Nimonic Alloy 105

7/30/2019 Nimonic Alloy 105

1/24

NIMONIC alloy 105 (W. Nr. 2.4634) is a wroughtnickel-cobalt-chromium-base alloy strengthened byadditions of molybdenum, aluminum and titanium. Ithas been developed for service up to 950C, and com-

bines the high strength of the age-hardening nickel-basealloys with good creep resistance.

NIMONIC alloy 105 is produced by high frequencymelting in air followed by casting in air, or, for morecritical applications the alloy is produced by vacuummelting and electroslag refining.

The alloy is used for turbine blades, discs, forgings,ring sections, bolts and fasteners.

Heat Treatment

The heat treatment recommended is dependent on theintended service condition.

Two heat treatments are recommended as follows:

(a) 4 h/1150C/AC+16 h/1050-1065C/AC+16h/850C/AC

(b) 4 h/1125C/AC+16 h/850/AC

In general, heat treatment (a) is intended for optimumlong-term creep strength and ductility at operating tem-

peratures in the range 850-950C. Heat-treatment (b)may be used where long-term properties are not of para-mount importance and tensile strength, elongation andimpact strength may be enhanced for operating temper-atures up to 700C. When applying heat-treatment (b)it is essential to ensure that cooling from 1125C takes

place freely and is not delayed due to close packing ofcomponents.

Examples of the use of these heat treatments are asfollows:

(a) turbine blades, discs, forgings and ring sections,all of which may be produced from as-extruded,as-forged or subsequently cold worked startingstock

(b) bolts and fasteners for which extruded and cold

worked bar or section is recommended as startingstock.

*Reference to the balance of an alloys composition does not guaran-tee this is exclusively of the element mentioned, but that it predomi-

nates and others are present only in minimal quantities.

Carbon.........................................................................0.17 max

Silicon............................................................................1.0 max

Copper...........................................................................0.2 max

Iron.................................................................................1.0 max

Manganese....................................................................1.0 max

Chromium....................................................................14.0-15.7

Titanium...........................................................................0.9-1.5

Aluminum.........................................................................4.5-4.9

Cobalt..........................................................................18.0-22.0

Molybdenum...................................................................4.5-5.5

Lead.........................................................................0.0015 max

Sulfur..........................................................................0.010 max

Boron.......................................................................0.003-0.010

Zirconium.....................................................................0.15 max

Nickel............................................................................Balance*

Composition, %

N

IMONIC

alloy10

5

www.specialmetals.co

The composition stated in BS HR 3 is as follows:


2/24

Physical Properties

Density 8.01 g/cm0.289 lb/in

The exact density is dependent on compositional variationwithin the release specification.

Melting Range Liquidus temperature 1345CSolidus temperature 1290C

The liquidus temperature was determined by inverse cool-ing techniques and the solidus temperature obtained by met-allographic examination. The accuracy of determination was 5C for the liquidus temperature and +0, -10C for thesolidus temperature.

2

Table 1 - Specific Heat

Table 2 - Thermal Conductivity

Temperature range, C

20-100

20-200

20-30020-400

20-500

20-600

20-700

20-800

20-900

20-1000

10-6/ C

12.2

12.8

13.1

13.4

13.7

14.0

14.5

15.3

16.5

18.0

Table 3 - Mean Coefficient of Linear Thermal Expansion

Extruded section subsequently cold rolled given heat t reatment

4 h/1150C/AC + 16 h/1050C/AC + 16 h/850C/AC.These data are average and subject to approximately 5% variation.

Temperature C

20

100

200

300

400

500

600

700

800

900

1000

Relative Resistance

1.000

1.021

1.044

1.066

1.089

1.107

1.155

1.117

1.106

1.088

1.055

Table 4 - Electrical Properties

Hot rolled bar subsequently cold drawn (wire) and given heat treatment 15

min/1150C/AC + 1 h/1050C/AC + 16 h/850C/AC.

Electrical resistivity at 20C = 131 microhm cm

Table 5 - Magnetic Properties

Magnetic permeability from

0.02T-0.2T 1.000715

Extruded bar subsequently forged and given heat treatment 4 h/1150C/AC

+ 16 h/1050C/AC + 16 h/850C/AC.

