CN103722803A - Strong-strength radiation coating for aircraft engine - Google Patents
Strong-strength radiation coating for aircraft engine Download PDFInfo
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- CN103722803A CN103722803A CN201310332284.XA CN201310332284A CN103722803A CN 103722803 A CN103722803 A CN 103722803A CN 201310332284 A CN201310332284 A CN 201310332284A CN 103722803 A CN103722803 A CN 103722803A
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- radiation coating
- engine
- strength
- strength radiation
- layer material
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Abstract
The invention discloses a strong-strength radiation coating for an aircraft engine. The coating consists of a bottom-layer material and a surface-layer material, wherein the bottom-layer material is one or more of NiCoCrAlY, NiCrAl and MCrAlY which are modified by adding rhenium; a surface-layer material is obtained by adding one or more of La2Zr2O7, La2Ce2O7, Ni/Al2O3 and Ni/ZrO2 to a main body consisting of CeO2 and Y2O3-stabilzed ZrO2 and HfC/SiC; the bottom-layer material is 10 to 100 microns thick; the surface-layer material is 0.1 to 5mm thick. The coating has strong peeling strength, high-temperature stability, high corrosion resistance and high abrasion resistance; due to low heat conductivity, heat conduction can be effectively blocked; due to extremely high heat radiance, heat reaching a surface layer of the engine can be greatly reduced, the efficiency of the engine can be improved, and the service life of the engine can be prolonged.
Description
Technical field
The present invention relates to a kind of coating, particularly relate to the high-strength radiation coating of a kind of aero-engine.
Background technology
Modern aeroengine design will concentrate on and reduces fuel consumption and strengthen thrust-weight ratio, improve reliability and life-span simultaneously.Meet the challenge that this demand faces structural design and new material, wherein face coat technology plays an important role to breaking through these bottlenecks.Coating is often referred to one deck special material that is coated on piece surface, very remarkable to the effect of raising material property, prolongation part time job performance, is that aero-engine is manufactured requisite technological means.Modern aeroengine has more than 75% part all to apply various coatings to improve Performance And Reliability.
Application number is in 201010500871.1 Chinese patent, to disclose a kind of formation to have high temperature resistant every radiant heat transfer and the inorganic figure layer preparation method of microwave compatibility thoroughly, with the own ester of positive silicic acid, ethanol, deionized water and hydrochloric acid colloidal sol processed; Silicon oxide microsphere with the synthetic diameter of the own ester of positive silicic acid, isopropyl alcohol, deionized water, ammoniacal liquor at 0.3～3 μ m, then, at the titanium oxide shell of the thick high index of refraction of silicon oxide microsphere growth 30～500nm, obtains nucleocapsid structure filler.Using the core-shell structure particles of preparation as fillers dispersed in colloidal sol, after heat treatment can obtain fine and close inorganic coating uniformly.
Application number is to disclose a kind of multiduty low conductivity ceramic/noble metal lamellar composite thermal barrier coating in 201110329537.9 Chinese patent, the layered composite structure that the present invention forms by the low thermal conductive ceramic layer of alternating deposit and layer of precious metal makes thermal barrier coating have excellent heat-proof quality and thermal shock resistance, coating structure is stable, service life is long, can be used for the high temperature alloys such as aero-engine, marine engine, ground gas turbine, rocket engine, or the high temperature protection of refractory alloy hot-end component.
Application number is to disclose a kind of heat insulation structural in 201120324889.0 Chinese patent, comprise: at least one deck applies the superfine fibre shape net of infra-red radiation reflectance coating or fibrous web and one deck crude fibre that weaving face fabric forms, the described fiber volume fraction compared with crude fibre layer is less than 1%, and fibre diameter is about 20～35 μ m.The intensity of the heat-barrier material that the utility model provides is relatively high, and stopping that the thermal-radiating while does not hinder wet steam transmission, improved heat-proof quality, and the weight of heat insulation structural is also relatively light, be applicable to warm wear, sleeping bag, building insulation system, electric automobile insulation system and aviation insulation system.
