Smithells Metals Reference Book Part 13 pdf

Test pieces of circular mrd rectangular cross-section Table 21.13 STANDARD TENSILE TEST PIECES FOR CAST IRON-BRITISH STANDARDS BS: 1452: 1977 Dimensions of machined tensile test piece

Test pieces of circular mrd rectangular cross-section

Table 21.13 STANDARD TENSILE TEST PIECES FOR CAST IRON-BRITISH STANDARDS BS: 1452: 1977

Dimensions of machined tensile test piece

Gauge diameter Minimum Minimum radius Plain ends Screwed ends

*If it is desired to calculate the tensile strength on the basis of the nominal diameter, the machining tolerance shall he 0.lOmm

Note: With screwed ends, any Corm of thread may be used provided that the diameter a1 the root of the thread is not Iess than that specified

Table 21.14 STANDARD TENSILE TEST PIECES FOR CAST IRON-AMERICAN STANDARDS

ASTM E&88 A N D BM-88

21-10 Mechanical testing

Table 21.14

ASTM E848 AND E8M-SB-contiwzd

STANDARD TENSILE TEST PIECES FOR CAST IRON-AMERICAN STANDARDS

A Length of reduced section, min 1$

L Overall length, min 3:

0.010

B Length of end section, approximate 1

C Diameter of end section, approximate 3

Note: The reduced section and shoulders (dimensions A, D E, F, G and R ) shall be as shown but the ends may be of any form

to fit the holders of the testing machine in such a way that the load shall be axial Commonly the ends are threaded and have the

dimensions B and C given above Imperial units are E8-88 and metric units are E8M-88

21.3 Impact testing of notched bars

21.3.1 I d test

The test consists of measuring the energy absorbed in breaking a notched test piece by one blow from a striker carried by a pendulum The test piece is gripped vertically with the root of the notch

in the same plane as the upper face of the grips The blow is struck on the same face as the notch

and at a fixed height above it Tests are usually performed at the ambient temperature of the test house

TEST PIECES

The standard test pieces are either lOmm square or 0.45 inches (11.4mm) diameter cross-section Complete dimensions are shown in Table 21.15 The notch profile is shown in Figure 21.2

Table 21.15

AND AMERICAN STANDARD ASTM ED-86

Item Square section Circular section

DIMENSIONS OF IZOD IMPACT TEST PIECES-BRITISH STANDARD BS 131:PART 1:1961 (1989)

Root radius of notch

Maximum depth below notch

Distance of plane of symmetry of notch from

free end of test piece and from the adjacent

8

28 45"

2.75 3.86

Notes: (1) American Standard overall length 75 m m (2.952 in)

(2) American Standard overall length 131 mm (5.157 in)

(3) American Standard overall length 137 mm (5.375 in)

Impact testing of notched bars 21-1 1

PRESENTATION OF RESULTS

When standard test pieces are used the following symbols are used in reporting the results of Izod

tests:

I for Izod

S for square section

Rs for circula cross-section with straight notch

Enlarged view of U-notch (three depths)

Enlarged view of keyhole notch (two depths)

The test consists of measuring the energy absorbed in breaking by one blow from a pendulum a

test piece notched in the middle and supported at each end

TEST PIECES

The standard test piece has a lOmm square cross-section with one of the three notch profiles shown in Figure 21.2 The test piece dimensions are shown in Table 21.16 Sub-standard test pieces

are used where material thicknesses do not permit full-size specimens It should be noted that the

values obtained from subsidiary specimens cannot be compared with full-size specimens nor can

the values obtained from different notches be compared

PRESENTATION OF RESULTS

The report of the tests should include the following information:

Type of test: Charpy V or U notch; striking energy of the machine; size of test piece if sub-

Standazd

Nominal depth of notch and form (W or 'keyhole')

The energy absorbed (J) and the test temperature:

e.g C16OV: x J at y "C

tBS 13l:Part 21972 uses SI units with 1 J s 4 / 3 It Ibf for striking energies (1 ft Ibf=1.35582 J)

21-12 Mechanical testing

An energy of x J was recorded from a Charpy V notch specimen tested at y "C with a striking

energy of 160 J:

e.g C320U2: x J at y "C

In this case the specimen was a Charpy with a U notch 2 mm deep and the striking energy was 320 J

