CN104372205A - CoCrW-base high-temperature alloy powder for engine turbine shroud ring wear-resistant coatings and preparation method thereof - Google Patents
CoCrW-base high-temperature alloy powder for engine turbine shroud ring wear-resistant coatings and preparation method thereof Download PDFInfo
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Abstract
The invention belongs to the field of manufacturing of aircraft engines, and particularly relates to a CoCrW-base high-temperature alloy powder for engine turbine shroud ring wear-resistant coatings and a preparation method thereof. The CoCrW-base high-temperature alloy powder for engine turbine shroud ring wear-resistant coatings is composed of the following chemical components in percentage by mass: 25.5-26% of Cr, 10-11.5% of Ni, 7-8% of W, 0.45-0.55% of C, less than 400ppm of O and the balance of Co. The particle size of the powder is less than or equal to 325 meshes, the flowability is 22-24 s/50g, and the apparent density is 4.3-4.8 g/cm<3>. The preparation method comprises the following steps: carrying out vacuum smelting on the chemical components to obtain an alloy solution, and sending the alloy solution into an atomization tank through a tundish and a guide pipe to perform atomization under the pressure of 0.6-3 MPa, thereby obtaining the CoCrW-base high-temperature alloy powder. The proportioning and charging sequence, alloy solution temperature and atomization injection conditions are controlled to obtain the spherical CoCrW-base high-temperature alloy powder which has the advantages of complete morphology, uniform particle size, favorable flowability and reasonable apparent density.
Description
Technical field
The invention belongs to aircraft engine and manufacture field, be specifically related to a kind of CoCrW based high-temperature alloy powder and preparation method of engine turbine outer shroud wear-resistant coating.
Background technology
The turbine outer ring coated material of engine particularly aircraft engine requires to have advanced high temperature resistance, anti-oxidant, heat resistanceheat resistant erosion and has good seal performance.CoCrW alloy powder is a kind of coated material that can be used as bottom, it can have good viscosity and bonding strength with superalloys such as titanium alloys, coating structure is evenly distributed, and does not have crackle, layering and coating and basal body interface separation phenomenon, is a kind of excellent spraying primer.
But CoCrW alloy melting point is high, viscosity is large, oxidizable, atomization process difficulty, gained powdered alloy sphericity is poor, mobility and pine lower, the requirement of high quality spraying coating material can not be met.In addition, the oxidizable control of element of CoCrW powdered alloy is unstable, and oxygen level is higher, the properties of alloy coat can be affected, in coating, oxide inclusion increases, and porosity becomes large, and the bonding strength of coating and matrix also may reduce due to the existence that bonding interface is mingled with.Therefore, in order to obtain the CoCrW alloy coat of excellent combination property, prepare the trend that low oxygen content powdered alloy has become inevitable.
Summary of the invention
For prior art Problems existing, the invention provides a kind of CoCrW based high-temperature alloy powder and preparation method of engine turbine outer shroud wear-resistant coating, object is by controlling rational atomization process parameter, prepares the CoCrW based high-temperature alloy powder meeting coating service requirements.
The CoCrW based high-temperature alloy powder of engine turbine outer shroud wear-resistant coating of the present invention, its chemical composition according to mass percent is: Cr25.5 ~ 26%, Ni10 ~ 11.5%, W7 ~ 8%, C0.45 ~ 0.55%, O < 400ppm, and surplus is Co; Granularity≤325 order of powder, mobility is 22 ~ 24s/50g, and pine is than 4.3 ~ 4.8g/cm
3.
The preparation method of the CoCrW based high-temperature alloy powder of engine turbine outer shroud wear-resistant coating of the present invention, carries out according to following steps:
(1) according to chemical composition mass percent Cr25.5 ~ 26%, Ni10 ~ 11.5%, W7 ~ 8%, C0.5 ~ 0.55%, surplus is Co batching, adopts medium-frequency induction furnace to carry out vacuum melting, vacuum tightness < 10Pa in stove, when feeding intake, nickel plate and part cobalt are placed on furnace bottom, and tungsten rod and chromium metal are put in the middle part of stove, more remaining cobalt plate is put into top, under protection of inert gas, melting obtains aluminium alloy;
(2) aluminium alloy enters in atomization tank through tundish and thrust-augmenting nozzle and is atomized, draft-tube diameter is 8mm, vacuum tightness≤2Pa in atomization tank, atomization temperature is 1500 ~ 1700 DEG C, atomizing nozzle selects folding and unfolding type circumferential weld nozzle, arranging jet apex angle is 30 ° ~ 60 °, injection rare gas element or nitrogen alloy liquid are atomized, atomizing pressure is 0.6 ~ 3MPa, in the collector of the powder that atomization obtains below atomization tank, after cyclonic separation, enter cyclone enrichment, obtain CoCrW based high-temperature alloy powder.
