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& Data & Reference Manual Data & Reference Manual To Titanium Industries Data and Reference Guide ! This Acrobat document contains all of the information in the hard copy version. Any page or the complete manual can be selected and printed using the print set up and print options from the file menu. Take advantage of the “FIND” feature which allows searching utilizing key words. This reader also contains a “Bookmark” function which acts as an index. When activated, you can immediately access a topic by clicking on it! Thank you for visiting the Titanium Web Site! March 1998

Transcript of Data & Reference ManualData & Reference Manual - reference manual.pdf · Data & Reference...

&

Data & Reference ManualData & Reference Manual

To Titanium Industries Data and Reference Guide !

This Acrobat document contains all of the information in thehard copy version. Any page or the complete manual can beselected and printed using the print set up and print optionsfrom the file menu.

Take advantage of the “FIND” feature which allowssearching utilizing key words.

This reader also contains a “Bookmark” function which actsas an index. When activated, you can immediately access atopic by clicking on it!

Thank you for visiting the Titanium Web Site!

March 1998

Data and Reference Manual

Table of Contents

Page

History and Production of Titanium . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1

Machining Titanium Alloys . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-8

Forming Titanium . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8

Welding Titanium . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

Room Temperature Properties . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

Working with 6AL-4V, 6AL-4V ELI . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10-11

Working with CP GR2, CP GR4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12-13

Measurement Conversions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14-15

Weight Formulas . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16-17

Converting Rounds to Hexagons and Squares . . . . . . . . . . . . . . . . . . . . . . . . 18-19

Metallurgical Definitions . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

Metallurgical Comparisons . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

General Specifications & ASTM Grades . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20-21 Military Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22-23

International Specifications . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

Fire Prevention . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

Corrosion Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

Rutile Oreor

Upgraded Ilmenite

Ore

TitaniumTetrachloride

Titanium Sponge

TitaniumScrap

Alloying Elements

Ingots

Remeltingand Finishing

to Mill Products

ArcMelting

Hearth Melting

MagnesiumTetrachloride

Reduction

1

TITANIUM & TITANIUM ALLOYS

Metallic titanium was first isolated in impure form in Titanium metal is abundant in the earth’s crust and is1887 and with higher purity in 1910; however, it was not extracted commercially from the ore minerals rutileuntil the 1950's that it began to come into use as a (titanium dioxide) and ilmenite (iron-titanium oxide). structural material. This was initially stimulated by air- The commercial extraction process involves treatmentcraft applications. Although the aerospace industry still of the ore with chlorine gas to produce titanium tetra-provides the major market, titanium and titanium alloys chloride, which is purified and reduced to a metallicare finding increasingly widespread use in other titanium sponge by reaction with magnesium or sodium. industries due to their many desirable properties. The sponge, blended with alloying elements (and re-Notable among these is their low densities, which fall claimed scrap) as desired, is then vacuum melted. between those of aluminum and iron and give very Several meltings may be necessary to achieve aattractive strength-to-weight ratios. In addition, titanium homogeneous ingot which is ready for processing intoand titanium alloys readily form stable protective sur- useful shapes, typically by forging followed by rolling. face layers which give them excellent corrosion For many applications the cost of titanium alloys canresistance in many environments, including oxidizingacids and chlorides, and good elevated temperatureproperties up to about 440 degrees C (1022 degrees F) insome cases.

be justified on the basis of desirable properties.

TITANIUM PRODUCTION Titanium, the fourth most abundant metallic element in the earth’s crust, occurs chiefly as an oxide ore. Thecommercially important forms are rutile (titanium dioxide) and ilmenite (titanium-iron oxide) the former beingrichest in titanium content. Titanium can be produced in the following manner:

2

Structural titanium alloys are coming in for increaseduse because they are light, ductile and have goodfatigue and corrosion-resistance properties. As aresult, more manufacturing engineers are learningthat machining these alloys can be a tricky job due totheir unique physical and chemical properties. Theproblems that arise in drilling, turning, and grindingof titanium can be better understood if we look atthese properties. They hold the key to successfulmachining operations.

Table 1 compares the general properties ofcommercially pure titanium with other commonlymachined metals. The specific weight of titanium isabout two-thirds that of steel and about 60 percenthigher than that of aluminum. In tensile and sheet

stiffness, titanium falls between steel and aluminum. But titanium's strength (80,000 PSI for pure titaniumand 150,000 PSI and above for its alloys) is fargreater than that of many alloy steels, giving it thehighest strength-to-weight ratio of any of today'sstructural metals.

Thermal properties are another matter. Titaniumalloys have high melting points, which is usually asign of excellent temperature stability. However, thestrengths of titanium alloys fall off rapidly attemperatures above 800 degrees F, and theircoefficients of expansion are even less than that forsteels. These unusually poor thermal propertiesaccount, to a large extent, for the difficulties inmachining titanium.

Machining Titanium Alloys By Dr. H.E. Trucks

TABLE 1 PROPERTIES OF TITANIUM AND OTHER STRUCTURAL METALS

PROPERTY TITANIUM STEEL STAINLESS ALUMINUM1020 18-8 7075

Structure * HCP BCC FCC FCCSpecific weight lb./cu in. 0.16 0.28 0.28 0.10Ultimate tensile strength, annealed, psi 80,000 50,000 90,000 12,000Young's modulus, E, psi x 10 16 30 30 106

Shear modulus, G, psi x 10 6 11.5 11.5 46

Melting point. 3200 2600 2600 1220 FCoefficient of linear expansion, F, x 10 5 6.6 9 13-6

Thermal conductivity, k, 2.0 7.5 2.2 16 Btu/in./sec/ ( F/in.) X 10-4

*HCP = hexagonal close-packed lattice; BCC = body centered cubic; FCC = face-centered cubic

A CLOSE LOOK

Titanium alloys have a hexagonal closed-packed (HCP) raising the beta transformation temperature to aboutlattice structure similar to magnesium alloys. However,at about 1625 degrees F, titanium undergoes anallotropic transformation, changing from HCP to a body-centered cubic (BCC) structure. These allotropic formsof titanium are known as alpha and beta respectively. Alloying elements favor one or the other. For example, a6-percent aluminum addition stabilizes the alpha phase,resulting in an increase in the alpha + beta and

1820 degrees F (±25 degrees F). It also increasesthe metal's elevated temperature strength level. Chromium, iron, molybdenum, manganese andvanadium lower the transformation temperature,thereby making the beta phase stable at a lowertemperature.

3

A CLOSE LOOK Continued

Titanium alloys fall into three classes, depending on TI-6Al-6V-2Sn, an extension of the aluminum-the structures present. In addition to the alpha and vanadium-titanium system, is the most highly beta-beta phases described in the preceding paragraph, stabilized grade of the alpha-beta the alpha phasethere is also an alpha-beta phase that includes most and increases the hot-workability range by raising theof the titanium alloys now in use. beta transus temperature to approximately 1735

TI-6Al-4V, an alloy introduced in 1954, comes as level above which the alpha phase in the structureclose to being a general-purpose grade as possible in transforms completely into the beta phase in antitanium. In fact, it's considered the workhorse equilibrium condition.)titanium alloy and is available in all product forms. Itsdensity is 0.160 pound per cubic inch. It can be heat- The alloying elements used in TI-6Al-6V-2Sn permittreated to ultimate strengths in excess of 170,000 PSI heat-treatment of the alloy to high strength levels byand responds to heat-treatment in sections up to 1½ solution treatment and aging. Due to the deepinches. This alloy is stable at temperatures ranging hardening capability of this alloy, it is recommendedfrom 423 degrees F to over 1000 degrees F. for high-tensile-strength forgings.

degrees F. (The beta transus is the temperature

KEEP TOOLS SHARP

Titanium has a tendency to gall, and its chips can weldto the cutting edges of the tool. This is particularly soonce tool wear begins. Sharp tools should beemployed at all times and should be replaced beforethey dull. The feed should not be stopped while thetool and work piece are in moving contact.

