Inconel alloy 718 (Sept 07) Web.qxd

INCONEL

alloy 718

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-308 31.3 12.5 0.25

-86 30.6 11.8 0.30

70 29.0 11.6 0.29

100 29.8 11.5 0.30

200 29.4 11.3 0.31

300 28.8 11.1 0.30

400 28.5 10.9 0.31

500 28.0 10.6 0.32

INCONEL

alloy 718 (UNS N07718/W.Nr. 2.4668) is a

high-strength, corrosion-resistant nickel chromium

material used at -423° to 1300°F. Typical composition

limits are shown in Table 1.

The age-hardenable alloy can be readily fabricated,

even into complex parts. Its welding characteristics,

especially its resistance to postweld cracking, are

outstanding.

The ease and economy with which INCONEL alloy 718

can be fabricated, combined with good tensile, fatigue,

creep, and rupture strength, have resulted in its use in a

wide range of applications. Examples of these are

components for liquid fueled rockets, rings, casings and

various formed sheet metal parts for aircraft and land-based

gas turbine engines, and cryogenic tankage. It is also used

for fasteners and instrumentation parts.

TTaabbllee 11

- Limiting Chemical Composition

, %

Nickel (plus Cobalt) .......................................................50.00-55.00

Chromium......................................................................17.00-21.00

Iron .....................................................................................Balance*

Niobium (plus Tantalum)....................................................4.75-5.50

Molybdenum .....................................................................2.80-3.30

Titanium.............................................................................0.65-1.15

Aluminum ..........................................................................0.20-0.80

Cobalt ...............................................................................1.00 max.

Carbon ..............................................................................0.08 max.

Manganese .......................................................................0.35 max.

Silicon ...............................................................................0.35 max.

Phosphorus.....................................................................0.015 max.

Sulfur...............................................................................0.015 max.

Boron ..............................................................................0.006 max.

Copper..............................................................................0.30 max.

PPHHYYSSIICCAALL CCOONNSSTTAANNTTSS AANNDD

TTHHEERRMMAALL PPRROOPPEERRTTIIEESS

Some physical constants of INCONEL alloy 718 are shown

in Table 2. Modulus data appear in Tables 3 and 4, and

thermal properties in Table 5. The values in these tables will

vary slightly, depending on the composition and condition

of the specimen tested. They are typical but are not suitable

for specification purposes.

TTaabbllee 22

- Physical Constants

Density, lb/in

Annealed..............................................................................0.296

Annealed and Aged .............................................................0.297

Melting Range, °F............................................................2300-2437

°C ...........................................................1260-1336

Specific Heat at 70°F, Btu/lb °F (at 21°C, J/kg °C) ........0.104 (435)

Curie Temperature, °F (°C)

Annealed Material...................................................<-320 (<-196)

Annealed and Aged Material ......................................-170 (-112)

Permeability at 200 oersted and 70°F

Annealed Material..............................................................1.0013

Annealed and Aged Material .............................................1.0011

TTaabbllee 33

- Modulus of Elasticity at Low Temperatures

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Cold-rolled sheet heat-treated in accordance with AMS 5596B.

Conforms to AMS specifications

Publication Number SMC-045

INCONEL is a trademark of the Special Metals

Corporation group of companies.

The data contained in this publication is for informational purposes only and may be

revised at any time without prior notice. The data is believed to be accurate and

reliable, but Special Metals makes no representation or warranty of any kind (express

or implied) and assumes no liability with respect to the accuracy or completeness of

the information contained herein. Although the data is believed to be representative

of the product, the actual characteristics or performance of the product may vary

from what is shown in this publication. Nothing contained in this publication should

be construed as guaranteeing the product for a particular use or application.

Reference to the ‘balance’ of a composition does not guarantee this

is exclusively of the element mentioned but that it predominates and

others are present only in minimal quantities.

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HHEEAATT TTRREEAATTIINNGG AANNDD MMEECCHHAANNIICCAALL PPRROOPPEERRTTIIEESS

For most applications, INCONEL alloy 718 is specified as: solution annealed and precipitation hardened (precipitation

hardening, age hardening, and precipitation heat treatment are synonymous terms). Alloy 718 is hardened by the precipitation

of secondary phases (e.g. 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 this

metallurgical 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 not

precipitate correctly and the full strength of the alloy with not be realized. To perform this function, the material must first be

solution 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 8

hours, furnace cool to 1150°F, hold at 1150°F for a total aging time of 18 hours, followed by air cooling.

•Solution anneal at 1900-1950°F followed by rapid cooling, usually in water, plus precipitation hardening at 1400°F for 10

hours, furnace cool to 1200°F, hold at 1200°F for a total aging time of 20 hours, followed by air cooling.

If the material is to be machined, formed, or welded, it typically is purchased in the mill annealed or stress relieved

condition. The material is then fabricated in its most malleable condition. After fabrication, it can be heat treated as required

per the applicable specification.

-320 - - - - 5.9

70 77 79 753 725 -

200 86 87 762 733 7.31

400 98 100 772 755 7.53

600 111 112 775 768 7.74

800 123 124 784 775 7.97

1000 135 136 798 788 8.09

1200 147 148 805 794 8.39

1400 160 161 802 797 8.91

1600 173 173 799 796 -

1800 185 186 801 800 -

2000 196 199 811 796 -

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TTaabbllee 55

- Thermal Properties

Annealing was 1800°F/1 hr; aging was 1325°F/8 hr, F.C. 20°/hr to 1150°F, held at 1150°F for total aging time of 18 hr. Conductivity calculated from resistivity values.

From 70°F to temperature shown.

Annealed 1750°F/1 hr and aged 1325°F/8 hr, F.C. to 1150°F/8 hr, A.C.

Samples tested were in both the annealed (1750°F/1 hr, A.C.) and annealed and aged (1750°F/1 hr + 1325°F/8 hr, F.C. to 1150°F, held at 1150°F for 10 hr, A.C.) conditions.

70 29.0 11.2 0.294

100 28.8 11.2 0.291

200 28.4 11.0 0.288

300 28.0 10.9 0.280

400 27.6 10.8 0.280

500 27.1 10.6 0.275

600 26.7 10.5 0.272

700 26.2 10.3 0.273

800 25.8 10.1 0.271

900 25.3 9.9 0.272

1000 24.8 9.7 0.271

1100 24.2 9.5 0.276

1200 23.7 9.2 0.283

TTaabbllee 44

- Modulus of Elasticity

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1300 23.0 8.9 0.292

1400 22.3 8.5 0.306

1500 21.3 8.1 0.321

1600 20.2 7.6 0.331

1700 18.8 7.1 0.334

1800 17.4 6.5 0.341

1900 15.9 5.8 0.366

2000 14.3 5.1 0.402

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Hot-rolled flat heat-treated 1800°F/1 hr, A.C. + 1325°F/8 hr, F.C. 20°F/hr to

1150°F, held for total aging time of 18 hr. Dynamic testing involved frequencies of

from 813 to 571 cps in bending and from 3110 to 2097 cps in torsion.

Computed from (E-2G)/2G, where E is Young’s Modulus and G is torsional

modulus.

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The 1700°-1850°F anneal with its corresponding aging

treatment as shown earlier is the optimum heat treatment for

alloy 718 where a combination of rupture life, notch rupture

life and rupture ductility is of greatest concern. The highest

room-temperature tensile and yield strengths are also

associated with this treatment. In addition, because of the

fine grain developed, it produces the highest fatigue

strength.

Material in this condition will meet the following

minimum requirements:

AMS 5596

Sheet, Strip, & Plate

PPrrooppeerrttyy 11220000°°FFRRoooomm TTeemmppeerraattuurree

Tensile Strength, ksi 180 140

145

Yield Strength 150 115

(0.2% Offset), ksi 120

Elongation in 2 ln.,% 12 5

Hardness

Rc 36

or equivalent

Stress Rupture

Stress, ksi - 95

- 100

Life, hr - 23

Elongation, % - 4

AMS 5589

Seamless Tubing

PPrrooppeerrttyy 11330000°°FFRRoooomm TTeemmppeerraattuurree

Tensile Strength, ksi 185 -

Yield Strength

150 -

(0.2% Offset), ksi

Elongation in 2 ln.,% 12 -

Hardness

Rc 36

or equivalent

Stress Rupture

Stress, ksi - 72.5

Life, hr - 23

Elongation, % - 5

Up to 0.025-in. thickness, inclusive.

Over 0.025-in. thickness.

Longitudinal.

Long transverse for forgings.

Transverse for bars.

Applies up to 5-in.-diam. or thickness, inclusive.

Properties apply only to O.D. of 0.125-in. and over with wall thickness of

0.015-in. and over.

11990000°°--11995500°° AAnnnneeaall aanndd AAggee

The 1900°-1950° anneal with its corresponding aging

treatment as shown above is the treatment preferred in

tensile-limited applications because it produces the best

transverse ductility in heavy sections, impact strength, and

low-temperature notch tensile strength. However, this

treatment has a tendency to produce notch brittleness in

stress rupture.

After precipitation hardening as shown, material will

meet the following requirements:

Tensile Strength, ksi 180 180 170

Yield Strength

(0.2% Offset), ksi

150 150 145

Elongation, % 10

15 15

Reduction of Area, %

Hardness

341 BHN Rc 38

or equivalent or equivalent

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Transverse direction.

Bars.

Forgings and flash-welded rings.

Properties apply only to O.D. of 0.125-in. and over with wall thickness of

0.015-in. and over.

Tensile Strength, ksi 185

145

180

140

180

140

Yield Strength

150 125

(0.2% Offset), ksi

Elongation in 2 ln.,% 12

Reduction of Area, % 15

Hardness

331 BHN

or equivalent

Stress Rupture

Stress, ksi - 100

Life, hr - 23

Elongation, % - 4

AMS 5662 and 5663

Bars, Forgings, & Rings

PPrrooppeerrttyy 11220000°°FFRRoooomm TTeemmppeerraattuurree

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TTaabbllee 66

- Mechanical Properties Aged Material for Oil Tool Applications

Room Temperature Tensile and Hardness, and Room Temperature and -75°F Impact

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Cold worked, 0.5 (12.7) to 150 (10,545) 120 (8436) 140 (9842) 20 25 40 (5.55) 30 40

solution 3 (76.2),

annealed & inclusive

aged

Hot worked, 0.5 (12.7) to 150 (10,545) 120 (8436) 140 (9842) 20 25 40 (5.55) 30 40

solution 8 (203.2),

annealed & inclusive

aged

Hot worked, 8 (203.2) 150 (10,545) 120 (8436) 140 (9842) 20 25 40 (5.55) 30 40

solution to 10 (254),

annealed & inclusive

aged

RROOOOMM TTEEMMPPEERRAATTUURREE TTEENNSSIILLEE PPRROOPPEERRTTIIEESS

The following data are representative of the effects of the above annealing and aging treatments on room-temperature

properties of a variety of products. More properties are shown under the section, High- and Low-Temperature Tensile

Properties, Fatigue Strength, and Weld Properties.

HHoott--FFiinniisshheedd PPrroodduuccttss

Table 7 shows properties of hot-rolled round annealed at 1750° or 1950°F. The effects of annealing at 1750° or 1950°F and

the associated aging treatments on bar of a range of diameters are given in Table 8. Properties produced by the two different

annealing and aging schedules in hot-rolled round are compared in Table 9.

The effect of direct aging (1325°F/time at temperature, 8 hours, F.C. to 1150°F, hold at 1150°F for total aging time of 18

hours) on various sizes of samples is given in Table 10.

Properties of a pancake forging with samples taken from various locations, annealed at 1700°F and aged, are shown in Table

11. Properties of forged products given the 1950°F anneal and aged are shown in Tables 12 and 13. The effects of the two

annealing and aging treatments on a forged pancake are compared in Table 14.

