different materials properties

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Alloy Steels A286 Super Alloy Specifications: AMS 5525, AMS 5726, AMS 5731, AMS 5732, AMS 5734, AMS 5737, AMS 5804, AMS 5805, AMS 5853 AMS 5858, AMS 5895, ASTM A453 GRADE 660, ASTM A638 GRADE 660, GE B50T1181,GE B50T12, B50T81,UNS S66286 A286 is an age-hardenable iron base superalloy for applications requiring high strength from -320°F up to 1000°F long time, 1300-1500°F short time. Oxidation resistance is high for continuous service to 1500°F, intermittent to 1800°F. Aqueous corrosion resistance is comparable to 316L stainless. A286 is used for reasonably low cost when moderate strength and oxidation resistance are required at temperatures greater than suitable for stainless steels. Applications for A-286 are, Jet engine components, high temperature fastners, springs, non-magnetic cryogenic equipment and gas turbines. A286 AMS 5731, A286 AMS 5732, A286 AMS 5737 are readily available. A286 Chemistry, % Min Max Chromium 13.5 16 Nickel 24 27 Molybdenum 1 1.5 Cobalt - 1 Vanadium 0.1 0.5 Aluminum - 0.35 Titanium 1.9 2.35 Boron 0.003 0.01 Carbon - 0.08 Iron remainder Manganese - 2 Silicon - 1 Phosphorus - 0.025 Sulfur - 0.025 SAE 4340 Alloy Steel Specifications: AMS 6359, AMS 6409, AMS 6414, AMS 6415, AMS 6454, ASTM A29, ASTM A322, ASTM A331, ASTM

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Page 1: Different Materials Properties

Alloy Steels  A286 Super Alloy Specifications: AMS 5525, AMS 5726, AMS 5731, AMS 5732, AMS 5734, AMS 5737, AMS 5804, AMS 5805, AMS 5853AMS 5858, AMS 5895, ASTM A453 GRADE 660, ASTM A638 GRADE 660, GE B50T1181,GE B50T12, B50T81,UNS S66286

A286 is an age-hardenable iron base superalloy for applications requiring high strength from -320°F up to 1000°F long time, 1300-1500°F short time. Oxidation resistance is high for continuous service to 1500°F, intermittent to 1800°F. Aqueous corrosion resistance is comparable to 316L stainless. A286 is used for reasonably low cost when moderate strength and oxidation resistance are required at temperatures greater than suitable for stainless steels. Applications for A-286 are, Jet engine components, high temperature fastners, springs, non-magnetic cryogenic equipment and gas turbines. A286 AMS 5731, A286 AMS 5732, A286 AMS 5737 are readily available.  A286  Chemistry, %    

             Min 

                 Max 

Chromium             13.5                   16

Nickel             24                           27

Molybdenum             1                   1.5

Cobalt              -                   1

Vanadium             0.1                   0.5

Aluminum              -                   0.35

Titanium             1.9                   2.35

Boron             0.003                   0.01

Carbon              -                   0.08

Iron                      remainder

Manganese                     -                   2

Silicon              -                   1

Phosphorus              -                  0.025

Sulfur              -                  0.025 SAE   4340 Alloy Steel   Specifications: AMS 6359, AMS 6409, AMS 6414, AMS 6415, AMS 6454, ASTM A29, ASTM A322, ASTM A331, ASTM A506,ASTM A519, ASTM A646, ASTM A752, ASTM A829, MIL-S-5000, UNS G43400 AISI 4340 is a heat treatable, low alloy steel containing nickel, chromium and molybdenum. Alloy 4340 is known for its toughness and capability of developing high strength in the heat treated condition while retaining good fatigue strength. Typical applications for 4340 alloy steel are for structural use, such as aircraft landing gear, power transmission gears and shafts and other structural parts.  4340 Steel Aircraft Quality Vacuum Melted Bar  per AMS 6414 N&T (Normalized & Tempered)4340 Steel  Aircraft Quality Air Melt Bar per AMS 64154340 Steel Aircraft Quality Plate & Sheet per AMS 6454, ASTM A322 SAE 4340 Chemical composition: C=0.40%, Mn=0.7%, Mo=0.25%, Cr=0.8%, Ni-1.8% Property Value in metric unit Value in US unit Density 7.872 *10³ kg/m³ 491.4 lb/ft³ Modulus of elasticity 205 GPa 29700 ksi Thermal expansion (20 ºC) 12.6*10-6 ºCˉ¹ 7.00*10-6 in/(in* ºF) Specific heat capacity 477 J/(kg*K) 0.114 BTU/(lb*ºF) Thermal conductivity 44.6 W/(m*K) 309 BTU*in/(hr*ft²*ºF) Electric resistivity 2.48*10-7 Ohm*m 2.48*10-5 Ohm*cm Tensile strength (annealed) 745 MPa 108000 psi Yield strength (annealed) 472 MPa 68500 psi

Page 2: Different Materials Properties

Elongation (annealed) 28 % 22 % Hardness (annealed) 96 RB 96 RB Tensile strength (normalized) 1279 MPa 195500 psi Yield strength (normalized) 862 MPa 125000 psi Elongation (normalized) 20 % 12 % Hardness (normalized) 40 (112) RC (RB) 40 (112) RC (RB)     SAE 4130 Alloy SteelSpecifications: AMS 6345, AMS 6348, AMS 6350, AMS 6351, AMS 6360, AMS 6361,AMS 6362, AMS 6370, AMS 6528, ASTM A29, ASTM A322, ASTM A331, ASTM A506, ASTM A507, ASTM A513, ASTM A519, ASTM A646, ASTM A752, ASTM A829, MIL-S-18729, MIL-S-6758

 AISI 4130 is a low alloy steel containing molybdenum and chromium as strengthening agents. The carbon content is nominally 0.30% and with this relatively low carbon content the alloy is excellent from the fusion weldability standpoint. The alloy 4130 can be hardened by heat treatment. Typical applications for 4130 low alloy steel include structural use such as aircraft engine mounts and welded tubing applications. 4130 Steel Aircraft Quality Annealed per AMS-S-6758 4130 Steel Aircaft Quality Annealed per AMS 6348 4130 Steel Aircaft Quality Annealed per AMS 6370 4130 Steel Aircraft Quality Annealed per AMS 6345 N&T 4130 Steel Aircraft Quality Annealed per AMS 6350  SAE 4130 Chemical composition: C=0.30%, Mn=0.5%, Mo=0.20%, Cr=1.0% Property Value in metric unit Value in US unit Density 7.872 *10³ kg/m³ 491.4 lb/ft³ Modulus of elasticity 205 GPa 29700 ksi Thermal expansion (20 ºC) 11.2*10-6 ºCˉ¹ 6.20*10-6 in/(in* ºF) Specific heat capacity 477 J/(kg*K) 0.114 BTU/(lb*ºF) Thermal conductivity 42.7 W/(m*K) 296 BTU*in/(hr*ft²*ºF) Electric resistivity 2.23*10-7 Ohm*m 2.23*10-5 Ohm*cm Tensile strength (annealed) 561 MPa 81300 psi Yield strength (annealed) 361 MPa 52300 psi Elongation (annealed) 28 % 28 % Hardness (annealed) 82 RB 82 RB Tensile strength (normalized) 669 MPa 97000 psi Yield strength (normalized) 436 MPa 63300 psi Elongation (normalized) 25 % 25 % Hardness (normalized) 93 RB 93 RB     SAE   4140 Alloy Steel  Specifications: AMS 6349, AMS 6381, AMS 6382, AMS 6390, AMS 6395, AMS 6529, ASTM A193, ASTM A194, ASTM A29, ASTM A320, ASTM A322, ASTM A331, ASTM A506, ASTM A513, ASTM A519, ASTM A646, ASTM A711, ASTM A752, ASTM A829, UNS G41400 

Alloy 4140 is an oil-hardening steel of relatively high hardenability. Its chromium content provides good hardness penetration, and the molybdenum imparts uniformity of hardness and high strength. C4140 responds well to heat-treatment and is comparatively easily machined in the heat-treated condition. With a combination of such highly desirable properties as good strength and wear

Page 3: Different Materials Properties

resistance, excellent toughness, coupled with good ductility, and the ability to resist stress at elevated temperatures. Typical applications for 4140 alloy steel include shafts, gears, bolts, couplings, spindles, tool holders, sprockets, hydraulic machinery shafts, oil industry drill collars,Kelly bars, tools joints. 

C Mn P Si Mo Cr 0.38 - 0.43 0.75 - 1.00 max. 0.035 max. 0.04 0.15 - 0.35 0.8 - 1.10

     SAE 6150 Alloy Steel Specifications: AMS 6448, AMS 6450, AMS 6455, AMS 7301, ASTM A29, ASTM A322, ASTM A331, ASTM A519, ASTM A752, ASTM A829, MIL-S-8503, UNS G61500 

6150 is a fine grained, highly abrasion resistant carbon-chromium alloy steel. Very good shock resistance and toughness are also key properties of this alloy in the heat treated condition. Alloy 6150 Commonly employed in heavily stressed machinery parts including shafts, gears, pinions and also in hand tool components.   SAE 6150 Chemical composition: C=0.50%, Mn=0.8%, Cr=0.95%, V=0.15%min Property Value in metric unit Value in US unit Density 7.872 *10³ kg/m³ 491.4 lb/ft³ Modulus of elasticity 205 GPa 29700 ksi Thermal expansion (20 ºC) 12.2*10-6 ºCˉ¹ 6.78*10-6 in/(in* ºF) Specific heat capacity 477 J/(kg*K) 0.114 BTU/(lb*ºF) Thermal conductivity 46.6 W/(m*K) 323 BTU*in/(hr*ft²*ºF) Electric resistivity 2.34*10-7 Ohm*m 2.34*10-5 Ohm*cm Tensile strength (annealed) 667 MPa 96800 psi Yield strength (annealed) 412 MPa 59800 psi Elongation (annealed) 23 % 23 % Hardness (annealed) 92 RB 92 RB Tensile strength (normalized) 940 MPa 136300 psi Yield strength (normalized) 616 MPa 89300 psi Elongation (normalized) 21 % 21 % Hardness (normalized) 28 (104) RC (RB) 28 (104) RC (RB)    SAE 8620 Alloy Steel Specifications: AMS 6274,AMS 6276, AMS 6277, AMS 6375, ASTM A29, ASTM A322, ASTM A331, ASTM A506, ASTM A507, ASTM A513, ASTM A519, ASTM A646, ASTM A752, ASTM A829, MIL-S-8690, UNS G86200 

AISI 8620 an alloy steel designed for case hardening applications. The nickel imparts good toughness and ductility. The chromium and molybdenum contribute increased hardness penetration and wear, that may be carburized. The well balanced alloy content permits hardening to produce a hard wear resistant case combined with a core strength in the order of 125,000 PSI. It has excellent machinability and responds well to polishing applications.. With the balanced analysis, this steel provides, uniform case depth, hardness and wear properties, and gives the advantage of low distortion. Typical applications for alloy 8620 are caburized splined shafts, piston pins, cam shafts, guide pins, bushings, automotive differential pinions and transmissions, arbors, bearings, sleeves king pins, carburized gears, general engineering purposes.  SAE 8620 Chemical composition: C=0.20%, Mn=0.75%, Mo=0.2%, Cr=0.5%, Ni=0.55% Property Value in metric unit Value in US unit

Page 4: Different Materials Properties

Density 7.872 *10³ kg/m³ 491.4 lb/ft³ Modulus of elasticity 205 GPa 29700 ksi

Thermal expansion (20 ºC) 12.2*10-6 ºCˉ¹ 6.78*10-6 in/(in* ºF) Specific heat capacity 477 J/(kg*K) 0.114 BTU/(lb*ºF) Thermal conductivity 46.6 W/(m*K) 323 BTU*in/(hr*ft²*ºF)

Electric resistivity 2.34*10-7 Ohm*m 2.34*10-5 Ohm*cm Tensile strength (annealed) 536 MPa 77800 psi Yield strength (annealed) 357 MPa 55900 psi

Elongation (annealed) 31 % 31 % Hardness (annealed) 80 RB 80 RB

Tensile strength (normalized) 633 MPa 91800 psi Yield strength (normalized) 385 MPa 81800 psi

Elongation (normalized) 26 % 26 % Hardness (normalized) 90 RB 90 RB

  

Page 5: Different Materials Properties

Aluminum Alloy

Admired for its lightweight, high strength to weight ratio, high corrosion resistance, high thermal and electrical conductivity, and ease of machinability, aluminum is often referred to as "the wonder metal" and is considered the ideal material choice for a variety of today's critical applications.Aluminum Alloy is used extensively in modern aircraft due to its high strength to weight ratio. Aluminum Alloy  is available in cold finished and extruded rod and bar, plate, pipe and tubing, and sheet. We can provide material in standard sizes, or custom processed to meet your specific requirements.

Product details The International Alloy Designation System is the most widely accepted naming scheme for wrought alloys. Each alloy is given a four-digit number, where the first digit indicates the major alloying elements. 

1000 series are essentially pure aluminum with a minimum 99% aluminum content by weight and can be work hardened. 2000 series are alloyed with copper, can be precipitation hardened to strengths comparable to steel. Formerly referred to as

duralumin, they were once the most common aerospace alloys, but were susceptible to stress corrosion cracking and are increasingly replaced by 7000 series in new designs.

3000 series are alloyed with manganese, and can be work-hardened. 4000 series are alloyed with silicon. They are also known as silumin. 5000 series are alloyed with magnesium, derive most of their strength from work hardening. It is suitable for cryogenic

applications and low temperature work. However is susceptible to corrosion above 60°C. 6000 series are alloyed with magnesium and silicon, are easy to machine, and can be precipitation-hardened, but not to the

high strengths that 2000, and 7000 can reach. 7000 series are alloyed with zinc, and can be precipitation hardened to the highest strengths of any aluminum alloy. 8000 series is a category mainly used for lithium alloys.

Heat temper grades for Aluminum: O,T3,T351, T3511, T4, T42, T6, T651, T6511,T7,T8

Aerospace Alloys

The following aluminum alloys are commonly used in aircraft and other aerospace structures:

 7075 Aluminum Alloy  

7075 is an aluminum alloy, with zinc as the primary alloying element. It is strong, with good fatigue strength and average machinability, but has less resistance to corrosion than many other alloys. Its relatively high cost limits its use to applications where cheaper alloys are not suitable.7075 aluminum alloy's composition includes 5.1-6.1% zinc, 2.1-2.9% magnesium, 1.2-2.0% copper, and less than half a percent of silicon, iron, manganese, titanium, chromium, and other metals. It is commonly produced in several heat temper grades, 7075-O, 7075-T351, 7075-T6, 7075-T651, .

 7050 Aluminium Alloy

 7050 Aluminum alloy  is the premier choice for aerospace applications requiring the best combination of strength, stress corrosion cracking (SCC) resistance and toughness. It is particularly suited for plate applications in the 3 to 6 inch (76.20 to 152.40mm) thickness range. Alloy 7050 exhibits better toughness/corrosion resistance characteristics than alloy 7075. Because it is less quench sensitive than most aerospace aluminum alloys, 7050 retains its strength properties in thicker sections while maintaining good stress corrosion cracking resistance and fracture toughness levels.

 6061 Aluminum Alloy

 6061 is a precipitation hardening aluminum alloy, containing magnesium and silicon as its major alloying elements. It has good mechanical properties and exhibits good weldability. It is one of the most common alloys of aluminum for general purpose use.It is commonly available in pre-tempered grades such as, 6061-O (solutionized), 6061-T6 (solutionized and artificially aged), 6061-T651 (solutionized, stress-relieved stretched and artificially aged).

6063 Aluminum Alloy

Page 6: Different Materials Properties

 6063 is an aluminum alloy, with magnesium and silicon as the alloying elements. The standard controlling its composition is maintained by The Aluminum Association. It has generally good mechanical properties and is heat treatable and weldable. It is similar to the British aluminum alloy HE9.6063 is mostly used in extruded shapes for architecture, particularly window frames, door frames, and roofs. It is typically produced with very smooth surfaces fit for anodizing. It is commonly produced in several heat temper grades 6063-O, 6063-T1, 6063-T4, 6063-T5, 6063-T6.  It is also produced in tempers T52, T53, T54, T55, and T832, with various improved properties.

2024 Aluminum Alloy

 2024 is an aluminum alloy, with copper and magnesium as the alloying elements. It is used in applications requiring high strength to weight ratio, as well as good fatigue resistance. It is not weldable, and has average machinability. Due to poor corrosion resistance, it is often clad with aluminum or Al-1Zn for protection, although this may reduce the fatigue strength. 2024 is widely used in aircraft structures, especially wing and fuselage structures under tension.

2124 Aluminum Alloy Plate

2124 aluminum alloy plate was developed primarily for elevated temperature applications requiring guaranteed fracture toughness and improved short transverse properties in plate gauges over 1.0 inches (25.40 mm) thick. This plate alloy also exhibits good strength retention and creep resistance at elevated temperatures up to 350° F (177°C). Fracture toughness levels of 2124-T851 plate are substantially higher than 2024-T851. Alloy 2124-T851 is recommended for moderately elevated temperature applications (250-350°F, 121-177°C) requiring better short-transverse ductility and fracture toughness guarantees than are available with 2024-T851 plate. The primary use is machined fuselage bulkheads and wing skins in high-performance military aircraft. 

Marine Alloys

These alloys are used for boat building and shipbuilding, and other marine and salt-water sensitive shore applications. 

5052 Aluminum   Alloy

5052 is one of the higher strength non-heat-treatable alloys. It has a high fatigue strength and is a good choice for structures subjected to excessive vibration. The alloy has excellent corrosion resistance, particularly in marine atmospheres. The formability of the grade is excellent and in the annealed condition it offers higher strengths than 1100 or 3003 grades.

5083 Aluminum Alloy

5083 is an aluminum alloy suitable for cryogenic applications down to design temperatures of minus 165 °C, since alloys of this type do not show the ductile/brittle transition phenomenon. Apart from aluminum, the main other ingredient is magnesium.

5086 Aluminum   Alloy

5086 is an aluminum alloy, primarily alloyed with magnesium. It is not strengthened by heat treatment, instead becoming stronger due to strain hardening, or cold mechanical working of the material.Since heat treatment doesn't strongly affect the strength, 5086 can be readily welded and retain most of its mechanical strength. The good results with welding and good corrosion properties in seawater make 5086 extremely popular for building boat and yacht hulls.

Page 7: Different Materials Properties

Hastelloy X

  Hastelloy X is a Nickel-Chromium-Iron-Molybdenum alloy with an exceptional combination of oxidation resistance, ease of fabrication and high temperature strength.  It has also been found to be exceptionally resistant to stress corrosion cracking in petrochemical applications. Applications include gas turbine engine components, industrial furnace applications, chemical processing and petrochemical industry.  

Chemical Analysis of ALLOY X

C MN P S Si Cr Ni Mo Cu Co Cb Ti Al Fe W Other

.05 -.15 1.0 max 0.04 max 0.03 max 1.0 max 20.5 - 23.0 bal 8.0 10.0   0.5 - 2.5     . 17.0 20.0 0.2 1.0  

 

Specifications

Sheet/Plate Round Bar/Wire Pipe Tube Fittings Forgings

ASME SB-435AMS 5536

 

ASME SB-572AMS 5754AMS 5798

ASME SB-622ASME SB-829ASME SB-619ASME SB-775

ASME SB-626ASME SB-751ASME SB-622

AMS 5587

 

ASME SB-366 AMS

Hastelloy C 276

Hastelloy C 276, This Nickel-Molybdenum-Chromium alloy with the addition of Tungsten has excellent corrosion resistance in a wide range of corrosive media and is especially resistant to pitting and crevice corrosion. Applications include pollution control, chemical processing, waste treatment, pulp and paper production.  

Chemical Analysis of Alloy C276 C MN P S Si Cr Ni Mo Cu Co Cb+Ta Ti Al Fe

 .01 max

1.00 max

.04 max 

.03 max

.08 max

14.5 -16.5  rem

 15.0 - 17.0  

2.5 max       

4.0 - 7.0

 3.0 - 4.5

 

Specifications Sheet/Plate Round Bar Pipe Tube Fittings Forgings

ASME SB-575 ASME SB-574 ASME SB-622ASME SB-619ASME SB-775

ASME SB-622ASME SB-516ASME SB-626

ASME SB-366 ASME SB-564

 

Page 8: Different Materials Properties

Inconel 625 Alloy (Acid resistant, good weldability)Specifications: AMS 5599, AMS 5869, AMS 5666, AMS 5837, ASME SB-443, ASME SB-446

Inconel 625 a Nickel-Chromium-Molybdenum alloy with excellent corrosion resistance in a wide range of corrosive media, being especially resistant to pitting and crevice corrosion. Inconel 625 is a favorable choice for sea water applications. Applications include the marine and aerospace industries, chemical processing, nuclear reactors and pollution control equipment.

Chemical Analysis of ALLOY 625

C MN P S Si Cr Ni Mo Cu Co Cb+Ta Ti Al

 .10 .50 max .015 max .015 max .50 max 20.0 -23.0 

58.0 min  8.0 - 10.0

  1.0 max    0.40 max 0.40 max 5.0 max

 

 

Inconel 718 Alloy (Gamma double prime strengthened with good weldability)

Specifications: AMS 5596, AMS 5662, AMS 5663, AMS 5832 

Inconel 718 a Nickel-Chromium alloy being precipitation hardenable and having high creep-rupture strength at high temperatures to about 700°C. It has higher strength than Inconel X-750 and better mechanical properties at lower temperatures than Nimonic 90 and Inconel X-750. Applications include gas turbines, rocket motors, space craft, nuclear reactors and pumps.

Specifications for Inconel 625

International Specifications Sheet/Plate Round

Bar/Wire Pipe Tube Fittings Forgings

  BS 3072, BS 3074,  BS 3076, NA 21 DIN 17744, DIN 17750, DIN 17751, DIN 17752, DIN 17754. Werkstoff Nr. 2.4856 AFNOR NC 22 D Nb    

ASME SB-443 AMS 5599AMS 5869

ASME SB-446AMS 5666AMS 5837

ASME SB-444ASME SB-829ASME SB-775ASME SB-705

ASME SB-444ASME SB-829ASME SB-751ASME SB-704AMS 5581

ASME SB-366 ASME SB-564AMS 5666

Page 9: Different Materials Properties

Chemical Analysis of Alloy 718

C MN P S Si Cr Ni Mo Cu Co Cb+Ta

          19 52.5 3.05   1 max 5.13  

Inconel 600 Alloy (Solid solution strengthened)  Alloy 600 is a nonmagnetic, nickel-based high temperature alloy possessing an excellent combination of high strength, hot and cold workability, and resistance to ordinary form of corrosion.This alloy also displays good heat resistance and freedom from aging or stress corrosion throughout the annealed to heavily cold worked condition range.

 

Chemical Analysis of ALLOY 600 C MN P S Si Cr Ni Mo Cu Co Cb+Ta Ti Al Fe Other

 .15 max 1.0 max   .015 max .5 max 14.0 -17.0  72.0 min    .5 max         6.0 - 10.0  

Specifications Sheet/Plate Round Bar Pipe Tube Fittings Forgings

ASME SB-168AMS 5540

ASME SB-166AMS 5665

ASME SB-167ASME SB-829ASME SB-517ASME SB-775

ASME SB-163ASME SB-516ASME SB751

AMS 5580

ASME SB-366 ASME SB-564AMS 5665

 

Specifications for Inconel 718

Sheet / Plate  Round Bar Weld Wire

AMS 5596 AMS 5662AMS 5663

AMS 5832

Page 10: Different Materials Properties

Monel 400

A Nickel-Copper alloy with high strength and excellent corrosion resistance in a range of acidic and alkaline situations and especially suitable for reducing conditions. It also has good ductility and thermal conductivity. Applications include marine engineering, chemical and hydro-carbon processing equipment, heat exchangers, valves and pumps.

Chemical Analysis of ALLOY 400 C MN P S Si Cr Ni Mo Cu Co Cb+Ta Ti Al Fe Other Other

 .3 max 2.0 max   .024 max .5 max   63.0 min    28 - 34         2.5 max    

Specifications Sheet/Plate Round Bar Pipe Tube Fittings Forgings

ASME SB-127AMS 4544

ASME SB-164QQ-N-281

ASME SB-165ASME SB-829ASME SB-775ASME SB-725

ASME SB-165ASME SB-163ASME SB-730ASME SB-751

ASME SB-366 ASME SB-564

  Monel K500

  A precipitation-hardenable nickel-copper alloy that combines the corrosion resistance of MONEL alloy 400 with greater strength and hardness. It also has low permeability and is nonmagnetic to under -150°F (-101°C). Used for pump shafts, oil-well tools and instruments, doctor blades and scrapers,springs,valvetrim,fasterners and marine propeller shafts. 

Chemical Analysis of ALLOY K500 C MN P S Si Cr Ni Mo Cu Co Cb+Ta Ti Al Fe Other Other

.25max 1.5 max   .01 max .5 max   63.0 min    27 - 33       2.30-3.15  2.0 max    

Specifications Sheet/Plate Round Bar Pipe Tube Fittings Forgings QQ-N-286 ASME SB-865

AMS 4676

QQ-N-286

QQ-N-286

AMS 4676

 

Page 11: Different Materials Properties

Dupont Vespel

Vespel SP-1 - Unfilled. Maximum strength & elongation; lowest modulus & thermal conductivielectricalproperties. Vespel SP-21 - 15% graphite (by weight). Enhances inherent wear resistance, improves long term thermal stability. Vespel SP-22 - 40% graphite (by weight). Gives low coefficient of thermal expansion. Maximum creep resistance. Vespel SP-211 - 15% graphite and 10% TEFLON® fluorocarbon resin (by weight). Lowest static friction. Vespel SP-3 - 15% MoS2(by weight). Best wear performance in dry environments.

Vespel SP1 - First in the Dupont Vespel family of products - highly durable polyimides that deliver exceptional wear resistance, insulation, and a low coefficient of friction. Within the S Line, Vespel Parts and Shapes include many products with differing sets of attributes. 

Superior wear properties, best electrical and thermal insulation for:

InsulatorsValve seatsBallsGasketsPoppetsWafer clampingClamping ringsIn-chamber semiconductor parts

Benefits

 Unfilled resinOperating temps from cryogenic to 300°C (570°F)Ultra high purityMinimal electrical and thermal conductivityMaximum strength and elongationLow outgrassingImproved tech uniformity

Excellent wear for longer life

Vespel SP21 - If insulation is less important than low-friction properties, then you're looking for graphite-enhanced SP-21.  Automotive engineers love to use SP-21 for parts like thrust washers, bearings and seals - because the low-friction properties mean they work with or without lubrication.

Superior wear and low-friction properties for:

Thrust washersSeal ringsValve seatsBearingsSeals

Benefits 

Low wear at high bearing PVsLow coefficient of frictionLong-term thermal stabilityHigh stiffnessLow elongationOutstanding performance with or without lubricationGood strength and impact resistance

Page 12: Different Materials Properties

 

Vespel SP211 - Need a lower coefficient of friction than SP-21?  Not as concerned about thermal and wear resistance?  Then SP-211 could be your solution.  With Teflon PTFE as an additive, the coefficient of friction is further reduced, even without lubrication.

Lowest coefficient-of-friction parts in both dry and lubricated applications such as:

Sliding and linear bearingsBushingsThrust washersSeal rings

Benefits

Low wear at high bearing PVsLow coefficient of frictionTeflon filledSuperior unlubricated wearExcellent creep resistanceWear resistant up to 300 FGood tensile strength, elongation and flexural modulus

 Vespel SP22 - Designing with tight tolerances? SP-22 is the answer. When you've no room for error, SP-22's minimal thermal expansion and dimensional stability give you the freedom to create exactly what you've imagined.

Graphite-enhanced polyimides for tight-tolerance applications:  

BearingsThrust washersSeal RingsFerrulesSleevesStripsVanes

Benefits

Enhanced resistance to friction and wearMinimal thermal expansionMaximum thermal conductivitHigh temperature resistanceImproved dimensional and oxidative stabilityMinimum elongation

 Vespel SP3 - Of course, working in vacuum and dry environments has its own challenges. Aerospace engineers have to worry about extra difficulties like outgassing. But SP-3 has proven high performance in aerospace applications, largely due to its ultra-low outgassing. 

Excellent performance in vaccuum and dry environment applications including:

BushingsBearings

Page 13: Different Materials Properties

Piston RingsSealsGears

 

Benefits

Maximum wear and friction resistance in vaccums and other dry environmentsUltra-low outgrassingHigh performance in aerospace applications

Vespel SCP5000 - Materials designed for those demanding applications that require even more toughness, thermal stability and chemical resistance than ST-2010.  SCP-50094 has been put to the test in ultra-high-stress environments like aircraft engines.  So, it's ready for just about any design challenge.  But for better plasma resistance, dimensional stability and chemical resistance than SP-1.

Unfilled resin designed to improve strength, temperature resistance and dimensional stability in:

Semiconductor applicationsAutomotiveAircraft engine parts

Benefits

Ultra-high purityHigh thermal oxidative stabilityHigh stiffness

 Vespel SCP50094 - Materials designed for those demanding applications that require even more toughness, thermal stability and chemical resistance than ST-2010.  SCP-50094 has been put to the test in ultra-high-stress environments like aircraft engines.  So, it's ready for just about any design challenge.  But for better plasma resistance, dimensional stability and chemical resistance than SP-1, check out SCP-5000.

Unfilled resin designed to improve strength, temperature resistance and dimensional stability in:

Semiconductor applicationsAutomotiveAircraft engine parts

Benefits

Excellent thermal oxidative stabilityHigh stiffnessExcellent dimensional stabilityLowest CTE

 Vespel CR6100 - A Teflon® PFA body, reinforced with high-tensile-strength carbon fiber - CR-6100 offers excellent chemical resistance while exhibiting superior resistance to creep - even up to 288°C (550°F)!  It also provides excellent wear resistance and easy machinability for tight-tolerance application.  Add in a CTE lower than steel in the x-y plane (due to planar carbon-fiber reinforcement), and you have an ideal material for a variety of applications.

The ultimate in chemical and creep resistance for:

Page 14: Different Materials Properties

Valve plates, seats and sealsPump and compressor componentsGasketsThrust washersMechanical seals, wear strips and platesBearings and bushingsGrinding, lapping and polishing components

Benefits

Outstanding creep resistance - even up to 288°C (550°F)Excellent chemical and wear resistanceEasy machinability for tight-tolerance applicationsVirtually no water absorptionIdeal for chemical and petroleum processing applicationsCTE lower than steel

Vespel SP202 - DuPont Vespel SP202 polyimide parts and shapes decrease electrostatic loading in the manufacturing and handling of flat glass panels for liquid crystal displays and plasmas.  They are ideal for use with products that are handled in high-temperature, vacuums or reactive environments.

Parts such as placing pins or pads and roller guides made from Vespel® SP-202 combine consistent levels of electrical conductivity with an unmatched combination of thermal resistance, wear resistance, moisture resistance, toughness, strength and machinability. Vespel® SP-202 parts demonstrate surface resistivity below 10³ ohms/square. Results of further tests to establish other typical characteristics will be available in the near future. Vespel SP-202 provides electrical conductivity and thermal resistance for:  Pads/stoppers for glass/wafer contact in sputter/CVD chamberPads/balls for glass/wafer transfer process

Physical Properties  

AntistaticGood machinabilityExcellent thermal resistance

Vespel ST2010 - Want a material that wears like SP21, but with improved toughness and better thermal oxidative stability?  Consider ST2010 or ST2030.  These products even include better resistance to solvents, acids and bases.

Fiber-reinforced polyimide resins ideal for:

Valve seatsSealsBearingsWashersSeal ringsFerrulesWear pads

Benefits

Excellent wearHigh oxidativeOutstanding strength

Page 15: Different Materials Properties

 

Vespel ST2030 - Want a material that wears like SP21, but with improved toughness and better thermal oxidative stability?  Consider ST2010 or ST2030.  These products even include better resistance to solvents, acids and bases.

Fiber-reinforced polyimide resins ideal for:

Valve seatsSealsBearingsWashersSeal ringsFerrulesWear pads

Benefits

Excellent wearHigh oxidativeOutstanding strength

Page 16: Different Materials Properties

Stainless Steel

In metallurgy, stainless steel is defined as a steel alloy with a minimum of 11% chromium content by mass. Stainless steel does not stain, corrode, or rust as easily as ordinary steel (it stains less), but it is not stain-proof. It is also called corrosion-resistant steel or CRES when the alloy type and grade are not detailed, particularly in the aviation industry. There are different grades and surface finishes of stainless steel to suit the environment to which the material will be subjected in its lifetime. Stainless steel differs from carbon steel by the amount of chromium present. Carbon steel rusts when exposed to air and moisture. This iron oxide film is active and accelerates corrosion by forming more iron oxide. Stainless steels have sufficient amounts of chromium present so that a passive film of chromium oxide forms which prevents further surface corrosion and blocks corrosion from spreading into the metal's internal structure.

 There are different types of stainless steels: when nickel is added, for instance, the austenite structure of iron is stabilized. This crystal structure

makes such steels non-magnetic and less brittle at low temperatures. For greater hardness and strength, carbon is added. When subjected to

adequate heat treatment, these steels are used as razor blades, cutlery, tools, etc.

Significant quantities of manganese have been used in many stainless steel compositions. Manganese preserves an austenitic structure in the steel as

does nickel, but at a lower cost.

Stainless steels are also classified by their crystalline structure:

  Austenitic, or 300 series, stainless steels comprise over 70% of total stainless steel production. They contain a maximum of 0.15% carbon, a

minimum of 16% chromium and sufficient nickel and/or manganese to retain an austenitic structure at all temperatures from

the cryogenic region to the melting point of the alloy. A typical composition of 18% chromium and 10% nickel, commonly known as 18/10

stainless. Similarly, 18/0 and 18/8 are also available. Super austenitic stainless steels, such as alloy AL-6XN and 254SMO, exhibit great

resistance to chloride pitting and crevice corrosion due to high molybdenum content (>6%) and nitrogen additions, and the higher nickel content

ensures better resistance to stress-corrosion cracking versus the 300 series. The higher alloy content of super austenitic steels makes them more

expensive. Other steels can offer similar performance at lower cost and are preferred in certain applications.

The low carbon versions of the Austenitic Stainless Steel, for example 316L or 304L, are used to avoid corrosion problem caused by welding. The

"L" means that the carbon content of the Stainless Steel is below 0.03%, this will reduce the sensitization effect, precipitation of Chromium Carbides

at grain boundaries, due to the high temperature produced by welding operation.

  Ferritic stainless steels are highly corrosion-resistant, but less durable than austenitic grades. They contain between 10.5% and 27% chromium

and very little nickel, if any, but some types can contain lead. Most compositions include molybdenum; some, aluminum or titanium. Common

ferritic grades include 18Cr-2Mo, 26Cr-1Mo, 29Cr-4Mo, and 29Cr-4Mo-2Ni. These alloys can be degraded by the presence of σ chromium, a

intermetallic phase which can precipitate upon welding.

  Martensitic stainless steels are not as corrosion-resistant as the other two classes but are extremely strong and tough, as well as

highly machineable, and can be hardened by heat treatment. Martensitic stainless steel contains chromium (12-14%), molybdenum (0.2-

1%), nickel (0-<2%), and carbon (about 0.1-1%) (giving it more hardness but making the material a bit more brittle). It is quenched and

magnetic.

  Precipitation-hardening martensitic stainless steels have corrosion resistance comparable to austenitic varieties, but can be precipitation

hardened to even higher strengths than the other martensitic grades. The most common, 17 4 PH, uses about 17% chromium and 4% nickel.

There is a rising trend in defense budgets to opt for an ultra-high-strength stainless steel when possible in new projects, as it is estimated that 2%

of the US GDP is spent dealing with corrosion. The Lockheed-Martin Joint Strike Fighter is the first aircraft to use a precipitation-hardenable

stainless steel—Custom 465—in its airframe.

  Duplex stainless steels have a mixed microstructure of austenite and ferrite, the aim being to produce a 50/50 mix, although in commercial alloys,

the mix may be 40/60 respectively. Duplex steels have improved strength over austenitic stainless steels and also improved resistance to

localized corrosion, particularly pitting, crevice corrosion and stress corrosion cracking. They are characterized by high chromium (19–28%)

Page 17: Different Materials Properties

and molybdenum (up to 5%) and lower nickel contents than austenitic stainless steels. The most used Duplex Stainless Steel are the 2205 (22%

Chromium, 5% Nickel) and 2507 (25% Chromium, 7% Nickel); the 2507 is also known as "Super Duplex" due to its higher corrosion

resistance.

Stainless Steel Grades

100 Series—austenitic chromium-nickel-manganese alloys Type 101—austenitic that is hardenable through cold working for furniture Type 102—austenitic general purpose stainless steel working for furniture 200 Series—austenitic chromium-nickel-manganese alloys Type 201—austenitic that is hardenable through cold working Type 202—austenitic general purpose stainless steel 300 Series—austenitic chromium-nickel alloys Type 301—highly ductile, for formed products. Also hardens rapidly during mechanical working. Good weldability.

Better wear resistance and fatigue strength than 304. Type 302—same corrosion resistance as 304, with slightly higher strength due to additional carbon. Type 303—free machining   version of 304 via addition of   sulfur   and   phosphorus. Also referred to as "A1" in accordance with   ISO 3506.

Type 304— the most common grade; the classic 18/8 stainless steel. Also referred to as "A2" in accordance with   ISO 3506.