The inner nozzle seam of described folding and unfolding type circumferential weld nozzle is 1.5mm along stitching along the distance on aluminium alloy flow direction with outer nozzle.
Compared with prior art, feature of the present invention and beneficial effect are:
Technical scheme of the present invention is by control batching and order of addition(of ingredients), aluminium alloy temperature and atomised jet condition acquisition pattern is complete, the rational spherical CoCrW based high-temperature alloy powder of epigranular, good fluidity and Song Bi, specifically:
The metallic element fusing point difference designed in the present invention is larger, they are difficult to be fused into homogeneous aluminium alloy in stove, easy generation component segregation, in induction furnace also there is difference in different zones temperature, so when carrying out feeding intake in stove, needs strictly to consider feeding sequence, in the present invention when feeding intake, nickel plate and part cobalt are placed on furnace bottom, and tungsten rod and chromium metal are put in the middle part of stove, more remaining cobalt plate is put into top;
The higher metal of vapour pressure when melting, the easy volatilization loss of alloying element, therefore melting needs to carry out under protection of inert gas, to avoid the metal bath surface boiling when melting, causes splash;
The atomization process of aluminium alloy controls gas to the mechanism of metal liquid stream, the kinetic energy of air-flow is made to be converted into newborn powder surface energy to greatest extent, wherein jet apex angle is 30 ° and 60 ° is blocking and nonclogging two criticalitys, when being greater than 60 °, atomization stops, and when being less than 30 °, is easy to jet occurs, powder is comparatively thick, is not even atomized;
The inner nozzle seam of circumferential weld nozzle is called outstanding position P along stitching with outer nozzle along the upper distance on aluminium alloy flow direction, as P < 0, in atomization process, some flies upward spraying contrary direction to atomizing medium the aluminium alloy flow down through tundish, and be condensed on bottom pour ladle mouth, result in blockage, atomization process is interrupted, affect production efficiency, during P > 0, along with the increase of P, atomised jet drift angle reduces, obtained powder is thicker, air-flow utilization ratio is lower, easily cause jet simultaneously, have a strong impact on atomizing effect, so the height at outstanding position is set to 1.5mm in the present invention,
In powder by atomization process, different size, the metallic particles of different states is subject to the effect of air-flow and gravity in flight course, travelling speed is also not all right same, they mutually may collide or collide with atomization tank inwall and deform, thus the spherical powder particle of various expense may be formed, but when superheating temperature improves, due to capillary effect, there is the trend that next year makes spheroid in decline process, thus obtain the powder of better sphericity, the mobility of powdered alloy will inevitably be made like this to improve, and then improve the Song Zhuan density of powder, this is the raising due to temperature, the viscosity of metal melt and surface tension reduce, simultaneously because the Drop Condensation process that temperature is high is long, the time on surface tension retracting drop surface is long, therefore easily obtain spherical powder, therefore the atomization temperature in the present invention is set as 1500 ~ 1700 DEG C,
Gaseous tension ensures that atomizing medium has the prerequisite of certain kinetic energy, along with the raising of gaseous tension, in powder, the ratio of fine powder increases, but it is also worthless that unlimited raising pressure reduces powder grain, therefore in the present invention, atomizing pressure is set as 0.6 ~ 3MPa;
Vacuum tightness in smelting furnace is relevant with the oxygen level of CoCrW based high-temperature alloy, only has when low vacuum in stove is in 10Pa, could by the Control for Oxygen Content in alloy in lower scope.
The CoCrW based high-temperature alloy powder that prepared by the inventive method obtain has smooth spherical microscopic appearance, and mobility is 22 ~ 24s/50g, and pine is than 4.3 ~ 4.8g/cm
3, oxygen level, lower than 400ppm, when being adopted supersonic spray coating technique to make coating, meets the service requirements of engine turbine outer shroud wear-resistant coating completely.
