03-manufacturing properties of metals

8/11/2019 03-Manufacturing Properties of Metals

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Manufacturing Processes Prof. T. zel

Structure and Manufacturing Properties

of Metals


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Turbine Blades for Jet Engines

FIGURE 3.1 Turbine blades for jet engines, manufactured by three different methods: (a)conventionally cast ; (b) directionally solidified, with columnar grains , as can be seenfrom the vertical streaks; and (c) single crystal .

Although more expensive, single crystal blades have properties at high temperatures that aresuperior to those to those of other blades. Source : Courtesy of United Technologies Pratt andWhitney.


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atoms pack in periodic, 3D arrays typical of:

Crystalline materials...

-metals-many ceramics-some polymers

atoms have no periodic packing occurs for:

Noncrystalline materials...

-complex structures-rapid cooling

Si Oxygen

crystalline SiO 2

noncrystalline SiO 2"Amorphous " = Noncrystalline

Adapted from Fig. 3.18(a),Callister 6e.

AMORPHOUS MATERIALS


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Dense, regular packing

Dense, regular-packed structures tend to have lower energy

Energy

r

typical neighborbond length

typical neighborbond energy

ENERGY AND PACKING

Non dense, random packing Energy

r

typical neighborbond length

typical neighborbond energy


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Body-Centered Cubic Crystal Structure

FIGURE 3.2a The body-centered cubic (bcc) crystal structure: (a) hard-ball model; (b)unit cell; and (c) single crystal with many unit cells. Source: W.G. Moffatt et al.


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Face-Centered Cubic Crystal Structure

FIGURE 3.2b The face-centered cubic (fcc) crystal structure: (a) hard-ball model; (b) unitcell; and (c) single crystal with many unit cell. Source : W.G. Moffatt et al.


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Hexagonal Close-Packed Crystal Structure

FIGURE 3.2c The hexagonal close-packed (hcp) crystal structure: (a) unit cell; and (b)single crystal with many unit cells. Source : W.G. Moffatt et al.


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Plastic Deformation of a Single Crystal

FIGURE 3.3 Permanent deformation,also called plastic deformation, of a singlecrystal subjected to a shear stress: (a)structure before deformation by slip. Theb/a ratio influences the magnitude of theshear stress required to cause slip.

FIGURE 3.4 (a) Permanent deformation of asingle crystal under a tensile load. Note thatthe slip planes tend to align themselves in thedirection of pulling. This behavior can besimulated using a deck of cards with a rubber

band around them. (b) Twinning in tension.

When crystals are subjected to an external force, they first undergoelastic deformation . If the force on the crystal structure is increasedsufficiently, the crystal undergoes plastic (or permanent) deformation .

SLIP TWINNING


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Shear Stress in Moving Planes of Atoms

FIGURE 3.5 Variation of shear stress in moving a plane of atoms over another plane.

The maximum theoretical shear stress,

max , to cause permanent deformation ina perfect crystal is obtained as follows: when there is no stress, the atoms in thecrystal are in equilibrium.

x =0 shear stress is zero. Each atom is attracted to the nearest atom of the lowerrow, resulting in non-equilibrium at positions 2 and 4, where shear stressbecomes max .


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Slip Lines and SlipBands in a Single

Crystal

FIGURE 3.6 Schematic illustration of sliplines and slip bands in a single crystalsubjected to a shear stress. A slip bandconsists of a number of slip planes. Thecrystal at the center of the upper drawing is anindividual grain surrounded by other grains.

Each "grain" is a single crystal.


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Cohesive Stress As a Function of Distance

FIGURE 3.7 Variation of cohesive stress as afunction of distance between a row of atoms.

Ideal tensile strength

Work done per unit area in breakingThe bond between the two atomic planes

Involving surface energy of the material

Approximately

10

2

max

max

max

max

E

a

E

Work

a

E

=

=

=


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Defects In a Crystal

FIGURE 3.8 Various defects in a single-crystal lattice.