NIMONIC alloy 105

Temperature ,C

20

100

200

300

400

500

600

700

800

900

1000

Thermal Conductivity, W/m C

10.89

12.10

13.57

14.99

16.33

17.67

18.63

20.56

22.23

24.03

26.21

These values have been calculatedfrom electrical resistance measurements

on a single 3-stage heat-treated specimen using the modified Wiedemann-

Franz equations.

Temperature, C

20

100

200

300

400

500

600

700

800

900

1000

Specific Heat, J/kgC

419

461

502

502

544

544

586

628

628

670

670


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3

Temperature

C

20

100

200

300

400

500

600

700

800

900

1000

Extruded bar

GPa

188

184

179

174

168

161

154

147

139

129

110

Extruded bar,

subsequently

forged

GPa

223

219

212

206

200

193

186

178

168

155

138

Extruded bar,

subsequently

cold rolled

GPa

220

216

210

204

198

191

185

177

168

154

137

Table 6 - Dynamic Youngs Modulus

Heat treatment 4 h/1150C/AC + 16 h/1050C/AC + 16 h/850C/AC.

Tensile Properties: Extruded Bar

The data given in Table 7 and presented graphically in Figures 1 and 2 represent the tensile properties for extruded bar afterthe 3-stage heat treatment.

Strain rate 0.005/min to proof stress (at room temperature), 0.002/min to proof stress (at elevated temperatures) and 0.1/minthereafter.

Temperature, C

20

100

200

300

400

500

600

700

800

900

1000

1100

0.1% proof stress

MPa

751

739

712

712

718

711

694

706

647

373

144

26

0.2% proof stress

MPa

776

762

735

735

743

740

720

732

677

400

152

29

Tensile strength

MPa

1140

1123

1084

1091

1101

1064

1038

1018

813

496

175

51

Elongation on 5.65

So, %

22

20

21

20

24

23

25

28

25

30

42

172

Reduction of area,

%

31

31

38

30

39

37

38

36

37

47

73

99

Table 7 - Heat treatment 4 h/1150C/AC + 16 h/1050-1065C/AC + 16 h/850C/AC

Average results of tests on 15 casts.

NIMONIC alloy 105


4/24

0

20

40

60

80

100

Temperature, F

200 1000800600400 1200 1400 1600 1800

20

40

60

80

0

Stress,

MPa

Reducti o

nofAr e

a,%

200 100080060040000

800

400

1200

1600

20

40

60

80

100

0

120

140

160

180

200220

Temperature, C

0.2% Proof Stress

R. of A.

Figure 1. Heat treatment 4h/1150C/AC + 16h/1050-1065C/AC + 16h/850C/AC

98% confidence region calculated on 15 casts

ton/in 10 lb/in

Temperature, F

200 1000800600400 1200 1400 1600 1800

20

40

60

80

0

Stress,

MPa

Elongati o

n,%

200 10008006004000

0

800

400

1200

1600

Temperature, C



Tensile Strength

Elongation

4

NIMONIC alloy 105

0

20

40

60

80

100

20

40

60

80

100

0

120

140

160

180

200

220

ton/in 10 lb/in


5/24

Tensile Properties: Extruded Bar Subsequently Forged

The data given in Table 8 and presented graphically in Figures 3 and 4 represent the tensile properties for extruded bar sub-sequently forged after the 3-stage heat treatment.