Special Metals produces INCONEL alloy 718 for use in oil field applications. 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 and

air cooled. Table 6 shows the mechanical properties this material will meet. Numerous proprietary heat treatments are used

for INCONEL alloy 718 depending on the properties required. Such heat treatment sequences are usually developed by

companies or agencies independent of the material supplier; consequently, discussion of procedures, tolerances, and resulting

properties should be with that company or agency.

All the data shown in the following sections are typical but not to be used for specification purposes.

OOtthheerr HHeeaatt TTrreeaattmmeennttss

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TTaabbllee 77

- Room-Temperature Tensile Properties of Annealed Hot-Rolled Round

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2.5 1750 L 135.5 77.5 45 49 -

T 129.5 73.5 32 29 -

1950 L 114.0 50.4 62 65 -

T 112.0 49.8 53 49 -

4 1750 L 117.5 55.0 53 52 90 Rb

T 119.0 56.5 50 46 88 Rb

1950 L 112.5 48.0 60 63 87 Rb

T 114.0 50.0 61 55 84 Rb

4 1750 L 125.5 71.5 45 49 97 Rb

T 123.5 67.0 46 43 93 Rb

1950 L 115.0 47.0 59 65 85 Rb

T 99.5 47.5 32 31 84 Rb

4 1750 L 126.0 71.5 45 47 96 Rb

T 114.0 60.0 26 25 90 Rb

1950 L 114.5 53.0 58 61 87 Rb

T 105.0 47.0 34 29 83 Rb

4 1750 L 122.0 63.0 51 51 92 Rb

T 109.0 56.5 32 31 89 Rb

1950 L 112.5 50.0 62 62 86 Rb

T 106.5 49.5 38 33 84 Rb

4 1750 L 119.0 56.5 51 54 91 Rb

T 114.5 54.0 45 38 85 Rb

1950 L 110.5 47.0 60 62 86 Rb

T 108.5 45.5 58 53 83 Rb

4 1750 T 111.0 54.5 41 35 -

1950 T 99.0 46.0 36 36 -

Eight separate heats represented.

Annealing for 1 hr, A.C.

L is longitudinal test orientation; T, transverse.

TTaabbllee 99

- Tensile Properties of Hot-Rolled Round (4-in. Diameter)

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Room Longitudinal 199.5 178.0 15.0 24.0 44

Room Transverse 198.5 173.5 12.0 16.0 40

1200 Longitudinal 167.0 152.5 13.0 24.0 -

Room Longitudinal 197.0 164.0 17.0 23.0 44

Room Transverse 192.0 165.0 19.0 24.0 44

Heat Treatment: 1750°F/1 hr, A.C. + 1325°F/8 hr, F.C. to 1150°F, Hold at 1150°F for Total Aging Time of 18 hr

Heat Treatment: 1950°F/1 hr, A.C. + 1400°F/10 hr, F.C. to 1200°F, Hold at 1200°F for Total Aging Time of 20 hr

In stress-rupture tests under conditions of 1300°F and 75 ksi, results were: 68.2 hr life, 10.0% elongation and 13.0% reduction of area.

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TTaabbllee 1100

- Room-Temperature Tensile Properties of Material Hot-Rolled and Aged

(1325°F/8 hr, F.C. to 1150°F, Hold at 1150°F for Total Aging Time of 18 hr)

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0.65625-in. Diam. 206.5 189.5 19.0 34.5 42

0.625-in.-Diam. 206.5 179.5 22.0 45.5 41

0.625-in.-Diam. 210.0 184.0 22.0 44.5 42

13/16-in.-Diam. 209.0 181.0 22.0 43.0 43

1.25- x 1.25-in. Flat 227.5 210.0 17.0 40.8 44

1.5- x 175-in. Flat 215.0 172.0 19.0 35.0 42

0.625- x 1-in. Flat 215.5 184.0 24.0 45.5 44

0.625 As-Rolled 140.0 85.7 46 58 23 Rc

1750°F/1 hr 140.0 83.0 45 49 99 Rb

1950°F/1 hr 117.5 48.5 58 64 85 Rb

1750°F/1 hr, Age 208.0 180.0 21 39 46 Rc

1950°F/1 hr, Age 194.0 157.0 23 34 45 Rc

0.625 As-Rolled 139.0 78.5 46 62 98 Rb

1750°F/1 hr 138.0 75.5 54 49 97 Rb

1950°F/1 hr 115.5 48.0 64 67 85 Rb

1750°F/1 hr, Age 208.5 179.5 20 39 45 Rc

1950°F/1 hr, Age 194.5 158.0 20 26 44 Rc

1.0 As-Rolled 130.0 65.0 54 67 95 Rb

1750°F/1 hr 129.0 64.5 55 61 94 Rb

1950°F/1 hr 112.5 52.0 64 68 87 Rb

1750°F/1 hr, Age 201.5 175.0 20 36 46 Rc

1950°F/1 hr, Age 188.0 152.0 21 34 45 Rc

1.5 As-Rolled 147.0 105.5 40 52 32 Rc

1750°F/1 hr 141.5 72.5 46 45 97 Rb

1950°F/1 hr 120.0 55.0 58 60 89 Rb

1750°F/1 hr, Age 205.0 167.5 20 28 46 Rc

1950°F/1 hr, Age 191.0 153.0 24 36 43 Rc

4.0 1750°F/1 hr 117.5 55.0 53 52 90 Rb

1950°F/1 hr 112.5 48.0 60 63 87 Rb

1750°F/1 hr, Age 192.0 165.0 17 24 46 Rc

1950°F/1 hr, Age 195.5 165.0 21 34 43 Rc

TTaabbllee 88

- Room-Temperature Tensile Properties of Hot-Rolled Bar

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Five separate heats represented. All tests are longitudinal.

When annealing is at 1750°F, aging is 1325°F/8 hr, F.C. to 1150°F for total aging time of 18 hr. When annealing is at 1950°F, aging is 1400°F/10 hr, F.C. to

1200°F for total aging time of 20 hr.

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TTaabbllee 1122

- Room-Temperature Tensile Properties of Forged Flats (1 x 2-in. Thick, Annealed 1950°F/1 hr, A.C. and Aged)

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Longitudinal 191.5 159.0 20 32 40

Transverse 187.0 153.0 13 16 40

Longitudinal 191.1 160.0 19 29 42

Transverse 185.5 152.0 14 14 42

Longitudinal 194.0 162.0 17 26 43

Transverse 192.5 160.0 17 25 43

Longitudinal 195.0 165.0 18 23 43

Transverse 195.0 163.0 16 18 43

Longitudinal 193.0 164.0 17 22 42

Transverse 191.5 159.0 16 23 42

Longitudinal 193.5 166.0 15 21 42

Transverse 190.0 158.5 14 22 42

Longitudinal 199.5 171.0 17 26 44

Transverse 200.0 167.5 19 28 44

Longitudinal 195.0 165.0 18 26 42

Transverse 195.0 160.0 20 28 42

Longitudinal 198.0 170.0 20 33 43

Transverse 192.5 163.0 15 29 43

Longitudinal 198.0 174.0 21 34 43

Transverse 196.5 170.0 18 25 43

Longitudinal 200.0 170.0 17 24 43

Transverse 193.0 158.0 17 30 43

Longitudinal 189.0 157.5 21 35 42

Transverse 189.0 157.0 18 27 42

1400°F/10 hr, F.C. to 1200°F, hold at 1200°F for total aging time of 20 hours.

TTaabbllee 1133

- Room-Temperature Tensile Properties of 1-in. Thick Pancake

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Radial 186.0 153.0 20 31 43

Tangential 186.5 154.0 18 29 43

Radial 195.0 151.0 20 33 43

Tangential 184.5 152.5 20 29 43

Radial 189.0 155.0 15 24 44

Tangential 185.0 154.0 19 23 44

Radial 188.0 153.0 20 31 43

Tangential 185.0 152.5 18 28 43

Upset-forged 3 to 1 reduction from a 4.0-in. diameter round. Forging temperature, 2000°F. Heat treatment: 1950°F/1-2 hr, plus 1400°F/10 hr, F.C. to 1200°F.

Hold at 1200°F for a total aging time of 20 hr. Samples are from 4 separate heats.

TTaabbllee 1111

- Room-Temperature Tensile Properties of Pancake Forging (1700°F/1 hr plus 1325°F/8 hr, F.C. to 1150°F,

Hold at 1150° for Total Aging Time of 18 hr)

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YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),, kkssii

TTeennssiillee SSttrreennggtthh,, kkssii

Radial center, top edge 182.0 159.0 10.0 10.5 -

Radial center, center 196.0 160.0 24.0 33.0 -

Radial center, bottom edge 186.5 159.5 16.0 19.0 -

Tangential, top edge 209.0 181.0 19.0 27.5 17-21

Tangential, bottom edge 210.0 179.0 18.0 29.5 21

Piece 6.75-in. long by 4.5-in. octagon, heated at 2050°F, upset to 4.5-in. thick; heated at 1800°F, upset to 2.25-in. thick by 8-in. diameter pancake.

IINNCCOONNEELL

®®

aallllooyy 771188

CCoolldd--FFiinniisshheedd PPrroodduuccttss

Properties of cold-rolled sheet aged at 1325°F/8 hr, F.C. to 1150°F, hold at 1150°F for total aging time of 18 hours are shown

in Table 15. Table 16 gives the effect of the heat treatment specified by AMS 5597 on material of various thickness.

Some properties of tubing are given in Table 17.

TTaabbllee 1155

- Room-Temperature Tensile Properties of Cold-Rolled Sheet

TThhiicckknneessss,, iinn.. CCoolldd RReedduuccttiioonn,, %%

CCoonnddiittiioonn

TTeennssiillee SSttrreennggtthh,, kkssii

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),, kkssii

EElloonnggaattiioonn iinn 22 llnn..,, %%

0.025 27 As Cold-Rolled 155.0 130.0 14

Cold-Rolled, Aged 209.0 190.0 10

As Cold-Rolled 154.0 128.0 15

Cold-Rolled, Aged 223.5 209.5 10

As Cold-Rolled 154.0 132.0 14

Cold-Rolled, Aged 211.5 194.0 8

As Cold-Rolled 156.0 132.0 14

Cold-Rolled, Aged 216.0 195.0 13

0.050 21 As Cold-Rolled 138.0 112.0 22

Cold-Rolled, Aged 208.0 189.0 9

As Cold Rolled 143.5 117.5 19

Cold-Rolled, Aged 212.5 196.0 10

0.093 18 As Cold-Rolled 140.5 115.0 26

Cold-Rolled, Aged 210.0 188.5 16

0.125 26 As Cold-Rolled 158.5 137.0 11

Cold-Rolled, Aged 219.0 206.5 8

0.125 23 As Cold-Rolled 140.5 120.0 21

Cold-Rolled, Aged 204.0 186.5 12

0.074 18.5 As Cold-Rolled 145.0 116.5 25

0.062 28 As Cold-Rolled 159.5 134.0 11

Aging--1325°F/8 hr, F.C. to 1150°F, hold at 1150°F for total aging time of 18 hours.

TTaabbllee 1144

- Tensile Properties of Pancake Forging

HHeeaatt TTrreeaattmmeenntt HHaarrddnneessss,, RRcc

RReedduuccttiioonn ooff

AArreeaa,, %%

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),, kkssii

EElloonnggaattiioonn,, %%

TTeennssiillee SSttrreennggtthh,,

kkssii

TTeesstt

TTeemmppeerraattuurree,, °°FF

1800°F/1 hr, W.Q. + 1325°F/8 hr, Room 204.5 176.0 16.0 23.0 38

F.C. to 1150°F, hold at 1150 °F for Room 201.0 168.0 21.0 28.3 41

total aging time of 18 hr 1200 163.0 145.5 26.0 47.4 -

1950°F/1 hr, W.Q. + 1400°F/10 hr,

F.C. to 1200°F, hold at 1200°F for Room 190.0 152.0 18.0 24.3 35

total aging time of 20 hr

Pieces 4-in. diameter by 2-in. length heated at 1900°F and upset-forged to 5.5-in.-diameter by 1-in.-thickness pancake. Tests are transverse center-to-

midsection.

