Investigation Of Damage Process Due To Fatigue On Heat Treated Aluminum 7075 With Effect Of Corrosion.
DECLARATION
I hereby declare that this report entitled “Investigation of damage process due to fatigue
on heat treated Aluminum 7075 with effect of corrosion” is the result of my own
research except as cited in the references.
Signature
: ……………………………………………..
Author’s Name: Mohd Fasihin b Abd Satar
Date
: 21th April 2010
APPROVAL
This report is submitted to the faculty of Manufacturing Engineering of UTem as a
partial fulfillment of the requirement for the degree of Bachelor of Manufacturing
Engineering (Material Engineering).
MOHD HAIDIR B. MASLAN
(PSM Supervisor)
ABSTRACT
The objective of this research are to investigate the damage process due to the fatigue
failure on heat treated aluminum alloy 7075 with the effect of corrosion. In these
research, the aluminum alloy 7075 been used because of it was the highest attainable
strength level of all forged alloy and have a good corrosion resistance. Moreover, the
aluminum alloy 7075 being used widely in automotive and aircraft industry. Many
research on this material behavior being discuss nowadays because of it is important in
safety and reliable. Many damaged from this material are related to the corrosion effect.
In this research, three condition of specimen being prepared. The specimens is non
heated, heated (T6 and RRA) and the heated (T6 and RRA) with effect of corrosion. The
sample been tested mechanically to investigate the damage process to the aluminum
alloy 7075. Here, the result of each specimen of tensile testing, hardness properties and
damaged due to the fatigue been discuss to investigate the damaged process. Then the
failure sample been cut and polished to investigate the microstructure properties and the
evolution of the grain boundary changed using optical microscope. From the analysis, it
showed the behavior of each type of specimen, the grain boundaries, and material
properties. The heated specimen score the best properties from the fatigue failure
followed corrosion specimen. The damaged in corrosion specimen is tend to crack faster
because of the attack in the pitting region had damaged the grain boundary and produce
starting tip that lead to the failure mechanism.
i
ABSTRAK
Tujuan utama kajian ini dilakukan adalah untuk mengkaji kegagalan lesu pada
aluminium aloi 7075 yang telah dibaiki sifatnya melalui pemanasan haba dengan kesan
pengaratan. Di dalam kajian ini, aluminium aloi telah dipilih kerana mempunyai tahap
kekuatan yang terbaik daripada kelasnya serta mempunyai sifat tahan pada pengaratan.
Tambahan pula, aluminium 7075 ini telah digunakan dengan meluas dalam industri
automobil dan penerbangan. Dewasa ini, banyak kajian telah dilakukan pada bahan ini
kerana kepentingannya terhadap keselamatan dan kebolehpercayaannya. Kebanyakan
kerosakan yang berlaku kepada bahan ini adalah disebabkan oleh kesan pengaratan.
Untuk kajian ini, tiga jenis keadaan sampel telah digunakan. Sampel tersebut adalah
tanpa pemanasan haba, dengan pemanasan haba dan sampel yang melalui pemanasan
haba tetapi dikaratkan. Sampel ini kemudiannya diuji secara mekanikal untuk mengkaji
proses kegagalan pada aluminum 7075. Disini, setiap data yang diperolehi melalui ujian
terikan, ujian kekerasan dan kegagalan pada ujian lesu telah dianalisis dan disiasat.
Kemudian, sampel tersebut telah dipotong dan dikilatkan supaya dapat mengkaji proses
kegagalan pada bahan melalui mikroskop. Daripada analisis yang dilakukan, ianya
menunjukkan sifat setiap sample, sempadan ira dan sifat bahan itu sendiri. Daripada data
yg diperolehi, sampel yg melalui proses pamanasan haba iaitu T6 dan RRA mempunyai
sifat bahan yang paling bagus. Manakala sampel berkarat lebih terdedah pada kegagalan
kerana kerosakan pada struktur bahan itu sendiri.
ii
AKNOWLEDGEMENT
Firstly, thankfull to Allah because of him, I finally finish my PSM II. I would like to
give my deepest thanks to my respective supervisor, Mr Haidir b.Maslan for helping and
giving me so much motivation and support to fulfill my this PSM report. It is a privilege
for me to complete my research as to fulfill my degree requirement.
Thanks also to my friend for supporting and helping me when I had faced with problem
during doing my PSM report. I appreciate all of their kind, and support to complete these
report. Hence, I would like to my housemate that really supported, sharing information
together amd always ready for helping me.
Lastly, I would like to thanks each and every individual that who have either directly or
indirectly helped me throughout the effort of this report be it in the form of
encouragement, advice or kind reminder. A special thanks to my beloved family
members, I extend my gratitude for their support, understanding and love.