Imperfections

1. Point defects2. Linear (1-D) defects, dislocations

3. Planar (2-D) defects, grain boundaries


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Edge and Screw Dislocations

FIGURE 3.9

(a) Edge dislocation, a linear defect at the edge of an extra plane of atoms.

(b) Screw dislocation, a helical defect in a three-dimensional lattice of atoms.


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Movement of An Edge Dislocation

FIGURE 3.10 Movement of an edge dislocation across the crystal lattice under a shearstress. Dislocations help explain why the actual strength of metals is much lower thanthat predicted by theory.

Strain hardening (work hardening)Dislocations can become entangled and interfere with each other,and be impeded by barriers, such as grain boundaries and impurities in the material.This causes increase in shear stress required and hence increase in overall strength,which is known as strain hardening , or work hardening .


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Polycrystalline Materials

FIGURE 3.11 Schematic illustration of the various stages during solidification of moltenmetal. Each small square represents a unit cell. (a) Nucleation of crystals at random sites inthe molten metal. Note that the crystallographic orientation of each site is different. (b) and(c) Growth of crystals as solidification continues. (d) solidified metal, showing individualgrains and grain boundaries. Note the different angles at which neighboring grains meet eachother. Source: W. Rosenhain.

Formation of grains and random grain boundaries Nuclei form during solidification, each of which grows intocrystals

Each"grain" is asinglecrystal.


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Tensile StressAcross a Plane

FIGURE 3.12 Variation of tensile stress across a plane of polycrystalline metal specimensubjected to tension. Note that the strength exhibited by each grain depends on its orientation.

Relation between grain sizeand yield strength

Hall-Petch EquationY =Y i + k d -1/2

Y i basic yield stressk constant indicating level of dislocationsd average grain diameter


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Embrittlement of Copper

FIGURE 3.13 Embrittlement of copper by

lead and bismuth at 350 C (660 F).Embrittlement has important effects on thestrength, ductility, and toughness ofmaterials. Source: After W. Rostoker.

Influence of grain boundaries

on:-strength-ductility

When brought into close atomiccontact with certain low-melting-

point metals,a normally ductile and strong metalcan crack under very low stresses,A phenomenon referred to as grainboundary embrittlement.


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Plastic Deformation in Compression

FIGURE 3.14 Plastic deformation of idealized (equiaxed) grains in a specimen subjected tocompression, such as is done metals: (a) before deformation; and (b) after deformation. Notethe horizontal alignment of grain boundaries.

Anisotropy(Texture)


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Result of Bulging Using a Steel Ball

FIGURE 3.15 (a) Illustration of a crack in sheet metal subjected to bulging, such as by pushinga steel ball against the sheet. Note the orientation of the crack with respect to the rollingdirection of the sheet. This material is anisotropic. (b) Aluminum sheet with a crack (vertical

dark line at center) developed in a bulge test. Source : Courtesy of J. S. Kallend, Illinois Instituteof Technology.


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Recovery,Recrystallization and

Grain Growth

FIGURE 3.16 Schematic illustration of

the effects of recovery, recrystallization,and grain growth on mechanical

properties and shape and size of grains. Note the formation of small new grainsduring recrystallization. Source: G.Sachs.

Recovery: It occurs at a certaintemperature range belowthe recrystallization temperature.

Recrystallization: The process inwhich, at a certain temperature range,new equiaxed and strain-free grains areformed.Grain growth: When temperature is

continuously increased, the grains beginto grow, and their size eventuallyexceed the original grain size.


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Variation of Strength and Hardness

FIGURE 3.17 Variation of strength and hardness with recrystallization temperature, time, and prior cold work. Note that the more a metal is cold worked, the less time it takes torecrystallize, because of the higher stored energy from cold working due to increaseddislocation density.


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Effects of PriorCold Work

FIGURE 3.18 The effect of prior coldwork on the recrystallized grain size of

alpha brass. Below a critical elongation(strain), typically 5%, no recrystallizationoccurs.

FIGURE 3.19 Surface roughness on thecylindrical surface of an aluminum specimen

subjected to compression. Source: A. Mulc andS. Kalpakjian.