IINNCCOONNEELL

®®

aallllooyy 771188

160

120

200018001600140012001000800600400200

200

Temperature, °F

Elongation, % Stress, ksi

Tensile Strength

Elongation

Yield Strength

FFiigguurree 11..

High-temperature properties of ½-in. diameter hot-rolled,

annealed (1800°F/1 hr) and aged (1325°F/8 hr, F.C. to 1150°F, hold

at 1150°F for total aging time of 18 hours) bar.

HHIIGGHH-- AANNDD LLOOWW--TTEEMMPPEERRAATTUURREE

PPRROOPPEERRTTIIEESS

Properties of hot-rolled bar annealed at 1800°F and aged

are shown in Figure 1. Table 18 shows room-temperature

properties of hot-rolled plate annealed and aged per AMS

5596H. Properties of hot-rolled round annealed at 1950°F

and aged are in Table 19. Data on hot-rolled round (annealed

at 1800°F and aged ) for the range of -320°F to 1300°F

are given in Table 20.

Table 21 compares low-temperature properties (short

transverse tests) of specimens machined from a forging and

given the 1800°F anneal and age with those given the

1950°F anneal and age.

Table 22 shows room and 1200°F and 1300°F

properties of a variety of hot-finished products annealed at

1800°F and aged.

HHoott FFiinniisshheedd PPrroodduuccttss

As-Tube Reduced

247.0 211.0 6.0 42.0

Aged 1325°F/8 hr, F.C.

100°F/hr to 1150°F/

266.0 261.0 4.0 51.5

8 hr, A.C.

TTaabbllee 1166

- Room-Temperature tensile properties of Sheet Annealed

and Aged in Accordance with AMS 5597

TThhiicckknneessss,, iinn EElloonnggaattiioonn,, %%

YYiieelldd SSttrreennggtthh,,

kkssii

TTeennssiillee

SSttrreennggtthh,, kkssii

0.010 192.5 172.5 17

0.012 204.0 169.5 19

0.015 198.0 162.0 19

0.016 196.0 163.5 19

0.018 196.5 155.5 21

0.021 202.5 169.0 20

0.025 199.0 162.5 20

0.031 197.0 160.0 21

0.040 208.0 172.0 16

0.047 199.0 166.5 20

0.050 211.0 177.0 16

0.062 203.5 171.0 18

0.078 192.0 158.5 17

0.080 200.0 163.5 20

0.093 199.0 167.0 19

0.100 208.0 176.0 18

0.109 204.0 171.0 19

0.125 203.5 172.0 16

0.156 196.5 161.0 21

0.187 207.5 182.0 18

0.210 194.5 160.0 22

0.250 205.0 170.5 19

TTaabbllee 1177

- Effect of Aging on Room-Temperature Properties of

Tube Reduced 70% to 0.133-in. Wall, 1.513-in. O.D.

TTeennssiillee

SSttrreennggtthh,,

kkssii

HHaarrddnneessss,,

RRcc

EElloonnggaattiioonn,,

YYiieelldd

SSttrreennggtthh

((00..22%%

OOffffsseett)),, kkssii

CCoonnddiit

tiioonn

0.5 206 177 18 43

0.75 204 170 19 42

1 204 173 17 42

IINNCCOONNEELL

®®

aallllooyy 771188

TTaabbllee 2200

- Effect of Temperature on Tensile Properties of Hot-Rolled Round (5/8-in. Diameter, Annealed 1800°F/1 hr and Aged)

TTeemmppeerraattuurree,, °°FF RReedduuccttiioonn ooff AArreeaa,, %%EElloonnggaattiioonn,, %%YYiieelldd SSttrreennggtthh,, kkssiiTTeennssiillee SSttrreennggtthh,, kkssii

-320 237.0 173.5 26.0 27.0

-60 201.5 158.0 23.0 33.5

80 190.5 153.5 22.0 32.5

1200 164.5 145.0 28.0 59.2

1300 145.5 133.0 22.0 34.0

1325°F/8 hr, F.C. to 1150°F, hold at 1150°F for total aging time of 18 hr.

TTaabbllee 1188

- Room-Temperature Tensile Properties of Hot-Rolled Plate Annealed and Aged in Accordance with AMS 5596H

TThhiicckknneessss,, IInn..

HHaarrddnneessss,, RRccEElloonnggaattiioonn,, %%YYiieelldd SSttrreennggtthh,, kkssiiTTeennssiillee SSttrreennggtthh,, kkssii

Values for each thickness are average of six samples, different heats.

Room 198.0 163.0 21 30

600 183.5 156.0 16 34

1000 173.0 148.0 16 30

1200 160.0 140.0 15 25

1300 146.0 135.0 8 10

1400 123.5 116.0 5 10

1500 105.0 100.0 15 20

TTaabbllee 1199

- High-Temperature Tensile Properties of Hot-Rolled Round, Annealed and Aged (1950°F/1 hr, plus 1400°F/10 hr, F.C. 100°F/hr to

1200°F, hold at 1200°F for 8 hr)

TTeesstt TTeemmppeerraattuurree,, °°FF

RReedduuccttiioonn ooff AArreeaa,,

EElloonnggaattiioonn,, %%

YYiieelldd SSttrreennggtthh ((00..22%%

OOffffsseett)),, kkssii

TTeennssiillee SSttrreennggtthh,, kkssii

Round, 4-in.diameter, from single heat.

TTaabbllee 2211

- Low-Temperature Properties of Forging (Short Transverse Tests)

TTeesstt TTeemmppeerraattuurree,, °°FF

NNoottcchh SSttrreennggtthh,,

TTeennssiillee SSttrreennggtthh

RRaattiioo

RReedduuccttiioonn ooff AArreeaa,, %%

EElloonnggaattiioonn iinn 44DD,,

YYiieelldd SSttrreennggtthh

((00..22%%OOffffsseett)),,

kkssii

TTeennssiillee SSttrreennggtthh,,

kkssii

Room 187.0 165.9 17.0 23.0 1.45

-110 198.9 174.4 17.2 20.0 1.37

-320 229.0 186.8 14.0 14.0 1.30

-423 237.2 194.9 13.5 11.5 1.30

Room 181.5 147.7 19.0 24.5 1.37

-110 195.9 158.1 15.0 18.5 1.41

-320 228.7 176.7 17.5 19.5 1.28

-423 244.2 186.8 16.5 18.0 1.19

1800°F/45 min, A.C. plus 1325°F/8 hr, F.C. to 1150°F, Hold at 1150°F for Total Aging Time of 18 hr

1950°F/45 min, A.C. plus 1400°F/10 hr, F.C. to 1200°F, Hold at 1200°F for Total Aging Time of 20 hr

Specimens machined from forging with dimensions 4 by 9 by 15-in.

Notch concentration factor K

, 6.3.

IINNCCOONNEELL

®®

aallllooyy 771188

TTaabbllee 2222

- High-Temperature Tensile Properties of Annealed and Aged Hot-Finished Material

(1800°F/1 hr, plus 1325°F/8 hr, F.C. to 1150°F, Hold at 1150°F for Total Aging Time of 18 hours)

FFoorrmm TTeemmppeerraattuurree,, °°FF

TTeennssiillee SSttrreennggtthh,,

kkssii

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),, kkssii

EElloonnggaattiioonn,, %%

Reedduuccttiioonn ooff AArreeaa,,

HHaarrddnneessss,, RRcc

Forged Pancake

Radial Center Room 196.0 160.0 24 33 -

Tang. Mid.Rad. 1200 162.0 138.5 23 38 -

1300 146.0 135.0 30 62 -

Hot Rolled, Room 201.0 171.0 26 50 41

0.625-in.-Diam. 1200 164.5 145.0 28 59 -

1300 145.5 133.0 22 34 -

Forged Rod, Room 184.5 152.0 28 42 -

6-in.-Diam. 1300 129.0 113.0 14 16 -

Hot-Rolled, Room 211.0 174.0 23 40 -

0.5-in.-Diam. 1200 168.0 148.8 22 32 -

1300 145.0 136.5 20 27 -

Hot-Rolled, Room 207.5 172.0 25 44 40

0.5-in.-Diam. 1200 163.5 145.0 26 49 -

1300 137.0 126.0 25 25 -

Forged Square, Room 180.0 152.0 23 40 -

1- x 1-in. 1200 159.0 138.0 20 28 -

1300 140.0 129.0 26 44 -

Forged Flat, Room 184.5 154.0 24 42 44

1- x 2-in. 1200 150.0 132.5 21 38 -

1300 140.0 125.5 17 22 -

Hot-Rolled, Room 190.0 152.0 22 37 42

2-in.-Diam. 1200 153.0 130.0 30 46 -

1300 131.5 117.0 23 34 -

Forged Round, Room 187.0 155.0 20 37 42

6-in.-Diam. 1200 156.0 134.0 18 24 -

1300 136.5 123.0 12 13 -

Forged Flat, Room 204.0 162.5 18 33 44

0.625- x 0.75-in. 1200 165.5 147.0 26 61 -

1300 138.0 126.0 32 68 -

6.75-in. long by 4.5-in octagonal heated at 2050°F, upset-forged to 4.5-in. thick; reheated at 1800°F, upset-forged to 2.25-in. thick pancake.

TTaabbllee 2244

- Tensile Properties of 0.065-in. Cold-Rolled Sheet

CCoonnddiittiioonn

HHaarrddnneessssEElloonnggaattiioonn,, %%

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),, kkssii

TTeennssiillee SSttrreennggtthh,,

kkssii

TTeesstt TTeemmppeerraattuurree,,

°°FF

GGrraaiinn SSiizzee,, AASSTTMM

NNoo..

Annealed 7 Room 141.0 73.0 38.0 99 Rb

Annealed and Aged

- Room 214.0 188.5 15.0 46 Rc

Annealed and Aged - 1200 166.0 149.5 13.5 -

In accordance with AMS 5596.

Stress-rupture properties at 1300°F and 72.5 ksi: 35.3 hr life, 22.0% elongation.

IINNCCOONNEELL

®®

aallllooyy 771188

CCoolldd--FFiinniisshheedd PPrroodduuccttss

High-temperature tensile properties of cold-rolled sheet

annealed in accordance with AMS 5596 are shown in Table

23. More data on 5596-processed material appear in Table

24.

Table 25 shows room-temperature tensile properties of

sheet annealed and aged per AMS 5596. Low-temperature

properties of sheet processed in accordance with AMS 5596

are shown in Table 26. These data indicate the effects of

sheet thickness as well as annealing and aging treatment.

Large increases in strength are achieved by cold working and

aging. Additional data on notch tensile strength are shown in

Figure 2.

Table 27 compares data on annealed and aged sheet

with direct-aged sheet over a temperature range from -110°

to 1000°F.

More data on sheets of various thicknesses are shown in

Table 28.

TTaabbllee 2233

- High-Temperature Tensile Properties of Cold-Rolled 0.054-in. Sheet Annealed in Accordance with AMS 5596

TTeemmppeerraattuurree,, °°FF EElloonnggaattiioonn,, %%YYiieelldd SSttrreennggtthh ((00..22%% OOffffsseett)),, kkssiiTTeennssiillee SSttrreennggtthh,, kkssii

Room 135.0 76.0 44.5

1000 119.5 55.5 43.0

1200 120.0 72.0 32.0

1400 103.0 64.5 7.0

1600 74.5 52.5 39.0

-400

300

160

280

260

240

220

200

180

1000-100-200-300

Temperature, °F

Stress, ksi

Cold-Rolled 20%

and Aged

Annealed

and Aged

FFiigguurree 22..