iii
TABLE OF CONTENTS
ABSTRACT…………………………………………………………………………… i
ABSTRAK……………………………………………………………………………..ii
DEDICATION………………………………………………………………………...iii
ACKNOWLEDGEMENT……………………………………………………………..iv
TABLE OF CONTENT………………………………………………………………..v
LIST OF TABLE…………………………………………………………………......viii
LIST OF FIGURE…………………………………………………………………….ix
LIST OF ABBREVIATION…………………………………………………………..x
1.0 INTRODUCTION
1
1.1
Background
1
1.2
Statement of problem
2
1.3
Objective
3
1.4
Scope
4
2.0 LITERATURE REVIEW
5
2.1
Introduction
5
2.2
Aluminum alloy
6
2.2.1
Engineering use
7
2.2.2
Wrought Alloy
8
2.2.3
Wrought aluminum-zinc-magnesium alloy 7075
9
2.3
Introduction to Fatigue
11
2.3.1
Basic Concept
11
iv
2.3.2
Factor that effect fatigue
13
2.3.3
Characteristic of Fatigue
14
2.4
Corrosion
15
2.4.1
Pitting Corrosion
16
2.4.2
Galvanic Corrosion
17
2.4.3
Corrosion in Alumunum Alloy 7075
17
2.4.4
Solution Potential
18
2.4.5
Effect of Composition and Microstructure on Corrosion
19
2.4.6
Stress Corrosion Cracking
19
2.5
Heat Treatment
22
2.5.1
Basic Aluminum Heat Treatment Designations
22
2.5.2
Heat Treatment of Aluminum Alloy
25
2.5.2.1 Quenching
26
2.5.2.2 Age Hardening
27
2.5.2.3 T6 Temper
28
2.5.2.4 Introduction to Retrogression and Re-aging
29
3.0
METHODOLOGY
30
3.1
Introduction
30
3.2
Research Design
31
3.3
Material Composition
33
3.4
Heat Treatment process
33
3.4.1
Material Preparation
34
3.4.2
Sample preparation
34
3.4.3
T6 heat treatment process
35
3.4.4
Retrogression and Re aging
36
3.5
Corrosion Process
36
3.6
Fatigue
37
3.6.1
Degradation Analysis
38
v
3.7
Testing
40
3.7.1
Mechanical Testing
40
3.7.2
Tensile Test
40
3.7.3
Optical Microscope
41
3.7.4
Hardness Test
42
3.7.5
Fatigue Test
43
3.8
Analysis
44
4.0
RESULT AND DISCUSSION
45
4.1
Characterization of aluminum alloy
45
4.1.1
Non heated aluminum alloy 7075
46
4.1.2
T6 + RRa heat treatment
47
4.1.3
T6 + RRa heat treatment corrosion exposure
4.2
Hardness properties of heat treated aluminum alloy 7075
49
4.2.1
Hardness Properties
50
4.2
Tensile properties of the heat treatment process on AA 7075
52
4.2.1
Tensile Properties
52
48
4.2.2. Microstructure Properties for Tensile
58
4.3
Fatigue properties of aluminum alloys
60
4.3.1
Low Cycle Fatigue
60
4.3.2
High cycle fatigue
61
4.3.3
Fatigue properties on un-heated Aluminum Alloy 7075
62
4.3.4
Fatigue properties on heated Aluminum Alloy 7075
64
4.3.5
Fatigue properties on heated Aluminum Alloy 7075
67
with effect with corrosion
4.4
Comparison on fatigue failure for various conditions of
71
Aluminum Alloy 7075
vi
5.0
CONCLUSION AND RECOMMENDATION
76
5.1
Conclusion
76
5.2
Recommendations
79
REFERENCES
80
APPENDICES
A
Gantt chart for PSM I and II
B
Tensile
C
Fatigue
D
Hardness
E
Microstructure
vii
LIST OF TABLE
Table 2.1 : Properties of Aluminum Alloy
10
Table 2.2 : Type of fatigue stress
12
Table 2.3: Basic Temper Designation
23
Table 2.4: Subdivisions of “T” Temper Heat Treatable Alloys
24
Table 2.5: Subdivisions of “H” Temper Heat Treatable Alloys
24
Table 4.1 : List of hardness value of each specimens
50
Table 4.2 : List of the results for Load at Break, Young Modulus, Maximum
53
Load, Tensile Stress at maximum Load and Elongation to break for
Tensile Test
Table 4.3: Fatigue test data for heated Aluminum Alloy 7075
65
Table 4.4: Fatigue test data for heated Aluminum Alloy 7075 with effect of
68
corrosion
Table 4.5: Comparison for different condition AL7075 on the number of cycles
71
for failed, rate of Young Modulus drop, and value of Young Modulus
viii
LIST OF FIGURES
Figure 2.1:The formation of salt bridge of corrosion
16
Figure 3.1: Process sequence for the whole project
31
Figure 3.2: Experimental flow chart of the whole research
32
Figure 3.3: Specimen been immersed in the EXCO solution
37
Figure 3.4: Specimen dimension for Fatigue test
38
Figure 3.5 :Pitting damage in the aluminum showing flat bottomed
39
pit development
Figure 3.6 :SEM picture of initiation pit cluster produced
39
Figure 3.7: Universal testing Machine
41
Figure 3.8: Specimen dimension for tensile test
41
Figure 3.9: Optical microscope
42
Figure 3.10: Rockwell Hardness testing Machine
43
Figure 3.11: Instron fatigue machine
43
Figure 3.12 : The initiation phase in the fatigue testing
44
Figure 4.1 :Microstructure of non heated AA7075 using optical microscope
46
Figure 4.2 :Microstructure of heated AA7075 using optical microscope
47
Figure 4.3 :Microstructure of corrosion AA7075 using optical microscope
49
Figure 4.4: The comparison of hardness value between each specimens
50
Figure 4.5: Tensile graph for un-heated and heated (T6-RRA) aluminum
52
alloy 7075
Figure 4.6: The result for elongation to break of the AA7075 with different
54
condition.
Figure 4.7: The result for the tensile strength of the AA7075 with different
55
condition
Figure 4.8: The result for the Young’s Modulus of the AA7075 with different
56
ix
condition
Figure 4.9: The result for the yield strength of the AA7075 with different
57
condition.
Figure 4.10: Microstructure for un-heated tensile aluminum alloy 7075
58
Figure 4.11: Microstructure for heated (T6-RRA) tensile aluminum alloy 7075
58
Figure 4.1 : Microstructure for corrosion (T6-RRA) tensile aluminum
59
alloy 7075
Figure 4.13 : The crack of low cycle fatigue in tested sample of AA7075
60
Figure 4.14: Crack of high cycle fatigue in tested sample of AA7075
62
Figure 4.15: Graph of Young Modulus Vs Num. of Cycles for un-heated
63
Aluminum Alloy 7075
Figure 4.16 : Microstructure of non-heated AA7075
63
Figure 4.17: Graph of Young Modulus Vs Num. of Cycles for heated
66
Aluminum Alloy 7075
Figure 4.18 : Microstructure fatigue failure of heated AA7075
67
Figure 4.19: Graph of Young Modulus Vs Num. of Cycles for corrosion
69
Aluminum Alloy 7075
Figure 4.20 : Microstructure of corrosion effect AA7075 at the center
70
of specimen.
