CN109554582A - A kind of nickel-base alloy, preparation method and manufacture article - Google Patents
A kind of nickel-base alloy, preparation method and manufacture article Download PDFInfo
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- CN109554582A CN109554582A CN201810985895.7A CN201810985895A CN109554582A CN 109554582 A CN109554582 A CN 109554582A CN 201810985895 A CN201810985895 A CN 201810985895A CN 109554582 A CN109554582 A CN 109554582A
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/023—Alloys based on nickel
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/03—Making non-ferrous alloys by melting using master alloys
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/175—Superalloys
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Abstract
The present invention provides a kind of nickel-base alloy, preparation method and manufacture article, alloys to be made of following element: the aluminium of 5.45wt%~6.45wt%；The chromium of 5.0wt%~7.0wt%；The cobalt of 5.5wt%~7.0wt%；The molybdenum of 2.0wt%~4.5wt%；The tungsten of 0.5wt%~4.5wt%；The titanium of 0.2wt%~1.0wt%；The tantalum of 6.5wt%~8.5wt%；The rhenium of 1.0wt%~6.0wt%；The hafnium of 0.0wt%~0.25wt%；The carbon of 0.0wt%~0.1wt%；The boron of 0.0wt%~0.01wt%；The nickel of surplus.The application significantly reduces segregation by the total content of the refractory elements such as reasonable disposition Mo, W, Ta and Re, and makes the volume fraction of eutectic phase in as-cast structure lower than 2.0%, maintains the good structure stability of alloy.
Description
Technical field
The present invention relates to nickel-base alloy technical field more particularly to a kind of nickel-base alloys, preparation method and manufacture article.
Background technique
High temperature alloy is a kind of alloy of development for hot environment military service (650 DEG C or more), usually with Fe, Co or Ni member
Element is matrix, containing a large amount of main alloying element Cr, Al, Ti, Ta, Nb, Mo, W or Re etc. and microelement C, B, Zr or Hf etc.,
Be mainly used in gas-turbine unit (including aero-turbine and ground gas turbogenerator), rocket propulsion and
The hot-end component of nuclear reactor etc..Compared to iron-based (iron is Ni-based) high temperature alloy and cobalt base superalloy, nickel base superalloy itself
With more good inoxidizability, and has and take into account intensity and the face-centered cubic crystal structure of toughness and higher mutually stabilization
Property etc., therefore the application on engine thermal end pieces is more extensive.
From microstructure, nickel base superalloy is mainly made of continuous γ matrix phase and discrete γ ' precipitated phase；
γ phase and γ ' Xiang Junwei face-centred cubic structure, the complete coherence of phase interface, but lattice constant, there are small difference, there are lattices
Mismatch.Alloying elements cr, Mo, W and Re etc. are mainly segregated in γ phase, play the role of solution strengthening；Al, Ti, Nb and Ta master
It participates in forming Ni3(Al, Ti, Nb, Ta) phase, i.e. γ ' phase, play apparent precipitation enhancement；When first containing micro C or B
When plain, a small amount of carbide or boride also will form in alloy, play certain precipitation enhancement.As setting up separately, meter is unreasonable
When, alloy is easy that the topological solid matter phase (TCP phase) for being rich in Cr, Mo, W or Re element, example is precipitated under service condition when high temperature is long
As σ phase, μ phase and P are equal；TCP phase itself is more crisp, and has extracted a large amount of solution strengthening elements, therefore will be greatly reduced conjunction
The elevated temperature strength of gold.Therefore, the appearance of TCP phase should be avoided when alloy designs.
The development of high temperature alloy and the development of turbogenerator are inseparable.Turbogenerator belongs to one kind of heat engine, mentions
The temperature of high combustion gas is conducive to increase the overall performance of turbogenerator, such as increases efficiency of combustion and subtract to increase thrust ratio
The discharge amount of few carbon dioxide.Therefore advanced turbogenerator demand for development be continuously improved combustion chamber, high pressure guide vane and
The service temperature of the hot-end components such as high-pressure turbine blade promotes the continuous development of high temperature alloy.
Turbo blade is surrounded turbine wheel shaft high speed rotation by the promotion of combustion gas when being on active service, will due to own wt
The work for generating significant centrifugal stress on blade, therefore requiring blade material that can meet with stresses for a long time at high temperature first
With that is, with good high-temperature creep resistance；Secondly, the presence of residual oxygen requires blade material with good in combustion gas
High-temperature oxidation resistance；Prolonged high temperature action requires blade material to have good structure stability, i.e., reduction will not be precipitated
The brittleness TCP phase of elevated temperature strength.In addition, the important physical and mechanical properties of blade material further include density, hot corrosion resistance,
Anti-fatigue performance etc..
From microstructure, the crystalline substance that is orientated by deformation or the high temperature alloy that manufactures of conventional cast mode by different crystal
Grain is constituted, and there are crystal boundaries between crystal grain.Compared to intra-die, crystal boundary actually belongs to a kind of crystal planar defect, the mistake of atom
Arrange very serious, vacancy and dislocation with higher density.Under the action of high temperature hot activation, crystal boundary is easy to happen apparent soft
Change, bond strength is substantially less than intra-die.It is (horizontal perpendicular to the crystal boundary of loading direction therefore when at high temperature by load
To crystal boundary) it is easier to become crackle origin or crack propagation channel, cause the elevated temperature strength of material to significantly reduce.
After eliminating transverse grain boundaries by directional solidification processes, the elevated temperature strength of nickel base superalloy is available significantly to be mentioned
Thus height has developed directionally solidified superalloy, DS superalloy.After further completely eliminating crystal boundary by single crystal process, and list is developed
Brilliant high temperature alloy.Since there is no crystal boundary, single crystal super alloy drastically reduces boundary-strengthening element C, B, Zr and Hf etc.
