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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:
7/30/2019 Nimonic Alloy 105
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
7/30/2019 Nimonic Alloy 105
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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
7/30/2019 Nimonic Alloy 105
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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
Figure 2. Heat treatment 4h/1150C/AC + 16h/1050-1065C/AC + 16h/850C/AC
98% confidence region calculated on 15 casts
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
7/30/2019 Nimonic Alloy 105
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.
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
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
Table 8 - Heat treatment 4 h/1150C/AC + 16 h/1050-1065C/AC + 16 h/850C/AC
Average results of tests on 15 casts.
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.
Figure 3. Heat treatment 4h/1150C/AC + 16h/1050-1065C/AC + 16h/850C/AC
98% confidence region calculated on 15 casts
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
7/30/2019 Nimonic Alloy 105
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
Table 9 - Heat treatment 4 h/1150C/AC + 16 h/1050-1065C/AC + 16 h/850C/AC
Average results of tests on 15 casts.
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
Figure 4. Heat treatment 4h/1150C/AC + 16h/1050-1065C/AC + 16h/850C/AC
98% confidence region calculated on 15 casts
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.
Strain rate 0.005/min to proof stress (at room temperature), 0.002/min to proof stress (at elevated temperatures) and 0.1/minthereafter.
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
7/30/2019 Nimonic Alloy 105
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.
Figure 5. Heat treatment 4h/1150C/AC + 16h/1050-1065C/AC + 16h/850C/AC
98% confidence region calculated on 15 casts
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
Figure 6. Heat treatment 4h/1150C/AC + 16h/1050-1065C/AC + 16h/850C/AC
98% confidence region calculated on 15 casts
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
7/30/2019 Nimonic Alloy 105
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.
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, 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
7/30/2019 Nimonic Alloy 105
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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.
Table 11 - Heat treatment 4 h/1150C/AC + 16 h/1050-1065C/AC + 16 h/850C/AC
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.
7/30/2019 Nimonic Alloy 105
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
Creep-Rupture Properties: Extruded Bar Subsequently Forged
1MPa x 101 = 107 N/m2 ; 1 N/mm2 (1 MN/m2) = 0.1 hbar = 1.02 kgf/mm2 = 0.0647 tonf/in2
7/30/2019 Nimonic Alloy 105
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11
NIMONIC alloy 105
Creep-Rupture Properties: Extruded Bar Subsequently Forged
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
7/30/2019 Nimonic Alloy 105
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.
Table 12 - Heat treatment 4 h/1125C/AC + 16 h/850C/AC
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
7/30/2019 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
Creep-Rupture Properties: Extruded Bar Subsequently Cold Stretched
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
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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
Creep-Rupture Properties: Extruded Bar Subsequently Cold Stretched
Plain
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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.
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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
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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
Mean tensile stress, ton/in
Mean tensile stress, MPa
Semi-rang
eofalternatingstress,
MPa
Semi-rangeofalternatings
tress,ton/in
Figure 13. Fatigue properties at 400C.
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
PP
PP
PP
PO
Fatigue Properties: Extruded Section Subsequently Cold Rolled
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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
Mean tensile stress, ton/in
Mean tensile stress, MPa
Semi-range
ofalternatingstress,
MPa
Semi-rangeofalternating
stress,ton/in
Figure 14. Fatigue properties at 650C.
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
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
Mean tensile stress, ton/in
Mean tensile stress, MPa
Semi-rang
eofalternatingstress,
MPa
Semi-rangeofalternatingst
ress,ton/in
Figure 15 . Fatigue properties at 750C.
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
PP
PP
PP
PO
Fatigue Properties: Extruded Section Subsequently Cold Rolled
18
NIMONIC alloy 105
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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
Mean tensile stress, ton/in
Mean tensile stress, MPa
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
Mean tensile stress, ton/in
Mean tensile stress, MPa
Semi-
rangeofalternatingstress,
MPa
Semi-rangeofalternatin
gstress,ton/in
50 h, 3 x 107 Cycles
500 h, 3 x 108 CyclesOP
PP
PP
PP
PO
14
12
10
8
6
4
2
0
Figure 16. Fatigue properties at 870C.
Heat treatment 4 h/1150C/AC + 4 h/1080C/AC + 8 h/850C/AC
Fatigue Properties: Extruded Section Subsequently Cold Rolled
Figure 17. Fatigue properties at 980C.
Heat treatment 4 h/1150C/AC + 4 h/1080C/AC + 8 h/850C/AC
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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
Table 16 - Heat treatment 4 h/1125C/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
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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 temperature, C
Table 19 - Room Temperature Impact Values
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
Table 20 - Elevated Temperature Impact Values
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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 temperature, C
Table 21 - Room Temperature Impact Values
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
Soaking temperature, C
Table 22 - Elevated Temperature Impact Values
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
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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.
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