Nickel Alloy K 500/ Monel K 500

Alloy K-500 is a precipitation hardened nickel-copper alloy which has excellent corrosion resistance together with increased strength and hardness of that of Alloy 400. Alloy K-500 is commonly used in the marine, chemical, medical and paper production industries for items such as pump shafts, oil-well tools, doctors blades and scrapers, springs, marine propeller shafts.

Chemical Composition Limits
Weight%	Ni+Co	C	Mn	Fe	S	Si	Cu	Al	Ti
K 500	63 min	0.25 max	1.5 max	2 max	0.01 max	0.5 max	27 - 33	2.3 - 3.15	0.35 - 0.85

Typical Mechanical Properties

Material	Form and Condition	Tensile Strength MPa	Yield Strength (0.2% Offset) MPa	Elongation (%)	Hardness Rockwell B
Alloy K 500 Rod and Bar	Cold Drawn Annealed	621-758	276-414	50-25	75-90B
Alloy K-500 Rod and Bar	Cold- Drawn Annealed and Aged	896-1310	586-827	30-20	24-35C

 

Nickel Alloy 600/Inconel 600®

Nickel Alloy 600 (N06600) is a nickel-chromium-iron alloy with good oxidation resistance at high temperatures and resistance to chloride-ion stress corrosion cracking corrosion by high-purity water, and caustic corrosion. Alloy 600 also has excellent mechanical properties and has a desirable combination of high strength and good workability. Used for furnace components, in chemical and food processing, in nuclear engineering and for the sparking electrodes.

Chemical Composition Limits
Weight%	C	S	Cr	Cu	Mn	Si	Ni	Fe
Nickel Alloy 600	0.15 max	0.015 max	14.0 - 17.0	0.50 max	1.0 max	0.50 max	72.0 min	6 - 10

Typical Mechanical Properties

Material	Form and Condition	Tensile Strength		Yield Strength		Elongation %	Hardness, Rockwell
		ksi	MPa	ksi	MPa
Alloy 600 rod and bar	Cold drawn Annealed	80-100	550-690	25-50	170-345	55-35	65-85B
Alloy 600 Plate	Hot rolled Annealed	80-100	550-725	30-50	205-345	55-35	65-85B
Alloy 600 Sheet	Cold Rolled Annealed	80-100	550-690	30-45	205-310	55-35	88B max
Alloy 600 Tube and Pipe	Cold Drawn Annealed	80-100	550-690	25-50	170-345	55-35	88B max
Alloy 600 Wire	Cold Drawn Annealed	80-120	550-830	35-75	240-520	45-20	-
Alloy 600 Wire	Cold Drawn No 1 Temper	105-135	725-930	70-105	480-725	35-15	-
Alloy 600 Wire	Spring Temper	170-220	1170-1520	150-210	1035-1450	5-2	-

 

Nickel Alloy 601/ Inconel 601®

Alloy 601 (UNS N06601) is a Nickel-Chromium alloy with an addition of Aluminium for outstanding resistance to oxidation and other forms of high temperature corrosion. Alloy 601 also has high mechanical properties at elevated temperatures. Alloy 601 is used for industrial furnaces, radiant tubes, themocouple tubes and heat treatment equipment, baskets, muffles, retorts. Petrochemical process equipment and aircraft components.

Chemical Composition Limits
Weight%	Ni	Cr	Fe	Al	C	Mn	S	Si	C
Alloy 601	58-63	21-25	Rem	1-1.7	0.10 max	1.0 max	0.015 max	0.50 max	1.0 max

Typical Mechanical Properties

Material	Form and Condition	Tensile Strength		Yield Strength		Elongation %	Hardness, HB
		ksi	MPa	ksi	MPa
Alloy 601 Bar	Bar Annealed	80-115	550-790	30-60	205-415	70-40	60-80
Alloy 601 Sheet	Sheet Annealed	85-100	585-690	30-50	205-345	55-35	65-80
Alloy 601 Plate	Plate Annealed	80-100	550-690	30-45	205-310	65-45	60-75

 

Nickel Alloy 617/ Inconel 617 ®

Alloy 617/ Inconel 617 ®(UNS N06617) is a nickel-chromium-cobalt-molybdenum alloy with an exceptional combination of high-temperature strength and oxidation resistance. The high nickel and chromium contents make the alloy 617 resistant to a variety of both reducing and oxidising environments, while the aluminium with the chromium provides oxidation resistance at high temperatures. Those elements with the molybdenum enable the alloy to withstand many wet corrosive environments.

Chemical Composition Limits

Weight%

Ni

Cr

Mo

Fe

S

C

Mn

B

Cu

Ti

Co

P

Si

Al

Alloy 617

44.5 min

20 - 24

8 - 10

3 max

0.15 max

0.05 - 0.15

1 max

0.006

0.50 max

0.60 max

10 - 15

0.15 max

1 max

0.8 -1 .5

Typical Mechanical Properties

Material	Form Condition	Yield Strength		Tensile Strength		Elongation %	Reduction of Area	Hardness, BHN
		ksi	MPa	ksi	MPa
Alloy 617 Bar	Solution Annealed	46.1	318	111.5	769	56	50	181
Alloy 617 Sheet	Solution Annealed	50.9	351	109.5	755	58	-	173
Alloy 617 Plate	Solution Annealed	46.7	322	106.5	734	62	56	172

 

Nickel Alloy 625 / Inconel 625®

Alloy 625 (UNS N06625) is a nickel-chromium-molybdenum alloy with an addition of niobium. The addition of molybdenum acts with the niobium to stiffen the alloy matrix, providing a high strength without a strengthening heat treatment. The alloy resists a wide range of corrosive environments and has a good resistance to pitting and crevice corrosion. Alloy 625 is used in chemical processing, aerospace and marine engineering oil & gas, pollution control equipment and nuclear reactors.

Chemical Composition Limits

Weight %

Ni

Cr

Mo

Nb + Ta

Fe

Ti

C

Mn

Si

S

P

Al

Co

Alloy 625

58.0 min

20 - 23

8 -10

3.15 -4.15

5.0 max

0.40 max

0.10 max

0.50 max

0.50 max

0.15 max

0.15 max

0.40 max

1.0 max

Typical Mechanical Properties

Material	Form and Condition	Tensile Strength MPa		Yield Strength (0.2% Offset) MPa		Elongation 4D(%)	Hardness HB
		Ksi	MPa	Ksi	MPa
Alloy 625 Bar	Annealed	120	827	60	414	30	≤ 287 HB
Alloy 625 Sheet	Annealed	120	827	60	414	30	145-240
Alloy 625 Tube Seamless and Welded	Annealed	120	827	60	414	35	-

 

Nickel Alloy 706/ Inconel 706®

Alloy 706 (UNS N09706) is a nickel-iron-chromium. As alloy 706 is a precipitation-hardenable alloy that provides high mechanical strength in combination with good fabricability. The properties of Alloy 706 are similar to Alloy 718 however alloy 706 is more readily fabricated. The main uses of Alloy 706 are for aerospace and land base gas turbine parts and components.

Chemical Composition Limits

Weight %

Ni+Co

Cr

Fe

Nb+Ta

Ti

Al

C

Cu

Mn

Si

S

P

B

Co

Alloy 706

39.0 - 44.0

14.5 - 17.5

Bal

2.5 - 3.3

1.5 -2.0

0.40 max

0.06 max

0.30 max

0.35 max

0.35 max

0.015 max

0.020 max

0.006 max

1 max

Typical Mechanical Properties

Material	Condition	Tensile Strength Ksi	Yield Strength Ksi	Elongation (%)
Alloy 706 Sheet Cold Rolled	Solution Annealed	109.8	55.5	47

 

Nickel Alloy 718/ Inconel 718®

Alloy 718 (UNS N07718, W Nr 2.4668) is an austenitic nickel-based superalloy. Alloy 718 exhibits excellent high yield tensile and creep-rupture properties at temperatures up to 1300ºF and oxidation resistance to 1800ºF. Alloy 718 is used in applications that require high strength such as parts for jet engines and high speed airframe parts such as wheels, buckets, spacers and high temperature bolts and fasteners.

Chemical Composition Limits
Weight %	C	Mn	P	S	Si	Cr	Ni	Mo	Cb	Ta	Ti	Al	Co	B	Cu	Fe
Alloy 718 AMS 5662	0.08	0.35	0.015	0.015	0.35	17-21	50-55	2.8-3.30	4.75-5.50	0.05	0.65-1.15	0.20-0.80	1.00	0.006	0.30	Rem

Typical Mechanical Properties

There are two main types of solution annealed and aging treatments:
1)
Solution Treatment (AMS 5662 Bar / AMS 5596 Sheet): 1725°F - 1850°F + Air Cool.
Heat Treatment (AMS 5663 Bar) : 1325°F for 8 hrs, cooling 100°F/hr to 1150°F, hold at 1150°F for 8hrs min, + Air Cool .

This treatment gives the highest room temperature tensile and yield strengths as well as producing the highest fatigue strength. It is the optimum heat treatment for Alloy 718 where a combination of rupture life, notch rupture life and rupture ductility is required.

2)
Alternative Solution Treatment (AMS 5664 Bar / AMS 5597 Sheet): 1900°F - 1950°F + Air Cool
Heat Treatment: 1400°F for 10hrs, furnace cool to 1200°F, hold at 1200°F for a total aging time of 20 hrs + Air Cool.

This is the prefered treatment in tensile-limited applications as 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.

Material	Condition	Tensile Strength ksi	Yield Strength ksi	Elongation 4D	Reduction of Area %	Hardness
AMS 5662 Bar	1700-1850°F Anneal	-	-	-	-	≤ 277 HB
AMS 5663 Bar	1700-1850°F Anneal + Age	185	150	12	15	≥331 HB
AMS 5664 Bar	1900-1950°F Anneal	-	-	-	-	3" dia 248 HB 3-5" dia 285 HB
	1900-1950°F Anneal + Age	180	150	10	12	≥341 HB

Typical Mechanical Properties of Alloy 718 Bar above and Alloy 718 Sheet below.

Material	Condition	Tensile Strength ksi	Yield Strength ksi	Elongation 4D	Hardness
Alloy 718 Sheet	AMS 5596 < 0.1874" thick	140	80	30	102 HRB
Alloy 718 Sheet	AMS 5596 Aged < 0.1874" thick	180	150	12	≥36 HRC
Alloy 718 Sheet	AMS 5597	140	75	30	≤ 25 HRC
Alloy 718 Sheet	AMS 5597 + Aged	180	150	15	≥38 HRC

 

Nickel Alloy 725 / Inconel 725®

Alloy 725 (UNS N07725) is a nickel-chromium-molybdenum-niobium alloy that is highly resistant to corrosion and has been age hardened for extremely high strength twice that of annealed alloy 625. Alloy 725 strength is developed by heat treatment rather than by cold work this also enables strength to be imparted to large non-uniform sections that cannot be strengthened by cold works. Alloy 725 is used for hangers, landing nipples and high strength fasteners in marine applications.

Chemical Composition Limits

Weight%

Ni

Cr

Mo

Nb

Ti

Al

C

Mn

Si

P

S

Fe

Alloy 725

55.0-59.0

19.0 -22.5

7.0-9.5

2.75-4.0

1.0-1.7

0.35 max

0.03 max

0.35 max

0.20 max

0.015 max

0.010 max

Rem

Typical Mechanical Properties

Material	Form and Condition	Yield Strength (0.2% Offset)		Tensile Strength		Elongation %	Hardness, Rc
		ksi	MPa	ksi	MPa
Alloy 725 round	Annealed	62.0	427	124.0	855	57	5
Alloy 725 round	Age Hardened	133.0	917	180.0	1241	30	36
Transverse Specimens from hot-finished rounds of 4.0 to 7.5 in (102 to 190mm) diameter

 

Nickel Alloy X-750/ Inconel X-750®

Alloy X-750 is a nickel-chromium alloy which has been made precipitation-hardenable by the additions of aluminum and titanium. Alloy X-750 has good resistance to corrosion and oxidation along with high tensile and creep rupture properties at temperature up to 1300ºF (700ºC). Due to X-750's excellent relaxation resistance it is useful for applications as high-temperature springs and bolts, X-750 is also used in gas turbines, rocket engines, nuclear reactors, pressure vessels, tooling and aircraft structures.

Chemical Composition Limits

Weight %

Ni +(Co)

Cr

Fe

Ti

Al

Nb + (Ta)

Mn

Si

S

Cu

C

Co

X-750 UNS N07750

70 min

14-17

5-9

2.25-2.75

0.40-1.0

0.70-1.2

1 max

0.50 max

0.01 max

0.50 max

0.08 max

1 max

UNS N07752 is available in billets for forging. UNS N0772 has limits of 0.05% on both Carbon and Cobalt

Typical Mechanical Properties

Material	Size	Ultimate Tensile Strength ksi	Yield Strength (0.2% Offset) Ksi	Elongation in 4D(%)	% Reduction of Area
Alloy X-750 Bar	Under 4.0"	165.0	105	20	25
Alloy X-750 Bar	4.0 " and over	160	100	15	17
Properties as described in AMS 5667 which requires that material following 1625°F/24 hrs, AC-Equalising + precipitation treatment have the following minimum room temperature properties. Hardness will lie in the range of 302-363 BHN

Rod, Bars and Forgings are available with the following heat treatments

AMS 5667 - 1625°F/24hr, AC + 1300°F/20 hr, AC (Equalising plus precipitation treatment). AMS 5667 Rod, Bars and Forgings have high strength and notch rupture ductility up to 1100°F

AMS 5668 - 2100°F anneal + 1550°F/24 hr, AC, +1300°F/20hr, AC (triple heat treatment). AMS 5668 has maximum creep, relaxation and rupture strength above about 1100°F.

AMS 5670 - 1800°F anneal + 1350°F/8hr, FC to 1150°F. Hold at 1150°F for total precipitation-treating time 18 hr, AC (solution treatment plus furnace cool precipitation treatment). Due to the heat treatments AMS 5670, AMS 5671 and AMS 5747 have increased tensile properties and reduced heat treatment time service up to about 1100°F.

With a heat treatment of 1800°F anneal + 1400°F/1hr, FC to 1150°F, hold at 1150°F for total precipitation-treating time of 6 hr, AC (solution treatment plus short furnace-cool precipitation treatment). This treatment of short furnace cool aging achieves only slightly lower properties than does AMS 5670 and AMS 5671.

Rods and Bars X-750 is available from 1/2" diameter to 6" diameter in 1/4" increments. From 6" diameter to 10" diameter it is available in 1/2" increments.

Material	Size	Tensile Strength ksi	Yield Strength (0.2% Offset) Ksi	Elongation in 2"(%)	% Hardness Rc
Alloy X-750 Sheet Annealed Condition	0.010 to 0.024", incl	140 max	-	30 min	-
Alloy X-750 Sheet Annealed Condition	over 0.024 - 0.125" incl	130 max	60 max	40 min	-
Alloy X-750 Sheet Annealed Condition	over 0.125 - 0.250 incl	130 max	65 max	40 min	-
Alloy X-750 Sheet After Precipitation Treating (1300°F/20hr, A.C)	0.010 to 0.025 incl	165 min	105 min	20 min	32 min
Alloy X-750 Plate After Precipitation Treating (1300°F/20hr, A.C)	0.187 to 4.000, excl	155 min	100 min	20 min	30 min

Sheet, Strip and Plate are available with the following heat treatments

AMS 5542 - 1300°F/20hr, AC (Constant-temperature precipitation treatment). AMS 5542 has high strength up to 1300°F

AMS 5598 - 1350°F/8hr, FC to 1150°F, hold at 1150°F for total precipitation-treating time of 18hr, AC (furnace-cool precipitation treatment. AMS 5598 has high strength up to 1300°F (Increased tensile properties to about 1100°F).

With heat treatment 1400°F/1hr, FC to 1150°F hold at 1150°F for total time of 6hr, AC (short furnace-cool precipitation treatment).

Material	Tensile Strength ksi	Yield Strength ksi	Elongation in 4D(%)	% Reduction of Area	Hardness
Alloy X-750 N07752 Type 1	160-185	100-130	20	20	27-40 HRC
Alloy X-750 Heat Treatment - Solution Treat 1.2 hrs @ 1975°F and Air Cool Precipitation Heat Treat 20 hrs @ 1320°F and Air Cool

UNS N07752 is available in billet for forging. UNS N07752 has limits on the Carbon and Cobalt levels (each has a maximum of 0.05%).

 

Nickel Alloy X / Inconel HX ®

Nickel Alloy X is a nickel-chromium-iron-molybdenum alloy with exceptional resistance to oxidation and outstanding strength, this alloy is used in nuclear engineering and heat treating furnaces. Nickel Alloy X is also know as Alloy HX®, Hastelloy X® and Inconel HX®.

Chemical Composition Limits
Weight %	C	Cr	Co	Fe	Mn	Mo	Ni	Si	W	P	S
Nicke Alloy X	0.05 - 0.15	20.5 -23	0.5 - 2.5	17.0 - 20.0	1 max	8-10	Bal	1 max	0.2 - 1.0	0.04 max	0.03 max

Typical Mechanical Properties

Material	Condition	Tensile Strength ksi	Yield Strength ksi	Elongation %	Hardness Rb
Nickel Alloy X Sheet	Annealed	115	50	45.5	90

 

Incoloy Alloy 800 / 800H/ 800HT

Alloy 800 - The 800 series of alloy (Incoloy 800, 800H and 800HT) are nickel-iron-chromium superalloys that have excellent properties of high temperature strength and resistance to oxidation, carburization and other types of high temperature corrosion. Alloy 800, 800H and 800HT are used in various applications from furnace components, petrochemical furnace cracker tubes to sheathing for electrical heating elements.

Chemical Composition Limits
Weight %	Ni	Cr	Fe	C	Al	Ti	Al+Ti
Alloy 800	30-35	19-23	39.5 min	0.10 max	0.15-0.60	0.15-0.60	0.30-1.20
Alloy 800H	30-35	19-23	39.5	0.05-0.10	0.15-0.60	0.15-0.60	0.30-1.20
Alloy 800HT	30-35	19-23	39.5	0.06-0.10	0.25-0.60	0.25-0.60	0.85-1.20
ASTM Grain Size - Alloy 800 is not specified, Alloy 800H is 5 or coarser, Alloy 800HT is 5 or coarser.

Typical Mechanical Properties

Material	Temp		Hardnes BHN	Tensile Strength MPa		Yield Strength (0.2% Offset)
	°F	°C		ksi	MPa	ksi	MPa
Alloy 800H and Alloy 800HT	80	27	126	77.8	536	21.7	150
Alloy 800H and Alloy 800HT	800	425		67.5	465	18.8	130
Alloy 800H and Alloy 800HT	1000	540	90	62.7	432	13.0	90
Alloy 800H and Alloy 800HT	1200	650	84	54.8	378	13.5	93
Alloy 800H and Alloy 800HT	1300	705	82	47.7	329	15.8	109
Alloy 800H and Alloy 800HT	1400	760	74	34.2	236	13.1	90
Alloy 800HT is a Trademark of Special Metals Corporation

 

Nickel Alloy 825/ Incoloy 825®

Alloy 825 is a nickel-iron-chromium alloy with additions of molybdenum and copper. It has excellent resistance to both reducing and oxidizing acids, to stress-corrosion cracking, and to localised attack such as pitting and crevice corrosion. Alloy 825 is especially resistant to sulphuric and phosphoric acid. Alloy 825 is used for chemical processing, pollution control equipment, oil and gas well piping, nuclear fuel reprocessing, acid production and pickling equipment and handling of radioactive wastes.

Chemical Composition Limits
Weight %	Ni	Fe	Cr	Mo	Cu	Ti	C	Mn	S	Si	Al
Alloy 825	38 - 46	22 min	19.5 - 23.5	2.5 - 3.5	1.5 - 3	0.6 - 1.2	0.05 max	1 max	0.03 max	0.5 max	0.2 max

Typical Mechanical Properties

Material	Form and Condition	Tensile Strength MPa	Yield Strength (0.2% Offset) MPa	Elongation (%)
Alloy 825 Tube	Annealed	772	441	36
Alloy 825 Tube	Cold Drawn	1000	889	15
Alloy 825 Bar	Annealed	690	324	45
Alloy 825 Plate	Annealed	662	338	45
Alloy 825 Sheet	Annealed	758	421	39

 

Nickel Alloy 901/ Nimonic 901®

Alloy 901 is an age-hardenable super alloy which contains Titanium and Aluminium for precipitation hardening and molybdenum for soild-solution strengthening. Alloy 901 has high yield strength and creep resistance at temperatures to about 1110°F (600°C). As Alloy 901 has a substantial iron content it enables alloy 901 to combine strength with good forging characteristics. Alloy 901 is commonly used for gas turbine engine discs, shafts, rings, casings and seals.

Chemical Composition Limits

Weight%

Ni

Cr

Mo

Ti

Co

Cu

Mn

Si

Al

C

S

Fe

Alloy 901

42.5

12.5

5.75

2.9

1.0 max

0.5 max

0.5 max

0.4 max

0.35 max

0.1 max

0.03 max

Bal

Typical Mechanical Properties

Material	Tensile Strength ksi	Yield Strength ksi	Elongation in 4D(%)	Reduction of Area %	Hardness HB
Alloy 901	150	100	12	15	302-388

 

Nickel Alloy 907/ Incoloy 907®

Alloy 907 (Incoloy alloy 907) is a nickel-iron-cobalt alloy with additions of niobium and titanium for precipitation hardening. It has the low coefficient of expansion and high strength of alloy 903 but alloy 907 has improved notch-rupture properties at elevated temperatures. Alloy 907 is used for gas turbines components (seals, shafts, casings and other structural parts).

Chemical Composition Limits
Weight%	Ni	Co	Fe	Nb	Ti	Al	Si
Alloy 907	35.0-40.0	12-16	Bal	4.3-5.2	1.3-1.8	0.2 max	0.07-0.35

 

Nickel Alloy 909 /Incoloy 909® (UNS N19909)

Alloy 909/ Incoloy 909® (UNS N19909) is a nickel-iron-cobalt alloy. Alloy 909 is a high strength alloy with impressive constant low coefficient of thermal expansion. Due to Alloy 909 characterisitics it has wide applications where low expansion together with high strength is required. Uses of Alloy 909 include gas turbines, rocket-engine thrust chambers, ordnance hardware, springs, steam-turbine bolts, gauge blocks, instrumentation, glass-sealing applications etc.

Chemical Composition Limits
Weight%	N	Co	Nb	Ti	Fe	Si	Al	C
Alloy 909	35.0 - 40.0	12.0 - 16.0	4.3 - 5.2	1.3 - 1.8	Bal	0.25 - 0.50	0.15 max	0.06 max

Typical Mechanical Properties

Material	Temperature		Yield Strength (0.2% Offset)		Tensile Strength		Elongation (%)	Reduction Area %
			Ksi	MPa	Ksi	MPa
Alloy 909	70F	20C	150	1034	185	1276	15	30
Alloy 909	1200	650	125	862	150	1034	25	60
Typical Tensile Properties of Age-Hardened Alloy 909

 

Nickel Alloy 925 /Incoloy 925®

Alloy 925 / Incoloy 925 / UNS N09925 is an age hardenable nickel-iron-chromium alloy with the addition of molybdenum, copper, titanium and aluminium. Each of these additions play their own part in making Alloy 925 a high strength alloy with excellent corrosion resistance. Alloy 925 is used in various applications in the crude oil and natural gas industry this is because Alloy 925 is resistant to sulfide stress cracking and stress-corrosion cracking and therefore a perfect alloy for use down-hole and surface gas well components.

Chemical Composition Limits

Weight%

Ni

Cr

Fe

Mo

Cu

Ti

Al

Mn

Si

Nb

C

S

Alloy 925

42 - 46

19.55 - 22.5

22 min

2.5 - 3.5

1.5 - 3.0

1.9 - 2.4

0.1 - 0.5

1.0 max

0.5 max

0.5 max

0.03 max

0.03 max

 

Nickel Alloy C276/ Inconel C276®/ Hastelloy C276®

Nickel Superalloy C276 is a nickel molybdenum chromium tungsten alloy with the addition of Tungsten. C276 has good fabricability and impressive corrosion resistance in some of the most severe environments. Due to C 276's properties it is commonly used in pollution control, chemical, petrochemical and waste incineration applications.

Chemical Composition Limits

Weight%

C

P

Si

Ni

Co

W

Mn

S

Cr

Mo

V

Fe

C276

0.01 max

0.040 max

0.08 max

Bal

2.5 max

3-4.5

1.00 max

0.030 max

14.5-16.5

15-17

0.35 max

4-7

Typical Mechanical Properties

Material	Ultimate Tensile (min)		Yield Strength (Min)		Elongation %	Hardness Rb
	Ksi	Mpa	Ksi	Mpa
C276 Tube	105.4	727	45.4	313	70	92
C276 Plate	107.4	741	50.3	347	67	89
C276 Bar	110.0	758	52.6	363	62	88
C276 Sheet	115.5	796	54.6	376	60	86

 

Nickel Alloy 75/ Nimonic 75®

Alloy 75 (UNS N06075, Nimonic 75) is a 80/20 nickel-chromium alloy with controlled additions of titanium and carbon. Nimonic 75 has good mechanical properties and oxidation resistance at high temperatures. Alloy 75 is most commonly used for sheet metal fabrications which require oxidation and scaling resistance together with medium strength at high operating temperatures. Alloy 75 (Nimonic 75) is also used in gas turbine engines, for components of industrial furnaces, for heat treating equipment and fixtures, and in nuclear engineering.

Chemical Composition Limits
Weight%	Ni	Cr	Ti	C	Si	Cu	Fe	Mn
Alloy 75 Nimonic 75	Bal	18.9 - 21.0	0.2 / 0.6	0.08 / 0.15	1.0 max	0.5 max	5.0 max	1.0 max

Typical Mechanical Properties

Material	Test Temp °F	Ultimate Tensile Strength (ksi)	0.2 % Yield Strength (ksi)	Elongation in 2"
Alloy 75 Sheet 1925°F Anneal	Room	114.4	59.4	31
Alloy 75 Sheet 1925°F Anneal	1000	105.6	51.9	27
Alloy 75 Sheet 1925°F Anneal	1200	69.3	40.0	32
Alloy 75 Sheet 1925°F Anneal	1400	41.4	22.0	75
Alloy 75 Sheet 1925°F Anneal	1600	20.2	9.9	90
Alloy 75 Sheet 1925°F Anneal	1800	9.7	4.4	91

 

Nickel Alloy 80A / Nimonic 80A®

Alloy 80A (Nimonic® alloy 80A) is a wrought, age-hardenable nickel-chromium alloy. Alloy 80A is similar to alloy 75 but made precipitation hardenable by additions of aluminium and titanium. Alloy 80A has good corrosion and oxidation resistance and high tensile and creep-rupture properties at temperatures to 815ºC (1500ºF). Vacuum refined versions are also available. Alloy 80A is used for gas-turbine components (blades, rings, discs), bolts, tube supports in nuclear generators, exhaust valves in internal combustion engines and has many other offshore/marine, automotive and electrical applications.

Chemical Composition Limits

Weight %

Ni

Cr

Ti

Al

C

Si

Cu

Fe

Mn

Co

B

Zr

S

Alloy 80A

Bal

18.0-21.0

1.8-2.7

1.0-1.8

0.10 max

1.0 max

0.2 max

3.0 max

1.0 max

2.0 max

0.008 max

0.15 max

0.015 max

Typical Mechanical Properties

Material	Condition	Ultimate Tensile Strength ksi	Yield Strength ksi	Elongation on 4D (min)	Hardness min
Alloy 80A	Solution Annealed & Precipatation Treated (aged)	145	90	20	300 HV

 

Nickel Alloy 86 / Nimonic 86

Alloy 86 is a nickel-chromium-molybdenum alloy. Alloy 86 has good formability and weldability with exceptional resistance to oxidation and scaling to 1050°C (1920°F). Alloy 86 is quite rare due to its "Cerium" addition although it is widely used in afterburners and heat treating furnaces.

Chemical Composition Limits
Weight%	Ni	Cr	Mo	Ce	C
Alloy 86	65	25.0	10.0	0.03	0.05 max

Typical Mechanical Properties

Material	Treatment	Temperature °C	UltimateTensile Strength MPa	Yield Strength (0.2% Offset) MPa	Elongation on 5.65 √ 50(%)
Alloy 86 Bar	Heat Treatment 4h/1150°C/ AC	300	251	692	49
Allloy 86 Bar	Heat Treatment 4h/1150°C/ AC	500	243	661	54
Allloy 86 Bar	Heat Treatment 4h/1150°C/ AC	700	239	557	56
Allloy 86 Bar	Heat Treatment 4h/1150°C/ AC	850	173	319	69

 

Nickel Alloy 90/ Nimonic 90®

Nimonic alloy 90 is a precipitation hardenable nickel-chromium-cobalt alloy strengthened by the addition of Titanium and Aluminium. Alloy 90 has a high stress rupture strength and creep-resistant at temperatures to 920°C. Nimonic Alloy 90 is typically used in extreme stress applications such as turbine blades, hot working tools, exhaust reheaters, disc and high-temperature springs.

The recommended heat treatments for Nimonic 90 are as follows:
Nimonic 90 Bar
Solution Treatment - 1080 °C (1975 °F) for 8 hours + air cool or oil/ water quench
Precipitation Heat Treatment (As per BS HR2) - 700 °C (1290 °F) for 16 hours + air cool

Nimonic 90 Sheet
Solution Treatment - 1100-1150 °C for 1-10 minutes + air cool or oil /water quench
Stabilization Heat Treatment - 925 °C for 1 hour + air cool
Precipitation Heat Treatment - 750 °C for 4 hours and air cool
(BS HR202/ MSRR 7016 / Siemens TLV 85252100 do not require the Stabilization Treatment stage)

Chemical Composition Limits

Weight %

Ni

Cr

Co

Ti

Al

C

Si

Cu

Fe

Mn

B

S

Zr

Pb

Alloy 90

Bal

18-21

15-21

2-3

1-2

0.2 max

1.0 max

0.2 max

1.5 max

1.0 max

0.02 max

0.015 max

0.15 max

0.0020 max

Typical Mechanical Properties

Material Extruded Bar	Temperature °C	Yield Strength 0.2 % (MPa)	Tensile Strength (MPa)	Elongation (%)	Hardness HV
Nimonic 90 bar Solution Treated (BS HR2)	RT	-	-	-	295 max
Nimonic 90 bar Precipition Treated (BS HR2)	RT	695 min	1080 min	20 min	310 min
Nimonic 90 Bar Precipitation Treated (BS HR2)	500	672 (typical)	1038 (typical)	31	-

 

Material Sheet	Temperature °C	Yield Strength 0.2 % (MPa)	Tensile Strength (MPa)	Elongation (%)	Hardness HV
Nimonic 90 sheet Solution Treated (BS HR202)	RT	-	-	-	250 max
Nimonic 90 sheet Precipitation Treated (BS HR202)	RT	695 min	1080 min	25 min (0.45mm-3.0mm)	280 min
Nimonic 90 sheet Precipitation Treated (BS HR 202)	500	740 (typical)	995 (typical)	30	-
Alloy 90 Cold Rolled Sheet (Heat Treated)

 

Nickel Alloy 263/ Nimonic 263®

Nimonic alloy 263 is an age-hardenable nickel-cobalt-chrome-molybdenum alloy which was designed to have excellent fabrication characteristics in the annealed condition but also very good aged strength properties. Alloy 263 is easier to form or weld than other materials such as Waspaloy or Rene 41 and exhibits excellent intermediate temperature ductility. Alloy 263 is supplied in the annealed condition and its excellent ductility in this condition makes it suitable for cold forming as well as hot working. Alloy 263 can be welded using matching composition filler wire in both TIG and MIG forms. The recommended heat treatments for Nimonic 263 are as follows:

Extruded Bar:
Solution Treatment - 1150 °C for 1.5-2.5 hours + water quench
Ageing Treatment - 800 °C for 8 hours + air cool
(As per BS HR10 / AMS 5886)

Hot-rolled Sheet
Solution Treatment - 1150 °C for 0.5 hours + water quench or air cool
Ageing Treatment - 800 °C for 8 hours + air cool
(As per BS HR206/ AMS 5872)

Cold-rolled Sheet
Solution Treatment - 1150 °C for 3-10 mins + water quench or fluidized bed quenching
Ageing Treatment - 800 °C for 8 hours + air cool
(As per BS HR206 / AMS 5872)

Chemical Composition Limits
Weight%	Ni	Cr	Mn	Si	C	Al	Ag	B	Fe
263	Bal	19-21	0.60 max	0.40 max	0.04-0.08	0.60 max	0.0005 max	0.005 max	0.07 max
Weight%	Cu	Mo	Co	Ti	Al+Ti	Pb	Bi	S
263	0.20 max	5.6-6.1	19-21	1.90-2.40	2.40-2.8	0.0020 max	0.0001 max	0.007 max

Typical Mechanical Properties

Material	Temp °C	Yield Strength 0.2% (Mpa)	Tensile Strength (Mpa)	Elongation %	Hardness HB
Nimonic 263 Bar Solution Treated (AMS 5886/ BS HR10)	RT	-	-	-	248 max
Nimonic 263 Bar Heat Treated (AMS 5886 / BS HR10)	RT	585 (typical)	1004 (typical)	45	-
Nimonic 263 Bar Heat Treated (AMS 5886/ BS HR10)	780	403 (min)	541 (min)	12	-

Material	Temp °C	Yield Strength (Mpa)	Tensile Strength (Mpa)	Elongation %	Hardness HRC
Nimonic 263 Sheet Solution Treated (AMS 5872 / BS HR206)	RT	-	-	-	22.5 max
Nimonic 263 Sheet Heat Treated (AMS 5872 / BS HR206	RT	580 (typical)	973 (typical)	39 -
Nimonic 263 Sheet Heat Treated (AMS 5872 / BS HR206	780	403 (min)	541 (min)	9	-

 

Nickel Alloy 105 /Nimonic 105®

Alloy 105 is a wrought nickel-colbalt-chromium base alloy which also contains molybdenum, aluminium and titanium which results in a high strength alloy that can be used in conditions up to 950°C with good creep resistance. Alloy 105 is used for turbine blades, discs, forgings, ring sections, bolts and fasteners.

Chemical Composition Limits
Weight%	C	Si	Cu	Fe	Mn	Cr	Ti	Al	Co	Mo	Pb	S	B	Zr	Ni
Alloy 105	0.12	1.0	0.2	1.0	1.0	14-15.7	0.9-1.5	4.5-5.5	18-22	4.5-5.5	0.0015	0.010	0.003-0.010	0.15	bal

 

Nickel Alloy PE11/ Nimonic PE11®

precipitation hardened and solid-solution strengthened. PE11 is commonly used in gas turbines because of its high tensile ductility strength and as it was developed for use at 550°C (1020°F).

Chemical Composition Limits
Weight%	Ni	Cr	Mo	Fe	Al	Ti	C
PE11	37 - 41	17 -19	4.75 - 5.75	Rem	0.70 - 1.0	2.2 - 2.5	0.03 - 0.08
Weight%	Cu	Si	Mn	Co	B	Zr	S
PE11	0.5 max	0.5 max	0.2 max	1.0 max	0.001 max	0.02 - 0.05	0.015 max

Typical Mechanical Properties

Material	Temperature	PE11 Rupture Strength (1000h) psi	PE11 Rupture Strength (1000h) MPa
PE11	650°C / 1200°F	49,000	340
PE11	705°C/ 1300°F	36,000	250
PE11	760°C/ 1400°F	21,000	140

 

Nickel Alloy PE16/ Nimonic PE16®

Alloy PE16 is a precipitation-hardenable nickel-iron-chromium alloy with an addition of molybdenum for solid-solution strengthening. PE16 has good strength and oxidation resistance at temperature to about 1380ºF (750ºC). Alloy PE16 is designed to provide a precipitation-hardened material having excellent hot-working, cold-working and welding characteristics. PE16 is commonly used in gas-turbines components and in nuclear reactors.

Chemical Composition Limits
Weight%	Ni + Co	Cr	Mo	Fe	Al	Ti	C
PE16	42-45	15.5-17.5	2.8-3.8	Rem	1.1-1.3	1.1-1.3	0.04-0.08
Weight%	Cu	Si	Mn	Co	B	Zr	S
PE16	0.5 max	0.5 max	0.2 max	2.0 max	0.005 max	0.02-0.04	0.015 max

Typical Mechanical Properties

Material	Condition 20°C	0.2 % Proof Stress MPa	Tensile Strength MPa	Elongation %	Reduction of Area %
PE16 Bar	Heat Treatment 2h/1040°C/AC +2h 800°C/AC + 16/700°C/AC	525	880	37	54
PE16 Bar	Heat Treatment 4h/1040°C/AC + 1h 900°C/AC + 8h/750°C / AC	450	830	29	55

 

Nickel Alloy PK33/ Nimonic PK33

Alloy PK33 is a nickel- chromium - cobalt precipitation hardenable alloy but the addition of Molybdenum makes Alloy PK33 solid-solution strengthened. PK33 is commonly used in gas turbines as flame tubes because of its high temperature strength, creep resistance and welded sheet structures.

Chemical Composition Limits
Weight%	Ni	Cr	Mo	Fe	Al	Ti	C
PK33	Bal	16-20	5-9	1.0 max	1.7-2.5	1.5-3.0	0.07 max
Weight%	Cu	Si	Mn	Co	B	Zr	S
PK33	0.2 max	0.5 max	0.5 max	12.0-16.0	0.005 max	0.06 max	0.015 max

Typical Mechanical Properties

Material	Condition 20°C	0.1 % Proof Stress MPa	Tensile Strength MPa	Elongation %	Reduction of Area %
PK33 Bar	Heat Treatment 2h/1100°C/AC +4h 850°C/AC	664	1127	33	41

 

Udimet Alloy L-605 / Haynes Alloy 25 is a solid solution strengthened cobalt-chromium-tungsten nickel alloy which combines excellent high temperature strength and oxidation resistance to 2000°F with good resistance to sulfidation, wear and galling. Alloy L-605 / Alloy 25 has good forming characteristics and is capable of being forged, hot worked or cold worked, althoug it does work-harden very rapidly so frequent intermediate annealing treatments are recommend for complex forming operations. Alloy 25 / L-605 can also be readily welded by most conventional welding methods using similar composition welding wire (AMS 5796) or coated electrodes (AMS 5797). Alloy L-605 / Alloy 25 is supplied solution heat treated in the range of 2150-2250°F and rapid air or water quenched to attain optimum properties. Alloy L-605 / Alloy 25 has many applications in military and commercial gas turbine engine components such as rings, blades and combustion chamber parts although for many modern engines it has largely been replaced by Alloy 188 or Alloy 230.

Chemical Composition Limits
Weight%	C	P	Si	Ni	W	Mn	S	Cr	Co	Fe
Alloy L-605	0.05 - 0.15	0.040 max	0.40 max	9.0 - 11.0	14.0 - 16.0	1.0 - 2.0	0.030 max	19.0 - 21.0	Bal	3.0 max

Typical Mechanical Properties

Material	Temperature °F	Yield Strength 0.2%	Tensile Strength	Elongation (%)	Hardness HB
Extruded Bar Alloy 25 / L-605	RT	310 Mpa 45 KSI	862 Mpa 125 KSI	30	277 max

Material Sheet	Thickness (inches)	Yield Strength 0.2% KSI	Tensile Strength KSI min	Elongation (%)	Hardness HRC
Alloy 25 / L-605 Solution Treated (AMS 5537)	0.005-0.020	55-80	130	30	-
Alloy 25 / L-605 Solution Treated (AMS 5537)	0.020-0.032	55-80	130	35	-
Alloy 25 / L-605 Solution Treated (AMS 5537)	0.032-0.043	55-80	130	40	-
Alloy 25 / L-605 Solution Treated (AMS 5537)	0.043-0225	55-80	130	45	-

 

Cobalt Alloy 188/ Haynes Alloy 188/ Udimet 188

Haynes 188 / Udimet alloy 188 is a cobalt based nickel-chromium-tungsten alloy with a small addition of lanthanum to give a very protective scale. Alloy 188 combines excellent high-temperature strength with good resistance to both oxidizing environments up to 2000°F and to sulfate deposit hot corrosion. Alloy 188 has good forming characteristics and is capable of being forged, hot worked or cold worked, althoug it does work-harden very rapidly so frequent intermediate annealing treatments are recommend for complex forming operations. Alloy 188 is supplied solution heat treated at 2150°F and rapid air or water quenched to attain optimum properties. A combination of good fabricability and weldability makes Alloy 188 suitable for a wide number of applications, particularly in gas turbine components such as combustors, flame holders, liners and tranistion ducts.

Chemical Composition Limits

Weight %

C

Mn

Si

P

S

Cr

Ni

W

La

B

Fe

Co

Alloy 188

0.05-0.15

1.25 max

0.20-0.50

0.02 max

0.015 max

20-24

20-24

13-16

0.02-0.12

0.015

3 max

Bal

Typical Mechanical Properties

Material	Temp°F	Yield Strength (0.2% Offset) min		Tensile Strength min		Elongation (%)	Hardness
		ksi	MPa	ksi	MPa
Alloy 188 Extruded Bar Solution Treated (AMS 5772)	RT	55	379	125	862	45	≤302HB

Material	Temp°F	Thickness (Inches)	Yield Strength (0.2% Offset) min		Tensile Strength min		Elongation (%)	Hardness HRC
			ksi	MPa	ksi	MPa
Alloy 188 Sheet Solution Treated (AMS 5608)	RT	≤0.020"	55	379	125	862	40	-
Alloy 188 Sheet Solution Treated (AMS 5608)	RT	≥0.020"	55	379	125	862	45	-
Alloy 188 Sheet Solution Treated (AMS 5608)	1200	≤0.020"	36	248	90	621	40	-
Alloy 188 Sheet Solution Treated (AMS 5608)	1200	≥0.020"	36	248	90	621	50	-

 

Nickel Alloy 230 /Haynes 230®

Alloy 230 is a nickel-chromium-tungsten-molybdenum alloy that combines excellent high temperature strength, outstanding resistance to nitriding environments and excellent long term thermal stability. Alloy 230 is easily fabricated and has very good forming and welding characteristics. Due to Alloy 230 combined properties it is very well suited to a wide variety of component applications in the aerospace and power industries. Alloy 230 is used for combustion cans, transition ducts, flame holders, thermocouple sheaths and other important gas turbine components. Haynes alloy 230 is solution treated at 2150 to 2275°F followed by rapid cooling, and is supplied in this condition (as per AMS 5891 and AMS 5878). Alloy 230 can be both hot worked and cold worked and all parts should be annealed and rapidly cooled in order to restore the best balance of properties.

Chemical Composition Limits
Weight%	C	Mn	Si	P	S	Cr	Co	Fe	Al	Ti	B	Cu	La	W	Mo	Ni
Haynes 230	0.05-0.15	0.30-1.0	0.25-0.75	0.03	0.015	20.0-24.0	5.0	3.0	0.20-0.50	0.10	0.015	0.50	0.005-0.05	13.0-15.0	1.0-3.0	Rem

Typical Mechanical Properties

Material	Test Temp °F	Ultimate Tensile Strength	0.2 % Yield Strength	Elongation in %	Hardness HB
Haynes Alloy 230 Extruded Bar Solution Treated (AMS 5891)	RT	758 Mpa 110 ksi	310 Mpa 45 ksi	35	241 max

Material	Test Temp °F	Ultimate Tensile Strength	0.2 % Yield Strength	Elongation in %	Hardness HB
Haynes Alloy 230 Sheet Solution Treated (AMS 5878)	RT	793 Mpa 115 ksi	345 Mpa 50 ksi	40	25 max
Haynes Alloy 230 Sheet Solution Treated (AMS 5878)	1000	699 Mpa 101.5 ksi	303 Mpa 44 ksi	53.7	-
Haynes Alloy 230 Sheet Solution Treated (AMS 5878)	1400	539 Mpa 78.3 ksi	323 Mpa 46.9 ksi	61.2	-
Haynes Alloy 230 Sheet Solution Treated (AMS 5878)	2000	90 Mpa 13.1 ksi	69 Mpa 10 ksi	37	-
(Non-room temperature figures are typical only)

 

Alloy MP159 (AMS 5841)

MP159 is a Nickel-Cobalt based multiphase alloy. This combination of properties enables ultra high strength, toughness, good ductility and excellent corrosion resistance. Through work strengthening and aging MP159 alloy exhibits ultimate tensile strength levels in excess of 1830 MPa. MP159 is used in many different industries from use in prosthetic devices, jet engine components, fasteners, marine applications to petroleum industry applications.

Chemical Composition Limits
Weight %	Ni	Co	Cr	Fe	Mo	Ti	Cb	Al
MP159	25.5	35.7	19.0	9.0	7.0	3.0	0.6	0.2

Typical Mechanical Properties

Material	Condtion	Tensile Strength ksi	Yield Strength ksi	Elongation %	Reduction of Area %	Hardness HRC
MP159	Annealed	123	58	60	69
MP159	AMS 5841	160 max	70 max	50	65	20 HRC max
MP159	Annealed, Cold Worked 48%	230	205	12	46
MP159	AMS 5842	-	-	-	-	≥38HRC
MP159	Annealed, Cold Worked + Aged	275	265	8	35
MP159	AMS 5843	260 min	250 min	6 min	20 min	≥44HRC

 

Alloy MP35N® (AMS 5844/AMS 5845/ NACE MR0175)

MP35N® is a multi-phase alloy containing Nickel, Cobalt, Chromium and Molybdenum with a unique range of properties - ultra high strength, toughness, biocompatibility and corrosion resistance. It is produced by vacuum induction melting and vacuum arc re-melting (VIM-VAR) and is then strengthened by work hardening and aging, giving hardnesses of up to 55-60 Rockwell C and strength levels as high as 260-300KSI.

Due, to this unique combination of properties, MP35N® has many applications in such industries as oil and gas, aerospace and medical. MP35N can be effectively used at cryogenic temperatures without embrittlement and maintain its properties at temperatures up to 600°F, and is also suitable for medical implants and orthodontic/prosthetic devices.

MP35N® is able to resist corrosion to most mineral acid, hydrogen sulfide and seawater environments whilst exhibiting excellent resistance to stress corrosion cracking and hydrogen embrittlement, even at high strength levels. NACE MR0175 allows a hardness of up to 51 HRC for material that has been work strengthened and aged by one of the processes listed in the table below.

Aircraft Materials supplies MP35N® in round bar certified to either AMS 5844 (0.270" - 1.520" diameter) or NACE MR0175 (0.5" - 2.5" diameter), as well as sheet, strip and plate products suitable for medical applications.

Chemical Composition Limits

Weight %

Ni

Co

Cr

Mo

Ti

Fe

Si

Mn

P

B

S

C

MP35N®

33-37

Bal

19-21

9-10.5

1 max

1 max

0.15 max

0.15 max

0.015 max

0.010 max

0.010 max

0.03 max

MP35N® is a registered trademark of SPS Technologies Inc.

Typical Mechanical Properties

Material	Condtion	Ultimate Tensile Strength ksi	0.2 % Yield Strength ksi	Elongation %	Reduction of Area %	Hardness HRC
MP35N ® AMS 5844	Solution Heat Treated and Work Strengthened	255	225	12	50	45
MP35N® AMS 5845	Solution Heat Treated and Work Strengthened and Aged	260	230	8	35	38 min

AMS 5844 is Solution Treated and Cold Worked. The AMS specification only requires that the hardness shall not be lower than 38 HRC or equivalent. However other typical mechanical properties of AMS 5844 are detailed above.

Material	Condtion	Tensile Strength ksi	Yield Strength ksi	Elongation %	Reduction of Area %	Hardness HRC
MP35N® NACE MR0175	Age @ 1300°F/ 4 hrs	220	210	10	40	51 max
MP35N® NACE MR0175	Age @ 1350°F / 4hrs	210	200	10	40	51 max
MP35N® NACE MR0175	Age @ 1425°F / 6hrs	190	180	10	40	51 max
MP35N® Properties as per NACE MR0175 - Cold Drawn - Reduced Strength (min properties, round bar under 2" dia)

 

Alloy Multimet N155 (AMS 5532 / AMS 5769)

Multimet N155 is a Nickel-Chromium-Cobalt alloy with additions of Molybdenum and Tungsten used typically in parts requiring high strength up to 1350°F and oxidation resistance up to 1800°F. Its high-temperature properties are inherent in the as-supplied condition (solution treated at 2150°F) and are not dependent on age-hardening. Multimet N155 is used in a number of aerospace applications such as tailpipes and tail cones, turbine blades, shafts and rotors, afterburner components and high-temperature bolts.

Chemical Composition Limits

Weight %

C

Mn

Si

P

S

Cr

Ni

Co

Mo

W

Nb

N

Fe

Multimet N155

0.08-0.16

1.00-2.00

1.00 max

0.040 max

0.030 max

20.00-22.50

19.00-21.00

18.50-21.00

2.50-3.50

2.00-3.00

0.75-1.25

0.10-0.20

Bal

Typical Mechanical Properties

Material	Form	Ultimate Tensile Strength ksi	Elongation in 2" (min)	Hardness Hb
Multimet N155	Bar (AMS 5769)			156-217
Multimet N155	Sheet / Plate (AMS 5532)	110-140	40	-

 

Nickel Superalloy Waspaloy

WASPALOY is a nickel based age hardenable alloy that possesses high temperature strength while still having a good corrosion resistance, especially to oxidation. WASPALOY can be used at temperatures up to 650°C (1200°F) which is critical rotating applications. WASPALOY is used in gas turbine engine components, missile systems, shafts, spacers, seals, rings, casings, fasteners and many other uses in engine hardware, airframe assemblies.

Chemical Composition Limits

Weight %

Cr

B

Zr

Al

Ti

Mo

Co

Cu

Fe

S

Si

Mn

C

P

Ni

Waspaloy

18-21

0.003-00.1

0.02-0.12

1.2-1.6

2.75-3.25

3.5-5.0

12-15

0.50 max

2 max

0.030 max

0.75 max

1 max

0.02-0.10 max

0.030 max

Bal

Typical Mechanical Properties

Material	Condtion	Thickness	Temp	Tensile Strength ksi	Yield Strength ksi	Elongation in 4D	Hardness HRC
Sheet	Sol Treated, Stabilization + Precipitation HT	0-0.020"	Room	170	110	15	34-44
Sheet	Sol Treated, Stabilization + Precipitation HT	0-0.020"	1000°F	145	100	13
Sheet	Sol Treated, Stabilization + Precipitation HT	over 0.020"	Room	175	115	20	34-44
Sheet	Sol Treated, Stabilization + Precipitation HT	over 0.020"	1000°F	150	105	15

 

Cobalt Alloy R41 / Rene 41

Alloy R41 (Rene 41) is an age hardening nickel base super alloy with has exceptional strength from room temperature through to between 650°C - 980°C (1200 - 1800ºF). R 41 is designed for use in severely stressed high temperature applications. R41 (Rene 41) is typically used in hot components for jet engines, rocket engines, turbine blades, turbine wheels, torque rings, bolting, springs and much more.

Chemical Composition Limits
Weight %	C	Si	Ni	Co	Al	Fe	Mn	Cr	Mo	Ti	B
R41 Rene 41	0.06 - 0.12	0.20 max	Bal	10-12	1.4-1.6	5.0 max	0.10 max	18-20	9.0-10.50	3-3.30	0.003-0.010

Typical Mechanical Properties

Material	Tensile Strength ksi	Yield Strength ksi	Elongation in 4D	Reduction of Area	Hardness
Rene 41 (R41) Solution Treated Bar					363 HB max
Rene 41 (R41) Solution Treated Aged Bar	170	130	8	10	311 HB min
Rene 41 (R41) Solution Treated Sheet	170 max	100 max	30 max		30HRC max
Rene 41 (R41) Solution Treated Aged Sheet	170 min	130 min	10 min		35 HRC min

Cobalt-chrome-molybdenum CCM ASTM F1537 Alloy 1

Technical Data Sheet

This alloy of Cobalt-Chromium-Molybdenum for implants is the MicroMelt® Biodur® Carpenter CCM® alloy (Cobalt CCM ASTM F1537). It meets the strictest requirements regarding biocompatibility and corrosion resistance. It is produced by powder metallurgy resulting in an exceptionally fine microstructure. But is also tough, ductile, hard, as well as fatigue and wear resistant. Its high cobalt content may impair its machinability and its cold deformability is difficult. It is non-magnetic.

Cobalt CCM ASTM F1537 is especially applicable for medical implants (endoprothesis and osteosynthesis) wherever high mechanical stress is expected. It is also widely used in the watch making industry as well as other industries where hardness, toughness, ductility and corrosion resistance are required.

Chemical Composition Limits
Weight %	C	Si	Mn	Cr	Mo	Ni	Fe	N	Co
CoCr28Mo	0.14 max	1 max	1 max	26.00-30.00	5.00-7.00	1 max	0.75 max	0.25 max	Bal
ASTM F1537	0.14 max	1 max	1 max	26.00-30.00	5.00-7.00	1 max	0.75 max	0.25 max	Bal

 

Cobalt Alloy 6b / Stellite 6b (AMS 5894)

Cobalt alloy 6b / Stellite 6b is a cobalt-based, chromium-tungsten alloy used extensively in wear environments where its low friction coefficient minimises the risk of seizing and galling, even in applications where lubrication is not practical. Stellite 6b is supplied in the solution treated condition (to AMS 5894) and its wear resistant properties inherent in this state limit the amount of heat treating and post machining. Typical applications for Alloy 6b include chain saw guide blades, furnace fan blades, high temperature bearings, valve stems, food processing equipment and steel mill equipment.

Chemical Composition Limits
Weight %	C	Mn	Si	P	S	Cr	Ni	Co	Mo	W	Fe
Cobalt Alloy 6b	0.90-1.40	0.50-2.00	0.20-2.00	0.04 max	0.03 max	28.00-32.00	3.00 max	bal	1.50 max	3.50-5.50	3.0 max

Typical Mechanical Properties (minimums)

Material	Form	Tensile Strength ksi	Yield Strength ksi	Elongation in 4D	Reduction of Area (*)	Hardness (HRC)
Alloy 6b	Bar (AMS 5894)	130	70	5	7	33-43
Alloy 6b	Sheet / Plate (AMS 5894)	130	70	5	7	33-43
Properties shown are for sheet and plate up to 1.0" thick and for round bar up to 3.5" diameter. *Reduction in area is not applicable to sheet or plate under 0.5" thick

 

Kovar / Nilo K (ASTM F15)

Kovar (Alloy K) is a nickel-iron-cobalt controlled-expansion alloy containing 29% nickel. Its coefficient of expansion, which decreases with rising temperature to the inflection point, matches the expansion rate of borosilicate glasses and alumina ceramics. Kovar (Alloy K) is used for glass-to-metal seals in applications requiring high reliability or resistance to thermal shock. Kovar (Alloy K) is used for high-power transmitting valves, transistor leads and headers, integrated-circuit lead frames, and photography flash bulbs.

Kovar Chemical Composition (Basic Density 8.36)

Weight %

Ni

Fe

Co

C

Mn

Si

Al

Cr

Mg

Zr

Ti

Cu

Mo

Alloy K Kovar

29.0

53.0

17.0

0.04 max

0.50 max

0.20

0.10 max

0.20 max

0.10 max

0.10 max

0.10 max

0.20 max

0.20 max

Typical Mechanical Properties

Material	Condition	Yield Strength (0.1% Offset)		Tensile Strength		Elongation %
		psi	MPa	psi	MPa
Alloy K Kovar	Annealed	49,000	340	75,000	520	42

 

Invar 36 /Nilo 36 / Alloy 36 (ASTM F1684)

Alloy 36 (NILO 36, INVAR 36) is a Nickel-Iron, low expansion alloy which contains 36% Nickel. Invar 36 has a low coefficient of expansion from cryogenic temperatures to about +500°F (260°C). Invar 36 also retains good strength and toughness at cryogenic temperatures. Common applications include tooling for aerospace composites, standards of length, measuring devices, thermostat rods, laser components and tanks and piping for the storage and transportation of liquefied gases.

Chemical Composition Limits
Weight %	Ni	Fe	C	Mn	P	S	Si	Cr	Mo	Co
Invar 36	35-38	Rem	0.10 max	0.06 max	0.025 max	0.025 max	0.35 max	0.50 max	0.50 max	1.0 max

Typical Mechanical Properties

Material	Condition	Ultimate Tensile Strength		Yield Strength 0.2 %		Elongation (%)
		psi	MPa	psi	MPa
Invar 36	Annealed	71,000	490	35,000	240	42

 

Nickel Iron Alloy 42/ Nilo 42 (ASTM F30)

Alloy 42 (Nilo 42) is a nickel-iron controlled-expansion alloy containing 42% nickel. Alloy 42 (Nilo 42) has a low and normally constant coefficient of thermal expansion from room temperature to about 300ºC (570ºF). Alloy 42 (Nilo 42) is used for semiconductor lead frames in integrated circuits, bi-metal thermostat strip, thermostat rods, for ceramic-to-metal seals with alumina ceramics, and various glass-to-metal seals such as the core of copper-clad-wire for sealing into glass envelopes of electric bulbs, radio valves, television tubes and fluorescent lights.

Chemical Composition Limits
Weight%	Ni	C	Mn	P	S	Si	Cr	Al	Fe
Alloy 42 Nilo 42	41 min	0.05 max	0.80 max	0.025 max	0.025 max	0.030 max	0.250 max	0.10 max	Rem

Typical Mechanical Properties

Material	Condition	Tensile Strength		Yield Strength (0.2% Offset)		Elongation (%)
		psi	MPa	psi	MPa
Alloy 42 (Nilo 42)	Annealed	71,000	490	36,000	250	43

 

Nickel Iron Alloy 45 / Low Expansion 45 Alloy

Chemical Composition Limits
Weight%	Ni	Cr	Mn	Si	C	Al	Mg	P	S	Fe
Alloy 45	46	0.10 max	0.80 max	0.30 max	0.05 max	0.10 max	0.50 max	0.025 max	0.025 max	Rem

Alloy 200 (UNS N02200) is a commercially pure wrought nickel, with good mechanical properties and an Controlled expansion alloys using compression or eyelet brazed seals

 

Nickel Iron Alloy 46 /Glass Sealing 46 Alloy

Alloy 46 is a iron-nickel alloy that are intended primarily for sealing to glass in electronic applications.

Chemical Composition Limits
Weight%	Ni	Cr	Mn	Si	C	Al	P	S	Fe
Alloy 46	46.0	0.25 max	0.80 max	0.30 max	0.05 max	0.10 max	0.025 max	0.025 max	Bal

 

Nickel Iron Alloy 48/ Nilo 48 (ASTM F30)

Alloy 48 (Nilo 48) is a nickel-iron controlled-expansion alloy containing 48% nickel. Alloy 48 (Nilo 48) coefficient of thermal expansion matches that of soft lead and soda lime glasses therefore Alloy 48's main use is for glass to metal seals in soft lead or soda lime type glasses. Alloy 48 is also used for thermostats in industrial applications up to 450°C (840°F).

Chemical Composition Limits
Weight %	Ni	Cr	Mn	Si	C	Al	P	S	Fe
Alloy 48	48	0.25 max	0.80 max	0.30 max	0.05 max	0.10 max	0.025 max	0.025 max	Bal

Typical Mechanical Properties

Material	Ultimate Tensile Strength		Yield Strength 0.2 %		Elongation (%)
	psi	MPa	psi	MPa
Alloy 48	75,000	520	38,000	260	43

Coefficient of Expansion - Alloy 48 (Nilo 48)
68-212°F, 10ˉ6 in/in °F	4.7
20-100°C, μ m/m °C	8.5
68-752 °F, 10ˉ6 in/in °F	4.6 / 5.2
20-400°C, μ m/m °C	8.3 / 9.3

 

Nickel Iron Alloy 52

Chemical Composition Limits
Weight%	Ni	Cr	Mn	Si	C	Al	Mg	P	S	Fe
Alloy 52	50.50	0.10 max	0.60 max	0.30 max	0.05 max	0.10 max	0.50 max	0.025 max	0.025 max	Rem

Controlled expansion alloys using compression or eyelet brazed seals

 

Magnetic Shielding Alloy Mu-Metal / HY-MU 80

Mumetal is 80% nickel with additions of iron and molybdenum as main elements in turn this alloy offers an extremely high initial permeability. It is only moderately resistant to moisture and atmospheric corrosion, it used mainly in in transformer cores but is well known for its magnetic properties which are used for shielding electrical components from magnetic fields. "HYMU 80" has a minimum DC permeability of 80,000 at a flux density of 40 gauss when heat treated by the recommended procedure and test in accordance with ASTM 596.

Chemical Composition Limits
Weight%	Ni	Cu	Cr	S	P	Si	Mn	C	Mo	Fe
Hymu 80 (Comp1)	79.0-80.6			0.008	0.02	0.42	0.95	0.03	3.8-5	Rem
MIL N 14411C (Comp2)	75.0-77.0	4.0-6.0	3.0	0.02	0.02	0.50	1.8	0.05

Typical Mechanical Properties

Mu-Metal
Yield Strength (psi)	Tensile Strength (psi)	Elongation in 2" (%)
44,000	100,000	40
Mechanical Properties in the Annealed Condition

 

AerMet ® 100 (AMS 6532)

AerMet® 100 (UNS K92580) is a alloy that has been designed to have properties of excellent hardness and strength combined with exceptional ductility and toughness. AM 100 is used in applications that require high fracture toughness and excellent resistance to stress corrosion cracking and fatigue. AerMet® 100 is considered as a candidate for use in applications such as Armor, Fasteners, Landing Gear, Jet Engine Shafts, Structural Members, Drive Shafts, Structural Tubing. Aermet 100 bar is supplied in the normalized and overaged condition (maximum hardness 372HB) ready for subsequent heat treatment.

Chemical Composition Limits
Weight%	C	Ni	Co	Cr	Mo	Fe
AerMet® 100	0.21-0.25	11-12	13-14	2.9-3.3	1.1-1.3	Bal

Heat Treatment: Aermet 100 bar (to AMS 6532) is supplied in the normalized and overaged as follows:
Normalize: 1650 °F ± 25 (899 °C ± 14) for 60 minutes ± 15 plus air cool
Overage: 1250 °F ± 25 (677 °C ± 14), for 16 hours minimum plus air cool

This followed by a three part heat treatment.
Solution Treatment: 1625°F +/-25°F (885°C +/-14°C) for 1 hour, followed by a controlled quench.
Cold Stabilization: Cool to –100 °F ± 15 (-73 °C ± 8) for 1 hour minimum, air warm
Ageing (standard): 900°F +/-10°F (482°C +/-6°C) for 5 hours, air cool

Typical Mechanical Properties

Material	Tensile Strength MPa	Yield Strength Mpa	Elongation (%)	Reduction of Area %	Hardness HRC
AerMet® 100 Longitudinal *	1931	1620	10	55	53
AerMet® 100 Transverse *	1931	1620	8	45
AerMet® 100 Longitudinal**	1965	1724	14	65
AerMet® 100 Transverse**	1965	1724	13	55
Heat Treatment 1625°F (885°C) 1 hour, air cooled, -100°F (-73°C) I hour, aged 900°F (482°C) 5 hours * Minimum values as per AMS 6532 ** Typical values

 

Maraging Steel 250 / C250 (AMS 6512 / BS S162)

Alloy 250 (UNS K92890 / Maraging 250) is an age-hardenable iron-nickel steel. Alloy 250 combines ultra-high strength (1800MPa), good toughness, readily machinable in pre-aged condition, excellent transverse properties and resistance to crack propagation. C250 is used for missile and ejector systems, slat tracks and drive shafts.

Chemical Composition Limits

Weight%

Ni

Co

Mn

Si

C

Al

Mo

S

P

Ti

Fe

Cr

Cu

C250

17.0 / 19.0

7.0 / 8.5

0.10 max

0.10 max

0.03 max

0.05 / 0.15

4.6 / 5.2

0.010 max

0.010 max

0.3 / 0.5

Bal

0.50

0.50

Typical Mechanical Properties

Material	Condition	Ultimate Tensile (min)		Yield Strength (Min)		Elongation in 4D % (min)	Hardness
		Mpa	Ksi	Mpa	Ksi
Alloy Maraging C250	After Maraging heat treatment 900°F	1758	255	1724	250	6	≥ 48 HRC

 

Maraging Steel 300/ C300 (AMS 6514, AMS 6521)

Maraging 300 is an age hardenable (maraging) iron nickel stainless steel. Maraging 300 has exceptional strength, toughness and is resistant to crack propagation. Maraging 300 is used for tooling, transmission shafts, autosport components and light aircraft landing gear.

Chemical Composition Limits
Weight%	C	Si	Mn	S	P	Co	Ni	Mo	Ti	Al	Fe
Maraging 300	0.03 max	0.10 max	0.10 max	0.010 max	0.010 max	8.0-9.5	18.0-19.0	4.6-5.2	0.55-0.80	0.05-0.15	Bal

Typical Mechanical Properties

Material	0.2 % Yield Strength ksi	Ultimate Tensile Strength ksi	Elongation in 4D(%)	Reduction of Area %	Hardness Rc
Maraging 300, Solution Annealed 1500° F (816°C), 1hr, AC	120	150	16	70	30
Solution Annealed Plus Aged 900 ° F (482°C), 3 hrs AC	280	290	8	40	52

 

Maraging Steel 350/ C350 (AMS 6515 / MIL-S-46850)

Maraging 350 is a nickel maraging steel which contains Cobalt as the primary strengthening agent. Maraging 350 has excellent mechanical properties, workability and heat treatment characteristics. Maraging 350 is used for missile and rocket motor cases, landing and takeoff gear components, high performance shafting, gears and fasteners.

Chemical Composition Limits

Weight%

Ni

Co

Mn

Si

C

B

P

S

Al

Mo

Ti

Zr

Maraging 350

18.50

12.0

0.10 max

0.10 max

0.03 max

0.003

0.01 max

0.01 max

0.10

4.8

1.40

0.01

Typical Mechanical Properties

Material	0.2 % Yield Strength ksi	Ultimate Tensile Strength ksi	Elongation in 4D(%)
Maraging 350	330	350	8

 

Nickel Alloy 20 / 20Cb3

Alloy 020 (UNS N08020, W. Nr 2.4660) is a nickel-iron-chromium alloy which has the addition of copper and molybdenum. With the additions of niobium Alloy 020 is stabilized against sensitization and resultant intergranular corrosion. Alloy 020 has excellent resistance to general corrosion, pitting and crevice corrosion and is commonly used for chemical, pharmaceutical and food processing, tanks, piping, heat exchangers, pumps, Kevlar production and much more.

Chemical Composition Limits
Weight %	Ni	Cr	Cu	Mo	Fe	C	Nb+Ta	Mn	P	S	Si
Alloy 20	32.0 - 38.0	19 - 21	3 - 4	2 - 3	bal	0.07 max	8 x C-1	2 max	0.045 max	0.035 max	1.0 max

Typical Mechanical Properties

Material	Yield Strength (0.2% Offset)		Tensile Strength		Elongation (%)
	psi	MPa	psi	MPa
Alloy 20	45,000	300	90,000	620	40

 

Alloy 28 (Wst 1.4563)

Alloy 28 (UNS N08028, W. Nr. 1.4563) is a nickel-iron-chromium alloy with additions of molybdenum and copper. It has excellent resistance to both reducing and oxidizing acids, to stress-corrosion cracking, and to localise attack such as pitting and crevice corrosion. The alloy are especially resistant to sulphuric and phosphoric acid. Used for chemical processing, pollution control equipment, oil and gas well piping, nuclear fuel reprocessing, acid production and pickling equipment.

Chemical Composition Limits
Weight%	Ni	Fe	Cr	Mo	Cu	Ti	C	Mn	S	Si	Al
Alloy 28	30-32	22 min	26-28	3-4	0.60-1.40	-	0.02 max	2 max	0.03 max	0.70 max	-

Typical Mechanical Properties

Material	Tensile Strength MPa	Yield Strength (0.2% Offset) MPa	Elongation (%)
Alloy 28 Tube	650	250	40

 

Alloy 22 / Hastelloy C-22 (UNS N06022)

Alloy 22 (UNS N06022) is the most versatile Nickel-Chromium-Molybdenum-Tungsten alloy with controlled Iron. Due to Alloy 22's content this alloy exhibits excellent resistance to both oxidising and reducing acid environments as well as those containing mixed acids. Alloy 22 is particularly useful for resistance to pitting and crevice corrosion in acid-halide environments. Alloy 22 is used in pickling chlorination, sulphonation plants, pollution control, chemical processing, marine and nuclear fuel reprocessing.

Chemical Composition Limits

Weight %

Ni

Cr

Mo

Fe

W

Co

V

C

Mn

S

Si

P

Alloy 22

Bal

20-22

12.5-14.5

2-6

2.5-3.5

2.5 max

0.35 max

0.015 max

0.50 max

0.02 max

0.08 max

0.02 max

Typical Mechanical Properties

Material	Yield Strength (0.2% Offset)		Tensile Strength		Elongation (%)
	ksi	MPa	ksi	MPa
Alloy 22 Bar	55	379	115	793	60