Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
General: Maraging is a 18% nickel, cobalt strengthened steel (C-type), with excellent mechanical properties, workability and heat
treatment characteristics.
Applications: Typical applications for maraging include missile and rocket motor cases, landing and takeoff gear, munitions,
aerospace, extrusion tooling, die casting, high performance shafting, gears and fasteners.
Composition:
C Mn Si P S NI
0.03 max 0.10 max 0.10 max 0.010 max 0.010 max 18.00-19.00
Co Mo Ti Al Cr Cu
11.50-12.50 4.60-5.20 1.30 -1.60 0.05-0.15 0.50 max 0.50 max Fe Bal
Material Melt Method: Maraging melt method is a VIM (Vacuum Induction Melt) + VAR (Vacuum Arc Remelt)
As Shipped Condition: Maraging is supplied in the annealed and descaled condition. The alloy is very tough, relatively soft (38
Rc Max.), therefore, readily machined and formed.
*Bar Tolerances: .250” - .499” .500” - .999” 1.000” – 3.625” 3.626” – 6.000” 6.001” – 8.000” 8.001” – 10.000”
-.000/+.005 -.000/+.010 -.000/+.031 -.000/+.047 -.000/+.063 -.000/+0.078
Minimum Properties after Aging:
Hardness ……………… 56 Rc Charpy V-notch ……… 6 ft/lbs. min Reduction of Area ……. 25%
Elongation ……………. 2.8% Yield Strength …………. 330 ksi Fracture Toughness ….. 25
Physical Properties:
Density………………………………… .289 lbs./cu. In
Average Coefficient of Thermal Expansion (70 – 900 F) ……………… 5.6 x 10 -6 in/in. F
Heat Treatment Aging Process: (Non Die Casting Applications)
Material is to be heat treated to 900 F +/- 10 holding at temperature for 6 hours then cooling at room air temperature. During the aging
treatment maraging shrinks uniformly and predictably on all dimensions .001 in/in
Heat Treatment Aging Process: (Die Casting Applications)
Following the rough machining of the die, anneal at 1500-1525 F for 1 hour per inch of thickness is recommended. After finish
machining, an aging heat treatment of 980-1000 F for 6 hours is recommended.
Machining:
Maraging steel in the annealed condition is comparable to 4340. However, when maraging is aged, the type of cutting tool and speeds
change. Rigid equipment, firm tool supports, sharp tools and abundant coolant are essential.
Welding:
Maraging is weld able without preheat, in both the annealed and aged condition. Only an aging heat treatment is needed to restore in the
weld.
Standards:
*Mil-S-46850D
*FIDES product is not supplied to the dimensional tolerances of MIL-S-46850D.
*The information, data and specifications presented here are representative only, and are not guaranteed values. Material or products
applications described are solely for illustrative purposes and should not be construed as express or implied warranties for fitness for these
or other applications.
Wednesday, June 29, 2011
MARAGING (C) 300
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
General: Maraging is a 18% nickel, cobalt strengthened steel (C-type), with excellent mechanical properties, workability and heat
treatment characteristics.
Applications: Typical applications for maraging include missile and rocket motor cases, landing and takeoff gear, munitions,
aerospace, extrusion tooling, die casting, high performance shafting, gears and fasteners.
Composition:
C Mn Si P S NI
0.03 max 0.10 max 0.10 max 0.010 max 0.010 max 18.00-19.00
Co Mo Ti Al Cr Cu
8.50-9.50 4.60-5.20 0.50 -0.80 0.05-0.15 0.50 max 0.50 max Fe Bal
Material Melt Method: Maraging melt method is a VIM (Vacuum Induction Melt) + VAR (Vacuum Arc Remelt)
As Shipped Condition: Maraging is supplied in the annealed and descaled condition. The alloy is very tough, relatively soft (36
Rc Max.), therefore, readily machined and formed.
