X6NiCrTiMoVB25-15-2
2018-02-09 16:47:12
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Steel Grade: X6NiCrTiMoVB25-15-2 | Material No.: 1.4980 | Aviation Standard Material No.: 1.4944
CHEMICAL COMPOSITION(X6NiCrTiMoVB25-15-2):
C(％) : 0.03～0.08
Si(％) : ≤1.00
Mn(％) : 1.00～2.00
P(％)≤: 0.025
S(％)≤: 0.015
Cr(％) : 13.5～16.0
Ni(％) : 24.0～27.0
Mo(％) : 1.00～1.50
Other(％) : Al≤0.35,Ti1.90～2.30,V0.10～0.50,V0.003～0.010
HEAT TREATMENT (X6NiCrTiMoVB25-15-2):
Thermal Forming/℃: 1100～950
Heat Treatment|Annealing/℃: —
Heat Treatment|Quenching or Solution Treatment/℃: 885～915Air/Water
Heat Treatment|Tempering/℃: 700～735
Heat Treatment|Ageing/℃: 710～730
MECHANICAL PROPERTIES UNDER NORMAL TEMPERATURE (X6NiCrTiMoVB25-15-2):
Condition: Precipitation Harding
Tensile Strength|σb/MPa: 930～1180
Yield Strength|σs≥/MPa: 635
Extensibility|δ5≥(％) : 12
Ballistic|Akv(DVM) : 27
Thermostability/℃⑥: 700
Non-Scale in Air/℃⑥: 820
MECHANICAL PROPERTIES UNDER NORMAL TEMPERATURE (X6NiCrTiMoVB25-15-2):
Tensile Strength|σ0.2|200℃/Mpa: 559 Tensile Strength|σ0.2|300℃/Mpa: 539
Tensile Strength|σ0.2|400℃/Mpa: 520 Tensile Strength|σ0.2|500℃/Mpa: 500
Tensile Strength|σ0.2|600℃/Mpa: 451 Tensile Strength|σ0.2|700℃/Mpa: 314
Tensile Strength|σ0.2|800℃/Mpa: 78
Creep Rupture|1000h|600℃/Mpa: 441 Creep Rupture|1000h|700℃/Mpa: 206
Creep Rupture|1000h|800℃/Mpa: — Creep Rupture|1000h|900℃/Mpa: —
Creep Rupture|10000h|600℃/Mpa: 304 Creep Rupture|10000h|700℃/Mpa: 118
Creep Rupture|10000h|800℃/Mpa: — Creep Rupture|10000h|900℃/Mpa: —
Creep Rupture|100000h|600℃/Mpa: — Creep Rupture|100000h|700℃/Mpa: —
Creep Rupture|100000h|800℃/Mpa: — Creep Rupture|100000h|900℃/Mpa: —
Remark(X6NiCrTiMoVB25-15-2):
①, Co15.0～21.0，Al1.00～2.00，Ti2.00～3.00，Zr≤0.15，B≤0.020，Fe≤1.50，Cu≤0.20；
②, Co18.0～22.0，Al4.5～4.9，Ti0.90～1.50，Zr≤0.15，B0.003～0.010，Fe≤1.0，Cu≤0.20；
③, Co5.00～7.50，Nb0.20～0.60，V0.10～0.60，B0.005～0.015，N≤0.035；
④, Co≤2.0，Al1.00～1.80，Ti1.80～2.70，B≤0.008，Fe≤3.00，Cu≤0.20
⑤, Co≤0.50，Al0.20～0.50，Ti0.20～0.50，Nb≤0.10，Cu≤0.50，N≤0.030。
⑥, The temperature is approximate data.
Introduction Valve Steel(X6NiCrTiMoVB25-15-2)
High temperature alloy refers to iron, nickel and cobalt based, a kind of metal material to high temperature is over 600 DEG C and a certain stress under the action of long-term work, is excellent in high temperature strength, oxidation resistance and thermal corrosion resistance, fatigue resistance and fracture toughness and good comprehensive performance, also known as the "super alloy, mainly used in the aerospace field and energy field.
Based on the above characteristics and high alloying degree of superalloys, it is also known as "super alloy". It is an important material widely used in aviation, aerospace, petroleum, chemical industry and warships. According to the matrix element, the superalloy is divided into iron base, nickel base, cobalt base and other high temperature alloys. The service temperature of iron-based superalloys can only reach 750~780 degrees. For those heat-resistant parts at higher temperatures, nickel based and refractory metal based alloys are used. Nickel based superalloys play an important role in the whole field of high temperature alloys. They are widely used to make the most hot end parts of aero jet engines and various industrial gas turbines.
Application(X6NiCrTiMoVB25-15-2)
Nickel-based superalloys are used in load-bearing structures to the highest homologous temperature of any common alloy system (Tm = 0.9, or 90% of their melting point). Among the most demanding applications for a structural material are those in the hot sections of turbine engines. The preeminence of superalloys is reflected in the fact that they currently comprise over 50% of the weight of advanced aircraft engines. The widespread use of superalloys in turbine engines coupled with the fact that the thermodynamic efficiency of turbine engines is increased with increasing turbine inlet temperatures has, in part, provided the motivation for increasing the maximum-use temperature of superalloys. In fact, during the past 30 years turbine airfoil temperature capability has increased on average by about 4 °F (2.2 °C) per year.y.
HOT SALE:
SA-675GR70, SA-387GR91, X6NiCrTiMoVB25-15-2, 17-4PH, 15-5PH, NKA80
ASTM 630, X3CrNiMo13-4, UNS41500, X10CrNiTi18-10, S17400,
X5CrNiCuNbl6-4, 316Ti, 301A, 303, 304L, 310S, 316L, 317L, 321,
NKA80, DIN 1.4731, DIN 1.4021, DIN 1.4016, DIN 1.4571, DIN 1.4418,
616, 440B, 440C, 431, 430FR, 430F, 430, 422, 416, 410, 405,
ASTM D2, X155CrMoV12-1, ASTM D3, AISI H11, AISI H13, X6NiCrTiMoVB25-15-2
Steel Grade: X6NiCrTiMoVB25-15-2 | Material No.: 1.4980 | Aviation Standard Material No.: 1.4944
CHEMICAL COMPOSITION(X6NiCrTiMoVB25-15-2):
C(％) : 0.03～0.08
Si(％) : ≤1.00
Mn(％) : 1.00～2.00
P(％)≤: 0.025
S(％)≤: 0.015
Cr(％) : 13.5～16.0
Ni(％) : 24.0～27.0
Mo(％) : 1.00～1.50
Other(％) : Al≤0.35,Ti1.90～2.30,V0.10～0.50,V0.003～0.010
HEAT TREATMENT (X6NiCrTiMoVB25-15-2):
Thermal Forming/℃: 1100～950
Heat Treatment|Annealing/℃: —
Heat Treatment|Quenching or Solution Treatment/℃: 885～915Air/Water
Heat Treatment|Tempering/℃: 700～735
Heat Treatment|Ageing/℃: 710～730
MECHANICAL PROPERTIES UNDER NORMAL TEMPERATURE (X6NiCrTiMoVB25-15-2):
Condition: Precipitation Harding
Tensile Strength|σb/MPa: 930～1180
Yield Strength|σs≥/MPa: 635
Extensibility|δ5≥(％) : 12
Ballistic|Akv(DVM) : 27
Thermostability/℃⑥: 700
Non-Scale in Air/℃⑥: 820
MECHANICAL PROPERTIES UNDER NORMAL TEMPERATURE (X6NiCrTiMoVB25-15-2):
Tensile Strength|σ0.2|200℃/Mpa: 559 Tensile Strength|σ0.2|300℃/Mpa: 539
Tensile Strength|σ0.2|400℃/Mpa: 520 Tensile Strength|σ0.2|500℃/Mpa: 500
Tensile Strength|σ0.2|600℃/Mpa: 451 Tensile Strength|σ0.2|700℃/Mpa: 314
Tensile Strength|σ0.2|800℃/Mpa: 78
Creep Rupture|1000h|600℃/Mpa: 441 Creep Rupture|1000h|700℃/Mpa: 206
Creep Rupture|1000h|800℃/Mpa: — Creep Rupture|1000h|900℃/Mpa: —
Creep Rupture|10000h|600℃/Mpa: 304 Creep Rupture|10000h|700℃/Mpa: 118
Creep Rupture|10000h|800℃/Mpa: — Creep Rupture|10000h|900℃/Mpa: —
Creep Rupture|100000h|600℃/Mpa: — Creep Rupture|100000h|700℃/Mpa: —
Creep Rupture|100000h|800℃/Mpa: — Creep Rupture|100000h|900℃/Mpa: —
Remark(X6NiCrTiMoVB25-15-2):
①, Co15.0～21.0，Al1.00～2.00，Ti2.00～3.00，Zr≤0.15，B≤0.020，Fe≤1.50，Cu≤0.20；
②, Co18.0～22.0，Al4.5～4.9，Ti0.90～1.50，Zr≤0.15，B0.003～0.010，Fe≤1.0，Cu≤0.20；
③, Co5.00～7.50，Nb0.20～0.60，V0.10～0.60，B0.005～0.015，N≤0.035；
④, Co≤2.0，Al1.00～1.80，Ti1.80～2.70，B≤0.008，Fe≤3.00，Cu≤0.20
⑤, Co≤0.50，Al0.20～0.50，Ti0.20～0.50，Nb≤0.10，Cu≤0.50，N≤0.030。
⑥, The temperature is approximate data.
Introduction Valve Steel(X6NiCrTiMoVB25-15-2)
High temperature alloy refers to iron, nickel and cobalt based, a kind of metal material to high temperature is over 600 DEG C and a certain stress under the action of long-term work, is excellent in high temperature strength, oxidation resistance and thermal corrosion resistance, fatigue resistance and fracture toughness and good comprehensive performance, also known as the "super alloy, mainly used in the aerospace field and energy field.
Based on the above characteristics and high alloying degree of superalloys, it is also known as "super alloy". It is an important material widely used in aviation, aerospace, petroleum, chemical industry and warships. According to the matrix element, the superalloy is divided into iron base, nickel base, cobalt base and other high temperature alloys. The service temperature of iron-based superalloys can only reach 750~780 degrees. For those heat-resistant parts at higher temperatures, nickel based and refractory metal based alloys are used. Nickel based superalloys play an important role in the whole field of high temperature alloys. They are widely used to make the most hot end parts of aero jet engines and various industrial gas turbines.
Application(X6NiCrTiMoVB25-15-2)
Nickel-based superalloys are used in load-bearing structures to the highest homologous temperature of any common alloy system (Tm = 0.9, or 90% of their melting point). Among the most demanding applications for a structural material are those in the hot sections of turbine engines. The preeminence of superalloys is reflected in the fact that they currently comprise over 50% of the weight of advanced aircraft engines. The widespread use of superalloys in turbine engines coupled with the fact that the thermodynamic efficiency of turbine engines is increased with increasing turbine inlet temperatures has, in part, provided the motivation for increasing the maximum-use temperature of superalloys. In fact, during the past 30 years turbine airfoil temperature capability has increased on average by about 4 °F (2.2 °C) per year.y.
HOT SALE:
SA-675GR70, SA-387GR91, X6NiCrTiMoVB25-15-2, 17-4PH, 15-5PH, NKA80
ASTM 630, X3CrNiMo13-4, UNS41500, X10CrNiTi18-10, S17400,
X5CrNiCuNbl6-4, 316Ti, 301A, 303, 304L, 310S, 316L, 317L, 321,
NKA80, DIN 1.4731, DIN 1.4021, DIN 1.4016, DIN 1.4571, DIN 1.4418,
616, 440B, 440C, 431, 430FR, 430F, 430, 422, 416, 410, 405,
ASTM D2, X155CrMoV12-1, ASTM D3, AISI H11, AISI H13, X6NiCrTiMoVB25-15-2
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