during fracture
(2.19)
for plane stress and
(2.20) for plane strain
tU
2t
s
dU 2 a0 4 0
da Es
fss1/ 2
sf
2Ea s
1/ 2
sf 2
2Ea(1 )
s
The Griffith theory is obeyed by materials which fail in a completely brittle elastic manner, e.g. glass, mica, diamond and refractory metals.
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Griffith’s Energy balance approach (Contd.)
Griffith extrapolated surface tension values of soda lime glass from
high temperature to obtain the value at room temperature as
Using value of E = 62GPa,The value of as 0.1
From the experimental study on spherical vessels he calculated
as 0.25 – 0.28
However, it is important to note that according to the Griffith theory,
it is impossible to initiate brittle fracture unless pre-existing defects
are present, so that fracture is always considered to be propagation-
(rather than nucleation-) controlled; this is a serious short-coming of
the theory.
2s 0.54J / m .
1/ 2
s2E
MPa m.
1/ 2
sc
2Ea
s
MPa m.
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Modification for Ductile MaterialsFor more ductile materials (e.g. metals and plastics) it is found that the functional form of the Griffith relationship is still obeyed, i.e. . However, the proportionality constant can be used to evaluate
s (provided E is known) and if this is done, one finds the value is many
orders of magnitude higher than what is known to be the true value of the surface energy (which can be determined by other means). For these materials plastic deformation accompanies crack propagation even though fracture is macroscopically brittle; The released strain energy is then largely dissipated by producing localized plastic flow at the crack tip. Irwin and Orowan modified the Griffith theory and came out with an expression
Where prepresents energy expended in plastic work. Typically for
cleavage in metallic materials p=104 J/m2 and s=1 J/m2. Since p>> s
we have
1/ 2
s pf
2E( )
a
s
1/ 2
pf
2E
a
s
1/ 2f as
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Strain Energy Release Rate
The strain energy release rate usually referred to
Note that the strain energy release rate is respect to crack length and most definitely not time. Fracture occurs when reaches a critical value which is denoted . At fracture we have so that
One disadvantage of using is that in order to determine it is necessary to know E as well as . This can be a problem with some materials, eg polymers and composites, where varies with composition and processing. In practice, it is usually more convenient to combine E and in a single fracture toughness parameter where . Then can be simply determined experimentally using procedures which are well established.
dUG
da
cGcG G
1/ 2
cf
1 EG
Y a s
cGfs
cG
cG
2c cK EGcK
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For LEFM the structure obeys Hooke’s law and global behavior is linear and if any local small scale crack tip plasticity is ignored
The fundamental principle of fracture mechanics is that the stress field around a crack tip being characterized by stress intensity factor K which is related to both the stress and the size of the flaw. The analytic development of the stress intensity factor is described for a number of common specimen and crack geometries below.
LINEAR ELASTIC FRACTURE MECHANICS (LEFM)
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Mode I - Opening mode: where the crack surfaces separate symmetrically with respect to the plane occupied by the crack prior to the deformation (results from normal stresses perpendicular to the crack plane);
Mode II - Sliding mode: where the crack surfaces glide over one another in opposite directions but in the same plane (results from in-plane shear); and
Mode III - Tearing mode: where the crack surfaces are displaced in the crack plane and parallel to the crack front (results from out-of-plane shear).
LINEAR ELASTIC FRACTURE MECHANICS (LEFM)
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In the 1950s Irwin [7] and coworkers introduced the concept of stress intensity factor, which defines the stress field around the crack tip, taking into account crack length, applied stress s and shape factor Y( which accounts for finite size of the component and local geometric features). The Airy stress function.In stress analysis each point, x,y,z, of a stressed solid undergoes
the stresses; sx sy, sz, txy, txz,tyz. With reference to figure 2.3,
when a body is loaded and these loads are within the same plane, say the x-y plane, two different loading conditions are possible:
LINEAR ELASTIC FRACTURE MECHANICS (Contd.)
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CrackPlane
ThicknessB
ThicknessB
s
s
s
s
sz sz
sz sza
Plane Stress Plane Strain
y
X
s
s
s
syy
1. plane stress (PSS), when the thickness of the body is comparable to the size of the plastic zone and a free contraction of lateral surfaces occurs, and,2. plane strain (PSN), when the specimen is thick enough to avoid contraction in the thickness z-direction.
LINEAR ELASTIC FRACTURE MECHANICS (Contd.)