Titanium's low modulus of elasticity can cause slenderwork pieces to deflect more than comparable pieces ofsteel. This can create problems of chatter, tool contactand holding tolerances.

The machining characteristics of titanium alloys changesignificantly at hardness levels of 38 Rockwell (Cscale). Above this hardness level, machiningoperations that normally employ high-speed-steel toolssuch as broaching, drilling, end milling and tapping)can present problems. In such cases, carbide toolingmay be required. Suggested feeds and speeds forturning, milling, drilling and grinding of titanium and itsalloys are provided in the tables on pages 5-6. Forturning and milling, speeds and feeds are provided forcarbide as well as high-speed-steel tooling.

High-speed steels are widely used for machiningtitanium because of their flexibility and lower cost thancemented carbides. When it comes to true tool

economy, do not equate least expensive tooling withthe most economical tooling; often the tooling that costsleast to buy ends up being the most expensive on a cost-per-cut basis. For best tool economy, the cutting toolshould be matched to the material being machined.

The machinability of materials can best be defined interms of tool life, power requirements and surface finish. Of these factors, tool life is usually the most important. In production operations, tool life is usually expressed asthe number of pieces machined per tool grind. Ingeneral, the aim of the manufacturing engineer is toachieve the optimum combination of tool life, productionrate, power input and surface finish for a givenmachining operation. This optimum condition results inan increase in production rate and a reduction in thecost of performing the operation. In order to determinethe most economical cutting-tool material for givenmachining operation. An analysis should be made as tothe break-even quantity of the cost of the cutting-toolmaterial being evaluated.

In conclusion, while titanium presents a unique set ofmachining problems, many of those problems can bealleviated or eliminated by adhering to the following setof guidelines:

4

The following pages are recommendations for speeds, feeds and otherparameters. The information presented in this booklet are nominalrecommendations and should be considered only as good starting points.

KEEP TOOLS SHARP Continued

Use the recommended cutting speeds and feeds. Use large volumes of recommended cutting fluids. Use the abrasion and heat-resisting cutting tools recommended in the tables. Replace cutting tools at the first sign of wear. Never stop feeding while the cutting tool and work piece are in moving contact.

It should be noted that these recommendations should be used as a guide and may vary slightly with various machinesand material input.

(NOTE: Portions of pages 5-6 have been reprinted from the Machine and Tool Blue Book Vol. 82 NO. 1 with permissiongranted by Dr. H.E. Trucks and Machine & Tool Blue Book

GRINDING OF TITANIUM

In grinding, the difference between titanium and other 2. Correct wheel speeds. A good guide is to use one-metals is the activity of titanium at high temperatures. At the localized points of wheel contact titanium canreact chemically with the wheel material. The mostimportant facts to consider in order to prevent this andensure successful grinding are:

1. Effective use of coolants. Water based soluble oils but the high speeds essential with these wheelscan be used but, in general, result in poor wheel life. Solutions of vapor-phase rust inhibitors of the nitriteamine type give good results with aluminum oxidewheels.

half to one-third of conventional operating wheelspeeds to get the best results with titanium.

3. Selection of proper wheels. Silicon carbide wheelscan be used at 4000-6000 surface feet per minute togive optimum surface finish at minimum wheel wear

produce intense sparking which can cause a firehazard unless the work is flooded with coolant. However, vitrified bond A60 wheels, hardness J-Mhave been successfully used at speeds of 1500 to2000 surface feet per minute while removing as muchas 0.08 cubic inches of metal per minute.

5

MILLING

HIGH SPEED STEEL CARBIDE TOOL

CONDITIONDepth of Tool Speed In. Feed Tool Speed In. FeedCut (in.) Material (fpm) (/TOOTH) Material (fpm) (/TOOTH)

Alloys Annealed .250 M-7, M-42 30 .006 C2 110 .006(BHN 320 - 370) .050 M-42 40 .004 C2 150 .004

Alloys STA .250 M-42 25 .007 C3 80 .006(BHN 375 - 420) .050 M-42 35 .004 C3 100 .004

Cutting Fluid: Water-based soluble oil or water-based chemicals for annealed condition. Highly chlorinated oil for STA condition.

DRILLING

FEED (INCHES/REVOLUTION AT INDICATEDNOMINAL HOLE DIAMETER -- INCHES)

CONDITIONTool Speed

Material (fpm) 1/8 1/4 ½ 3/4 1 1 ½ 2 3Alloys Annealed(BHN 320 - 370)

M-3, M-7, 20 .002 .005 .006 .007 .008 .009 .010 .011M-42

Alloys STA(BHN 375 - 420)

M-42, M-33 15 .0005 .001 .0015 .0015 .002 .002 .003 .004

Cutting Fluid: Water-based soluble oil or water-based chemical

GRINDING

WHEEL DESIGNATION WHEEL SPEED (fpm)

CONDITION of cut m Oxide Carbide m Oxide Carbide Speed Feed FeedType Aluminu Silicon Aluminu Silicon Table Down Cross

(fpm) in/Pass in\Pass

Alloys Annealed(BHN 320-370)

Rough A 46 JV C 46 JV 1500-2500 3000- 40 .001 .0625500

Finish A 60 LV A 70 LV 1500-2500 3000- 40 .0005 Max .0505500

Alloys STA(BHN 375-420)

Rough C 46 JV 3000- 40 .001 .0625500

Finish C 60 LV 3000- 40 .0005 Max .0505500

Grinding Fluid: Highly chlorinated oil or 10% sodium nitrite-amine

6

TURNING

HIGH SPEED STEEL CARBIDE TOOL SPEED (fpm)Condition Depth Tool Speed Feed Tool Brazed Throw-a- Feed

Of Material (fpm) (ipr) Material Tool way tool (ipr)Cut (in.)

Commercially .250 M-7 125 .015 C2 310 375 .015Pure .100 M-7 160 .008 C2 375 425 .008

.050 M-7 240 .008 C3 425 460 .005

Alloys Annealed .250 M-7 40 .015 C2 110 150 .015(BHN 320 - 370) .100 M-7 50 .010 C2 130 165 .010

.025 M-7 60 .005 C3 155 185 .005

Alloys STA .250 M-42 30 .010 C2 80 100 .010(BHN 375 - 420) .100 M-42 40 .010 C2 100 120 .010

.025 M-42 50 .005 C3 120 150 .005

TOOL GEOMETRY FOR TURNING TITANIUM

ROUGH & INTERRUPTED TURNING FINISH TURNING

TOOL ANGLE HSS Tools Carbide Tools HSS Tools Carbide Tools(degrees) (degrees) (degrees) (degrees)

Back rake 0 to +5 +5 to -5 0 to +5 0 to +05Side rake 0 to +15 0 to -5 0 to +5 0 to +15 Side cuttingedge

+6 to +15 +5 to +25 +5 to +6 0 to +20

End cuttingedge

+5 to +6 +6 to +10. +5 to +6 +6 to +10

End relief +5 to +7 +5 to +10 +5 to +7 +6 to +10Side relief +5 to +7 +5 to +10 +5 to +7 +5 to +10 Nose radius, in. .020 to .030 .030 to .045 .020 to .030 .030 to .045

JOINING OF TITANIUM

Titanium and titanium alloys can be readily joined Fusion, resistance, flash butt, electron beam,by normal mechanical fastener techniques. With diffusion bonding and pressure weldingthe exception of brazing and friction welding, techniques are available and are widelythese methods are the only satisfactory means of practiced to produce joints in titanium andmaking joints between two nonweldable titaniumalloys or between titanium and dissimilar materials.

titanium alloys.