Accompanying drawing explanation
Fig. 1 is the SEM figure of the CoCrW based high-temperature alloy powder prepared in the embodiment of the present invention 1;
Fig. 2 is the SEM figure of the CoCrW based high-temperature alloy powder prepared in the embodiment of the present invention 2;
Fig. 3 is the metallographic structure figure be combined with matrix after the CoCrW based high-temperature alloy powder prepared in the embodiment of the present invention 2 makes coating;
Fig. 4 is the SEM figure of the CoCrW based high-temperature alloy powder prepared in the embodiment of the present invention 3;
Fig. 5 is the X-ray diffraction curve of the CoCrW based high-temperature alloy powder prepared in the embodiment of the present invention 3;
Fig. 6 is the metallographic structure figure be combined with matrix after the CoCrW based high-temperature alloy powder prepared in the embodiment of the present invention 3 makes coating.
Embodiment
In the raw material adopted in the embodiment of the present invention, the specification trade mark of Ni is Ni9996, purchased from Beijing Jin Dou goods and materials agency; The specification of Cr is 99A, purchased from Jinzhou Metal Material Inst.; The specification of Co is 99, purchased from Jinchuan Non-ferrous Metals Company; The specification of W is 99A, purchased from Zhuzhou mechanically resistant material factory.
The medium-frequency induction furnace power adopted in the embodiment of the present invention is 100kW, and IF-FRE is 2500Hz, and specified charge amount is 50kg, by IGBTFA power control pod with middle frequency power supply control.
Embodiment 1
The CoCrW based high-temperature alloy powder of engine turbine outer shroud wear-resistant coating of the present invention, its chemical composition according to mass percent is: Cr 25.5%, Ni 10%, W 8%, C 0.50%, O < 400ppm, and surplus is Co; Granularity≤325 order of powder, mobility is 22s/50g, and pine compares 4.8g/cm
3.
The preparation method of the CoCrW based high-temperature alloy powder of engine turbine outer shroud wear-resistant coating of the present invention, carries out according to following steps:
(1) according to chemical composition mass percent Cr 25.5%, Ni 10%, W 8%, C 0.50%, surplus is Co batching, adopts medium-frequency induction furnace to carry out vacuum melting, vacuum tightness < 10Pa in stove, when feeding intake, nickel plate and part cobalt are placed on furnace bottom, and tungsten rod and chromium metal are put in the middle part of stove, more remaining cobalt plate is put into top, under protection of inert gas, melting obtains aluminium alloy;
(2) aluminium alloy enters in atomization tank through tundish and thrust-augmenting nozzle and is atomized, draft-tube diameter is 8mm, vacuum tightness≤2Pa in atomization tank, atomization temperature is 1500 DEG C, atomizing nozzle selects folding and unfolding type circumferential weld nozzle, its inner nozzle seam is 1.5mm along stitching along the distance on aluminium alloy flow direction with outer nozzle, arranging jet apex angle is 60 °, injection rare gas element or nitrogen alloy liquid are atomized, atomizing pressure is 3MPa, in the collector of the powder that atomization obtains below atomization tank, cyclone enrichment is entered after cyclonic separation, obtain CoCrW based high-temperature alloy powder, after testing, granularity≤325 order of powder, mobility is 22s/50g, pine compares 4.8g/cm
3, its SEM schemes as shown in Figure 1, and the powdered alloy that as can be seen from Figure 1 vacuum atomizing obtains is spherical, significantly improves mobility and the loose density of powdered alloy.
Supersonic spray coating technique is adopted to be prepared into coating in the CoCrW based high-temperature alloy powder obtained, coating hardness mean value is 85 after testing, be 69MPa with the bonding strength of metallic matrix, 20 thermal shock tests are carried out in 700 DEG C, shake rear surface state is intact, coating is unchanged, and coating is combined well with matrix surface.
Embodiment 2
The CoCrW based high-temperature alloy powder of engine turbine outer shroud wear-resistant coating of the present invention, its chemical composition according to mass percent is: Cr 26%, Ni 10.5%, W 7.5%, C 0.45%, O < 400ppm, and surplus is Co; Granularity≤325 order of powder, mobility is 23s/50g, and pine compares 4.5g/cm
3.