*Bar Tolerances: .250” - .499” .500” - .999” 1.000” – 3.625” 3.626” – 6.000” 6.001” – 8.000” 8.001” – 10.000”
-.000/+.005 -.000/+.010 -.000/+.031 -.000/+.047 -.000/+.063 -.000/+0.078
Minimum Properties after Aging:
Hardness ……………… 52 Rc Charpy V-notch ……… 12 ft/lbs. min Reduction of Area ……. 47%
Elongation ……………. 5.0% Yield Strength …………. 280 ksi Fracture Toughness ….. 60
Physical Properties:
Density………………………………… .289 lbs./cu. In
Average Coefficient of Thermal Expansion (70 – 900 F) ……………… 5.6 x 10 -6 in/in. F
Heat Treatment Aging Process: (Non Die Casting Applications)
Material is to be heat treated to 900 F +/- 10 holding at temperature for 6 hours then cooling at room air temperature. During the aging
treatment maraging shrinks uniformly and predictably on all dimensions .001 in/in
Heat Treatment Aging Process: (Die Casting Applications)
Following the rough machining of the die, anneal at 1500-1525 F for 1 hour per inch of thickness is recommended. After finish
machining , an aging heat treatment of 980-1000 F for 6 hours is recommended.
Machining:
Maraging steel in the annealed condition is comparable to 4340. However, when maraging is aged, the type of cutting tool and speeds
change. Rigid equipment, firm tool supports, sharp tools and abundant coolant are essential.
Welding:
Maraging is weld able without preheat, in both the annealed and aged condition. Only an aging heat treatment is needed to restore in the
weld.
Standards:
AMS 6514 ASTM A 538 *Mil-S-46850D UNS K93120
*DMI product is not supplied to the dimensional tolerances of MIL-S-46850D.
*The information, data and specifications presented here are representative only, and are not guaranteed values. Material or products
applications described are solely for illustrative purposes and should not be construed as express or implied warranties for fitness for these
or other applications.
Contact Us for More Informations
General: Maraging is a 18% nickel, cobalt strengthened steel (C-type), with excellent mechanical properties, workability and heat
treatment characteristics.
Applications: Typical applications for maraging include missile and rocket motor cases, landing and takeoff gear, munitions,
aerospace, extrusion tooling, die casting, high performance shafting, gears and fasteners.
Composition:
C Mn Si P S NI
0.03 max 0.10 max 0.10 max 0.010 max 0.010 max 18.00-19.00
Co Mo Ti Al Cr Cu
8.50-9.50 4.60-5.20 0.50 -0.80 0.05-0.15 0.50 max 0.50 max Fe Bal
Material Melt Method: Maraging melt method is a VIM (Vacuum Induction Melt) + VAR (Vacuum Arc Remelt)
As Shipped Condition: Maraging is supplied in the annealed and descaled condition. The alloy is very tough, relatively soft (36
Rc Max.), therefore, readily machined and formed.
*Bar Tolerances: .250” - .499” .500” - .999” 1.000” – 3.625” 3.626” – 6.000” 6.001” – 8.000” 8.001” – 10.000”
-.000/+.005 -.000/+.010 -.000/+.031 -.000/+.047 -.000/+.063 -.000/+0.078
Minimum Properties after Aging:
Hardness ……………… 52 Rc Charpy V-notch ……… 12 ft/lbs. min Reduction of Area ……. 47%
Elongation ……………. 5.0% Yield Strength …………. 280 ksi Fracture Toughness ….. 60
Physical Properties:
Density………………………………… .289 lbs./cu. In
Average Coefficient of Thermal Expansion (70 – 900 F) ……………… 5.6 x 10 -6 in/in. F
Heat Treatment Aging Process: (Non Die Casting Applications)
Material is to be heat treated to 900 F +/- 10 holding at temperature for 6 hours then cooling at room air temperature. During the aging
treatment maraging shrinks uniformly and predictably on all dimensions .001 in/in
Heat Treatment Aging Process: (Die Casting Applications)
Following the rough machining of the die, anneal at 1500-1525 F for 1 hour per inch of thickness is recommended. After finish
machining , an aging heat treatment of 980-1000 F for 6 hours is recommended.
Machining:
Maraging steel in the annealed condition is comparable to 4340. However, when maraging is aged, the type of cutting tool and speeds
change. Rigid equipment, firm tool supports, sharp tools and abundant coolant are essential.
Welding:
Maraging is weld able without preheat, in both the annealed and aged condition. Only an aging heat treatment is needed to restore in the
weld.
