Alloy Steels A286 Super AlloySpecifications: 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, 13001500°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, % Chromium Nickel Molybdenum Cobalt Vanadium Aluminum Titanium Boron Carbon Iron Manganese Silicon Phosphorus Sulfur 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 Min 13.5 24 1 0.1 1.9 0.003 remainder - Max 16 27 1.5 1 0.5 0.35 2.35 0.01 0.08 2 1 0.025 0.025 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 6415 4340 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 7.872 *10³ kg/m³ Density 205 GPa Modulus of elasticity -6 12.6*10 ºCˉ¹ Thermal expansion (20 ºC) 477 J/(kg*K) Specific heat capacity 44.6 W/(m*K) Thermal conductivity Value in US unit 491.4 lb/ft³ 29700 ksi -6 7.00*10 in/(in* ºF) 0.114 BTU/(lb*ºF) 309 BTU*in/(hr*ft²*ºF) Electric resistivity Tensile strength (annealed) Yield strength (annealed) Elongation (annealed) Hardness (annealed) Tensile strength (normalized) Yield strength (normalized) Elongation (normalized) Hardness (normalized) 2.48*10-7 745 472 28 96 1279 862 20 40 (112) Ohm*m MPa MPa % RB MPa MPa % RC (RB) 2.48*10-5 108000 68500 22 96 195500 125000 12 40 (112) Ohm*cm psi psi % RB psi psi % RC (RB) SAE 4130 Alloy Steel Specifications: 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 7.872 *10³ kg/m³ Density 205 GPa Modulus of elasticity -6 11.2*10 ºCˉ¹ Thermal expansion (20 ºC) 477 J/(kg*K) Specific heat capacity 42.7 W/(m*K) Thermal conductivity -7 2.23*10 Ohm*m Electric resistivity 561 MPa Tensile strength (annealed) 361 MPa Yield strength (annealed) 28 % Elongation (annealed) 82 RB Hardness (annealed) 669 MPa Tensile strength (normalized) 436 MPa Yield strength (normalized) 25 % Elongation (normalized) 93 RB Hardness (normalized) Value in US unit 491.4 lb/ft³ 29700 ksi -6 6.20*10 in/(in* ºF) 0.114 BTU/(lb*ºF) 296 BTU*in/(hr*ft²*ºF) -5 2.23*10 Ohm*cm 81300 psi 52300 psi 28 % 82 RB 97000 psi 63300 psi 25 % 93 RB SAE 4140 Alloy Steel Specifications: AMS 6349, AMS 6381, AMS 6382, AMS 6390, AMS 6395, AMS 6529, ASTM A193, ASTM A194, ASTM ASTM A322.35 Cr 0. gears. coupled with good ductility. ASTM A320.10 SAE 6150 Alloy Steel Specifications: AMS 6448. It has excellent machinability and responds well to polishing applications. V=0. AMS 6450. MIL-S-8503. . hydraulic machinery shafts. 0. oil industry drill collars. Alloy 6150 Commonly employed in heavily stressed machinery parts including shafts. AMS 7301. ASTM A829. Typical applications for 4140 alloy steel include shafts.. Mn=0. UNS G61500 6150 is a fine grained.035 Si max.50%.15 . SAE 6150 Chemical composition: C=0. ASTM A711. Very good shock resistance and toughness are also key properties of this alloy in the heat treated condition.Kelly bars.78*10 in/(in* ºF) 0.43 Mn 0. Cr=0. highly abrasion resistant carbon-chromium alloy steel. UNS G41400 Alloy 4140 is an oil-hardening steel of relatively high hardenability. and the ability to resist stress at elevated temperatures.34*10-5 Ohm*cm 96800 psi 59800 psi 23 % 92 RB 136300 psi 89300 psi 21 % 28 (104) RC (RB) SAE 8620 Alloy Steel Specifications: AMS 6274. ASTM A331.95%.AMS 6276. spindles. ASTM A646. ASTM A752.1. ASTM A829.34*10-7 Ohm*m Electric resistivity 667 MPa Tensile strength (annealed) 412 MPa Yield strength (annealed) 23 % Elongation (annealed) 92 RB Hardness (annealed) 940 MPa Tensile strength (normalized) 616 MPa Yield strength (normalized) 21 % Elongation (normalized) 28 (104) RC (RB) Hardness (normalized) Value in US unit 491. ASTM A752. With the balanced analysis. ASTM A519. pinions and also in hand tool components. ASTM A829. ASTM A506. MIL-S-8690. ASTM A322. bolts. excellent toughness.1. ASTM A513.000 PSI. gears.8 . ASTM A331.15%min Property Value in metric unit 7.0. couplings.2*10 ºCˉ¹ Thermal expansion (20 ºC) 477 J/(kg*K) Specific heat capacity 46.8%. ASTM A331.0. AMS 6375. AMS 6277. uniform case depth.872 *10³ kg/m³ Density 205 GPa Modulus of elasticity -6 12.75 . 0. The well balanced alloy content permits hardening to produce a hard wear resistant case combined with a core strength in the order of 125. With a combination of such highly desirable properties as good strength and wear resistance. ASTM A519. ASTM A646.A29. AMS 6455. this steel provides. ASTM A513.00 P max.38 .6 W/(m*K) Thermal conductivity 2. that may be carburized. ASTM A29. ASTM A29. The chromium and molybdenum contribute increased hardness penetration and wear. ASTM A322. ASTM A519.04 Mo 0. and the molybdenum imparts uniformity of hardness and high strength. The nickel imparts good toughness and ductility. ASTM A506. sprockets.4 lb/ft³ 29700 ksi -6 6. Its chromium content provides good hardness penetration. UNS G86200 AISI 8620 an alloy steel designed for case hardening applications. C4140 responds well to heat-treatment and is comparatively easily machined in the heat-treated condition. ASTM A752. C 0.114 BTU/(lb*ºF) 323 BTU*in/(hr*ft²*ºF) 2. tool holders. tools joints. ASTM A507. bearings.2*10-6 ºCˉ¹ Thermal expansion (20 ºC) 477 J/(kg*K) Specific heat capacity 46. bushings. and gives the advantage of low distortion.hardness and wear properties.34*10-5 Ohm*cm 77800 psi 55900 psi 31 % 80 RB 91800 psi 81800 psi 26 % 90 RB .2%. general engineering purposes.34*10-7 Ohm*m Electric resistivity 536 MPa Tensile strength (annealed) 357 MPa Yield strength (annealed) 31 % Elongation (annealed) 80 RB Hardness (annealed) 633 MPa Tensile strength (normalized) 385 MPa Yield strength (normalized) 26 % Elongation (normalized) 90 RB Hardness (normalized) Value in US unit 491.20%.75%. Cr=0.5%. Mo=0.114 BTU/(lb*ºF) 323 BTU*in/(hr*ft²*ºF) 2.6 W/(m*K) Thermal conductivity 2. Mn=0. SAE 8620 Chemical composition: C=0. piston pins. arbors. Ni=0.55% Property Value in metric unit 7. cam shafts.4 lb/ft³ 29700 ksi 6.872 *10³ kg/m³ Density 205 GPa Modulus of elasticity 12. sleeves king pins. automotive differential pinions and transmissions.78*10-6 in/(in* ºF) 0. carburized gears. Typical applications for alloy 8620 are caburized splined shafts. guide pins. derive most of their strength from work hardening. stress corrosion cracking (SCC) resistance and toughness. high thermal and electrical conductivity. It is particularly suited for plate applications in the 3 to 6 inch (76. 