Temperature, C

20

100

200

300

400

500

600

700

800

900

1000

1100

0.1% proof stress

MPa

796

760

745

739

732

748

735

739

680

390

152

28

0.2% proof stress

MPa

827

793

774

766

763

782

769

768

714

411

156

31

Tensile strength

MPa

1180

1185

1188

1162

1126

1148

1111

1075

836

491

189

56

Elongation on 5.65

So, %

16

21

24

20

23

23

22

26

24

28

43

132

Reduction of area,

%

16

24

34

24

33

31

32

33

34

38

60

99



5

NIMONIC alloy 105

200 1000800600400 1200 1400 1600 1800

20

40

60

80

0

Reduct io

nofA

rea,%

200 100080060040000

800

400

1200

1600

Temperature, C

0.2% Proof Stress

R. of A.



Temperature, F

0

20

40

60

80

100

20

40

60

80

100

0

120

140

160

180

200

220

ton/in 10 lb/in

Stress,

MPa


6/24

Temperature, C

20

100

200

300

400

500

600

700

800

900

1000

0.1% proof stress

MPa

795

780

755

744

744

752

743

744

681

392

168

0.2% proof stress

MPa

826

811

785

772

783

785

775

778

718

420

176

Tensile strength

MPa

1246

1220

1234

1239

1226

1195

1177

1092

856

533

221

Elongation on 5.55

So, %

25

24

26

26

27

27

25

31

25

31

48

Reduction of area,

%

29

30

31

31

31

31

31

31

31

39

61



Temperature, F

200 1000800600400 1200 1400 1600 1800

20

40

60

80

0

Stress,

MPa

Elong

ation,%

200 100080060040000

800

400

1200

1600

Temperature, C



Tensile Strength

Elongation

Tensile Properties: Extruded Section Subsequently Cold Rolled

The data given in Table 9 and presented graphically in Figures 5 and 6 represent the tensile properties for extruded sectionsubsequently cold rolled after the 3-stage heat treatment.


6

NIMONIC alloy 105

0

20

40

60

80

100

20

40

60

80

100

0

120

140

160

180

200

220

ton/in 10 lb/in


7/24

7

NIMONIC alloy 105

Temperature, F

200 1000800600400 1200 1400 1600 1800

20

40

60

80

0

Stress,

MPa

Reductio

nofAr e

a,%

200 10008006004000

0

800

400

1200

1600

Temperature, C

0.2% Proof Stress

R. of A.



Temperature, F

200 1000800600400 1200 1400 1600 1800

20

40

60

80

0

Stress,

MPa

Elongati o

n,%

200 10008006004000

0

800

400

1200

1600

Temperature, C



Tensile Strength

Elongation

0

20

40

60

80

100

20

40

60

80

100

0

120

140

160

180

200

220

ton/in 10 lb/in

0

20

40

60

80

100

20

40

60

80

100

0

120

140

160

180

200

220

ton/in 10 lb/in


8/24

Temperature, C

20

100

200

300

400

500

600

700

800

900

1000

0.1% proof stress

MPa

791

749

731

732

740

740

726

723

678

407

155

0.2% proof stress

MPa

811

777

757

752

760

771

759

752

706

430

161

Tensile strength

MPa

1220

1177

1186

1183

1143

1140

1106

1060

817

496

210

Elongation on 5.55

So, %

25

24

27

25

28

28

26

30

27

27

46

Reduction of area,

%

35

39

34

36

35

35

35

33

35

35

59

Table 10 - Heat treatment 4 h/1125C/AC + 16 h/850C/AC

Test on 1 cast.

Tensile Properties: Extruded Bar Subsequently Cold Stretched

The data given in Table 10 and presented graphically in Figure 7 represent the tensile properties for extruded bar subsequentlycold stretched after the 2-stage heat treatment.


Temperature, F

200 1000800600400 1200 1400 1600 1800

20

40

60

80

0

Stress,

MPa

Elo

ngation

andRe

duction

ofArea

,%

200 10008006004000

0

800

400

1200

1600

Temperature, C

0.2% Proof Stress

R. of A.

Figure 7. Heat treatment 4h/1125C/AC + 16h/850C/AC

Elongation

Tensile Strength

8

NIMONIC alloy 105

0

20

40

60

80

100

20

40

60

80

100

0

120

140

160

180

200

220

ton/in 10 lb/in


9/24

9

NIMONIC alloy 105

Creep Properties

The creep characteristics for NIMONIC alloy 105 have been determined for bar after the 3-stage heat treatment.Creep-rupture properties for extruded bar subsequently forged are shown in Table 11 and Figures 8 and 9, by Larson-

Miller presentation and Graham and Walles technique.Creep-rupture properties for extruded bar subsequently cold stretched are shown in Table 12 and Figures 10 and 11.Derived total plastic strain data were created from test specimens 9.1 - 11.7 mm diameter x 76 mm gauge length (0.357 -

0.461 in diameter x 3 in gauge length) and are shown in Table 13.