SurfaceRoughening


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Cold, Warm and Hot Working

Table 3.1 Homologous temperature ranges for various processes

PROCESS T /T mCold workingWarm workingHot working

< 0.30.3 to 0.5

> 0.6

Hot working - above recrystallization temperature

recrystallization, grain growth occurs

Cold working - below recrystallization temperature

no recrystallization or grain growth, significant grain elongation and work hardeningresults

Warm working - intermediate temperature.

Rcrystallization occurs, but little or no grain growth. Grains are equiaxed but smallerthan hot working.


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Fracture in Metals

Ductile fracture is characterized by

plastic deformation Brittle fracture occurs with little or no

plastic deformation Buckling


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Types of Failure in Materials

FIGURE 3.20 Schematic illustration of types offailure in materials:

(a) necking and fracture of ductile materials ;

(b) buckling of ductile materials under acompressive load;

(c) fracture of brittle materials in compression;

(d) cracking on the barreled surface of ductilematerials in compression.

FIGURE 3.21 Schematic illustration of the typesof fracture in tension:(a) brittle fracture in polycrystalline metals ;

(b) shear fracture in ductile single crystals;(c) ductile cup-and-cone fracture inpolycrystalline metals

(d) complete ductile fracture in polycrystallinemetals , with 100% reduction of area.

FractureBuckling


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Surface of Low-Carbon

Steel

FIGURE 3.22 Surface of ductile fracturein low-carbon steel, showing dimples.Fracture is usually initiated at impurities,inclusions, or preexisting voids in themetal. Source : K.-H. Habig and D.Klaffke. Photo by BAM, Berlin,

Germany.

Upon close examination of a

ductile fracture , we see fibrous pattern with dimples, as if anumber of very small tensiontests have been carried out over

fracture surface.

Failure is initiated with theformation of tiny voids, usuallyaround small inclusions or

preexisting voids, which thengrow and coalesce, developing

cracks that grow in size and leadfracture.


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Sequence of Necking And Fracture

FIGURE 3.23 Sequence of events on necking and fractureof a tensile-test specimen:

(a) early stage of necking;(b) small voids begin to form within the necked region;(c) voids coalesce, producing an internal crack;(d) rest of cross-section begins to fail at the periphery by

shearing;(e) final fracture surfaces, known as cup-(top fracture

surface) and-cone (bottom surface) fracture.

Voids and porositiesdeveloped during

processing of themetal, such as fromcasting, reduce theductility of a material.


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Effect of Second Phase Particles on True Strainat Fracture

FIGURE 3.24 The effect of volume fractionof various second-phase particles on the truestrain at fracture in a tensile test for copper.Source: After B. I. Edelson and W. M.

Baldwin.

Inclusions have animportant influence onductile fracture and thus onthe formability of thematerials.

Inclusions may consist ofimpurities of various kinds

and second-phase particlessuch as oxides, carbides,and sulfides.

Fatigue fracture isbasically ofa brittle nature.


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Deformation of Soft and Hard Inclusions

FIGURE 3.25 Schematic illustration of the deformation of soft and hard inclusions andtheir effect on void formation in plastic deformation. Note that hard inclusions, because theydo not comply with the overall deformation of the ductile matrix, can cause voids.

There are two factors affecting void formation:(1) strength of the bond at the interface of an inclusion and the matrix.(2) The hardness of the inclusion. If the inclusion is soft, such as manganesesulfide, it will conform to the overall change in shape of the specimen orworkpiece during plastic deformation.If it is hard, such as a carbide or oxide, it could lead to void formation.Hard inclusions may also break up into smaller particles during deformation.


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TransitionTemperature

FIGURE 3.26 Schematic illustration oftransition temperature. Note the narrowtemperature range across which thebehavior of the metal undergoes a majortransition.

FIGURE 3.27 Strain aging and its effect onthe shape of the true-stress-true-strain curvefor 0.03% C rimmed steel at 60 C (140 F).Source: A. S. Keh and W. C. Leslie.

Strain Aging

Many metals go undergo a sharp changein ductility and toughness across a narrowtemperature arnge called the transitiontemperature.