Table 21.16 DIMENSIONS OF CHARPY IMPACT TEST PIECES-BRITISH STANDARDS BS 131:PART 2:1972;

BS 131:PART 3:1972 (1982); AMERICAN STANDARD ASTM E23-86

Nominal dimension

Length

Width standard test piece

subsidiary test piece'

subsidiary test piece

subsidiary test piece

Thickness

Root radius of V notch

Depth below V notch

Root radius of U notch

Depth below U notch

Distance of notch from one end of test piece

Angle between plane of symmetry of notch and longitudinal

axis of test piece

Angle of V notch

55

10 7.5 5.0 2.5

10 0.25

45"

2.165 0.394 0.295

0 97 0.098 0.394 0.010 0.315 0.039 0.315 0.276 0.197 1.083

Mores: (1) Additional subsidiary test pieces are permitted by ASTM ED-86 as follows: S m m thick with 4 m m depth below the notch and 5.10 or 20 mm width and 3 mm thick with 0.094 in (2.39 mm) depth below notoh and 10 m m width (2) Not specified in ASTM E23-86

(3) The 2, 3 and 5 mm notches are sometimes referred to as 'Mesnager', 'DVM' and 'Charpy', respectively

21.4.1 Plane strain &)

Standards: British BS 5447:1977 (1987)

The method involves the loading to faiiure in tension or three point bend of notched specimens which have been precracked by fatigue loading The load versus displacement across the notch at the specimen edge is recorded autographically The load corresponding to a 2% increment of crack extension is established by a specified deviation from the linear portion of the record The fracture

toughness, K,,, value is calculated from this load by equations which have been established on the basis of elastic stress analysis of the two specimen types

Stress-intensityfactor K,: A measure of the stress-field intensity near the tip of a crack in a linear elastic body when deformed so that the crack faces are displaced apart, normal to the crack plane (Opening Mode or Mode I deformation) K , is directly proportional to the applied load and

depends on the specimen geometry

Plain strain fracture toughness K,: A material toughness property-the c r i t i d value of the stress

intensity factor at which rapid propagation of a crack occurs during static loading

American ASTM E399-83

TEST PIECES

The particular type of test piece used depends upon the form, the strength and the toughness of the material under test

Fracture toughness testing 21-13

The basis of the test piece size requirements* is that both the crack length, a, and the thickness,

B, shall be not less than 2.5[(Krc)/(uy)]2 where uy is 0.2% proof stress of the material under the conditions of test, i.e orientation, temperature and loading rate In the first place, the test piece size has to be based on an approximate estimate of the K I c of the material, it is better to overestimate the K , value initially and subsequently use a more conservative test piece if possible,

on the basis of the first test results Alternatively, the ratio of yield strength to Young's modulus

given in Table 21.17 can be used a a guide for selecting the initial test piece size

T a b 21.17 RECOMMENDED THICKNESS AND

CRACK LENGTH FOR FRACTURE TOUGHNESS TEST

PIECES

Minimum recommended thickness and crack length

Minimum thickness for plane strain Cmml

Yield strength, cry (MPa)

Figure 21.3 Yield strength versus fracture toughness data for several alloy systems at 20 "C

The upper scale of the diagram indicates the minimum thickness requirement for a given

strength and toughness by projection of the line joining the origin and data point

(Source: Fulmer Materials Optimizer, Fulmer Laboratories Ltd, Buckinghamshire, UK)

'For graphical assessment see Figure 21.3

MuLti-notch bend test piece

Test piece Proportion, dimensions and limits

Notch width not greater than W (when W is equal to or less than 25 mm N may be up to 1: mm) Faces

parallel and perpendicular to 0.02 mm taper per 10 mm run

Figure 21.4 Standard bend test piecefrom BS 5447: 1977 (1987)

Fracture toughness testing 21-15

Half hole centres E =0.275 W

G=not less than 0.55 W

When W is equal to or less than 25 mm N may be up to I t mm Surfaces parallel and perpendicular as

applicable to 0.02 mm taper/per 10 mrn run

Size 18 W C a max N max E F H D G min

Finish to be 0.8 unless otherwise specified

The dimensions given above are for a resonunended series of test piece sizes

Figure 21.5 Standard tension test piece from BS 5447: 1977 (1987)