Figure 4.21 : Microstructure of corrosion effect AA7075 at the edge of specimen. 70
Figure 4.22: Graph of Young Modulus Vs Num. of Cycles for un-heated
72
and heated Aluminum Alloy 7075
Figure 4.23: Shows schematically a portion of the surface containing a
74
flaw before and after load application.
x
LIST OF ABBREVIATIONS, SYMBOLS, SPECIALIZED
NOMENCLATURE
A
-Cross sectional area
AA
-Aluminum Alloy
Al
-Aluminum
ASTM
-American Standard Test Method
Cº
-Degree Celsius
CF
-Corrosion Fatigue
CFCP
-Corrosion Fatigue Crack Propagation
Cr
-Chromium
Cu
-Copper
E
-Young Modulus
EXCO
-Exfoliation Corrosion
Fe
-Ferrous
GP
-Guiner Preston Zones
HNO3
- Nitric Acid
Hr
-Hour
HT
-Heat Treatment
KNO3
-Potassium Nitride
L
-Length
Mg
-Magnesium
Mn
-Manganese
Mpa
-Mega Pascal
N
-Newton
NaCl
-Sodium Chloride
RRA
-Retrogression and Re-ageing
SCC
-Stress Corrosion Cracking
SSSS
-Super Saturated Solid Solution
SHT
-Solution Heat Treatment
xi
T
-Temper
Wt. %
-Weight of percentages
Zn
-Zinc
σ
-Stress
ε
-Strain
η
-Stable MgZn2
η’
- Metastable precipitation
xii
CHAPTER 1
INTRODUCTION
1.1
Background of Project
Engineering system may fail in many different ways. If only the behavior of the
structural members is considered, some of the damage will occur such as large elastic or
inelastic deformation, buckling, loss of bonds in material structure and others. The
treatment of corrosion 7075 aluminum alloy fracture process by numerical technique is
the aim for this research, and it is therefore worthwhile to look at the phenomenological
aspect of fracture process before it start to failure.
One of the most striking origin for the failure is metal fatigue. It is the result of
application of load variations the properties of metallic material can change. These
change would be observe on a micro scale (dislocation formation and movement) and
macro scale (growth of defect). Depending on the scale of observation we can
distinguish between damage process and crack process. In general, a region can be
indicated that can be discussed using arguments applicable to the micro domain as well
as using argument from the macro regime.
1
1.2
Problem Statement
Aluminum Alloy 7075 been used widely in aircraft technology because of it properties.
Year by year, the discussion about the capabilities of this 7075 Aluminum Alloy been
discussed widely among scientist and manufacturer. In the aircraft design the safe
service life of metallic components subjected to fatigue load and corrosion effect can be
demonstrate by adopting the Safe Life concept (Brit, H.J.et al., 2002). This paper
describes work on the effect of corrosion on the fatigue and fracture behaviour of a
7178-T6 aluminum alloy Although a substantial work has been reported on heat
treatment and recrystallization behavior of 7xxx series aluminum alloys a limited studies
have been reported on fracture and impact-toughness behavior of the alloys by use of
impact test especially on sheet and plate that have small thickness. This research paper,
reports a comparative analysis of tensile and fatigue behavior of cold-worked and
recrystallized 7075 aluminum alloy.
The 7xxx series aluminum alloys have been widely used as structural materials due to
their attractive comprehensive properties, such as low density, high strength, ductility,
toughness and resistance to fatigue. The 7075 aluminum alloy is one of the most
important engineering alloys and has been utilized extensively in aircraft structures
because of its high strength-to-density ratio. Metal alloys, which have undergone
extensive plastic deformation by rolling or extrusion, exhibit a significant anisotropy of
mechanical properties. Even in the case of untextured metals showing isotropic or
almost isotropic yielding behavior, ductility can be very anisotropic.
Corrosion damage is often found on structural components subjected to fatigue loading.
Many structures are expected to endure long lives while exposed to corrosive
environments. It is well known that corrosion and fatigue damage can occur
simultaneously and they have a combined effect much more severe than each one
occurring on its own [3,5–7]. However, even the simpler problem of fatigue cracks
initiating from preexisting corrosion damage is still not well understood. One of the
2
major objectives of the current investigation is to determine an appropriate methodology
for assessing the remaining fatigue life of an aircraft or similar component containing
corrosion damage (Mohammad et al, 2001).
The corrosion fatigue life of structural elements could be divided into two phases: the
corrosion fatigue crack initiation life and the corrosion fatigue crack propagation
(CFCP) life to be investigated. The CFCP life of typical structure elements is a portion
of total corrosion fatigue and especially for large structure elements, is dominant. In
addition, the CFCP rate is based on damage tolerance design of typical structure
elements in a corrosive environment using a fracture mechanics approach. Therefore,
more attention has been paid to CFCP rate investigations in steels and aluminum alloys.
It is recognized that the CFCP mechanism is similar to those proposed for stress
corrosion cracking. The CFCP rate is regarded as an enhanced crack propagation rate
promoted in a certain corrosive environment by cyclic loading (Wang, 1996).
