CN109653965B - Composite material blade protection method - Google Patents
Composite material blade protection method Download PDFInfo
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- CN109653965B CN109653965B CN201811421213.6A CN201811421213A CN109653965B CN 109653965 B CN109653965 B CN 109653965B CN 201811421213 A CN201811421213 A CN 201811421213A CN 109653965 B CN109653965 B CN 109653965B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D80/00—Details, components or accessories not provided for in groups F03D1/00 - F03D17/00
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
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- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
Abstract
The invention provides a composite material blade protection method, which comprises the following steps: coating a bottom layer on the surface to be protected of the composite material blade; coating the middle layer on the surface of the bottom layer; and coating an erosion-resistant layer on the surface of the intermediate layer. The invention improves the bonding effect between the blade and the external protective coating by coating the bottom layer on the surface of the blade. Meanwhile, the coating structure of the intermediate layer and the erosion-resistant layer is adopted, so that the integral erosion resistance of the coating can be ensured, the toughness of the metal protective coating can be improved, and the possibility of cracking of the coating is reduced.
Description
Technical Field
The application relates to the technical field of aviation, in particular to a composite material blade protection method.
Background
The resin-based composite material blade is an important means for reducing weight of a modern aviation turbofan engine, but due to the fact that the resin-based composite material blade accords with the characteristics of the material, under the condition of a service environment, the front edge of the composite material blade is very easy to be damaged due to impact or scouring of foreign matters, gravel and the like, and as shown in figure 1, the position O is an accidental damage position. Therefore, it is usually necessary to arrange a V-shaped metal protective shell at the leading edge of the blade to improve the erosion resistance of the composite material blade, and the common manufacturing methods at present include numerical control machining, hot forming, cold spraying and the like.
The V-shaped metal protective shell can protect the composite material blade through a machining and cementing method, due to the fact that strain difference exists between the V-shaped metal protective shell and the composite material blade, the front edge can generate temperature rise in the working process of an engine, the V-shaped metal protective shell can be separated from the composite material blade to be protected, and impurity-mixed particles between the V-shaped metal protective shell and the composite material blade further aggravate damage, so that protection failure and blade fracture are caused. And as the efficiency of the engine is improved, the shape of the blade is increasingly complex, and the application difficulty of the method is increased.
The existing manufacturing method of the V-shaped metal shell comprises numerical control machining and hot forming. The numerical control machining method is carried out by adopting bars or die forgings, has the defects of high cost, low yield, environmental pollution and the like, and particularly has more remarkable defects when machining parts with thin walls and complex shapes like metal protective cases. In the thermal forming process, because a high-temperature process which cannot be borne by the composite material exists, the manufactured metal protective shell cannot be directly covered on the surface of the composite material blade. For this reason, it has been proposed to directly manufacture a metal edge on the surface of a composite blade by a cold spray technique, but the metal edge is not well bonded to the composite substrate and the coating is easily cracked.
Disclosure of Invention
In order to solve one of the technical problems, the invention provides a composite material blade protection method.
The embodiment of the invention provides a composite material blade protection method, which comprises the following steps:
coating a bottom layer on the surface to be protected of the composite material blade;
coating the middle layer on the surface of the bottom layer;
and coating an erosion-resistant layer on the surface of the intermediate layer.
Preferably, the material of the bottom layer is copper, nickel or a copper-nickel mixture.
Preferably, the thickness of the bottom layer is 0.1mm to 0.3 mm.
Preferably, the material of the intermediate layer is titanium, aluminum, nickel or titanium-aluminum-nickel alloy.
Preferably, the thickness of the intermediate layer is 0.1mm to 0.5 mm.
Preferably, the material of the erosion-resistant layer is a mixture of metal and hard particles.
Preferably, the metal in the erosion-resistant layer material is titanium, aluminum, nickel or titanium-aluminum-nickel alloy, the hard particles are one or a combination of several of tungsten carbide, chromium carbide, titanium nitride, titanium boride or titanium carbide, and the content of the hard particles is 20wt% -40 wt%.
Preferably, the thickness of the erosion resistant layer is 0.2mm to 0.4 mm.
Preferably, before the step of coating the surface of the composite blade with the bottom layer, the method further comprises the following steps: the composite blade is roughened and/or sensitized.
Preferably, before the step of coating the surface of the composite blade with the bottom layer, the method further comprises the following steps: and carrying out sealing protection on other areas except the surface to be protected on the composite material blade.
The invention has the following beneficial effects: the invention improves the bonding effect between the blade and the external protective coating by coating the bottom layer on the surface of the blade. Meanwhile, the coating structure of the intermediate layer and the erosion-resistant layer is adopted, so that the integral erosion resistance of the coating can be ensured, the toughness of the metal protective coating can be improved, and the possibility of cracking of the coating is reduced.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
FIG. 1 is a schematic illustration of an accidental injury to a leading edge of a composite blade;
FIG. 2 is a flow chart of a composite blade protection method according to an embodiment of the present invention;
FIG. 3 is a schematic composition diagram of a metal passivation layer according to an embodiment of the invention;
fig. 4 is a schematic cross-sectional view of a metal protection layer according to an embodiment of the invention.