Unlike most other forms of mechanical test, plane strain fracture toughness testing has to be completed and the results analysed before it is known if a valid measurement has been made It is necessary to calculate a provisional result Kq, which involves a construction from the test record,

and then to determine whether this result is consistent with the test piece size requirements for the proof stress of the material

21-16 Mechanical testing

OFFSET PROCEDURE

A secant line through the origin is drawn with a slope 5% less than the slope of the tangent to the

initial linear part of the record The force P Q is defined as the intersection of the secant line with the test record or any higher recorded value of force preceding the intersection

CALCULATION OF K Q

K Q is calculated from PQ using one of the following relationships

For the bend test

However, L = 2 hence K Q = P Q Y , / B W 1 ‘ 2

Values for Yl for specific values of a/W are given in Table 21.18

For tension test piece

Hence KQ=%

Values of Y, for specific values of a/W are given in Table 21.19

CALCULATION OF K , ,

The factor 2.5 [(K~)/(ay)]’ shall be &lculated and if this is less than both the thickness and

the crack length of the test piece then KQ is equal to K, Otherwise, it is necessary to use a larger test piece to determine K,,, such that both thickness and crack length are not less than 2.5 [(KIc)/(ay)12 The new dimensions can be estimated on the basis of K Q

Table 21.18

SPAN TO TEST PIECE WIDTH RATIO 4 1

VALUES OF Y , AGAINST a/w FOR BEND TEST PIECE THREE-POINT LOADED OVERALL

9.18 9.21 9.23 9.26 9.46 9.49 9.52 9.54 9.15 9.78 9.81 9.84 10.06 10.09 10.12 10.15 10.38 10.41 10.44 10.48 10.71 10.75 10.78 10.82 11.07 11.11 11.14 11.18 11.44 11.48 11.52 11.56 11.83 11.87 11.91 11.96 12.25 12.30 12.33 12.37

9.29 9.57 9.81 10.18 10.51 10.85 11.22 11.60 12.00 12.42

9.32 9.35 9.60 9.63 9.90 9.93 10.21 10.25 10.54 10.58 10.89 10.93

11.25 1129

11.64 11.67 12.04 1208 12.46 12.50

Fracture toughness resting 21-17 Table 28.19 VALUES OF Yz AGAINST a/W FOR TENSION TEST PIECE

RECORDING OF TEST RESULTS

The following data are usually recorded for each test:

1 Thickness: E in metres

2 Width Win metres

3 Half loading span: Lin metres for bend test only

5 Crack length n in metres The crack length is measured from the fractured test piece at 25%, 50%

and 75% of the specimen thickness and the average of these three values quoted The crack is regarded as unsatisfactory if any of these measurements differ by more than 2.5% W or if any two

possible crack length measurements differ by more than 5% W

6 Test temperature

7 Environment

8 Loading rate in terms of

9 0.2% proof stress in MPa

(change in stress intensity factor per unit time) if outside the standard range of 0.5-2.5 MNm-3/2s-'

10 K1,: in MN m-3'2 Note Kl,=KQ if the size requirements are satisfied,

21.4.2 PlanestressCOD

Standards: BS 5762:1979 (1986)

This standard extends the fracture toughness test beyond the linear elastic behaviour in the plane strain regime, covered by BS 5447 and E399, into the elastic-plastic regime of plane stress The crack opening displacement, COD, at the crack tip is determined as a measure of the stress intensity This test method is used for full thickness test pieces of material not thick enough to give valid

IClc values, but which, nevertheless, fail by crack propagation before general yield The critical COD is not a material property; it is only valid for the thickness of material under the conditions

of the test See Figures 21.6 and 21.7

21-18 Mechanical testing

C/ip gauge

R

Figure 21.6 Schematic representation of the methodfor deriving the crack

opening dispIacement from clip gauge dispIacement

Figure 21.7 Schematic force-displacement record for COD test showing the critical valves at the

points (Pi, y), (P" V,) and (P,,,V_) with corresponding plastic components, Vp of V,

TEST PIECES

Bend test pieces of full thickness to BS 5447 with a relaxation of the crack length requirement so that a=0.15W to 0.719: See Figure 21.4

Fracture toughness testing 21-19 CALCULATION A N D INTERPRETATION OF RESULTS

Symbols:

Pf=The applied force at which slow crack growth starts

PU = The applied force at either

(a) unstable fracture, or

(b) the onset of arrested brittle crack propagation, preceded by slow crack growth P,,,=The applied force at the maximum force plateau