Strain aging is a phenomenon in whichcarbon atoms in steels segregate todislocations, thereby pinning them and thusincreasing the steels resistance todislocation movement.


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Fracture Surface of Steel

FIGURE 3.28 Typical fracture surface of steel that has failed in a brittle manner.The fracture path is transgranular (through the grains).Magnification: 200X. Source : Courtesy of B. J. Schulze, S. L. Meiley, and PackerEngineering Associates, Inc.

Brittle fracture occurs with little or no gross plastic deformation preceeding theseparation of the material into two or more pieces.In tension fracture takes place along a crystallographic plane, called a cleavageplane, on which the normal tensile stress is a maximum.


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Intergranular Fracture

FIGURE 3.29 Intergranular fracture, at two different magnifications. Grains and grainboundaries are clearly visible in this micrograph. The fracture path is along the grainboundaries. Magnification: left, 100X; right, 500X. Source: Courtesy of B. J. Schulze,S. L. Meiley, and Packer Engineering Associates, Inc.

Where the fracture path is along the grain boundaries, generallyoccurs when grain boundaries are soft, contain a brittle phase, orhave been weakened by liquid-or solid metal embrittlement.


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Modes of Fracture

FIGURE 3.30 Three modes of fracture.Mode I has been studied extensively, because it is the most commonly observed inengineering structures and components.Mode II is rare.Mode III is the tearing process; examples include opening a pop-top can, tearing apiece of paper, and cutting materials with a pair of scissors.


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Typical Fatigue Fracture Surface

FIGURE 3.31 Typical fatigue fracture surface on metals, showing beach

marks. Most components in machines and engines fail by fatigue and notby excessive static loading. Magnification; left, 500X; right, 1000X.Source : Courtesy of B. J. Schulze, S. L. Meiley, and Packer EngineeringAssociates, Inc.


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Surface Finishand Fatigue

Strength

FIGURE 3.32 Reduction infatigue strength of cast steelssubjected to various surface-

finishing operations. Notethat the reduction is greateras the surface roughness andstrength of the steelincrease. Source : M. R.Mitchell.


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Properties of Materials

Table 3.2 Physical properties of various materials at room temperature.

METALDENSITY

(kg/m3)

MELTING POINT(C)

SPECIFIC HEAT(J/kgK)

THERMALCONDUCTIVITY

(W/m K)

COEFFICIENTOF THERMALEXPANSION

( m/mC) Aluminum Aluminum alloysBeryliumColumbium (niobium)Copper Copper alloysGoldIronSteelsLeadLead alloysMagnesiumMagnesium alloysMolybdenum alloysNickelNickel alloysSiliconSilver Tantalum alloysTitaniumTitanium alloysTungsten

27002630-2820

185485808970

7470-8940193007860

6920-913011350

8850-113501745

1770-1780102108910

7750-88502330

10500166004510

4430-470019290

660476-654

127824681082

885-126010631537

1371-1532327

182-326650

610-62126101453

1110-14541423961

29961668

1549-16493410

900880-920

1884272385

337-435129460

448-502130

126-18810251046276440

381-544712235142519

502-544138

222121-239

14652

39329-234

31774

15-5235

24-46154

75-13814292

12-631484295417

8-12166

23.623.0-23.6

8.57.1

16.516.5-20

19.311.5

11.7-17.329.4

27.1-31.126.026.05.1

13.312.7-18.4

7.6319.36.5

8.358.1-9.5

4.5NONMETALLICCeramicsGlassesGraphitePlasticsWood

2300-55002400-27001900-2200900-2000400-700

-580-1540

-110-330

-

750-950500-850

8401000-20002400-2800

10-170.6-1.7

5-100.1-0.40.1-0.4

5.5-13.54.6-707.86

72-2002-60


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Properties of Stainless Steels

Table 3.3 Room-temperature mechanical properties and typical applications ofannealed stainless steels.

