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Inconel alloy 718 (Sept 07) Web - Special Metals …

Inconel alloy alloy 718 (UNS N07718 ) is ahigh-strength, corrosion-resistant nickel chromiummaterial used at -423 to 1300 F. Typical compositionlimits are shown in Table age-hardenable alloy can be readily fabricated,even into complex parts. Its welding characteristics,especially its resistance to postweld cracking, ease and economy with which Inconel alloy 718can be fabricated, combined with good tensile, fatigue,creep, and rupture strength, have resulted in its use in awide range of applications. Examples of these arecomponents for liquid fueled rockets, rings, casings andvarious formed sheet metal parts for aircraft and land-basedgas turbine engines, and cryogenic tankage. It is also usedfor fasteners and instrumentation 11- Limiting Chemical Compositiona, %Nickel (plus Cobalt) ..Balance*Niobium (plus Tantalum).. physical constants of Inconel alloy 718 are shownin Table 2.

INCONEL® alloy 718 2 HEAT TREATING AND MECHANICAL PROPERTIES For most applications, INCONEL alloy 718 is specified as: solution annealed and precipitation hardened (precipitation

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Transcription of Inconel alloy 718 (Sept 07) Web - Special Metals …

1 Inconel alloy alloy 718 (UNS N07718 ) is ahigh-strength, corrosion-resistant nickel chromiummaterial used at -423 to 1300 F. Typical compositionlimits are shown in Table age-hardenable alloy can be readily fabricated,even into complex parts. Its welding characteristics,especially its resistance to postweld cracking, ease and economy with which Inconel alloy 718can be fabricated, combined with good tensile, fatigue,creep, and rupture strength, have resulted in its use in awide range of applications. Examples of these arecomponents for liquid fueled rockets, rings, casings andvarious formed sheet metal parts for aircraft and land-basedgas turbine engines, and cryogenic tankage. It is also usedfor fasteners and instrumentation 11- Limiting Chemical Compositiona, %Nickel (plus Cobalt) ..Balance*Niobium (plus Tantalum).. physical constants of Inconel alloy 718 are shownin Table 2.

2 Modulus data appear in Tables 3 and 4, andthermal properties in Table 5. The values in these tables willvary slightly, depending on the composition and conditionof the specimen tested. They are typical but are not suitablefor specification 22- Physical ConstantsDensity, and Aged .. Range, C ..1260-1336 Specific Heat at 70 F, Btu/lb F (at 21 C, J/kg C) .. (435)Curie Temperature, F ( C)Annealed <-320 (<-196)Annealed and Aged Material ..-170 (-112)Permeability at 200 oersted and 70 FAnnealed Material .. and Aged Material .. 33- Modulus of Elasticity at Low TemperaturesaTTeemmppeerraattuurree,, FFPP ooiissssoonn ss RRaattiiooTToorrssiioonnaallMMoodduulluu ssYYoouunngg ssMMoodduulluussMMoodduulluuss ooff EEllaassttiicciittyy,, kkssii xx 110033aCold-rolled sheet heat-treated in accordance with AMS to AMS specificationsPublication Number SMC-045 Copyright Special Metals Corporation, 2007 (Sept 07) Inconel is a trademark of the Special MetalsCorporation group of data contained in this publication is for informational purposes only and may berevised at any time without prior notice.

3 The data is believed to be accurate andreliable, but Special Metals makes no representation or warranty of any kind (expressor implied) and assumes no liability with respect to the accuracy or completeness ofthe information contained herein. Although the data is believed to be representativeof the product, the actual characteristics or performance of the product may varyfrom what is shown in this publication. Nothing contained in this publication shouldbe construed as guaranteeing the product for a particular use or application.*Reference to the balance of a composition does not guarantee thisis exclusively of the element mentioned but that it predominates andothers are present only in aallllooyy 7711882 HHEEAATT TTRREEAATTIINNGG AANNDD MMEECCHHAANNIICCAALL PPRROOPPEERRTTIIEESSFor most applications, Inconel alloy 718 is specified as: solution annealed and precipitation hardened (precipitationhardening, age hardening, and precipitation heat treatment are synonymous terms).

4 alloy 718 is hardened by the precipitationof secondary phases ( gamma prime and gamma double-prime) into the metal matrix. The precipitation of these nickel-(aluminum, titanium, niobium) phases is induced by heat treating in the temperature range of 1100 to 1500 F. For thismetallurgical reaction to properly take place, the aging constituents (aluminum, titanium, niobium) must be in solution(dissolved in the matrix); if they are precipitated as some other phase or are combined in some other form, they will notprecipitate correctly and the full strength of the alloy with not be realized. To perform this function, the material must first besolution heat treated (solution annealed is a synonymous term).Two heat treatments are generally utilized for Inconel alloy 718: Solution anneal at 1700-1850 F followed by rapid cooling, usually in water, plus precipitation hardening at 1325 F for 8hours, furnace cool to 1150 F, hold at 1150 F for a total aging time of 18 hours, followed by air cooling.