7

JOINING OF TITANIUM Continued

Production of joints by fusion welding is restricted atmospheric gases is essential and can beto commercially pure titanium or weldable titanium achieved by supplying argon to the surfacesalloys. which reach a temperature above 450 degrees C

The D.C. argon-arc process (electrode negative)is recommended using titanium wire or tungstenelectrodes with titanium filler rods. Protectionfrom

either directly by blowing argon on to the weldarea or by carrying out the welding operationwithin an argon filled cabinet.

HINTS FOR MACHINING TITANIUM

Titanium can be fabricated using techniques which are Two other factors influence machining operations. no more difficult than those used to machine Type 316stainless steel. Commercially pure grades of titaniumwith tensile strengths of 35,000 to 80,000 psi machinefabricate far easier than the aircraft alloys (i.e.) 6Al-4Vwith tensile strengths up to 200,000 psi.

Titanium's work hardening rate is less than austeniticstainless steels, and about equivalent to 0.20 carbonsteel. Titanium requires low shearing forces, has anabsence of “built-up edge”, and is not notch sensitive. Titanium has been classified as difficult to machinedue to its physical properties. Heat caused by thecutting action does not dissipate quickly becausetitanium is a poor heat conductor. Titanium has astrong alloying tendency or chemical reactivity withmaterial in the cutting tools which cause galling,welding, smearing and rapid destruction of the cuttingtool. Due to its relatively low modulus titanium has atendency to move away from the cutting tool unlessheavy cuts are maintained or proper back-up isemployed.

1. Because of the lack of a stationary mass of metal(built-up edge) ahead of the cutting tool, a highshearing angle is formed. This causes a thin chip tocontact a relatively small area on the cutting toolface and results in high bearing loads per unit area. The high bearing force, combined with the frictiondeveloped by the chip as it rushes over the bearingarea results in a great increase in heat on a verylocalized portion of the cutting tool.

2. The combination of high bearing forces and heatproduces cratering action to the cutting edge,resulting in rapid tool breakdown. The basicmachining properties of titanium cannot be altered;however the following basic rules have beendeveloped in machining titanium:

Use low cutting speeds. A change of 20 surface feet per minute to 150 surface feet per minute using carbide tools results in a temperature change from 800 to 1700 F. Maintain high feed rates. Temperature is not affected by feed rate so much as by speed, and the highest feed rates consistent with good machining should be used. Use copious amounts of cutting fluid. Use sharp tools and replace them at the first sign of wear. Tool failure occurs quickly after a small initial amount of wear. Never stop feeding while tool and work are in moving contact. Allowing a tool to dwell in moving contact causes work hardening and promotes smearing, galling, seizing and tool breakdown.

8

HINTS FOR MACHINING TITANIUM Continued

Working with Titanium: Titanium is highly reactive Annealing of Titanium: Residual stress can be and will react with its environment at relatively low removed by annealing the titanium at a temperaturetemperatures. When it is heated in air, a self- between 932 and 1112 degrees F. Full annealing isprotective, titanium-oxide film, which is very adherent, accomplished at about 1292 degrees F. Heating ofwill form on its exposed surfaces. In many corrosive narrow or thin items must be done in a vacuum orenvironments, the film becomes a barrier and, in the inert-gas atmosphere. Atmospheric annealing isabsence of abrasion will decrease the corrosion rate. sufficient for forging, thick plate, etc. However, itIf titanium is heated in the presence of hydrogen, the must be done in an oxidizing atmosphere. Thetitanium readily absorbs the hydrogen. Upon cooling, titanium can be left in the furnace until it reachestitanium hydrides form and may seriously impair room temperature.ductility.

Forming of Titanium: Titanium can be formed intovarious shapes by bending, shearing, pressing, deep- easily be eliminated by pickling in a solution of 2%drawing, expanding, fluid pressure bulging, etc. hydrofluoric acid and 20% nitric acid. However,However, when designing, it is necessary to take into scales formed by full annealing under normalconsideration titanium's strong spring-back atmosphere (greater than 1292 degrees F) arecharacteristics. Forming high-yield strength alloy difficult to remove by pickling alone. These thicktitanium is difficult at room temperature -- a 392 to scales deteriorate corrosion resistant properties and752 degrees F temperature range is recommended. must be removed mechanically or by pickling by the

Descaling of Titanium: Scales formed duringatmospheric annealing (under 1112 degrees F) can

above mentioned mixture of acids.

(Note: “Hints for Machining Titanium” has been reprinted from OREMET Titanium technical data. OREMET is the parent company of Titanium Industries, Inc.)

FORMING TITANIUM

Commercially pure titanium is readily formed at after forming titanium for which compensationroom temperature, using techniques and equipment must be made.suitable for steel. When correct parameters havebeen established, tolerances similar to those 3. The galling tendency of titanium is greaterattainable with stainless steel are possible with than that of stainless steel. This necessitatestitanium and its alloys. close attention to lubrication in any forming

Recognition of several unique characteristics of (particularly moving contact) with metal dies ortitanium will aid in ease of forming: other forming equipment.

1. The room temperature ductility of titanium and itsalloys, as measured by uniform elongation, isgenerally less than that of other common structuralmetals. This means that titanium may require moregenerous bend radii and has lower stretchformability. Hot forming may be required for severebending or stretch forming operations.

2. The modulus of elasticity of titanium is about halfthat of steel. This causes significant spring back

operation in which titanium is in contact

Preparation for Forming

Normally, titanium surfaces are acceptable forforming operations as received from the mill. Gouges and other surface marks introducedduring handling should be removed by sanding. To prevent edge cracking, burred and sharpedges should be filed smooth before forming.

9

WELDING TITANIUM

In general, welding of titanium and its alloys can be Unalloyed titanium and alpha alloys arereadily performed, but it is necessary to exclude generally weldable and welded joints generallyreactive gases, including oxygen and nitrogen from have accep-table strength and ductility. the air, and to maintain cleanliness. Thus weld Postweld stress-relief annealing of weldments isproperties are heavily influenced by welding recommended. Some alpha-beta alloys,procedures, especially by the adequacy of inert gas specifically Ti-6Al-4V, are weldable in theshielding. annealed condition as well as in the solution

The GTAW (gas tungsten arc welding) process is be completed during the post-weld heatcommon, although GMAW (gas metal arc welding), treatment). Strongly stabilized alpha-beta alloysfriction welding, laser welding, resistance welding, can be embrittled by welding, the result of phaseplasma arc welding, electron beam welding, and transformations occurring in the weld metal ordiffusion bonding are all used in some cases. Both the heat affected zone. Some beta alloys arealloy composition and microstructure are important weldable in the annealed or the solution treatedin determining weldability, with the presence of betaphase having a deleterious effect.

treated and partially aged condition (aging can

condition.

