CN114951659B - Machining method of complex titanium alloy component with tungsten carbide coating - Google Patents
Machining method of complex titanium alloy component with tungsten carbide coating Download PDFInfo
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
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- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/10—Sintering only
- B22F3/1003—Use of special medium during sintering, e.g. sintering aid
- B22F3/1007—Atmosphere
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/009—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine components other than turbine blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
- B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/08—Coating starting from inorganic powder by application of heat or pressure and heat
- C23C24/082—Coating starting from inorganic powder by application of heat or pressure and heat without intermediate formation of a liquid in the layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/241—Chemical after-treatment on the surface
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/241—Chemical after-treatment on the surface
- B22F2003/242—Coating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
- B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
- B22F3/24—After-treatment of workpieces or articles
- B22F2003/247—Removing material: carving, cleaning, grinding, hobbing, honing, lapping, polishing, milling, shaving, skiving, turning the surface
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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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/25—Process efficiency
Abstract
The invention belongs to the field of titanium alloy composite material processing, and particularly relates to a processing method of a complex titanium alloy member with a tungsten carbide coating. According to the processing method of the complex titanium alloy component with the tungsten carbide coating, the prefabricated titanium alloy primary blank is put into the sheath of the adaptive structure and the tungsten carbide powder is added for hot isostatic pressing treatment, so that the uniform coating of the tungsten carbide material on the surface of the titanium alloy component is realized, the densification treatment of the vacuum sintered titanium alloy is realized, the comprehensive performance of the titanium alloy component is improved, and the titanium alloy component with low density, high strength, high hardness, high wear resistance, high density and long service life can be obtained.
Description
Technical Field
The invention belongs to the field of titanium alloy composite material processing, and particularly relates to a processing method of a complex titanium alloy member with a tungsten carbide coating.
Background
Titanium alloy is widely used in the fields of aerospace, ship manufacturing and the like as a material with high specific strength, small deformation coefficient, high heat resistance and good low-temperature toughness. However, the problems of refractory smelting, difficult machining and the like are also caused by the characteristics of high melting point and high strength, and further, the difficult machining of complex titanium alloy components is caused. At present, a casting or vacuum melting method is generally adopted for the forming processing of the titanium alloy complex component, however, the obtained finished product has poor compactness, internal defects of the product are difficult to avoid, and the quality of the product is difficult to ensure.
In addition, for titanium alloy components that are required to frequently withstand large loads, the hardness of the titanium alloy component product alone is often insufficient to meet the conditions of use. Many researchers have proposed methods of coating the surface of titanium alloy components with a tungsten carbide coating to enhance their hardness properties. At present, more coating methods mainly comprise laser cladding, plasma spraying and more advanced supersonic flame spraying methods, but the tungsten carbide coating obtained by the process methods is thinner, and the defect of limited service life of the product still exists.
In view of the above, a processing method of a complex titanium alloy component with a tungsten carbide coating, which can effectively ensure the quality and the service performance of the product, is developed, and has positive significance for the application and popularization of the titanium alloy component.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to provide a processing method of a complex titanium alloy member with a tungsten carbide coating, so as to solve the problem of non-ideal product quality of the complex titanium alloy member with the tungsten carbide coating in the prior art;
the second technical problem to be solved by the invention is to provide a complex titanium alloy component with a tungsten carbide coating, which has good product quality and service performance.
In order to solve the technical problems, the processing method of the complex titanium alloy component with the tungsten carbide coating comprises the following steps:
(1) According to the selected composition of the titanium alloy component, raw material powder is added into a rigid die with the inner layer shape being the same as the shape of the titanium alloy component, vacuum high-temperature sintering treatment is carried out, and demoulding is carried out to obtain a titanium alloy primary blank for later use;
(2) Placing the titanium alloy primary blank into a sheath for hot isostatic pressing, filling tungsten carbide powder, and performing compaction, degassing and seal welding for later use;
(3) Carrying out hot isostatic pressing treatment on the titanium alloy component and the sheath together to obtain a titanium alloy component with a silicon carbide coating of the sheath;
(4) And carrying out chemical milling treatment on the titanium alloy component with the sheath to obtain the required titanium alloy component with the tungsten carbide coating.
Specifically, in the step (1), the size of the titanium alloy primary blank is reduced in an equal proportion to the size of the selected titanium alloy member.