6061-T651 (solutionized. 6061 Aluminum Alloy 6061 is a precipitation hardening aluminum alloy. plate. It is commonly produced in several heat temper grades. They are also known as silumin. and ease of machinability.T8 Aerospace Alloys The following aluminum alloys are commonly used in aircraft and other aerospace structures: 7075 Aluminum Alloy 7075 is an aluminum alloy.Aluminum Alloy is used extensively in modern aircraft due to its high strength to weight ratio. aluminum is often referred to as "the wonder metal" and is considered the ideal material choice for a variety of today's critical applications. Alloy 7050 exhibits better toughness/corrosion resistance characteristics than alloy 7075.1-6. 6000 series are alloyed with magnesium and silicon.T3. T6511. manganese.T7. 1000 series are essentially pure aluminum with a minimum 99% aluminum content by weight and can be work hardened. but not to the high strengths that 2000.1% zinc. can be precipitation hardened to strengths comparable to steel. with good fatigue strength and average machinability. but has less resistance to corrosion than many other alloys. 1. they were once the most common aerospace alloys. Product details The International Alloy Designation System is the most widely accepted naming scheme for wrought alloys. Formerly referred to as duralumin. 7075-T6. but were susceptible to stress corrosion cracking and are increasingly replaced by 7000 series in new designs.7075 aluminum alloy's composition includes 5. 6063 Aluminum Alloy . 2000 series are alloyed with copper. 7075-O. and can be work-hardened. with zinc as the primary alloying element. . high strength to weight ratio. and sheet. 2. and can be precipitation-hardened. 7000 series are alloyed with zinc. 7075-T651. 6061-T6 (solutionized and artificially aged). and 7000 can reach. and can be precipitation hardened to the highest strengths of any aluminum alloy.It is commonly available in pre-tempered grades such as.9% magnesium. pipe and tubing. chromium.40mm) thickness range. 4000 series are alloyed with silicon. 8000 series is a category mainly used for lithium alloys. Heat temper grades for Aluminum: O. 3000 series are alloyed with manganese.T351. T3511. T651. It is one of the most common alloys of aluminum for general purpose use. It is strong. and less than half a percent of silicon. containing magnesium and silicon as its major alloying elements.Aluminum Alloy Admired for its lightweight. However is susceptible to corrosion above 60°C. 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. We can provide material in standard sizes.2-2.20 to 152. are easy to machine. 7050 Aluminium Alloy 7050 Aluminum alloy is the premier choice for aerospace applications requiring the best combination of strength. T42. T4. Each alloy is given a four-digit number. Its relatively high cost limits its use to applications where cheaper alloys are not suitable. T6.1-2. Aluminum Alloy is available in cold finished and extruded rod and bar. stress-relieved stretched and artificially aged). It is suitable for cryogenic applications and low temperature work. 5000 series are alloyed with magnesium. iron.0% copper. where the first digit indicates the major alloying elements. and other metals. or custom processed to meet your specific requirements. 6061-O (solutionized). titanium. It has good mechanical properties and exhibits good weldability. high corrosion resistance. 7075-T351. 5086 Aluminum Alloy 5086 is an aluminum alloy. 2024 Aluminum Alloy 2024 is an aluminum alloy. It is similar to the British aluminum alloy HE9. 6063-T1. instead becoming stronger due to strain hardening.6063 is an aluminum alloy. since alloys of this type do not show the ductile/brittle transition phenomenon. The alloy has excellent corrosion resistance. 121-177°C) requiring better short-transverse ductility and fracture toughness guarantees than are available with 2024-T851 plate. 2024 is widely used in aircraft structures. The good results with welding and good corrosion properties in seawater make 5086 extremely popular for building boat and yacht hulls. Fracture toughness levels of 2124-T851 plate are substantially higher than 2024-T851. It is commonly produced in several heat temper grades 6063-O. 5083 Aluminum Alloy 5083 is an aluminum alloy suitable for cryogenic applications down to design temperatures of minus 165 °C. especially wing and fuselage structures under tension. although this may reduce the fatigue strength. the main other ingredient is magnesium. 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. T53. T54. T55.0 inches (25. or cold mechanical working of the material.6063 is mostly used in extruded shapes for architecture. Marine Alloys These alloys are used for boat building and shipbuilding. with various improved properties. It is also produced in tempers T52. 5086 can be readily welded and retain most of its mechanical strength. It has a high fatigue strength and is a good choice for structures subjected to excessive vibration. The formability of the grade is excellent and in the annealed condition it offers higher strengths than 1100 or 3003 grades. Alloy 2124-T851 is recommended for moderately elevated temperature applications (250-350°F. 5052 Aluminum Alloy 5052 is one of the higher strength non-heat-treatable alloys. Due to poor corrosion resistance. It is not weldable. door frames. This plate alloy also exhibits good strength retention and creep resistance at elevated temperatures up to 350° F (177°C). particularly window frames. It is typically produced with very smooth surfaces fit for anodizing. and roofs. with magnesium and silicon as the alloying elements. as well as good fatigue resistance. and T832. particularly in marine atmospheres. with copper and magnesium as the alloying elements. primarily alloyed with magnesium.40 mm) thick. and other marine and salt-water sensitive shore applications. It is not strengthened by heat treatment. it is often clad with aluminum or Al-1Zn for protection. . 