1.3
Objective
The objectives of this project are:
a) To investigated the Damage Process due to Fatigue on Heat Treated Aluminum
7075 with effect of the corrosion.
b) To study the changing in mechanical properties in AA7075 as a result from the
mechanical testing.
c) To understand the phenomenons of failure process just before it start to form a
crack or damage.
d) To study the Young’s Modulus of the material and to related it with the damaged
of material
3
1.4
Scope
To ensure the objective was successfully achieved, there are several elements that
needed to follow as well.
a) The understanding of the physical and mechanical characteristic of aluminum
alloy of 7075 series.
b) The behavior of fatigue failure process in AA7075 in effect of corrosion.
c) The study of retrogression and re-ageing (RRA) treatment process that suitable
for the AA7075.
d) Some of mechanical testing must be carried out for investigate the tensile,
hardness and fracture properties of the aluminum alloy 7075.
e) The damage process of AA7075 after being pointed with the load in mechanical
testing.
f) To investigate the influence of fatigue damage due to the corrosion effect on the
AA7075.
4
CHAPTER 2
LITERATURE REVIEW
2.1
Introduction
7xxx series aluminum alloy are widely use in automotive and aircraft industry due to
their high strength to density ratio. Such as AA7075 with T6 heat treatment process can
reach their peak strength through proper T6 aging treatment. However they are very
susceptible to intergranular stress corrosion cracking (SCC) in the T6 temper, especially
in chloride-containing media in the short transverse direction of thick section. Overaging
treatments (like T73 temper) were develop to improve the short transverse SCC
resistance by increasing the grain boundary precipitate size and spacing, but with some
reduction of tensile strength from the T6 temper.
However , it cannot be assumed that alloy and temper with goo SCC resistance would
show good resistance to corrosion fatigue (CF) as CF failure from aluminum alloy are
characteristically transgranular. For example Jacko and Duquette reported that no
significant different in total fatigue lives could be detected between 7075-T6 and T73
aluminum alloy when they were tested in the form of smooth axial fatigue specimens in
aerated 0.5 N NaCL solution.
This chapter will explain general information that related to the work. We will discuss
about the aluminum alloy and it wrought which will choose to determine the material
and heat treatment that used. When aluminum alloy being heat treatment, it basically
5
will strengthen their hardness, tensile strength and electrical conductivity that make it
more suitable for the manufacture of aircraft components.
Moreover, this chapter will explain about the fatigue which includes how the process of
fatigue failure happen from the S-N curve observation and basic term in corrosion that
effect the crack propagation process. There also will explain about S-N curve and factor
that affect the fatigue life
2.2
Aluminum Alloy
Aluminum alloys are mixtures of aluminum with other metals (called an alloy), often
with copper, zinc, manganese, silicon, or magnesium. They are much lighter and more
corrosion resistant than plain carbon steel, but not as corrosion resistant as pure
aluminum. Bare aluminum alloy surfaces will keep their apparent shine in a dry
environment due to the formation of a clear, protective oxide layer. Galvanic corrosion
can be rapid when aluminum alloy is placed in electrical contact with stainless steel, or
other metals with a more negative corrosion potential than the aluminum alloy, in a wet
environment. Aluminum alloy and stainless steel parts should only be used together in
water-containing systems or outdoor installations if provision is made for either
electrical or electrolytic isolation between the two metals.
Aluminum alloy compositions are registered with the Aluminum Association. Many
organizations publish more specific standards for the manufacture of aluminum alloy,
including the Society of Automotive Engineers standards organization, specifically its
aerospace standards subgroups, and ASTM International.
6
2.2.1
Engineering use
Aluminum alloys with a wide range of properties are used in engineering structures.
Alloy systems are classified by a number system (ANSI) or by names indicating their
main alloying constituents (DIN and ISO). Selecting the right alloy for a given
application entails considerations of strength, ductility, formability, weldability and
corrosion resistance to name a few. A brief historical overview of alloys and
manufacturing technologies is given in Ref.[2] Aluminum is used extensively in modern
aircraft due to its high strength to weight ratio.
Improper use of aluminum may result in problems, particularly in contrast to iron or
steel, which appear "better behaved" to the intuitive designer, mechanic, or technician.
The reduction by two thirds of the weight of an aluminum part compared with a
similarly sized iron or steel part seems enormously attractive, but it must be noted that
this replacement is accompanied by a reduction by two thirds in the stiffness of the part
(Miller et al, 2002). Therefore, although direct replacement of an iron or steel part with a
duplicate made from aluminum may still give acceptable strength to withstand peak
loads, the increased flexibility will cause three times more deflection in the part.
Where failure is not an issue but excessive flex is undesirable due to requirements for
precision of location, or efficiency of transmission of power, simple replacement of steel
tubing with similarly sized aluminum tubing will result in a degree of flex which is
undesirable; for instance, the increased flex under operating loads caused by replacing
steel bicycle frame tubing with aluminum tubing of identical dimensions will cause
misalignment of the power-train as well as absorbing the operating force. To increase
the rigidity by increasing the thickness of the walls of the tubing increases the weight
proportionately, so that the advantages of lighter weight are lost as the rigidity is
restored.
7
2.2.2
Wrought alloys
The International Alloy Designation System is the most widely accepted naming scheme
for wrought alloys. Each alloy is given a four-digit number, where the first digit
indicates the major alloying elements.
1000 series are essentially pure aluminum with a minimum 99% aluminum
content by weight and can be work hardened
2000 series are alloyed with copper, can be precipitation hardened to strengths
comparable to steel. Formerly referred to as duralumin, they were once the most
common aerospace alloys, but were susceptible to stress corrosion cracking and
are increasingly replaced by 7000 series in new designs.
4000 series are alloyed with silicon. They are also known as silumin.
3000 series are alloyed with manganese, and can be work-hardened.
5000 series are alloyed with magnesium, derive most of their strength from work
hardening. It is suitable for cryogenic applications and low temperature work.
However is susceptible to corrosion above 60°C.
6000 series are alloyed with magnesium and silicon, are easy to machine, and
can be precipitation-hardened, but not to the high strengths that 2000, and 7000
can reach.
highest strengths of any aluminum alloy.