Specifically, in the step (1), the temperature of the vacuum high-temperature sintering step is 1000-1300 ℃, and the vacuum degree in the furnace is lower than 10 -3 Pa。
Specifically, in the step (2), the thickness of the tungsten carbide coating is 0.1-5mm.
According to one embodiment of the invention, the tungsten carbide powder is prepared by ball milling broken tungsten carbide particles by a ball mill, deformation energy and surface energy of the tungsten carbide powder after ball milling are increased, bonding capacity with titanium alloy in a hot isostatic pressing process is enhanced, and melting point reduction caused by ball milling is also beneficial to metallurgical bonding capacity among powder particles.
Specifically, in the step (2), the jacket includes a first jacket component and a second jacket component that can be spliced; the spliced sheath has a structure in which the inner space is consistent with the size and shape of the titanium alloy member with the tungsten carbide coating.
Specifically, the sheath is provided with holes connected with the powder inlet pipe, and can be used for adding the tungsten carbide powder and degassing.
According to one embodiment of the invention, wherein the rigid mould is made of alloy tool steel and the sheath is made of low carbon steel.
Specifically, the processing method of the complex titanium alloy member with the tungsten carbide coating layer specifically comprises the following steps:
the sheath is vertically placed on a vibrating table to be filled with powder and compacted at the same time;
heating, degassing and sealing welding;
and (3) converting the sealed and welded sheath from the original vertical placement to the horizontal placement, and performing multi-point impact on a multi-point impact device to uniformly distribute the powder around the component.
According to one embodiment of the invention, the method for placing the titanium alloy blank into the sheath is as follows: and accurately placing the titanium alloy primary blank into a first sheath assembly according to the target shape, placing a second sheath assembly corresponding to the target shape, and finally connecting the two sheaths through argon arc welding.
According to one embodiment of the invention, the multipoint impact device is composed of a fixed base, a bracket and air pressure hammers, and the bracket, the number of the air pressure hammers and the impact direction of the air pressure hammers are properly selected according to the shape of the sheath so as to ensure that powder is uniformly distributed between the titanium alloy primary blank and the sheath.
Specifically, in the step (3), the step of hot isostatic pressing is as follows: under the inert atmosphere, the heating temperature is 700-900 ℃, the pressure is 100-140MPa, and the hot isostatic pressing treatment time is 2-5h.
Specifically, in the step (4), in the chemical milling treatment step, the treatment medium is sulfuric acid with concentration of 10-15%, the working current is not more than 200A, and the working voltage is not more than 5V.
The invention also discloses a complex titanium alloy component with a tungsten carbide coating prepared by the method.
According to the processing method of the complex titanium alloy component with the tungsten carbide coating, the prefabricated titanium alloy primary blank is put into the sheath of the adaptive structure and the tungsten carbide powder is added for hot isostatic pressing treatment, so that the uniform coating of the tungsten carbide material on the surface of the titanium alloy component is realized, the densification treatment of the vacuum sintered titanium alloy is realized, the comprehensive performance of the titanium alloy component is improved, and the titanium alloy component with low density, high strength, high hardness, high wear resistance, high density and long service life can be obtained.
The processing method of the complex titanium alloy component with the tungsten carbide coating ensures that the tungsten carbide is uniformly coated on the surface of the titanium alloy through matching with the step of multipoint compaction treatment in the step of hot isostatic pressing treatment, thereby well improving the uniformity of the coating, meeting the requirement of uniform performance of the component in all directions, realizing quantitative coating of the tungsten carbide on the surface of the titanium alloy, not only overcoming the problem of poor service life of the traditional coating due to over-thinness, but also breaking through the limitation that the thickness of the coating cannot be ensured in the traditional coating mode, being capable of processing complex titanium alloy components with tungsten carbide coatings with different thickness requirements,
drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of the processing method of the present invention;
FIG. 2 is a block diagram of a workpiece according to one embodiment of the invention;
fig. 3 is a three-view of the workpiece of fig. 2, with the first capsule assembly 1 in a vertical position, wherein (a) front view, (b) side view, and (c) top view;
fig. 4 is a three views of the workpiece of fig. 2, with the second jacket assembly 2 vertically disposed, wherein: a front view, (b) a side view, and (c) a top view;
FIG. 5 is a schematic view of the jacket after the whole body of the titanium alloy preform is assembled, wherein (1) is a schematic view of the jacket being vertically placed and (2) is a schematic view of the jacket being horizontally placed, wherein the 1-first jacket assembly, the 2-second jacket assembly, the 3-jacket joint, the 4-titanium alloy preform;
fig. 6 is a schematic structural view of a multipoint impact device according to an embodiment of the present invention, wherein the device comprises a 11-fixed base, a 12-pneumatic hammer, and a 13-bracket.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention.
Example 1
The method for manufacturing the complex titanium alloy component with the silicon carbide coating can well solve the problem of difficult price, meets the requirements of high strength and high wear resistance, and takes the aircraft engine turbine with the diameter of 300mm and the width of 80mm as shown in fig. 2 as an example for describing the processing method of the invention.
As shown in the flowchart of fig. 1, the processing method of the complex titanium alloy member with the tungsten carbide coating in this embodiment includes the following steps:
(1) According to the selected composition of the titanium alloy component, raw material powder TA15 (Ti-6 Al-2Zr-1 Mo-1V) is added into a rigid die with the inner layer shape the same as the shape of the titanium alloy component, vacuum high-temperature sintering treatment is carried out, and demoulding is carried out to obtain a titanium alloy primary blank for later use;
the rigid die is made of alloy tool steel with the internal shape being the same as the shape of a required finished product, the diameter being 298mm and the width being 78mm, and the size of each direction being reduced along with the diameter, the width and the like in proportion to the target shape;
the vacuum high-temperature sintering is performed at 1200 ℃, and the vacuum degree in the furnace is lower than 10 -3 Pa。
(2) Placing the titanium alloy primary blank into a sheath for hot isostatic pressing, filling a sufficient amount of tungsten carbide powder (taking the sheath as a standard for filling up the sheath), and compacting, degassing and sealing for later use;
the sheath is a low-carbon steel sheath with a split structure of a first sheath component 1 and a second sheath component 2, wherein, as shown in the structure of figures 3-4, after the two parts of the first sheath component 1 and the second sheath component 2 are integrally split, the structure and the size of the formed internal space are the same as the shape and the size of a required finished product, and the external size is slightly larger than the shape of the required finished product. The first sleeve component 1 and the second sleeve component 2 are spliced to form a hexagonal prism structure, wherein the second sleeve component 2 is different from the first sleeve component 1 in that a cylinder with the same size and shape as the central hole of the target component is arranged in the center of the second sleeve component 2, as shown in fig. 3 and 4, and the rectangle in the side view and the top view is the section of the part of the cylinder which is not covered by the sleeve. As shown in fig. 3-4, the sheath should have a hole for connecting the powder discharging tube for powder charging and degassing.
With the structure shown in fig. 5, the method for placing the turbine blank 4 of the engine into the sheath is as follows: and accurately placing the engine turbine primary blank 5 into the first sleeve component 1 according to the target shape, placing the second sleeve component 2 corresponding to the first sleeve component 1 according to the target shape, and finally connecting the first sleeve component and the second sleeve component through argon arc welding, wherein the sleeve joint 3 formed by the first sleeve component and the second sleeve component is as shown in the figure.
In this embodiment, the tungsten carbide powder is prepared by ball milling broken tungsten carbide particles by a ball mill for 90 hours, so that the particle size of the tungsten carbide powder is reduced to below 0.5 μm, the deformation energy and the surface energy of the tungsten carbide powder after ball milling are increased, the bonding capability with titanium alloy in the hot isostatic pressing process is enhanced, the melting point reduction caused by ball milling is also beneficial to the metallurgical bonding capability among powder particles, and the falling or cracking of a tungsten carbide coating is avoided.
In this embodiment, after the turbine preform of the engine is loaded into the jacket, the tungsten carbide powder should be loaded into the jacket by a powder loading device, and the powder loading process should be performed simultaneously with the vibration process on the vibration table, so that the powder is fully and uniformly vibrated around the component, the frequency of the vibration table is set to 800Hz, the vibration time is 1h, and the placement mode of the jacket during the vibration process on the vibration table should be in the vertical direction as shown in fig. 5. And after the vibration operation of the vibration table is finished, sending the sheath into heating-degassing-sealing welding integrated equipment to perform heating-degassing-sealing welding integrated treatment, namely, performing hydraulic clamping on the powder discharging pipe after heating and degassing for 30min in a vacuum degassing bin.
After the heating-degassing-sealing integrated treatment, the sheath is placed on a multipoint impact device for multipoint impact for 2 hours, the placing direction is horizontal as shown in fig. 5, and uneven distribution of powder in the vertical direction generated by vibration of a vibration table is eliminated, so that the powder can be uniformly distributed between the titanium alloy primary blank and the sheath in all directions.
As shown in fig. 6, the multipoint impact device should be composed of a fixed base 11, a bracket 13 and an air pressure hammer 12, and is a device for uniformly impacting a sheath in all directions according to the shape of the sheath, and according to the hexagonal sheath shown in fig. 3, six brackets should be installed on the multipoint impact device, six pneumatic hammers are respectively installed on the brackets, the striking period of the pneumatic hammers is set to 50 times/min, the impact force is 20N, and the six pneumatic hammers are connected by using relay pipes and installed at the same height.
(3) Carrying out hot isostatic pressing treatment on the titanium alloy component and the sheath together to obtain a titanium alloy component with a silicon carbide coating of the sheath; the hot isostatic pressing treatment is as follows: under argon atmosphere, the heating temperature is 800 ℃, the pressure is 120MPa, and the hot isostatic pressing treatment time is 3h.
(4) And carrying out chemical milling treatment on the titanium alloy component with the sheath, wherein the chemical milling treatment medium is sulfuric acid with the concentration of 12%, the working current is 160A, and the working voltage is 4V, so that the aircraft engine turbine with the tungsten carbide coating is obtained.
Example 2
The method for processing a complex titanium alloy member with a tungsten carbide coating according to this embodiment is the same as that of embodiment 1, and the structure of the turbine of the aircraft engine is the same as that of embodiment 1, except that in the step (3), the hot isostatic pressing treatment is as follows: under argon atmosphere, the heating temperature is 700 ℃, the pressure is 140MPa, and the hot isostatic pressing treatment time is 5h.
Example 3
The method for processing a complex titanium alloy member with a tungsten carbide coating according to this embodiment is the same as that of embodiment 1, and the structure of the turbine of the aircraft engine is the same as that of embodiment 1, except that in the step (3), the hot isostatic pressing treatment is as follows: under argon atmosphere, the heating temperature is 900 ℃, the pressure is 100MPa, and the hot isostatic pressing treatment time is 2h.
Comparative example 1
According to the composition of the selected titanium alloy component, raw material powder TA15 (Ti-6 Al-2Zr-1 Mo-1V) is added into a rigid die with the same shape as the titanium alloy component in the inner layer, hot isostatic pressing treatment is carried out, a sheath is removed, and a titanium alloy primary blank is obtained for standby, wherein the hot isostatic pressing treatment is as follows: under argon atmosphere, the heating temperature is 800 ℃, the pressure is 120MPa, and the hot isostatic pressing treatment time is 3h.
And coating a tungsten carbide coating with the thickness of 1mm on the surface of the titanium alloy primary blank by using a laser cladding method.
Comparative example 2
According to the selected composition of the titanium alloy component, raw material powder TA15 (Ti-6 Al-2Zr-1 Mo-1V) is added into a rigid die with the same shape as the titanium alloy component in the inner layer, vacuum high-temperature sintering treatment is carried out, and demoulding is carried out to obtain a titanium alloy primary blank for later use.
And coating a tungsten carbide coating with the thickness of 1mm on the surface of the titanium alloy primary blank by using a laser cladding method.
Experimental example
The tensile strength, hardness, abrasion resistance and other properties of the constructions prepared and constructed in examples 1-3 and comparative examples 1-2 were tested as follows:
tensile strength: taking a part of components without tungsten carbide in the inside as a sample to test in a uniaxial tensile testing machine;
hardness: measuring the surface hardness of the component by using a Vickers hardness tester;
abrasion resistance test: the surface wear resistance of the component is tested by adopting a pin-disc friction wear testing machine, 180-mesh alumina sand paper is adopted as an abrasive, no lubricant is added, the load is 4.9N, and the wear length is 120m.
The test results are shown in table 1 below.
Table 1 results of performance testing of the components
| Index (I) | Example 1 | Example 2 | Example 3 | Comparative example 1 | Comparative example 2 |
| Tensile strength (MPa) | 913 | 882 | 857 | 910 | 713 |
| Hardness (HV) | 1310 | 1330 | 1270 | 630 | 630 |
| Wear Rate (%) | 3.9 | 3.5 | 4.7 | 9 | 9 |
Therefore, the processing method of the complex titanium alloy component with the tungsten carbide coating realizes the uniform coating of the tungsten carbide material on the surface of the titanium alloy component, realizes the densification treatment of the vacuum sintered titanium alloy, and improves the comprehensive performance of the titanium alloy component.
The foregoing has outlined rather broadly the more detailed description of embodiments of the invention, wherein the principles and embodiments of the invention are explained in detail using specific examples, the above examples being provided solely to facilitate the understanding of the method and core concepts of the invention; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present invention, the present description should not be construed as limiting the present invention in view of the above.
Claims (6)
1. A method of processing a complex titanium alloy component having a tungsten carbide coating, comprising the steps of:
(1) According to the selected composition of the titanium alloy component, raw material powder is added into a rigid die with the inner layer shape being the same as the shape of the titanium alloy component, vacuum high-temperature sintering treatment is carried out, and demoulding is carried out to obtain a titanium alloy primary blank for later use;
(2) Placing the titanium alloy primary blank into a sheath for hot isostatic pressing, filling tungsten carbide powder, and performing compaction, degassing and seal welding for later use;
(3) Carrying out hot isostatic pressing treatment on the titanium alloy component and the sheath together to obtain a titanium alloy component with a silicon carbide coating of the sheath;
(4) Carrying out chemical milling treatment on the titanium alloy component with the sheath to obtain the titanium alloy component with the tungsten carbide coating;
wherein, the step (2) specifically comprises:
the sheath is vertically placed on a vibrating table to be filled with powder and compacted at the same time;
heating, degassing and sealing welding;
the sealed and welded sheath is converted into a horizontal one, and multipoint impact is carried out, so that the powder is uniformly distributed around the component;
in the step (3), the hot isostatic pressing treatment step is as follows: heating at 700-900 deg.c and 100-140MPa in inert atmosphere for 2-5 hr;
in the step (1), the size of the titanium alloy primary blank is reduced in equal proportion in all directions relative to the size of the selected titanium alloy member;
in the step (2), the thickness of the tungsten carbide coating is 0.1-5mm.
2. The method for producing a complex titanium alloy member having a tungsten carbide coating according to claim 1, wherein in said step (1), the temperature of said vacuum high temperature sintering step is 1000 to 1300 ℃, and the degree of vacuum in the furnace is less than 10 -3 Pa。
3. The method of working a complex titanium alloy component with tungsten carbide coating according to claim 1 or 2, wherein in step (2), the jacket comprises a first jacket assembly (1) and a second jacket assembly (2) which can be joined together; the spliced sheath has a structure in which the inner space is consistent with the size and shape of the titanium alloy member with the tungsten carbide coating.
4. The method of claim 1, wherein the jacket is provided with holes for connection to a powder feed tube.
5. The method according to claim 1 or 2, wherein in the step (4), the treatment medium is sulfuric acid with concentration of 10-15% in the chemical milling treatment step, the working current is not more than 200A, and the working voltage is not more than 5V.
6. A complex titanium alloy component with tungsten carbide coating produced by the method of any one of claims 1-5.
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| JPS52151608A (en) * | 1976-06-14 | 1977-12-16 | Hitachi Metals Ltd | Process for production of titaniummnitrideecontaining superhard alloy |
| JP2001087805A (en) * | 1999-09-21 | 2001-04-03 | Hitachi Metals Ltd | Composite sleeve made of sintered hard alloy |
| CN101954481B (en) * | 2010-07-07 | 2012-08-08 | 航天材料及工艺研究所 | Titanium alloy rotor near-net manufacturing method |
| ITCO20110061A1 (en) * | 2011-12-12 | 2013-06-13 | Nuovo Pignone Spa | METHOD AND ANTI-WEAR MATERIAL FUNCTIONALLY GRADUATED |
| CN106735229B (en) * | 2017-01-06 | 2018-10-09 | 昆山中士设备工业有限公司 | A kind of screw rod and preparation method thereof |
| CN108194113A (en) * | 2017-12-12 | 2018-06-22 | 昆山中士设备工业有限公司 | A kind of hydraulic prop for mine and its manufacturing method |
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