6063-T4. 6063-T6. 6063-T5.Since heat treatment doesn't strongly affect the strength. and has average machinability. The standard controlling its composition is maintained by The Aluminum Association. The primary use is machined fuselage bulkheads and wing skins in high-performance military aircraft. It has generally good mechanical properties and is heat treatable and weldable. It is used in applications requiring high strength to weight ratio. Apart from aluminum. pulp and paper production.0 17. chemical processing.0 max P 0.5 Ni rem Mo 15. ease of fabrication and high temperature strength.00 max P .0 Cu Co 0. It has also been found to be exceptionally resistant to stress corrosion cracking in petrochemical applications.0 20. Chemical Analysis of ALLOY X C . Applications include pollution control.Hastelloy X Hastelloy X is a Nickel-Chromium-Iron-Molybdenum alloy with an exceptional combination of oxidation resistance.5 2.5 Cb Ti Al .01 max MN 1.03 max Si . industrial furnace applications.03 max Si 1. Applications include gas turbine engine components.0 Cu Co 2. Fe 17.04 max S 0.0 W 3.0 W 0.0 Ni bal Mo 8.04 max S . 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.0 4.5 16.5 V .0 Other Specifications Sheet/Plate ASME SB-435 AMS 5536 Round Bar/Wire ASME SB-572 AMS 5754 AMS 5798 Pipe ASME SB-622 ASME SB-829 ASME SB-619 ASME SB-775 Tube ASME SB-626 ASME SB-751 ASME SB-622 AMS 5587 Fittings ASME SB-366 Forgings AMS Hastelloy C 276 Hastelloy C 276.15 MN 1. Chemical Analysis of Alloy C276 C .08 max Cr 14.05 . waste treatment. chemical processing and petrochemical industry.2 1.0 7.0 max Cr 20.5 max Cb+Ta Ti Al Fe 4.35 max Specifications Sheet/Plate ASME SB-575 Round Bar ASME SB-574 Pipe ASME SB-622 ASME SB-619 ASME SB-775 Tube ASME SB-622 ASME SB-516 ASME SB-626 Fittings ASME SB-366 Forgings ASME SB-564 .0 10.5 23. Chemical Analysis of ALLOY 625 C . nuclear reactors and pumps.015 max Si .5 Other Other Specifications for Inconel 718 .40 max Fe 5.Inconel 625 Alloy (Acid resistant. DIN 17750. being especially resistant to pitting and crevice corrosion.0 Cu Co 1.9 Al . space craft. BS 3074. DIN 17751.13 Ti . ASME SB-446 Inconel 625 a Nickel-Chromium-Molybdenum alloy with excellent corrosion resistance in a wide range of corrosive media. DIN 17752. chemical processing. It has higher strength than Inconel X-750 and better mechanical properties at lower temperatures than Nimonic 90 and Inconel X-750. AMS 5832 Inconel 718 a Nickel-Chromium alloy being precipitation hardenable and having high creep-rupture strength at high temperatures to about 700°C.4856 AFNOR NC 22 D Nb ASME SB443 AMS 5599 AMS 5869 Round Bar/Wire ASME SB-446 AMS 5666 AMS 5837 Pipe ASME SB-444 ASME SB-829 ASME SB-775 ASME SB-705 Tube Fittings Forgings ASME SB-444 ASME SB-366 ASME SB-564 ASME SB-829 AMS 5666 ASME SB-751 ASME SB-704 AMS 5581 Inconel 718 Alloy (Gamma double prime strengthened with good weldability) Specifications: AMS 5596.05 Cu Co 1 max Cb+Ta 5. Inconel 625 is a favorable choice for sea water applications. AMS 5869. nuclear reactors and pollution control equipment.5 Fe 18. BS 3076. NA 21 DIN 17744. ASME SB-443.15 4.0 max Cb+Ta Ti 0.0 10.10 MN .50 max Cr 20. 2. AMS 5837. AMS 5666.40 max Al 0.50 max P . Applications include gas turbines.015 max S .15 Other Specifications for Inconel 625 International Specifications Sheet/Plate BS 3072.0 max Nb 3. good weldability) Specifications: AMS 5599. AMS 5662.0 min Mo 8. Chemical Analysis of Alloy 718 C MN P S Si Cr 19 Ni 52. AMS 5663. DIN 17754. rocket motors.0 Ni 58.5 Mo 3. Applications include the marine and aerospace industries. Werkstoff Nr.0 23. 0 Ni 72. and resistance to ordinary form of corrosion. Chemical Analysis of ALLOY 600 C . hot and cold workability.10.0 min Mo Cu .Sheet / Plate AMS 5596 Round Bar AMS 5662 AMS 5663 Weld Wire AMS 5832 Inconel 600 Alloy (Solid solution strengthened) Alloy 600 is a nonmagnetic.0 .15 max MN 1.0 -17.0 Other Specifications Sheet/Plate ASME SB-168 AMS 5540 Round Bar ASME SB-166 AMS 5665 Pipe ASME SB-167 ASME SB-829 ASME SB-517 ASME SB-775 Tube ASME SB-163 ASME SB-516 ASME SB751 AMS 5580 Fittings ASME SB-366 Forgings ASME SB-564 AMS 5665 .5 max Cr 14.5 max Co Cb+Ta Ti Al Fe 6. nickel-based high temperature alloy possessing an excellent combination of high strength.015 max Si .This alloy also displays good heat resistance and freedom from aging or stress corrosion throughout the annealed to heavily cold worked condition range.0 max P S . 5 max Other Other Specifications Sheet/Plate ASME SB-127 AMS 4544 Round Bar ASME SB-164 QQ-N-281 Pipe ASME SB-165 ASME SB-829 ASME SB-775 ASME SB-725 Tube ASME SB-165 ASME SB-163 ASME SB-730 ASME SB-751 Fittings ASME SB-366 Forgings 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.01 max Si . valves and pumps.5 max Specifications Sheet/Plate QQ-N-286 Round Bar ASME SB-865 AMS 4676 QQ-N-286 Pipe Tube Fittings Forgings QQ-N-286 AMS 4676 . Used for pump shafts.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. Chemical Analysis of ALLOY K500 C MN P S .0 min Mo Cu 28 . It also has good ductility and thermal conductivity.024 max Si . oil-well tools and instruments.25max 1.fasterners and marine propeller shafts.34 Co Cb+Ta Ti Al Fe 2.0 max Other Other .3 max MN 2.valvetrim. doctor blades and scrapers. chemical and hydro-carbon processing equipment. It also has low permeability and is nonmagnetic to under -150°F (-101°C).33 Co Cb+Ta Ti Al 2. Applications include marine engineering.5 max Cr Ni 63. heat exchangers.30-3.0 max P S .springs. Chemical Analysis of ALLOY 400 C .0 min Mo Cu 27 .5 max Cr Ni 63.15 Fe 2. 