7000 series are alloyed with zinc, and can be precipitation hardened to the
8000 series is a category mainly used for lithium alloys
8
I hereby declare that this report entitled “Investigation of damage process due to fatigue
on heat treated Aluminum 7075 with effect of corrosion” is the result of my own
research except as cited in the references.
Signature
: ……………………………………………..
Author’s Name: Mohd Fasihin b Abd Satar
Date
: 21th April 2010
APPROVAL
This report is submitted to the faculty of Manufacturing Engineering of UTem as a
partial fulfillment of the requirement for the degree of Bachelor of Manufacturing
Engineering (Material Engineering).
MOHD HAIDIR B. MASLAN
(PSM Supervisor)
ABSTRACT
The objective of this research are to investigate the damage process due to the fatigue
failure on heat treated aluminum alloy 7075 with the effect of corrosion. In these
research, the aluminum alloy 7075 been used because of it was the highest attainable
strength level of all forged alloy and have a good corrosion resistance. Moreover, the
aluminum alloy 7075 being used widely in automotive and aircraft industry. Many
research on this material behavior being discuss nowadays because of it is important in
safety and reliable. Many damaged from this material are related to the corrosion effect.
In this research, three condition of specimen being prepared. The specimens is non
heated, heated (T6 and RRA) and the heated (T6 and RRA) with effect of corrosion. The
sample been tested mechanically to investigate the damage process to the aluminum
alloy 7075. Here, the result of each specimen of tensile testing, hardness properties and
damaged due to the fatigue been discuss to investigate the damaged process. Then the
failure sample been cut and polished to investigate the microstructure properties and the
evolution of the grain boundary changed using optical microscope. From the analysis, it
showed the behavior of each type of specimen, the grain boundaries, and material
properties. The heated specimen score the best properties from the fatigue failure
followed corrosion specimen. The damaged in corrosion specimen is tend to crack faster
because of the attack in the pitting region had damaged the grain boundary and produce
starting tip that lead to the failure mechanism.
i
ABSTRAK
Tujuan utama kajian ini dilakukan adalah untuk mengkaji kegagalan lesu pada
aluminium aloi 7075 yang telah dibaiki sifatnya melalui pemanasan haba dengan kesan
pengaratan. Di dalam kajian ini, aluminium aloi telah dipilih kerana mempunyai tahap
kekuatan yang terbaik daripada kelasnya serta mempunyai sifat tahan pada pengaratan.
Tambahan pula, aluminium 7075 ini telah digunakan dengan meluas dalam industri
automobil dan penerbangan. Dewasa ini, banyak kajian telah dilakukan pada bahan ini
kerana kepentingannya terhadap keselamatan dan kebolehpercayaannya. Kebanyakan
kerosakan yang berlaku kepada bahan ini adalah disebabkan oleh kesan pengaratan.
Untuk kajian ini, tiga jenis keadaan sampel telah digunakan. Sampel tersebut adalah
tanpa pemanasan haba, dengan pemanasan haba dan sampel yang melalui pemanasan
haba tetapi dikaratkan. Sampel ini kemudiannya diuji secara mekanikal untuk mengkaji
proses kegagalan pada aluminum 7075. Disini, setiap data yang diperolehi melalui ujian
terikan, ujian kekerasan dan kegagalan pada ujian lesu telah dianalisis dan disiasat.
Kemudian, sampel tersebut telah dipotong dan dikilatkan supaya dapat mengkaji proses
kegagalan pada bahan melalui mikroskop. Daripada analisis yang dilakukan, ianya
menunjukkan sifat setiap sample, sempadan ira dan sifat bahan itu sendiri. Daripada data
yg diperolehi, sampel yg melalui proses pamanasan haba iaitu T6 dan RRA mempunyai
sifat bahan yang paling bagus. Manakala sampel berkarat lebih terdedah pada kegagalan
kerana kerosakan pada struktur bahan itu sendiri.
ii
AKNOWLEDGEMENT
Firstly, thankfull to Allah because of him, I finally finish my PSM II. I would like to
give my deepest thanks to my respective supervisor, Mr Haidir b.Maslan for helping and
giving me so much motivation and support to fulfill my this PSM report. It is a privilege
for me to complete my research as to fulfill my degree requirement.
Thanks also to my friend for supporting and helping me when I had faced with problem
during doing my PSM report. I appreciate all of their kind, and support to complete these
report. Hence, I would like to my housemate that really supported, sharing information
together amd always ready for helping me.
Lastly, I would like to thanks each and every individual that who have either directly or
indirectly helped me throughout the effort of this report be it in the form of
encouragement, advice or kind reminder. A special thanks to my beloved family
members, I extend my gratitude for their support, understanding and love.
