24,657 materials
Inconel 600 is a nickel-chromium austenitic superalloy with excellent oxidation and corrosion resistance up to 1100°C, used in aerospace, chemical processing, and nuclear applications. The annealed condition provides optimal ductility and corrosion resistance with reduced yield strength compared to cold-worked tempers, making it suitable for applications requiring high toughness and resistance to intergranular corrosion in service temperatures up to approximately 900°C.
Inconel 600 cold-drawn tubing is a nickel-chromium superalloy (Ni-20Cr-8Fe) in work-hardened condition, offering elevated yield and tensile strength with maintained ductility for high-temperature applications in aerospace and chemical processing requiring corrosion and oxidation resistance to approximately 1100°C. Cold drawing increases strength over annealed conditions while preserving the alloy's excellent creep resistance and notch toughness in aggressive environments.
Inconel 600 is a nickel-chromium superalloy with iron additions, used in high-temperature corrosion and oxidation resistance applications including aerospace, chemical processing, and nuclear reactors. The cold-worked condition provides elevated strength through strain hardening while maintaining excellent creep resistance and thermal fatigue performance up to approximately 1100°F (593°C), with yield strength, ultimate tensile strength, and elongation data defined per ASTM B166.
Inconel 600 is a nickel-chromium superalloy with excellent oxidation and corrosion resistance up to 1100°C, used in high-temperature applications including aerospace engines, chemical processing, and nuclear reactors. The hot-worked condition provides good strength and ductility with moderate work hardening, suitable for applications requiring both elevated-temperature capability and fabricability in round, square, hexagonal, and rectangular forms per ASTM B166.
Inconel 625 offers outstanding corrosion and oxidation resistance, with excellent weldability. Used in marine, chemical, and aerospace applications where extreme corrosion resistance at elevated temperatures is needed.
Inconel 625 is a nickel-chromium-molybdenum superalloy designed for service in oxidizing and corrosive environments up to approximately 2000°F, with excellent fatigue and creep resistance. The annealed condition provides optimal ductility and toughness for fabrication while maintaining outstanding strength retention at elevated temperatures, making it suitable for aerospace engine components, chemical processing equipment, and marine applications.
Inconel 706 is a nickel-iron-based superalloy strengthened by gamma-double-prime precipitation, designed for high-temperature structural applications requiring moderate strength retention to approximately 1300°F (704°C). Primary applications include aircraft engine casings, fasteners, and gas turbine components in aerospace and power generation industries, with excellent creep resistance and thermal fatigue resistance in the intermediate temperature range.
Inconel 706 is a nickel-iron-chromium precipitation-hardening superalloy with columbium and titanium additions, designed for high-strength applications in aerospace gas turbines and fasteners operating to approximately 1300°F (704°C). The heat-treated condition provides excellent tensile strength and bearing properties with good ductility, making it suitable for critical rotating and structural components requiring sustained elevated-temperature performance with reliable stress-rupture resistance.
Inconel 718 is the dominant nickel superalloy for gas turbine engine disks and casings, accounting for over 50% of all superalloy production. Excellent high-temperature strength up to ~650°C and good weldability.
Inconel 718 produced via selective laser melting (SLM) is a nickel-based superalloy manufactured through additive manufacturing, combining the exceptional high-temperature strength and corrosion resistance of conventional Inconel 718 with the design freedom and complexity capabilities of metal 3D printing. This material is increasingly adopted in aerospace, power generation, and oil & gas industries where engineers need intricate cooling channels, lightweight geometries, or rapid prototyping of high-performance components that would be difficult or impossible to machine from wrought stock. SLM Inconel 718 is valued for its ability to maintain structural integrity in aggressive thermal and corrosive environments while enabling near-net-shape manufacturing, though careful process control and post-processing (such as heat treatment) are critical to achieve consistent mechanical properties and eliminate porosity inherent to the additive process.
Inconel 718 is a nickel-base superalloy containing chromium, iron, niobium, and molybdenum, designed for high-temperature structural applications in jet engines, gas turbines, and aerospace components requiring strength retention to approximately 650°C (1200°F). The ST (solution-treated) condition, produced via investment casting per AMS 5383, provides controlled mechanical properties including yield strength, ultimate tensile strength, and bearing strength suitable for critical fasteners and bearing applications with intermediate ductility.