15% graphite (by weight). Automotive engineers love to use SP-21 for parts like thrust washers. Superior wear and low-friction properties for: Thrust washers Seal rings Valve seats Bearings Seals Benefits Low wear at high bearing PVs Low coefficient of friction Long-term thermal stability High stiffness Low elongation Outstanding performance with or without lubrication Good strength and impact resistance .15% MoS2(by weight). Vespel Parts and Shapes include many products with differing sets of attributes. Best wear performance in dry environments. improves long term thermal stability. lowest modulus & thermal conductivielectricalproperties. best electrical and thermal insulation for: Insulators Valve seats Balls Gaskets Poppets Wafer clamping Clamping rings In-chamber semiconductor parts Benefits Unfilled resin Operating temps from cryogenic to 300°C (570°F) Ultra high purity Minimal electrical and thermal conductivity Maximum strength and elongation Low outgrassing Improved tech uniformity Excellent wear for longer life Vespel SP21 . Within the S Line. Gives low coefficient of thermal expansion. Maximum creep resistance. Lowest static friction.highly durable polyimides that deliver exceptional wear resistance.15% graphite and 10% TEFLON® fluorocarbon resin (by weight). Vespel SP-21 . Vespel SP-211 .First in the Dupont Vespel family of products .Unfilled.because the low-friction properties mean they work with or without lubrication. Superior wear properties.If insulation is less important than low-friction properties.40% graphite (by weight). Enhances inherent wear resistance. Vespel SP-22 . and a low coefficient of friction. Vespel SP1 . insulation. Maximum strength & elongation. bearings and seals . Vespel SP-3 . then you're looking for graphite-enhanced SP-21.Dupont Vespel Vespel SP-1 . Aerospace engineers have to worry about extra difficulties like outgassing.Of course. elongation and flexural modulus Vespel SP22 . But SP-3 has proven high performance in aerospace applications. Graphite-enhanced polyimides for tight-tolerance applications: Bearings Thrust washers Seal Rings Ferrules Sleeves Strips Vanes Benefits Enhanced resistance to friction and wear Minimal thermal expansion Maximum thermal conductivit High temperature resistance Improved dimensional and oxidative stability Minimum elongation Vespel SP3 . the coefficient of friction is further reduced. largely due to its ultra-low outgassing.Designing with tight tolerances? SP-22 is the answer. Excellent performance in vaccuum and dry environment applications including: Bushings Bearings Piston Rings .Vespel SP211 . working in vacuum and dry environments has its own challenges. Lowest coefficient-of-friction parts in both dry and lubricated applications such as: Sliding and linear bearings Bushings Thrust washers Seal rings Benefits Low wear at high bearing PVs Low coefficient of friction Teflon filled Superior unlubricated wear Excellent creep resistance Wear resistant up to 300 F Good tensile strength. When you've no room for error. even without lubrication. SP-22's minimal thermal expansion and dimensional stability give you the freedom to create exactly what you've imagined.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. dimensional stability and chemical resistance than SP-1. reinforced with high-tensile-strength carbon fiber .Materials designed for those demanding applications that require even more toughness. SCP-50094 has been put to the test in ultra-high-stress environments like aircraft engines.A Teflon® PFA body.Seals Gears Benefits Maximum wear and friction resistance in vaccums and other dry environments Ultra-low outgrassing High performance in aerospace applications Vespel SCP5000 . The ultimate in chemical and creep resistance for: . and you have an ideal material for a variety of applications. check out SCP-5000. Unfilled resin designed to improve strength. But for better plasma resistance. thermal stability and chemical resistance than ST-2010. thermal stability and chemical resistance than ST-2010. Unfilled resin designed to improve strength. But for better plasma resistance. So. temperature resistance and dimensional stability in: Semiconductor applications Automotive Aircraft engine parts Benefits Excellent thermal oxidative stability High stiffness Excellent dimensional stability Lowest CTE Vespel CR6100 . dimensional stability and chemical resistance than SP-1. So.CR-6100 offers excellent chemical resistance while exhibiting superior resistance to creep .Materials designed for those demanding applications that require even more toughness. it's ready for just about any design challenge. SCP-50094 has been put to the test in ultra-high-stress environments like aircraft engines. it's ready for just about any design challenge. temperature resistance and dimensional stability in: Semiconductor applications Automotive Aircraft engine parts Benefits Ultra-high purity High thermal oxidative stability High stiffness Vespel SCP50094 .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). lapping and polishing components Benefits Outstanding creep resistance .even up to 288°C (550°F) Excellent chemical and wear resistance Easy machinability for tight-tolerance applications Virtually no water absorption Ideal for chemical and petroleum processing applications CTE lower than steel Vespel SP202 . acids and bases. moisture resistance.Valve plates.Want a material that wears like SP21. Fiber-reinforced polyimide resins ideal for: Valve seats Seals Bearings Washers Seal rings Ferrules Wear pads Benefits Excellent wear High oxidative Outstanding strength . wear strips and plates Bearings and bushings Grinding. but with improved toughness and better thermal oxidative stability? Consider ST2010 or ST2030.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. These products even include better resistance to solvents. 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. 