iii
TABLE OF CONTENTS
ABSTRACT…………………………………………………………………………… i
ABSTRAK……………………………………………………………………………..ii
DEDICATION………………………………………………………………………...iii
ACKNOWLEDGEMENT……………………………………………………………..iv
TABLE OF CONTENT………………………………………………………………..v
LIST OF TABLE…………………………………………………………………......viii
LIST OF FIGURE…………………………………………………………………….ix
LIST OF ABBREVIATION…………………………………………………………..x
1.0 INTRODUCTION
1
1.1
Background
1
1.2
Statement of problem
2
1.3
Objective
3
1.4
Scope
4
2.0 LITERATURE REVIEW
5
2.1
Introduction
5
2.2
Aluminum alloy
6
2.2.1
Engineering use
7
2.2.2
Wrought Alloy
8
2.2.3
Wrought aluminum-zinc-magnesium alloy 7075
9
2.3
Introduction to Fatigue
11
2.3.1
Basic Concept
11
iv
2.3.2
Factor that effect fatigue
13
2.3.3
Characteristic of Fatigue
14
2.4
Corrosion
15
2.4.1
Pitting Corrosion
16
2.4.2
Galvanic Corrosion
17
2.4.3
Corrosion in Alumunum Alloy 7075
17
2.4.4
Solution Potential
18
2.4.5
Effect of Composition and Microstructure on Corrosion
19
2.4.6
Stress Corrosion Cracking
19
2.5
Heat Treatment
22
2.5.1
Basic Aluminum Heat Treatment Designations
22
2.5.2
Heat Treatment of Aluminum Alloy
25
2.5.2.1 Quenching
26
2.5.2.2 Age Hardening
27
2.5.2.3 T6 Temper
28
2.5.2.4 Introduction to Retrogression and Re-aging
29
3.0
METHODOLOGY
30
3.1
Introduction
30
3.2
Research Design
31
3.3
Material Composition
33
3.4
Heat Treatment process
33
3.4.1
Material Preparation
34
3.4.2
Sample preparation
34
3.4.3
T6 heat treatment process
35
3.4.4
Retrogression and Re aging
36
3.5
Corrosion Process
36
3.6
Fatigue
37
3.6.1
Degradation Analysis
38
v
3.7
Testing
40
3.7.1
Mechanical Testing
40
3.7.2
Tensile Test
40
3.7.3
Optical Microscope
41
3.7.4
Hardness Test
42
3.7.5
Fatigue Test
43
3.8
Analysis
44
4.0
RESULT AND DISCUSSION
45
4.1
Characterization of aluminum alloy
45
4.1.1
Non heated aluminum alloy 7075
46
4.1.2
T6 + RRa heat treatment
47
4.1.3
T6 + RRa heat treatment corrosion exposure
4.2
Hardness properties of heat treated aluminum alloy 7075
49
4.2.1
Hardness Properties
50
4.2
Tensile properties of the heat treatment process on AA 7075
52
4.2.1
Tensile Properties
52
48
4.2.2. Microstructure Properties for Tensile
58
4.3
Fatigue properties of aluminum alloys
60
4.3.1
Low Cycle Fatigue
60
4.3.2
High cycle fatigue
61
4.3.3
Fatigue properties on un-heated Aluminum Alloy 7075
62
4.3.4
Fatigue properties on heated Aluminum Alloy 7075
64
4.3.5
Fatigue properties on heated Aluminum Alloy 7075
67
with effect with corrosion
4.4
Comparison on fatigue failure for various conditions of
71
Aluminum Alloy 7075
vi
5.0
CONCLUSION AND RECOMMENDATION
76
5.1
Conclusion
76
5.2
Recommendations
79
REFERENCES
80
APPENDICES
A
Gantt chart for PSM I and II
B
Tensile
C
Fatigue
D
Hardness
E
Microstructure
vii
LIST OF TABLE
Table 2.1 : Properties of Aluminum Alloy
10
Table 2.2 : Type of fatigue stress
12
Table 2.3: Basic Temper Designation
23
Table 2.4: Subdivisions of “T” Temper Heat Treatable Alloys
24
Table 2.5: Subdivisions of “H” Temper Heat Treatable Alloys
24
Table 4.1 : List of hardness value of each specimens
50
Table 4.2 : List of the results for Load at Break, Young Modulus, Maximum
53
Load, Tensile Stress at maximum Load and Elongation to break for
Tensile Test
Table 4.3: Fatigue test data for heated Aluminum Alloy 7075
65
Table 4.4: Fatigue test data for heated Aluminum Alloy 7075 with effect of
68
corrosion
Table 4.5: Comparison for different condition AL7075 on the number of cycles
71
for failed, rate of Young Modulus drop, and value of Young Modulus
viii
LIST OF FIGURES
Figure 2.1:The formation of salt bridge of corrosion
16
Figure 3.1: Process sequence for the whole project
31
Figure 3.2: Experimental flow chart of the whole research
32
Figure 3.3: Specimen been immersed in the EXCO solution
37
Figure 3.4: Specimen dimension for Fatigue test
38
Figure 3.5 :Pitting damage in the aluminum showing flat bottomed
39
pit development
Figure 3.6 :SEM picture of initiation pit cluster produced
39
Figure 3.7: Universal testing Machine
41
Figure 3.8: Specimen dimension for tensile test
41
Figure 3.9: Optical microscope
42
Figure 3.10: Rockwell Hardness testing Machine
43
Figure 3.11: Instron fatigue machine
43
Figure 3.12 : The initiation phase in the fatigue testing
44
Figure 4.1 :Microstructure of non heated AA7075 using optical microscope
46
Figure 4.2 :Microstructure of heated AA7075 using optical microscope
47
Figure 4.3 :Microstructure of corrosion AA7075 using optical microscope
49
Figure 4.4: The comparison of hardness value between each specimens
50
Figure 4.5: Tensile graph for un-heated and heated (T6-RRA) aluminum
52
alloy 7075
Figure 4.6: The result for elongation to break of the AA7075 with different
54
condition.
Figure 4.7: The result for the tensile strength of the AA7075 with different
55
condition
Figure 4.8: The result for the Young’s Modulus of the AA7075 with different
56
ix
condition
Figure 4.9: The result for the yield strength of the AA7075 with different
57
condition.
Figure 4.10: Microstructure for un-heated tensile aluminum alloy 7075
58
Figure 4.11: Microstructure for heated (T6-RRA) tensile aluminum alloy 7075
58
Figure 4.1 : Microstructure for corrosion (T6-RRA) tensile aluminum
59
alloy 7075
Figure 4.13 : The crack of low cycle fatigue in tested sample of AA7075
60
Figure 4.14: Crack of high cycle fatigue in tested sample of AA7075
62
Figure 4.15: Graph of Young Modulus Vs Num. of Cycles for un-heated
63
Aluminum Alloy 7075
Figure 4.16 : Microstructure of non-heated AA7075
63
Figure 4.17: Graph of Young Modulus Vs Num. of Cycles for heated
66
Aluminum Alloy 7075
Figure 4.18 : Microstructure fatigue failure of heated AA7075
67
Figure 4.19: Graph of Young Modulus Vs Num. of Cycles for corrosion
69
Aluminum Alloy 7075
Figure 4.20 : Microstructure of corrosion effect AA7075 at the center
70
of specimen.