ROOM TEMPERATURE MECHANICAL AND OTHER PROPERTIES

Grade/ 0.2% Proof Stress Ultimate Tensile Elongation Density WeldabilityRef. No. min Strength min min Rating

KSI MPa KSI MPa % lb/in gm/cc3

Grade 1 25 170 35 240 24 .163 4.51 Excellent

Grade 2 40 275 50 345 20 .163 4.51 Excellent

Grade 3 55 380 65 450 18 .163 4.51 Excellent

Grade 4 70 485 80 550 15 .163 4.51 Excellent

Ti 2% Pd (Gr7) 40 275 50 345 20 .163 4.51 Excellent

Grade 12 50 345 70 483 18 .163 4.51 Excellent

Ti-6AI-4V 120 830 130 895 10 .161 4.42 Good

Ti-4AI-4-Mo2.5Sn

125 850 170 1160 10 .167 4.60 Poor

Ti-10-2-3 160 1100 180 1250 8 .168 4.65 Good

Ti-15-3 160 1100 185 1280 10 .172 4.76 Excellent

Ti-6-2-4-2 120 830 160 1100 10 .164 4.54 Good

Ti6-2-4-6 140 970 190 1300 10 .168 4.65 Fair

10

MECHANICAL DATA for 6Al-4V & 6Al-4V ELI

Technical Data 6Al-4V 6Al-4V ELI

Guaranteed Guaranteed Room Typical Strength (%RT) Room Typical Strength (%RT)

Temperature & Ductility Temperature & DuctilityMinimum Mini mum400F 600F 800F 1000F -320F -423F

Ultimate Tensile Strength, psi 130,000 77 74 68 54 120,000 218,000 263,000

Yield Strength, 0.2% Offset, psi 120,000 75 68 63 45 202,000 248,000115,000

El in 2"(>0.025" thick), pct. 10 17 17 18 27 13.5 610

Reduction of Area, Percent 20 50.5 51.5 52.1 67.9 25

Bend Radius 4.5T 5T 4.5T , 5T

Impact, Charpy V, ft-lb. Room 18 19 Temp

Welded Bend Radius 6-10T 6-10T

Hardness Rc 30/34 Rc 30/34Rupture, Stress to Produce in ( ) 1000 hr 1000 hr Hr. psi 98,000 58,000Creep Data, Stress to Produce ( ) 0.1% 0.1%Percent elongation in ( ) Hr, psi 1000 hr 1000 hr

70,000 32,000

PHYSICAL PROPERTIES for 6Al-4V & 6Al-4V ELI

Technical Data 6Al-4V 6Al-4V ELI

Modulus of Elasticity, psi(10 ) Tension 16.5 16.56

Modulus of Elasticity, psi(10 ) Torsion Approximately 6.10 Approximately 6.106

Density, lb/cu Inch 0.160 0.160

Melting Range, Degree F Approximately 3000F Approximately 3000F

Specific Electrical Resistivity 171 at room temperature; 171 at room temperature micro ohms/cm/sq cm 187 at 800F

Specific Heat, Btu/lb/ F 0.135 at room temperature 0.125 at room temperature

Thermal Conductivity, Btu/hr.Ft ft 4.2 at room temperature; 6.8 at 800F2- F/

Mean Coefficient of 32- 212F 4.9 5.3

of Thermal Expansion 32- 600F 5.1 5.3

Per F. (10 ) 32-1000F 6 5.3 5.3

32-1200F 5.5 5.5

32-1500F 5.7 5.7

Oxidation Characteristics in Air 400F 600F 800F 1000F

Short Time Good Good Good Moderate Long Time Good Good Slight Moderate

11

REMARKS ON FABRICATION for 6Al-4V & 6Al-4V ELI

Technical Data 6Al-4V 6Al-4V ELI

Beta Transus 1830F± 25F 1830F± 25F

Cutting Readily cuts with saw or abrasive wheel Readily cuts with saw or abrasive wheel

Machining Rigid set-up, slow speed, heavy feed, sharp Rigid set-up, slow speed, heavy feed,tools, adequate coolant sharp tools, adequate coolant

Forming Formed at room temp. whenever possible. Formable: Warm forming useful withHot forming recommended for complex solution-treated material

structures. Joining, Welding Sound moderately ductile welds if protected. Sound ductile welds if protected

REMARKS ON HEAT TREATMENT for 6Al-4V & 6Al-4V ELI

Technical Data 6Al-4V 6Al-4V ELI

Initial Forging 1805F, no higher than 1775F to finish. 1800 - 1820F, no higher than 1750F tofinish

Annealing 1300-1550F 1-8 hr. , slow cool to 1300-1550F, 1-8 hr., AC1050F, AC

1700-1750F, 1 hr., water quench (bar) Not applicableSolution Treating 1660-1725F, 5-20 min. WQ(sheet and

plate)

Aging 1000F, 4 hr., AC Not applicable

Stress Relief Annealing 900-1200F, 1-4 hr., AC 900-1200F, 1-4 hr., AC

OTHER TECHNICAL DATA for 6Al-4V & 6Al-4V ELI

Technical Data 6Al-4V 6Al-4V ELI

Principal UsesAirframe and turbine engine parts (blades, Principle uses: Surgical appliances & implants,discs, wheels, spacer rings), ordnance orthopaedic implants, pressure vessels,equipment, pressure vessels, rocket motor airframes, etc.cases.

Available Forms Sheet, strip, plate, bar billet, wire, extrusions Sheet, strip, bar, billet, wire, extrusions, tubing

Nominal Composition0.08% max C, 0.05% max N, 0.015% max H 0.08% max C. 0.05% max N, 0.015%(sheet), 0.25% max Fe, 5.75-6.75% Al, 3.5- max H (sheet), 0.13% max O, 5.5-6.5% Al,4.5% V, 0.20% max O 3.5-4.5 % V, 0.25% max Fe

Type Structure Alpha-Beta Alpha-Beta

Footnotes for Charts on Pages 10-11

See reference 3 for properties in agedcondition.

0.0125% max 11 (bar). 0.0100% max 11 (billet).

<0.070 inch. >0.070 inch.

0.0125% max H (bar) 0.0100% max H (billet)

0.20 and below 8%: 10 % for plate;determined by configuration of bar and forgings.

<0.070 inch >0.070 inch Min. Yield 110,000 for 1.75 diameter or larger

12

MECHANICAL PROPERTIES for CP GR2 & CP GR4

Technical Data CP GR2 CP GR4

Guaranteed Guaranteed Room Typical Strength (%RT) Room Typical Strength (%RT)Temperature & Ductility Temperature & Ductility Minimum Minimum200F 400F 600F 800F 1000F 200F 400F 600F 800F 1000F

Ultimate Tensile Strength, psi 50,000 80 57 46 36 28 80 57 46 36 2880,000

Yield Strength, 0.2% Offset, psi 40,000 76 46 30 26 20 76 46 30 26 2070,000

El in 2"(>0.025" thick), pct. 42 37 25 3122 15

Reduction of Area, Percent 57 76 76 7535 35

Bend Radius 2T 2.5T 2T 2.5T

Impact, Charpy V, ft-lb. Room 11-15Temp.

Welded Bend Radius Approx. 3-4T Approx. 3-4T

Hardness Brinell 200 Brinell 265Rupture, Stress to Produce in ( ) 225 hr 430 hr Hr. psi 65,000 17,000

PHYSICAL PROPERTIES for CP GR2 & CP GR4

Technical Data CP GR2 CP GR4Modulus of Elasticity, psi(10) Tension6 14.9 15.1

Modulus of Elasticity, psi(10) Torsion6 Approximately 6.5 Approximately 6.5

Density, lb/cu Inch 0.163 0.164

Melting Range, Degree F 3000-3100F 3020F± 18F

Specific Electrical Resistivity micro 56 60 ohms/cm/sq cm

Specific Heat, Btu/lb/ F 0.125 at room temperature 0.129

Thermal Conductivity, Btu/hr.Ft ft2- F/ Approx. 9.5 at room temp. Approx. 9.8 at room temp.

Mean Coefficient of 32- 212F 4.8 4.8

of Thermal Expansion 32- 600F 5.1 5.1

Per F. (10 ) 32-1000F 6 5.4 5.4

32-1200F 5.6 5.6

32-1500F 5.6 5.6

Oxidation Characteristics in Air 400F 600F 800F 1000F 400F 600F 800F 1000F

Short Time Good Good Good Moderate Good Good Good Moderate

Long Time Good Good Slight Moderate Good Good Slight Moderate

13

REMARKS ON FABRICATION for CP GR2 & CP GR4

Technical Data CP GR2 CP GR4Beta Transus 1675F±25F 1740F ± 25 F

Cutting Readily cut with saw or abrasive wheel Readily cut with saw or abrasive wheel

Machining Rigid set-up, medium speed, heavy Rigid set-up, slow speed, heavy feed,feed, sharp tools, adequate coolant sharp tools, adequate coolant

Forming Readily formable at room temp. Readily formable at room temp. ComplexComplex shapes require heat. shapes require heat.