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 chamber Pads/balls for glass/wafer transfer process Physical Properties Antistatic Good machinability Excellent thermal resistance Vespel ST2010 . seats and seals Pump and compressor components Gaskets Thrust washers Mechanical seals. vacuums or reactive environments. toughness. They are ideal for use with products that are handled in hightemperature. Vespel ST2030 . These products even include better resistance to solvents. acids and bases.Want a material that wears like SP21. Fiber-reinforced polyimide resins ideal for: Valve seats Seals Bearings Washers Seal rings Ferrules Wear pads Benefits Excellent wear High oxidative Outstanding strength . but with improved toughness and better thermal oxidative stability? Consider ST2010 or ST2030. but can be precipitation hardened to even higher strengths than the other martensitic grades. They contain a maximum of 0. and 29Cr-4Mo-2Ni. commonly known as 18/10 stainless. The Lockheed-Martin Joint Strike Fighter is the first aircraft to use a precipitation-hardenable stainless steel—Custom 465—in its airframe. precipitation of Chromium Carbides at grain boundaries. nickel (0-<2%). and the higher nickel content ensures better resistance to stress-corrosion cracking versus the 300 series. uses about 17% chromium and 4% nickel. It is also called corrosion-resistant steel or CRES when the alloy type and grade are not detailed. and can be hardened by heat treatment. For greater hardness and strength. or 300 series. Martensitic stainless steel contains chromium (12-14%). cutlery. molybdenum (0. stainless steels comprise over 70% of total stainless steel production. Carbon steel rusts when exposed to air and moisture. Martensitic stainless steels are not as corrosion-resistant as the other two classes but are extremely strong and tough. When subjected to adequate heat treatment. but it is not stain-proof. these steels are used as razor blades. Stainless steels are also classified by their crystalline structure: Austenitic. A typical composition of 18% chromium and 10% nickel. Most compositions include molybdenum.5% and 27% chromium and very little nickel. aluminum or titanium. but less durable than austenitic grades. 18/0 and 18/8 are also available. carbon is added. Stainless steel does not stain. This crystal structure makes such steels non-magnetic and less brittle at low temperatures. 26Cr-1Mo. or rust as easily as ordinary steel (it stains less). Super austenitic stainless steels. Manganese preserves an austenitic structure in the steel as does nickel. These alloys can be degraded by the presence of σ chromium. 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. the aim being to produce a 50/50 mix.15% carbon. although in commercial alloys.1-1%) (giving it more hardness but making the material a bit more brittle). etc. some. tools. and carbon (about 0. but at a lower cost. This iron oxide film is active and accelerates corrosion by forming more iron oxide. as well as highly machineable. but some types can contain lead. the austenite structure of iron is stabilized. 17 4 PH. The "L" means that the carbon content of the Stainless Steel is below 0. corrode. as it is estimated that 2% of the US GDP is spent dealing with corrosion.03%. stainless steel is defined as a steel alloy with a minimum of 11% chromium content by mass. Similarly. a intermetallic phase which can precipitate upon welding. Duplex stainless steels have a mixed microstructure of austenite and ferrite. It is quenched and magnetic. crevice corrosion and stress corrosion cracking. the mix may be 40/60 respectively. due to the high temperature produced by welding operation. exhibit great resistance to chloride pitting and crevice corrosion due to high molybdenum content (>6%) and nitrogen additions. Stainless steel differs from carbon steel by the amount of chromium present. They are characterized by high chromium (19–28%) . Common ferritic grades include 18Cr-2Mo. The low carbon versions of the Austenitic Stainless Steel. for instance. They contain between 10.21%). such as alloy AL-6XN and 254SMO. There is a rising trend in defense budgets to opt for an ultra-high-strength stainless steel when possible in new projects. particularly pitting. 29Cr-4Mo. for example 316L or 304L. 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.Stainless Steel In metallurgy. Ferritic stainless steels are highly corrosion-resistant. There are different types of stainless steels: when nickel is added. this will reduce the sensitization effect. The higher alloy content of super austenitic steels makes them more expensive. are used to avoid corrosion problem caused by welding. particularly in the aviation industry. Other steels can offer similar performance at lower cost and are preferred in certain applications. The most common. if any. Precipitation-hardening martensitic stainless steels have corrosion resistance comparable to austenitic varieties. Significant quantities of manganese have been used in many stainless steel compositions. Duplex steels have improved strength over austenitic stainless steels and also improved resistance to localized corrosion. There are different grades and surface finishes of stainless steel to suit the environment to which the material will be subjected in its lifetime. therefore it is used in flexible chimney liners. for food and surgical stainless steel uses. used for automobile exhausts. Type 321—similar to 304 but lower risk of weld decay due to addition of titanium. Type 303—free machining version of 304 via addition of sulfur and phosphorus. Type 440—a higher grade of cutlery steel. Type 410—martensitic (high-strength iron/chromium). Is slightly weaker than 304. better known as 17-4 PH. Type 316L— extra low carbon grade of 316.g. See also 347 with addition of niobium for desensitization during welding. also sometimes used as filler metal when welding dissimilar steels. The most used Duplex Stainless Steel are the 2205 (22% Chromium. most display-only and replica swords or knives are made of 440 stainless. e. the classic 18/8 stainless steel. 650 through 653: Austenitic steels strengthened by hot/cold work. ferritic (iron/chromium only). 