The preparation method of the CoCrW based high-temperature alloy powder of engine turbine outer shroud wear-resistant coating of the present invention, carries out according to following steps:
(1) according to chemical composition mass percent Cr 26%, Ni 10.5%, W 7.5%, C 0.45%, surplus is Co batching, adopts medium-frequency induction furnace to carry out vacuum melting, vacuum tightness < 10Pa in stove, when feeding intake, nickel plate and part cobalt are placed on furnace bottom, and tungsten rod and chromium metal are put in the middle part of stove, more remaining cobalt plate is put into top, under protection of inert gas, melting obtains aluminium alloy;
(2) aluminium alloy enters in atomization tank through tundish and thrust-augmenting nozzle and is atomized, draft-tube diameter is 8mm, vacuum tightness≤2Pa in atomization tank, atomization temperature is 1600 DEG C, atomizing nozzle selects folding and unfolding type circumferential weld nozzle, its inner nozzle seam is 1.5mm along stitching along the distance on aluminium alloy flow direction with outer nozzle, arranging jet apex angle is 45 °, injection rare gas element or nitrogen alloy liquid are atomized, atomizing pressure is 1.5MPa, in the collector of the powder that atomization obtains below atomization tank, cyclone enrichment is entered after cyclonic separation, obtain CoCrW based high-temperature alloy powder, after testing, powder size≤325 order, mobility is 23s/50g, pine compares 4.5g/cm
3, its SEM schemes as shown in Figure 2, and the powdered alloy that as can be seen from Figure 2 vacuum atomizing obtains is spherical, significantly improves mobility and the loose density of powdered alloy.
Supersonic spray coating technique is adopted to be prepared into coating in the CoCrW based high-temperature alloy powder obtained, coating hardness mean value is 87 after testing, be 72MPa with the bonding strength of metallic matrix, 20 thermal shock tests are carried out in 700 DEG C, shake rear surface state is intact, coating is unchanged, and coating is combined with matrix surface well, as shown in Figure 3.
Embodiment 3
The CoCrW based high-temperature alloy powder of engine turbine outer shroud wear-resistant coating of the present invention, its chemical composition according to mass percent is: Cr 25.8%, Ni 11.5%, W 7%, C 0.55%, O < 400ppm, and surplus is Co; Granularity≤325 order of powder, mobility is 24s/50g, and pine compares 4.3g/cm
3.
The preparation method of the CoCrW based high-temperature alloy powder of engine turbine outer shroud wear-resistant coating of the present invention, carries out according to following steps:
(1) according to chemical composition mass percent Cr 25.8%, Ni 11.5%, W 7%, C 0.55%, surplus is Co batching, adopts medium-frequency induction furnace to carry out vacuum melting, vacuum tightness < 10Pa in stove, when feeding intake, nickel plate and part cobalt are placed on furnace bottom, and tungsten rod and chromium metal are put in the middle part of stove, more remaining cobalt plate is put into top, under protection of inert gas, melting obtains aluminium alloy;
(2) aluminium alloy enters in atomization tank through tundish and thrust-augmenting nozzle and is atomized, draft-tube diameter is 8mm, vacuum tightness≤2Pa in atomization tank, atomization temperature is 1700 DEG C, atomizing nozzle selects folding and unfolding type circumferential weld nozzle, its inner nozzle seam is 1.5mm along stitching along the distance on aluminium alloy flow direction with outer nozzle, arranging jet apex angle is 30 °, injection rare gas element or nitrogen alloy liquid are atomized, atomizing pressure is 0.6MPa, in the collector of the powder that atomization obtains below atomization tank, cyclone enrichment is entered after cyclonic separation, obtain CoCrW based high-temperature alloy powder, after testing, powder size≤325 order, mobility is 24s/50g, pine compares 4.3g/cm
3its SEM schemes as shown in Figure 4, and the powdered alloy that as can be seen from Figure 4 vacuum atomizing obtains is spherical, significantly improves mobility and the loose density of powdered alloy, as shown in Figure 5, as can be seen from Figure 5 alloy constituent element Cr and Ni is mainly with Cr for its X-ray diffraction curve
3ni
2form exists.
Supersonic spray coating technique is adopted to be prepared into coating in the CoCrW based high-temperature alloy powder obtained, coating hardness mean value is 84 after testing, be 55MPa with the bonding strength of metallic matrix, 20 thermal shock tests are carried out in 700 DEG C, shake rear surface state is intact, and coating is unchanged, and its metallographic structure figure as shown in Figure 6, as can be seen from Figure 6, coating is combined well with matrix.
Claims (3)
1. a CoCrW based high-temperature alloy powder for engine turbine outer shroud wear-resistant coating, is characterized in that chemical composition according to mass percent is: Cr25.5 ~ 26%, Ni10 ~ 11.5%, W7 ~ 8%, C0.45 ~ 0.55%, O < 400ppm, surplus is Co; Granularity≤325 order of powder, mobility is 22 ~ 24s/50g, and pine is than 4.3 ~ 4.8g/cm
3.