Type 304L— same as the 304 grade but contains less carbon to increase weldability. Is slightly weaker than 304. Type 304LN—same as 304L, but also nitrogen is added to obtain a much higher yield and tensile strength than 304L. Type 308—used as the filler metal when welding 304 Type 309—better temperature resistance than 304, also sometimes used as filler metal when welding dissimilar steels, along with   inconel. Type 316—the second most common grade (after 304); for food and   surgical stainless steel   uses; alloy addition of molybdenum prevents specific

forms of corrosion. It is also known as marine grade stainless steel due to its increased resistance to chloride corrosion compared to type 304. 316 is often used for building   nuclear reprocessing   plants.

Type 316L— extra low carbon grade of 316, generally used in stainless steel watches and marine applications due to its high resistance to corrosion. Also referred to as "A4" in accordance with   ISO 3506.

Type 316Ti—includes titanium for heat resistance, therefore it is used in flexible chimney liners. Type 321—similar to 304 but lower risk of   weld decay   due to addition of titanium. See also 347 with addition of niobium for desensitization during

welding. 400 Series—ferritic and martensitic chromium alloys Type 405— ferritic for welding applications Type 408—heat-resistant; poor corrosion resistance; 11% chromium, 8% nickel. Type 409—cheapest type; used for   automobile   exhausts; ferritic (iron/chromium only).

Type 410—martensitic (high-strength iron/chromium). Wear-resistant, but less corrosion-resistant. Type 416— 416 SS   is easy to machine due to additional sulfur Type 420—Cutlery Grade martensitic. Excellent polishability. Type 430—decorative, e.g., for automotive trim; ferritic. Good formability, but with reduced temperature and

corrosion resistance. Type 439—ferritic grade, a higher grade version of 409 used for catalytic converter exhaust sections. Increased

chromium for improved high temperature corrosion/oxidation resistance. Type 440—a higher grade of cutlery steel, with more carbon, allowing for much better edge retention when properly heat-treated. It can be

hardened to approximately   Rockwell  58 hardness, making it one of the hardest stainless steels. Due to its toughness and relatively low cost, most display-only and replica swords or knives are made of 440 stainless. Also known as razor blade steel. Available in four grades: 440A, 440B, 440C, and the uncommon 440F (free machinable). 440A, having the least amount of carbon in it, is the most stain-resistant; 440C, having the most, is the strongest and is usually considered more desirable in knife making than 440A, except for diving or other salt-water applications.

Type 446—For elevated temperature service 5 00 Series—heat-resisting chromium alloys 600 Series—martensitic   precipitation hardening  alloys

601 through 604: Martensitic low-alloy steels.   610 through 613: Martensitic secondary hardening steels.

614 through 619: Martensitic chromium steels. 630 through 635: Semi austenitic and martensitic precipitation-hardening stainless steels. Type 630 is most common PH stainless, better known as 17-4 PH; 17% chromium, 4% nickel. 650 through 653: Austenitic steels strengthened by hot/cold work. 660 through 665: Austenitic super alloys; all grades except alloy 661 are strengthened by second-phase precipitation. Type 2205— the most widely used duplex (ferritic/austenitic) stainless steel grade. It has both excellent corrosion

resistance and high strength.

Page 18: Different Materials Properties

 

Stainless Steel Designations

SAE designation

UNS designation

 % Cr  % Ni  % C  % Mn  % Si  % P  % S  % N Other

Austenitic

201 S20100 16–18 3.5–5.5 0.15 5.5–7.5 0.75 0.06 0.03 0.25 -

202 S20200 17–19 4–6 0.15 7.5–10.0

0.75 0.06 0.03 0.25 -

205 S20500 16.5–18 1–1.75 0.12–0.25

14–15.5 0.75 0.06 0.03 0.32–0.40

-

301 S30100 16–18 6–8 0.15 2 0.75 0.045 0.03 - -

302 S30200 17–19 8–10 0.15 2 0.75 0.045 0.03 0.1 -

302B S30215 17–19 8–10 0.15 2 2.0–3.0 0.045 0.03 - -

303 S30300 17–19 8–10 0.15 2 1 0.2 0.15 min

- Mo 0.60 (optional)

303Se S30323 17–19 8–10 0.15 2 1 0.2 0.06 - 0.15 Se min

304 S30400 18–20 8–10.50 0.08 2 0.75 0.045 0.03 0.1 -

304L S30403 18–20 8–12 0.03 2 0.75 0.045 0.03 0.1 -

304Cu S30430 17–19 8–10 0.08 2 0.75 0.045 0.03 - 3–4 Cu

304N S30451 18–20 8–10.50 0.08 2 0.75 0.045 0.03 0.10–0.16

-

305 S30500 17–19 10.50–13 0.12 2 0.75 0.045 0.03 - -

Page 19: Different Materials Properties

308 S30800 19–21 10–12 0.08 2 1 0.045 0.03 - -

309 S30900 22–24 12–15 0.2 2 1 0.045 0.03 - -

309S S30908 22–24 12–15 0.08 2 1 0.045 0.03 - -

310 S31000 24–26 19–22 0.25 2 1.5 0.045 0.03 - -

310S S31008 24–26 19–22 0.08 2 1.5 0.045 0.03 - -

314 S31400 23–26 19–22 0.25 2 1.5–3.0 0.045 0.03 - -

316 S31600 16–18 10–14 0.08 2 0.75 0.045 0.03 0.10 2.0–3.0 Mo

316L S31603 16–18 10–14 0.03 2 0.75 0.045 0.03 0.10 2.0–3.0 Mo

316F S31620 16–18 10–14 0.08 2 1 0.2 0.10 min

- 1.75–2.50 Mo

316N S31651 16–18 10–14 0.08 2 0.75 0.045 0.03 0.10–0.16

2.0–3.0 Mo

317 S31700 18–20 11–15 0.08 2 0.75 0.045 0.03 0.10 max 3.0–4.0 Mo

317L S31703 18–20 11–15 0.03 2 0.75 0.045 0.03 0.10 max 3.0–4.0 Mo

321 S32100 17–19 9–12 0.08 2 0.75 0.045 0.03 0.10 max Ti 5(C+N) min, 0.70 max

329 S32900 23–28 2.5–5 0.08 2 0.75 0.04 0.03 - 1–2 Mo

330 N08330 17–20 34–37 0.08 2 0.75–1.50

0.04 0.03 - -

347 S34700 17–19 9–13 0.08 2 0.75 0.045 0.030 - Nb + Ta, 10 x C min, 1 max

348 S34800 17–19 9–13 0.08 2 0.75 0.045 0.030 - Nb + Ta, 10 x C min, 1 max, but 0.10 Ta max; 0.20 Ca

Page 20: Different Materials Properties

384 S38400 15–17 17–19 0.08 2 1 0.045 0.03 - -

904L 19-23 23-28 0.02 2 1 0.045 0.035 - Mo 4-5, Cu 1-2

Ferritic

405 S40500 11.5–14.5 - 0.08 1 1 0.04 0.03 - 0.1–0.3 Al, 0.60 max

409 S40900 10.5–11.75

0.05 0.08 1 1 0.045 0.03 - Ti 6 x C, but 0.75 max

429 S42900 14–16 0.75 0.12 1 1 0.04 0.03 - -

430 S43000 16–18 0.75 0.12 1 1 0.04 0.03 - -

430F S43020 16–18 - 0.12 1.25 1 0.06 0.15 min

- 0.60 Mo (optional)

430FSe S43023 16–18 - 0.12 1.25 1 0.06 0.06 - 0.15 Se min

434 S43400 16–18 - 0.12 1 1 0.04 0.03 - 0.75–1.25 Mo

436 S43600 16–18 - 0.12 1 1 0.04 0.03 - 0.75–1.25 Mo; Nb+Ta 5 x C min, 0.70 max

442 S44200 18–23 - 0.2 1 1 0.04 0.03 - -

446 S44600 23–27 0.25 0.2 1.5 1 0.04 0.03 - -

Martensitic

403 S40300 11.5–13.0 0.60 0.15 1 0.5 0.04 0.03 - -

410 S41000 11.5–13.5 0.75 0.15 1 1 0.04 0.03 - -

414 S41400 11.5–13.5 1.25–2.50

0.15 1 1 0.04 0.03 - -

416 S41600 12–14 - 0.15 1.25 1 0.06 0.15 - 0.060 Mo (optional)

Page 21: Different Materials Properties

min

416Se S41623 12–14 - 0.15 1.25 1 0.06 0.06 - 0.15 Se min

420 S42000 12–14 - 0.15 min 1 1 0.04 0.03 - -

420F S42020 12–14 - 0.15 min 1.25 1 0.06 0.15 min

- 0.60 Mo max (optional)

422 S42200 11.0–12.5 0.50–1.0 0.20–0.25

0.5–1.0 0.5 0.025 0.025 - 0.90–1.25 Mo; 0.20–0.30 V; 0.90–1.25 W

431 S41623 15–17 1.25–2.50

0.2 1 1 0.04 0.03 - -

440A S44002 16–18 - 0.60–0.75

1 1 0.04 0.03 - 0.75 Mo

440B S44003 16–18 - 0.75–0.95

1 1 0.04 0.03 - 0.75 Mo

440C S44004 16–18 - 0.95–1.20

1 1 0.04 0.03 - 0.75 Mo

Heat resisting

501 S50100 4–6 - 0.10 min 1 1 0.04 0.03 - 0.40–0.65 Mo

502 S50200 4–6 - 0.1 1 1 0.04 0.03 - 0.40–0.65 Mo

Martensitic Precipitation Hardening

630 (17-4 PH)  S17400 15-17 3-5 0.07 1 1 0.04 0.03 - Cu 3-5, Ta 0.15-0.45 

 

Page 22: Different Materials Properties

15-5 PH Stainless Steel

Specification: AMS 5862, AMS 5659, AMS 5826, ASTM A 564, ASTM SA 564, ASTM A 693, ASME SA 693, ASTM A 705,  ASME SA 705 Please enable JavaScript to view this page content properly.

15-5PH Precipitation Hardening Stainless Steel Alloy (S15500) is a variant of the older 17-4 PH (S17400) chromium-nickel-copper precipitation hardening stainless steel. Both alloys exhibit high strength and moderate corrosion resistance. High strength is maintained to approximately 600°F (316°C). The 15-5 PH alloy was designed to have greater toughness than 17-4 PH, especially in the through-thickness (short transverse) direction. This improved toughness is achieved by reduced delta ferrite content and control of inclusion size and shape. The composition and processing of 15-5 PH alloy is carefully controlled to minimize its content of delta ferrite, which is present in the 17-4 PH stainless steel material. Inclusion control is done by consumable electrode remelting using the electro-slag remelting (ESR) process. The 15-5 PH alloy is martensitic in structure in the annealed condition and is further strengthened by a relatively low temperature heat treatment which precipitates a copper containing phase in the alloy. Like the 17-4PH alloy, the 15-5 PH stainless steel alloy requires only a simple heat treatment; a one step process conducted at a temperature in the range 900°F (482°C) to 1150°F (621°C) depending on the combination of strength and toughness desired. A wide range of properties can be produced by this one step heat treatment. Heat treatment in the 900°F (482°C) range produces highest strength, although slightly less than those of semi-austenitic alloys like S17700 (17-7 PH) or S15700 (15-7 PH). The latter precipitation hardening alloys generally require more steps to complete heat treatment. The15-5 PH alloy is generally better-suited for plate applications than are the semi austenitic alloys.

  Element                             Typical  

                Composition (Weight Percent) Carbon   0.04  Manganese   0.75  Phosphorus   0.020  Sulfur   0.005  Silicon   0.50  Chromium   14.5  Nickel   4.8  Columbium + Tantalum 0.30  Copper 3.5  Iron Balance  

 MECHANICAL PROPERTIES PER 15-5 PH AMS 5659, AMS 5862

15-5 PHCondition

ACondition

H 900Condition

H 1075Condition

H 1150

0.2% OffsetYield Strength

psi 110,000 175,000 135,000 125,000

(MPa) 760 1,200 930 860

Ultimate TensileStrength

psi 150,000 195,000 155,000 145,000

(MPa) 1,030 1,340 1,070 1,000

Elongation(percentage in 2")

8 15 15 15

HardnessRockwell C scale

33 43 31 28

Page 23: Different Materials Properties

17-4 PH Stainless Steel

Specification: AMS 5604, AMS 5622, AMS 5643, AMS 5825, AMS 5827, AMS 7474, ASTM A 564, ASME SA 564,  ASTM A 693,  ASME SA 693, ASTM A 705, ASME SA 705

17-4PH Precipitation Hardening Stainless Steel Alloy (S17400), Type 630, is a chromium-nickel-copper precipitation hardening stainless steel used for applications requiring high strength and a moderate level of corrosion resistance. High strength is maintained to approximately 600°F (316°C).The 17-4 PH stainless steel alloy is martensitic in structure in the annealed condition and is further strengthened by a low temperature treatment which precipitates a copper containing phase in the alloy. In comparison to many alloys in the precipitation hardening family, the S17400 (17-4 PH) alloy requires a simple heat treatment; a one step process conducted at a temperature in the range 900°F (482°C) to 1150°F (621°C) depending on the combination of strength and toughness desired. A wide range of properties can be produced by this one step heat treatment.

  Element                   Typical

                  Composition (Weight Percent) Carbon   0.04

Manganese   0.40

Phosphorus   0.020 Sulfur   0.005

Silicon   0.50 Chromium   15.5

Nickel   4.5

Columbium + Tantalum 0.30 Copper 3.50 Iron Balance

 MECHANICAL PROPERTIES PER 17-4 PH AMS 5643, AMS 5604

Condition Yield Strength Ultimate Tensile Strength Elongation (%) (Rockwell) Hardness

A psi 110,000 MPa  760 psi 150,000 MPa 1,030 8 33 (C)

H 950 psi 180,000 MPa 1,240 psi 195,000 MPa 1,340 10 43 (C)

H 1075 psi 160,000 MPa 1,100 psi 190,000 MPa 1,310 10 42 (C)

H 1150 psi 160,000 MPa 1,100 psi 190,000 MPa 1,310 10 42 (C)

PH13-8MO Alloy

Specification: AISI  632, AMS 5629, AMS 5864, ASTM A564, ASMT A693, ASTM A705, UNS S13800, XM-13

General13-8 Stainless Steel [PH 13-8 Mo (tm),Vasco13-8 (tm)(UNS S13800) is a precipitation hardening stainless steel that combines excellent strength, good toughness, and good general corrosion resistance. It is a through-hardening alloy, which allows it to be used in parts with large cross sections, where yield strengths in excess of 200 ksi. (1,380 MPa) may be required. Good transverse toughness properties are achieved by tight chemical composition control (to prevent the formation of delta phase), low carbon content (to minimize grain boundary precipitation), and double vacuum melting (to reduce alloy segregation). Since the rate of cooling from the solution temperature is not critical, large cross sections can be air-cooled. This alloy is produced by a primary vacuum induction melt process (VIM), followed by a consumable vacuum arc remelting (VAR) step. Typical uses are aircraft parts, rocket engine mounts, nuclear reactor parts, landing gear components, high performance shafts, and petrochemical parts that require high strength combined with good resistance to stress corrosion.

SpecificationsPH 13-8 Mo AMS 5629 - Bars, forgings, rings, and extrusionsPH 13-8 Mo AMS 5864 - Plate

Page 24: Different Materials Properties

Physical propertiesMelting Range: 2,560 to 2,680 F (1,404 to 1,471 C)Density: 0.279 lbs/in3 (7.76 gm/cc)Heat TreatmentSolution treatment from 1,675 to 1,725 F (913 to 941 C) for 15 to 30 minutes at temperature. Air cool or oil quench to below 60F (15 C) to ensure complete transformation to martensite. Aging is normally carried out from 950 to 1,150 F (510 to 621 C), depending upon the desired final properties. Heat treatment is usually performed in air. Heat treatment of brazed components maybe done in inert atmospheres. Reducing atmospheres should not be used because of the potential for nitrogen contamination.

HARDNESSHardness in the solution annealed condition is approximately Rockwell C 33.

OXIDATION AND CORROSION RESISTANCEPH13-8MO alloy has excellent oxidation resistance up to 1,500 F (816 C). Corrosion resistance decreases slightly as the aging temperature is raised. This alloy has the best resistance to stress corrosion cracking of all of the precipitation hardenable stainless steels. Its resistance to general corrosion is greatest in the fully-hardened condition. The alloy shows very little rusting when exposed to a 5 percent salt fog at 95 F (35 C).

FORGEABILITY/ FORMABILITYPH13-8MO alloy has good hot working characteristics, and can be forged over a wide temperature range. Temperatures up to 2,200°F(1,204 C) may be used. For optimum properties, forging temperature should not exceed 1,900 F(1,038 C). Hot working shouldnot be done below 1,700 F (927 C). After forging, parts should be cooled to room temperature, then solution treated prior to aging.The alloy can be cold formed in the annealed condition, utilizing conventional cold forming techniques.

MACHINABILITYPH 13-8 MO alloy can be machined in both the annealed and hardened conditions. In the annealed condition, usemachine speeds 20 to 30 percent lower than those used on 304 stainless steel.

WELDABILITYPH13-8MO alloy is normally welded using inert gas tungsten arc techniques, although most other welding processes may be used. These include plasma arc, electron beam, gas metal arc, and shielded metal arc processes. Helium is the preferred shielding gas.

SPECIAL PRECAUTIONSAll lubricants and coolants, particularly sulfur-bearing, should be removed prior to heat treatment, brazing and pickling. 

 

Page 25: Different Materials Properties

Titanium

Titanium alpha-beta alloy, Grade 5 (Ti-6Al-4V)  Specifications: AMS 4905, AMS 4906, AMS 4911, AMS 4920, AMS 4928, AMS 4930, AMS 4934, AMS 4935, AMS 4954,  AMS 4965, AMS 4967, ASTM B265, ASTM B348, ASTM B381, DMS 1570, MIL-F-83142,MIL-T-81556,MIL-T-81915, MIL-T-9046, MIL-T-9047, UNS R56400

 Ti 6AL-4V is known as the workhorse of the titanium industry because it is by far the most common Ti alloy, accounting for more than 50 % of total titanium usage. it is an alpha-beta alloy that is heat treatable to achieve moderate increase in strength. Ti 6AL-4V offeres a combination of high strength, light weight, formability and corrosion resistance which have made it a world standard in aerospace applications. Some of the many applications where this alloy has been used include aircraft turbine engine components, aircraft structural components, aerospace fasteners, high performance automotive parts, marine applications, medical devices, and sports equipment. Titanium α-β alloy, Grade 5 (Ti-6Al-4V) Chemical composition: O=0.08% max., Al=6%, V=4%, Ti balance Property Value in metric unit Value in US unit Density 4.43 *10³ kg/m³ 277 lb/ft³ Modulus of elasticity 114 GPa 16500 ksi Thermal expansion (20 ºC) 9.5*10-6 ºCˉ¹ 5.0*10-6 in/(in* ºF) Specific heat capacity 565 J/(kg*K) 0.135 BTU/(lb*ºF) Thermal conductivity 6.6 W/(m*K) 45.6 BTU*in/(hr*ft²*ºF) Electric resistivity 171*10-8 Ohm*m 171*10-6 Ohm*cm Tensile strength (annealed) 1000 MPa 145000 psi Yield strength (annealed) 910 MPa 132000 psi Elongation (annealed) 18 % 18 % Hardness (annealed) 36 HRC 36 HRC Tensile strength (prec. hard.) 1172 MPa 170000 psi Yield strength (precip. hard) 1103 MPa 160000 psi Elongation (precip. hardened) 10 % 10 % Hardness (precipit. hardened) 41 HRC 41 HRC Solution temperature 900 ºC 1650 ºF Aging temperature 510 ºC 950 ºF Aging time 4-8 hrs. 4-8 hrs. Liquidus temperature 1660 ºC 3020 ºF Solidus temperature 1605 ºC 2920 ºF Beta Transus temperature 996 ºC 1825 ºF

Page 26: Different Materials Properties

Carbon Steel     Tool Steel Stainless Steel Nickel, Cobalt, Special Alloys

1008 A2 300 Series A-286, AM-355

1010 A6 301 Deltalloy

1018 A10 302 Custom 450, 455

1020 A514 303 Ferralium 255

1040 D2, D3, D5, D6 304, 304L Hastelloy B2, C276

1045 H11 306 Haynes 188, 230

1050 M2 309 Incoloy 800, 825,

1055 P20 310 901-200-20,

1060 S1 314 Inconel 600, 601, 617

1070 S5 316, 316L Inconel 625,  Inconel 718

1075 S7 321 722, 750, 751

1095 T1 322 Invar 36, 42

A36 W1, W2 347 Kovar

A656 (GR 80)   348 Rodar

Cor-Ten Special Grades 400 & 500 Series L605 (Haynes 25)

Free Max15 D6AC 403 Maraging 250

  A193 405 Maraging 300

Alloys AL6XNS 409 Maraging 350

  HY80-HY100 410 Monel 400 

4130 F-11 (1-1/4CR- 416 Monel 405

4135 1/2MO) 418 (Greek Ascoloy) Monel 500 (K)

4140 F-22 (2-1/4CR- 420 Nickel 200, 201

41L40 1MO) 422 N155

4142 17-22-A 430F Nimonic 75

4145 17-22-AS 431 Rene 41

4150 17-22-AV 440A,C Udimet 500, 700

4155 Nitralloy 135N 446 Vascojet 1000

4160 SA, A-516, GR 70 904L Waspaloy

4215 SA, A-516, GR 65 Zirconium

4320 SA, A-204, GR B 20 CB 

4330, 4330M SA, A-387, GR 5   Copper Alloys

4335 SA, A-387, GR 9 Aluminum Alloys  C18200

4340, 4340M SA, A-387, GR11   Alum Brz C 613

4615 SA, A-387, GR 12   Alum Brz 614, 20CU

4620 SA, A-387, GR 22 1100, 1144, 1145, Alloy 182

4630 Maxel 2014, 2024, 2219 Alloy 932

4640 Molybdenum 3003,  5052 Ni Alum Brz C623, C624,

4720 Tantalum 5083, 5086, C630, C632

4750 Magnesium 6061,6063 Copper Ni C 706(90/10)

5150 Niobium 7050 C715(70/30), C172

Page 27: Different Materials Properties

52100 MP35N 7075 C17200

6120 A182 7475 PH Grades

6140 A234    

6145 A242 Titanium 13-8MO

6150 A333 Commercially Pure 15-3PH

8620 A335 3AL-2.5V 15-5PH

8630 Stellite 5AL-2.5SN 15-7MO

8640 Tungsten 6AL-2SN-4ZR-2MO 17-4PH

8642 HY-TUF 6AL-2SN-4ZR-6MO 17-7PH

8645 Telcut 40 6AL-4V 17-22PH

8720 Aermet 100 6AL-4V Eli  

8735 Zinc 6A1-6V-2SN Valve/Flange/Fittings

8740 8AL-1MO-1V Call for availability

8750 13.5V-11CR-3AL

9010 15-3-3-3

10-3-3-3

Ti-17