400 Series—ferritic and martensitic chromium alloys Type 405— ferritic for welding applications Type 408—heat-resistant. 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 automotive trim. Type 302—same corrosion resistance as 304. Also hardens rapidly during mechanical working. Type 416— 416 SS is easy to machine due to additional sulfur Type 420—Cutlery Grade martensitic.and molybdenum (up to 5%) and lower nickel contents than austenitic stainless steels. Also referred to as "A4" in accordance with ISO 3506. the 2507 is also known as "Super Duplex" due to its higher corrosion resistance. with more carbon. Due to its toughness and relatively low cost. and the uncommon 440F (free machinable). Good weldability. Also referred to as "A2" in accordance with ISO 3506. allowing for much better edge retention when properly heat-treated. 630 through 635: Semi austenitic and martensitic precipitation-hardening stainless steels. Type 304LN—same as 304L. Type 316—the second most common grade (after 304). but less corrosion-resistant. Type 439—ferritic grade. alloy addition of molybdenum prevents specific forms of corrosion. 11% chromium. making it one of the hardest stainless steels. poor corrosion resistance. Good formability. 4% nickel. Available in four grades: 440A. except for diving or other salt-water applications.. Type 308—used as the filler metal when welding 304 Type 309—better temperature resistance than 304. Also referred to as "A1" in accordance with ISO 3506. ferritic. 5% Nickel) and 2507 (25% Chromium. 440B. a higher grade version of 409 used for catalytic converter exhaust sections. Type 304—the most common grade. It can be hardened to approximately Rockwell 58 hardness. 440C. 316 is often used for building nuclear reprocessing plants. Type 304L— same as the 304 grade but contains less carbon to increase weldability. Increased chromium for improved high temperature corrosion/oxidation resistance. Type 316Ti—includes titanium for heat resistance. 614 through 619: Martensitic chromium steels. Type 630 is most common PH stainless. Type 430—decorative. is the most stain-resistant. 7% Nickel). Better wear resistance and fatigue strength than 304. Type 409—cheapest type. is the strongest and is usually considered more desirable in knife making than 440A. 8% nickel. all grades except alloy 661 are strengthened by second-phase precipitation. having the most. generally used in stainless steel watches and marine applications due to its high resistance to corrosion. 660 through 665: Austenitic super alloys. . with slightly higher strength due to additional carbon. Type 446—For elevated temperature service 500 Series—heat-resisting chromium alloys 600 Series—martensitic precipitation hardening alloys 601 through 604: Martensitic low-alloy steels. 440C. for formed products. Excellent polishability. but with reduced temperature and corrosion resistance. having the least amount of carbon in it. along with inconel. Also known as razor blade steel. 610 through 613: Martensitic secondary hardening steels. 440A. 17% chromium. It is also known as marine grade stainless steel due to its increased resistance to chloride corrosion compared to type 304. but also nitrogen is added to obtain a much higher yield and tensile strength than 304L. Wear-resistant. 045 0.5 0.1 - 304Cu S30430 17–19 8–10 0.045 0.15 5.5–5.15 2 1 0.2 0.15 min - Mo 0.15 2 2.06 - 0.75 0.045 0.15 Se min 304 S30400 18–20 8–10.75 0.06 0.08 2 0.03 0. It has both excellent corrosion resistance and high strength.08 2 0.10– 0.25 14–15.045 0.0 0.1 - 304L S30403 18–20 8–12 0.60 (optional) 303Se S30323 17–19 8–10 0.1 - 302B S30215 17–19 8–10 0.045 0.40 - 301 S30100 16–18 6–8 0.15 7.0 0.15 2 0.06 0.75 0.06 0.25 - 205 S20500 16.03 0.08 2 0.2 0.045 0.03 0.0–3. Type 2205— the most widely used duplex (ferritic/austenitic) stainless steel grade.25 - 202 S20200 17–19 4–6 0.03 0.03 0.5 0.75 0.16 - .03 - - 303 S30300 17–19 8–10 0. Stainless Steel Designations SAE designation UNS designation % Cr % Ni %C % Mn % Si %P %S %N Other Austenitic 201 S20100 16–18 3.50 0.75 0.5 0.75 0.75 0.03 0.03 2 0.15 2 0.03 - - 302 S30200 17–19 8–10 0.75 0.75 0.5–7.50 0.045 0.5– 10.03 0.03 - 3–4 Cu 304N S30451 18–20 8–10.12– 0.75 0.5–18 1–1.15 2 1 0.32– 0. 045 0.03 0.045 0.04 0.2 2 1 0.03 - - 308 S30800 19–21 10–12 0.10 2.75 0.75 0.045 0.75 0.03 0.2 0.08 2 0.75 0.0 0.25 2 1.045 0.030 - Nb + Ta.10 min - 1.03 - - 310S S31008 24–26 19–22 0.08 2 0.50–13 0.10 max 3.0–3.03 0.03 - - 347 S34700 17–19 9–13 0.0 Mo 317L S31703 18–20 11–15 0.03 - 1–2 Mo 330 N08330 17–20 34–37 0. 10 x C min.0 Mo 317 S31700 18–20 11–15 0.03 0.10 Ta max.045 0.25 2 1.5–3. 10 x C min.75 0.03 - - 316 S31600 16–18 10–14 0.03 2 0.5 0.08 2 0.70 max 329 S32900 23–28 2.045 0.0–3.03 0.08 2 1.045 0.08 2 0.75– 1.045 0.045 0.16 2.030 - Nb + Ta. 1 max 348 S34800 17–19 9–13 0.045 0.75–2.045 0.045 0.03 - - 310 S31000 24–26 19–22 0.03 0.08 2 0.0 Mo 316L S31603 16–18 10–14 0.0 Mo 321 S32100 17–19 9–12 0. 0.03 2 0.12 2 0.03 - - 309S S30908 22–24 12–15 0.75 0.03 - - 314 S31400 23–26 19–22 0.75 0.08 2 1 0.0 Mo 316F S31620 16–18 10–14 0.305 S30500 17–19 10.0–4.045 0.04 0.75 0.75 0.75 0. .03 - - 309 S30900 22–24 12–15 0.08 2 0.0–3.50 Mo 316N S31651 16–18 10–14 0.08 2 0.10– 0.045 0. 1 max.08 2 1 0. but 0.10 2.10 max 3.5–5 0.50 0.10 max Ti 5(C+N) min.5 0.08 2 1 0.0–4.045 0.08 2 0. 75 0.04 0.04 0.5– 11.03 - - 414 S41400 11.25 Mo 436 S43600 16–18 - 0.5 0.25 Mo.03 - - 430F S43020 16–18 - 0.08 1 1 0.03 - 0.5–13.15 Se min 434 S43400 16–18 - 0.05 0.12 1 1 0.0.045 0.75 0.75 0.25 1 0.75 0.04 0.03 - - 410 S41000 11.5–14.03 - - 430 S43000 16–18 0.3 Al.04 0.03 - - 904L 19-23 23-28 0.12 1 1 0.06 0.12 1 1 0.1–0.25 1 0.5 - 0.5 0.045 0.25– 2.08 1 1 0.035 - Mo 4-5.02 2 1 0.04 0.04 0.20 Ca 384 S38400 15–17 17–19 0.15 1 0.12 1. 0.15 1 1 0.06 0.60 Mo (optional) 430FSe S43023 16–18 - 0.5–13.5–13.50 0.15 1 1 0.75–1.5 1.04 0.03 - 0.04 0.60 max 409 S40900 10.60 0.5 1 0. but 0.12 1.03 - - Martensitic 403 S40300 11.75 max 429 S42900 14–16 0. Nb+Ta 5 x C min.04 0.06 - 0.12 1 1 0.15 min - 0.08 2 1 0.045 0.70 max 442 S44200 18–23 - 0.03 - 0.03 - Ti 6 x C.75–1. 