Y , = Clip gauge displacement

q = Value at V, at Pt

%=Value of V, at P

V,=Value of V, at first attainment of the force plateau

V,=The plastic component of V, determined from the force-displacement record as the

offset from the initial elastic load line (the procedure employed in proof stress determinations)

6 =The crack tip opening displacement

z=The distance of the clip gauge location from the test piece surface

RECORDING OF TEST RESULTS

The data recorded for BS 5447 are required by BS 5762 with the following additions:

(1) the force displacement record,

(2) the plastic component of the clip gauge displacement K, V , or V, (mm),

(3) the corresponding force Pi, P or P, (N),

(4) distance of the clip gauge location z (mm) from the surface of the test piece, and

( 5 ) the critical COD 6,, 6, or 6 , (mm) calculated from the equation above using corresponding values at q, V , or V,

22 Mechanical

alloys

properties of metals and

The following tables summarize the mechanical properties of the more important industrial metals and alloys

In the tables of tensile properties at normal temperatures the nominal composition of the alloys is

given, followed by the appropriate British and other spedfication numbers Most specifications pennit considerable latitude in both composition and properties, but the data given in thess tables represent

typical average values which would be expected frum materials of the nominal composition quoted,

unless otherwise stated For design purposes it is essential to consult the appropriate specifications

to obtain minimum and maximum values and special conditions where these apply

The data in the tables referring to properties at elevated and at sub-normal temperatures, and for creep, fatigue and impact strength have been obtained from a more limited number of tests and sometimes from B single example In these cases the data refer to the particular specimens tested and

cannot be relied upon as so generally applicable to other samples of material of the same nominal

composition

22.1 Mechanical properties of aluminium and aluminium alloys

The compositional specifications for wrought aluminium alloys are now internationally agreed throughout Europe Australia, Japan and the USA The system involves a four-digit description

of the aUoy and is now specified in the UK as BS EN 573, 1995 Registration of wrought alloys is

administered by the Aluminum Association in Wassngton, DC International agreement on temper designations has been achieved, and the standards agreed for the European Union, the Euro-Norms,

are replacing the former British Standards Thus BS EN 515.1995 specifies in more detail the temper designations to be used for wrought alloys in the UK At present, there is no Euro-Norm for cast alloys and the old temper designations are still used for cast alloys

In the following tables the four-digit system is used, wherever possible, for wrought materials

221.1 Alloy designation system for wrought aluminium

The first of the four digits in the designation indicates the alloy group according io the major alloying elements, as follows: lXXX - aluminium of 99.0% minimum purity and higher; 2XXX - copper; 3XXX - manganese; 4XXX - silicon; 5XXX - magnesium; 6XXX - magnesium and silicon; 7XXX - zinc; 8XXX - other element, incl lithium; 9XXX - unused; lXXX Group - In

this group the hst two digits indicate the minimum aluminium percentage Thus 1099 indicates aluminium with a minimum purity of 99.99% The second digit indicates modifications in impurity

or alloying element limits 0 signifier unalloyed aluminium and integers 1 to 9 are allocated to

specific additions; 2xXr-8XXX Groups - In these groups the last two digits are simply used to

identify the different alloys in the groups and have no special significance The second digit in- dicates alloy modifications, zero being allotted to the original alloy

National variations of existing compositions are indicated by a letter after the numerical designation, allotted in alphabetical sequence, swing with A for the first national variation registered

The specifications and properties for Cast AlumNum Alloys are tabulated in Chapter26 as

Table 26.26

22.1.2 Temper designation system for aluminium alloys

Tlae Following tables use the internationally agreed temper designations for wrought dloys, (BS EN

515 1995) and the more frequently used ones are listed below The old ones still used for existing

BS specificarions e.g BS 1490.1989 for castings are compared with the new ones at the end of this section

22- 1

22-2 Mechanical properties of rneta1.r and alloys

H Strain hardened non-heat-matable material

H2x Strain hardened only and partially annealed to achieve required temper

H3x Strain hardened only and stabilized by low temperaNre heat treatment to achieve required temper