5 Solution anneal at 1900-1950 F followed by rapid cooling, usually in water, plus precipitation hardening at 1400 F for 10hours, furnace cool to 1200 F, hold at 1200 F for a total aging time of 20 hours, followed by air the material is to be machined, formed, or welded, it typically is purchased in the mill annealed or stress relievedcondition. The material is then fabricated in its most malleable condition. After fabrication, it can be heat treated as requiredper the applicable ++ AAggeeddTTeemmppeerraattuurree,, 11880000 FF//11 ++ 11880000 FF//11 hhrrMMeeaann LLiinneeaarrEExxppaannssiioonnbb,,cc,,ii nn//iinn// FF xx 1100--66 TThheerrmmaall CCoonndduuccttiivviittyy,,aaBBTTUU iinn//fftt22 hh FFEE lleeccttrriiccaall RReessiissttiivviittyy,,aaoohhmm cciirrcc mmiill//ffttTTaabbllee 55- Thermal PropertiesaAnnealing was 1800 F/1 hr; aging was 1325 F/8 hr, 20 /hr to 1150 F, held at 1150 F for total aging time of 18 hr. Conductivity calculated from resistivity 70 F to temperature 1750 F/1 hr and aged 1325 F/8 hr, to 1150 F/8 hr, tested were in both the annealed (1750 F/1 hr, ) and annealed and aged (1750 F/1 hr + 1325 F/8 hr, to 1150 F, held at 1150 F for 10 hr, ) 44- Modulus of ElasticityaTTeemmppeerraattuurree,, FFPP ooiissssoonn ssRRaattiioobbTToorrssiioonnaallMMoodduu lluussYYoouunngg ssMMoodduulluussMMoodduulluuss ooff EEllaassttiicciittyy,, kkssii xx ,, FFPP ooiissssoonn ssRRaattiioobbTToorrssiioonnaallMMoodduu lluussYYoouunngg ssMMoodduulluussMMoodduulluuss ooff EEllaassttiicciittyy,, kkssii xx 110033aHot-rolled flat heat-treated 1800 F/1 hr, + 1325 F/8 hr, 20 F/hr to1150 F, held for total aging time of 18 hr.

6 Dynamic testing involved frequencies offrom 813 to 571 cps in bending and from 3110 to 2097 cps in from (E-2G)/2G, where E is Young s Modulus and G is aallllooyy 771188311770000 --11885500 FF AAnnnneeaall aanndd AAggeeThe 1700 -1850 F anneal with its corresponding agingtreatment as shown earlier is the optimum heat treatment foralloy 718 where a combination of rupture life, notch rupturelife and rupture ductility is of greatest concern. The highestroom-temperature tensile and yield strengths are alsoassociated with this treatment. In addition, because of thefine grain developed, it produces the highest in this condition will meet the followingminimum requirements:AMS 5596 Sheet, Strip, & PlatePPrrooppeerrttyy11220000 FFRR oooomm TTeemmppeerraattuurreeTensile Strength, ksi180140a145bYield Strength150115a( Offset), ksi120bElongation in 2 ln.,%125 HardnessRc 36-or equivalentStress RuptureStress, ksi-95a-100bLife, hr-23 Elongation, %-4 AMS 5589 Seamless TubinggPPrrooppeerrttyy11330000 FFRR oooomm TTeemmppeerraattuurreeTensile Strength, ksi185-Yield Strength150-( Offset), ksiElongation in 2 ln.

7 ,%12-HardnessRc 36-or equivalentStress RuptureStress, , hr-23 Elongation, %-5aUp to thickness, transverse for for up to or thickness, apply only to of and over with wall thickness and --11995500 AAnnnneeaall aanndd AAggeeThe 1900 -1950 anneal with its corresponding agingtreatment as shown above is the treatment preferred intensile-limited applications because it produces the besttransverse ductility in heavy sections, impact strength, andlow-temperature notch tensile strength. However, thistreatment has a tendency to produce notch brittleness instress precipitation hardening as shown, material willmeet the following requirements:Tensile Strength, ksi180180170 Yield Strength( Offset), ksi150150145 Elongation, %10b151512cReduction of Area, %12b--15cHardness341 BHNRc 38or equivalentor equivalentPPrrooppeerrttyyaaAAMMSS 55559900 SSeeaammlleessssTTuubbiinnggddAAMMSS 55559977 SShheeeett,, SSttrriipp,, &&PPllaatteeAAMMSS 55666644 BBaarrss,, FFoorrggiinnggss,, &&RRiinnggssaTransverse and flash-welded apply only to of and over with wall thickness and Strength, ksi185c145c180d140d180e140eYield Strength150125( Offset), ksiElongation in 2 ln.

8 ,%12c12c10d10d6e6eReduction of Area, %15c15c12d12d8e8eHardness331 BHN-or equivalentStress RuptureStress, ksi-100 Life, hr-23 Elongation, %-4fAMS 5662 and 5663 Bars, Forgings, & RingsPPrrooppeerrttyy11220000 FFRR oooomm TTeemmppeerraattuurreeIINNCCOONNEELL aallllooyy 7711884 TTaabbllee 66- Mechanical Properties Aged Material for Oil Tool ApplicationsRoom Temperature Tensile and Hardness, and Room Temperature and -75 F ImpactDDiiaammeetteerr,, ((mmmm))CCoonnddiittiioonnmmaaxxiimmuumm HHaarrddnneessss,, RRoocckkwweellll CCII mmppaaccttSSttrreennggtthh,,fftt llbb ((KKgg mm)) ooffAArreeaa,, %%mmiinniimmuummEElloonnggaattiioonn iinn22 (( )) oorr 44DD%%mmiinniimmuummmmaaxxiimmuummYYiiee lldd SSttrreennggtthh(( OOffffsseett)),, kkssii ((KKgg//ccmm22))TTeennssiilleeSSttrreenn ggtthh,, kkssii((KKgg//ccmm22)) worked, ( ) to 150 (10,545)120 (8436)140 (9842)202540 ( )3040solution3 ( ),annealed &inclusiveagedHot worked, ( ) to 150 (10,545)120 (8436)140 (9842)202540 ( )3040solution8 ( ),annealed &inclusiveagedHot worked,8 ( )150 (10,545)120 (8436)140 (9842)202540 ( )3040solution to 10 (254),annealed &inclusiveagedRROOOOMMTTEEMMPPEERRAATTUU RREETTEENNSSIILLEEPPRROOPPEERRTTIIEESSTh e following data are representative of the effects of the above annealing and aging treatments on room-temperatureproperties of a variety of products.

9 More properties are shown under the section, High- and Low-Temperature TensileProperties, Fatigue Strength, and Weld PPrroodduuccttssTable 7 shows properties of hot-rolled round annealed at 1750 or 1950 F. The effects of annealing at 1750 or 1950 F andthe associated aging treatments on bar of a range of diameters are given in Table 8. Properties produced by the two differentannealing and aging schedules in hot-rolled round are compared in Table effect of direct aging (1325 F/time at temperature, 8 hours, to 1150 F, hold at 1150 F for total aging time of 18hours) on various sizes of samples is given in Table of a pancake forging with samples taken from various locations, annealed at 1700 F and aged, are shown in Table11. Properties of forged products given the 1950 F anneal and aged are shown in Tables 12 and 13. The effects of the twoannealing and aging treatments on a forged pancake are compared in Table Metals produces Inconel alloy 718 for use in oil field applications.

10 This material is produced under the NACE specification MR0175 which requires the solution annealed and aged material to meet a maximum hardness value of 40 Rockwell C . Such material is typically solution heat treated at 1850-1900 F and aged at 1450 F for six to eight hours andair cooled. Table 6 shows the mechanical properties this material will meet. Numerous proprietary heat treatments are usedfor Inconel alloy 718 depending on the properties required. Such heat treatment sequences are usually developed bycompanies or agencies independent of the material supplier; consequently, discussion of procedures, tolerances, and resultingproperties should be with that company or agency. All the data shown in the following sections are typical but not to be used for specification HHeeaatt TTrreeaattmmeennttssIINNCCOONNEELL aallllooyy 7711885 TTaabbllee 77- Room-Temperature Tensile Properties of Annealed Hot-Rolled RoundDDiiaammeetteerraa,, ooffAArreeaa,, %%EElloonnggaattiioonn,, %%YYiieelldd SSttrreennggtthh(( OOffffsseett)),, kkssiiTTeennssiillee SSttrreennggtthh,,kkssiiTTeesstt OOrriieennttaattiioonnccAAnnnneeaalliinn ggTTeemmppeerraattuurreebb,, separate heats for 1 hr, is longitudinal test orientation; T, 99- Tensile Properties of Hot-Rolled Round (4-in.)


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