AISI(UNS)

ULTIMATETENSILE

STRENGTH(MPa)

YIELDSTRENGTH

(MPa)

ELONGATION(%)

CHARACTERISTICS AND TYPICAL APPLICATIONS

303(S30300)

550-620 240-260 50-53 Screw-machine products, shafts, valves, bolts,bushings, and nuts; aircraft fittings; bolt; nuts;rivets; screws; studs.

304(S30400)

565-620 240-290 55-60 Chemical and food processing equipment,brewing equipment, cryogenic vessels, gutters,downspouts, and flashings.

(316(S31600)

550-590 210-290 55-60 High corrosion resistance and high creep strength.Chemical and pulp handling equipment,photographic equipment, brandy vats, fertilizer parts, ketchup cooking kettles, and yeast tubs.

410(S41000)

480-520 240-310 25-35 Machine parts, pump shafts, bolts, bushings, coalchutes, cutlery, fishing tackle, hardware, jet

engine parts, mining machinery, rifle barrels,screws, and valves.

416(S41600)

480-520 275 20-30 Aircraft fittings, bolts, nuts, fire extinguisher inserts, rivets and screws.


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Types of Tool and Die Steels

Table 3.4 Basic types of tool and die steels.

TYPE AISIHigh speed M (molybdenum base)

T (tungsten base)Hot work H1 to H19 (chromium base)

H20 to H39 (tungsten base)H40 to H59 (molybdenum base)

Cold work D (high carbon, high chromium) A (medium alloy, air hardening)O (oil hardening)

Shock resisting SMold steels P1 to P19 (low carbon)

P20 to P39 (others)Special purpose L (low alloy)

F (carbon-tungsten)Water hardening W


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Applications of Tool and Die Steels

Table 3.5 Typical tool and die materials for various processes.

PROCESS MATERIALDie castingPowder metallurgy

PunchesDies

Molds for plastic and rubber Hot forgingHot extrusionCold headingCold extrusion

PunchesDies

CoiningDrawing

WireShapes

Bar and tubingRolls

RollingThread rollingShear spinning

Sheet metalsShearing

Cold

HotPressworkingDeep drawing

Machining

H13, P20

A2, S7, D2, D3, M2WC, D2, M2S1, O1, A2, D2, 6F5, 6F6, P6, P20, P21, H136F2, 6G, H11, H12H11, H12, H13W1, W2, M1, M2, D2, WC

A2, D2, M2, M4O1, W1, A2, D252100, W1, O1, A2, D2, D3, D4, H11, H12, H13

WC, diamondWC, D2, M2

WC, W1, D2

Cast iron, cast steel, forged steel, WC A2, D2, M2 A2, D2, D3

D2, A2, A9, S2, S5, S7

H11, H12, H13Zinc alloys, 4140 steel, cast iron, epoxy composites, A2, D2, O1W1, O1, cast iron, A2, D2Carbides, high-speed steels, ceramics, diamond, cubic boron nitride


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Non-ferrous Alloys in a Jet Engine

FIGURE 3.33 Cross-section of a jet engine (PW2037) showing various components and thealloys used in making them. Source : Courtesy of United Aircraft Pratt & Whitney.


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Properties of Aluminum Alloys

Table 3.6 Properties of various aluminum alloys at room temperature.

ALLOY (UNS) TEMPERULTIMATE TENSILESTRENGTH (MPa)

YIELD STRENGTH(MPa)

ELONGATIONIn 50 mm (%)

1100 (A91100)11002024 (A92024)20243003 (A93003)3003

5052 (A95052)50526061 (A96061)60617075 (A97075)7075

OH14

OT4O

H14

OH34OT6OT6

90125190470110150

190260125310230570

3512075

32540

145

9021555

275105500

35-459-20

20-2219-2030-408-16

25-3010-1425-3012-1716-17

11


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Properties of Wrought Aluminum

Table 3.7 Manufacturing properties and typical applications of wrought aluminum alloys.