Figure 4.21 : Microstructure of corrosion effect AA7075 at the edge of specimen. 70
Figure 4.22: Graph of Young Modulus Vs Num. of Cycles for un-heated
72
and heated Aluminum Alloy 7075
Figure 4.23: Shows schematically a portion of the surface containing a
74
flaw before and after load application.
x
LIST OF ABBREVIATIONS, SYMBOLS, SPECIALIZED
NOMENCLATURE
A
-Cross sectional area
AA
-Aluminum Alloy
Al
-Aluminum
ASTM
-American Standard Test Method
Cº
-Degree Celsius
CF
-Corrosion Fatigue
CFCP
-Corrosion Fatigue Crack Propagation
Cr
-Chromium
Cu
-Copper
E
-Young Modulus
EXCO
-Exfoliation Corrosion
Fe
-Ferrous
GP
-Guiner Preston Zones
HNO3
- Nitric Acid
Hr
-Hour
HT
-Heat Treatment
KNO3
-Potassium Nitride
L
-Length
Mg
-Magnesium
Mn
-Manganese
Mpa
-Mega Pascal
N
-Newton
NaCl
-Sodium Chloride
RRA
-Retrogression and Re-ageing
SCC
-Stress Corrosion Cracking
SSSS
-Super Saturated Solid Solution
SHT
-Solution Heat Treatment
xi
T
-Temper
Wt. %
-Weight of percentages
Zn
-Zinc
σ
-Stress
ε
-Strain
η
-Stable MgZn2
η’
- Metastable precipitation
xii
CHAPTER 1
INTRODUCTION
1.1
Background of Project
Engineering system may fail in many different ways. If only the behavior of the
structural members is considered, some of the damage will occur such as large elastic or
inelastic deformation, buckling, loss of bonds in material structure and others. The
treatment of corrosion 7075 aluminum alloy fracture process by numerical technique is
the aim for this research, and it is therefore worthwhile to look at the phenomenological
aspect of fracture process before it start to failure.
One of the most striking origin for the failure is metal fatigue. It is the result of
application of load variations the properties of metallic material can change. These
change would be observe on a micro scale (dislocation formation and movement) and
macro scale (growth of defect). Depending on the scale of observation we can
distinguish between damage process and crack process. In general, a region can be
indicated that can be discussed using arguments applicable to the micro domain as well
as using argument from the macro regime.
1
1.2
Problem Statement
Aluminum Alloy 7075 been used widely in aircraft technology because of it properties.
Year by year, the discussion about the capabilities of this 7075 Aluminum Alloy been
discussed widely among scientist and manufacturer. In the aircraft design the safe
service life of metallic components subjected to fatigue load and corrosion effect can be
demonstrate by adopting the Safe Life concept (Brit, H.J.et al., 2002). This paper
describes work on the effect of corrosion on the fatigue and fracture behaviour of a
7178-T6 aluminum alloy Although a substantial work has been reported on heat
treatment and recrystallization behavior of 7xxx series aluminum alloys a limited studies
have been reported on fracture and impact-toughness behavior of the alloys by use of
impact test especially on sheet and plate that have small thickness. This research paper,
reports a comparative analysis of tensile and fatigue behavior of cold-worked and
recrystallized 7075 aluminum alloy.
The 7xxx series aluminum alloys have been widely used as structural materials due to
their attractive comprehensive properties, such as low density, high strength, ductility,
toughness and resistance to fatigue. The 7075 aluminum alloy is one of the most
important engineering alloys and has been utilized extensively in aircraft structures
because of its high strength-to-density ratio. Metal alloys, which have undergone
extensive plastic deformation by rolling or extrusion, exhibit a significant anisotropy of
mechanical properties. Even in the case of untextured metals showing isotropic or
almost isotropic yielding behavior, ductility can be very anisotropic.
Corrosion damage is often found on structural components subjected to fatigue loading.
Many structures are expected to endure long lives while exposed to corrosive
environments. It is well known that corrosion and fatigue damage can occur
simultaneously and they have a combined effect much more severe than each one
occurring on its own [3,5–7]. However, even the simpler problem of fatigue cracks
initiating from preexisting corrosion damage is still not well understood. One of the
2
major objectives of the current investigation is to determine an appropriate methodology
for assessing the remaining fatigue life of an aircraft or similar component containing
corrosion damage (Mohammad et al, 2001).
The corrosion fatigue life of structural elements could be divided into two phases: the
corrosion fatigue crack initiation life and the corrosion fatigue crack propagation
(CFCP) life to be investigated. The CFCP life of typical structure elements is a portion
of total corrosion fatigue and especially for large structure elements, is dominant. In
addition, the CFCP rate is based on damage tolerance design of typical structure
elements in a corrosive environment using a fracture mechanics approach. Therefore,
more attention has been paid to CFCP rate investigations in steels and aluminum alloys.
It is recognized that the CFCP mechanism is similar to those proposed for stress
corrosion cracking. The CFCP rate is regarded as an enhanced crack propagation rate
promoted in a certain corrosive environment by cyclic loading (Wang, 1996).