Joining, Welding Completely weldable, fusion welding Completely weldable, fusion weldingrequires protection. requires protection.

REMARKS ON HEAT TREATMENT for CP GR2 & CP GR4

Technical Data CP GR2 CP GR4Initial Forging Approx. 1650F rough breakdown, Approx. 1715F rough breakdown, finish

finish 1550F 1550F

Annealing 1300F, 2hr, air cool 1300F, 2hr, air cool

Solution Treating Not applicable Not applicable

Aging Not applicable Not applicable

Stress Relief Annealing 900-1000F, 45 min. 900-1000F, 45 min.

OTHER TECHNICAL DATA for CP GR2 & CP GR4

Technical Data CP GR2 CP GR4

Principal Uses chemical industry, applications where applications.Airframe applications, skins, Airframe, chemical, marine and similar

maximum formability required withmoderate strength.

Available Forms Sheet, strip, plate, bar, billet, wire, Sheet, strip, plate, bar, billet, wire,tubing, extrusions. tubing, extrusions.

Nominal Composition 0.08% max C, 0.05% max N, 0.015% 0.08% max C, 0.05% max N, 0.015%max H (sheet), 0.20% max Fe. max H (sheet), 0.30% max Fe

Type Structure Alpha Alpha

Footnotes for Charts on pages 12-13

0.0125% max H (bar). 0.0100% max (billet)

Sheet Bar <0.070 inch thick. >0.070 inch thick.

Highest strength commercially puresheet grade

0.0125% maxH (bar) 0.0100% max (billet)

Sheet Bar: 70,000 Bar: 60,000 Bar <0.070 inch thick >0.070 inch thick.

1/4

3/8

1/2

3/16

5/16

1/8

7/16

1/16

5/8

11/16

13/16

9/16

7/8

15/16

1

3/4

.01562 0.397

.03125 0.794

.04688 1.191

.06250 1.588

3/64

1/32

1/64

5/64 .07812 1.984

.09375 2.381

.10938 2.778

.12500 3.175

3/32

7/64

.14062 3.572

.15625 3.969 .17188 4.366

.18750 4.763

.20312 5.159

.21875 5.556

.23438 5.953

.25000 6.350

9/64

5/3211/64

13/64

7/32

15/64

.26562 6.747

.28125 7.144

.29688 7.541

.31250 7.938

.32812 8.334

.34375 8.731 .35938 9.128

.37500 9.525

.39062 9.922

.40625 10.319

.42188 10.716

.43750 11.113 .45312 11.509

.46875 11.906

.48438 12.303

.50000 12.700

17/64

9/32

19/64

21/64

11/3223/64

25/64

13/32

27/64

15/32

31/64

.53125 13.494

.51562 13.097

.54688 13.891

.56250 14.288 .57812 14.684

.59375 15.081

.60398 15.478

.65625 16.669

.62500 15.875

.64062 16.272

.67188 17.066

.68750 17.463

.70312 17.859

.71875 18.256

.73438 18.653

.75000 19.050 .76562 19.447

.78125 19.844

.79688 20.241

.81250 20.638

.82812 21.034

.84375 21.431 .85938 21.828

.87500 22.225

.89062 22.622

.90625 23.019

.92188 23.416

.93750 23.813 .95312 24.209

.96875 24.606

.98438 25.003

1.00000 25.400

29/64

33/64

17/32

35/64

37/64

19/32

39/64

41/64

21/3243/64

45/64

23/32

47/64

49/64

25/32

51/64

53/64

27/3255/64

57/64

29/32

59/64

61/64

31/32

63/64

Fraction Decimal mm Fraction Decimal mm

14

DECIMAL AND METRIC EQUIVALENTS OF COMMON FRACTIONS OF AN INCH

15

U.S. AND METRIC SYSTEM EQUIVALENTS

UNIT Millimeter Centimeter Inch Feet Yard Meter Mile(Statute)

1 Millimeter 1 .1 .03937 .003281 .001094 .0011 Centimeter 10 1 .3937 .032808 .010936 .011 Inch 25.4001 2.54001 1 .083333 .027778 .0254001 Foot 304.801 30.4801 12 1 .333333 .3048011 Yard 914.402 91.4402 36 3 1 .9144021 Meter 1000 100 39.37 3.28083 1.09361 11 Kilometer 3280.8 1093.6 1000 .621371 Mile (Statute) 5280 1760 1609. 1

Grain Gram Ounce Ounce Pound Pound Kilogram(Troy) (Avoir) (Troy) (Avoir.)

1 Grain 1 .064799 .002083 .002286 .000174 .000143 .0000651 Gram 15.4324 1 .32151 .035274 .002679 .002205 .0011 Ounce (Troy) 480 31.1035 1 1.09714 .083333 .068571 .0311041 Ounce (Avoir.) 437.5 28.3495 .911458 1 .075955 .0625 .0283501 Pound (Troy) 5760 373.242 12 13.1657 1 .822857 .3732421 Pound (Avoir.) 7000 453.592 14.5833 16 1.21528 1 .4535921 Kilogram 15432.4 1000 32.1507 35.2740 2.67923 2.20462 1

Metric Ton Net Ton Gross Ton Pound Pound Kilogram(Short) (Long) (Troy) (Avoir.)

1 Metric Ton 1 1.10231 .984206 2679.23 2204.62 10001 Net (Short) Ton .907185 .892857 2430.56 2000 907.1851

1 Gross (long) Ton 1.01605 1.12 1 2722.22 2240 1016.05

Millimeter Centimeter Decimete Decameter Hectometer Kilometerr

1 Meter .001m .01m .10m 10m 100m 1000m

Milligram Centigram Decigram Decagram Hectogram Kilogram Ton1 Gram .001g .01g .1g 10g 100g 1000g 1,000,000g

Troy Weight: 12 oz. to 1 lb.Avoirdupois Weight: 16 oz. to 1 lb.

16

TITANIUM WEIGHT FORMULAS

(All weights are predicated upon a cubic inch of titanium weighing .163 pound.)

ROUNDS Lbs. per Lineal Foot = 1.5369 X Diameter2 Lbs. per Lineal Inch = .1281 X Diameter2

SQUARES Lbs. per Lineal Foot = 1.9568 X Diameter2 Lbs. per Lineal Inch = .1631 X Diameter2

RECTANGLES Lbs. per Lineal Foot = 1.9568 X Thickness X Width Lbs. per Lineal Inch = .1631 X Thickness X Width

HEXAGONS Lbs. per Lineal Foot = 1.6947 X Diameter2 Lbs. per Lineal Inch = .1412 X Diameter2

OCTAGONS Lbs. per Lineal Foot = 1.6211 X Diameter2 Lbs. per Lineal Inch = .1351 X Diameter2

CIRCLES Weight of Circles in Lbs. = .1281 X Thickness X Diameter2

17

TITANIUM WEIGHT FORMULAS Continued

RINGS Weight of Rings in Lbs. = .1281 X Thickness X (Outside Diameter2 - Inside Diameter2)

SHEET / PLATELbs. per Square Foot = Thickness X 23.472

ROUND SEAMLESS TUBINGW = 6.14 (D-T) TW = Weight in Pounds per FootD = Outside Diameter in Inches and Decimals of an InchT = Wall Thickness in Decimals of an Inch

SQUARE SEAMLESS TUBINGW = 7.82 (D-T) TW = Weight in Pounds per FootD = Outside Diameter in Inches and Decimals of an Inch

Measured at Right Angles to the SidesT = Wall Thickness in Decimals of an Inch

RECTANGULAR SEAMLESS TUBINGW = 3.9095 (A + B-2T) TW = Weight in Pounds per Foot

A and B = The two outside dimensions in inches measured at right angles to the sides