0.03 - - 446 S44600 23–27 0.04 0. Cu 1-2 Ferritic 405 S40500 11.03 - - .0 0.2 1 1 0.25 0.2 1. 25 Mo.50–1.65 Mo 502 S50200 4–6 - 0.40–0.90–1.04 0.25 W 431 S41623 15–17 1.06 0.75 1 1 0.0–12.03 - - 440A S44002 16–18 - 0.15 Se min 420 S42000 12–14 - 0.03 - 0.15 min 1 1 0.06 0.75 Mo Heat resisting 501 S50100 4–6 - 0.03 - 0.03 - 0.15 min - 0.5 0.50 0.60 Mo max (optional) 422 S42200 11.25 1 0. 0.04 0.1 1 1 0.25– 2.03 - 0.04 0.04 0. Ta 0.0 0.06 0.75 Mo 440C S44004 16–18 - 0.15 min - 0.20–0.45 .025 - 0.25 0.04 0.06 - 0.04 0.0 0.5–1.04 0.04 0.60– 0.5 0.10 min 1 1 0.90–1.40–0.15 1.03 - 0. 0.07 1 1 0.416 S41600 12–14 - 0.03 - Cu 3-5.65 Mo Martensitic Precipitation Hardening 630 (17-4 PH) S17400 15-17 3-5 0.20– 0.95 1 1 0.025 0.25 1 0.75– 0.03 - - 420F S42020 12–14 - 0.30 V.15 1.95– 1.75 Mo 440B S44003 16–18 - 0.2 1 1 0.25 1 0.15-0.060 Mo (optional) 416Se S41623 12–14 - 0.20 1 1 0.15 min 1. This improved toughness is achieved by reduced delta ferrite content and control of inclusion size and shape. which is present in the 17-4 PH stainless steel material. especially in the through-thickness (short transverse) direction.8 0. AMS 5862 15-5 PH 0. Element Typical Composition (Weight Percent) 0.000 1.000 1. ASTM A 705. 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.30 3. The15-5 PH alloy is generally better-suited for plate applications than are the semi austenitic alloys. 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. The composition and processing of 15-5 PH alloy is carefully controlled to minimize its content of delta ferrite.5 4. High strength is maintained to approximately 600°F (316°C). AMS 5826.020 0.000 760 150.000 1.5 Balance Carbon Manganese Phosphorus Sulfur Silicon Chromium Nickel Columbium + Tantalum Copper Iron MECHANICAL PROPERTIES PER 15-5 PH AMS 5659. The latter precipitation hardening alloys generally require more steps to complete heat treatment.04 0. AMS 5659. although slightly less than those of semi-austenitic alloys like S17700 (17-7 PH) or S15700 (15-7 PH). ASME SA 693.030 8 33 Condition H 900 175. Inclusion control is done by consumable electrode remelting using the electro-slag remelting (ESR) process.000 1.15-5 PH Stainless Steel Specification: AMS 5862.000 1.200 195. Heat treatment in the 900°F (482°C) range produces highest strength. ASME SA 705 Please enable JavaScript to view this page content properly.000 860 145.005 0. The 15-5 PH alloy was designed to have greater toughness than 17-4 PH. A wide range of properties can be produced by this one step heat treatment.2% Offset Yield Strength Ultimate Tensile Strength psi (MPa) psi (MPa) Condition A 110.000 15 28 Elongation (percentage in 2") Hardness Rockwell C scale . 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. the 15-5 PH stainless steel alloy requires only a simple heat treatment.50 14.000 930 155.340 15 43 Condition H 1075 135. ASTM SA 564. ASTM A 564.75 0. Like the 174PH alloy. ASTM A 693.070 15 31 Condition H 1150 125. Both alloys exhibit high strength and moderate corrosion resistance. 04 0. followed by a consumable vacuum arc remelting (VAR) step.40 0.340 1.50 Balance Carbon Manganese Phosphorus Sulfur Silicon Chromium Nickel Columbium + Tantalum Copper Iron MECHANICAL PROPERTIES PER 17-4 PH AMS 5643.100 psi psi psi psi 150.000 190. ASME SA 564. ASME SA 705 17-4PH Precipitation Hardening Stainless Steel Alloy (S17400).000 MPa MPa MPa 760 1. ASTM A564.100 1. XM-13 General 13-8 Stainless Steel [PH 13-8 Mo (tm). A wide range of properties can be produced by this one step heat treatment. and double vacuum melting (to reduce alloy segregation). In comparison to many alloys in the precipitation hardening family. Type 630. Since the rate of cooling from the solution temperature is not critical. ASMT A693.000 160. rocket engine mounts.Vasco13-8 (tm)(UNS S13800) is a precipitation hardening stainless steel that combines excellent strength. ASTM A705. forgings. ASTM A 705. AMS 7474. AMS 5604 Condition Yield Strength Ultimate Tensile Strength A H 950 H 1075 H 1150 psi psi psi psi 110. large cross sections can be air-cooled.30 3. AMS 5622. It is a through-hardening alloy. and good general corrosion resistance. AMS 5864.005 0. ASTM A 693. which allows it to be used in parts with large cross sections.000 MPa 180.000 MPa MPa MPa MPa 1. landing gear components.380 MPa) may be required. AMS 5827. high performance shafts.030 1. rings.310 Elongation (%) 8 10 10 10 (Rockwell) Hardness 33 (C) 43 (C) 42 (C) 42 (C) PH13-8MO Alloy Specification: AISI 632.000 190. Typical uses are aircraft parts.50 15. AMS 5825. (1. ASTM A 564. good toughness. the S17400 (17-4 PH) alloy requires a simple heat treatment. AMS 5643.020 0. Good transverse toughness properties are achieved by tight chemical composition control (to prevent the formation of delta phase). High strength is maintained to approximately 600°F (316°C). 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.310 1. This alloy is produced by a primary vacuum induction melt process (VIM).5 4. is a chromium-nickel-copper precipitation hardening stainless steel used for applications requiring high strength and a moderate level of corrosion resistance. ASME SA 693.