Creep-Rupture Properties: Extruded Bar Subsequently Forged

The data given in Table 11 and presented graphically in Figures 8 and 9 represent the average results of 15 casts of extrudedbar subsequently forged.


Test

temperature

C

750 GW

LM

815 GW

LM

870 GWLM

940 GW

LM

980 GW

LM

Stress toproducerupture in

100 h

MPa456

448

324

324

208208

108

108

68

68

300 h

MPa

394

417

278

270

178173

82

85

51

51

1000 h

MPa

340

363

232

224

131134

(60)

(62)

31

32

3000 h

MPa

270

317

178

185

99102

(36)

(39)

(17)

(19)

10 000 h

MPa

(201)

(263)

(130)

(144)

(54)(77)

(20)

(25)

30 000 h

MPa

(154)

(224)

(77)

(116)

(31)(54)

100 000 h

MPa

(83)

(178)

(42)

(85)

(17)(39)

Elongation

at fracture

on 5.65

So, %

12-18

8-21

7-17

10-21

12-22

GW=Graham and Walles analysis. LM=Larson-Miller analysis. ( ) =Outside range of determination.


10/24

10

NIMONIC alloy 105

10090807060

50

40

3025

20

15

109876

5

4

3

2

1.5

1

20

100

200

300

400

500

600

700

800

900

1000

1100

1200

100

200

300

400

500600

700

800

900

1000

1100

1200

1300

1400

1500

1600

1700

1800

1900

2000

2100

2200

2300

F C

10-1 100 101 102 103 104 105

Time, hours

Figure 8 - Larson-Miller Parameter, T(20 + log t) x10-3; T in K, t in hours; Heat treatment 4 h/1150C/AC + 16 h/1050-1065C/AC +

16 h/850C/AC

MPax101

5 10 15 20 25 30 35


1MPa x 101 = 107 N/m2 ; 1 N/mm2 (1 MN/m2) = 0.1 hbar = 1.02 kgf/mm2 = 0.0647 tonf/in2


11/24

11

NIMONIC alloy 105


3

4

5

6

7

8

9

10

12

14

16

18

20

22

24

26

28

30

35

40

45

50

55

60

65

70

80

90

100

110

120

130

140

1.5

2

2.5

3

4

5

6

7

8

9

10

12

14

16

18

20

2224

26

28

30

35

40

45

50

55

60

20

30

40

50

60

70

80

90

100

200

300

400

500

600

700

800

900

1000

10 100 1000 10 000 100 000

Time, hours

Stress,

MPa

750C

815C

870C

940C

980C

ton/in 10 lb/in

Figure 9. Heat-treatment 4 h/1150C/AC + 16h/1050-1065C/AC + 16 h/850C/AC


12/24

Creep-Rupture Properties: Extruded Bar Subsequently Cold Stretched

The data given in Table 12 and presented graphically in Figure 10 represent the creep-rupture properties of extruded bar sub-sequently cold stretched.


Test temperature,

C

550

600

650

700

Stress to produce

rupture in

100h 300h 1000h

MPa MPa MPa

1050 1020 989

958 911 865

819 742 680

634 572 495

Elongation at

fracture on 5.65

So, %

18-21

8-17

9-13

13-19

Test on 1 cast.

12

NIMONIC alloy 105


13/24

13

NIMONIC alloy 105

1009080706050

40

3025

20

15

109876

5

4

3

2

1.5

1

20

100

200

300

400

500

600

700

800

900

1000

1100

1200

2300

F C

10-1 100 101 102 103 104 105

Time, hours

Figure 10 - Larson-Miller Parameter, T(20 + log t) x10 -3; T in K, t in hours.