Inconel 718 STA is a nickel-chromium-iron precipitation-hardening superalloy solution heat-treated and aged to provide tensile strength around 1,380 MPa (200 ksi) with excellent creep resistance up to approximately 650°C, used primarily in jet engine turbine disks, fasteners, and high-temperature aerospace components. The STA condition balances high yield strength, good fatigue resistance, and toughness suitable for critical rotating and static load applications in extreme thermal environments.
Inconel 718 is a nickel-based superalloy in wrought form that has been precipitation-hardened through aging heat treatment to achieve high strength at elevated temperatures. It is widely used in aerospace, power generation, and oil & gas industries where components must withstand extreme thermal and mechanical stresses while maintaining structural integrity. Engineers select this alloy for critical applications requiring excellent creep resistance, fatigue strength, and corrosion resistance in operating environments that would cause conventional steels and aluminum alloys to fail.
Inconel X-750 is a nickel-based superalloy strengthened by gamma-prime precipitation, designed for high-temperature aerospace applications requiring sustained strength to approximately 1300°F (704°C). The alloy exhibits excellent creep resistance, fatigue strength, and corrosion resistance in jet engine components, gas turbine blades, and fasteners, with the Equalized and Aged temper providing optimal strength development through controlled solution treatment and precipitation hardening.
Inconel X-750 is a precipitation-hardenable nickel-chromium superalloy with aluminum and titanium additions, used primarily in aerospace gas turbine engines, fasteners, and high-temperature structural applications requiring strength retention to approximately 1300°F (700°C). The annealed condition provides a softened baseline microstructure suitable for machining and forming prior to age hardening, with moderate strength and good ductility as supplied per AMS 5542.
Inconel X-750 is a precipitation-hardened nickel-iron-base superalloy strengthened by gamma-double-prime (γ″) phase, designed for high-temperature applications in gas turbines, jet engines, and aerospace components requiring sustained strength to approximately 1300°F (704°C). The equalized and aged condition provides optimized strength and creep resistance through controlled heat treatment, with tensile yield strength typically in the 140–160 ksi range and superior bearing and shear strength characteristics suitable for critical fasteners and structural components.
L-605 (CoCrWNi) is a cobalt-based superalloy containing tungsten and nickel, designed for high-temperature structural applications in gas turbines and aerospace engines, offering exceptional strength and oxidation resistance up to approximately 1000°C. Available in annealed (stress-relieved, lower strength) and solution-treated (precipitation-hardened, higher strength) conditions, it provides superior creep resistance and thermal fatigue performance compared to iron-based alternatives in demanding propulsion and power generation environments.
L-605 (Haynes 25) is a cobalt-nickel-chromium superalloy solution-treated to provide high strength and excellent creep resistance up to 1200°C (2200°F), suitable for jet engine combustors, afterburners, and high-temperature airframe components. This condition delivers optimal combination of tensile strength, ductility, and thermal fatigue resistance for demanding aerospace applications requiring sustained elevated-temperature performance.
MP159 is a cobalt-based superalloy containing nickel, chromium, and molybdenum, designed for high-temperature aerospace applications requiring excellent fatigue strength and corrosion resistance up to approximately 700°C. The STA (solution-treated and aged) cold-drawn condition provides enhanced tensile strength and fatigue performance through precipitation hardening, making it suitable for engine components, fasteners, and structural elements in military aircraft and gas turbine applications.
MP159 is a nickel-cobalt-base superalloy containing chromium, molybdenum, and tungsten, designed for high-strength fastener and spring applications in aerospace engines and structures. The STA (Solution Treated and Aged) cold-drawn condition provides superior tensile strength and yield strength with controlled ductility, maintaining excellent fatigue resistance and stress-rupture performance at elevated temperatures up to approximately 700°C.
MP35N is a cobalt-nickel-chromium-molybdenum superalloy designed for high-strength, corrosion-resistant applications requiring excellent fatigue resistance and performance in cryogenic to moderate elevated temperatures. Primarily used in aerospace fasteners, springs, and medical implants, MP35N offers yield strengths exceeding 1,000 MPa with superior resistance to stress-corrosion cracking and seawater corrosion compared to conventional stainless steels.
MP35N is a cobalt-nickel-chromium-molybdenum superalloy solution treated to a fully annealed condition, providing excellent corrosion and fatigue resistance for aerospace applications requiring high strength retention at elevated temperatures. Solution-treated MP35N offers optimal ductility and toughness with moderate strength levels, making it suitable for critical rotating components and fasteners in jet engines and gas turbines operating up to approximately 650°C.