It is added.After the content for limiting these elements, the fusing point of alloy is increased substantially, thus can consolidating using higher temperature
Molten heat treatment completely eliminates the as-cast structure formed when solidification, obtains the precipitated phase distribution of fine uniform, closes to improve again
The elevated temperature strength of gold.
However, with refractory element, the especially increase of W and Re content is easily formed in nickel-base alloy as-cast structure significant
Microsegregation --- it is dry that the refractory elements such as W and Re are gathered in dendrite, and the element aggregations such as Al, Ti and Ta cause in interdendritic
Interdendritic forms a large amount of low melting point eutectic phase, seriously affects the progress of solution treatment.The element segregation that do not eliminate results in nickel
Based alloy ingredient and tissue it is uneven, structure stability and mechanical property of the alloy when long under service condition will be reduced.For
The solution treatment degree for improving nickel-base alloy, generallys use higher solution treatment time and higher solid solution temperature,
Under conditions of eutectic phase does not melt, spread refractory element fully, to eliminate microcosmic in cast sturcture
Segregation.Such as the 3.0wt% of amount containing Re, the CMSX-4 alloy of the 6.4wt% of amount containing W, volume fraction of eutectic phase reaches in as-cast structure
12.4%, solid solution temperature is up to 1324 DEG C, and total solution treatment time is up to 16h；And amount containing Re is 6wt%, amount containing W is
The CMSX-10 alloy of 5wt%, for volume fraction of eutectic phase up to 25.6%, solid solution temperature is up to 1365 DEG C in as-cast structure,
Total solution treatment time is up to 45h.Although this high-temperature heat treatment can effectively eliminate the microsegregation in nickel-base alloy,
Complicated and very high temperature heat treating regime not only seriously affects the manufacturing process progress of alloy, and proposes to Equipment for Heating Processing
Acid test.
Summary of the invention
Present invention solves the technical problem that being to provide a kind of nickel-base alloy, nickel-base alloy provided by the present application has lower
Microsegregation degree and lower eutectic phase fraction, to guarantee the performance of microstructure stability and mechanical property.
In view of this, being made of this application provides a kind of nickel-base alloy following element:
The aluminium of 5.45wt%~6.45wt%；
The chromium of 5.0wt%~7.0wt%；
The cobalt of 5.5wt%~7.0wt%；
The molybdenum of 2.0wt%~4.5wt%；
The tungsten of 0.5wt%~4.5wt%；
The titanium of 0.2wt%~1.0wt%；
The tantalum of 6.5wt%~8.5wt%；
The rhenium of 1.0wt%~6.0wt%；
The hafnium of 0.0wt%~0.25wt%；
The carbon of 0.0wt%~0.1wt%；
The boron of 0.0wt%~0.01wt%；
The nickel of surplus.
Preferably, the content of the aluminium is 5.8wt%~6.1wt%.
Preferably, the content of the chromium is 5.8wt%~6.2wt%.
Preferably, the content of the cobalt is 6.2wt%~6.6wt%.
Preferably, the content of the molybdenum is 2.6wt%~4.2wt%.
Preferably, the content of the tungsten is 1.8wt%~4.2wt%.
Preferably, the content of the titanium is 0.5wt%~0.7wt%.
Preferably, the content of the tantalum is 7.3wt%~7.7wt%.
Preferably, the content of the rhenium is 1.0wt%~3.0wt%.
Preferably, the content of the rhenium is 1.4wt%~1.6wt%.
Preferably, the content of the rhenium is 3.0wt%~6.0wt%.
Preferably, the content of the hafnium is 0.08wt%~0.12wt%.
Preferably, the content of the carbon is 0.0wt%~0.04wt%, the content of the boron be 0.0wt%~
0.004wt%.
Preferably, it is made of following element: the aluminium of 5.85wt%, the chromium of 6.1wt%, the cobalt of 6.4wt%, 2.8wt%'s
Molybdenum, the tungsten of 4.2wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%, the rhenium of 1.55wt%, the hafnium of 0.1wt% and the nickel of surplus.
Preferably, it is made of following element: the aluminium of 5.9wt%, the chromium of 6.1wt%, the cobalt of 6.5wt%, 4.0wt%'s
Molybdenum, the tungsten of 2.0wt%, the titanium of 0.55wt%, the tantalum of 7.6wt%, the rhenium of 1.57wt%, the hafnium of 0.1wt% and the nickel of surplus.
Preferably, it is made of following element: the aluminium of 5.9wt%, the chromium of 6.1wt%, the cobalt of 6.4wt%, 2.8wt%'s
Molybdenum, the tungsten of 2.8wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%, the rhenium of 3.0wt%, the hafnium of 0.1wt% and the nickel of surplus.
Preferably, it is made of following element: the aluminium of 5.8wt%, the chromium of 6.1wt%, the cobalt of 6.4wt%, 2.8wt%'s
Molybdenum, the tungsten of 0.8wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%, the rhenium of 5.0wt%, the hafnium of 0.1wt% and the nickel of surplus.
Present invention also provides the preparation methods of the nickel-base alloy, comprising the following steps:
A) Ni-based mother alloy ingot is prepared according to composition proportion；
B) by the Ni-based mother alloy ingot remelting, then nickel-base alloy casting is prepared；
C) the nickel-base alloy casting is heat-treated, obtains nickel-base alloy.
Preferably, the nickel-base alloy casting includes the equiax crystal casting prepared using investment casting, based on cloth Ritchie
The column crystal casting of graceful method directional solidification preparation or the single crystal casting prepared based on Bridgman method directional solidification.