Heat treatment 4 h/1125C/AC +16 h/850C/AC

MPax101

5 10 15 20 25 30 35


2200

2100

2000

1800

1900

1700

1600

1500

1400

1300

1200

1100

1000

900

800

700

600

500

400

300

200

100

1MPa x 101 = 107 N/m2

1 N/mm2 (1 MN/m2) = 0.1 hbar = 1.02 kgf/mm2 = 0.0647 tonf/in2


14/24

1400 1200 1000 800 600 400 200

10 000

1000

100

10

Stress, MPa

Life

torupture,

hours

Figure 11. Heat-treatment 4 h/1125C/AC + 16 h/850C/AC

}

550C

600C

650C

700C

Notched

550C

600C

650C

700C

14

NIMONIC alloy 105


Plain


15/24

15

NIMONIC alloy 105

Total Plastic Strain Data

This data has been determined on as extruded bar and extruded section subsequently cold worked.

Test

temperature

C

650

750

815

870

980

Strain %

0.1

0.2

0.5

rupture

0.1

0.2

0.5

rupture

0.1

0.2

0.5

rupture

0.1

0.2

0.5

rupture

0.1

0.2

0.5

rupture

100 h

MPa

599

625

667

772

314

358

391

479

190

241

309

133

156

170

193

22

28

36

60

300 h

MPa

541

568

602

703

275

317

352

427

139

190

229

263

105

128

142

164

17

26

43

1000 h

MPa

479

510

539

618

233

275

310

368

97

134

181

218

76

97

111

130

15

31

3000 h

MPa

422

456

486

549

196

238

273

314

74

100

136

178

54

71

83

99

22

10 000 h

MPa

(358)

394

428

471

(154)

196

232

263

57

74

93

135

37

46

54

65

12

30 000 h

MPa

(375)

410

(159)

(195)

(209)

49

57

99

34

(37)

40

Stress to give total plastic strain in

( ) = Outside range of determination Tests on 3 casts.


16/24

Fatigue Properties: Extruded Section Subsequently Cold Rolled

Fatigue properties for extruded section subsequently coldrolled given the heat treatment 4h/1150C/AC + 4h/1080C/AC + 8 h/850C/AC are given in Table 14.

Gerber Diagrams

Figures 12 to 17 illustrate the fatigue properties ofNIMONIC alloy 105 extruded section subsequently coldrolled (heat treatment 4 h/1150C/AC + 4 h/1080C/AC +8 h/850C/AC) at 20C, 400C, 650C, 750C, 870C and980C respectively, under conditions of uniaxial stressingwith varying mean stress. The abscissae represent the

mean stress and the ordinate fluctuating stress. Thus apoint on the horizontal axis represents the steady stresswhich will produce fracture in a specific time in a normalcreep rupture test. A point on the vertical axis indicates thefluctuating stress required to produce a pure fatigue failurein the same time at the particular testing frequency adopt-ed. The lines radiating from the origin correspond to stressconditions of the form P CP where P is the steady stressand C is a constant for any line. The full lines join pointscorresponding to lines of 50 and 500 hours for varyingstress conditions.

Test tempera-

ture

C

20

400

650

750

870

980

Stress

form

O P

P 2P

P P

P P

P P

O P

P P

P P

P P

P O

O P

P P

P P

P P

P O

O P

P P

P P

P P

P O

O P

P P

P P

P P

P O

O P

P P

P P

P P

P O

50 h

(3 x 107 cycles)

MPa

348

155

271

433

618

232

193

371

618

1004

271

240

417

711

834

263

232

417

502

502

240

201

240

240

240

170

84

84

84

84

500 h

(3 x 108 cycles)

MPa

248

116

209

356

556

232

193

371

618

1004

271

240

417

688

688

248

209

371

386

386

193

155

155

155

155

124

46

46

46

46

Stress for lives of

Table 14 - Heat treatment 4 h/1150C/AC + 4 h/1080C/AC + 8

h/850C/AC

16

NIMONIC alloy 105


17/24

17

NIMONIC alloy 105

0 100 200 300 400 500 600 700 800 900 1000 1100 1200

0 10 20 30 40 50 60 70

800

700

600

500

400

300

200

100

0

50

40

30

20

10

0

Mean tensile stress, ton/in

Mean tensile stress, MPa

Semi-rangeofalternatingstress,

MPa

Semi-rangeofalternatingstress,ton/in

Figure 12. Fatigue properties at room temperature.

