CN106756739B - Nickel base superalloy CoCrAlYTaSi coating - Google Patents
Nickel base superalloy CoCrAlYTaSi coating Download PDFInfo
- Publication number
- CN106756739B CN106756739B CN201611060743.3A CN201611060743A CN106756739B CN 106756739 B CN106756739 B CN 106756739B CN 201611060743 A CN201611060743 A CN 201611060743A CN 106756739 B CN106756739 B CN 106756739B
- Authority
- CN
- China
- Prior art keywords
- coating
- cocralytasi
- nickel base
- base superalloy
- spray
- 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.)
- Active
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C30/00—Alloys containing less than 50% by weight of each constituent
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The invention discloses a kind of nickel base superalloy CoCrAlYTaSi coating, which uses is made using plasma spraying, the ingredient of the dusty spray of plasma spraying are as follows: Co37wt.%, Cr24wt.%, Al19wt.%, Y2wt.%, Ta15wt.%, Si3wt.%.Coating consistency of the invention reaches 98%, and binding force reaches 70Mpa, has good high temperature oxidation resistance, and thermal shock performance is more than 300 times at 1100 DEG C, and have the function of preferable self-healing and.
Description
Technical field
The present invention relates to technical field of surface coating, and in particular to a kind of nickel base superalloy CoCrAlYTaSi coating
Preparation method.
Background technique
For GH202 mainly for the manufacture of aeroengine rotor blade, normal use temperature is 850 DEG C, is more than this temperature,
The high temperature oxidation resistance of alloy will sharply decline.However due to its special Service Environment, actually using temperature may reach
To 1100 DEG C or more.The thrust ratio of alternate-engine is up to 12-15, and inlet temperature also can be higher, this has speeded up alloy
Oxidation corrosion, alloy surface prepare one layer of high temperature oxidation corrosion resistance coating be the effective means for solving the problems, such as this.Mesh
Preceding many coating materials its effect in 1100 DEG C or more military services is not satisfactory, and mainly coating and matrix thermal expansion coefficient be not
Match, can generate peeling under the conditions of heat fatigue, thus new coating material exploitation and preparation process become particularly important.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of nickel base superalloy CoCrAlYTaSi coatings, improve anti-height
Warm oxidation susceptibility and thermal shock performance.
In order to solve the above technical problems, the present invention adopts the following technical scheme that: nickel base superalloy CoCrAlYTaSi is applied
Layer, the coating are made using plasma spraying, the ingredient of the dusty spray of plasma spraying are as follows: Co37wt.%, Cr24wt.%,
Al19wt.%、Y2wt.%、Ta15wt.%、Si3wt.%。
Ta element can increase the hardness of coating in coating of the invention, reduce crack sensitivity, while also having to inhale and support
Effect inhibits the oxidation of other elements in coating.
The preparation method of nickel base superalloy CoCrAlYTaSi coating of the invention, includes the following steps:
(1) nickel base superalloy sample linear cutter is milled on SiC sand paper at 40mm × 40mm × 5mm
180 molybdenums impregnate 10h in acetone, and are cleaned with supersonic wave cleaning machine, drying；
(2) by specimen holder on fixture, with 16# corundum, sandblasting roughening treatment is carried out under 4 atmospheric compressed air；
(3) sample is preheated to 400 DEG C, is sprayed using high energy plasma；
(4) spray-on coating is with a thickness of 148-152um.
Further, the main gas of high energy plasma spraying is N2, auxiliary gas and carrier gas are Ar2；Spray power is 30Kw, distance
For 100mm, primary air amount is 60L/min, and auxiliary throughput is 25L/min, carrier gas flux 2r/min.
Further, spray-on coating is with a thickness of 150um.
The present invention first carries out blasting treatment before plasma spraying, and blasting treatment is mainly the oxidation film for removing matrix surface
And surface roughness is made to increase to increase the binding force of matrix and coating.
Beneficial effects of the present invention: coating consistency of the invention reaches 98%, and binding force reaches 70Mpa, painting of the invention
Thermal shock resistance is more than 300 times at 1100 DEG C of layer, and coating of the invention, the silicon melted at high operating temperatures flow to cracks for crackle
Again fill up so that coating have the function of at high temperature self-healing and.
Detailed description of the invention
Fig. 1 is CoCrAlYTaSi coating cross sections micro-structure diagram.
Fig. 2 is the distribution diagram of element that CoCrAlYTaSi coating is EPMA analysis.
Fig. 3 is coating surface appearance figure after thermal shock experiment.
Specific embodiment
Embodiment 1
Nickel base superalloy CoCrAlYTaSi coating, the coating are made using plasma spraying, the spraying of plasma spraying
The ingredient of powder are as follows: Co37wt.%, Cr24wt.%, Al19wt.%, Y2wt.%, Ta15wt.%, Si3wt.%.Coating layer thickness is
150um。
Preparation method includes the following steps:
(1) nickel base superalloy sample linear cutter is milled on SiC sand paper at 10mm × 10mm × 5mm
180 molybdenums impregnate 10h in acetone, and are cleaned with supersonic wave cleaning machine, drying；
(2) by specimen holder on fixture, with 16# corundum, sandblasting roughening treatment is carried out under 4 atmospheric compressed air；
(3) sample is preheated to 400 DEG C, is sprayed using high energy plasma；The main gas of high energy plasma spraying is N2, auxiliary gas
It is Ar with carrier gas2；Spray power is 30Kw, and distance is 100mm, and primary air amount is 60L/min, and auxiliary throughput is 25L/min, is carried
Throughput is 2r/min；
(4) spray-on coating is with a thickness of 148-152um.