But the Thermal Barrier Coatings For Aeroengines of mentioning in above-mentioned patent is all due to material and structure, all has a series of problems to be solved that have on mechanical property and resistance to high temperature corrosion performance, temperature tolerance, peel strength and effect of heat insulation.Therefore, explore a kind of superhigh temperature resistant, corrosion-resistant, the high Thermal Barrier Coatings For Aeroengines that possesses again super-high structure intensity of thermal emissivity rate becomes a study hotspot now.
Summary of the invention
The present invention is intended to overcome the deficiency of existing thermal barrier coating technology of preparing, provides a kind of aero-engine high-strength radiation coating.This invention thermal deformation is little, anti-corrosion, wear-resisting, high-strength, thermal emissivity rate is high, can effectively reduce engine temperature, improves engine efficiency, increasing service life of engine.
For the problems referred to above, the invention provides the technical scheme of the high-strength radiation coating of a kind of aero-engine:
The high-strength radiation coating of a kind of aero-engine, is characterized in that being comprised of primer and surface material.
Described primer is one or more in interpolation rhenium element modified NiCoCrAlY, NiCrAl, MCrAlY, rhenium has high-melting-point, high strength, good plasticity, wear resistance and corrosion resistance and excellent mechanical stability, under high temperature and rapid heat cycle condition, all there is good creep-resistant property, can do not corroded by hot oxygen, so the primer after mixing rhenium modification has possessed more high-strength structural strength and adhesion strength, thereby peel strength is improved greatly, and its higher thermal emissivity rate makes primer possess equally excellent radiation heat insulation function simultaneously.
Described surface material main body is CeO
2and Y
2o
3stable ZrO
2, HfC/SiC, add La simultaneously
2zr
2o
7, La
2ce
2o
7, Ni/Al
2o
3, Ni/ZrO
2in one or more, make surface material there is fabulous high temperature resistance, anti-thermal shock, erosion resistance and high radiation heat insulation performance.
Described primer thickness is 10～100 μ m, and described surface material thickness is 0.1～5mm.
Described aero-engine adopts plasma spraying method deposition with the primer of high-strength radiation coating, surface material adopts plasma spraying, vapour deposition and sol-gel deposition, the method Multiple depositions such as magnetron sputtering deposition, form 3～8 layers of micro-laminated construction replacing each other, thereby obtain fine and close crystal coating, composition and pattern also can form graded from the teeth outwards, rely on compound between refractory metal that high strength and creep resistance are provided, utilize high-temperature metal to make malleableize element, thereby overcome well the fragility of intermetallic compound, can greatly reduce the thermal conductivity factor of coating simultaneously.
Described aero-engine can be for the high temperature alloy in 1000～2400 ℃ of temperature ranges or the high temperature protection of refractory alloy with high-strength radiation coating.
Major advantage of the present invention is: 1. coating thermal conductivity is low, can effectively hinder insulating heat conduction holes; 2. thermal emissivity rate is high, can greatly reduce the heat that arrives engine top layer, improves engine efficiency, extends engine life; 3. there is higher peel strength; 4. there is high-temperature stability; 5. excellent corrosion-resistant, abrasion resistance properties.
The specific embodiment
Below in conjunction with specific embodiment, further illustrate the present invention, should understand these embodiment is only not used in and limits the scope of the invention for the present invention is described, after having read the present invention, those skilled in the art all fall within the application's claims to the modification of the various equivalent form of values of the present invention and limit.
Embodiment 1
The high-strength radiation coating of a kind of aero-engine, to add the element modified MCrAlY of rhenium as primer, adopts plasma spraying to deposit 20 μ m; With CeO
2and Y
2o
3stable ZrO
2, HfC/SiC and La
2zr
2o
7for surface material, alternately adopt plasma spraying deposition CeO
2and Y
2o
3stable ZrO
2, sol-gel deposition HfC/SiC, plasma spraying deposition La
2zr
2o
7, micro-laminated construction of formation 3 bed thickness 0.2mm.