Heat treatment 4 h/1150C/AC + 4 h/1080C/AC + 8 h/850C/AC

50 h, 3 x 107 Cycles

500 h, 3 x 108 Cycles

OP

P2P

PP

PP

PP

0 100 200 300 400 500 600 700 800 900 1000 1100 1200

0 10 20 30 40 50 60 70

800

700

600

500

400

300

200

100

0

50

40

30

20

10

0



Semi-rang

eofalternatingstress,

MPa

Semi-rangeofalternatings

tress,ton/in

Figure 13. Fatigue properties at 400C.



500 h, 3 x 108 Cycles

OP

PP

PP

PP

PO



18/24

0 100 200 300 400 500 600 700 800 900 1000

0 10 20 30 40 50 60

800

700

600

500

400

300

200

100

0

50

40

30

20

10

0



Semi-range

ofalternatingstress,

MPa

Semi-rangeofalternating

stress,ton/in




500 h, 3 x 108 Cycles

OP

PP

PP

PP

PO

0 100 200 300 400 500 600 700 800 900 1000

0 10 20 30 40 50 60

800

700

600

500

400

300

200

100

0

50

40

30

20

10

0



Semi-rang

eofalternatingstress,

MPa

Semi-rangeofalternatingst

ress,ton/in

Figure 15 . Fatigue properties at 750C.



500 h, 3 x 108 Cycles

OP

PP

PP

PP

PO


18

NIMONIC alloy 105


19/24

19

NIMONIC alloy 105

0 50 100 150 200 250

0 2 4 6 8 10 12 14250

200

150

100

50

0

14

12

10

8

6

4

2

0



Semi-rangeofalternatingstress,

MPa

Semi-rangeofalternatingstress,ton/in

500 h, 3 x 108

Cycles

50 h, 3 x 107

Cycles

OP

PP

PP

PP

PO

0 50 100 150 200 250

0 2 4 6 8 10 12 14250

200

150

100

50

0



Semi-

rangeofalternatingstress,

MPa

Semi-rangeofalternatin

gstress,ton/in


500 h, 3 x 108 CyclesOP

PP

PP

PP

PO

14

12

10

8

6

4

2

0







20/24

Stress Relaxation Properties

Stress relaxation data is given for extruded bar given the two recommended heat treatments. It should be noted that only verylimited data has been established, and that Tables 15 and 16 only give a general guide to the level of these properties.

Stress Relaxation Properties: Extruded Bar Subsequently Hot Rolled

Stress Relaxation Properties: Extruded Bar Subsequently Cold Stretched

Residual Stress at stated time in MPaTest Condition

Stress

MPa539

502

Temp.

C650

700

Final reading

Temp.

C

600

650

700

750

800

850

Stress

MPa

274

280

277

269

243

223

232

10 000

8000

14 000

17

201

4600

160

3

186

7400

310

9

170

10 500

600

20

155

1120

40

139

2100

74

10

124

4000

130

21

109

7200

250

38

93

450

70

77

810

140

62

1750

290

Time

h

10 000

8613

13 427

16 546

2014

698

Stress

MPa

232

231

161

99

60

33

Test condition Time (h) to reach indicated residual stress Final Reading

Table 15 - Heat treatment 4 h/1150C/AC + 16 h/1050C/AC + 16 h/850C/AC


100 h525

374

300 h501

325

1000 h445

283

3000 h382

249

Time

h3841

4104

Stress

MPa366

238

20

NIMONIC alloy 105

0.15% Initial Strain

0.30% Initial Strain


21/24

21

NIMONIC alloy 105

Impact Data:

Extruded Bar Subsequently Forged

The room temperature Charpy impact strength forNIMONIC alloy 105 extruded bar subsequently forgedand given the recommended heat treatment of 4h/1150C/AC + 16 h/1050C/AC + 16 h/850C/AC is ofthe order of 16 J.