Coating consistency of the invention reaches 98% or more, and binding force reaches 70MPa.
(a) and (b) is CoCrAlYTaSi coating cross sections microstructure in Fig. 1, and 7 be coating and matrix from Fig. 1 (b)
Line of demarcation, the combination between coating and matrix is closely as can be seen from the figure.There is a large amount of in coating after spraying
Strip aluminium oxide (as shown in (a) 1), there are also a large amount of sphere (as shown in (a) 2), there are many these spheres
It is wrapped in by the aluminium oxide of outer layer.Sphere (as shown in (a) 3) according to the white in energy spectrum analysis sphere is rich Y
Oxide and the irregular pure Ta(of shapes and sizes are as shown in (b) 5).The intermediate white ball for having stain is also found simultaneously
Body is the compound (as shown in (b) 6) of rich Si and Ti according to analysis, and centre is aluminium oxide.In addition there is also have in figure layer
A small amount of stomata (as shown in (a) 4).
Fig. 2 is the distribution diagram of element that CoCrAlYTaSi coating is EPMA analysis, the as can be seen from the figure distribution of Co and Cr
It is very intensive, but in the Al that strip is also distributed among them2O3, wherein most all with interface balance, Ta Elemental redistribution
Comparatively uniformly, there is moiety aggregation in the position on surface and faying face, Y element is only distributed in the position at coating and interface, Si
Constituent content is seldom, and the regularity of distribution is unobvious.
Thermal shock experiment (being kept for 10 minutes at 1100 DEG C, taking-up is placed in water) is done at 1100 DEG C, recycles 300 secondary coatings
It does not peel off.
Coating surface appearance after Fig. 3 tests for thermal shock: (a) thermal shock 20 times, (b) thermal shock 100 times, (c) thermal shock 200 times,
(d) thermal shock 300 times.There is one very long continuous crackle in 20 rear surfaces of thermal shock, and crackle still has but do not connect after 100 times
It is continuous, several very short crackles are only seen after 200 times, coating surface is after 300 times almost without crackle.It should according to analysis
Coating have the function of at high temperature self-healing and, the silicon of melting flow to cracks and fills up crackle again.
Embodiment described above is only that the preferred embodiment of the present invention is described, not to design of the invention
It is defined with range, without departing from the design concept of the invention, ordinary engineering and technical personnel is to this hair in this field
The all variations and modifications that bright technical solution is made should all fall into protection scope of the present invention, claimed skill of the invention
Art content is all documented in technical requirements book.
Claims (3)
1. nickel base superalloy CoCrAlYTaSi coating, it is characterised in that: the coating is made using plasma spraying, plasma
The ingredient of the dusty spray of spraying are as follows: Co37wt.%, Cr24wt.%, Al19wt.%, Y2wt.%, Ta15wt.%, Si3wt.%；Its
In, specific step is as follows for plasma spraying:
(1) nickel base superalloy sample linear cutter is milled to 180 mesh at 40mm × 40mm × 5mm on SiC sand paper
, 10h is impregnated in acetone, and cleaned with supersonic wave cleaning machine, dry up；
(2) by specimen holder on fixture, with 16# corundum, sandblasting roughening treatment is carried out under 4 atmospheric compressed air；
(3) sample is preheated to 400 DEG C, is sprayed using high energy plasma；
(4) spray-on coating is with a thickness of 148-152um.
2. the preparation method of nickel base superalloy CoCrAlYTaSi coating according to claim 1, it is characterised in that: high
The main gas of energy plasma spraying is N2, auxiliary gas and carrier gas are Ar2；Spray power is 30Kw, and distance is 100mm, and primary air amount is
60L/min, auxiliary throughput are 25L/min, carrier gas flux 2r/min.