Notch tensile strength of 0.031-in. sheet, heat-treated in

accordance with AMS 5596 (K

=7.2; transverse tests).

TTaabbllee 2255

- Room-Temperature Tensile Properties of Cold-Rolled Sheet, Annealed and Aged in Accordance with AMS 5596

TThhiicckknneessss,, iinn.. HHaarrddnneessss,, RRccEElloonnggaattiioonn,, %%YYiieelldd SSttrreennggtthh,, kkssiiTTeennssiillee SSttrreennggtthh,, kkssii

0.187 205 177 20 44

0.156 207 180 20 44

0.125 206 178 19 44

0.100 209 183 19 44

0.063 205 179 19 44

0.035 208 184 18 44

0.025 203 177 19 44

Each size average of four samples, four heats.

IINNCCOONNEELL

®®

aallllooyy 771188

TTaabbllee 2266

- Tensile Properties of Cold-Rolled Sheet (Annealed and Aged in Accordance with AMS 5596; Transverse Tests)

TThhiicckknneessss,,

iinn..

TTeemmppeerraattuurree,, °°FF

TTeennssiillee

SSttrreennggtthh,,

kkssii

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),,

kkssii

EElloonnggaattiioonn,,

HHaarrddnneessss,,

RRcc

NNoottcchh TTeennssiillee

SSttrreennggtthh,, kkssii

((KK

==66..33))

NNoottcchh//UUnnnnoottcchh

TTeennssiillee SSttrreennggtthh

RRaattiioo

0.025 Room 204.5 177.0 14.0 48 - -

-320 253.5 203.0 12.5 48 215.5 0.85

0.062 Room 205.75 174.5 19.0 45 204.0 0.99

(30% Reduction)

-320 254.25 200.0 20.0 45 219.5 0.86

0.075 Room 201.0 170.25 18.0 44 213.25 1.06

(10% Reduction)

-320 249.25 194.25 18.0 44 233.25 0.94

0.93 Room 202.0 170.5 16.0 41 - -

-320 251.0 189.5 22.5 45 244.0 0.97

0.125 Room 205.5 181.0 13.5 47 - -

-320 262.5 208.5 18.0 46 255.0 0.97

Values for these specimens are averages of 2 tests.

TTaabbllee 2277

- Tensile Properties of 0.027-in. Sheet Reduced 20% (Transverse Tests)

YYiieelldd

SSttrreennggtthh

((00..22%%

OOffffsseett)),,

kkssii

TTeesstt

TTeemmppeerraattuurree,,

°°FF

TTeennssiillee

SSttrreennggtthh,, kkssii

YYiieelldd

SSttrreenng

gtthh

TTeennssiillee

SSttrreennggtthh

TTeennssiillee

SSttrreennggtthh//

00..229977

llbb//ccuu.. iinn..

NNoottcchh

TTeennssiillee

SSttrreennggtthh,, kkssii

((KK

==66..33))

EElloonnggaattiioonn,,

SSaammppllee

RRaattiioo ooff NNoottcchh TTeennssiillee

SSttrreennggtthh ttoo

Room-temperature density.

Stressed at 40 ksi for 1000 hr at 650°F prior to testing.

Cold-Rolled, Annealed -110 212.0 168.5 25.0 195.0 714,000 0.92 1.16

and Aged in Accordance 85 196.0 163.0 21.0 183.0 660,000 0.93 1.12

with AMS 5596 85

197.0 162.5 21.0 178.0 - 0.91 1.10

350 191.0 153.0 20.0 - - - -

650 171.5 141.5 20.0 158.0 578,000 0.92 1.11

650

172.0 137.5 23.0 163.0 - 0.95 1.19

800 188.0 141.0 23.0 156.0 - 0.83 1.11

1000 169.0 135.0 24.0 143.0 570,000 0.85 1.06

Cold-Rolled and Aged -320 260.5 229.0 13.0 236.5 877,000 0.91 1.03

in Accordance with -110 232.0 206.5 17.0 209.0 781,000 0.88 1.01

AMS 5596 85 221.0 198.5 12.0 196.5 745,000 0.89 0.99

212.0 195.5 13.0 199.0 - 0.94 1.02

350 205.0 188.5 12.0 179.0 - 0.88 0.96

650 193.5 179.0 12.0 173.5 652,000 0.90 0.97

650

198.5 182.0 13.0 172.0 - 0.87 0.95

800 - - - 169.0 - - -

1000 180.5 165.3 10.0 166.5 608,000 0.92 1.01

75 L 114.0 47.3 43 89.2 0.78

T 116.0 47.0 49 88.8 0.77

-320 L 152.0 70.7 50 121.0 0.80

T 157.0 75.8 43 118.0 0.75

-423 L 187.0 97.3 49 146.0 0.78

T 176.0 91.8 40 142.0 0.81

75 L 192.0 155.0 21 198.0 1.03

T 189.0 154.0 20 196.0 1.04

-320 L 243.0 186.0 26 234.0 0.96

T 239.0 181.0 22 229.0 0.96

-423 L 267.0 200.0 21 254.0 0.95

T 262.0 195.0 21 259.0 0.99

75 L 195.0 157.0 20 207.0 1.06

T 194.0 157.0 20 206.0 1.06

-100 L 214.0 171.0 23 221.0 1.03

T 213.0 170.0 23 223.0 1.04

-320 L 232.0 185.0 33 214.0 0.92

T 247.0 192.0 26 229.0 0.93

-423 L 278.0 205.0 28 276.0 0.99

T 276.0 204.0 27 269.0 0.97

75 L 214.0 197.0 15 238.0 1.11

T 204.0 183.0 13 226.0 1.11

-320 L 268.0 227.0 25 272.0 1.01

T 254.0 214.0 21 262.0 1.03

-423 L 286.0 239.0 28 293.0 1.02

T 281.0 228.0 22 286.0 1.02

75 L 230.0 218.0 7 248.0 1.08

T 223.0 206.0 7 248.0 1.11

-100 L 249.0 230.0 11 267.0 1.07

T 242.0 218.0 8 262.0 1.08

-320 L 292.0 259.0 16 292.0 1.00

T 273.0 238.0 13 285.0 1.04

-423 L 309.0 269.0 15 309.0 1.00

T 295.0 251.0 16 301.0 1.02

75 L 240.0 231.0 6 261.0 1.09

-320 L 297.0 274.0 9 304.0 1.02

-423 L 337.0 287.0 12 320.0 0.95

IINNCCOONNEELL

®®

aallllooyy 771188

TTaabbllee 2288

- Low-Temperature Tensile Properties of Sheet (Heat-Treated in Accordance with 5596)

TTeesstt TTeemmppeerraattuurree,,

°°FF

TTeesstt OOrriieennttaattiioonn

TTeennssiillee SSttrreennggtthh,,

kkssii

YYiieelldd SSttrreennggtthh,, kkssii

EElloonnggaattiioonn,,

NNoottcchh TTeennssiillee

SSttrreennggtthh

ppssii

NNoottcchh//UUnnnnoottcchh

TTeennssiillee SSttrreennggtthh

RRaattiioo

0.018-0.025-in. Material - 30% Cold-Rolled and Aged (Heat 3)

0.031-in. Material - 20% Cold-Rolled and Aged (Heat 2)

0.031-in. Material - Annealed and Aged (Heat 2)

0.010-in. Material - Annealed and Aged (Heat 1)

L, longitudinal; T, transverse.

Notch concentration, K

, 6.3

0.018-0.025-in. Material - 50% Cold-Rolled and Aged (Heat 3)

0.010-in. Material - Annealed (Heat 1)

IINNCCOONNEELL

®®

aallllooyy 771188

TTaabbllee 2299

- Room-Temperature Impact Strength of Hot-Finished Products

DDiiaammeetteerr

iinn..

TTeennssiillee SSttrreennggtthh,,

kkssii

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),, kkssii

CChhaarrppyy VV--NNoottcchh

IImmppaacctt SSttrreennggtthh,, fftt••llbb

Reedduuccttiioonn ooff AArreeaa,,

EElloonnggaattiioonn,,

0.625 208.0 180.0 21.0 39.0 18.5

1 209.0 174.0 20.0 24.8 10.0

1.5 204.0 165.5 19.0 24.5 11.0

8 209.0 183.5 17.0 32.0 13.0

12 196.0 165.0 25.0 39.1 24.0

0.625 194.0 157.0 23.0 34.0 26.0

1 188.0 152.0 21.0 34.0 33.0

1.5 191.0 153.0 24.0 36.0 28.5

8 194.5 160.0 22.0 34.3 35.0

12 192.5 162.0 27.0 42.0 39.0

Diameters of 8- and 12-in. were forged; others are hot-rolled.

Average of 2 tests.

IIMMPPAACCTT SSTTRREENNGGTTHH

Room-temperature impact strength of some hot-finished

products are shown in comparison with their tensile

properties in Table 29. The data also point out the effect of

annealing at 1750°F and aging at 1325°F/8 hr, F.C. to

1150°F, hold at 1150°F for total aging time of 18 hours

versus annealing at 1950°F and aging at 1400°F/10 hr, F.C.

to 1200°F for total aging time of 20 hours. Some impact

properties of a pancake forging are shown in Table 11 (page 7).

Low-temperature impact strength of plate is shown in Table

30.

TTaabbllee 3300

- Impact Strength of 1-in. Plate (Annealed and Aged in

Accordance with AMS 5596)

TTeennssiillee PPrrooppeerrttiieess ((LLoonnggiittuuddiinnaall OOrriieennttaattiioonn))

TTeemmppeerraattuurree,, °°FF

CChhaarrppyy VV--NNoottcchhCChhaarrppyy KKeeyyhhoollee

IImmppaacctt SSttrreennggtthh,, fftt••llbb

Room 15.5, 16.0, 17.0 19.5, 20.5, 22.5

-320 13.5, 13.5, 15.0 18.5, 19.0, 19.5

TTaabbllee 3311

- Room-Temperature Fatigue Strength of 6- by 9-in. Forging

CCoonnddiittiioonn

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AArreeaa,, %%

EElloonnggaattiioonn,, %%

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),, kkssii

TTeennssiillee SSttrreennggtthh,,

kkssii

1100

CCyycclleess

1100

CCyycclleess

1100

CCyycclleess

GGrraaiinn SSiizzee,,

iinn..

TTeennssiillee PPrrooppeerrttiieess FFaattiigguuee SSttrreennggtthh,, kkssii

Annealed 143.0

99.5

0.0023

74.0 67.5 66.5

Annealed and Aged 191.25 169.5 10.5 20 0.0021 77.5 71.0 69.5

Rotating-beam fatigue tests. Values are average of 2 samples (polished specimens)--center short transverse and mid short transverse.

Annealing at 1750°F/1 hr Aging at 1325°F/8 hr, F.C. to 1150°F, hold at 1150°F for total aging time of 18 hr.

Values for center short transverse only.

Heat Treatment: 1950°F/1 hr, A.C. + Aged 1400°F/10 hr, F.C. to 1200°F, Hold at 1200°F for Total Aging Time of 20 hours

Heat Treatment: 1750°F/1 hr, A.C. + Aged 1325°F/8 hr, F.C. to 1150°F, Hold at 1150°F for Total Aging Time of 18 hours

Room-temperature fatigue properties of annealed and

annealed and aged (1750°F, plus 1325°F/8 hr, F.C. to

1150°F, hold at 1150°F for total aging time of 18 hours)

forging specimens are shown in Table 31. Table 32 presents

fatigue strength of hot-rolled plate annealed and aged in

accordance with AMS 5596.