Long-term embrittlement of this alloy has been inves-tigated by Charpy impact testing at room and elevatedtemperatures and the results of duplicate tests are given inTables 17 and 18 respectively.

Charpy test specimen had square cross-section of 10

mm, test area of 80 mm and V-notch angle of 45.

Impact Data:

Extruded Section SubsequentlyCold Rolled

The room temperature Charpy impact strength ofNIMONIC alloy 105 extruded section subsequently coldrolled and given the recommended heat treatment of 4h/1150C/AC + 16 h/1050C/AC + 16 h/850C/AC is ofthe order of 20 J.

Long-term embrittlement of this alloy has beeninvestigated by Charpy impact testing at room and ele-vated temperatures and the results of duplicate tests aregiven in Tables 19 and 20 respectively.

Charpy test specimen had square cross-section of 10

mm, test area of 80 mm and V-notch angle of 45.

Soaking

time,

h

30

100

300

1000

300010 000

700

J

11 : 11

8 : 11

8 : 8

9 : 11

8 : 511 : 8

750

J

9 : 8

11 : 12

14 : 15

12 : 14

14 : 1511 : 11

800

J

14 : 16

16 : 16

16 : 19

15 : 14

14 : 159 : 11

850

J

23 : 22

26 : 19

16 : 19

16 : 14

14 : 127 : 9

900

J

22 : 22

20 : 19

12 : 11

8 : 9

8 : 88 : 5

Soaking temperature, C

Table 17 - Room Temperature Impact Values

Soaking

time,

h

0

30

100

300

1000

3000

10 000

700

J

24 : 30

16 : 19

18 : 9

8 : 11

18 : 14

15 : 15

14 : 16

750

J

23 : 22

19 : 19

15 : 19

19 : 20

22 : 19

18 : 19

20 : 20

800

J

23 : 22

19 : 23

23 : 23

23 : 20

20 : 20

15 : 23

18 : 19

850

J

23 : 24

23 : 23

22 : 24

24 : 23

22 : 20

20 : 19

16 : 15

900

J

27 : 27

24 : 26

23 : 26

22 : 26

19 : 19

22 : 20

27 : 22

Soaking and test temperature, C

Table 18 - Elevated Temperature Impact Values

Soaking

time,

h

30

100

300

1000

300010 000

700

J

11 : 11

8 : 9

5 : 8

7 : 8

9 : 912 : 12

750

J

14 : 14

15 : 12

11

12 : 12

14 : 1215 : 14

800

J

14 : 19

18 : 15

14 : 16

19 : 16

14 : 1215 : 14

850

J

20 : 20

23

16 : 18

16 : 20

12 : 128 : 9

900

J

24 : 26

22 : 23

18 : 16

11 : 11

7 : 99 : 5



Soaking

time,

h

0

30

100

300

1000

3000

10 000

700

J

33 : 30

16 : 19

20 : 18

16 : 16

16 : 15

18 : 18

20 : 20

750

J

22 : 22

14 : 14

12 : 15

18 : 20

22 : 24

22 : 24

23 : 24

800

J

22 : 19

19 : 26

24 : 26

26 : 26

30 : 27

24 : 24

23 : 22

850

J

23 : 22

23 : 24

24 : 24

24 : 24

23 : 23

19 : 19

15 : 16

900

J

28 : 30

28 : 27

30 : 30

28 : 26

22 : 24

22 : 20

18 : 18

Soaking and test temperature, C



22/24

600C

1.6

2.3

2.1

700C

8.7

1.1

0.5

800C

15.0

0.6

0.6

1000C

0.6

2.1

Descaled weight loss (mg/cm) after

1000 hours at

Temperature

C

890

910

990

1010

1090

1110

Time to onset

of spalling (h)