Reference numerals:
1. the composite material blade comprises a composite material blade body, 2, a bottom layer, 3, a middle layer, 4, an erosion resistant layer, 5, a metal protective layer, 6 and hard particles.
Detailed Description
In order to make the technical solutions and advantages of the embodiments of the present application more apparent, the following further detailed description of the exemplary embodiments of the present application with reference to the accompanying drawings makes it clear that the described embodiments are only a part of the embodiments of the present application, and are not exhaustive of all embodiments. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
As shown in fig. 2, the present embodiment proposes a composite blade protection method, which includes:
s102, coating a bottom layer 2 on the surface to be protected of the composite material blade 1;
s104, coating the middle layer 3 on the surface of the bottom layer 2;
and S106, coating the erosion resistant layer 4 on the surface of the intermediate layer 3.
Specifically, as shown in fig. 3 and 4, the essence of the method for protecting a composite blade according to the present embodiment is to coat a metal protection layer 5 on the surface of the blade, where the metal protection layer 5 includes three parts, namely, a bottom layer 2, an intermediate layer 3 and an erosion-resistant layer 4.
In the embodiment, firstly, a chemical plating or electroplating method is adopted to form a metal bottom layer 2 on the surface of the composite material blade 1, the material of the bottom layer 2 can be copper, nickel or a mixture of copper and nickel, and the thickness of the bottom layer 2 is controlled to be 0.1mm-0.3 mm.
Then, the pure metal intermediate layer 3 is prepared by adopting a cold spraying mode, and the material of the intermediate layer 3 can be titanium, aluminum, nickel or alloy thereof. The thickness of the middle layer 3 can reach 0.1mm-0.5 mm.
And finally, preparing an erosion-resistant layer 4 consisting of metal and hard particles 6 on the surface of the middle layer 3, wherein the metal can be titanium, aluminum, nickel or titanium-aluminum-nickel alloy, the hard particles 6 are one or a combination of more of tungsten carbide, chromium carbide, titanium nitride, titanium boride or titanium carbide, the content of the hard particles 6 is 20-40 wt%, and the thickness of the erosion-resistant layer 4 is 0.2-0.4 mm.
Through the structure of the bottom layer 2, the middle layer 3 and the erosion-resistant layer 4, the coatings can be effectively combined, the overall anti-scouring capability and toughness of the coatings are ensured, and the possibility of cracking of the coatings is reduced.
Between the application of the bottom layer 2 to the surface of the composite blade 1, a step of sealing protection of the composite blade 1 in the areas where no metal protection layer is required is also required to avoid corrosion of the areas by the coating substance. In addition, in order to stably coat the base layer 2 on the surface of the blade, the surface of the blade needs to be roughened and/or sensitized. The coating of the coating can be better achieved by the above preparation.
The method of the present embodiment is implemented by a specific process as follows:
the protective adhesive tape is pasted on the area of the composite material blade 1 without the metal protective layer, so that the adhesive tape is perfectly attached to the profile of the blade, and the subsequent corrosive medium is prevented from entering;
the surface of the composite material blade 1 is roughened by using a dilute sulfuric acid solution, wherein the concentration of the roughening solution is 430g/L-450g/L sulfuric acid and 360g/L-400g/L chromium trioxide, the roughening temperature is controlled to be 65-80 ℃, and the roughening time is 8-12 min;
adopting colloidal palladium to perform surface sensitization on the composite material blade 1, wherein the sensitization solution and the concentration are 0.8-1.0 g/L of palladium chloride, 300-340 g/L of hydrochloric acid, 50-60 g/L of stannous chloride dihydrate and 7-10 g/L of sodium stannate heptahydrate, the sensitization temperature is room temperature, and the time is 18-20 min;
electroless nickel plating, the solution is controlled as follows: 30g/L of nickel sulfate hexahydrate, 30g/L of sodium hypophosphite monohydrate and 20g/L of citric acid, wherein the pH value is 4.2-5.2, the temperature is 70-80 ℃, the time is 6 hours, and the plating layer is about 0.05-0.07 mm.
Copper electroplating, the solution control is as follows: copper sulfate 180-200g/L and sulfuric acid 50-70 g/L. The cathode current density is about 1A/dm2-1.5A/dm2The deposition time is 10 hours; the thickness of the plating layer is about 0.07mm to 0.09 mm.
Cold spraying titanium, wherein the granularity of titanium alloy TC4 powder is 5-60 mu m; the cold spraying process parameters are as follows: the nitrogen pressure is 3.5MPa to 4.0 MPa; the temperature is 780-820 ℃; gas flow 80m3/h-85m3H; the powder feeding speed is 3rpm to 5 rpm; the spraying distance is 35mm-45mm, and the spraying angle is 75-90 degrees; the moving speed of the spray gun is 500mm/s-600mm/s, and the thickness is 0.1mm-0.5 mm.