MP35N STA Cold Drawn is a cobalt-nickel-chromium-molybdenum superalloy in solution-treated and aged condition with cold-drawing, used primarily in high-temperature aerospace fasteners and springs requiring exceptional strength retention to 600°C and excellent corrosion resistance in oxidizing and seawater environments. The cold-drawn condition provides increased yield and tensile strength with controlled ductility, making it suitable for applications demanding both mechanical performance and fatigue resistance at elevated temperatures.
N-155 is a cobalt-based superalloy containing chromium, aluminum, and tungsten, designed for high-temperature structural applications in jet engines and gas turbines requiring strength retention above 1000°C. The solution-treated condition provides optimal strength and creep resistance through controlled precipitation hardening, with excellent oxidation resistance and fatigue performance in extreme thermal cycling environments.
N-155 Solution Treated is a cobalt-based superalloy with nickel, chromium, and tungsten alloying elements designed for high-temperature structural applications in jet engines and gas turbines where sustained strength above 1200°F is required. The solution-treated condition provides balanced strength and ductility through controlled grain structure, with tensile properties defined in AMS 5532/5585 specifications for sheet, strip, plate, and tubing forms.
Ni-Mn-Ga is a ferromagnetic shape memory alloy (FSMA) that combines magnetic properties with the ability to recover large strains when heated or exposed to magnetic fields, enabling actuation without traditional electrical current. The alloy is employed in niche applications requiring compact, silent, responsive actuators—particularly in aerospace, automotive adaptive systems, and biomedical devices where conventional electromagnetic or piezoelectric solutions are impractical. Engineers choose this material when shape recovery must be triggered magnetically, when noise and power efficiency are critical, or when space constraints demand high strain output from minimal volume, though availability, cost, and brittleness relative to conventional shape memory alloys (like NiTi) currently limit adoption to specialized, performance-critical roles.
NiTiCu is a copper-modified nickel-titanium shape memory alloy that combines the reversible phase transformation behavior of NiTi with improved thermal stability from copper alloying. The addition of copper narrows the thermal hysteresis and raises transition temperatures, making this alloy useful for applications requiring precise actuation within constrained temperature windows or where repeatability across thermal cycles is critical. Unlike binary NiTi, the ternary composition offers better control over the austenite-finish and martensite-start temperatures, reducing energy losses and improving cycling durability in temperature-sensitive systems.
NiTiHf is a ternary shape memory alloy combining nickel, titanium, and hafnium, engineered to extend the operating temperature range beyond conventional NiTi by raising transformation temperatures while maintaining superelastic and shape-memory functionality. It is used in aerospace propulsion systems, high-temperature actuators, and thermal-cycling-resistant seals where traditional NiTi becomes unreliable; the hafnium addition is critical for applications demanding performance above 100°C where shape recovery and damping are essential design features. Compared to NiTi, NiTiHf trades some strain capacity and thermal stability window for significantly higher service temperatures, making it the material of choice when heating rules out conventional shape memory alloys but full-ceramic or superalloy rigidity is undesirable.
NiTiNb is a ternary nickel-titanium-niobium shape memory alloy engineered to exhibit wide thermal hysteresis, enabling large temperature differentials between the martensite and austenite phases during thermomechanical cycling. This composition is used in applications requiring high actuation temperatures, damping over broad temperature ranges, or robust recovery behavior under cyclic loading, particularly in aerospace sealing systems, precision actuators, and vibration isolation devices where conventional NiTi alloys lack sufficient thermal span or functional stability.
Nitinol (NiTi) is a near-equiatomic nickel-titanium intermetallic alloy that exhibits shape memory and superelastic behavior, allowing it to recover large deformations upon heating or unloading without permanent plastic strain. This unique metallurgical behavior—driven by reversible martensitic phase transformations—makes it invaluable in applications requiring actuators, dampers, or components that must return to a programmed geometry after deformation. Engineers select Nitinol over conventional metals when design space is constrained and active or passive motion control is needed, or when the ability to absorb large strains without failure is critical to device function.