Fatigue strength of cold-rolled sheet is shown in Figure

If fatigue strength is of prime importance, INCONEL

alloy 718 forgings can be used in the annealed rather than the

annealed and aged condition; aging raises fatigue strength

only slightly (less than 4 ksi in Table 31).

Grain size is a major factor in achievement of high

fatigue strength. Its effect can be seen in Figure 4. The low-

temperature heat-treatment schedule (such as that in AMS

5596) will promote the requisite fine grain. See also Tables

31 and 32. High-temperature fatigue strength of annealed

and aged bar is shown in Table 33.

Low-cycle fatigue life of INCONEL alloy 718 is the

same whether tested in fully reversed bending or in zero-to-

maximum bending. Test results are shown in Figure 5.

FFAATTIIGGUUEE SSTTRREENNGGTTHH

IINNCCOONNEELL

®®

aallllooyy 771188

100

120

Cycles to Failure

Stress, ksi

Longitudinal

Transverse

FFiigguurree 33..

Room-temperature fatigue strength of 0.068-in. cold-

rolled sheet annealed and aged in accordance with AMS 5596

(Krouse tests). Average grain size, 0.002 in.

0.000

120

100

0.0060.0040.002

Average Grain Size, in.

Stress, ksi

FFiigguurree 44..

Effect of grain size on endurance limit (10

cycles) of

plate annealed and aged in accordance with AMS 5596.

Annealed Longitudinal 132.5 58.0 46 46.6 0.0008 73.0 70.0 70.0

Annealed and Aged Longitudinal 201.5 159.5 26 46.0 0.0005 96.0 81.0 78.0

Transverse 199.0 158.0 24 38.0 0.0007

Annealed and Aged Longitudinal 202.0 160.5 26 44.5 0.0015 96.0 88.0 85

Transverse 197.5 159.0 24 41.0 0.0005

Annealed and Aged Longitudinal 196.5 158.0 27 48.5 0.0009 91.0 82.0 77.0

Transverse 196.5 158.0 27 43.0 0.0008

Annealed and Aged Longitudinal 191.0 153.5 28 41.5 0.0014 90.0 81.0 74.0

Transverse 188.5 151.5 28 41.5 0.0013

Aged Longitudinal 215.0 193.5 20 39.1 0.0008 95.0 84.0 80.0

Transverse 210.0 187.0 17 37.5 0.0012

TTaabbllee 3322

- Room-Temperature Fatigue Strength of 1.125-in. Hot-Rolled Plate

HHeeaatt

TTrreeaattmmeenntt

TTeesstt OOrriieennttaattiioonn

TTeennssiillee

SSttrreennggtthh,,

kkssii

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),,

kkssii

EElloonnggaattiioonn,,

GGrraaiinn

SSiizzee,,

iin

n..

1100

CCyycclleess

1100

CCyycclleess

1100

CCyycclleess

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ooff AArreeaa,, %%

FFaattiigguuee SSttrreennggtthh,, kkssii

TTeennssiillee PPrrooppeerrttiieess

Fatigue tests run on R.R. Moore rotating-beam fatigue machines at 10,000. Specimens were 0.300-in. diameter polished longitudinally.

In accordance with AMS 5596.

0.001

0.08

0.06

0.04

0.02

0.01

0.008

0.006

0.004

0.002

0.1

Cycles to Failure

Total Strain, in./in.

Reverse Bending

Zero to Maximum Bending

FFiigguurree 55..

Low-cycle life of plate annealed and aged in accordance

with AMS 5596. (Test orientation parallel to rolling direction). Grain

size, 0.0021-in. Modified Krouse plate fatigue machine.

IINNCCOONNEELL

®®

aallllooyy 771188

RRUUPPTTUURREE AANNDD CCRREEEEPP

PPRROOPPEERRTTIIEESS

For creep-limited and rupture-limited applications INCONEL alloy 718 is annealed at 1700°F-1850°F and aged at 1325°F/8

hr, F.C. to 1150°F, hold for total aging time of 18 hours (or an equivalent treatment such as in AMS 5596). Rupture and creep

properties shown in this bulletin are typical of material receiving this low-temperature treatment.

Figure 6, a plot of high-temperature rupture life, also shows the excellent properties at 1200° and 1300°F of notch

specimens of small-diameter bar.

Figure 7 shows creep strength of annealed and aged hot-rolled bar.

These rupture and creep data have been used for construction of Larson-Miller and Manson-Haferd parameter plots

(Figures 8 and 9). For convenience in design, the typical properties are also shown on the basis of 100, 1000, and 10,000 hours

(Figures 10, 11 and 12).

Rupture properties of annealed and aged cold-rolled sheet are shown in the form of a Larson-Miller parameter plot (Figure

13). As indicated by the specifications, thickness will influence rupture life.

Rupture life of round and sheet in comparison with tensile properties is shown in Tables 9 (page 6) and 24 (12).

1 10,0001,00010010

200

Rupture Life, hr

Stress, ksi

Notch

Smooth

FFiigguurree 66..

Smooth and notch rupture life of hot-rolled bar, 0.625-

in.(15.9 mm) diameter (1800°F(982°C)/1 hr, W.Q. and aged

1325°F(718°C)/8 hr, F.C. to 1150°F(621°C), hold at 1150°F(621°C)

for total aging time of 18 hr), K

=4.

200

100

0.000001 0.10.010.0010.00010.00001

1300°F(704°C)

1200°F(649°C)

1100°F(593°C)

Stress, ksi

Minimum Creep Rate, %/hr

FFiigguurree 77..

Creep strength of hot-rolled bar 0.625-in.(15.9 mm)

diameter (1800°F(982°C)/1 hr, W.Q. and aged 1325°F(718°C)/8 hr,

F.C. to 1150°F(621°C), hold at 1150°F(621°C) for total aging time

of 18 hr).

1300°F(704°C)

1200°F(649°C)

1100°F(593°C)

1000°F(538°C)

1200°F

(649°C)

TTaabbllee 3333

- High-Temperature Fatigue Strength of Hot-Rolled Bar (Annealed 1750°F/1 hr, A.C. and Aged)

TTeesstt TTeemmppeerraattuurree,,

°°FF

1100

CCyycclleess

1100

CCyycclleess

1100

CCyycclleess

1100

CCyycclleess

FFaattiigguuee SSttrreennggtthh,, kkssii

Room 132.0 101.0 92.0 90.0

600 115.0 110.0 110.0 110.0

1000 111.0 102.0 95.0 90.0

1200 100.0 94.0 88.0 72.0

Rotating-beam tests. Average grain size, 0.0008-in. Aging--1325°F/8 hr, F.C. to 1150°F, hold at 1150°F for total aging time of 18 hr.

100

500

1000

Stress, MPa

100

500

1000

Stress, MPa

100

IINNCCOONNEELL

®®

aallllooyy 771188

FFiigguurree 88

. Larson-Miller parameter plot of rupture life of hot-rolled,

0.625-in.(15.9 mm) diameter bar (1800°F(982°C)/1 hr, W.Q. and

aged 1325°F(718°C)/8 hr, F.C. to 1150°F(621°C), hold at

1150°F(621°C) for total aging time of 18 hours). In the Larson Miller

parameter, P, T is temperature, °F, and t is time, hr.

FFiigguurree 1100..

Creep-rupture properties (100 hr) of hot-rolled, 0.625-in.

(15.9 mm) diameter bar (1800°F(982°C)/1 hr, W.Q. and aged

1325°F(718°C)/8 hr, F.C. to 1150°F(621°C), hold at 1150°F(621°C)

for total aging time of 18 hr).

FFiigguurree 99..

Manson-Haferd parameter plot of minimum creep rate of

hot-rolled bar, 0.625-in. (15.9 mm) diameter (1800°F(982°C)/1 hr,

W.Q. and aged 1325°F(718°C)/8 hr, F.C. to 1150°F(621°C), hold at

1150°F(621°C) for total aging time of 18 hr). In the Manson-Haferd

parameter, S, T is temperature, °F, and C.R. is creep rate.

FFiigguurree 1111..

Creep-rupture properties (1000 hr) of hot-rolled, 0.625-

in. (15.9 mm) diameter bar (1800°F(982°C)/1 hr, W.Q. and aged

1325°F(718°C)/8 hr, F.C. to 1150°F(621°C), hold at 1150°F(621°C)

for total aging time of 18 hr).

200

100

1000

100

39 52515049484746454443424140

1100°F(593°C)

1100°F(593°C) 1200°F(649°C)

1200°F(649°C)

1400°F(760°C)

1300°F(704°C)

1400°F(760°C)

P = (460 + T) (25 + log t) x 10

-3

Stress, ksi

Life, hr

Notch Bar Life

Rupture Life

1.0% Plastic Strain

0.1% Plastic Strain

0.2% Plastic Strain

0.5% Plastic Strain

1400°F

(760°C)

1300°F

704°C)

1200°F

(649°C)

1100°F

(593°C)

1000°F

(538°C)

26 46444240383634323028 48 50

100

150

0.00001

0.0001

0.001

0.01

S =

T - 200

log C.R. + 30

Stress, ksi

Creep, %/hr

120

(827)

(138)

(276)

(414)

(552)

100

(690)

1300(704)1200(649)1100(593)

Stress to Produce

in 100 hr

0.5% Plastic

Strain

1.0% Plastic

Strain

0.2% Plastic

Strain

Rupture

Temperature, °F (°C)

Stress, ksi (MPa)

1100(593) 1300(704)1200(649)

120

(827)

100

(690)

(552)

(414)

(276)

(138)

0.5% Plastic

Strain

1.0% Plastic

Strain

0.2% Plastic

Strain

Stress to Produce

in 1000 hr

Rupture

Temperature, °F (°C)

Stress, ksi (MPa)

1100°F

(593°C)

1200°F

(649°C)

1300°F

704°C)

1400°F

(760°C)

1100°F

(593°C)

1200°F

(649°C)

1300°F

704°C)

1400°F

(760°C)

1000°F

(538°C)

1100°F

(593°C)

1200°F

(649°C)

1300°F

704°C)

1400°F

(760°C)

Stress, MPa

1000

500

100

Stress, MPa

1000

900

800

700

600

500

400

300

200

IINNCCOONNEELL

®®

aallllooyy 771188

FFiigguurree 1122..

Creep-rupture properties (10,000 hr) of hot-rolled,

0.625-in. (15.9 mm) diameter bar (1800°F(982°C)/1 hr, W.Q. and

aged 1325°F(718°C)/8 hr, F.C. to 1150°F(621°C), hold at

1150°F(621°C) for total aging time of 18 hr).

(138)

120

(827)

100

(690)

(552)

(414)

(276)

1300(704)1200(649)1100(593)

Stress, ksi (MPa)

Temperature, °F (°C)

Stress to Produce in

10,000 hr

1.0% Plastic

Strain

0.5% Plastic

Strain

0.2% Plastic

Strain

Rupture

TTaabbllee 3344

- Composition, %, of INCONEL Filler Metal 718

Nickel (plus Cobalt) .........................................................50.00-55.00

Copper................................................................................0.30 max.

Manganese .........................................................................0.35 max.

Iron.........................................................................................Balance

Silicon .................................................................................0.35 max.

Carbon ................................................................................0.08 max.

Sulfur.................................................................................0.015 max.

Titanium...............................................................................0.65-1.15

Aluminum ............................................................................0.20-0.80

Niobium (plus Tantalum)......................................................4.75-5.50

Chromium............................................................................17.0-21.0

Molybdenum .......................................................................2.80-3.30

Phosphorus.......................................................................0.015 max.

Cobalt .................................................................................1.00 max.

Boron ................................................................................0.006 max.

WWEELLDD PPRROOPPEERRTTIIEESS

INCONEL alloy 718 is readily welded by the gas tungsten-

arc (TIG) process using INCONEL Filler Metal 718.

Composition of this filler metal is shown in Table 34.

Mechanical properties of its all-weld metal specimens are

shown in Table 35. These test data show the effect of

postwelding treatment on tensile properties. Highest room-

temperature ductility is obtained by annealing at 1950°F

prior to aging.

Slow response of alloy 718 to age hardening enables

parts to be welded and directly age-hardened without an

intermediate stress relief. Joint efficiencies very close to

100% were realized in the tests shown in Table 38; these

specimens were from plate that had been annealed, then

welded and aged. Better properties, however, are obtained by

re-annealing after welding prior to aging.

Silver brazing compounds are known to cause stress

cracking in nickel-based alloys. If alloy 718 is cold-worked

and/or precipitation-hardened, silver brazing compounds

should not be used. Also, brazing alloys containing cadmium

are best avoided; while cadmium has not been shown to

cause cracking by itself, it can aggravate cracking from other

sources.

160

(1103)

1000

100

(414)

(552)

100

(690)

120

(827)

140

(965)

1000°F(538°C)

1200°F

(649°C)

1250°F(677°C)

1100°F(593°C)

1000°F(538°C)

1100°F(593°C)

1200°F(649°C)

1250°F(677°C)

48464442403836

P = (460 + T) (25 + log t) x 10

-3

Life, hr

Stress, ksi (MPa)

FFiigguurree 1133..

Larson-Miller parameter plot of rupture life of cold-rolled

sheet, 0.025-0.250 in. (0.64-6.35 mm) (Annealed and aged in

accordance with AMS 5596). In the Larson-Miller parameter, P, T is

temperature, °F, and t is time, hr.

1200°F

(649°C)

TTaabbllee 3377

- Room-Temperature Tensile Properties

(Transverse Tests) of Welds in 0.5-in. Plate

(Gas Tungsten-Arc Process Using INCONEL Filler Metal 718)

Direct Age 185.0 158.0 6.5 15.8

Annealed

and Aged

190.0 163.3 7.5 13.9

Annealed

and Aged

191.5 164.5 9.5 16.3

PPoossttwweelldd

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TTrreeaattmmeenntt

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AArreeaa,,

EElloonnggaattiioonn

iinn 11 llnn..,,

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SSttrreennggtthh

((00..22 %%

OOffffsseett)),, kkssii

TTeennssiillee

SSttrreennggtthh,, kks

sii

Average of 2 tests.

According to AMS 5596.

IINNCCOONNEELL

®®

aallllooyy 771188

0.028 AMS 5596 1 Crack-Free Crack-Free

0.030 1 Crack-Free Crack-Free

0.035 1 Crack-Free Crack-Free

0.035 2 Crack-Free Cracked

0.062 2 Crack-Free Crack-Free

0.062 AMS 5597 2 Crack-Free Cracked

0.062 1 Crack-Free Crack-Free

0.062 2 Crack-Free Crack-Free

0.078 1 Crack-Free Cracked

0.093 2 Crack-Free Cracked

0.109 2 Crack-Free Crack-Free

TTaabbllee 3366

- Weld-Patch Testing of Cold-Rolled, Annealed Sheet

(Procedure: Anneal plus Weld plus Age plus

Repair-Weld plus Re-Age)

SShheeeett

TThhiicckknneessss,,

iinn..

RReeppaaiirr

WWeellddiinngg aanndd

RRee--AAggiinngg

WWeellddiinngg aanndd

AAggiinngg

PPaattcchh TTeesstt

AAsssseemmbbllyy

HHeeaatt

TTrreeaattmmeenntt

CCoonnddiittiioonn AAfftteerr

Seven different heats represented in these tests.

See Figure 15.

0.045 As-Welded

125.50 84.30 28.0 30.0

1750°F, Age 180.25 148.50 7.8 12.3

1950°F, Age 197.25 162.75 18.8 26.5

1325°F, Age 186.00 153.50 11.0 13.5

0.045 As-Welded 120.75 82.30 28.0 30.5

1750°F, Age 169.50 144.00 7.8 12.0

1950°F, Age 193.50 164.85 13.3 17.0

1325°F, Age 180.50 147.75 7.8 10.3

0.09375 As-Welded 123.75 84.00 28.0 31.3

1750°F, Age 174.50 145.25 7.7 12.5

1950°F, Age

197.00 168.50 10.0 18.0

1325°F, Age

166.50 150.50 4.0 4.0

0.062 As-Welded

125.20 83.50 28.0 37.5

1750°F, Age 174.50 152.00 4.9 7.0

1950°F, Age 198.00 179.25 13.8 21.5

1325°F, Age

175.50 151.00 4.0 7.5

0.062 As-Welded 123.25 75.05 34.3 35.3

1750°F, Age 180.00 144.00 12.6 18.0

1950°F, Age

196.50 161.00 16.0 31.0

1325°F, Age 176.75 140.00 15.5 22.5

TTaabbllee 3355

- Effect of Postwelding Heat Treatment on Tensile Properties of INCONEL Filler Metal 718 All-Weld Metal

(Manual Gas Tungsten-Arc Process between 0.5-in. Plates) (Average of 2 Tests)

FFiilllleerr MMeettaall

DDiiaammeetteerr,, iinn..

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ooff AArreeaa,, %%

EElloonnggaattiioonn,,

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),, kkssii

TTeennssiillee SSttrreennggtthh,,

kkssii

HHeeaatt TTrreeaat

tmmeenntt

Each separate size shown represents test run on separate heat.

Heat treatments: 1750°F, Age is 1750°F anneal plus age at 1325°F/8 hr , F.C. 100°F/hr to 1150°F, hold at 1150°F for a total of 18 hours. 1950°F, Age is 1950°F

anneal plus age at 1400°F/10 hr, F.C. 100°F/hr to 1200°F, hold at 1200°F for a total aging time of 20 hours. 1325°F, Age is at 1325°F/8 hr, F.C. 100°F/hr to

1150°, hold at 1150°F for total aging time of 18 hr.

One test only.

All-Weld Metal Direct Age 174.50 139.25 18.3 21.5

1950°F/1 hr, Age 185.75 155.50 22.0

31.8

Transverse

Direct Age 183.50 149.50 12.0 24.8

1950°F/1 hr, Age 192.25 160.75 17.3 23.5

183.0 159.5 8.0 19.0

183.5 158.5 7.0 16.0

186.5 162.0 6.0 12.8

185.5 163.0 6.0 21.0

184.0 163.0 6.0 16.5

192.5 166.0 9.0 17.5

191.5 164.0 6.0 12.5

182.0 156.5 4.0 6.8

188.5 168.0 4.0 11.5

188.0 170.0 5.0 10.0

Average 186.5 163.0 6.0 14.4

180.5 157.5 10.0 16.0

182.5 162.0 8.0 14.0

178.0 154.0 11.0 12.5

177.5 150.0 14.0 18.5

180.0 153.5 10.0 22.0

180.0 158.5 7.0 11.5

183.5 160.5 6.0 8.5

Average 180.0 156.5 9.0 15.0

IINNCCOONNEELL

®®

aallllooyy 771188

TTaabbllee 3388

- Room Temperature Tensile Properties of Welds (Aged

1325°F/8 hr, F.C. to 1150°F, Held at 1150°F for Total Aging Time of

18 Hours)

TTeennssiillee

SSttrreennggtthh,,

kkssii

RReedduuccttiioonn

ooff AArreeaa,,

EElloonnggaattiioonn

iinn 11 llnn..,,

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),,

kkssii

Transverse Tests Across Joints

All-Weld Metal Tests

0.252-in.-diameter specimens prepared from TIG-welded 0.500-in. plate.

Plate annealed in accordance with AMS 5596 prior to welding. All tests

broke in weld. Filler metal was INCONEL 718.

TTaabbllee 3399

- Room-Temperature Tensile Properties

of Welds in 0.5-in.

Plate (Gas Tungsten-Arc Process Using INCONEL Filler Metal 718)

PPoossttwweelldd

HHeeaatt

TTrreeaattmmeenntt

RReedduuccttiioonn

ooff AArreeaa,,

EElloonnggaattiioonn

iinn 00..55 llnn..,,

YYiieelldd

SSttrreennggtthh

((00..22 %%

OOffffsseett)),,

kkssii

TTeennssiillee

SSttrreennggtthh,,

kkssii

SSaammppllee

Average of 2 tests.

Age--1400°F/10 hr, F.C. to 1200°F, hold at 1200°F for total aging time of 20 hours.

One test.

All fractures were in weld.

WWeelldd TTeennssiillee PPrrooppeerrttiieess

Room-temperature properties of welds receiving the low-

temperature anneal and/or age can be compared with results

of the high-temperature anneal and/or age in Tables 38 and

39.

Additional properties of welds annealed at 1950°F/15

min. and aged at 1400°F/10 hr, F.C. to 1200°F, hold at

1200°F for a total aging time of 20 hours are shown in Table

40. Welding was by the manual gas tungsten-arc process,

using Filler Metal 718. These welds were found satisfactory

in bend tests and radiographic examination. Slightly better

results were obtained when helium was used as the torch gas.

Notch strength of butt-welded sheet in both the heat-affected

zone and weld is shown in Table 41. These welds were heat-

treated by the low-temperature schedule.

Another laboratory using the high-temperature heat

treatment has found that notch toughness of the parent metal

and that of the weld metal are quite consistent and exceed a

notch-to-smooth bar tensile ratio of 1.30 throughout the test-

temperature range of -423°F to 1200°F. Test data are

shown in Table 42. The weld joint efficiency is

approximately 93% at -423°F and 95% at room temperature

and 1200°F.

1 188.00 11.7

2 184.20 10.0

3 184.50 10.0

4 190.20 14.3

5 192.70 17.3

Average 187.92 12.7

6 189.20 11.7

7 191.00 15.3

8 187.80 12.7

9 191.70 18.3

10 194.00 18.7

Average 190.74 15.3

TTaabbllee 4400

- Room-Temperature Tensile Properties of Annealed and

Aged Welds in 0.063-in. Sheet

TTeennssiillee SSttrreennggtthh,,

kkssii

WWeelldd EElloonnggaattiioonn llnn 11 iinn..,, %%

Argon Torch Gas; Helium Root Gas

Helium Torch Gas; Argon Root Gas

Welded manually with INCONEL FIller Metal 718. One bead. Average of 3

tests. All sheet from same heat. Heat treatment after welding: 1950°F/15

min., plus 1400°F/10 hr, F.C. to 1200°F, hold at 1200°F for total aging time of

20 hr.

IINNCCOONNEELL

®®

aallllooyy 771188

Aged 154.0 129.0

183.8 133.5

Annealed 175.0 132.3

1800°F/1 hr and Aged 163.3 136.0

TTaabbllee 4411

- Notch-Strength of Butt-Welded,

0.051-in. Cold-Rolled, Annealed Sheet

TTrreeaattmmeenntt ooff WWeelldd

WWeellddHHeeaatt--AAffffeecctteedd ZZoonnee

NNoottcchh SSttrreennggtthh

,, kkssii

Aging--1325°F/8 hr, F.C. to 1150°F, hold for total aging time of 18 hr, A.C.

All welds milled flush to parent metal. Welds made by automatic gas

tungsten-arc process with INCONEL Filler Metal 718.

Average of 2 values. Notches were milled in the center of the weld and in

the parent metal about 0.025-in. from the fusion zone K

, approximately 24.

TTaabbllee 4433

- Shear Strength of As-Welded INCONEL Filler Metal 718 Overlay on INCONEL Alloy 718

SSppeecciimmeenn

SShheeaarr SSttrreennggtthh

kkssii

TTeennssiillee SSttrreennggtthh,,

kkssii

YYiieelldd SSttrreennggtthh,,

kkssii

EElloonnggaattiioonn,,

RReedduuccttiioonn ooff AArreeaa,,

A 86.0 121.0 73.5 27.0 30.0

B 86.5 120.0 73.4 28.0 26.5

C 80.0 120.0 72.0 30.0 33.8

Specimens from 0.625-in. thick, 3-in. wide, 6-in. long overlay. Axes were parallel to direction of welding. Gage diam. of tensile specimen, 0.252-in.; gage

length, 4 x diam. Double-shear test specimens 0.250-in. diam., 1.5-in. long.

Double shear.

WWeelldd FFaattiigguuee PPrrooppeerrttiieess

Weldments were found to have a room-temperature fatigue

strength (10

cycles) of approximately 62.5 ksi (tested in

R.R. Moore rotating-beam apparatus). They were made from

hot-rolled , annealed (per AMS 5596) 0.500-in. plate, joined

with 0.125-in.-diameter INCONEL Filler Metal 718 by the

gas tungsten-arc process. Samples were aged 1325°F/8 hr,

F.C. to 1150°F, hold at 1150°F for total aging time of 18

hours and tested as polished specimens. In comparable tests,

alloy 718 bar had a fatigue strength (10

cycles) of 89.0 ksi.

WWeelldd SShheeaarr PPrrooppeerrttiieess

Shear strength of as-deposited Filler Metal 718 is shown in Table 43. The test specimens were taken from a 0.625-in. thick

overlay made by the automatic gas tungsten-arc process using 0.062-in.-diameter INCONEL Filler Metal 718.

TTaabbllee 4422

- Tensile Properties of Ring-Forging Specimens Gas-Tungsten-Arc Welded with INCONEL filler Metal 718

(Weldments Annealed 1950°F/1 hr and Aged 1400°/10 hr, F.C. to 1200°F, Hold at 1200°F for Total Aging Time of 20 hours)

SSppeecciimmeenn

NNoottcchh//UUnnnnoottcchh

TTeennssiillee SSttrreennggtthh

RRaattiioo

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),,

kkssii

EElloonnggaattiioonn,,

RReedduuccttiioonn

ooff AArreeaa,,

NNoottcchh TTeennssiillee

SSttrreennggtthh

,, kkssii

TTeennssiillee SSttrreennggtthh,,

kkssii

Room Temp.

Parent Metal 197.5 163.8 25.5 38.5 272.8 1.38

Weld 189.7 165.6 19.3 38.1 263.1 1.39

-423°F

Parent Metal 245.9 203.6 22.5 33.1 323.8 1.32

Weld 237.9 201.0 19.7 30.7 308.7 1.30

1200°F

Parent Metal 143.8 125.7 21.1 40.7 207.4 1.44

Weld 147.3 127.3 11.9 30.2 204.2 1.39

Data are averages of 2-5 tests.

Notch concentration factor, K

, 6.3

IINNCCOONNEELL

®®

aallllooyy 771188

WWeelldd RRuuppttuurree PPrrooppeerrttiieess

Rupture strength at 1200° and 1300°F of heat-treated weldments in sheet is compared with parent metal in Table 44. In other

tests, welds whose process steps were age, weld, and age had lives of 0.3 hr (1200°F, 100.0 ksi) and 4.9 hr (1300°F, 72.5 ksi)

; fractures were in the heat-affected zone. Notch-bar life at 1300°F and 75.0 ksi is shown in Table 45.

SSPPRRIINNGG PPRROOPPEERRTTIIEESS

The excellent relaxation resistance of INCONEL alloy 718

is a factor in its successful use for springs at temperatures up

to 1100°F. Some relaxation data are shown in Figure 14.

BBOOLLTTIINNGG

INCONEL alloy 718 combines excellent mechanical

properties over a wide temperature range with superior

oxidation and corrosion resistance. Because of these

properties it is specified for many fastener applications

where superior performance is required under varying

environmental conditions.

INCONEL alloy 718 can be strengthened in two ways:

(1) by solution treating and age hardening or (2) by cold

working and age hardening only. See Table 46.

The use of alloy 718 for bolting applications is

addressed under Section I and Section VIII, Division I of the

ASME Code by Code Case 1993.

10008006004002000

Time, hr

Relaxation, %

1100°F/70 ksi

1000°F/60 ksi

1100°F/60 ksi

FFiigguurree 1144..

Relaxation of helical coil springs made from 0.148-in.-

diameter cold-drawn No. 1 Temper wire. (Springs annealed

1800°F/1 hr and aged 1325°F/8 hr, F.C. to 1150°F, hold at 1150°F

for total aging time of 18 hr.

All-Weld Metal

Aged 11.7 4.0 6.0 14.1

Annealed and Aged 12.2 5.0 7.5 45.5

Transverse Joint

Aged 25.5 4.0 (in 0.5 in) 5.0 30.1

Annealed and Aged 15.3 3.0 (in. 0.5 in.) 8.5 25.1

TTaabbllee 4455

- Rupture Strength of Welds

(Test Conditions: 1300°F and 75.0 ksi)

LLiiffee,,

hhrr

NNoottcchh BBaarr LLiiffee,,

hhrr

RReedduuccttiioonn ooff AArreeaa,,

EElloonnggaattiioonn,,

SSppeecciimmeenn

HHeeaatt TTrreeaattmmeenntt

Weld deposit by gas tungsten-arc process between 0.5-in. plates using INCONEL Filler Metal 718.

In accordance with AMS 5596.

All fractures in weld.

Parent Metal Annealed 1200 100.0 47.3 85.0 -

and Aged 1300 72.5 26.1 11.0 -

Annealed and Aged

1200 100.0 10.8 1.0 Weld

1300 72.5 9.4 1.0 Weld

Aged

1200 100.0 16.4 1.0 Weld

1300 72.5 15.8 2.0 Weld

TTaabbllee 4444

- Rupture Strength of Butt Joints in Annealed Sheet

SSttrreessss,,

kkssii

LLooccaattiioonn ooff FFrraaccttuurree

EElloonnggaattiioonn,,

LLiiffee,,

hhrr

TTrreeaattmmeenntt ooff WWeelldd TTeesstt TTeemmppeerraattuurree,, °°FF

0.060-in. sheet, welded with INCONEL FIller Metal 718. Parent metal and weld heat-treated in accordance with AMS 5596. Welds ground flush.

0.51 - - - -

0.76 161 178 16 41

1.01 150 176 15 38

1.51 - - - -

0.51 227 243 11 48

0.76 223 234 11 47

1.01 222 237 11 47

1.51 229 244 11 46

0.51 168 211 20 42

0.76 165 208 21 42

1.01 165 212 20 42

1.51 - - - -

TTaabbllee 4466

- Cold Working and Age Hardening

TTeennssiillee SSttrreennggtthh,,

kkssii

HHaarrddnneessss,,

RRcc

EElloonnggaattiioonn,,

DDiiaammeetteerr,,

iinn

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),, kkssii

As Cold Drawn

CCoolldd DDrraawwnn aanndd AAggeedd ((11332255°°FF//88 hhrr,, FF..CC.. ttoo 11115500°°FF,, hhoolldd aatt 11115500°°FF ffoorr ttoottaall aaggiinngg ttiimmee ooff 1188 hhrr))

CCoolldd DDrraawwnn,, SSoolluuttiioonn AAnnnneeaalleedd aanndd AAggeedd

((11775500°°FF//11 hhrr,, AA..CC.. tthheenn 11332255°°FF//88 hhrr FF..CC.. ttoo 11115500°°FF,, hhoolldd aatt 11115500°°FF ffoorr ttoottaall aaggiinngg ttiimmee ooff 1188 hhrr..))

Average of minumum five samples from five different heats.

IINNCCOONNEELL

®®

aallllooyy 771188

HHeeaattiinngg aanndd PPiicckklliinngg

When INCONEL alloy 718 is heated care must be taken to

maintain both the furnace and the material being heated at

correct temperatures.

Fuels used for heating must be extremely low in sulfur.

The alloy must be absolutely clean and free from all oil,

paint, grease, and shop soil when charged into the furnace.

The furnace atmosphere for forging or open annealing

should be slightly reducing, containing at least 2% carbon

monoxide. A slight positive pressure should be maintained

in the furnace to prevent air infiltration.

When alloy 718 is heated in a reducing atmosphere, a

thin, adherent green-black film of oxide will be left on the

surface of the material. In oxidizing atmospheres, a heavy

black scale is produced that is very difficult to remove.

Every precaution should be taken in heating so that only the

green-black film is formed.

WWOORRKKIINNGG IINNSSTTRRUUCCTTIIOONNSS

MMEETTAALLLLOOGGRRAAPPHHYY

INCONEL alloy 718 is an age-hardenable austenitic

material. Strength is largely dependent on the precipitation

of a gamma prime phase during heat treatment.

A major part of the development effort with this alloy

was concerned with establishment of the proper heat

treatments for producing optimum properties. These heat

treatments and the applications for which they are intended

are described in the section, Mechanical Properties.

The microstructure of alloy 718, especially with regard

to the effects of heat treatment, has been extensively studied

and reported. The literature should be consulted for detailed

discussions on the various phases developed by various heat

treatments and other metallurgical investigations.

CCOORRRROOSSIIOONN RREESSIISSTTAANNCCEE

INCONEL alloy 718 has excellent corrosion resistance to

many media. This resistance, which is similar to that of

other nickel-chromium alloys, is a function of its

composition. Nickel contributes to corrosion resistance in

many inorganic and organic, other than strongly oxidizing,

compounds throughout wide ranges of acidity and alkalinity.

It also is useful in combating chloride-ion stress-corrosion

cracking. Chromium imparts an ability to withstand attack

by oxidizing media and sulfur compounds. Molybdenum is

known to contribute to resistance to pitting in many media.

TTaabbllee 4488

- Effect of Hot-Forming Temperature on Rupture Properties

(1200°F, 100 ksi)

HHoott--FFoorrmmiinngg

TTeemmppeerraattuurree,, °°FF

AASSTTMM GGrraaiinn SSiizzee

LLiiffee,,

hhrr

EElloonnggaattiioonn,,

RReedduuccttiioonn ooff

AArreeaa,, %%

HHaarrddnneessss,,

HHeeaatt

TTrreeaattmmeenntt

NNoottcchh BBaarr

LLiiffee

hhrr

2050 A 20% 0.5, 30% 4.5, 40% 6.5, 10% 9 193.5 3 6.5 45 16.2

B 100% 1.5 209.5 4 8.5 46 16.5

1950 A 70% 8, 30% 3 274.5 7 9.0 45 55.1

B 60% 3, 30% 8, 10% 7 291.4 8 10.0 45 56.7

1850 A 95% 4.5, 5% 9 193.3 11 16.0 46 123.9

B 35% 4.5, 60% 9, 5% 7 231.6 10 13.0 46 99.2

1750 A 20% 6, 20% 7, 60% 10 121.3 13 22.0 46 131.4

B 40% 7, 55% 9, 5% 5 248.3 14 16.0 46 179.6

1650 A 100% 9.5 48.0 33 53.5 46 426.2

B 100% 9.5 124.3 28 43.5 46 426.1

SSmmooootthh BBaarr

Hot-finished, 25% reduction, one pass.

A--1750°F/1 hr, A.C., + 1325°F/8 hr, F.C. 100°F/hr to 1150°F, hold at 1150°F/8 hr, A.C.

B--1800°F/1 hr, A.C., + 1325°F/8 hr, F.C. 100°F/hr to 1150°F, hold at 1150°F/8 hr, A.C.

, 3.5 to 4.0; root diameter, 0.252-in.

Test discontinued.

IINNCCOONNEELL

®®

aallllooyy 771188

HHoott FFoorrmmiinngg

Because of its strength, INCONEL alloy 718 is more

resistant than most materials to deformation during hot

forming. Its relative resistance is shown by pressures

developed in the roll gap at 20% reduction (Table 47). It is

readily hot-worked if sufficiently powerful equipment is

used.