H12,?l22,H32 Quarter hard, equivalent to about 20-25% cold reduction

H14,H24,H34 Half hard, equivalent to about 35% cold reduction

H16.H26.H36 Three-ouarter hard eauivalent to 50-55% cold reduction

Fully card, equivaienl to about 75% cold reduction

Cooled from an Elevated Twnperature Shaping Process and aged mturally to a substanrially stable condition

Cooled from an Elevated Temperahm Shaping PrOcRrs, cold worked and aged natorally to a

substantially stable condition

Solution heat-treated, cold worked and aged nalurally to a substantially stable condition Solution heat-treated and aged naturally to a substantially stable condition

Cooled from an Elevated Temperatam Shapiig Process and then artificially aged

Solutiou heat-treated and then artificially aged

Solution heat-mted and then stabilized (over-aged)

Solution heat-treated, cold worked and then m c i a l l y aged

Solution heat-treated, artificially aged and then cold worked

Cooled from an Elevated Temperature Shaping Process, artificially aged and then cold worked alloys

-

A large number of variants in these tempers has been introduced by adding additional dqyts to the

above designations For example, the addition of the digit 5 after TI-9 signifies that a stress relieving

treatment by stretching has been applied after solution heat-treatment

A full list is given in BS EN 515 1995 but some of the more common ones used in the following tables are given below

T351 Solution heat-treated, stress-relieved by stretching a controlled amount (usually I-3%

permanent set) and then naturally aged There is no further straightening after stretching

This applies to sheet, plate, rolled rod and bar and ring forging

The same as T351 but applied to extruded rod, bar, shapes and tubes

A T3510, except that minor straightening is allowed to meet tolerances

Solution heat-tmted stress-relieved by compressing (1-5% permanent set) and then naturally aged

Solution heat-treated, stress-relieved by stretching a controlled amount (usually 1-3% permanent set) and then aaificially aged There is no fuxther straightening after stretching This applies to sheet, plate, rolled rod and bar and ring forging

The same T651 but applied to extruded rod, bar, shapes and tubes

As T65 10, except that minor straightening is allowed to meet tolerances

Solution heat-treated and then artificially overaged to improve conosion resistance Solution heat-treated, stress-relieved by stretching a controlled amount (Again about 1-38 permanent set) and then artificially over-aged in order to obtain a good resistance

to exfoliation corrosion There is no furtha straightening after stretching This applies to sheet, plate, rolled rod and bar and to ring forging

As T7651 but applied to extruded rod, bar shapes and tubes

As T7510, except that minor straightening is allowed to meet to tolerances

are as follows TH7 is as TH and then stabilised; FIM is as manufactured or fabricated

In some specifications, the old system is still being applied The equivalents between old and new

Table 22.2 ALUMlNIlJM AND ALUMINNJM ALLOYS-MECHANICAL PROPERTIES AT ROOM TEMPERATURE

Wrought Mays

Firrigiii,

cumpusition stress strength ( ~ 2 6 m m ) smngth lurdness 500 MHz engery toughness

Specifcution % Form Condition MPa MPa or 5 6 5 a MPa ( P = 5 D 2 ) MPa J (MPam’/’) Remarks

~~

coni/l""ilior~ stress slrrnRili (22.6 mni) simii~th htrrtlrress 500 MHz mpp toufhrress

Plate Barltube

T45 1 T65 1

1070A)

Structural applications, especially ortnsport and aerospace

T6

Plate T8 1 Plate (12.5mm) T81 Plate (12mm) T8X51 Plate (4Omm) T8X51

(IOIlUll)

(30mm) Plate (12 nun) T85 1

Medium strength low

density aero-alloy in damage-tolerant temper

Medium strength, low density am-alloy Medium strength, low

density aero-alloy Weldable, creep mistant, high- temperature aerospace applications

