CN107794411A - The high temperature alloy ball strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface - Google Patents
The high temperature alloy ball strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface Download PDFInfo
- Publication number
- CN107794411A CN107794411A CN201711111827.XA CN201711111827A CN107794411A CN 107794411 A CN107794411 A CN 107794411A CN 201711111827 A CN201711111827 A CN 201711111827A CN 107794411 A CN107794411 A CN 107794411A
- Authority
- CN
- China
- Prior art keywords
- high temperature
- pressure turbine
- axial end
- turbine disk
- end tooth
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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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
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D7/00—Modifying the physical properties of iron or steel by deformation
- C21D7/02—Modifying the physical properties of iron or steel by deformation by cold working
- C21D7/04—Modifying the physical properties of iron or steel by deformation by cold working of the surface
- C21D7/06—Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like
-
- 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
Abstract
The invention discloses a kind of high temperature alloy ball strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface, its mass percent is chromium 15.00~17.00%, cobalt 12.00~14.00%, tungsten 3.80~4.20%, molybdenum 3.80~4.20%, niobium 0.50~1.00%, aluminium 2.00~2.40%, titanium 3.50~3.90%, carbon 0.02~0.05%, zirconium 0.025~0.07%, boron 0.006~0.017, surplus are nickel and inevitable impurity element.The high temperature alloy ball strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface prepared by the present invention is not in hollow and face crack phenomenon, it has density, element ratio uniformity high, hardness deviation is small, many advantages, such as good endurance, it is particularly suitable for aircraft high-pressure turbine disk, the surface Hardening Treatment of aircraft drum barrel axial end tooth, the fatigue strength of part can be effectively lifted, lifts the life-span of part.
Description
Technical field
The present invention relates to a kind of metal product, and in particular to is used for aircraft high-pressure turbine disk and drum barrel axial end tooth to one kind
The high temperature alloy ball of surface peening.
Background technology
At present, intensive treatment is typically carried out to aircraft high-pressure turbine disk and drum barrel axial end tooth surface using cast steel ball.Casting
Shot is to aircraft high-pressure turbine disk and the reinforcing DeGrain of drum barrel axial end tooth surface, in addition, cast steel ball can be brought seriously
Irony pollution.
The content of the invention
In order to solve the above-mentioned technical problem, one aspect of the present invention offer one kind is used for aircraft high-pressure turbine disk and drum barrel shaft end
The high temperature alloy ball that face tooth surface is strengthened, its concrete technical scheme are as follows：
A kind of high temperature alloy ball strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface, its mass percent
For chromium 15.00~17.00%, cobalt 12.00~14.00%, tungsten 3.80~4.20%, molybdenum 3.80~4.20%, niobium 0.50~
1.00%, aluminium 2.00~2.40%, titanium 3.50~3.90%, carbon 0.02~0.05%, zirconium 0.025~0.07%, boron 0.006~
0.017, surplus is nickel and inevitable impurity element.
In a specific embodiment, the impurity element includes iron, copper and nonmetalloid, by mass percentage, institute
State impurity element satisfaction：Iron≤0.05%, copper≤0.05%, nonmetalloid≤0.1%.
In a specific embodiment, the high temperature strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface
The average hardness determined under alloy pellets load is HV350, described strong for aircraft high-pressure turbine disk and drum barrel axial end tooth surface
The hardness deviation scope of the alloy pellets of change is ± 80HV.
In a specific embodiment, the high temperature strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface
The size distribution of alloy pellets meets：The quantity of alloy pellets of the granularity less than 125 μm is no more than 5%, and granularity is more than 200 μm of alloy
The quantity of ball is no more than 0.05%, and the quantity of alloy pellets of the granularity between 180~300 μm is not less than 70%.
Another aspect of the present invention provides a kind of height strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface
The preparation method of temperature alloy ball, it in turn includes the following steps：Sorting → Mechanical Crushing → pure melting → vacuum aerosolization →
Solidification → screening → passivation grinding → fine screen point → detection → storage, or：Sorting → Mechanical Crushing → pure melting → plasma
Rotating electrode atomized → solidification → screening → passivation grinding → fine screen point → detection → storage.