Nitinol (NiTi) is a nickel-titanium shape-memory and superelastic alloy that exhibits remarkable strain recovery—when deformed, it returns to its original shape upon unloading or heating, depending on the alloy's thermal state. This property stems from a reversible phase transformation between austenite and martensite crystal structures, making it fundamentally different from conventional metals. In superelastic form (used at room temperature above the austenite finish temperature), Nitinol absorbs and releases large elastic deformations repeatedly without permanent set, enabling designs where flexibility and damage tolerance are critical. The alloy is widely deployed in medical devices—stents, guidewires, orthodontic wires, and surgical instruments—where its biocompatibility, fatigue resistance, and ability to conform to complex geometries while maintaining structural integrity are essential; it is also found in aerospace actuators, seismic dampers, and precision mechanical switches where its unique combination of elasticity and hysteretic energy absorption outperforms conventional springs or elastic materials.
Oxidized Zr-2.5Nb (marketed as Oxinium) is a surface-hardened zirconium alloy created by controlled oxidation of a zirconium-niobium base metal, producing a ceramic oxide layer bonded to a ductile metallic substrate. This material is engineered specifically for bearing and articulating surfaces in orthopedic implants, where the hard oxide exterior minimizes wear and the tough underlying alloy provides damage tolerance. Compared to conventional cobalt-chromium or alumina-on-plastic combinations, Oxinium offers reduced wear rates and improved scratch resistance while maintaining the fracture toughness advantage of metallic substrates, making it particularly valuable in hip and knee replacements where long-term durability and low particulate generation are critical.
PH13-8Mo is a precipitation-hardening martensitic stainless steel (13% Cr, 8% Ni, Mo) used in aerospace and high-performance applications requiring high strength (yield strength typically 1,240–1,520 MPa depending on temper) and good corrosion resistance up to ~300°C. The H-series tempers (H950–H1150) provide increasing strength levels through controlled aging, with H1050 being the most common aerospace specification balancing strength and fracture toughness.
PH13-8Mo is a martensitic precipitation-hardening stainless steel (13% Cr, 8% Ni, Mo, Al) that achieves ultra-high strength in the H1000 condition through age hardening, providing yield strengths around 1310 MPa with good corrosion resistance and fatigue performance for aerospace fasteners, bearings, and critical structural components. The H1000 temper represents maximum strength conditioning and maintains useful strength to approximately 300°C with excellent bearing fatigue and fatigue crack growth resistance, making it suitable for demanding load-bearing applications where both strength and corrosion resistance are required.
PH13-8Mo is a martensitic precipitation-hardening stainless steel (13% Cr, 8% Mo) that achieves high strength through aging heat treatment, offering excellent corrosion resistance and fatigue performance in aerospace and defense applications up to approximately 480°C. The H1025 condition (solution-treated and aged) provides tensile strength around 1310 MPa with good ductility and toughness, suitable for highly stressed structural components including fasteners, landing gear, and pressure vessels.
PH13-8Mo is a martensitic precipitation-hardening stainless steel (13% Cr, 8% Ni, Mo, Al additions) used in aerospace applications requiring high strength and corrosion resistance to approximately 600°C; the H1050 condition provides a yield strength around 1,050 ksi through precipitation hardening, with excellent fatigue performance and stress-corrosion cracking resistance in chloride environments.
PH13-8Mo H1100 is a precipitation-hardened martensitic stainless steel (13% Cr, 8% Mo, 2.5% Ni) that achieves high strength (typically 1310 MPa yield) through H1100 heat treatment (1100°F aging), providing excellent corrosion resistance and fatigue performance for aerospace fasteners, landing gear components, and other critical applications requiring high strength-to-weight ratio at elevated temperatures up to ~315°C. Available in forged, ring, and extruded bar forms, this alloy offers good ductility and toughness balanced with superior tensile strength suitable for demanding structural and fastening applications per AMS 5629.
PH13-8Mo is a precipitation-hardening martensitic stainless steel (13% Cr, 8% Ni, 2.5% Mo) used in aerospace applications requiring high strength (typically 1300+ MPa yield) combined with moderate corrosion resistance and good fatigue properties; the H1150 condition provides optimal strength through heat treatment at 1150°F with excellent dimensional stability for critical fasteners and structural components.
PH13-8Mo stainless steel is a precipitation-hardening martensitic stainless steel containing molybdenum and copper that delivers high strength (typically 1,310 MPa yield) with good corrosion resistance, suited for aircraft engine components and fasteners. The H950 condition is aged to provide peak hardness and tensile properties while maintaining adequate ductility and fracture toughness for critical aerospace applications per AMS 5629.