Cold spraying titanium and tungsten carbide particles, wherein the powder components are 75% of titanium alloy TC4 and 25% of tungsten carbide cobalt powder WC12Co, the granularity of the titanium alloy TC4 powder is 5-60 mu m, and the granularity of the tungsten carbide cobalt powder WC12Co is 5-30 mu m; the cold spraying process parameter is that the nitrogen pressure is 3.5MPa-4.0 MPa; the temperature is 780-820 ℃; gas flow 80m3/h-85m3H; the powder feeding speed is 3rpm to 5 rpm; the spraying distance is 35mm-45mm, and the spraying angle is 75-90 degrees; the moving speed of the spray gun is 500mm/s-600mm/s, and the thickness is 0.3mm-0.5 mm.
Numerical control machining and manual clamping, wherein a numerical control machining center is adopted to machine the blade shape to the digital-analog requirement, and manual clamping is adopted for micro areas such as corners and the like to meet the use requirement.
The present embodiment improves the bonding effect between the blade and the outer protective coating by coating the surface of the blade with the primer layer 2. Meanwhile, the coating structure of the middle layer 3 and the erosion-resistant layer 4 is adopted, so that the integral erosion resistance of the coating can be ensured, the toughness of the metal protective coating can be improved, and the possibility of cracking of the coating is reduced.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (5)
1. A method of composite blade protection, the method comprising:
firstly, pasting a protective adhesive tape on an area of the composite material blade, which does not need a metal protective layer, so that the adhesive tape is perfectly attached to the molded surface of the blade, and a subsequent corrosive medium is prevented from entering; coarsening the surface of the composite material blade by using a dilute sulfuric acid solution, wherein the coarsening solution and the concentration thereof are 430g/L-450g/L of sulfuric acid and 360g/L-400g/L of chromium trioxide, the coarsening temperature is controlled to be 65-80 ℃, and the coarsening time is 8min-12 min;
adopting colloidal palladium to perform surface sensitization on the composite material blade, wherein the sensitization solution and the concentration are 0.8-1.0 g/L of palladium chloride, 300-340 g/L of hydrochloric acid, 50-60 g/L of stannous chloride dihydrate and 7-10 g/L of sodium stannate heptahydrate, the sensitization temperature is room temperature, and the time is 18-20 min;
coating a bottom layer on the surface to be protected of the composite material blade, wherein the coating of the bottom layer sequentially comprises chemical nickel plating and electrolytic copper plating; wherein in the chemical nickel plating, the solution is controlled as follows: 30g/L of nickel sulfate hexahydrate, 30g/L of sodium hypophosphite monohydrate and 20g/L of citric acid, wherein the pH value is 4.2-5.2, the temperature is 70-80 ℃, the time is 6 hours, the plating thickness is about 0.05mm-0.07mm, and in the electrolytic copper plating, the solution control is as follows: copper sulfate 180-200g/L and sulfuric acid 50-70g/L, and the cathode current density is about 1A/dm2-1.5A/dm2The deposition time is 10 hours; the thickness of the electroplating layer is about 0.07mm-0.09 mm;
coating the middle layer on the surface of the bottom layer;
the surface of the middle layer is coated with an erosion-resistant layer, the erosion-resistant layer is made of a mixture of metal and hard particles, the metal in the erosion-resistant layer is titanium, aluminum, nickel or titanium-aluminum-nickel alloy, the hard particles are one or a combination of more of tungsten carbide, chromium carbide, titanium nitride, titanium boride or titanium carbide, and the content of the hard particles is 20-40 wt%.
2. The method of claim 1, wherein the bottom layer has a thickness of 0.1mm to 0.3 mm.
3. The method of claim 1, wherein the material of the intermediate layer is titanium, aluminum, nickel, or a titanium-aluminum-nickel alloy.
4. A method according to claim 1 or 3, characterised in that the thickness of the intermediate layer is 0.1-0.5 mm.
5. The method of claim 1, wherein the erosion resistant layer has a thickness of 0.2mm to 0.4 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811421213.6A CN109653965B (en) | 2018-11-27 | 2018-11-27 | Composite material blade protection method |
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| CN201811421213.6A CN109653965B (en) | 2018-11-27 | 2018-11-27 | Composite material blade protection method |
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| CN109653965A CN109653965A (en) | 2019-04-19 |
| CN109653965B true CN109653965B (en) | 2019-12-20 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8449994B2 (en) * | 2009-06-30 | 2013-05-28 | Honeywell International Inc. | Turbine engine components |
| JP6793039B2 (en) * | 2014-04-09 | 2020-12-02 | ヌオーヴォ ピニォーネ ソチエタ レスポンサビリタ リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｓ．Ｒ．Ｌ． | How to protect turbo engine components from droplet erosion, components and turbo engines |
| CN106335251A (en) * | 2016-08-22 | 2017-01-18 | 联诺欧机械科技江苏有限公司 | Oxidation resistant metal composite material |
| CN106321494A (en) * | 2016-10-25 | 2017-01-11 | 郑州航空工业管理学院 | Anti-erosion and friction-resistant film for fan blades of aeto-turbofan engine and preparation method of anti-erosion and friction-resistant film |
| CN108397418A (en) * | 2018-02-08 | 2018-08-14 | 合肥峰腾节能科技有限公司 | A kind of high-strength abrasion-proof corrosion protection radiating fan blade |
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