H I 1 1

H 14

H18

H l l l H14 H18

F

H l l l H22 H24 H28

Sheet metal work

with good-corrosion resistance and high fatigue resistance

Marine and transport applications; good

workabilitv combined 0 5

1 s

b

Welded structures, storage tanks, salt water service

k

continued overleaf

Table 22.2 ALUMINIUM AND ALUMINIUM ALLOYS-MECHANICAL PROPERTIES AT ROOM TEMPERATURE - criiifiniird

composition stress strength (22.6 mm) strength hardness 500MHz engery toughness

weldable and corrosion-resistant

T6

T4 T6 T4

composition stress strength (22.6mm) strength hardness 5OOMHz engery toughness

forgings sheetlplatel

vehicle bumpers

Bumper backing

bars

Domestic foil

24 h at RT,

48h at 170°C) soln trt 530"C, WQ, 8

3 lOOh at 170°C) a

I Table 22.2 ALUMINIUM AND ALUMINIUM ALLOYS-MECHANICAL PROPERTIES AT ROOM TEMPERATUE - continued

composition stress strength (22.6 nun) strength hardness 500MHz energy toughness

Sandcast F Chill cast F Sandcast T4 Chill cast T4 Sandcast F

Chill cast F

Sandcast F Chill cast F

Si 8.0 Die cast (LM4) Cu 3.0 Sandcast

Si 5.0 Chill cast

Sand cast Chill cast

T4 T4 T6 T6

F

F

F

F T6 T6

B

resistance Intricate castings

very similar alloys, 9

excellent casting characteristics and COI-

rosion resistance LM6 has slightly supperior corrosion resistance

Good strength in fairly difficult castings

Cast vehicle wheels Aircraft castings

c u 4.5 Die cast F 240 275 1 - 120 - - wear resistance,

for low-pressure castings

continued overleaf

Good combination of

impact resistance and strength General purpose die casting alloy Castings to withstand high hydraulic pressure Sand castings for

Table 22.2 ALUMINIUM AND ALUMINWM ALLOYS-MECHANICAL PROPERTIES AT ROOM TEMPF.RATLXE - continued

(LM26) Si 9.0

Cu 3.0

Mg 1.0

Ni 0.7 AI-Cu-Si- (3L52) Cu 2.0

Mg-Fe-Ni Si 1.5

Mg 1.0

Fe 1.0

Ni 1.25 AI-Cu-Si- (3L51) Cu 1.5

Sandcast T6

Chillcast T6

sandcast T5 Chill cast T5

Awcraft engine castings

*Fatigue Limit for 50 x lo6 cycles

M = as manufactured

H l l l =annealed

2 intermediate tempers

H6

H8 = fully hard temper

(1) Spedal temper for maximum stms corrosion resistance (US designation T73)

(2) Special hea! treatment for combination of propetties (US designation T736)

(3) Special heat treatment for combination of propetties (US designation T61)

(4) Special heat treatment for combination of properties (US designation "7351)

a

s

2:

"1)

22-16 Mechanical properties of metals and alloys

Table 22.3 ALUMINIUM AND ALUMINNM ALLOYS - MECHANICAL FROPERTIES AT ELEVATED TEMPERATURES

~

10 000

10 OOO

1 0 m

1oOOO loo00

Mechanical properties of aluminium and aluminium alloys 22-17

Table 22.3 A L W N M A M ) ALUMINNM ALLOYS - MECHANICAL PROPEGIES AT ELEVATED

mmERAm - conrinued

Maerial composition Emp temp Proofstress strength or

1 o m 20 loo00 90

10000 90 loo00 90 loo00 75

lOOa0 50 loo00 35 loo00 20 loo00 215 loo00 205 loo00 185 loo00 105 loo00 50 loo00 35 loo00 20 loo00 255 loo00 255 loo00 200 loo00 105 loo00 50 loo00 35 loo00 20 loo00 125 loo00 125 loo00 125 loo00 95 loo00 60 loo00 40 loo00 30 loo00 225 loo00 220 loo00 195