T = Wall Thickness in Decimals of an Inch

D Ed

F

18

SIZES OF ROUNDS REQUIRED TO MAKE HEXAGONS OR SQUARESDISTANCES ACROSS CORNER OF HEXAGONS AND SQUARES

Distances across Cornersof Hexagons and Squares

D=1/1547dE=1.4142dF=0.5773d

d D E F d D E F1/16 0.0721 0.0884 0.0361 1-11/32 1.5516 1.9003 0.77541/8 0.1443 0.1767 0.0721 1-3/8 1.5877 1.9445 0.7934

3/16 0.2164 0.2651 0.1082 1-13/32 1.6238 1.9887 0.81141/4 0.2886 0.3535 0.1443 1-7/16 1.6598 2.0329 0.8295

9/32 0.3247 0.3977 0.1623 1-15/32 1.6959 2.0771 0.84755/16 0.3603 0.4419 0.1803 1-1/2 1.7320 2.1213 0.865511/32 0.3698 0.4861 0.1983 1-17/32 1.7681 2.1655 0.88363/8 0.4329 0.5303 0.2164 1-9/16 1.8042 2.2097 0.9016

13/32 0.4690 0.5745 0.2344 1-19/32 1.8403 2.2539 0.91967/16 0.5051 0.6187 0.2524 1-5/8 1.8764 2.2981 0.937715/32 0.5412 0.6629 0.2705 1-21/32 1.9124 2.3423 0.95571/2 0.5773 0.7071 0.2885 1-11/16 1.9485 2.3865 0.9742

17/32 0.6133 0.7513 0.3065 1-23/32 1.9846 2.4306 0.99189/17 0.6494 0.7955 0.3246 1-3/4 2.0207 2.4708 1.009819/32 0.6855 0.8397 0.3426 1-25/32 2.0568 2.5190 1.02785/8 0.7216 0.9839 0.3606 1-13/16 2.0929 2.5832 1.0459

21/32 0.7576 0.9281 0.3787 1-27/32 2.1289 2.6074 1.063911/16 0.7937 0.9723 0.3967 1-7/8 2.1650 2.6516 1.081923/32 0.8298 1.0164 0.4147 1-29/32 2.2011 2.6958 1.10003/4 0.8659 1.0606 0.4328 1-15/16 2.2372 2.7400 1.1180

25/32 0.9020 1.1048 0.4508 1-31/32 2.2733 2.7842 1.136013/16 0.9380 1.1490 0.4688 1-3/32 1.2629 1.5468 0.631127/32 0.9741 1.1932 0.4869 1-1/8 1.2990 1.5910 0.64917/8 1.0102 1.2374 0.5049 1-5/32 1.3351 1.6352 0.6672

29/32 1.0463 1.2816 0.5229 1-3/16 1.3712 1.6793 0.685215/16 1.0824 1.3258 0.5410 1-7/32 1.4073 1.7235 0.703231/32 1.1184 1.3700 0.5590 1-1/4 1.4434 1.7677 0.7213

1 1.1547 1.4142 0.5770 1-9/32 1.4794 1.8119 0.73931-1/32 1.1907 1.4584 0.5950 1-5/16 1.5155 1.8561 0.75731-1/16 1.2268 1.5026 0.6131

D Ed

F

19

SIZES OF ROUNDS REQUIRED TO MAKE HEXAGONS OR SQUARES DISTANCES ACROSS CORNER OF HEXAGONS AND SQUARES Continued

Distances across Cornersof Hexagons and Squares

D=1/1547dE=1.4142dF=0.5773d

d D E F d D E F2 2.3094 2.8284 1.1540 2-3/8 2.7423 3.3587 1.3704

2-1/32 2.3453 2.8726 1.1720 2-7/16 2.8146 3.4471 1.40652-1/16 2.3815 2.9168 1.1901 2-1/2 2.8867 3.5355 1.44252-3/32 2.4176 2.9610 1.2081 2-9/16 2.9583 3.6239 1.47862-1/8 2.4537 3.0052 1.2261 2-5/8 3.0311 3.7123 1.51472-5/32 2.4898 3.0404 1.2442 2-11/16 3.1032 3.8007 1.55072-3/16 2.5259 3.0936 1.2622 2-3/4 3.1754 3.8891 1.58682-1/4 2.5981 3.1820 1.2983 2-13/16 3.2476 3.9794 1.62292-5/16 2.6702 3.2703 1.3343 3-13/16 4.4023 5.3917 2.19992-7/8 3.3197 4.0658 1.6589 3-7/8 4.4744 5.4801 2.2359

2-15/16 3.3919 4.1542 1.6950 3-15/16 4.5466 5.5684 2.27203 3.4641 4.2426 1.7310 4 4.6188 5.6568 2.3080

3-1/16 3.5362 4.3310 1.7671 4-1/8 4.7631 5.8336 2.38013-1/8 3.6084 4.4194 1.8032 4-1/4 4.9074 6.0104 2.45233-3/16 3.6806 4.5078 1.8392 4-3/8 5.0518 6.1872 2.52443-1/4 3.7627 4.5962 1.8753 4-1/2 5.1961 6.3639 2.59653-5/16 3.8219 4.6846 1.9114 4-3/4 5..485 6.717 2.74003-3/8 3.8971 4.7729 1.9474 5 5.774 7.071 2.89003-7/16 3.9692 4.8613 1.9835 5-1/4 6.062 7.425 3.03003-1/2 4.0414 4.9497 2.0196 5-1/2 6.351 7.778 3.19003-9/16 4.1136 5.0381 2.0556 5-3/4 6.640 8.132 3.32003-5/8 4.1857 5.1265 2.0917 6 6.928 8.485 3.4600

3-11/16 4.2579 5.2149 2.1277

20

METALLURGICAL DEFINITIONS

STRESS Force per unit area.

STRAIN A measure of the relative change in the size or shape of a body.

STRESS-STRAIN CURVES Plot of stress (in lbs./in ) versus strain (usually in in./in.).2

MACRO Refers to macroscopic examination, capable of being seen with the unaided eye.

MICRO Refers to microscopic examination, requires visual enhancement to be viewed .

COMPARATIVE STRENGTH TO WEIGHT RATIOS OF TITANIUM AND OTHER ALLOYS

Material Yield Strength Density Yield Strength to % Ratio relative to % Ratio ralative to MPa g/cc Density Ratio Ti-Grade 2 Ti-Grade 5

Ti-Grade 2 275 4.51 61 100 32

Ti-Grade 5 830 4.42 188 308 100

316 Stainless 230 7.94 29 48 15

254 SMO 300 8.00 38 62 20

2205 Duplex 450 7.80 58 95 31

Monel 400 175 8.83 20 32 11

Inconel 625 415 8.44 49 80 26

Hastalloy C-276 355 8.89 40 66 21

70/30 Cu-Ni 120 8.90 13 21 7

GENERAL SPECIFICATIONS

ASTM B265 Plate and Sheet ASTM B299 Sponge ASTM B337 Pipe (Annealed) Seamless and welded ASTM B338 Welded Tube ASTM B348 Bar and Billet ASTM B363 Fittings ASTM B367 Castings ASTM B381 Forgings ASTM B862 Pipe - As welded, no anneal ASTM B863 Wire - Titanium and titanium alloy ASTM F1108 6Al-4V Castings for surgical implants ASTM F1295 6Al-4V Niobium alloy for surgical implant applications ASTM F1341 Unalloyed titanium wire for surgical implant applications ASTM F136(e-1) 6Al-4V ELI alloy for surgical implant applications.