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In the former case, the overall stress state is reduced to the three
components; sx, sy, xy, since; sz, xz, yz= 0, while, in the latter case,
a normal stress, sz, is induced which prevents the z
displacement, z = w = 0. Hence, from Hooke's law:
sz = (sx+sy) where is Poisson's ratio.For plane problems, the equilibrium conditions are:
If is the Airy’s stress function satisfying the biharmonic compatibility Conditions
¶¶
¶¶
¶¶
¶¶
s s x xy y xy
x y y x0 0 ;
4
0
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Then
For problems with crack tip Westergaard introduced Airy’s stress function as
Where Z is an analytic complex function
2 2 2
x y xy2 2, ,y x xy
¶ ¶ ¶ s s
¶ ¶ ¶
Re[ ] y Im[Z]Z
Z z z y z z x iybg Re[ ] Im[ ] ; = +
And are 2nd and 1st integrals of Z(z)Then the stresses are given by
Z,Z
2'
x 2
2'
y 2
2'
xy
'
Re[Z] y Im[Z ]y
Re[Z] y Im[Z ]x
y Im[Z ]xy
where Z =dZ dz
¶ s ¶
¶ s ¶¶ ¶
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Opening mode analysis or Mode I
Consider an infinite plate a crack of length 2a subjected to a biaxialState of stress. Defining:
Boundary Conditions :• At infinity • On crack faces x y xy| z | , 0 s s s
x xya x a;y 0 0 s
s
s
x
y
2a
s
2 2
zZ
z a
s
By replacing z by z+a , origin shifted to crack tip.
Zz a
z z a
s b gb g2
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And when |z|0 at the vicinity of the crack tip
KI must be real and a constant at the crack tip. This is due to a Singularity given by
The parameter KI is called the stress intensity factor for opening mode I.
Za
az
K
z
K a
I
I
s
s
2 2
1
z
Since origin is shifted to crack tip, it is easier to use polar Coordinates, Using
Further Simplification gives:
z ei
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Ix
Iy
Ixy
K 3cos 1 sin sin
2 2 22 r
K 3cos 1 sin sin
2 2 22 r
K 3sin cos cos
2 2 22 r
s s
Iij ij I
KIn general f and K Y a
2 r where Y = configuration factor
s s
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From Hooke’s law, displacement field can be obtained as
2I
2I
2(1 ) r 1u K cos sin
E 2 2 2 2
2(1 ) r 1v K sin cos
E 2 2 2 2
where u, v = displacements in x, y directions
(3 4 ) for plane stress problems
3 for plane strain problems
1
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The vertical displacements at any position along x-axis (is given by
The strain energy required for creation of crack is given by the work done by force acting on the crack face while relaxing the stress sto zero
2 2
22 2
v a x for plane stressE
(1 )v a x for plane strain
E
s
s
x
v
x
y
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a
2a a2 2 2 2
a a0 0
2 2
1 U Fv
2For plane stress For plane strain
(1 )U 4 a x dx U 4 a x dx
E E
a
E
s s s s
s 2 2 2
a
2 2 2
I I
2I
I
a (1 )
EThe strain energy release rate is given by G dU da
a (1 )aG = G =
E E
KG =
E
s
s s
2 2I
I
K (1 ) G =
E
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Sliding mode analysis or Mode 2
For problems with crack tip under shear loading, Airy’s stress function is taken as
Using Air’s definition for stresses
II y Re[Z]
2'
x 2
2'
y 2
2'
xy
2 Im[Z] y Re[Z ]y
y Re[Z ]x
Re[Z] y Im[Z ]xy
¶ s
¶
¶ s
¶¶
¶
y
2a
0
0
Using a Westergaard stress function of the form
0
2 2
zZ
z a
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Boundary Conditions :• At infinity • On crack faces x y xy 0| z | 0, s s
x xya x a;y 0 0 s With usual simplification would give the stresses as
IIx
IIy
IIxy
K 3cos cos 2 cos cos
2 2 2 22 r
K 3cos sin cos
2 2 22 r
K 3cos 1 sin sin
2 2 22 r
s s
Displacement components are given by
II
II
K ru (1 )sin 2 cos
E 2 2
K rv (1 )cos 2 cos
E 2 2
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II o
2I
I
2 2I
I
K a
KG = for plane stress
E
K (1 ) G = for plane strain
E
Tearing mode analysis or Mode 3
In this case the crack is displaced along z-axis. Here the displacements u and v are set to zero and hence
x y xy yx
xy yx yz zy
yzxz
2 22
2 2
0
w w and
x y
the equilibrium equation is written as
0 x y
Strain displacement relationship is given by
w ww 0
x y
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xy yz
Z
if w is taken as
1w Im[ ]
GThen
Im[Z ]; Re[Z ]
Using Westergaard stress functionas
0
2 2
0
z yz xy
yz 0
zZ
z a
where is the applied boundary shear stress
with the boundary conditions
on the crack face a x a;y 0 0
on the boundary x y ,
s
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IIIxz
IIIyz
x y xy
III
III o
The stresses are given by
Ksin
22 r
Kcos
22 r0
and displacements are given by
K 2rw sin
G 2
u v 0
K a
s s