1oo00 110 loo00 60 loo00 40 loo00 30

10000 270 loo00 255

loo00 220 loo00 105 loo00 60 loo00 40

22-18 Mechanical propenies of metals and alloys

TaMe 22.3 ALUMNKJM A N D AUlMINRlM A!LOYS -MECHANICAL PROPERTIES AT ELEVATED

TEhPERATWR!B - continued

Material composition Temp temp Proofstress strength or

loo00 213

loo00 35 1Oo00 17 loo00 14

Mechanical propetties of aluminium and aluminium alloys 22-19

Table 22.3 ALUMINNM AND ALUMINIUM ALLOYS - MECHANICAL PROpERTDes AT EEVATED

~ E R A T u R E s - r o n t i n u e d

Material composition Temp temp PToofstress strength or

lo00

lo00 loo0 lo00 lo00

Material composition Emp temp Proof stress strength or

Pressure die cast

100

200

300

400 T6 20

10 o00

loo00 loo00 loo00 loo00 loo00

10 o00

lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00

1000 lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00 lo00

280 320

110 165

15 35 200* 275

*O.l% Roof stress

Table 22.4 A L U m I U M AND ALUMINIUM ALLOYS -MECHANICAL PROPERTIES AT LOW TEMF'ERMUREX

Pca- tion Temp stress strength on 50- area toughness

tion) % Condition "C MPa MPa or50mm % MPa m1I2 Reference

A1 99.0 Rolled and 24

drawnrcd H l l l -28

-196 H18 24 -80

-28 -80 -196

Mechanical properties of aluminium and aluminium alloys 22-21

TaMe 22.4 ALUMINIUM AND ALuMINNN[ ALLOYS - MECHANICAL PROPERTIES AT LOW

m M p E R p ; I z T R E s- conrinued

pca- tion Temp stress strength on 50mm area roughness

tion) % Condition "C MPa MPa or50mm % MPam'f2 Reference

-80 -196 Mg2.5 Rolledand 24

Cr 0.25 drawnrod H l l l -28

-80 -196

H18 24 -28 -80 -196 Mg3.5 Sheet B l l l 26

Cr 0.25 -28

-80 -196 H18 26 -80 -196 -253 Mg5.0 Rate HI11 20

-196 Mg0.7 Exmsion T4 26

115

215

220 22s

130

220

195 20s 21s

80.6 80.6 19.9 71.2 63.5 64.4 66.5 62.3 72.0 74.2 76.4 69.0 59.1 63.2 64.5 51.4

continued overleaf

22-22 Mechanical propertiis of metals and alloys

Table 22.4 A L W I Z T M AND AL.UMlNNM ALLOYS - MEcIiANIcAL PROpwllEs AT LOW

?EMPERATmEs - continued

fica- tion Rmp stress smngth a 50mm area toughness

tion) % Condition "C MPa MPa o r 5 ~ m m % MParn'l' Reference

26 -28 -80 -196

26

-80 -196 -253

27 -196 -269

27 -73 -196 -269

24 -28 -80 -196

HI8 = FUny hard temper

T4 = Solution treated end m d y aged

T6 = Solution treated and pipitation vmced

Table 22.5 ALUMINIUM ALOYS - CREEP DATA

Minimum Total Material composition Temp Stress % p e r % i n

(specc$cation) % Condition "C MPa lOOOh lOOOh Reference

45 0.005

110 0.055 I15 0.17

125 0.21

30 0.08

45 0.20

60 0.62 3.90 0.045 7.7 0.12

15 0.35

0.39 1.28 0.045 0.065 0.047 0.047 0.052 0.152 0.085 0.33 3 0.57 1.19 0.21 0.39 0.92 0.10 0.25

0.60

Mechanical properties of aluminium and aluminium alloys 22-23 Table 22.5 ALUMINIUM ALLOYS -CREEP DATA -continued

Minimwn Total

(specgication) % Condition "C MPa lO00h lOOOh Reference

15 0.147 7.5 0.107

34 0.01

68 0.11 8.90 0.12 13.1 0.43

15 0.223

15 0.001

31 0.022 34.8 0.040 38.6 0.060 42.5 0.13

0.126 3 0.107 0.174 0.413 0.647 0.341 0.658

22-24

Table225 (continued)

Mechanical properties of metals and alloys

Minimum Toral

Material CompOSthO?I Temp Srress % p e r % i n

(specific&.on) % Condition "C Mpa 1OOOh l W h Reference

200

300

300

400 Clad sheet T6 35

77

116

7

15 1.50

0.04

0.028 0.16 0.037 0.5

0.05

0.01 0.08 0.018 0.08 0.06 0.1

1 .o

10.0 0.1 1.0 10.0 0.1

1 .o

10.0 0.1 1.0 10.0 0.007 0.010 0.11 1.6 0.0087 0.023 0.22 0,011

0.040

0.13 0.28

T4 = Solution mated and namlany aged, will nspnd to PreCipitatioD ueatment

T6 = Solution treated and aniliciaUy aged

Table 22.6 ALUMlNRTM ALOYS -FATIGUE STRENGTH AT VARIOUS TEMPERATURES

Material composifion Temp (unnorched)

(spec@cation) 5% Condition "C MPa MHz Remarks Reference

A1-Mg Mg 5.0 Extruded -65 184 20 Rotatingbeam

f 2 0 133

Mechanical properties of aluminium and aluminium alloys 22-25

Table 22.6 (contitwed)