1.3
Objective
The objectives of this project are:
a) To investigated the Damage Process due to Fatigue on Heat Treated Aluminum
7075 with effect of the corrosion.
b) To study the changing in mechanical properties in AA7075 as a result from the
mechanical testing.
c) To understand the phenomenons of failure process just before it start to form a
crack or damage.
d) To study the Young’s Modulus of the material and to related it with the damaged
of material
3
1.4
Scope
To ensure the objective was successfully achieved, there are several elements that
needed to follow as well.
a) The understanding of the physical and mechanical characteristic of aluminum
alloy of 7075 series.
b) The behavior of fatigue failure process in AA7075 in effect of corrosion.
c) The study of retrogression and re-ageing (RRA) treatment process that suitable
for the AA7075.
d) Some of mechanical testing must be carried out for investigate the tensile,
hardness and fracture properties of the aluminum alloy 7075.
e) The damage process of AA7075 after being pointed with the load in mechanical
testing.
f) To investigate the influence of fatigue damage due to the corrosion effect on the
AA7075.
4
CHAPTER 2
LITERATURE REVIEW
2.1
Introduction
7xxx series aluminum alloy are widely use in automotive and aircraft industry due to
their high strength to density ratio. Such as AA7075 with T6 heat treatment process can
reach their peak strength through proper T6 aging treatment. However they are very
susceptible to intergranular stress corrosion cracking (SCC) in the T6 temper, especially
in chloride-containing media in the short transverse direction of thick section. Overaging
treatments (like T73 temper) were develop to improve the short transverse SCC
resistance by increasing the grain boundary precipitate size and spacing, but with some
reduction of tensile strength from the T6 temper.
However , it cannot be assumed that alloy and temper with goo SCC resistance would
show good resistance to corrosion fatigue (CF) as CF failure from aluminum alloy are
characteristically transgranular. For example Jacko and Duquette reported that no
significant different in total fatigue lives could be detected between 7075-T6 and T73
aluminum alloy when they were tested in the form of smooth axial fatigue specimens in
aerated 0.5 N NaCL solution.
This chapter will explain general information that related to the work. We will discuss
about the aluminum alloy and it wrought which will choose to determine the material
and heat treatment that used. When aluminum alloy being heat treatment, it basically
5
will strengthen their hardness, tensile strength and electrical conductivity that make it
more suitable for the manufacture of aircraft components.
Moreover, this chapter will explain about the fatigue which includes how the process of
fatigue failure happen from the S-N curve observation and basic term in corrosion that
effect the crack propagation process. There also will explain about S-N curve and factor
that affect the fatigue life
2.2
Aluminum Alloy
Aluminum alloys are mixtures of aluminum with other metals (called an alloy), often
with copper, zinc, manganese, silicon, or magnesium. They are much lighter and more
corrosion resistant than plain carbon steel, but not as corrosion resistant as pure
aluminum. Bare aluminum alloy surfaces will keep their apparent shine in a dry
environment due to the formation of a clear, protective oxide layer. Galvanic corrosion
can be rapid when aluminum alloy is placed in electrical contact with stainless steel, or
other metals with a more negative corrosion potential than the aluminum alloy, in a wet
environment. Aluminum alloy and stainless steel parts should only be used together in
water-containing systems or outdoor installations if provision is made for either
electrical or electrolytic isolation between the two metals.
Aluminum alloy compositions are registered with the Aluminum Association. Many
organizations publish more specific standards for the manufacture of aluminum alloy,
including the Society of Automotive Engineers standards organization, specifically its
aerospace standards subgroups, and ASTM International.
6
2.2.1
Engineering use
Aluminum alloys with a wide range of properties are used in engineering structures.
Alloy systems are classified by a number system (ANSI) or by names indicating their
main alloying constituents (DIN and ISO). Selecting the right alloy for a given
application entails considerations of strength, ductility, formability, weldability and
corrosion resistance to name a few. A brief historical overview of alloys and
manufacturing technologies is given in Ref.[2] Aluminum is used extensively in modern
aircraft due to its high strength to weight ratio.
Improper use of aluminum may result in problems, particularly in contrast to iron or
steel, which appear "better behaved" to the intuitive designer, mechanic, or technician.
The reduction by two thirds of the weight of an aluminum part compared with a
similarly sized iron or steel part seems enormously attractive, but it must be noted that
this replacement is accompanied by a reduction by two thirds in the stiffness of the part
(Miller et al, 2002). Therefore, although direct replacement of an iron or steel part with a
duplicate made from aluminum may still give acceptable strength to withstand peak
loads, the increased flexibility will cause three times more deflection in the part.
Where failure is not an issue but excessive flex is undesirable due to requirements for
precision of location, or efficiency of transmission of power, simple replacement of steel
tubing with similarly sized aluminum tubing will result in a degree of flex which is
undesirable; for instance, the increased flex under operating loads caused by replacing
steel bicycle frame tubing with aluminum tubing of identical dimensions will cause
misalignment of the power-train as well as absorbing the operating force. To increase
the rigidity by increasing the thickness of the walls of the tubing increases the weight
proportionately, so that the advantages of lighter weight are lost as the rigidity is
restored.
7
2.2.2
Wrought alloys
The International Alloy Designation System is the most widely accepted naming scheme
for wrought alloys. Each alloy is given a four-digit number, where the first digit
indicates the major alloying elements.
1000 series are essentially pure aluminum with a minimum 99% aluminum
content by weight and can be work hardened
2000 series are alloyed with copper, can be precipitation hardened to strengths
comparable to steel. Formerly referred to as duralumin, they were once the most
common aerospace alloys, but were susceptible to stress corrosion cracking and
are increasingly replaced by 7000 series in new designs.
4000 series are alloyed with silicon. They are also known as silumin.
3000 series are alloyed with manganese, and can be work-hardened.
5000 series are alloyed with magnesium, derive most of their strength from work
hardening. It is suitable for cryogenic applications and low temperature work.
However is susceptible to corrosion above 60°C.
6000 series are alloyed with magnesium and silicon, are easy to machine, and
can be precipitation-hardened, but not to the high strengths that 2000, and 7000
can reach.
highest strengths of any aluminum alloy.
7000 series are alloyed with zinc, and can be precipitation hardened to the
8000 series is a category mainly used for lithium alloys
8