at max cycletemperature of

C

>1000

>1000

600

300

150

75

Rate of

spalling

(mg/cm/h) atmax cycle

temperature of

C

0.150

0.408

0.946

1.170

Weight change

in 100 h

(mg/cm) atmax cycle

temperature of

C

+0.66

+1.05

-51.9

-229

-748

-955

Descaled weight loss (mg/cm) after 100 hours at

Soaking

time,h

100

300

1000

500

J

31

33

24

550

J

33

33

27

600

J

28

21

17

650

J

24

16

8



Soaking

time,

h

0

100300

1000

500

J

48

4545

44

550

J

43

4748

41

600

J

47

4437

29

650

J

47

4128

15



800C

0.11

900C

0.49

950C

0.99

1000C

1.43

1100C

6.41

Descaled weight loss (mg/cm) after 100 hours at

800C

900C

1.19

950C

1.59

1000C

1.61

1100C

13.3

Atmosphere

3% SO2-Argon

3% SO2-Air

3% SO2-5% O2-Argon

Impact Data:Extruded Bar Subsequently Cold

StretchedThe room temperature Charpy impact strength of

NIMONIC alloy 105 extruded bar subsequently coldstretched and given the heat treatment of 4h/1125C/AC+ 16h/850C/AC is of the order of 36 J.

Long-term embrittlement of this alloy has beeninvestigated by Charpy impact testing at room and ele-vated temperatures and the results of single tests aregiven in Tables 21 and 22 respectively.

Charpy test specimen had square cross-section of 10mm, test area of 80 mm and V-notch angle of 45.

Corrosion Resistance

22

NIMONIC alloy 105

Oxidation in Air

Continuous Heating

Intermittent Heating

(Cooling to room temperature every 24 hrs)

Cyclic Heating

(15 min in furnace, 5 min outside furnace)

Resistance to Atmospheres Containing SO2


23/24

23

NIMONIC alloy 105

Fabrication

Hot working

NIMONIC alloy 105 may be hot worked in the temperaturerange 1050-1200C.

Annealing

Interstage annealing of NIMONIC alloy 105 should be car-ried out at 1150C followed by air cooling of fluidized bedquenching. Water quenching is not recommended as severesurface cracking may result from thermal shock.

Machining

NIMONIC alloy 105 should be in the fully heat-treated con-

dition for all machining operations. The high hardnessrange, 320-385 HV, necessitates the use of tungsten carbidetipped tools. High speed steel shock-proof tools can be usedif the cut is of an intermittent nature.

Welding

Fusion welding of NIMONIC alloy 105 using conventionalprocesses such as T.I.G. or M.I.G. welding is not recom-mended as microfissuring can occur both in the weld andheat affected zones. Electron beam welding has been usedsuccessfully but the danger of microfissuring still exists andwelding trials should always be carried out before the

process is specified.

Similar difficulties can be expected with resistance spot,stitch or seam welding. Flash-butt welding is, however, quitesatisfactory and in regular use for the production of turbinerings.

High temperature brazing

High temperature brazing in vacuum, dry hydrogen or inertatmospheres is satisfactory for joining NIMONIC alloy105. However, the brazing cycle chosen should not involvetemperatures above the solution treatment temperature(1150C) as this could adversely affect the properties of thematerial.

Available Products and Specifications

NIMONIC alloy 105 is generally available in the following

forms, subject to minimum order quantities. Other forms aresubject to enquiry.

Bar and billet for forgingRod and bar for machiningExtruded section, rectangular or profiled, for

machining, rolling and welding to rings, etc.Extruded and cold worked section

NIMONIC alloy 105 is designated W. Nr. 2.4634 and is avail-able to the following specifications:

BS. HR3 billets, bars and forgingsAICMA Ni-P61-HT billets, bars and forgings

Swedish Defence Material Administration MH.14 forged barDIN designation NiCo20Cr15MoAlTi forged barAFNOR NCKD 20ATvAECMA PrEn 2179-2181

Units of stress

The primary units for property data are those of the SI sys-tem. The unit of stress is the Megapascal. Its relationshipwith other units is as follows:

1MPa = N/mm = 1 MN/m = 0.1 hbar = 0.102 kgf/mm =0.0647 tonf/in.

Publication SMC-081Copyright Special Metals Corporation, 2007 (Jan 07)

NIMONIC is a trademark of the Special Metals Corporationgroup 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 reli-

able, 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.


24/24

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Documents

Nimonic Alloy 105