Editorial changes were made throughout March 1994 ASTM F1472 6Al-4V for Surgical implant applications ASTM F620 6Al-4V ELI Forgings for surgical implants ASTM F67 Unalloyed titanium for surgical implant applications

21

TITANIUM ASTM GRADES

ASTM Grade Alloy Composition Minimum Tensile Minimum Yield Elastic Modulus (KSI) (KSI) (PSI -10 )6

1 Unalloyed Ti 35 25 14.9

2 Unalloyed Ti 50 40 14.9

3 Unalloyed Ti 65 55 14.9

4 Unalloyed Ti 80 70 15

5 Ti-6AL-4V 130 120 16.4

6 Ti-5Al-2.5Sn 120 115 16

7 Ti-0.15Pd 50 40 14.9

9 Ti-3Al-2.5V 90 70 13.1

10 Ti-11.5Mo-6Zr-4.5Sn 100 90 14.9

11 Ti-0.15Pd 35 25 14.9

12 Ti-0.3-Mo-0.8Ni 70 50 14.9

13 Ti-0.5Ni-0.05Ru 40 25 14.9

14 Ti-0.5Ni-0.05Ru 60 40 14.9

15 Ti-0.5Ni-0.05Ru 70 55 14.9

16 Ti-0.05Pd 50 40 14.9

17 Ti-0.05Pd 35 25 14.9

18 Ti-3Al-2.5V-0.05Pd 90 70 15.3

19 Ti-3Al-8V-6Cr-4Zr-4Mo 115 110 14.9

20 Ti-3Al-8V-6Cr-4Zr-4Mo-0.05Pd 115 110 14.9

21 Ti-15Mo-2.7Nb-3Al-0.25Si 115 110 14.9

23 Ti-6Al-4V ELI 120 110 16.3

24 Ti-6Al-4V-0.05Pd 130 120 16.4

25 Ti-6Al-4V-0.5Ni-0.05Pd 130 120 16.4

26 Ti-0.1Ru 50 40 14.9

27 Ti-0.1Ru 35 25 14.9

28 Ti-3Al-2.5V-0.1 R 90 70 13.1

29 Ti-6Al-4V-0.1Ru 120 110 16.3

22

MILITARY SPECIFICATIONS -- TITANIUM AND TITANIUM ALLOY (Sheet - Strip - Plate)

MIL-T-9046J (Jan. 1983)

Commercially Pure Titanium (CP) Code Designation CP - 1 ( 70 KSI-YS) CP - 2 ( 55 KSI-YS) CP - 3 ( 40 KSI-YS) CP - 4 ( 25 KSI-YS)

Alpha Titanium Alloys (A) Code Designation Composition A - 1 5Al - 2.5 Sn A - 2 5Al - 2.5 Sn (ELI) A - 3 6Al - 2Cb - 1Ta - 0.8Mo A - 4 8Al - 1Mo - 1V

Alpha-Beta Titanium Alloy (AB) Code Designation Composition AB - 1 6Al - 4V AB - 2 6Al - 4V (ELI) AB - 3 6Al - 6V - 2Sn AB - 4 6Al - 2Sn - 4Zr - 2Mo AB - 5 3Al - 2.5V AB - 6 8Mn

Beta Titanium Alloys (B) Code Designation Composition B - 1 13V - 11Cr - 3Al B - 2 11.5Mo - 6Zr - 4.5Sn B - 3 3Al - 8V - 6Cr - 4Mo - 4Zr

23

MILITARY SPECIFICATIONS -- TITANIUM ALLOY (Bars and Reforge Stock)

MIL-T-9047G Rev Dec 1978

Commercially Pure TiCP 70

Alpha Titanium Alloys5Al - 2.5Sn5Al - 2.5Sn (ELI)8Al - 1Mo - 1V6Al - 2Cb - 1Ta - 0.8Mo

Alpha-Beta Ti Alloys3Al - 2.5V6Al - 4V6Al - 4V (ELI)6Al - 6V - 2Sn7Al -4Mo6Al - 2Sn - 4Zr - 2Mo6Al - 2Sn - 4Zr - 6Mo

Beta Titanium Alloys13V - 11Cr - 3Al11.5Mo - 6Zr - 4.5Sn8Mo - 8V - 2Fe - 3Al3Al - 8V - 6Cr - 4Mo - 4Zr

Other SpecificationsMIL-H-81200 Heat treatment of titanium and titanium alloys

AMS 2631 Ultrasonic InspectionsMIL-STD 2154 Ultrasonic Inspections

24

INTERNATIONAL TITANIUM & TITANIUM ALLOY SPECIFICATIONSFORMS AVAILABLE

Grade/Reference Forms ASTM DIN British Aerospace Aerospace RemarksNumber Available Standards American American

TA AMS MIL-T9046 - 9047

GR-1 BPSTWF 1 3.7025 1 CP4GR-2 BPSTWFC 2 3.7035 2,3,4,5 4902,4941 CP3 Commercially pure

4942,4951 titanium, usedprimarily forcorrosion resistance. Strength increaseswith Grade Number.

GR-3 BPSWFC 3 3.7055 4900 CP2

GR-4 BPSWFC 4 3.7065 6,7,8,9 4901 CP1 CP-70

GR-7 BPSTWFC 7.11 Industrial alloys withsuperior corrosionresistance.GR-12 BPSTWF 12

GR-5 28,56,59 4928 AB2 medium strength forBPSWFC 5 3.7165 10,11,12, 4911, AB1/ As Comp Popular alloys of

airframe and engines

Ti-4AI-4 Mo- BPF 45-512.5Sn (550) and 57

Ti-10Fe-2V-3AI BF 4983 Beta alloys having(10-2-3) excellent fabricability

and high strengthdeveloped by heattreatment.

Ti-15V-3AI-3 Cr- PSWT 49163Sn (15-3)

Ti-6AI-2Sn BPSF 4975 AB4 As Comp Alloys developed for4Zr-2Mo (6-2-4-2) 4976 aero engine use

Ti-6AI-2Sn- BPSF 4981 As Comp4Zr-6Mo(6-2-4-6)

B=Billet/Bar P=Plate S=Sheet T=Tube W=Wire F=Forgings C=Castings

25

FIRE PREVENTION

Storage of coarse titanium turnings and chips is relatively safe. Storage or accumulation of titanium finesconstitutes a fire hazard. Clean machines and good workshop practice are usually sufficient to avoid any dangerof fire when machining titanium.

Titanium chips, turnings or fines should not be allowed to accumulate in machines.

If a fire does start its effect can be minimized by isolating the burning material from the bulk. The fire can thenbe extinguished with a dry powder extinguisher. A sodium chloride base powder can be an effective agent. UseNational Fire Protection Association Class D extinguisher (salt). Use salt or sand to reduce oxygen. Fire may beisolated and allowed to burn itself out.

Fire or explosions may be initiated by exposing any concentrated dust suspension in an enclosed area to spark orflame. Generally, titanium dust or powder must be minus 100-mesh in order to create an explosive dust-airmixture.Cutting and grinding fires can present an explosion hazard when airborne in levels above 35 mg/m (U.S. Bureau of Mines, Report of Investigation3

No. 4835).