Standards:
AMS 6514 ASTM A 538 *Mil-S-46850D UNS K93120
*DMI product is not supplied to the dimensional tolerances of MIL-S-46850D.
*The information, data and specifications presented here are representative only, and are not guaranteed values. Material or products
applications described are solely for illustrative purposes and should not be construed as express or implied warranties for fitness for these
or other applications.
MARAGING (C) 250
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
General: Maraging is a 18% nickel, cobalt strengthened steel (C-type), with excellent mechanical properties, workability and heat
treatment characteristics.
Applications: Typical applications for maraging include missile and rocket motor cases, landing and takeoff gear, munitions,
aerospace, extrusion tooling, die casting, high performance shafting, gears and fasteners.
Composition:
C Mn Si P S NI
0.03 max 0.10 max 0.10 max 0.010 max 0.010 max 17.00-19.00
Co Mo Ti Al Cr Cu
7.00-8.50 4.60-5.20 0.30-0.50 0.05-0.15 0.50 max 0.50 max Fe Bal
Material Melt Method: Maraging melt method is a VIM (Vacuum Induction Melt) + VAR (Vacuum Arc Remelt)
As Shipped Condition: Maraging is supplied in the annealed and descaled condition. The alloy is very tough, relatively soft
(30/34 Rc), therefore, readily machined and formed.
*Bar Tolerances: .250” - .499” .500” - .999” 1.000” – 3.625” 3.626” – 6.000” 6.001” – 8.000” 8.001” – 10.000”
-.000/+.005 -.000/+.010 -.000/+.031 -.000/+.047 -.000/+.063 -.000/+0.078
Minimum Properties (After Heat Treatment):
Hardness ……………… Rc 48 Charpy V-notch ……… 15 ft/lbs Reduction of Area ……. 50%
Elongation ……………. 6.0% Yield Strength …………. 240 ksi Fracture Toughness ….. 75 KIC
Physical Properties:
Density………………………………… .289 lbs./cu. In
Average Coefficient of Thermal Expansion (70 – 900 F) ……………… 5.6 x 10 -6 in/in. F
Heat Treatment Aging Process: (Non Die Casting Applications)
Material is to be heat treated to 900 F +/- 10 holding at temperature for 6 hours then cooling at room air temperature. During the aging
treatment maraging shrinks uniformly and predictably on all dimensions .0009 in/in
Heat Treatment Aging Process: (Die Casting Applications)
Following the rough machining of the die, anneal at 1500-1525 F for 1 hour per inch of thickness is recommended. After finish
machining , an aging heat treatment of 980-1000 F for 6 hours is recommended.
Machining:
Maraging steel in the annealed condition is comparable to 4340. However, when maraging is aged, the type of cutting tool and speeds
change. Rigid equipment, firm tool supports, sharp tools and abundant coolant are essential.
Welding:
Maraging is weld able without preheat, in both the annealed and aged condition. Only an aging heat treatment is needed to restore in the
weld.
Standards:
AMS 6512 ASTM A 538 *Mil-S-46850D UNS K92890
*DMI product is not supplied to the dimensional tolerances of MIL-S-46850D.
*The information, data and specifications presented here are representative only, and are not guaranteed values. Material or products
applications described are solely for illustrative purposes and should not be construed as express or implied warranties for fitness for these
or other applications.
Contact Us for More Informations
General: Maraging is a 18% nickel, cobalt strengthened steel (C-type), with excellent mechanical properties, workability and heat
treatment characteristics.
Applications: Typical applications for maraging include missile and rocket motor cases, landing and takeoff gear, munitions,
aerospace, extrusion tooling, die casting, high performance shafting, gears and fasteners.
Composition:
C Mn Si P S NI
0.03 max 0.10 max 0.10 max 0.010 max 0.010 max 17.00-19.00
Co Mo Ti Al Cr Cu
7.00-8.50 4.60-5.20 0.30-0.50 0.05-0.15 0.50 max 0.50 max Fe Bal
Material Melt Method: Maraging melt method is a VIM (Vacuum Induction Melt) + VAR (Vacuum Arc Remelt)
As Shipped Condition: Maraging is supplied in the annealed and descaled condition. The alloy is very tough, relatively soft
(30/34 Rc), therefore, readily machined and formed.
*Bar Tolerances: .250” - .499” .500” - .999” 1.000” – 3.625” 3.626” – 6.000” 6.001” – 8.000” 8.001” – 10.000”
-.000/+.005 -.000/+.010 -.000/+.031 -.000/+.047 -.000/+.063 -.000/+0.078
Minimum Properties (After Heat Treatment):
Hardness ……………… Rc 48 Charpy V-notch ……… 15 ft/lbs Reduction of Area ……. 50%
Elongation ……………. 6.0% Yield Strength …………. 240 ksi Fracture Toughness ….. 75 KIC
Physical Properties:
Density………………………………… .289 lbs./cu. In
Average Coefficient of Thermal Expansion (70 – 900 F) ……………… 5.6 x 10 -6 in/in. F
Heat Treatment Aging Process: (Non Die Casting Applications)
Material is to be heat treated to 900 F +/- 10 holding at temperature for 6 hours then cooling at room air temperature. During the aging
treatment maraging shrinks uniformly and predictably on all dimensions .0009 in/in
Heat Treatment Aging Process: (Die Casting Applications)
Following the rough machining of the die, anneal at 1500-1525 F for 1 hour per inch of thickness is recommended. After finish
machining , an aging heat treatment of 980-1000 F for 6 hours is recommended.
Machining:
Maraging steel in the annealed condition is comparable to 4340. However, when maraging is aged, the type of cutting tool and speeds
change. Rigid equipment, firm tool supports, sharp tools and abundant coolant are essential.
Welding:
Maraging is weld able without preheat, in both the annealed and aged condition. Only an aging heat treatment is needed to restore in the
weld.
Standards:
AMS 6512 ASTM A 538 *Mil-S-46850D UNS K92890
*DMI product is not supplied to the dimensional tolerances of MIL-S-46850D.
*The information, data and specifications presented here are representative only, and are not guaranteed values. Material or products
applications described are solely for illustrative purposes and should not be construed as express or implied warranties for fitness for these
or other applications.
9310
Applications
High performance helicopter transmission gears, components.
Composition nominal wt. % C 0.11, Cr 1.2, Mn 0.55, Mo 0.12, Ni 3.3, P 0.013, S 0.013, Si 0.25
Specifications AMS 6260, 6265; MIL-S-7393.
ASTM A 29, A 331, A 519, A 646; BMS 7-249.
Density lb/in3 (gcm3) ASTM A 29, A 331, A 519, A 646; BMS 7-249.
0.284 (7.86)
Metallurgical Condition
1,650°F normalization
Tensile Strength ksi (MPa) 140 (966)
0.2% Yield Strength ksi (MPa) 130 (897)
Elongation % 15
Reduction in Area % 40
Hardness 36 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
A286
Applications
Jet engines, superchargers, missile components, fasteners, cryogenic equipment, nuclear, corrosive deep well hardware.
Composition nominal wt. % Al 0.18, B 0.006, C 0.04, Cr 14.8, Mn 1.0, Mo 1.3, Ni 25.5, P 0.02, S 0.015, Si 0.5, Ti 2.13, V 0.3
Specifications AMS 5525, 5731, 5732, 5734, 5737.
MIL-S-24550; ASTM A 453.
Density lb/in3 (gcm3) MIL-S-24550; ASTM A 453.
0.286 (7.92)
Metallurgical Condition
1,800°F + age
Tensile Strength ksi (MPa) 150 (1,035)
0.2% Yield Strength ksi (MPa) 110 (759)
Elongation % 25
Reduction in Area % 40
Hardness 32 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
4340
Applications
Rocket motor cases, ordnance hardware, aircraft structural components, transmission gears, components, fasteners.
Composition nominal wt. % C 0.41, Cr 0.8, Mn 0.7, Mo 0.25, Ni 1.9, P O.018, S 0.02, Si 0.23
Specifications AMS 6414, 6359, 6409, 6415, 6454; BMS 7-28.
ASTM A 29, A 320, A 322, A 331; MIL-S-5000.
Density lb/in3 (gcm3) ASTM A 29, A 320, A 322, A 331; MIL-S-5000.
0.283 (7.83)
Metallurgical Condition
1,650°F Q + T
Tensile Strength ksi (MPa) 250 (1,724)
0.2% Yield Strength ksi (MPa) 220 (1,517)
Elongation % 8
Reduction in Area % 18
Hardness 45 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
410
Applications
Compressor blades, turbine parts.
Composition nominal wt. % C 0.15, Cr 12.0, Mn 0.5, P 0.02, S 0.01, Si 0.5
Specifications AMS 5504, 5611, 5612, 5613; MS 83, 511.
ASTM A 276, A 511, A 565; PDS 10705BA-BC.
Density lb/in3 (gcm3) ASTM A 276, A 511, A 565; PDS 10705BA-BC.
0.278 (7.70)
Metallurgical Condition
1,700°F anneal
Tensile Strength ksi (MPa) 100 (690)
0.2% Yield Strength ksi (MPa) 90 (621)
Elongation % 22
Reduction in Area % 65
Hardness 90 HRB
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Titanium 6Al-2Sn-4Zr-6Mo
Applications
Intermediate-temperature jet engine applications. Blades, discs, spacers, seals. Standard, rotor/premium grades.
Composition nominal wt. % Al 6.0, C 0.10 max, Fe 0.10, H 0.015, Mo 6.0, N 0.02, O 0.12, Sn 2.0, Ti rem, Zr 4.0
Specifications AMS 4981.
MIL-T-9047, -83142.
Density lb/in3 (gcm3) MIL-T-9047, -83142.
0.168 (4.65)
Metallurgical Condition
1,625°F + age
Tensile Strength ksi (MPa) 170 (1,172)
0.2% Yield Strength ksi (MPa) 160 (1,104) Elongation %
10
Reduction in Area % 15
Hardness 38 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Titanium 6Al-2Sn-4Zr-2Mo
Applications
High-temp jet engines. Blades, dics, spacers, seals. High performance automotive valves. Standard, rotor/premium grades.
Composition nominal wt. % Al 6.0, C 0.10 max, Fe 0.05, H 0.015 max, Mo 2.0, N 0.04, O 0.2, Sn 2.0, Ti rem, Zr 4.0
Specifications AMS 4919, 4975, 4976; DMS 2275, 2287.
MIL-T-9046, -9047, -81556; GM 3104.
Density lb/in3 (gcm3) MIL-T-9046, -9047, -81556; GM 3104.
0.164 (4.54)
Metallurgical Condition
1,800°F + age
Tensile Strength ksi (MPa) 150 (1,035)
0.2% Yield Strength ksi (MPa) 140 (966) Elongation %
15
Reduction in Area % 30
Hardness 34 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Titanium 6Al-6V-2Sn
Applications
Airframes, jet engines, rocket engine cases, nuclear reactor compoenets, ordnance components.
Composition nominal wt. % Al 5.5, C 0.05, Cu 0.5, Fe 0.5, H 0.015 max, N 0.02, O 0.12, Sn 2.0, Ti rem, v 5.5
Specifications AMS 4918, 4936, 4937, 4971, 4978, 4979.
MIL-T-9047, -81556; DMS 1879, 1870, 1887.
Density lb/in3 (gcm3) MIL-T-9047, -81556; DMS 1879, 1870, 1887.
0.164 (4.54)
Metallurgical Condition
1,325°F anneal
Tensile Strength ksi (MPa) 140 (966)
0.2% Yield Strength ksi (MPa) 130 (897) Elongation %
15
Reduction in Area % 35
Hardness 35 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Titanium 6Al-4V
Applications
Blades, discs, rings, airframe, fasteners, components. Vessels, cases, hubs, forgings. Standard, rotor/premium grades.
Composition nominal wt. % Al 6.0, C 0.10 max, Fe 0.20 max, N 0.03, O 0.20 max, Ti rem, V 4
Specifications AMS 4920, 4928, 4965, 4967; MIL-T-9046, -9047, -81556; GM 3103.
ASTM B 348, B 381, F 1472; DMS 1583, 1570, 1536, 1592.
Density lb/in3 (gcm3) ASTM B 348, B 381, F 1472; DMS 1583, 1570, 1536, 1592.
0.160 (4.43)
Metallurgical Condition
1,300°F anneal
Tensile Strength ksi (MPa) 135 (931)
0.2% Yield Strength ksi (MPa) 125 (862) Elongation %
15
Reduction in Area % 30
Hardness 32 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Titanium CP-4 Grade 1
Applications
Airframe components, cryogenic vessels, heat exchangers, CPI equipment, condenser tubing, pickling baskets.
Composition nominal wt. % C 0.10 max, Fe 0.50 max, H 0.015 max, N 0.05 max, O 0.40 max, Ti rem
Specifications AMS 4901; MIL-T-9046,-9057.
ASTM F 67; ASTM B 265, 337, 338, 348, 381.
Density lb/in3 (gcm3) ASTM F 67; ASTM B 265, 337, 338, 348, 381.
0.163 (4.51)
Metallurgical Condition
1,300°F anneal
Tensile Strength ksi (MPa) 80 (552)
0.2% Yield Strength ksi (MPa) 70 (783)
Elongation % 15
Reduction in Area % 25
Hardness 100 HRB
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Titanium CP-3 Grade 2
Applications
Airframe skin, heat exchangers, cryogenic vessels, components for CPI equipment, condenser tubing, exhaust pipe shrouds.
Composition nominal wt. % C 0.10 max, Fe 0.30 max, H 0.015 max, N 0.05 max, O 0.35 max, Ti rem
Specifications AMS 4900; MIL-T-9046,-81556.
ASTM F 67; ASTM B 265, 337, 338, 348.
Density lb/in3 (gcm3) ASTM F 67; ASTM B 265, 337, 338, 348.
0.163 (4.51)
Metallurgical Condition
1,300°F anneal
Tensile Strength ksi (MPa) 65 (448)
0.2% Yield Strength ksi (MPa) 55 (379)
Elongation % 18
Reduction in Area % 30
Hardness 90 HRB
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Titanium CP-2 Grade 3
Applications
Airframe components, cryogenic vessels, heat exchangers, CPI equipment, condenser tubing, pickling baskets.
Composition nominal wt. % C 0.10 max, Fe 0.30 max, H 0.015 max, N 0.03 max, O 0.25 max, Ti rem
Specifications AMS 4902, 4921, 4942; MIL-T-9046,-81556.
ASTM F 67; ASTM B 265, 337, 338, 348.
Density lb/in3 (gcm3) ASTM F 67; ASTM B 265, 337, 338, 348.
0.163 (4.51)
Metallurgical Condition
1,300°F anneal
Tensile Strength ksi (MPa) 50 (345)
0.2% Yield Strength ksi (MPa) 40 (276)
Elongation % 20
Reduction in Area % 30
Hardness 80 HRB
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Titanium CP-1 Grade 4
Applications
Airframe components, cryogenic vessels, heat exchangers, CPI equipment, condenser tubing, pickling baskets.
Composition nominal wt. % C 0.10 max, Fe 0.20 max, H 0.015 max, N 0.03 max, O 0.18 max, Ti rem
Specifications MIL-T-81556.
ASTM B 265, 33, 338: ASTM F 67.
Density lb/in3 (gcm3) ASTM B 265, 33, 338: ASTM F 67.
0.163 (4.51)
Metallurgical Condition
1,300°F anneal
Tensile Strength ksi (MPa) 35 (241)
0.2% Yield Strength ksi (MPa) 25 (172)
Elongation % 24
Reduction in Area % 30
Hardness 70 HRB
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
TITANIUM and TITANIUM BASE ALLOYS
| Fides offers titanium and titanium base alloys in metal grades such as, Titanium CP-1 Grade 4, Titanium 6-4, Titanium 6-4 Eli and more. Click on a grade listed below to view its specifications. Mechanical properties are for typical room temperature. | |||||||||
|
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Inconel 718
Applications
Jet engine rings, discs, shafts, compressor blades, seals, spacers. Fasteners, nuclear, oil & gas components.
Composition nominal wt. % A1 0.5, C 0.02, Cb 5.3, Cr 19.0, Fe rem, Mo 3.1, Ni 54.0, Ti 0.9
Specifications AMS 5662, 5663, 5664, 5596, 5597; B50TF181, -14, -15.
MIL-N-24469; RDT m2-18T; ASTM B 637; LBO 170-186.
Density lb/in3 (gcm3) MIL-N-24469; RDT m2-18T; ASTM B 637; LBO 170-186.
0.296 (8.19)
Metallurgical Condition
1,800°F + age
Tensile Strength ksi (MPa) 195 (1,345)
0.2% Yield Strength ksi (MPa) 160 (1,104)
Elongation % 22
Reduction in Area % 35
Hardness 42 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Rene 41
Applications
Jet and rocket engines, torque rings, after burners, hardware.
Composition nominal wt. % A1 1.6, B 0.007, C 0.06, Co 11.0, Cr 19.0, Fe 3.0, Mo 9.75, Ni rem, Ti 3.15
Specifications AMS 5712, 5713.
Density lb/in3 (gcm3) 0.298 (8.24)
Metallurgical Condition
1,975°F + age
Tensile Strength ksi (MPa) 180 (1,241)
0.2% Yield Strength ksi (MPa) 115 (793)
Elongation % 20
Reduction in Area % 25
Hardness 36 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Waspaloy 5708
Applications
Turbine compressor blades and discs, shafts, spacers, fasteners, miscellaneous jet engine hardware.
Composition nominal wt. % A1 1.40, B 0.01, C 0.5, Co 13.0, Cr 19.5, Fe 1.0, Mo 4.3, Mi rem, Ti 3.0, Zr .07
Specifications AMS 5704, 5706, 5707, 5708, 5709, 5544.
ASTM B 637; SPS-M-175.
Density lb/in3 (gcm3) ASTM B 637; SPS-M-175.
0.296 (8.19)
Metallurgical Condition
1,850°F + age
Tensile Strength ksi (MPa) 185 (1,276)
0.2% Yield Strength ksi (MPa) 130 (897)
Elongation % 23
Reduction in Area % 25
Hardness 38 HRC
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
L-605
Applications
High temperature applications, jet engine components, devices in high fatigue service.
Composition nominal wt. % C 0.1, Co rem, Cr 20.0, Fe 0.5, Mn 1.7, Ni 10.0, W 15.0
Specifications AMS 5759, 5844.
ASTM F 90; B50T26
Density lb/in3 (gcm3) ASTM F 90; B50T26
0.333 (9.22)
Metallurgical Condition
2,200°F anneal
Tensile Strength ksi (MPa) 150 (1,035)
0.2% Yield Strength ksi (MPa) 60 (414)
Elongation % 60
Reduction in Area % 40
Hardness 80 HRB
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Inconel 625
Applications
Engine ducting, nozzles, thrust reverser assemblies, combustion systems, afterburner and spray bars, CPI and nuclear uses.
Composition nominal wt. % A1 0.3, C 0.05, Cb 3.7, Cr 21.5, Fe 2.5, Mo 9.0, Ni rem, Ti 0.3
Specifications AMS 5666, 5599.
EB 2949.
ASTM B 444, B 446.
Density lb/in3 (gcm3) EB 2949.
ASTM B 444, B 446.
0.305 (8.44)
Metallurgical Condition
1,700°F anneal
Tensile Strength ksi (MPa) 130 (897)
0.2% Yield Strength ksi (MPa) 70 (483)
Elongation % 40
Reduction in Area % 50
Hardness 90 HRB
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
C-276
Applications
High temperature applications also requiring good resistance to corrosive fluids such as liquids and combustion products.
Composition nominal wt. % C 0.01, C o.5, Cr 15.5, Fe 5.0, Mo 16.0, Ni rem, W 3.5
Specifications ASTM B 574, B 622.
AMS 5530, 5750.
Density lb/in3 (gcm3) AMS 5530, 5750.
0.323 (8.94)
Metallurgical Condition
2,050°F anneal
Tensile Strength ksi (MPa) 115 (793)
0.2% Yield Strength ksi (MPa) 45 (310)
Elongation % 65
Reduction in Area % 75
Hardness 80 HRB
Fides (China) Investment & Trading Co., Ltd
Contact Us for More Informations
Subscribe to:
Posts (Atom)