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The need for nickel-base powder metallurgy(PM)superalloy turbine discs is becoming increasingly evident.With the eventual aim of improving thrust-to-weight ratio of aeroengines for power generation,well integration of significantly high strength,high damage tolerance and high-temperature capability would be reasonably required.An advanced PM superalloy,which was designed for applications up to 815-850 ℃,was experimentally investigated.Emphasis was primarily put on microstructure and mechanical properties.The results indicated the measured phases in the sample were composed ofγ,γ′,MC,and M3B2.With uniform coarse grain microstructure(ASTM 5-6),the sample appeared to exhibit overwhelming superiority over the prior art materials FGH95,FGH96,FGH97 and FGH98.The dominant embodiments consisted of high tensile strength(R m =1 000 MPa and R p0.2=800MPa at 850℃),strong creep resistance(ξp=0.12%at 815℃/400MPa/50h),and considerable stressrupture life(τ=457.4hat 815 ℃/450 MPa).The technical practicability of applications up to 815-850 ℃ of this alloy was conclusively proved.
The need for nickel-base powder metallurgy (PM) superalloy turbine discs is becoming increasingly evident.With the eventual aim of improving thrust-to-weight ratio of aeroengines for power generation, well integration of significantly high strength, high damage tolerance and high- Temperature capability would be reasonably required. An advanced PM superalloy, which was designed for applications up to 815-850 ° C, was experimentally investigated. Emphasis was been put on microstructure and mechanical properties. The results indicated that the measured phases in the sample were composed of γ , γ ’, MC, and M3B2.With uniform coarse grain microstructure (ASTM 5-6), the sample has to exhibit overwhelming superiority over the prior art materials FGH95, FGH96, FGH97 and FGH98. Rm = 1 000 MPa and R p0.2 = 800 MPa at 850 ° C), strong creep resistance (ξp = 0.12% at 815 ° C / 400 MPa / 50h), and considerable stress rupture life (τ = 457.4 ha 815 ° C / 450 MPa) The tec hnical practicability of applications up to 815-850 ℃ of this alloy was conclusively proved.