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. low carbon content (to minimize grain boundary precipitation). Specifications PH 13-8 Mo AMS 5629 .17-4 PH Stainless Steel Specification: AMS 5604. and extrusions PH 13-8 Mo AMS 5864 . AMS 5629. and petrochemical parts that require high strength combined with good resistance to stress corrosion. nuclear reactor parts.000 195.240 1.000 160. where yield strengths in excess of 200 ksi.5 0.Plate . Element Typical Composition (Weight Percent) 0.Bars. UNS S13800. Heat treatment is usually performed in air.675 to 1. . Temperatures up to 2.76 gm/cc) Heat Treatment Solution treatment from 1. brazing and pickling.680 F (1. After forging. In the annealed condition. although most other welding processes may be used. FORGEABILITY/ FORMABILITY PH13-8MO alloy has good hot working characteristics.The alloy can be cold formed in the annealed condition.204 C) may be used.150 F (510 to 621 C). Heat treatment of brazed components maybe done in inert atmospheres. These include plasma arc. and shielded metal arc processes. use machine speeds 20 to 30 percent lower than those used on 304 stainless steel.500 F (816 C).Physical properties Melting Range: 2. The alloy shows very little rusting when exposed to a 5 percent salt fog at 95 F (35 C). utilizing conventional cold forming techniques. particularly sulfur-bearing.700 F (927 C). depending upon the desired final properties.725 F (913 to 941 C) for 15 to 30 minutes at temperature. Corrosion resistance decreases slightly as the aging temperature is raised. Aging is normally carried out from 950 to 1.200°F(1. and can be forged over a wide temperature range. This alloy has the best resistance to stress corrosion cracking of all of the precipitation hardenable stainless steels. For optimum properties.404 to 1. should be removed prior to heat treatment. WELDABILITY PH13-8MO alloy is normally welded using inert gas tungsten arc techniques. forging temperature should not exceed 1.900 F(1. HARDNESS Hardness in the solution annealed condition is approximately Rockwell C 33.279 lbs/in3 (7. parts should be cooled to room temperature. Helium is the preferred shielding gas. SPECIAL PRECAUTIONS All lubricants and coolants.560 to 2. OXIDATION AND CORROSION RESISTANCE PH13-8MO alloy has excellent oxidation resistance up to 1. electron beam. gas metal arc. Its resistance to general corrosion is greatest in the fully-hardened condition. MACHINABILITY PH 13-8 MO alloy can be machined in both the annealed and hardened conditions.471 C) Density: 0.038 C). Air cool or oil quench to below 60F (15 C) to ensure complete transformation to martensite. Hot working shouldnot be done below 1. then solution treated prior to aging. Reducing atmospheres should not be used because of the potential for nitrogen contamination. UNS R56400 Ti 6AL-4V is known as the workhorse of the titanium industry because it is by far the most common Ti alloy. hard) 10 % Elongation (precip. high performance automotive parts. 3020 ºF 2920 ºF 1825 ºF . AMS 4928. light weight.6 BTU*in/(hr*ft²*ºF) 171*10-6 Ohm*cm 145000 psi 132000 psi 18 % 36 HRC 170000 psi 160000 psi 10 % 41 HRC 1650 ºF 950 ºF 4-8 hrs.43 *10³ kg/m³ Density 114 GPa Modulus of elasticity -6 9. MIL-T-9046. Ti balance Property Value in metric unit 4. AMS 4911. hardened) 41 HRC Hardness (precipit. medical devices. Titanium α-β alloy. AMS 4967. formability and corrosion resistance which have made it a world standard in aerospace applications. DMS 1570.. and sports equipment.5*10 ºCˉ¹ Thermal expansion (20 ºC) 565 J/(kg*K) Specific heat capacity 6. hard. Some of the many applications where this alloy has been used include aircraft turbine engine components.135 BTU/(lb*ºF) 45. AMS 4965. accounting for more than 50 % of total titanium usage. ASTM B381.) 1103 MPa Yield strength (precip.6 W/(m*K) Thermal conductivity 171*10-8 Ohm*m Electric resistivity 1000 MPa Tensile strength (annealed) 910 MPa Yield strength (annealed) 18 % Elongation (annealed) 36 HRC Hardness (annealed) 1172 MPa Tensile strength (prec. AMS 4954. AMS 4934. MIL-T-9047. Grade 5 (Ti-6Al-4V) Chemical composition: O=0. aircraft structural components. marine applications. ASTM B348. AMS 4920. Aging time 1660 ºC Liquidus temperature 1605 ºC Solidus temperature 996 ºC Beta Transus temperature Value in US unit 277 lb/ft³ 16500 ksi -6 5. MIL-F-83142.08% max.MIL-T-81915.MIL-T-81556. AMS 4935. V=4%. AMS 4930. AMS 4906. aerospace fasteners. ASTM B265.Titanium Titanium alpha-beta alloy. Ti 6AL-4V offeres a combination of high strength. Al=6%. it is an alpha-beta alloy that is heat treatable to achieve moderate increase in strength. Grade 5 (Ti-6Al-4V) Specifications: AMS 4905.0*10 in/(in* ºF) 0. hardened) 900 ºC Solution temperature 510 ºC Aging temperature 4-8 hrs. Cobalt. GR 70 SA. GR 9 SA. Special Alloys A-286. 304L 306 309 310 314 316. C624. 201 N155 Nimonic 75 Rene 41 Udimet 500. C276 Haynes 188. GR B SA. 825. 601.C 446 904L Alloys AL6XNS HY80-HY100 4130 4135 4140 41L40 4142 4145 4150 4155 4160 4215 4320 4330. D5. D3. Inconel 600. 1144. A-387. 5052 Alloy 182 Alloy 932 Ni Alum Brz C623. 751 Invar 36. 617 Inconel 625. 700 Vascojet 1000 Waspaloy Zirconium 20 CB Copper Alloys Special Grades D6AC A193 400 & 500 Series 403 405 409 410 416 418 (Greek Ascoloy) 420 422 430F 431 440A. A-387. 230 Incoloy 800. AM-355 Deltalloy Custom 450. 2219 3003. W2 Stainless Steel 300 Series 301 302 303 304. A-387. Inconel 718 722.Carbon Steel 1008 1010 1018 1020 1040 1045 1050 1055 1060 1070 1075 1095 A36 A656 (GR 80) Cor-Ten Free Max15 Tool Steel A2 A6 A10 A514 D2. GR 65 SA. 2014. GR 22 Maxel Molybdenum Aluminum Alloys C18200 Alum Brz C 613 Alum Brz 614. 2024. 901-200-20. . 316L 321 322 347 348 Nickel. 1145. 455 Ferralium 255 Hastelloy B2. GR 5 SA. 42 Kovar Rodar L605 (Haynes 25) Maraging 250 Maraging 300 Maraging 350 Monel 400 Monel 405 Monel 500 (K) Nickel 200. A-516. A-204. A-387. 20CU 1100. GR11 SA. GR 12 SA. 750. 4340M 4615 4620 4630 4640 F-11 (1-1/4CR1/2MO) F-22 (2-1/4CR1MO) 17-22-A 17-22-AS 17-22-AV Nitralloy 135N SA. A-516. A-387. 4330M 4335 4340. D6 H11 M2 P20 S1 S5 S7 T1 W1. C172 C17200 PH Grades Titanium Commercially Pure 3AL-2. 6061. 5086.5V-11CR-3AL 15-3-3-3 10-3-3-3 Ti-17 13-8MO 15-3PH 15-5PH 15-7MO 17-4PH 17-7PH 17-22PH Valve/Flange/Fittings Call for availability .5V 5AL-2. C632 Copper Ni C 706(90/10) C715(70/30).5SN 6AL-2SN-4ZR-2MO 6AL-2SN-4ZR-6MO 6AL-4V 6AL-4V Eli 6A1-6V-2SN 8AL-1MO-1V 13.6063 7050 7075 7475 C630.4720 4750 5150 52100 6120 6140 6145 6150 8620 8630 8640 8642 8645 8720 8735 8740 8750 9010 Tantalum Magnesium Niobium MP35N A182 A234 A242 A333 A335 Stellite Tungsten HY-TUF Telcut 40 Aermet 100 Zinc 5083.