2. the preparation method of the CoCrW based high-temperature alloy powder of engine turbine outer shroud wear-resistant coating as claimed in claim 1, is characterized in that carrying out according to following steps:
(1) according to chemical composition mass percent Cr25.5 ~ 26%, Ni10 ~ 11.5%, W7 ~ 8%, C0.5 ~ 0.55%, surplus is Co batching, adopts medium-frequency induction furnace to carry out vacuum melting, vacuum tightness < 10Pa in stove, when feeding intake, nickel plate and part cobalt are placed on furnace bottom, and tungsten rod and chromium metal are put in the middle part of stove, more remaining cobalt plate is put into top, under protection of inert gas, melting obtains aluminium alloy;
(2) aluminium alloy enters in atomization tank through tundish and thrust-augmenting nozzle and is atomized, draft-tube diameter is 8mm, vacuum tightness≤2Pa in atomization tank, atomization temperature is 1500 ~ 1700 DEG C, atomizing nozzle selects folding and unfolding type circumferential weld nozzle, arranging jet apex angle is 30 ° ~ 60 °, injection rare gas element or nitrogen alloy liquid are atomized, atomizing pressure is 0.6 ~ 3MPa, in the collector of the powder that atomization obtains below atomization tank, after cyclonic separation, enter cyclone enrichment, obtain CoCrW based high-temperature alloy powder.
3. the preparation method of the CoCrW based high-temperature alloy powder of a kind of engine turbine outer shroud wear-resistant coating according to claim 2, is characterized in that the inner nozzle seam of described folding and unfolding type circumferential weld nozzle is 1.5mm along stitching along the distance on aluminium alloy flow direction with outer nozzle.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106493502A (en) * | 2016-11-16 | 2017-03-15 | 中国人民解放军第五七九工厂 | A kind of restorative procedure of aero-engine bridle end wear |
| CN106975742A (en) * | 2017-04-27 | 2017-07-25 | 天津成立航空技术有限公司 | A kind of aero-engine wear part cobalt-based dusty spray and preparation method thereof |
| CN112853157A (en) * | 2020-12-31 | 2021-05-28 | 广州湘龙高新材料科技股份有限公司 | Cobalt-chromium-molybdenum-tungsten-silicon alloy bar |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102021559A (en) * | 2009-09-09 | 2011-04-20 | 沈阳大陆激光技术有限公司 | Cobalt-based alloy powder for laser cladding of steam turbine last-stage blade |
| CN102423806A (en) * | 2011-12-15 | 2012-04-25 | 北京矿冶研究总院 | Preparation method of fine-particle-size cobalt-based alloy powder |
| JP2013060633A (en) * | 2011-09-14 | 2013-04-04 | Fukuda Metal Foil & Powder Co Ltd | Co-BASED ALLOY FOR SURFACE HARDENING |
-
2014
- 2014-10-29 CN CN201410590154.0A patent/CN104372205B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102021559A (en) * | 2009-09-09 | 2011-04-20 | 沈阳大陆激光技术有限公司 | Cobalt-based alloy powder for laser cladding of steam turbine last-stage blade |
| JP2013060633A (en) * | 2011-09-14 | 2013-04-04 | Fukuda Metal Foil & Powder Co Ltd | Co-BASED ALLOY FOR SURFACE HARDENING |
| CN102423806A (en) * | 2011-12-15 | 2012-04-25 | 北京矿冶研究总院 | Preparation method of fine-particle-size cobalt-based alloy powder |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106493502A (en) * | 2016-11-16 | 2017-03-15 | 中国人民解放军第五七九工厂 | A kind of restorative procedure of aero-engine bridle end wear |
| CN106975742A (en) * | 2017-04-27 | 2017-07-25 | 天津成立航空技术有限公司 | A kind of aero-engine wear part cobalt-based dusty spray and preparation method thereof |
| CN112853157A (en) * | 2020-12-31 | 2021-05-28 | 广州湘龙高新材料科技股份有限公司 | Cobalt-chromium-molybdenum-tungsten-silicon alloy bar |
| CN112853157B (en) * | 2020-12-31 | 2021-11-30 | 广州湘龙高新材料科技股份有限公司 | Cobalt-chromium-molybdenum-tungsten-silicon alloy bar and preparation method thereof |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Patentee before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |