CN212223077U - Titanium alloy shaft part - Google Patents
Titanium alloy shaft part Download PDFInfo
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- CN212223077U CN212223077U CN202020868608.7U CN202020868608U CN212223077U CN 212223077 U CN212223077 U CN 212223077U CN 202020868608 U CN202020868608 U CN 202020868608U CN 212223077 U CN212223077 U CN 212223077U
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Abstract
The utility model provides a titanium alloy axle class piece relates to aviation spare part technical field. The utility model provides a titanium alloy shaft part, which comprises a titanium alloy base body, wherein the titanium alloy base body comprises a threaded part, a positioning part, a matching rotating part and a nozzle part which are connected in sequence, and further comprises an air supersonic speed coating deposited on the surface of the matching rotating part; and a magnetron sputtering hard coating deposited on the surface of the air supersonic speed coating; the air supersonic coating is a WC-10Co-4Cr layer, a WC-12Co layer, a WC-17Co layer or WC-20Cr layer3C27.5Ni layer, wherein the magnetron sputtering hard coating is a CrN layer or a CrAlN layer. The utility model provides a titanium alloy axle class piece has low stress, and the coating is high with the bonding strength of titanium alloy base member, and hardness is high, has excellent wear-resisting and corrosion resistance, and long service life can effectively use on the aircraft air brake motion section of thick bamboo that marine atmosphere environment was on active service.
Description
Technical Field
The utility model relates to an aviation spare part technical field, in particular to titanium alloy axle class piece.
Background
The titanium alloy has the advantages of high specific strength, good corrosion resistance and the like, is widely applied to high-end aviation equipment, but has the problems of poor wear resistance, low seizure resistance, insufficient atmosphere corrosion resistance life and the like, so that the service life of the titanium alloy on a plurality of key parts is extremely short. If the titanium alloy shaft part for connecting the airplane speed reduction plate moving cylinder in service in the marine atmosphere environment is used, because no lubricating medium exists between the shaft and the shaft sleeve, the shaft fails due to adhesion abrasion among metals in the sliding friction process, and due to the corrosion effect of the marine atmosphere environment, the service life of the shaft is extremely short, and the flying cost is greatly increased.
In order to improve the wear resistance and corrosion resistance of titanium alloy in marine atmosphere environment, the prior art deposits a metal chromium layer on the surface of the titanium alloy through a chromium electroplating process or deposits NiCr-Cr on the surface of the titanium alloy through an oxy-kerosene supersonic flame spraying process3C2The coating or the Co-WC coating, but the metal chromium layer needs to be hydrogenated in the chromium electroplating process, so that hydrogen is polymerized in the titanium alloy to cause stress concentration, fine cracks exist in the titanium alloy, and embrittlement or cracking occurs under the action of an external load; and NiCr-Cr3C2The coating or the Co-WC coating can not avoid interface inclusions because the base material is subjected to sand blasting treatment before the oxygen kerosene supersonic flame spraying, and the higher preparation temperature enables an oxide layer to be generated on the interface, thereby seriously influencing the bonding performance of the coating and the base body.
SUMMERY OF THE UTILITY MODEL
In view of this, the present invention provides a titanium alloy shaft. The utility model provides a hydrogen embrittlement hidden danger has been eliminated to titanium alloy axle class piece, has the low stress, and the coating is high with the bonding strength of titanium alloy base member, and hardness is high, has excellent wear-resisting and corrosion resistance, long service life.
In order to realize the purpose of the utility model, the utility model provides a following technical scheme:
the utility model provides a titanium alloy axle class piece, including the titanium alloy base member, the titanium alloy base member still includes including screw thread portion 1, location portion 2, cooperation rotation portion 3 and mouthpiece portion 5 that connect in order:
an air supersonic coating deposited on the surface of said mating rotating part 3;
and a magnetron sputtering hard coating deposited on the surface of the air supersonic speed coating;
the air supersonic coating is a WC-10Co-4Cr layer, a WC-12Co layer, a WC-17Co layer or WC-20Cr layer3C27.5Ni layer, wherein the magnetron sputtering hard coating isA CrN layer or a CrAlN layer.
Preferably, the thickness of the air supersonic coating is 80-400 μm, and the thickness of the magnetron sputtering hard coating is 5-10 μm.
Preferably, the thickness of the air supersonic coating is 100-350 μm, and the thickness of the magnetron sputtering hard coating is 6-8 μm.
Preferably, the sum of the outer diameter of the matching rotating part 3, the thickness of the air supersonic coating and the thickness of the magnetron sputtering hard coating is 30-50 mm.
Preferably, the sum of the outer diameter of the matching rotating part 3, the thickness of the air supersonic coating and the thickness of the magnetron sputtering hard coating is 34-42 mm.
Preferably, the total length of the titanium alloy shaft part is 150-450 mm.
The utility model provides a titanium alloy shaft part, which comprises a titanium alloy base body, wherein the titanium alloy base body comprises a thread part 1, a positioning part 2, a matching rotating part 3 and a nozzle part 5 which are connected in sequence; further comprises an air supersonic coating deposited on the surface of the matching rotating part 3; and a magnetron sputtering hard coating deposited on the surface of the air supersonic speed coating; the air supersonic coating is a WC-10Co-4Cr layer, a WC-12Co layer, a WC-17Co layer or WC-20Cr layer3C27.5Ni layer, wherein the magnetron sputtering hard coating is a CrN layer or a CrAlN layer. The utility model has the advantages that the air supersonic speed coating and the magnetron sputtering hard coating are sequentially deposited on the surface of the matching rotating part of the titanium alloy matrix, compared with the chromium electroplating coating, the hydrogen embrittlement hidden danger is eliminated without hydrogenation process, the titanium alloy shaft part has low stress, and the service life is prolonged; the air supersonic coating is used as a bonding layer, has the characteristics of low porosity, good wear resistance and corrosion resistance of the coating, and has high bonding strength with a titanium alloy matrix, high bonding strength of the magnetron sputtering coating, compact microstructure, high hardness and excellent corrosion resistance. Therefore, the utility model provides a titanium alloy axle class piece has low stress, coating and titanium alloy baseThe body has high bonding strength, high hardness, excellent wear resistance and corrosion resistance and long service life, and can be effectively applied to the airplane speed reduction plate moving cylinder in service in the marine atmosphere environment.
The example result shows that the surface hardness of the coating of the titanium alloy shaft part provided by the utility model is more than 1800HV0.05The stress of the coating is less than 0.8GPa, the bonding strength of the coating and the substrate is more than 76MPa, the loss mass of the coating is only 0.0126-0.0132 g after 2h of frictional wear under the 100N load condition, and the coating has no corrosion point after 240h of neutral salt spray corrosion test.
Drawings
Fig. 1 is a schematic structural view of a titanium alloy shaft part according to the present invention; in fig. 1, 1 denotes a threaded portion, 2 denotes a positioning portion, 3 denotes a co-rotating portion, 4 denotes a coating of the surface of the co-rotating portion, and 5 denotes a nozzle portion.
Detailed Description
The utility model provides a titanium alloy axle class piece, including the titanium alloy base member, the titanium alloy base member still includes including screw thread portion 1, location portion 2, cooperation rotation portion 3 and mouthpiece portion 5 that connect in order:
an air supersonic coating deposited on the surface of said mating rotating part 3;
and a magnetron sputtering hard coating deposited on the surface of the air supersonic speed coating;
the air supersonic coating is a WC-10Co-4Cr layer, a WC-12Co layer, a WC-17Co layer or WC-20Cr layer3C27.5Ni layer, wherein the magnetron sputtering hard coating is a CrN layer or a CrAlN layer.
The utility model provides a titanium alloy axle class piece includes the titanium alloy base member, the titanium alloy base member is including screw thread portion 1, location portion 2, cooperation rotation portion 3 and the nozzle portion 5 of connecting in order. The present invention has no particular requirement on the chemical composition of the titanium alloy matrix, and titanium alloys known to those skilled in the art may be used, such as TC2, TC4, and TC 11. In the present invention, the titanium alloy shaft is shown in fig. 1, 1 indicates a threaded portion, 2 indicates a positioning portion, 3 indicates a matching rotating portion, 4 indicates a coating layer on the surface of the matching rotating portion, and 5 indicates a nozzle portion; wherein the threaded part, the positioning part, the matching rotating part and the nozzle part form a titanium alloy shaft part base body.
The titanium alloy shaft part provided by the utility model also comprises an air supersonic coating deposited on the surface of the matching rotating part; the air supersonic coating is a WC-10Co-4Cr layer, a WC-12Co layer, a WC-17Co layer or WC-20Cr layer3C2-7.5Ni layer. In the utility model discloses, the thickness of air supersonic speed coating is preferred 80 ~ 400 mu m, more preferred 100 ~ 350 mu m. The utility model discloses in, the air supersonic speed coating has the characteristics that the coating porosity is low, wear resistance decreases and corrosion resistance is good as the tie coat, and is high with the bonding strength of titanium alloy base member.
The utility model provides a titanium alloy axle class piece is in including the deposit the magnetron sputtering hardcoat on air supersonic speed coating surface, magnetron sputtering hardcoat is CrN layer or CrAlN layer. In the utility model discloses, magnetron sputtering hardcoat's thickness preferred is 5 ~ 10 mu m, more preferred is 6 ~ 8 mu m. The utility model discloses in, magnetron sputtering coating bonding strength is high, and the microstructure is compact, and hardness is high, and corrosion resistance is excellent, and as the surface coating on air supersonic speed spraying layer, not only can block up the hole on air supersonic speed spraying layer surface (although the porosity is low, still can have less than 1% hole in air supersonic speed spraying layer), but also can further improve titanium alloy surface wear resistance and corrosion resistance; compared with chromium electroplating coatings, the air supersonic coating and the magnetron sputtering hard coating have no hydrogenation process, eliminate hydrogen embrittlement hidden danger, enable titanium alloy shaft parts to have low stress and prolong the service life.
The utility model discloses in, the external diameter of cooperation rotating part, the thickness of air supersonic speed coating and the thickness sum of magnetron sputtering hardcoat are preferred 30 ~ 50mm, more preferred 34 ~ 42 mm. The utility model has no special requirements on the specific sizes of the other parts (the thread part, the positioning part and the nozzle part) of the titanium alloy shaft part, and is just the size of the titanium alloy shaft part base body for connecting the airplane speed reduction plate actuating cylinder, which is well known by the technical personnel in the field; in the embodiment of the present invention, the total length of the titanium alloy substrate is preferably 150 to 450 mm.
The utility model provides a titanium alloy axle class piece has low stress, and the coating is high with the bonding strength of titanium alloy base member, and hardness is high, has excellent wear-resisting and corrosion resistance, long service life.
The utility model discloses in, titanium alloy axle class piece is preferred to be obtained according to following step preparation:
(1) alloy powder is sprayed on the surface of the matching rotating part 3 of the titanium alloy substrate in an air supersonic speed manner to form an air supersonic speed coating; the chemical composition of the alloy powder is WC-10Co-4Cr, WC-12Co, WC-17Co or WC-20Cr3C2-7.5Ni；
(2) Polishing the air supersonic coating until the surface roughness Ra is less than 0.8 mu m, and then sequentially performing plasma glow etching and magnetron sputtering on the surface of the polished air supersonic coating to obtain the titanium alloy shaft part; the target material of the magnetron sputtering is a chromium target or a chromium-aluminum target, and the sputtering gas is nitrogen.
The utility model adopts the air supersonic speed spraying method to spray alloy powder on the surface of the matching rotating part of the titanium alloy matrix to form an air supersonic speed coating; the chemical composition of the alloy powder is WC-10Co-4Cr, WC-12Co, WC-17Co or WC-20Cr3C27.5 Ni. In the present invention, the particle size of the alloy powder is preferably 5 to 50 μm, and more preferably 10 to 35 μm; the utility model has no special requirements on the source of the alloy powder, and the corresponding alloy powder with the source well known by the technicians in the field can be adopted. In the present invention, the technological parameters of the air supersonic spraying method are preferably: taking nitrogen as a powder conveying carrier gas, wherein the pressure of the nitrogen is 0.0015-0.0018 MPa, and more preferably 0.0016-0.0017 MPa; the pressure of the air is preferably 40-45 MPa, and more preferably 42-43 MPa; propane is used as main fuel gas, and the pressure of the propane is preferably 0.8-0.9 MPa, and more preferably 0.85 MPa; hydrogen is used as secondary fuel gas, and the pressure of the hydrogen is preferably 0.1-0.15 MPa, and more preferably 0.12-0.13 MPa; during the air supersonic speed spraying process, the temperature of the titanium alloy matrix is preferably not more than 120 ℃.
Before the air supersonic speed sprays the alloy powder, the utility model preferably adopts an air supersonic speed spray gun to spray and sweep on the surface of the titanium alloy substrate to remove a surface oxide layer and pollutants, and only the air, the propane and the hydrogen are introduced in the process without introducing the alloy powder; the number of the blasting is preferably two. The utility model discloses it is right no special requirement of the embodiment of air supersonic speed spraying method, adopt the familiar mode of technical personnel in the field can, the homogeneity of spraying coating is guaranteed to the rotatory revolving stage of accessible in the spraying process. The utility model discloses in, air supersonic speed spraying preparation temperature is low, spraying flame velocity is higher, and the energy when combining with the base member is high, and the coating porosity that obtains is low, wear-resisting damage and corrosion-resistant characteristic and better with the bonding strength of base member, and in addition, air supersonic speed spraying production efficiency is high, need not sandblast in advance, can greatly reduced processing cost.
After forming the air supersonic speed coating, the utility model discloses will the air supersonic speed coating is polished to surface roughness Ra < 0.8 mu m, then carries out plasma glow etching and magnetron sputtering in proper order on the air supersonic speed coating surface after polishing, obtains titanium alloy axle class spare. The utility model discloses it is right preferably to adopt the mode of grinding air supersonic speed coating is polished, the grinding is preferred: and grinding and fine-processing the air supersonic coating by using a diamond wheel or a cubic borax nitride wheel until the surface of the coating has no cracks and no macroscopic pores, and the surface roughness Ra of the coating after grinding is less than 0.8 mu m.
After polishing, the utility model discloses still preferably carry out ultrasonic cleaning and drying in proper order with the air supersonic speed coating after polishing. In the present invention, the cleaning agent for ultrasonic cleaning is preferably acetone; the ultrasonic power of the ultrasonic cleaning is preferably 1kW, and the time is preferably 12-15 min; removing cutting fluid and oil stains remained on the surface of the coating during polishing by the ultrasonic cleaning; the drying temperature is preferably 100 ℃ and the drying time is preferably 10 min.
In the present invention, the plasma glow etching conditions preferably include: the degree of vacuum is preferably 2X 10- 3Pa; the gas source is preferablyArgon gas, wherein the flow rate of the gas source is preferably 180-200 sccm, and more preferably 190 sccm; the power of the ion source is preferably 1.2-1.5 kW, and more preferably 1.3-1.4 kW; the etching time is preferably 30-45 min, and more preferably 35-40 min. The utility model discloses a plasma glow etching mainly is pollutant and the oxide layer on getting rid of air supersonic speed coating surface, and the deposit of the sputtering ion of being convenient for is on activation appearance piece surface.
In the utility model, the target material of magnetron sputtering is a chromium target or a chromium-aluminum target, and the sputtering gas is nitrogen; the magnetron sputtering conditions preferably include: the degree of vacuum is preferably 2X 10-3Pa; the flow rate of the sputtering gas is preferably 100-150 sccm, and more preferably 120-130 sccm; the sputtering power is preferably 5-8 kW, and more preferably 6-7 kW; the bias voltage of the substrate is preferably 80-150V, more preferably 100-120V; the sputtering time is preferably 4 h.
In the embodiment of the present invention, the plasma glow etching and the magnetron sputtering are both performed in the magnetron sputtering device, and the specific operation is preferably: fixing the titanium alloy shaft part polished with the air supersonic speed coating on a rotating stand of a magnetron sputtering device, and then vacuumizing until the vacuum degree reaches 2 x 10-3Pa, starting an ion source to perform plasma glow etching on the titanium alloy shaft part; and after the etching is finished, introducing sputtering gas, starting the target material, and performing magnetron sputtering. The utility model has no special requirements on the magnetron sputtering equipment, and the magnetron sputtering equipment which is well known by the technical personnel in the field can be adopted.
The utility model provides a preparation method process is simple, easily operation, and production efficiency is high, and the yield is high.
The titanium alloy shaft part provided by the utility model can be remanufactured after the coating is worn; the remanufacturing method is preferably: and removing the air supersonic coating and the magnetron sputtering hard coating on the surface of the matched rotating part by adopting a mechanical grinding or water jet method (a part of a matrix of the matched rotating part can be removed in the removing process), and preparing the air supersonic coating and the magnetron sputtering hard coating by adopting the method again (the thickness of the prepared air supersonic coating is increased to fill the removed matrix part). The utility model discloses a refabrication can prolong the life of part.
The utility model provides a titanium alloy axle class piece is used in an aircraft speed reduction board motion section of thick bamboo, during the application, titanium alloy axle class piece connects bushing through the motion bobbin of cooperation rotation portion with the aircraft speed reduction board, and specific connected mode is that the screw thread portion of titanium alloy axle class piece is fixed on a speed reduction board motion section of thick bamboo, and location portion and speed reduction board motion section of thick bamboo location are connected, and cooperation rotation portion rotates with the cooperation of motion bobbin nipple cover, and mouthpiece portion is connected with aircraft hydraulic pressure pipe in addition, constitutes hydraulic circuit. Aircraft speed reduction board is in active service in the marine atmosphere environment, and when the cooperation portion of rotating of titanium alloy axle class spare was received the pipe box cooperation with the motion and is rotated, there was reciprocal wearing and tearing to contact corrosive environment, the utility model provides a titanium alloy axle class spare has low stress, and the coating is high with the bonding strength of titanium alloy base member, and hardness is high, has excellent wear-resisting and corrosion resistance, and long service life can effectively use on the aircraft speed reduction board motion section of thick bamboo that marine atmosphere environment was in active service.
The titanium alloy shaft parts provided by the present invention will be described in detail with reference to the following examples, but they should not be construed as limiting the scope of the present invention.
Example 1
A titanium alloy shaft part used in matching installation with a connecting sleeve of a moving cylinder of an airplane speed reducer is 153mm in total length, 40mm in outer diameter of a matching rotating part and made of TC2 material; the preparation process of the titanium alloy shaft part comprises the following steps:
(1) fixing a titanium alloy shaft part base body on a rotary table, scanning the surface of a matched rotating part of a titanium alloy shaft twice by adopting an air supersonic speed spray gun, and only introducing mixed gas (air, propane and hydrogen) without spraying powder in the process so as to remove an oxide layer and pollutants on the surface of the matched rotating part;
using nitrogen as powder feeding carrier gas, wherein the pressure is 0.0015MPa, introducing WC-10Co-4Cr powder with the particle size of 10-35 μm into an air supersonic spray gun, and when air supersonic spraying is performed, the air pressure is 40MPa, propane is used as main fuel gas, the propane pressure is 0.8MPa, hydrogen is used as secondary fuel gas, and the hydrogen pressure is 0.1 MPa; the uniformity of a sprayed layer is ensured by rotating the rotary table in the spraying process, meanwhile, the shaft temperature is controlled not to exceed 120 ℃, and a micrometer is adopted to measure the increment of the thickness of the coating on the surface of the matched rotating part by 350 mu m in the spraying process;
(2) after air supersonic spraying, grinding and finish machining are carried out on the coating by adopting a diamond grinding wheel until no crack exists on the surface of the coating and no pore is visible to naked eyes, the surface roughness Ra of the coating after grinding is controlled to be less than 0.8 mu m, and the dimensional accuracy is ensured to be within the required matching range; then ultrasonically cleaning the titanium alloy shaft by using acetone, wherein the ultrasonic power is 1kW, the ultrasonic time is 15min, and after cleaning, putting the titanium alloy shaft into a 100 ℃ oven for heat preservation treatment for 10 min;
(3) fixing the titanium alloy shaft obtained in the step (2) on a rotating stand of a magnetron sputtering device, then vacuumizing until the vacuum degree of a vacuum chamber reaches 2 multiplied by 10-3After Pa, introducing argon gas for plasma glow etching cleaning, wherein the flow of the argon gas is 200sccm, the power of an ion source is set to be 1.5kW, and the etching time is 30 min; and after the plasma glow etching, introducing 120sccm nitrogen, starting a chromium target, sputtering the power of 6kW, biasing the substrate to 120V, depositing for 4h, and increasing the coating thickness by 6 microns to obtain the titanium alloy shaft part, wherein the structural schematic diagram is shown in FIG. 1, 1 represents a threaded part, 2 represents a positioning part, 3 represents a matching rotating part, 4 represents a coating on the surface of the matching rotating part, and 5 represents a nozzle part.
The test shows that the surface hardness of the coating of the titanium alloy shaft part in the embodiment is 1950HV0.05The bonding strength of the coating and the titanium alloy matrix is 79.93MPa, the coating stress is 0.8GPa, the loss mass of the coating is only 0.0126g after 2h of frictional wear under the 100N load condition, the coating has no corrosion point after 240h of neutral salt spray corrosion test (the hardness is tested by a microhardometer, the bonding strength is tested by a tensile testing machine, the coating stress is tested by X-ray diffraction, the frictional wear is tested by a ball-disk frictional wear testing machine, and the salt spray is tested by a salt spray test box).
Example 2
A titanium alloy shaft which is matched with a connecting pipe sleeve of a moving cylinder of an airplane speed reducer for installation and use has the total length of 420mm, the outer diameter of a matching rotating part of 34mm and TC4 material; the preparation process of the titanium alloy shaft part comprises the following steps:
(1) fixing a titanium alloy shaft part base on a rotary table, firstly, sweeping the surface of a matched rotating part of a titanium alloy shaft twice by adopting an air supersonic spray gun, and only introducing mixed gas (air, propane and hydrogen) without spraying powder in the process so as to remove an oxide layer and pollutants on the surface of the matched rotating part; nitrogen is used as a powder feeding carrier gas, the pressure is 0.0018MPa, WC-20Cr3C2-7.5Ni powder with the particle size of 5-45 mu m is introduced into an air supersonic spray gun, the air pressure is 45MPa when air supersonic spraying is carried out, propane is used as a main fuel gas, the propane pressure is 0.9MPa, hydrogen is used as a secondary fuel gas, and the hydrogen pressure is 0.15 MPa; the uniformity of a sprayed layer is ensured by rotating the rotary table in the spraying process, the shaft temperature is controlled not to exceed 120 ℃, and a micrometer is adopted to measure the increment of the thickness of the coating on the surface of the matched rotating part by 300 mu m in the spraying process;
(2) after air supersonic spraying, grinding and finish machining the coating by using a cubic borax nitride wheel until the surface of the coating has no cracks and no pores visible to naked eyes, controlling the surface roughness Ra of the ground coating to be less than 0.8 mu m, and ensuring that the dimensional accuracy is within the required matching range; then ultrasonically cleaning the titanium alloy shaft by using acetone, wherein the ultrasonic power is 1kW, the ultrasonic time is 12min, and after cleaning, putting the titanium alloy shaft into a 100 ℃ oven for heat preservation treatment for 10 min;
(3) fixing the titanium alloy shaft obtained in the step (2) on a rotating stand of a magnetron sputtering device, then vacuumizing until the vacuum degree of a vacuum chamber reaches 2 multiplied by 10-3After Pa, introducing argon gas for plasma glow etching, wherein the argon gas flow is 180sccm, the ion source power is set to be 1.2kW, and the etching time is 45 min; and after plasma glow etching cleaning, introducing 150sccm nitrogen, starting a chromium-aluminum target, sputtering the power of 8kW, biasing the substrate to 100V, depositing the coating for 4h, and increasing the thickness of the coating by 8 μm to obtain the titanium alloy shaft part, wherein the structural schematic diagram is shown in FIG. 1, 1 represents a threaded part, 2 represents a positioning part, 3 represents a matching rotating part, 4 represents a coating on the surface of the matching rotating part, and 5 represents a nozzle part.
Through tests, the surface hardness of the coating of the titanium alloy shaft part in the embodiment is 1880HV0.05The bonding strength of the coating is 76.58MPa, the stress of the coating is 0.6GPa, and the load bar is 100NAfter the part is abraded by friction for 2 hours, the loss mass of the coating is only 0.0132g, and the coating has no corrosion point after 240 hours of neutral salt spray corrosion test.
Can see by above embodiment, the utility model provides a titanium alloy axle class piece has low stress, and the coating is high with the bonding strength of titanium alloy base member, and hardness is high, has excellent wear-resisting and corrosion resistance to can show improvement long service life.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (6)
1. The utility model provides a titanium alloy axle class piece, includes the titanium alloy base member, the titanium alloy base member is including screw thread portion (1), location portion (2), cooperation rotation portion (3) and mouthpiece portion (5) that connect in order, its characterized in that still includes:
an air supersonic coating deposited on the surface of the mating rotating part (3);
and a magnetron sputtering hard coating deposited on the surface of the air supersonic speed coating;
the air supersonic coating is a WC-10Co-4Cr layer, a WC-12Co layer, a WC-17Co layer or WC-20Cr layer3C27.5Ni layer, wherein the magnetron sputtering hard coating is a CrN layer or a CrAlN layer.
2. The titanium alloy shaft part as set forth in claim 1, wherein the thickness of the air supersonic coating is 80-400 μm, and the thickness of the magnetron sputtering hard coating is 5-10 μm.
3. The titanium alloy shaft part as set forth in claim 1 or 2, wherein the thickness of the air supersonic coating is 100-350 μm, and the thickness of the magnetron sputtering hard coating is 6-8 μm.
4. The titanium alloy shaft part as set forth in claim 1, wherein the sum of the outer diameter of the mating rotating part (3), the thickness of the air supersonic coating and the thickness of the magnetron sputtering hard coating is 30-50 mm.
5. The titanium alloy shaft part as set forth in claim 1 or 4, wherein the sum of the outer diameter of the mating rotating part (3), the thickness of the air supersonic coating and the thickness of the magnetron sputtering hard coating is 34-42 mm.
6. The titanium alloy shaft part as set forth in claim 1, wherein the total length of the titanium alloy shaft part is 150 to 450 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020868608.7U CN212223077U (en) | 2020-05-21 | 2020-05-21 | Titanium alloy shaft part |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020868608.7U CN212223077U (en) | 2020-05-21 | 2020-05-21 | Titanium alloy shaft part |
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| CN212223077U true CN212223077U (en) | 2020-12-25 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111411318A (en) * | 2020-05-21 | 2020-07-14 | 北京金轮坤天特种机械有限公司 | Titanium alloy shaft part and preparation method and application thereof |
| CN112877637A (en) * | 2021-01-12 | 2021-06-01 | 兰州理工大学 | Heat-corrosion-resistant composite protective coating and preparation method thereof |
-
2020
- 2020-05-21 CN CN202020868608.7U patent/CN212223077U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111411318A (en) * | 2020-05-21 | 2020-07-14 | 北京金轮坤天特种机械有限公司 | Titanium alloy shaft part and preparation method and application thereof |
| CN112877637A (en) * | 2021-01-12 | 2021-06-01 | 兰州理工大学 | Heat-corrosion-resistant composite protective coating and preparation method thereof |
| CN112877637B (en) * | 2021-01-12 | 2022-02-08 | 兰州理工大学 | Heat-corrosion-resistant composite protective coating and preparation method thereof |
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