Hot forming is performed in the 1650°-2050°F

temperature range. In the last operation, the metal should be

worked uniformly with a gradually decreasing temperature,

finishing with some light reduction in the 1650°-1750°F

range. This procedure is necessary to ensure notch ductility

in stress-rupture applications when material has been

annealed and aged. (See below). In heating for hot working,

the material should be brought up to temperature, allowed to

soak a short time to ensure uniformity, and withdrawn.

To avoid duplex grain structure INCONEL alloy 718

should be given uniform reductions. Final reductions of 20%

minimum should be used for open-die work and 10%

minimum for closed-die work. Parts should generally be air-

cooled from the hot-working temperature rather than water-

quenched.

Care should be taken to avoid overheating the metal by

heat buildup due to working. Also, the piece should be

reheated when any portion has cooled below 1650°F.

Preheating tools and dies to 500°F is recommended. Any

TTaabbllee 4477

- Pressure, ksi, Developed in Roll Gap at 20% Reduction

11880000 2200000011990000

MMaatteerriiaall

22110000

Mild Steel (1020) 22.4 18.3 14.3 10.3

Type 302 Stainless Steel 27.8 24.3 21.4 18.0

INCONEL alloy 600 40.8 34.6 28.3 22.3

INCONEL alloy X-750 48.6 43.3 38.4 33.3

INCONEL alloy 718 63.3 55.8 48.3 41.0

PPrreessssuurree,, kkssii

HHoott--FFoorrmmiinngg TTeemmppeerraattuurree,, °°FF

ruptures appearing on the surface of the workpiece must be

removed at once.

Data shown in Table 48 show the importance of a

1650°F-1750°F finish-forging temperature for achievement

of notch ductility in large forgings in stress-rupture

applications. In these tests, 0.75-in. square forged bar was

cut into 12-in. lengths, heated to the rolling temperatures

shown in Table 48, and given 25% reduction in one pass.

Following annealing and aging, specimens were rupture-

tested at 1200°F and 100 ksi. Success in achieving notch-

rupture ductility with forgings of alloy 718 through this type

of procedure has also been reported by others.

IINNCCOONNEELL

®®

aallllooyy 771188

0 117.0 44.0 60.0 87 Rb - - -

5.9 115.0 68.2 45.0 19 161.0 103.0 38.0

18.5 145.0 116.5 25.0 33 189.0 153.0 24.0

27.9 159.5 134.0 10.5 36 204.0 169.0 15.0

48.3 191.0 165.0 7.0 40 231.0 204.0 15.0

0 187.0 172.5 19.5 44 248.0 188.5 26.0

5.9 203.0 175.5 22.0 45 255.0 211.0 13.0

18.5 217.0 201.0 16.0 47 270.0 235.0 12.5

48.3 244.0 232.5 4.0 49 289.0 269.0 2.5

CCoolldd FFoorrmmiinngg

INCONEL alloy 718 can be cold-formed by standard

procedures used for steel and stainless steel. Figure 16 shows

its rate of work hardening in comparison with other

materials.

The effect of cold reduction on the tensile properties of

sheet in the cold-rolled and cold-rolled and aged conditions

is shown in Table 49.

BBeennddiinngg

A guide to the minimum bend diameters of hot-rolled and

annealed plate and annealed sheet and strip is given in Table

50. In the determination of those diameters a sample is

judged to have passed the 180°-bend test if its surface

shows no ductile fracturing. Because of the effect of various

surface conditions and heat treatments on bendability, the

bends cannot be guaranteed. Many of the materials can

nevertheless be bent in stages to tighter bends than those that

are suggested in Table 50, provided that the initial bend is

not severe.

TTaabbllee 4499

- Effect of Cold Reduction on Properties of Sheet

CCoolldd RReedduuccttiioonn,,

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),,

kkssii

HHaarrddnneessss,,

RRcc

TTeennssiillee

SSttrreennggtthh,,

kkssii

EEllo

onnggaattiioonn,,

EElloonnggaattiioonn,,

YYiieelldd SSttrreennggtthh

((00..22%% OOffffsseett)),,

kkssii

TTeennssiillee

SSttrreennggtthh,,

kkssii

TTeessttss aatt RRoooomm TTeemmppe

erraattuurree

TTeessttss aatt --332200°°FF

Aged 1325°F/8 hr, F.C. 100°F/1 hr to 1150°F (Held for Total Aging Time of 18 hr, A.C.) after Cold Rolling

TTaabbllee 5500

- Minimum Bend Diameters for Annealed Sheet and Strip

and Hot-Rolled and Annealed Plate in 180° Bend

AAllllooyy

MMiinniimmuumm

DDiiaammeetteerr

mmmmiinn..

TThhiicckknneessss ((TT))

Sheet and Strip Sheet and Strip

INCONEL alloy 718

0.012-0.049 0.30-1.24 1T

0.050-0.250 1.27-6.35 2T

Bend tests were performed according to ASTM Standard Method E 290-77

with a guided-bed jig as described in ASTM Standard Method E 190-64

(Reapproved 1976).

Sheared edges of samples of INCONEL alloy 718 were ground or

machined.

MMaacchhiinniinngg

INCONEL alloy 718 can be readily machined, but its high

strength and work-hardening characteristics must be

considered in the selection and use of proper tool materials

and design, operating speeds, and coolants.

When machined in the age-hardened condition the alloy

will have a slightly better finish; chip action on chipbreaker

tools will be better. The use of annealed material, however,

provides easier machining and longer tool life.

500

706050403020100

100

200

300

400

INCONEL alloy 625

Aluminum

Copper

Mild Steel

Nickel 200

INCONEL alloy 400

INCONEL alloy 600

INCONEL alloy X-750

Type 304 Stainless Steel

INCONEL alloy 718

Cold Reduction, %

Vickers Hardness No.

FFiigguurree 1166..

Effect of cold work on hardness.

SSuuppeerr--PPllaassttiicc FFoorrmmiinngg

A special grade of alloy 718 that is specifically designed for

the super-plastic forming process is manufactured by

Special Metals. This alloy, designated INCONEL alloy

718SPF, is available as annealed sheet in thicknesses from

0.02 to 0.08 inches (0.5 to 2.0 mm) in widths up to 36 inches

(914 mm). The specification SAE AMS 5950 was developed

to define the requirements for the alloy. Complete

information describing the properties of alloy 718SPF and

how it is formed is available in the technical bulletin for the

alloy on the website www.specialmetals.com.

IINNCCOONNEELL

®®

aallllooyy 771188

AAnnnneeaalliinngg aanndd AAggee HHaarrddeenniinngg

For most applications, INCONEL alloy 718 receives one of

the following treatments:

Anneal at 1700°-1850°F, A.C. and age at

1325°F/8 hr, F.C. to 1150°F, hold at 1150°F for total

aging time of 18 hr, or

Anneal at 1900°-1950°F, A.C. and age at

1400°F/10 hr, F.C. to 1200°F, hold at 1200°F for total

aging time of 20 hr.

Rate of furnace cooling during aging is not critical, but

a rate of 100°F/hr is sometimes specified. Recommended

total times should be observed. Properties of material

receiving these heat treatments are shown in the section,

Mechanical Properties.

The effect of annealing for 30 minutes at various

temperatures on the grain size of sheet is shown in Figure 17.

Aging response of niobium-aluminum-titanium-

hardened INCONEL alloy 718 is rather slow in comparison

with that of aluminum-titanium-hardened alloys. Thus, in

most sizes, the alloy can be heated and cooled through the

aging temperature range at normal speeds yet retain softness

and ductility.

Figure 18 shows the effect of aging time and

temperature on the hardness of annealed sheet. Virtually no

hardening occurs during the first 2-3 minutes of exposure.

This is ample time to permit air cooling after welding or

annealing. An aluminum-titanium-hardened alloy having

sufficient hardener content to approach the strength level of

INCONEL alloy 718 would develop almost full hardness in

the same period of time.

1950

185017501650

Cold Work

Shown

On Curves

28%

48%

18.5%

Annealing Temperature, °F/30 min.

Average Grain Size, ASTM No.

FFiigguurree 1177..

Effect of annealing temperature on grain size of sheet.

AAVVAAIILLAABBLLEE PPRROODDUUCCTTSS AANNDD

SSPPEECCIIFFIICCAATTIIOONNSS

INCONEL alloy 718 is designated at UNS N07718, UNS

N07719, and Werkstoff Nr. 2.4668. It is listed in NACE MR-

01-75 for oil and gas service. Alloy 718 is available as pipe,

tube, sheet, strip, plate, round bar, flat bar, forging stock,

hexagon, wire and extruded section.

Rod, Bar, Wire and Forging Stock - ASTM B 637, ASME

SB 637, SAE AMS 5662, SAE AMS 5663, SAE AMS

5664, SAE AMS 5832, SAE AMS 5914, SAE AMS 5962,

ASME Code Case 1993, ASME Code Case 2206, ASME

Code Case 2222, AECMA PrEN 2404, AECMA PrEN

2405, AECMA PrEN 2952, AECMA PrEN 2961, AECMA

PrEN 3219, AECMA PrEN 3666, ISO 9723, ISO 9724, ISO

9725, DIN 17752-17754

Plate, Sheet and Strip - ASTM B 670, ASTM B 906,

ASME SB 670, ASME SB 906, SAE AMS 5596, SAE

AMS 5597, SAE AMS 5950, AECMA PrEN 2407,

AECMA PrEN 2408, ISO 6208, DIN 17750

0.1

1800

100501051.00.50.05

1700

1600

1500

1400

1300

1200

1100

Aging Time, hr

Aging Temperature, °F

35 Rc

39-40 Rc

38 Rc

30 Rc

25 Rc

20 Rc

12 Rc

10 Rc

FFiigguurree 1188..

Effect of aging conditions on hardness of annealed

sheet. (Initial hardness, as-annealed condition, Rc 4.

Pipe and Tube - SAE AMS 5589, SAE AMS 5590, ASME

Code Case N-253, DIN 17751

Welding Product - INCONEL Filler Metal 718 - AWS

5.14 / ERNiFeCr-2

Others - ASME Code Case N-62, ASME Code Case N-

208, DIN 17744

wwwwww..ssppeecciiaallmmeettaallss..ccoomm

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Phone +91 (0) 80 2666 9159

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Phone +31 (0) 10 451 44 55

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Special Metals Pacific Pte. Ltd.

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Phone +86 21 3229 0011

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Special Metals Pacific Pte. Ltd.

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Phone +86 10 8766 7100

Fax +86 10 8766 7101

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#12 Fengcheng Er Road

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Development Zone

Xi’an 7100016 China

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#27-04 Clifford Centre

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Phone +65 6532 3823

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Billet & bar products

4317 Middle Settlement Road

New Hartford, NY 13413-5392

Phone +1 (315) 798-2900

+1 (800) 334-8351

Fax +1 (315)798-2016

Shape Memory Alloys

4317 Middle Settlement Road

New Hartford, NY 13413-5392

Phone +1 (315) 798-2939

Fax +1 (315) 798-6860

United Kingdom

Special Metals Wiggin Ltd.

Holmer Road

Hereford HR4 9SL

Phone +44 (0) 1432 382200

Fax +44 (0) 1432 264030

Special Metals Wire Products

Holmer Road

Hereford HR4 9SL

Phone +44 (0) 1432 382556

Fax +44 (0) 1432 352984

Germany

Special Metals Deutschland Ltd.

Postfach 20 04 09

40102 Düsseldorf

Phone +49 (0) 211 38 63 40

Fax +49 (0) 211 37 98 64

Hong Kong

Special Metals Pacific Pte. Ltd.

Unit A, 17th Floor, On Hing Bldg

1 On Hing Terrace

Central, Hong Kong

Phone +852 2439 9336

Fax +852 2530 4511