Preferably, the heat treatment specifically includes at the solution treatment successively carried out, high-temperature aging processing and low temperature aging
Reason；
The solution treatment specifically: by the nickel-base alloy casting in 1260~1300 DEG C of 2~4h of heat preservation, then at 1280
~1320 DEG C of heat preservation 2h~4h, then in 1310~1350 DEG C of 6~12h of heat preservation, last air quenching；
The high-temperature aging processing specifically: the nickel-base alloy casting after solution treatment is kept the temperature 2 in 1060~1120 DEG C
~8h, then air quenching；
Low temperature aging processing specifically: keep the temperature high-temperature aging treated nickel-base alloy casting in 850~920 DEG C
10~30h, then air quenching.
It is Ni-based as described in above scheme present invention also provides a kind of manufacture article applied to gas-turbine unit
Alloy is prepared.
Preferably, the manufacture article is gas-turbine unit turbine blade.
This application provides a kind of nickel-base alloys, are made of following element: the aluminium of 5.45wt%~6.45wt%；
The chromium of 5.0wt%~7.0wt%；The cobalt of 5.5wt%~7.0wt%；The molybdenum of 2.0wt%~4.5wt%；0.5wt%~
The tungsten of 4.5wt%；The titanium of 0.2wt%~1.0wt%；The tantalum of 6.5wt%~8.5wt%；The rhenium of 1.0wt%~6.0wt%；
The hafnium of 0.0wt%~0.25wt%；The carbon of 0.0wt%~0.1wt%；The boron of 0.0wt%~0.01wt%；The nickel of surplus.This
Apply for the total content by adjusting refractory elements such as Mo, W, Ta and Re, especially has adjusted the content of Mo, thereby dramatically reduce conjunction
Gold segregation, and make the volume fraction of eutectic phase in Microstructures of As cast Alloys lower than 2.0%, so that alloy is easier to carry out solution treatment,
To ensure that the structure stability and mechanical property of alloy.
Detailed description of the invention
Fig. 1 is the preparation flow figure of nickel-base alloy provided by the invention；
Fig. 2 is cast sturcture's comparison diagram of the embodiment of the present invention with nickel-base alloy in the prior art；
Fig. 3 is that the embodiment of the present invention and the average electron vacancy number Nv of nickel-base alloy in the prior art compare column diagram；
Fig. 4 is that the embodiment of the present invention and the average d orbital energy level Md of nickel-base alloy in the prior art compare column diagram；
Fig. 5 is the embodiment of the present invention and the thermodynamic parameter of nickel-base alloy in the prior art and structural parameters comparison cylindricality
Figure.
Specific embodiment
For a further understanding of the present invention, the preferred embodiment of the invention is described below with reference to embodiment, still
It should be appreciated that these descriptions are only further explanation the features and advantages of the present invention, rather than to the claims in the present invention
Limitation.
Aiming at the problem that nickel-base alloy microsegregation in the prior art, the present invention provides a kind of nickel-base alloy, this kind of nickel
Based alloy has developed one kind with lower microsegregation degree and lower eutectic by balancing the content of refractory alloy element
The nickel-base alloy of phase fraction thereby ensures that the structure stability and mechanical property of the alloy.Specifically, herein described Ni-based
Alloy is made of following element:
The aluminium of 5.45wt%~6.45wt%；
The chromium of 5.0wt%~7.0wt%；
The cobalt of 5.5wt%~7.0wt%；
The molybdenum of 2.0wt%~4.5wt%；
The tungsten of 0.5wt%~4.5wt%；
The titanium of 0.2wt%~1.0wt%；
The tantalum of 6.5wt%~8.5wt%；
The rhenium of 1.0wt%~6.0wt%；
The hafnium of 0.0wt%~0.25wt%；
The carbon of 0.0wt%~0.1wt%；
The boron of 0.0wt%~0.01wt%；
The nickel of surplus.
In the nickel-base alloy of the application, aluminium (Al) is the essential element to form γ ' phase, is significantly precipitated for alloy strip
Strengthening effect.In addition, Al element is easy to generate fine and close Al in alloy surface at high temperature2O3Film hinders oxygen element to alloy
Internal diffusion, so as to improve the inoxidizability of alloy.Aluminium content described herein is 5.45wt%~6.45wt%, should
Aluminium in content range can promote the γ '-Ni that about 55~70% volume fractions are precipitated in alloy3Al precipitated phase, guarantees simultaneously
Alloy surface generates Al under high temperature2O3The continuity of film.In certain specific embodiments, the content of the aluminium be 5.6wt%~
6.2wt%；In certain specific embodiments, the content of the aluminium is 5.8wt%~6.1wt%.
Chromium (Cr) is mainly segregated in γ matrix phase, plays a small amount of solution strengthening effect；Cr antioxygen with higher itself
The property changed and hot corrosion resistance, existing also can promote Al under high temperature2O3The formation of film improves the inoxidizability of alloy；But it is excessively high
Cr content lead to the addition for being easy that TCP phase is precipitated, and limits strong solution strengthening element Re, W and Mo etc. in alloy, be unfavorable for
The elevated temperature strength of alloy.Adjusted, the content of herein described chromium is 5.0wt%~7.0wt%；In certain specific embodiments
In, the content of the chromium is 5.5wt%~6.8wt%；In certain specific embodiments, the content of the chromium be 5.8wt%~
6.2wt%.
Cobalt (Co) can form continuous substitution solid solution in nickel, reduce the stacking fault energy of γ matrix phase, and to a certain degree
The solution temperature of the upper solidus temperature for improving alloy and γ ' phase；But Co is less with respect to the resource of Ni, and price is higher, excessive
Co be also easy to cause the formation of TCP phase.Adjusted, the content of herein described cobalt is 5.5wt%~7.0wt%；Certain
In specific embodiment, content 6.0wt%~6.8wt% of the cobalt；In certain specific embodiments, the content of the cobalt is
6.2wt%~6.6wt%.
Molybdenum (Mo) is mainly segregated in γ matrix phase, is played significant solution strengthening effect, is improved the elevated temperature strength of alloy.This
Outside, Mo is lower with respect to the density of W, can be relieved refractory element addition to the adverse effect of alloy density.But Mo inoxidizability itself
The precipitation of TCP phase can be readily facilitated with the poor and excessively high Mo content of corrosion and heat resistant.The application thinks after study:
Low-alloyed degree of segregation can drop in being suitably added for Mo, and alloy is made to be easier to homogenize.Adjusted, herein described molybdenum contains
Amount is 2.0wt%~4.5wt%；In certain specific embodiments, the content of the molybdenum is 2.3wt%~4.3wt%；Certain
In specific embodiment, the content of the molybdenum is 2.6wt%~4.2wt%.
Tungsten (W) is mainly segregated in γ matrix phase, but W has lower diffusion rate with respect to Mo, can effectively reduce γ '
The roughening rate of phase increases creep life.Other than Re element, W is most important solution strengthening element, can partially substitute Re's
Invigoration effect, but excessively high W equally will cause alloy and be easy that TCP phase is precipitated.Adjusted, the content of herein described tungsten is
0.5wt%~4.5wt%；In certain specific embodiments, the content of the tungsten is 1.5wt%~4.3wt%；Certain specific
In embodiment, the content of the tungsten is 1.8wt%~4.2wt%.
Titanium (Ti) is mainly segregated in γ ' phase, and the position that can substitute Al forms more γ ' phases, plays precipitation strength work
With.Ti can more effectively improve the solid solubility temperature of γ ' phase and the lattice constant of γ ' phase with respect to Al, and by increasing γ '
The Apb Energies of phase and additional strengthening effect is provided.But excessive Ti is unfavorable to the casting character of alloy, and causes
Degree of segregation of the Cr and Mo in γ phase increases, to increase the risk that TCP phase is precipitated in alloy.It is adjusted, herein described titanium
Content be 0.2wt%~1.0wt%；In certain specific embodiments, the content of the titanium is 0.5wt%~0.7wt%.
Effect of the tantalum (Ta) in high temperature alloy is similar to Ti, is mainly segregated in γ ' phase, increases the volume point of γ ' phase
Number, but opposite Ti element has higher High-Temperature Strengthening effect, can significantly improve solid solubility temperature, the solidus of the γ ' phase of alloy
Temperature, tensile strength and improvement in creep resistance.However, relatively other alloying elements, Ta itself is a kind of somewhat expensive metal, and density
Higher, excessively high Ta causes being significantly increased for alloy density and cost.Adjusted, the content of herein described tantalum is 6.5wt%
~8.5wt%；In certain specific embodiments, the content of the tantalum is 7.0wt%~8.0wt%；In certain embodiments, institute
The content for stating tantalum is 7.3wt%~7.7wt%.
Rhenium (Re) is mainly to be segregated in γ matrix phase in high temperature alloy to the strongest element of elevated temperature strength hoisting power,
Movement of the dislocation in matrix phase is hindered significantly, while improving the solidus temperature of alloy.But Re element is a kind of extremely high
Expensive rare metal, the addition of every 1wt%Re element will lead to the about double growth of manufacturing cost of alloy.It is adjusted, the application
The rhenium content is 1.0wt%~6.0wt%；In a particular embodiment, the content of the rhenium be preferably 1.0wt%~
3.0wt%；Further, in certain specific embodiments, the content of the rhenium is preferably 1.4wt%~1.6wt%.Separately
Outside, in certain specific embodiments, the content of the rhenium is 3.0wt%~6.0wt%.
Hafnium (Hf) exists in the form of microelement in high temperature alloy.Micro Hf can be adsorbed effectively in alloy
Objectionable impurities elements S to increase the intensity and toughness of alloy, while can also increase the adhesiveness of coating, to improve conjunction
The environmental resistance of gold.But Hf can drop significantly low-alloyed fusing point, drop low-alloyed heat treatment window.It is adjusted, the application
The hafnium content is 0.0wt%~0.25wt%；In certain specific embodiments, the content of the hafnium be 0.05wt%~
0.20wt%；In certain specific embodiments, the content of the hafnium is 0.08wt%~0.12wt%.
Carbon (C), boron (B) element exist equally in the form of microelement in high temperature alloy.They tend to be segregated in
At the sub boundary of alloy, and carbide or boride are formed with alloying elements such as Ti, Ta, Mo, W, strengthens sub boundary, to reduce
The sub boundary tearing tendency of alloy；But C and B can significantly reduce the fusing point of alloy.Adjusted, the content of herein described carbon is
0.0wt%~0.1wt%；Boron content is 0.0wt%~0.01wt%.In certain specific embodiments, the content of the carbon is
0.0wt%~0.04wt%；The content of the boron is 0.0wt%~0.004wt%.
In certain specific embodiments, the nickel-base alloy is made of following element: the aluminium of 5.85wt%, 6.1wt%'s
Chromium, the cobalt of 6.4wt%, the molybdenum of 2.8wt%, the tungsten of 4.2wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%, the rhenium of 1.55wt%,
The hafnium of 0.1wt% and the nickel of surplus.
In certain specific embodiments, the nickel-base alloy is made of following element: the aluminium of 5.9wt%, 6.1wt%'s
Chromium, the cobalt of 6.5wt%, the molybdenum of 4.0wt%, the tungsten of 2.0wt%, the titanium of 0.55wt%, the tantalum of 7.6wt%, the rhenium of 1.57wt%,
The hafnium of 0.1wt% and the nickel of surplus.
In certain specific embodiments, the nickel-base alloy is made of following element: the aluminium of 5.8wt%, 6.1wt%'s
Chromium, the cobalt of 6.4wt%, the molybdenum of 2.8wt%, the tungsten of 0.8wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%, the rhenium of 5.0wt%,
The hafnium of 0.1wt% and the nickel of surplus.
In certain specific embodiments, the nickel-base alloy is made of following element: the aluminium of 5.9wt%, 6.1wt%'s
Chromium, the cobalt of 6.4wt%, the molybdenum of 2.8wt%, the tungsten of 2.8wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%, the rhenium of 3.0wt%,
The hafnium of 0.1wt% and the nickel of surplus.
Present invention also provides the preparation methods of nickel-base alloy, comprising the following steps:
A) Ni-based mother alloy ingot is prepared according to the composition proportion of above-mentioned nickel-base alloy；
B) by the Ni-based mother alloy ingot remelting, then nickel-base alloy casting is prepared；
C) the nickel-base alloy casting is heat-treated, obtains nickel-base alloy.
In the preparation method of above-mentioned nickel-base alloy, concrete composition in Ni-based mother alloy ingot is above-mentioned to be had been carried out specifically
It is bright, herein without repeating.
It is above-mentioned prepare nickel-base alloy during, the method for preparing Ni-based mother alloy ingot is according to art technology
Method known to personnel carries out, and exemplary, raw material is put into melting in vacuum melting furnace according to composition proportion by the application, to obtain
Ni-based mother alloy ingot.
According to the present invention, Ni-based mother alloy ingot is then subjected to remelting, the remelting is according to mode well known in the art
Progress, exemplary, the application carries out the remelting of Ni-based mother alloy ingot in vacuum equipment；Nickel-base alloy casting is prepared again
Part, the nickel-base alloy casting can be prepared into column crystal casting as desired by directional solidification method, can also pass through screw selecting crystalline substance
Method or seed-grain method are prepared into single crystal casting.
Nickel-base alloy casting is finally heat-treated by the application, it is described heat treatment according to mode known to nickel-base alloy into
Row；In this application, the step of heat treatment is handled according to solution treatment-high-temperature aging processing-low temperature aging is successively
It carries out, specifically, the solution treatment specifically: by the nickel-base alloy casting in 1260~1300 DEG C of 2~4h of heat preservation, then at
1280~1320 DEG C of heat preservation 2h~4h, then in 1310~1350 DEG C of 6~12h of heat preservation, last air quenching；The high-temperature aging processing
Specifically: by the nickel-base alloy casting and 1060~1120 DEG C of 2~8h of heat preservation after solution treatment, then air quenching；When the low temperature
Effect processing specifically: by high-temperature aging treated nickel-base alloy casting in 850~920 DEG C of 10~30h of heat preservation, then air quenching.
In a particular embodiment, the nickel-base alloy prepares molding, institute by vacuum induction melting+directional solidification processes
Method preparation flow figure is stated as shown in Figure 1, being specially the alloy material that (1) prepares mentioned component by vacuum induction melting, is obtained
The mother alloy ingot accurately controlled to ingredient；(2) by ingot material remelting, by directional solidification processes be prepared into single crystal casting or
Orient casting；(3) the suitable casting of size is obtained by machining；(4) as-cast structure in alloy is eliminated by heat treatment, obtained
Obtain optimal microstructure.
According to an embodiment of the invention, the generation type of herein described nickel-base alloy is manufacture article, the article
It can be applied to gas-turbine unit, more specifically, can be applied to gas-turbine unit turbine blade, by including following member
The alloy of element is prepared: the aluminium of 5.45wt%~6.45wt%；The chromium of 5.0wt%~7.0wt%；5.5wt%~7.0wt%
Cobalt；The molybdenum of 2.0wt%~4.5wt%；The tungsten of 0.5wt%~4.5wt%；The titanium of 0.2wt%~1.0wt%；6.5wt%~
The tantalum of 8.5wt%；The rhenium of 1.0wt%~6.0wt%；The hafnium of 0.0wt%~0.25wt%；The carbon of 0.0wt%~0.1wt%；
The boron of 0.0wt%~0.01wt%；The nickel of surplus.
In certain specific embodiments, the manufacture article is prepared by the alloy comprising following element: 5.85wt%
Aluminium, the chromium of 6.1wt%, the cobalt of 6.4wt%, the molybdenum of 2.8wt%, the tungsten of 4.2wt%, the titanium of 0.55wt%, 7.5wt%'s
Tantalum, the rhenium of 1.55wt%, the hafnium of 0.1wt% and the nickel of surplus.
In certain specific embodiments, the manufacture article is prepared by the alloy comprising following element: 5.9wt%'s
Aluminium, the chromium of 6.1wt%, the cobalt of 6.5wt%, the molybdenum of 4.0wt%, the tungsten of 2.0wt%, the titanium of 0.55wt%, the tantalum of 7.6wt%,
The rhenium of 1.57wt%, the hafnium of 0.1wt% and the nickel of surplus.
In certain specific embodiments, the manufacture article is prepared by the alloy comprising following element: 5.9wt%'s
Aluminium, the chromium of 6.1wt%, the cobalt of 6.4wt%, the molybdenum of 2.8wt%, the tungsten of 2.8wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%,
The rhenium of 3.0wt%, the hafnium of 0.1wt% and the nickel of surplus.
In certain specific embodiments, the manufacture article is prepared by the alloy comprising following element: 5.8wt%'s
Aluminium, the chromium of 6.1wt%, the cobalt of 6.4wt%, the molybdenum of 2.8wt%, the tungsten of 0.8wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%,
The rhenium of 5.0wt%, the hafnium of 0.1wt% and the nickel of surplus.
For a further understanding of the present invention, nickel-base alloy provided by the invention is carried out specifically below with reference to embodiment
Bright, protection scope of the present invention is not limited by the following examples.
Embodiment
The application nickel-base alloy significantly reduces segregation, and is lower than the volume fraction of eutectic phase in as-cast structure
2.0%, meanwhile, nickel-base alloy structure stability, in terms of realize good balance, have excellent synthesis
Performance.In order to further illustrate the effect of the application, the application lists 6 specific embodiments, and carries out with 5 kinds of existing alloys
Comparison.6 embodiment alloying components and 5 kinds of existing alloying components are as shown in table 1；In embodiment, the nickel-base high-temperature closes
The preparation method of gold specifically:
1) it will be put into vacuum induction melting furnace molten alloy according to the raw material of composition proportion shown in table 1, is prepared into master alloy
Ingot casting；
2) solidifying by orienting then in the formwork that refractory material is formed by mother alloy ingot remelting in vacuum equipment
Gu method is prepared into column crystal casting or is prepared into single crystal casting by spiral crystal separation method or seed-grain method；
3) casting is heat-treated, heat treatment specifically includes: (1) solution treatment: is protected in 1260 DEG C~1300 DEG C
Temperature 2~4h, then 1280 DEG C~1320 DEG C heat preservation 2~4h, then 1310 DEG C~1350 DEG C 6~12h of heat preservation, last air quenching；(2)
High-temperature aging processing: in 1060 DEG C~1120 DEG C 2~8h of heat preservation, then air quenching；(3) low temperature aging is handled: in 850 DEG C~920
DEG C 10~30h of heat preservation, then air quenching；Finally obtain the nickel base superalloy of even tissue.
The nickel base high temperature alloy composition tables of data (wt%) that 1 embodiment of table and the prior art provide
| Alloy | Al | Cr | Co | Mo | W | Ti | Ta | Nb | Re | Hf | Ni |
| Embodiment 1 | 5.85 | 6.1 | 6.4 | 2.8 | 4.2 | 0.55 | 7.5 | 0 | 1.55 | 0.1 | It is remaining |
| Embodiment 2 | 5.9 | 6.1 | 6.5 | 4.0 | 2.0 | 0.55 | 7.6 | 0 | 1.57 | 0.1 | It is remaining |
| Embodiment 3 | 5.95 | 6.05 | 6.4 | 4.0 | 2.0 | 0.6 | 7.5 | 0 | 1.45 | 0.1 | It is remaining |
| Embodiment 4 | 6.05 | 5.85 | 6.55 | 2.78 | 4.15 | 0.55 | 7.35 | 0 | 1.55 | 0.1 | It is remaining |
| Embodiment 5 | 5.9 | 6.1 | 6.4 | 2.8 | 2.8 | 0.55 | 7.5 | 0 | 3.0 | 0.1 | It is remaining |
| Embodiment 6 | 5.8 | 6.1 | 6.4 | 2.8 | 0.8 | 0.55 | 7.5 | 0 | 5.0 | 0.1 | It is remaining |
| CMSX-2 | 5.6 | 8 | 4.6 | 0.6 | 8 | 1 | 6 | 0 | 0 | - | It is remaining |
| René N4 | 4.2 | 9.8 | 7.5 | 1.5 | 6 | 3.5 | 4.8 | 0.5 | 0 | 0.1 | It is remaining |
| AM3 | 5.95 | 8 | 5.5 | 2.25 | 5 | 2 | 3.5 | 0 | 0 | - | It is remaining |
| René N5 | 6.2 | 7 | 7.5 | 1.5 | 5 | 0 | 6.5 | 0 | 3 | 0.15 | It is remaining |
| CMSX-4 | 5.6 | 6.5 | 9 | 0.6 | 6 | 1 | 6.5 | 0 | 2.9 | 0.1 | It is remaining |
1) segregation
Fig. 2 is cast sturcture's comparison diagram of nickel-base alloy prepared by embodiment 1 and CMSX-10 alloy and CMSX-4 alloy,
Scheme cast sturcture's comparison diagram that (a) is CMSX-10 alloy, figure (b) is cast sturcture's comparison diagram of CMSX-4 alloy, and figure (c) is
Cast sturcture's figure of alloy prepared by embodiment 1, as seen from the figure, eutectic phase in the nickel-base alloy that the embodiment of the present application 1 provides
Volume fraction is lower than 2.0%.
2) there is good structure stability
The application alloy has good structure stability under long term high temperature timeliness, it is not easy to harmful TCP phase be precipitated.
Fig. 3 is the cylindricality of 6 embodiments and 5 kinds of existing alloy average electron vacancy number Nv according to PHACOMP method the application alloy
Comparison diagram；Fig. 4 is the d track energy that is averaged according to 6 embodiments and 5 kinds of existing alloys of New PHACOMP method the application alloy
The cylindricality comparison diagram of grade Md；As seen from Figure 3, the Nv value of the application alloy is significantly lower than existing alloy CMSX-2, AM3, Ren
The calculated value of é N4, CMSX-4 and Ren é N5；As seen from Figure 4, the Md value of the application alloy is suitable with alloy CMSX-4,
Significantly lower than alloy Ren é N4 and AM3, the slightly above calculated value of alloy Ren é N5.This synthesis illustrates that the alloy of the application has
Good structure stability.
3) there is excellent Properties of High Temperature Creep
The application considers the high-temperature creep resistance of alloy in terms of 4: (1) phase transition temperature of alloy；(2) alloy
Solution strengthening degree；(3) the precipitation strength phase amount of alloy；(4) lattice equations of alloy；
3 important phase transition temperatures of nickel base superalloy are as follows: 1. γ ' phase solid solubility temperature is increased with temperature, γ ' is mutually complete
Fully dissolved is to the critical-temperature in γ phase；2. solidus temperature is increased with temperature, alloy starts the critical-temperature of fusing；③
Liquidus temperature is increased with temperature, the critical-temperature that alloy is completely melt, γ ' phase solid solubility temperature is higher, then not molten under high temperature
The γ ' of solution is mutually more, and the high temperature precipitations strengthening effect of alloy is higher；Solidus, liquidus temperature are higher, show alloy itself
Temperature resistant capability is higher.Fig. 5 (a) show 6 embodiments of the application alloy and the γ ' phase solid solubility temperature of 5 kinds of existing alloys, consolidates
The comparison column diagram of liquidus temperature and liquidus temperature calculated value；As can be seen that γ ' the phase of 6 embodiments of the application alloy
Solid solubility temperature is not less than 5 existing alloys；Solidus, liquidus temperature temperature and alloy CMSX-2, CMSX-4 and Ren é N5
Quite, slightly above alloy AM3 and Ren é N4.
The solution strengthening degree of alloy mainly investigates the effect of solution strengthening element Re, W and Mo 3 strong.The application uses
One solution strengthening factor ISSSTo evaluate the solution strengthening degree of alloy.ISSSIt is higher, show that the solution strengthening degree of alloy is got over
It is high.Fig. 5 (b) show 6 embodiments and 5 kinds of existing alloy I of the application alloySSSThe comparison column diagram of calculated value；It can see
Out, due to the addition of a large amount of W, Mo and Re, the I of 6 embodimentsSSSIt is apparently higher than the calculating of alloy CMSX-2, Ren é N4 and AM3
Value, the I of embodiment 5 and 6SSSThe even higher than calculated value of alloy CMSX-4, Ren é N5.
The precipitation strength degree of alloy mainly investigates the score of γ ' phase in alloy under service temperature, and value is higher, illustrates to close
The potentiality of golden precipitation strength are bigger.Fig. 5 (c) is shown by calculating, 6 embodiments and 5 kinds of existing alloys of the application alloy
γ ' the phase mole fraction at 850 DEG C, 900 DEG C, 1050 DEG C and 1100 DEG C compares column diagram respectively；As can be seen that in Xiang Tongwen
Under degree, the γ ' phase mole fraction of 6 embodiments is suitable with alloy CMSX-2, AM3, Ren é N4, CMSX-4 and Ren é N5.
Another key parameter relevant to alloy creep intensity is γ/γ ' phase lattice equations；Studies have shown that brilliant
Lattice mismatch is negative, and when absolute value is higher, is conducive to the increase of creep strength, but excessively high mismatch will lead to γ/γ '
Two-phase coherent structural unstability loses coherence strengthening effect instead.Fig. 5 (d) show 6 embodiments of the application alloy and 5 kinds
The comparison column diagram of existing alloy lattice mismatch calculated value；As can be seen that the lattice equations of the application alloy are negative, absolutely
It is suitable with alloy AM3, Ren é N5 to being worth, it is higher than alloy Ren é N4, CMSX-4 and CMSX-2.From the point of view of above 4 points, this Shen
Please alloy have excellent Properties of High Temperature Creep.
The manufacture article that the nickel-base alloy that above-described embodiment is prepared is formed, is applied particularly to gas-turbine unit whirlpool
Impeller blade, it may have the same performance of above-mentioned nickel-base alloy.
The above description of the embodiment is only used to help understand the method for the present invention and its core ideas.It should be pointed out that pair
For those skilled in the art, without departing from the principle of the present invention, the present invention can also be carried out
Some improvements and modifications, these improvements and modifications also fall within the scope of protection of the claims of the present invention.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (22)
1. a kind of nickel-base alloy is made of following element:
The aluminium of 5.45wt%~6.45wt%；
The chromium of 5.0wt%~7.0wt%；
The cobalt of 5.5wt%~7.0wt%；
The molybdenum of 2.0wt%~4.5wt%；
The tungsten of 0.5wt%~4.5wt%；
The titanium of 0.2wt%~1.0wt%；
The tantalum of 6.5wt%~8.5wt%；
The rhenium of 1.0wt%~6.0wt%；
The hafnium of 0.0wt%~0.25wt%；
The carbon of 0.0wt%~0.1wt%；
The boron of 0.0wt%~0.01wt%；
The nickel of surplus.
2. nickel-base alloy according to claim 1, which is characterized in that the content of the aluminium is 5.8wt%~6.1wt%.
3. nickel-base alloy according to claim 1, which is characterized in that the content of the chromium is 5.8wt%~6.2wt%.
4. nickel-base alloy according to claim 1, which is characterized in that the content of the cobalt is 6.2wt%~6.6wt%.
5. nickel-base alloy according to claim 1, which is characterized in that the content of the molybdenum is 2.6wt%~4.2wt%.
6. nickel-base alloy according to claim 1, which is characterized in that the content of the tungsten is 1.8wt%~4.2wt%.
7. nickel-base alloy according to claim 1, which is characterized in that the content of the titanium is 0.5wt%~0.7wt%.
8. nickel-base alloy according to claim 1, which is characterized in that the content of the tantalum is 7.3wt%~7.7wt%.
9. nickel-base alloy according to claim 1, which is characterized in that the content of the rhenium is 1.0wt%~3.0wt%.
10. nickel-base alloy according to claim 9, which is characterized in that the content of the rhenium is 1.4wt%~1.6wt%.
11. nickel-base alloy according to claim 1, which is characterized in that the content of the rhenium is 3.0wt%~6.0wt%.
12. nickel-base alloy according to claim 1, which is characterized in that the content of the hafnium be 0.08wt%~
0.12wt%.
13. nickel-base alloy according to claim 1, which is characterized in that the content of the carbon be 0.0wt%~
0.04wt%, the content of the boron are 0.0wt%~0.004wt%.
14. nickel-base alloy according to claim 1, which is characterized in that be made of following element: the aluminium of 5.85wt%,
The chromium of 6.1wt%, the cobalt of 6.4wt%, the molybdenum of 2.8wt%, the tungsten of 4.2wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%,
The rhenium of 1.55wt%, the hafnium of 0.1wt% and the nickel of surplus.
15. nickel-base alloy according to claim 1, which is characterized in that be made of following element: the aluminium of 5.9wt%,
The chromium of 6.1wt%, the cobalt of 6.5wt%, the molybdenum of 4.0wt%, the tungsten of 2.0wt%, the titanium of 0.55wt%, the tantalum of 7.6wt%,
The rhenium of 1.57wt%, the hafnium of 0.1wt% and the nickel of surplus.
16. nickel-base alloy according to claim 1, which is characterized in that be made of following element: the aluminium of 5.9wt%,
The chromium of 6.1wt%, the cobalt of 6.4wt%, the molybdenum of 2.8wt%, the tungsten of 2.8wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%,
The rhenium of 3.0wt%, the hafnium of 0.1wt% and the nickel of surplus.
17. nickel-base alloy according to claim 1, which is characterized in that be made of following element: the aluminium of 5.8wt%,
The chromium of 6.1wt%, the cobalt of 6.4wt%, the molybdenum of 2.8wt%, the tungsten of 0.8wt%, the titanium of 0.55wt%, the tantalum of 7.5wt%,
The rhenium of 5.0wt%, the hafnium of 0.1wt% and the nickel of surplus.
18. the preparation method of the described in any item nickel-base alloys of claim 1~17, comprising the following steps:
A) Ni-based mother alloy ingot is prepared according to composition proportion；
B) by the Ni-based mother alloy ingot remelting, then nickel-base alloy casting is prepared；
C) the nickel-base alloy casting is heat-treated, obtains nickel-base alloy.
19. preparation method according to claim 18, which is characterized in that the nickel-base alloy casting includes being cast using fusible pattern
Make equiax crystal casting, the column crystal casting based on the preparation of Bridgman method directional solidification or legal based on Bridgman of method preparation
To the single crystal casting of solidification preparation.
20. preparation method according to claim 18, which is characterized in that the heat treatment specifically includes consolidating of successively carrying out
Molten processing, high-temperature aging processing and low temperature aging processing；
The solution treatment specifically: by the nickel-base alloy casting in 1260~1300 DEG C of 2~4h of heat preservation, then at 1280~
1320 DEG C of heat preservation 2h~4h, then in 1310~1350 DEG C of 6~12h of heat preservation, last air quenching；
High-temperature aging processing specifically: by the nickel-base alloy casting after solution treatment in 1060~1120 DEG C of 2~8h of heat preservation,
Then air quenching；
Low temperature aging processing specifically: high-temperature aging treated nickel-base alloy casting keeps the temperature in 850~920 DEG C to 10~
30h, then air quenching.
21. a kind of manufacture article applied to gas-turbine unit, by the described in any item nickel-base alloys of claim 1~17
It is prepared.
22. manufacture article according to claim 21, which is characterized in that the manufacture article is gas-turbine unit whirlpool
Impeller blade.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114585769A (en) * | 2019-10-08 | 2022-06-03 | 赛峰集团 | Aircraft component made of a superalloy containing rhenium and/or ruthenium and method for the production thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1123874A (en) * | 1993-08-06 | 1996-06-05 | 株式会社日立制作所 | Blade for gas turbine, manufacturing method of the same, and gas turbine including the blade |
| CN104736731A (en) * | 2012-10-31 | 2015-06-24 | 通用电气公司 | Nickel-based superalloy and articles |
-
2018
- 2018-08-28 CN CN201810985895.7A patent/CN109554582A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1123874A (en) * | 1993-08-06 | 1996-06-05 | 株式会社日立制作所 | Blade for gas turbine, manufacturing method of the same, and gas turbine including the blade |
| CN104736731A (en) * | 2012-10-31 | 2015-06-24 | 通用电气公司 | Nickel-based superalloy and articles |
Non-Patent Citations (3)
| Title |
|---|
| 刘正东: "《电站耐热材料的选择性强化设计与实践》", 31 January 2017 * |
| 王周让: "《航空工程材料》", 28 February 2010 * |
| 胡德昌等: "《新型材料特性及其应用》", 30 September 1996 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114585769A (en) * | 2019-10-08 | 2022-06-03 | 赛峰集团 | Aircraft component made of a superalloy containing rhenium and/or ruthenium and method for the production thereof |
| CN114585769B (en) * | 2019-10-08 | 2024-04-26 | 赛峰集团 | Aircraft component made of a superalloy containing rhenium and/or ruthenium and method for producing the same |
| US12110581B2 (en) | 2019-10-08 | 2024-10-08 | Safran | Aircraft part made of superalloy comprising rhenium and/or ruthenium and associated manufacturing method |
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Application publication date: 20190402 |