Material &ompositio?l T q (unnotched)

200 Sand cast 20

22-26

Table 22.6 (cutzrbufed)

Mechanical properties of metals and alloys

Nominal Material composition

149

204

260

Endurance (unnotched)

T4 = Solution tmtcd and naturally aged, will respond to precipitation treatmfnl

T6 = Solution treated and aaiacidly aged

REFERENCES

1 Bogardus, S W Steckley and F M Howell, N.A.C.A Technical Note 2082, 1950

2 ‘A Review of Current Literature of Metals at Very Low Temperatures’ Battelle Memorial Institute; 1961

3 J McKeown and R D S Lushey, Metallurgia, 1951, 43, 15

4 A E Hanigan, L F Tedsen and J E Dom, Trans Amer Inst Min Met Eng., 1947, t71, 213

5 R R Kennedy, Proc Am Soc Test Mat., 1935, 33, 218

6 J McKeown, D E Dineen and L H Back, Metallurgica, 1950, 41, 393

7 F M Howell and E S Howarth, Proc Am SOC Test Mat., 1937, 37, 206

8 N P Inglis and E G Larke, J Inst Mech Engrs., 1959

9 P H Frith, ‘Properties of Wrought and Cast Aluminium and Magnesium Alloys at Atmospheric and Elevated Temperatures’, HMSO, 1956

10 R Grimes, T Davis, H J Saxty and J E Fearon, ‘4th International AI-Li Conference, 10- 12th June, 1987’,

J de Physique, Sept 1987.48, CoUoque C3, pll

11 G Leroy et aL, ibid., C3, p33

12 M J Birt and C J Beevers, 5rh IntemationalAL-Li Conference, williamburg, Virginia, March 27-31.1989 (ed T.H Sanders and EA Stake), Materials and Component Engineering Publications Ltd, UK, p983

13 EL D Peacock and J W Manin, $2, p1013

14 J Glazer and I W Morris, &id, pI471

15 G R D Shrimpton and H C Argus, ibid, p1565

16 A F Smith, ibid, p1587

FURTHER INFORMATION

1 The Properties of Aluminium and its Alloys, The Aluminium Federation (8th Edition)

2 Metals Handbook, Vol 2, 10th Edition, ASM International, 1990

- British Standards - BS designation

Copper alloy ingots and copper and copper alloy castings

Rolled copper and copper alloys, sheet, strip and coil Copper and copper alloys - forgoing stock and forgings Copper and copper alloys - wire

Copper and copper alloys - rods and sections Copper and copper alloys - plate

Copper and copper alloys - t u b s

International Standards Organization - I S 0 designation

ISO/R1190-1 1971 Copper and copper alloys Parts 1 and 2

Mechanical properties of copper and copper alloys 22-27

1973 Wrought copper-zinc alloys Part 1

1973 Wrought copper-zinc alloys Part 2

1973 Wrought copper-aluminium alloys

1973 Wrought copper-nickel alloys

1973 Wrought copper-nickel-zinc alloys

1972 Electrolytic tough pitch copper

1961 Classification of coppers

1971 Special wrought copper alloys

1971 Copper and copper alloys Parts 1 and 2 IS0 427 1973 Wrought copper-tin alloys

CuAll OFe 1 CuNi30MnlFe Cast d ~ o y s CuZn33Pb2-GB

CuZn33Pb2-GS CuSnl2-GS CuCr 10-M

CuSnl2-GB Master Alloys C uA150(A)-M

CuS20-M

C W l l l C CW305G CW354H CB750S cc75os CB483K CC483K CM344G CM204E CM220E

Temper designations are also given by CEN TC133 For copper and copper alloys letters are

used for mandatory properties as follows: A - elongation, B - spring bending limit, G - grain size,

H - hardness (Brinell for castings Vickers for wrought products), M - as manufactured, R - tensile

strength, Y - 0.2% proof stress

For further reference to the CEN system for Copper, contact the Copper Development Association

or tbeir CD ROM Megabyres on Copper

A s the CEN standard has not yet been adopted in the UK, the IS0 designation has been used in

Column 1 of Table 22.7 and the current BS specification numbers have been used in Column 2 of Table 22.7 and in Table 22.8