Abstract: The isothermal oxidation behavior of a new developed Ni base superalloy named DM02
for high temperature dies was studied in this paper. The dynamic curve was achieved by monitoring
weight gain of the alloy as a function of time. The results showed that the alloy had fairly good
oxidation resistance at 1050°C and 1100°C. The oxidation kinetics at both 1050°C and 1100°C
followed parabolic rules in segment. It has been found that the oxidation of the alloy was controlled
by multi-oxides of (Ni, Co)O, (Ni, Co)Al2O4, and NiWO4, growth mechanism in the primary stage,
and by Al2O3, NiAl2O4 growth mechanism in the following stage. After oxidation at 1050°C for 100h,
the oxide scale of the alloy was mainly composed of two areas. Some were thin uniform (Ni，
Co)Al2O4(outer)/Al2O3 (inner) composites scale and others were multi-layer oxide scale of ( Ni,Co)O
/ multi-oxides (mainly NiWO4、NiO and NiAl2O4.) /Al2O3.
Abstract: The effect of Ta, Nb, Hf and Zr on the microstructure and high temperature tensile
properties of DM02 alloy, which is a novel developed Ni base superalloy for high temperature die
material, had been studied in this paper. The results showed that the four alloying elements affect the
composition and morphology of carbides obviously, and have almost no effect on the morphology and
size of γ´ phase in DM02 alloy. 0.5-1wt% Hf make the morphology of MC carbide change from
bone-like to blocky and inhibit the formation of primary M6C carbide, thus improve the ductility of
DM02 alloy, while 0.1wt% Zr has no similar effect. The strengthening effect of 3wt% Ta is better
than that of 1.5wt% Nb. DM02 alloy with 3wt% Ta and 0.5wt% Hf has high strength and good
ductility at 1050°C.
Abstract: Recently developed alloy 783 (nominal composition of Ni-34Co-26Fe-5.4Al-3Nb-3Cr,
UNS R30783) is precipitation strengthened by Ni3Al-type gamma prime and NiAl-type beta phases.
The alloy is being used for seals/casings in aircraft gas turbines and for bolting in steam turbines due
to its low co-efficient of thermal expansion, high strength, and good oxidation resistance. It has also
been specified for other aircraft gas turbine components such as rings for casings and shrouds. This
paper presents the alloy’s basic characteristics, applications, and hot and cold workability.
Abstract: A new kind of cast & wrought (C&W) Ni-Co base superalloys named as “TMW alloys”
was developed recently for compressor and turbine disk of gas turbine engines in the High
Temperature Materials 21 Project at the National Institute for Materials Science (NIMS) in Japan.
These Ni-Co base superalloys combine the characters of two kinds of γ- γ’ two-phase alloys (Ni-base
and Co-base superalloys) and can be fabricated by cheap cast and wrought processing route. The
results showed that some of these TMW alloys have superior tensile strength at temperatures up to
750 °C and higher creep resistances up to 725 °C than commercial UDIMET 720 LI alloy.
Abstract: High temperature structure stability of 2 important Nb-containing Ni-base superalloys
Inconel 718 (Ni-19Cr-18Fe-3Mo-5Nb-1Ti-0.5Al) and Inconel 740 (Ni-25Cr-20Co-0.5Mo-2Nb
-1.8Ti-0.8Al) have been studied on the relationship of microstructure to mechanical properties via
SEM, TEM, SAD, XRD and quantitative determination of precipitated phases by micro-chemical
analysis. The longest exposure times are 50,000hrs at 650°C for Alloy 718 and 4,000hrs at 704°C,
725°C and 760°C for Alloy 740.
The structure instabilities for these 2 Alloys are: 1) strengthening phases γ″/γ′ coarsening; 2)
meta-stable strengthening phases change to stable phase, such as γ″→ δ-Ni3Nb for Alloy 718 and
γ′→ η-Ni3Ti for Alloy 740; 3) embrittling phases formation, such as α-Cr and σ-phase formation in
Alloy 718 and high Si-containing G-phase formation in Alloy 740.
On the base of understanding phase changes at high temperature exposures the structure stability
of Inconel 718 and Inconel 740 has been improved both by minor adjustment of alloys chemistry.
The modifications of Alloy 718 and Alloy 740 are to be developed in the near future.
Abstract: Some basic principles of non-equilibrium grain boundary segregation (NGS) and their
applications to B, Mg P segregation to boundaries in Ni-base superalloy are reviewed. An attempt is
made to emphasize the evidences of NGS for B, Mg, P in Ni-base superalloy.
Abstract: The nucleation and development of dynamic recrystallization (DRX) in hot deformed
superalloy Inconel 718 during uniaxial compression were investigated by optical microscopy and
electron back-scattered diffraction (EBSD) technique. The results showed that the discontinuous
dynamic recrystallization was the predominant DRX mechanism in this alloy. The variations of
partial crystallographic orientations led to the individual nucleation inside the deformed grains, which
implied the occurrence of local continuous dynamic recrystallization. The progressive subgrain
rotation can be confirmed neither near the prior high angle grain boundaries nor within the original
grains. It was found that, as the strain increased, the initial twin boundaries were gradually
transformed to ordinary mobile high angle boundaries. Meanwhile, the new twin boundaries were
formed inside the recrystallized grain necklaces. It was suggested that the characteristics of the twin
boundaries evolution with increasing strain were associated with the transformation of initial twin
boundaries as well as the generation of new ones, which resulted in the development of DRX.
Abstract: During long-term thermal exposure, the degeneration of primary MC carbide is a
diffusion-controlled process. With the element exchange between the primary MC carbide and the γ
matrix, three MC degeneration reactions, that is, γ + MC → γ' + M23C6 (Reaction I), MC + γ →η+
M23C6 (Reaction II) and MC + γ →η+ M6C (Reaction III), sequentially operates. Of them Reaction III
has never been reported in the previous references and is kinetically most difficulty. It is also shown
that the grain boundary MC decomposes much more rapidly than the grain interior MC and that
Reaction III is not as often seen at the grain boundary as in the grain interior.
Abstract: Ni-based superalloys are extensively used in the manufacture of aircraft engine
components because of their excellent heat-resistant and corrosion-resistant properties. The principal
joining processes for Ni-based superalloys are TIG welding, MIG welding, submerged arc welding,
electron beam welding, and CO2 laser welding. In this investigation, a robotic 4-kW continuous-wave
Nd:YAG laser system was used to identify the optimal laser welding process for 2.0 mm thick Inconel
(IN) 718 sheets. The effect of various processing parameters, which included power input, welding
speed, weld geometry and filler wire, was studied using the Taguchi design of experiment (DOE)
methodology. The DOE methodology enabled the evaluation of the relationship between the process
parameters and the quality of the welded joints, from which the optimal Nd:YAG laser welding
process was developed for IN718 alloy. Joint quality was examined by tensile and nondestructive
testing methods. Using the optimal process established in this research, mechanically-sound welds
with narrow fusion and heat-affected zones were produced. The outcome of this research
demonstrates the feasibility of the application of Nd:YAG laser in the joining of IN718 sheets for the
manufacture of aircraft engine components.