Embodiment 2
The high-strength radiation coating of a kind of aero-engine, to add the element modified MCrAlY of rhenium and NiCoCrAlY as primer, adopts plasma spraying to deposit 80 μ m; With CeO
2and Y
2o
3stable ZrO
2, HfC/SiC add La
2zr
2o
7, La
2ce
2o7, Ni/Al
2o
3and Ni/ZrO
2for surface material, alternately adopt plasma spraying deposition CeO
2and Y
2o
3stable ZrO
2, sol-gel deposition HfC/SiC, plasma spraying deposition La
2zr
2o
7, La
2ce
2o7, Ni/Al
2o
3and Ni/ZrO
2, micro-laminated construction of formation 6 bed thickness 4mm.
Above are only two specific embodiment of the present invention, but design concept of the present invention is not limited to this, allly utilizes this design to carry out the change of unsubstantiality to the present invention, all should belong to the behavior of invading the scope of protection of the invention.In every case be the content that does not depart from technical solution of the present invention, any type of simple modification, equivalent variations and the remodeling above embodiment done according to technical spirit of the present invention, still belong to the protection domain of technical solution of the present invention.
Claims (7)
1. the high-strength radiation coating of aero-engine, is characterized in that being comprised of primer and surface material two parts.
2. high-strength radiation coating according to claim 1, is characterized in that described primer is one or more in interpolation rhenium element modified NiCoCrAlY, NiCrAl, MCrAlY.
3. high-strength radiation coating according to claim 1, is characterized in that described surface material main body is CeO
2and Y
2o
3stable ZrO
2, HfC/SiC, add La simultaneously
2zr
2o
7, La
2ce
2o
7, Ni/Al
2o
3, Ni/ZrO
2in one or more.
4. high-strength radiation coating according to claim 1, is characterized in that described primer thickness is 10～100 μ m.
5. high-strength radiation coating according to claim 1, is characterized in that described surface material thickness is 0.1～5mm.
6. high-strength radiation coating according to claim 1, it is characterized in that described primer adopts plasma spraying method deposition, described surface material adopts the method Multiple depositions such as plasma spraying, vapour deposition and sol-gel deposition, magnetron sputtering deposition, forms 3～8 layers of micro-laminated construction replacing each other.
7. high-strength radiation coating according to claim 1, is characterized in that the described high-strength radiation coating of aero-engine can be for the high temperature alloy in 1000～2400 ℃ of temperature ranges or the high temperature protection of refractory alloy.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310332284.XA CN103722803A (en) | 2013-08-02 | 2013-08-02 | Strong-strength radiation coating for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310332284.XA CN103722803A (en) | 2013-08-02 | 2013-08-02 | Strong-strength radiation coating for aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103722803A true CN103722803A (en) | 2014-04-16 |
Family
ID=50447215
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310332284.XA Pending CN103722803A (en) | 2013-08-02 | 2013-08-02 | Strong-strength radiation coating for aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103722803A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108384245A (en) * | 2018-04-04 | 2018-08-10 | 宁波伟铄电子科技有限公司 | A kind of polynary silicone grease heat conducting nanometer material of electronic component |
| CN108754386A (en) * | 2018-07-27 | 2018-11-06 | 北方工业大学 | Thermal shock resistant MCrAlY coating and preparation method thereof |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110300357A1 (en) * | 2008-12-15 | 2011-12-08 | Alstom Technology Ltd | Thermal barrier coating system, components coated therewith and method for applying a thermal barrier coating system to components |
-
2013
- 2013-08-02 CN CN201310332284.XA patent/CN103722803A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110300357A1 (en) * | 2008-12-15 | 2011-12-08 | Alstom Technology Ltd | Thermal barrier coating system, components coated therewith and method for applying a thermal barrier coating system to components |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108384245A (en) * | 2018-04-04 | 2018-08-10 | 宁波伟铄电子科技有限公司 | A kind of polynary silicone grease heat conducting nanometer material of electronic component |
| CN108384245B (en) * | 2018-04-04 | 2021-06-15 | 江门嘉钡电子科技有限公司 | Multi-element silicone grease heat-conducting composite material for electronic element |
| CN108754386A (en) * | 2018-07-27 | 2018-11-06 | 北方工业大学 | Thermal shock resistant MCrAlY coating and preparation method thereof |
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| DD01 | Delivery of document by public notice |
Addressee: TAICANG PAIOU TECHNOLOGY CONSULTATION SERVICE CO., LTD. Document name: Notification of Passing Preliminary Examination of the Application for Invention |
|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20140416 |