CHARACTERISTICS*

ALLOYCORROSIONRESISTANCE MACHINABILITY WELDABILITYTYPICAL APPLI CATIONS

1100 A D-C A Sheet-metal work, spun hollow wear, tin stock2014 C C-B C-B heavy-duty forgings, plate and extrusions for

aircraft structural components, wheels.3003 A D-C A Cooking utensils, chemical equipment, pressure

vessels, sheet metal work, buildershardware,storage tanks

5054 A D-C A Welded structures, pressure vessels, tube for

marine uses.6061 B D-C A Trucks, canoes, furniture, structural applications7005 D B-D B Extruded structural members, large heat

exchangers, tennis racquets and softball bats.

* From A (excellent) to D (poor)


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Properties of Wrought Magnesium Alloys

Table 3.8 Properties and typical forms of various wrought magnesium alloys.

COMPOSITION (%) ALLOY Al Zn Mn Zr

CONDI-TION

ULTIMATETENSILE

STRENGTH(MPa)

YIELDSTRENGTH

(MPa)

ELONGA-TION

IN 50 mm(%) TYPICAL FORMS

AZ31B

AZ80AHK31A

*

ZK60A

3.0

8.5

1.0

0.5

5.7

0.2

0.20.7

0.55

FH24T5

H24T5

260290380255365

200220380255365

151578

11

ExtrusionsSheet and platesExtrusions and forgingsSheet and platesExtrusions and forgings

* HK31A also contains 3% Th.

Properties of Wrought Copper and Brasses


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Properties of Wrought Copper and Brasses

Table 3.9 Properties and typical applications of various wrought copper and brasses.

TYPE

AND UNSNUMBER

NOMINAL

COMPOSI-TION (%)

ULTIMATETENSILE

STRENGTH(MPa)

YIELD

STRENGTH(MPa)

ELONG- ATION IN

50 mm (%) TYPICAL APPLICATIONSOxygen-freeelectronic(C10100)

99.99 Cu 220-450 70-365 55-4 Busbars, waveguides, hollow conductors,lead in wir es, coaxial cables and tubes,microwave tubes, rectifiers.

Red brass,85%(C23000)

85.0 Cu15.0 Zn

270-72 70-435 55-3 Weather-stripping, conduit, sockets,fasteners, fire extinguishers, condenser andheat exchanger tubing

Low Brass,80%(C24000)

80.0 Cu20.0 Zn

300-850 80-450 55-3 Battery caps, bellows, musical instruments,clock dials, flexible hose.

Free-cuttingbrass(C36000)

61.5 Cu,3.0 Pb,35.5 Zn

340-470 125-310 53-18 Gears, pinions, automatic high-speedscrew machine parts

Naval brass(C46400 toC46700)

60.0 Cu,39.25 Zn,0.75 Sn

380-610 170-455 50-17 Aircraft turnbuckle barrels, balls, bolts,marine hardware, valve stems, condensor plates

Brass= copper + zincBronze= copper + tin or copper + aluminum


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Properties of Wrought Bronzes

Table 3.10 Properties and typical applications of various wrought bronzes.

TYPE AND UNSNUMBER

NOMINALCOMPOSI-TION (%)

ULTIMATETENSILE

STRENGTH(MPa)

YIELDSTRENGTH

(MPa)

ELONG- ATION IN50 mm (%)

TYPICAL APPLICATIONS Architecturalbronze(C38500)

57.0 Cu,3.0 Pb,40.0 Zn

415 140(As

extruded)

30 Architectural extrusions, store fronts,thresholds, trim, butts, hinges

Phosphor bronze, 5% A (C51000)

95.0 Cu,5.0 Sn,trace P

325-960 130-550 64-2 Bellows, clutch disks, cotter pins,diaphragms, fasteners, wire brushes,chemical hardware, textile machinery

Free-cuttingphosphor bronze(C54400)

88.0 Cu,4.0 Pb,4.0 Zn,4.0 Sn

300-520 130-435 50-15 Bearings, bushings, gears, pinions, shafts,thrust washers, valve parts

Low siliconbronze, B(C65100)

98.5 Cu,1.5 Si

275-655 100-475 55-11 Hydraulic pressure lines, bolts, marinehardware, electrical conduits, heatexchanger tubing

Nickel-silver, 65-18(C74500)

65.0 Cu,17.0 Zn,18.0 Ni

390-710 170-620 45-3 Rivets, screws, zippers, camera parts, basefor silver plate, nameplates, etching stock.


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Properties of Nickel Alloys

Table 3.11 Properties and typical applications of various nickel alloys (all alloy names aretrade names).

ALLOY(CONDITION)

PRINCIPAL ALLOYINGELEMENTS

(%)

ULTIMATETENSILE

STRENGTH(MPa)

YIELDSTRENGTH

(MPa)

ELONGATIONin 50 mm

(%) TYPICAL APPLI CATIONSNickel 200(annealed)

None 380-550 100-275 60-40 Chemical and food processingindustry, aerospace equipment,electronic parts

Duranickel 301(agehardened)

4.4 Al,0.6 Ti

1300 900 28 Springs, plastics extrusion equipment,molds for glass, diaphragms

Monel R-405(hot rolled)

30 Cu 525 230 35 Screw-machine products, water meter parts.

Monel K-500(agehardened)

29 Cu,3Al

1050 750 20 Pump shafts, valve stems, springs

Inconel 600(annealed)

15 Cr,8 Fe

640 210 48 Gas turbine parts, heat-treatingequipment, electronic parts, nuclear reactors

Hastelloy C-4(solution-treated andquenched)

16 Cr,15 Mo

785 400 54 High temperature stability, resistanceto stress corrosion cracking


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Properties of Nickel-Base Superalloys

Table 3.12 Properties and typical applications of various nickel-base superalloys at 870C(1600 F). All alloy names are trade names.

ALLOY CONDITION ULTIMATETENSILE

STRENGTH(MPa)

YIELDSTRENGTH

(MPa)

ELONGATIONIN 50 mm

(%)

TYPICAL APPLICATIONS

Astroloy Wrought 770 690 25 Forgings for high temperatureHastelloy X Wrought 255 180 50 Jet engine sheet partsIN-100 Cast 885 695 6 Jet engine blades and wheelsIN-102 Wrought 215 200 110 Superheater and jet engine parts

Inconel 625 Wrought 285 275 125 Aircraft engines and structures,chemical processing equipmentInconel 718 Wrought 340 330 88 Jet engine and rocket partsMAR-M 200 Cast 840 760 4 Jet engine bladesMAR-M 432 Cast 730 605 8 Integrally cast turbine wheelsRen 4 1 Wrought 620 550 19 Jet engine partsUdimet 700 Wrought 690 635 27 Jet engine partsWaspaloy Wrought 525 515 35 Jet engine parts


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Properties of Wrought Titanium Alloys

Table 3.13 Properties and typical applications of wrought titanium alloys.

ROOM TEMPERATURE VARIOUS TEMPE RATURES

NOMINALCOMPOSI-TION (%) UNS

COND-ITION

ULTIMATETENSILE

STRENGTH(MPa)

YIELDSTRENGTH

(MPa)

ELON-GATION

IN 50mm (%)

REDUC-TION

OF AREA(%)

TEMP( C)

ULTIMATETENSILE

STRENGTH(MPa)

YIELDSTRENGTH (MPa)

ELON-GATION

IN 50mm (%)

REDUC-TION

OF AREA(%) TYPICAL APPLICATIONS

99.5 Ti R50250

Annealed 330 240 30 55 300 150 95 32 80 Airframes; chemical, desalination,and marine parts; plate type heatexchangers

5 Al, 2.5Sn

R54520

Annealed 860 810 16 40 300 565 450 18 45 Aircraft engine compressor blades and ducting; steam turbineblades

6 Al, 4 V R56400

Annealed 1000 925 14 30 300425550

725670530

650570430

141835

354050

Rocket motor cases; blades anddisks for aircraft turbines andcompressors; orthopedic implants

Solution+ age

1175 1100 10 20 300 980 900 10 28 structural forgings and fasteners

13 V 11 Cr

3 Al

R58010

Solution+ age

1275 1210 8 - 425 1100 830 12 - High strength fasteners;aerospace components;

honeycomb panels.

03-manufacturing properties of metals

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