PH15-7Mo is a precipitation-hardening stainless steel (Fe-Cr-Ni-Mo-Al) combining high strength up to ~1380 MPa with good corrosion resistance and fracture toughness, used primarily in aerospace applications requiring excellent fatigue performance and environmental resistance at moderate temperatures. The material is available in F (solution-treated), H1050 (aged for strength), and Sta (stress-relieved annealed) conditions, with elastic property data from MIL-HDBK-5J providing design allowables for aerospace structural applications.
PH15-7Mo is a precipitation-hardening stainless steel with molybdenum strengthening providing yield strengths around 1,380 MPa (200 ksi) in the H1050 condition, suitable for aerospace fasteners, springs, and high-strength structural components requiring corrosion resistance at elevated temperatures. The H1050 temper delivers optimized strength through controlled aging while maintaining toughness for critical bearing and fastening applications in aircraft engines and airframes.
Porous tantalum, also known by the trade name Trabecular Metal, is a highly biocompatible pure tantalum foam structure engineered with interconnected porosity to mimic cancellous bone architecture. Its combination of biological integration capability, corrosion resistance, and radiopacity makes it the preferred choice for orthopedic and spinal implants where bone on-growth and long-term fixation are critical; it outperforms alternatives like titanium alloys in applications requiring rapid osseointegration and can eliminate the need for bone cement or supplemental fixation screws.
QE22A is a rare-earth magnesium alloy containing rare-earth elements and silver, designed for elevated-temperature aerospace applications requiring creep resistance up to approximately 250°C. The T6 temper (solution heat-treated and artificially aged) provides optimized strength and dimensional stability for gas turbine engine components and similar high-temperature service environments.
QE22A is a magnesium alloy containing rare earth elements (primarily cerium and lanthanum) designed for elevated-temperature aerospace applications, offering superior creep resistance and strength retention up to approximately 300°C. The T6 temper (solution heat-treated and artificially aged) provides optimal mechanical properties and dimensional stability for sand-cast components in engines and structural applications operating under thermal stress.
René 41 is a cobalt-based superalloy containing nickel, chromium, molybdenum, and aluminum alloying elements, designed for high-temperature structural applications in gas turbines and jet engines. The STA (solution-treated and aged) condition provides elevated-temperature strength retention and creep resistance up to approximately 1200°F (650°C), with excellent fatigue performance and oxidation resistance for demanding aerospace propulsion environments.
René 41 STA is a nickel-base superalloy (Ni-Co-Cr-Mo-W-Al-Ti) in solution heat-treated and aged condition, designed for high-temperature structural applications in jet engines and gas turbines operating up to 1100°F (593°C). The STA condition provides optimized strength and creep resistance through controlled grain structure and precipitation hardening, with excellent bearing strength and fatigue performance in bar, forging, plate, and sheet forms.
René 88DT is a nickel-based superalloy designed for high-temperature structural applications requiring exceptional strength and creep resistance at elevated temperatures. It is used primarily in aerospace propulsion systems—particularly in turbine engine components such as blades, vanes, and casings—where sustained thermal and mechanical loads demand reliable performance in extreme environments. Engineers select this alloy when superior high-temperature capability and fatigue resistance are critical, making it preferable to conventional nickel superalloys in next-generation engine designs and demanding industrial gas turbine applications.
Unalloyed tantalum (ASTM F560) is a highly pure refractory metal (≥99.5% Ta) prized for its exceptional corrosion resistance, biocompatibility, and ability to withstand extreme temperatures without degradation. It is widely used in chemical processing equipment, medical implants, and aerospace/defense applications where exposure to aggressive corrosive environments or physiological fluids demands a material that remains stable and inert over extended service life. Engineers select tantalum when stainless steels and nickel alloys prove insufficient due to chloride pitting, sulfuric acid attack, or when direct contact with living tissue requires proven biocompatibility without elution of harmful ions.
Ti-10V-2Fe-3Al is a near-beta titanium alloy designed for high-strength aerospace applications, combining vanadium and iron as beta-stabilizers with aluminum for strength and density control. The STA (solution-treated and aged) condition provides tensile strength in the 1200–1400 MPa range with good fracture toughness and fatigue resistance, making it suitable for landing gear, fasteners, and engine components requiring elevated strength-to-weight performance.
Ti-10V-2Fe-3Al is a high-strength metastable beta titanium alloy containing vanadium, iron, and aluminum alloying elements, used primarily in aerospace landing gear, fasteners, and structural components requiring excellent damage tolerance and fatigue resistance. The STA (solution treated and aged) condition provides yield strength in the 1200–1400 MPa range with good fracture toughness and ductility, enabling reliable performance in demanding bearing and shear-critical applications.
Ti-13Nb-13Zr is a near-beta titanium alloy composed primarily of titanium with balanced additions of niobium and zirconium, designed to achieve low elastic modulus while maintaining strength and biocompatibility. It is primarily used in orthopedic implants and dental applications where reducing the stiffness mismatch between implant and bone is critical to prevent stress shielding and promote long-term integration. This alloy is notable for combining β-stabilizing elements (Nb, Zr) that lower the Young's modulus compared to conventional titanium alloys, making it attractive for load-bearing implants that require both mechanical reliability and biological acceptance without the cytotoxicity concerns of vanadium-containing alternatives.
Ti-13V-11Cr-3Al is a metastable beta titanium alloy containing high vanadium and chromium additions designed for applications requiring high strength-to-weight ratio and moderate temperature capability in aerospace structural components. The alloy exhibits excellent hardenability through solution treatment and aging, with density approximately 4.8 g/cm³ and Young's modulus around 103 GPa, with strength varying significantly across Annealed, F (mill annealed), and STA (solution treated and aged) conditions.
Ti-13V-11Cr-3Al is a metastable beta titanium alloy containing vanadium and chromium additions for enhanced strength and hardenability, primarily used in aerospace fasteners, springs, and bearing applications. The annealed condition provides moderate strength levels (approximately 130–150 ksi yield) with improved ductility and fracture toughness compared to aged conditions, suitable for applications requiring good fatigue resistance and damage tolerance.
Ti-13V-11Cr-3Al is a metastable beta titanium alloy containing 13% vanadium, 11% chromium, and 3% aluminum, designed for high-strength aerospace fastener and structural applications requiring superior bearing strength and fatigue resistance. The STA (solution-treated and aged) condition provides yield strengths in the 1,200–1,400 MPa range with excellent compressive properties and damage tolerance, making it suitable for critical bearing surfaces and highly stressed mechanical components in aircraft structures and engines.
Ti-15Mo is a metastable beta-phase titanium alloy containing 15 wt% molybdenum, designed to combine the corrosion resistance and biocompatibility of titanium with the strength and lower modulus benefits of beta-stabilized microstructures. It is used in biomedical implants (orthopedic and dental), aerospace components, and chemical processing equipment where corrosion resistance, biocompatibility, and moderate strength are prioritized; compared to α+β titanium alloys like Ti-6Al-4V, Ti-15Mo offers improved corrosion resistance and lower stiffness while maintaining good strength, making it particularly valuable in load-bearing implants where modulus matching to bone or tissue is beneficial.
Ti-15V-3Cr-3Sn-3Al is a metastable beta titanium alloy designed for high-strength aerospace applications requiring excellent damage tolerance and fatigue resistance. The alloy offers tensile strengths exceeding 150 ksi with good fracture toughness, making it suitable for aircraft fuselage structure, fasteners, and landing gear components.
Ti-15V-3Cr-3Sn-3Al is a near-beta titanium alloy designed for high-strength applications requiring excellent damage tolerance and formability, with applications in aerospace fasteners, springs, and structural components. The STA (solution treated and aged at 1000°F for 8 hours) condition provides optimized strength and ductility balance, typically yielding tensile strengths in the 140-160 ksi range with good fatigue resistance and fracture toughness retention.
Alpha titanium alloy with excellent weldability and cryogenic toughness. 795 MPa yield. Used in cryogenic applications (liquid hydrogen/oxygen), high-pressure gas bottles, and airframe forgings. One of the oldest aerospace titanium alloys.
Ti-5Al-2.5Sn is a near-alpha titanium alloy used primarily in aircraft engines and high-temperature aerospace applications, offering good creep resistance and tensile strength up to approximately 600°F. The annealed condition provides optimal ductility and dimensional stability after hot forming operations, with yield strength around 70-90 ksi and excellent damage tolerance characteristics.
Ti-6Al-2Sn-4Zr-2Mo is a near-alpha titanium alloy combining aluminum, tin, zirconium, and molybdenum additions for elevated temperature strength and creep resistance; used primarily in compressor and fastener applications in military and commercial jet engines operating up to ~600°C with good fatigue and stress-rupture performance.