3. the preparation method of nickel base superalloy CoCrAlYTaSi coating according to claim 1, it is characterised in that: spray
Coating layer is with a thickness of 150um.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611060743.3A CN106756739B (en) | 2016-11-28 | 2016-11-28 | Nickel base superalloy CoCrAlYTaSi coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611060743.3A CN106756739B (en) | 2016-11-28 | 2016-11-28 | Nickel base superalloy CoCrAlYTaSi coating |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106756739A CN106756739A (en) | 2017-05-31 |
| CN106756739B true CN106756739B (en) | 2019-03-26 |
Family
ID=58913176
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611060743.3A Active CN106756739B (en) | 2016-11-28 | 2016-11-28 | Nickel base superalloy CoCrAlYTaSi coating |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106756739B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107653432A (en) * | 2017-09-28 | 2018-02-02 | 中国航发动力股份有限公司 | A kind of high energy plasma spraying prepares the process of thermal barrier coating |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4339509A (en) * | 1979-05-29 | 1982-07-13 | Howmet Turbine Components Corporation | Superalloy coating composition with oxidation and/or sulfidation resistance |
| US4447503A (en) * | 1980-05-01 | 1984-05-08 | Howmet Turbine Components Corporation | Superalloy coating composition with high temperature oxidation resistance |
| US6346134B1 (en) * | 2000-03-27 | 2002-02-12 | Sulzer Metco (Us) Inc. | Superalloy HVOF powders with improved high temperature oxidation, corrosion and creep resistance |
| CN102828137B (en) * | 2012-08-31 | 2014-06-11 | 华南理工大学 | High-temperature alloy surface nanometer composite coating and preparation method thereof |
| CN104213067A (en) * | 2014-09-25 | 2014-12-17 | 上海交通大学 | Method for coating high-temperature corrosion and wear resistant coating layer on surface of steel material |
| CN104357782A (en) * | 2014-11-14 | 2015-02-18 | 北京矿冶研究总院 | Method for reducing interdiffusion of interface elements of high-temperature alloy and protective coating |
| CN105483597B (en) * | 2016-02-16 | 2017-09-29 | 哈尔滨工程大学 | A kind of preparation method of the thermal barrier coating of zirconic acid lanthanum fiber doping zirconic acid lanthanum |
-
2016
- 2016-11-28 CN CN201611060743.3A patent/CN106756739B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106756739A (en) | 2017-05-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20100266409A1 (en) | Method for Coating a Blade and Blade of a Gas Turbine | |
| CN105132908A (en) | Gas turbine blade thermal barrier coating bonding layer and preparation method thereof | |
| EP2371986B1 (en) | Metallic coating for non-line of sight areas | |
| CN103993913B (en) | There is turbine components and its manufacture method of anti-erosion and corrosion resistant coating system | |
| CN102115836A (en) | High-temperature protective coating of MCrAlY alloy system and preparation method | |
| CN108118190B (en) | A kind of environment resistant deposit corrosion thermal barrier coating and preparation method thereof | |
| CN106119760B (en) | A kind of thermal barrier coating and preparation method thereof with the double-deck adhesive layer | |
| TW200700567A (en) | Method of preparing metal matrix composite and coating layer and bulk prepared by using the same | |
| CN105648296B (en) | A kind of high temperature resistance tungsten carbide-base metal-ceramic composite powder end, coating and its preparation process containing Re | |
| US9845526B2 (en) | Slip and process for producing an aluminum diffusion layer | |
| CN102312188A (en) | Method for preparing SiAl coating by sintering slurry | |
| CN107805775A (en) | A kind of high-temperature abradable seal coating and preparation method thereof | |
| CN108118278A (en) | One kind is used for the low guide vane method for preparing heat barrier coating of IC10 alloys | |
| CN105386041B (en) | A kind of method that laser melting coating prepares modified compound Hf Ta metal coatings | |
| CN106947934A (en) | A method for preparing α-Al2O3 coatings by plasma spraying | |
| CN107716933B (en) | A kind of interface purification method of the wear-resisting antioxidant coating of single crystal super alloy | |
| CN106756739B (en) | Nickel base superalloy CoCrAlYTaSi coating | |
| US9896585B2 (en) | Coating, coating system, and coating method | |
| CN108660412B (en) | Modified β-NiAl coating of a kind of active element and preparation method thereof and workpiece | |
| CN205329146U (en) | Novel siC whisker reinforcing gas turbine blade composite biocoating | |
| CN108728786A (en) | A method of preparing silumin coating | |
| CN105463382B (en) | A kind of coating and preparation method thereof improving TiAl alloy oxidation drag | |
| CN107904547A (en) | A kind of preparation method of titanium alloy Wear-resistant, high-temperature resistant coating | |
| CN105132853A (en) | Hard high-damping coating preparation process used for surface of high-temperature damping part | |
| WO2015121008A1 (en) | Component with an abradable coating and a method for coating the abradable coating |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB03 | Change of inventor or designer information |
Inventor after: Cao Jiangdong Inventor after: Lu Lixin Inventor after: Gao Keke Inventor after: Chen Yan Inventor after: Cao Xueyu Inventor after: Xu Dan Inventor after: Hang Xiaohu Inventor after: Ding Jianbo Inventor after: Yan Shuai Inventor after: Lu Huabin Inventor before: Cao Jiangdong Inventor before: Chen Yan Inventor before: Cao Xueyu Inventor before: Xu Dan Inventor before: Hang Xiaohu Inventor before: Ding Jianbo Inventor before: Yan Shuai Inventor before: Lu Huabin Inventor before: Lu Lixin |
|
| CB03 | Change of inventor or designer information | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 226000 No.185 Tongsheng Avenue, Nantong Economic and Technological Development Zone, Jiangsu Province Patentee after: JIANGSU VOCATIONAL & TECHNICAL SHIPPING College Address before: 226000 No.185 Tongsheng Avenue, Nantong Economic and Technological Development Zone, Jiangsu Province Patentee before: NANTONG SHIPPING College |
|
| CP01 | Change in the name or title of a patent holder |