In a specific embodiment, the dispensing refers to the raw material from various elements by component ratio and finished product one
Cause is fed intake, and the Mechanical Crushing refers to that raw material are put into disintegrating machine is crushed, and the pure melting refers to will be broken
Raw material afterwards are inserted in heating furnace to produce the aluminium alloy of melting, the vacuum aerosolization and the plasma rotating electrode mist
Change refers to nebulize aluminium alloy impact to prepare high temperature alloy ball, and the screening and the fine screen point refer to from high temperature alloy ball
In filter out the particle size range of requirement, the detection refers to hardness and durability detection.
Prepared by the present invention is used for the high temperature alloy ball that aircraft high-pressure turbine disk and drum barrel axial end tooth surface are strengthened, and it is not
Hollow and face crack phenomenon occurs, it has density, element ratio uniformity high, and hardness deviation is small, and good endurance etc. is all
More advantages, it is particularly suitable for aircraft high-pressure turbine disk, the surface Hardening Treatment of aircraft drum barrel axial end tooth, can effectively lifts zero
The fatigue strength of part, lift the life-span of part.
Embodiment
To make the above objects, features and advantages of the present invention, can be more obvious understandable, below to the present invention preferable reality
Apply example to be described in detail, apparent clearly defined so as to be made to protection scope of the present invention.
Many details are elaborated in the following description to facilitate a thorough understanding of the present invention, still the present invention can be with
It is different from other manner described here using other to implement, those skilled in the art can be without prejudice to intension of the present invention
In the case of do similar popularization, therefore the present invention is not limited by following public specific embodiment.
In one has been embodied, provided by the present invention for the high temperature alloy of aircraft high-pressure turbine dish cart surface strengthening
Ball, its mass percent are chromium 15.00~17.00%, cobalt 12.00~14.00%, tungsten 3.80~4.20%, molybdenum 3.80~
4.20%, niobium 0.50~1.00%, aluminium 2.00~2.40%, titanium 3.50~3.90%, carbon 0.02~0.05%, zirconium 0.025~
0.07%, boron 0.006~0.017, surplus is nickel and inevitable impurity element
In one has been embodied, the impurity element includes iron, copper and nonmetalloid, by mass percentage, on
Stating each impurity element and accounting for the mass percents of alloy pellets needs to meet：Iron≤0.05%, copper≤0.05%, nonmetalloid≤
0.1%.
In a specific embodiment, it is of the invention to be used for aircraft high-pressure turbine disk and drum barrel axial end tooth surface strengthens
The specific production technology of alloy pellets is：Sorting → Mechanical Crushing → pure melting → vacuum aerosolization → solidification → screening → passivation
Grinding → fine screen point → detection → storage.In some other embodiment, of the invention is used for aircraft high-pressure turbine disk and drum barrel
The specific production technology of alloy pellets that axial end tooth surface is strengthened is：Sorting → Mechanical Crushing → pure melting → plasma rotation
Electrode atomized → solidification → screening → passivation grinding → fine screen point → detection → storage.Wherein：
Sorting refers to that the metal precentagewise content from various elements is consistent with finished product and fed intake, specially：Chromium
15.00~17.00%, cobalt 12.00~14.00%, tungsten 3.80~4.20%, molybdenum 3.80~4.20%, niobium 0.50~1.00%,
Aluminium 2.00~2.40%, titanium 3.50~3.90%, carbon 0.02~0.05%, zirconium 0.025~0.07%, boron 0.006~0.017,
Surplus is nickel and inevitable impurity element.
Mechanical Crushing refers to that raw material are put into disintegrating machine is cut, crushes.
Pure melting refers to that the raw material after crushing are inserted in heating furnace to produce the aluminium alloy of melting.
Vacuum aerosolization or PREP refer to be solidified after aluminium alloy impact is nebulized to prepare
High temperature alloy ball.The general principle of atomization is：The aluminium alloy of melting is led through jet nozzle flow guide pipe outflow and edge under gravity
Flow tube mouth is extending transversely into liquid film, and liquid film into fine drop, is formed high by supersonic airstream impact grinding after droplet solidification
Temperature alloy ball.
Screening and fine screen point refer to the particle size range that requirement is filtered out from high temperature alloy ball.In a specific embodiment
In, the screening includes primary dcreening operation and fine screen.It is specific as follows：The larger sifter device of mesh is used to carry out primary dcreening operation to filter out the μ of particle diameter 125
The high temperature alloy ball of m~350 μm, then high temperature alloy ball is ground using milling tool, it is finally less using mesh
Sifter device carries out washed ore to filter out the high temperature alloy ball of 125 μm~300 μm of particle diameter.
In a specific embodiment, it is used for aircraft high-pressure turbine disk and drum barrel axial end tooth surface prepared by the present invention
The high temperature alloy ball of reinforcing, its size distribution need to meet：The quantity of high temperature alloy ball of the granularity less than 125 μm is no more than 5%, grain
The quantity of high temperature alloy ball of the degree more than 300 μm is no more than 0.05%, high temperature alloy ball of the granularity between 180~300 μm
Quantity is not less than 70%.
Detection refers to hardness and durability detection, wherein：
The specific method of hardness determination is：100 high temperature alloy balls are collected at random, is inlayed, is inlayed temperature and be no more than
120 degrees Celsius, grinder buffing is used after the completion of inlaying, makes high temperature alloy ball exposure close to high temperature alloy ball nominal diametrical dimension
1/3rd, then high temperature alloy ball face is polished with red sand paper, wet-milling is used in sand paper bruting process, prevents high temperature alloy ball
Hot-spot, then to 20 of the center on this flour milling by its Vickers hardness of GB/14340 standard testings, 20 high temperature alloys
The hardness number of ball takes arithmetic mean of instantaneous value after being added.The average hardness that high temperature prepared by the present invention closes ball is HV350, and deviation range is
±80HV。
Durability detection specific method be：500 grams of high temperature alloy balls of random sampling and standby from tested high temperature alloy ball
With 100 grams of high temperature alloy balls, 100 grams of high temperature alloy balls are all put into Ervin testing machines and tested, Ervin testing machines set 500
Switch to a circulation, if taking primary alloy ball and dust with 0.15 millimeter of standard separating sieve sieve of nominal diameter after a cyclic test,
With standby high temperature alloy ball supplement its loss high temperature alloy ball weight, the like cyclic test until loss high temperature close
The weight of golden ball reaches 100 grams, thus calculates that the revolution of weightless 100 grams of high temperature alloy balls is set to durability.
Prepared by the present invention is used for the high temperature alloy ball load that aircraft high-pressure turbine disk and drum barrel axial end tooth surface are strengthened
The average hardness of lower measure is HV 350, the alloy pellets strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface
Hardness deviation scope be ± 80HV.It has density, element ratio uniformity high, and hardness deviation is small, and good endurance etc. is many
Advantage, it is particularly suitable for aircraft high-pressure turbine disk, the surface Hardening Treatment of aircraft drum barrel axial end tooth, can effectively lifts part
Fatigue strength, lift life-span of part.
The description with certain particularity detailed enough has been carried out to the present invention above.Ordinary skill in art
Personnel are it should be understood that what the description in embodiment was merely exemplary, before without departing from true spirit and scope of the present invention
Put make it is all change should all belong to protection scope of the present invention.Scope of the present invention is by described power
What sharp claim was defined, rather than limited by foregoing description in embodiment.
Claims (6)
1. the high temperature alloy ball strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface, it is characterised in that：Its quality
Percentage is chromium 15.00~17.00%, cobalt 12.00~14.00%, tungsten 3.80~4.20%, molybdenum 3.80~4.20%, niobium
0.50~1.00%, aluminium 2.00~2.40%, titanium 3.50~3.90%, carbon 0.02~0.05%, zirconium 0.025~0.07%, boron
0.006~0.017, surplus is nickel and inevitable impurity element.
2. alloy pellets as claimed in claim 1, it is characterised in that the impurity element includes iron, copper and nonmetalloid, presses
Mass percent, the impurity element meet：Iron≤0.05%, copper≤0.05%, nonmetalloid≤0.1%.
3. the high temperature alloy ball strengthened as claimed in claim 1 for aircraft high-pressure turbine disk and drum barrel axial end tooth surface,
It is characterized in that：Determined under the alloy pellets load strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface flat
Equal hardness is HV350, the hardness deviation of the alloy pellets strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface
Scope is ± 80HV.
4. the high temperature alloy ball strengthened as claimed in claim 1 for aircraft high-pressure turbine disk and drum barrel axial end tooth surface,
It is characterized in that：Its size distribution meets：The quantity of alloy pellets of the granularity less than 125 μm is no more than 5%, and granularity is more than 300 μm
The quantity of alloy pellets be no more than 0.05%, the quantity of alloy pellets of the granularity between 180~300 μm is not less than 70%.
5. a kind of prepare the high temperature as claimed in claim 1 strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface
The method of alloy pellets, it is characterised in that it in turn includes the following steps：
Sorting → Mechanical Crushing → pure melting → vacuum aerosolization → solidification → screening → passivation grinding → fine screen point → detection
→ storage,
Or：Sorting → Mechanical Crushing → pure melting → PREP → solidification → screening → passivation grinding → essence
Screening → detection → storage.
6. method as claimed in claim 5, it is characterised in that：The dispensing refers to the raw material from various elements by composition
Ratio is consistent with finished product to be fed intake, and the Mechanical Crushing refers to that raw material are put into disintegrating machine is crushed, described pure molten
Refining refer to will it is broken after raw material insert in heating furnace with produce the aluminium alloy of melting, the vacuum aerosolization and the grade from
Son is rotating electrode atomized to be referred to nebulize aluminium alloy impact to prepare high temperature alloy ball, and the screening and the fine screen point refer to
The particle size range of requirement is filtered out from high temperature alloy ball, the detection refers to hardness and durability detection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711111827.XA CN107794411A (en) | 2017-11-13 | 2017-11-13 | The high temperature alloy ball strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711111827.XA CN107794411A (en) | 2017-11-13 | 2017-11-13 | The high temperature alloy ball strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107794411A true CN107794411A (en) | 2018-03-13 |
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ID=61534923
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711111827.XA Pending CN107794411A (en) | 2017-11-13 | 2017-11-13 | The high temperature alloy ball strengthened for aircraft high-pressure turbine disk and drum barrel axial end tooth surface |
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| CN105689730A (en) * | 2016-02-24 | 2016-06-22 | 西安欧中材料科技有限公司 | Method for preparing Inconel 625 alloy spherical powder |
| CN106623958A (en) * | 2016-12-19 | 2017-05-10 | 西安欧中材料科技有限公司 | Method for preparing GH5605 alloy spherical powder through plasma rotating electrode method |
| CN106623959A (en) * | 2016-12-19 | 2017-05-10 | 西安欧中材料科技有限公司 | Preparation method of Waspalloy spherical powder for additive manufacturing |
| CN106862447A (en) * | 2017-03-07 | 2017-06-20 | 钢铁研究总院 | A kind of multiway forging method of high-alloying high temperature alloy bar stock/biscuit |
| CN107262730A (en) * | 2017-08-01 | 2017-10-20 | 北京有色金属研究总院 | The gas atomization preparation method and its equipment of a kind of superfine spherical metal powder |
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Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102079070A (en) * | 2009-11-26 | 2011-06-01 | 大丰市大奇金属磨料有限公司 | Stainless steel pill |
| CN102139473A (en) * | 2010-01-28 | 2011-08-03 | 天津市新潮铸钢磨料厂 | Process for clearing metal grinding materials for derusting by using special steel wires for steel wire rope |
| CN103978131A (en) * | 2014-05-05 | 2014-08-13 | 凌源市龙源资源回收利用有限公司 | Preparation method for high-performance steel shots |
| CN105385961A (en) * | 2015-12-16 | 2016-03-09 | 淄博鲁宝金属制品有限公司 | Wear-resisting low-carbon steel shot, preparation method thereof and centrifugal atomizing device |
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| CN106623959A (en) * | 2016-12-19 | 2017-05-10 | 西安欧中材料科技有限公司 | Preparation method of Waspalloy spherical powder for additive manufacturing |
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Application publication date: 20180313 |
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