TITANIUM CORROSION RATE DATA (Commercially Pure Grades) C = Concentration % T = Temperature F ( C) R = Corrosion rate, mpy (mm/y)

26

Media C T R Media C T R

Acetaldehyde 75 300(149) 0.02(0.001) Cupric chloride 40 boiling 0.2(0.005)

Acetic acidAcetic anhydrideAcidic gasses Containing CO2 H OCl ,SO SO2 , 2 2, 3 H S,0 ,NH2 4 3Adipic AcidAluminum chloride, aeratedAluminum chloride, aeratedAluminum fluoride Aluminum nitrateAluminum sulfateAmmonium acid phosphateAmmonia anhydrousAmmonia steam, waterAmmonium acetateAmmonium bicarbonateAmmonium bisulfite, pH 2.05

Ammonium chlorideAmmonium hydroxideAmmonium nitrateAmmonium nitrate + 1% nitric acidAmmonium oxalateAmmonium sulfateAmmonium sulfate + 12% H SO2 4Aqua regiaAqua regiaBarium chlorideBarium hydroxideBarium hydroxide

Barium nitrateBarium fluorideBenzoic acidBoric acidBoric acidBromineBromine moistN-butyric acidCalcium bisulfite

Calciuim carbonateCalcium chlorideCalcium chlorideCalcium chlorideCalcium chlorideCalcium chlorideCalcium hydroxideCalcium hypochloriteCalcium hypochloriteCalcium hypochlorite

Carbon dioxideCarbon tetrachlorideCarbon tetrachlorideChlorine gas, wetChlorine gas, wetChlorine header sludge and wet chlorineChlorine gas dryChlorine dioxide

Chloride dioxide in steamChlorine trifluoride

Chloracetic acidChloracetic acidChlorosulfonic acid

ChloroformChromic acidChromic acidChromic acidChromium plating bathcontaining fluorideChromic acid + 5% Nitric acidCitric acidCitric acid

Citric acid

Citric acidCupric chloride

100 300(149) nil Cupric choride 55 246(119) 0.1(0.003)5 to 99.7 255(124) nil (boiling)99.5 boiling 0.5(0.013) Cupric cyanide saturated room nil

67 450(232) nil Dichlorobenzene+ 4-5% HCl -- 355(179) 4(0.102)10 212(100) 0.09(0.002)* Diethylene triamine 100 room nil25 212(100) 124(3.15)* Ethyl alcohol 95 boiling 0.5(0.013)saturated room nil Ethylene dichloride 100 boiling 0.2-5.0saturated room nil (0.005-0.127)saturated room nil Ethylene diamine 100 room nil10 room nil Ferric chloride 10-20 room nil100 104(40) <5.0(<0.127) Ferric chloride 10-30 212(100) <0.5(<0.127)-- 431(222) 440(11.2) Ferric chloride 10-40 boiling nil10 room nil Ferric chloride 50 236(113) nil50 212(100) nil (boiling)spent 159(71) 0.6(0.015) Ferric chloride 50 302(150) 0.1(0.003)pulping Ferric sulfate 9H O 10 room nilliquor Flubonic acid 5-20 elevated rapidsaturated 212(100) <0.5(<0.013) Fluorsilicic 10 room 1870(47.5)28 room 0.1(0.003) Food products -- ambient no attack28 boiling nil Fomaldehyde 37 boiling nil28 boiling nil Formamide vapor -- 572(300) nil

saturated room nil Formic acid aerated 90 212(100) 0.05(0.001)**10 212(100) nil Formic acid 25 212(100) 44(2.44)**saturated room 0.4(0.010) non-aerated 90 212(100) 118(3.00)**

3:1 room nil Gluconic acid 50 room nil3:1 175(79) 34.8(0.884) Glycerin -- room nil25 212(100) nil Hydorgen chloride, gas air mixture ambient nilsaturated room nil Hydrochloric acid 1 boiling >100(>2.54)27 boiling some Hydrochloric acid 3 boiling 550(14.0)

10 room nil chlorine saturated 5 374(190) <1(<0.025)saturated room nil 10 374(190) >1120(>28.5)saturated room nil 200ppm Cl 36 room 17.0(0.432)saturated room nil + 1% HNO 5 200(93) 3.6(0.091)10 boiling nil + 5% HNO 5 200(93) 1.2(0.030)liquid 86(30) rapid + 5% HNO 1 boiling 2.9(0.074)vapor 86(30) <0.1(<0.003) + 5% HNO + 1.7 g/l 1 boiling nilundiluted room nil TiClcooking 79(26) 0.02(0.01) + 0.5% CrO 5 200(93) 1.2(0.031)liquor + 1% CrO 5 100(38) 0.72(0.018)saturated boiling nil + 1% CrO 5 200(93) 1.2(0.031)5 212(100) 0.02(0.005)* + 0.05% CuSO 5 200(93) 3.6(0.091)10 212(100) 0.29(0.007)* + 0.5% CuSO 5 200(93) 2.4(0.061)20 212(100) 0.61(0.015)* + 0.05% CuSO 5 boiling 2.5(0.064)55 220(104) 0.02(0.001)* + 0.5% CuSO 5 boiling 3.3(0.084)60 300(149) <0.1(<0.003)* Hydrofluonic acid 1.48 room rapidsaturated boiling nil Hydrogen peroxide 3 room <5(<0.127)6 212(100) 0.05(0.001) Hydrogen peroxide 6 room <5(<0.127)18 70(21) nil Hydrogen peroxide 30 room <12(<0.305)saturated -- nil Hrdrogen suflide, steam 7.65 200-230 nilslurry and 0.077% mercaptans (93-110)100 -- excellent Hypochlorous acid 17 100(38) 0.001(0.000)liquid boiling nil + Cl O and Cl gasesvapor boiling nil Iodine in water + -- room nil>0.7H O room nil Potassium Iodide2>1.5H O 392(200) nil Lactic acid 10-85 212(100) <5.0(<0.127)2-- 207(97) 0.03(0.001) Lactic acid 10 boiling <5.0(<0.127)

<0.5H O room may react Linseed oil, boiled -- room nil25 in steam 180(82) <0.1(<0.003) Lithium chloride 50 300(149) nilgas + H O Magnesium chloride 5-40 boiling nil2and air Magnesium hydroxide saturated room nil5 210(99) nil Magnesium sulfate saturated room nil100 86(30) vigorous Manganous chloride 5-20 212(100) nil

30 180(82) <5.0(<0.127) Mercuric chloride 10 212(100) 0.04(0.001)100 boling <5.0(<0.127) Mercuric chloride saturated 212(100) <5(<0.127)100 room 7.5-12.3 Mercuric cyanide saturated room nil

vapor & liquid boiling 0.01(0.000) Nickel chloride 5 212(100) 0.17(0.004)10 boiling 0.1(0.003) Nickel chloride 20 212(100) 0.11(0.003)15 180(82) 0.6(0.015) Nitric acid, aerated 10 room 0.19(0.005)50 180(82) 1.1(0.028) Nitric acid, aerated 50 room 0.08(0.002)240g/l Nitric acid, aerated 70 room 0.18(0.005)plating salt 171(77) 58.3(1.48) Nitric acid, aerated 10 104(40) 0.10(0.003)5 70(21) <0.1(<0.003) Nitric acid, aerated 50 140(60) 1.46(0.037)50 140(60) 0.01(0.000) Nitric acid, aerated 70 158(70) 1.56(0.040)50 212(100) <5.0(<0.127) Nitric acid, aerated 40 392(200) 24(0.610)aerated Nitric acid, aerated 70 518(270) 48(1.22)50 boiling 5.50(0.127-1.27) Nitric acid, aerated 20 554(290) 12(0.305)

62 300(149) corroded Nitric acid 17 boiling 3-4(0.076-0.102)20 boiling nil Nitric acid 35 boiling 5-20(0.127-0.508)

100-500 <1.0(<0.025) Cuprous chloride 50 194(90) <0.1(<0.003)(38-260) Cyclohexane (plus traces of -- 302(150) 0.1(0.003)

small pits Hydrochloric acid 5 boiling 400(10.2)

reaction Maleic acid 18-20 95(35) 0.6(0.002)

(0.191-0.312) Methyl alcohol 91 95(35) nil

formic acid)Dichloroacetic acid 100 boiling 0.29(0.007)

2

Formic acid aerated 25 212(100) 0.04(0.001)**

Furfural 100 room nil

2

3

3

3

3

4

3

3

3

4

4

4

4

2 2

Lead acetate saturated room nil

Nitric acid, non aerated 70 176(80) 1-3(0.025-0.076)

*May corrode in crevices **Grade 7 and 12 immune