CN113714584A - Connecting method and auxiliary tool for titanium-aluminum compound turbine and steel shaft - Google Patents
Connecting method and auxiliary tool for titanium-aluminum compound turbine and steel shaft Download PDFInfo
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- CN113714584A CN113714584A CN202111053049.XA CN202111053049A CN113714584A CN 113714584 A CN113714584 A CN 113714584A CN 202111053049 A CN202111053049 A CN 202111053049A CN 113714584 A CN113714584 A CN 113714584A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/008—Soldering within a furnace
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K3/00—Tools, devices, or special appurtenances for soldering, e.g. brazing, or unsoldering, not specially adapted for particular methods
- B23K3/08—Auxiliary devices therefor
- B23K3/087—Soldering or brazing jigs, fixtures or clamping means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/02—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape
- B23K35/0222—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape for use in soldering, brazing
- B23K35/0244—Powders, particles or spheres; Preforms made therefrom
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
- B23K35/24—Selection of soldering or welding materials proper
- B23K35/30—Selection of soldering or welding materials proper with the principal constituent melting at less than 1550 degrees C
- B23K35/302—Cu as the principal constituent
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/22—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by the composition or nature of the material
- B23K35/24—Selection of soldering or welding materials proper
- B23K35/32—Selection of soldering or welding materials proper with the principal constituent melting at more than 1550 degrees C
- B23K35/325—Ti as the principal constituent
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a method for connecting a titanium-aluminum compound turbine and a steel shaft and an auxiliary tool, which mainly comprise the following steps: step one, carrying out structural design on matching surfaces of a turbine and a steel shaft, designing the matching surfaces into a special-shaped structure interface, and processing the turbine and the steel shaft to be a component to be welded; step two, uniformly mixing a certain proportion of solder alloy powder and titanium-aluminum alloy powder, and hot-pressing the mixture in a die to form a cake blank which is used as an intermediate layer material for later use; and step three, prefabricating the cake blank between the components to be welded, heating the cake blank in a vacuum atmosphere to melt the solder powder in the cake blank but not melt the titanium-aluminum powder, filling gaps among the components by the melt in the heat preservation process, carrying out isothermal solidification on the melt, and simultaneously carrying out chemical reaction on the titanium-aluminum powder and the components on two sides to connect the components into a metallurgical combination. The invention adopts the special-shaped structure design to increase the joint connecting area, decompose the stress state of the joint and improve the strength and stability of the joint of the titanium-aluminum alloy and the stainless steel by the auxiliary transition liquid phase welding method.
Description
Technical Field
The invention belongs to the technical field of welding, relates to a connecting technology of a titanium-aluminum compound turbine, and particularly relates to a high-reliability connecting method and an auxiliary tool for the titanium-aluminum compound turbine and a steel shaft by adopting special-shaped structure welding interface design, powder metallurgy and transition liquid phase diffusion welding.
Background
The titanium-aluminum intermetallic compound material is a light metal material, is applied to tank supercharged engines in China at present, serves as a turbine rotor part, replaces a high-temperature alloy material, and has remarkable structure weight reduction and efficiency improvement effects. The titanium aluminum turbine is proved to remarkably reduce the rotational inertia of a turbine rotor in a supercharger and improve the acceleration responsiveness of an engine.
The titanium-aluminum turbine rotor component relates to the connection of a titanium-aluminum turbine and a stainless steel shaft, and is an important key technology for manufacturing the rotating shaft system. Because the thermal physical property difference between the titanium-aluminum intermetallic compound material and stainless steel is large, K418 high-temperature alloy is selected as a transition body in foreign countries (Japan), and a method of brazing and electron beam welding is adopted, so that the titanium-aluminum turbine is firstly connected with the transition body through brazing, and then the transition body is connected with a stainless steel shaft through electron beam welding. At present, the three-body connection is adopted at home, and the difference is that I-the high-temperature alloy transition body and the titanium-aluminum turbine are connected by an interference method, and II-the high-temperature alloy transition body and the stainless steel shaft are connected by a friction welding method; the performance of the transition body part of the rotating shaft system in the high-temperature service process is proved to be unstable, and the connection reliability of the titanium-aluminum turbine and the rotating shaft thereof is urgently needed to be improved.
There are other related technologies reported in the disclosure, for example, patents CN102343468A and ZL02133239.8 all propose to connect a titanium-aluminum turbocharger rotor and a steel shaft by a pressurized vacuum diffusion welding method, but there are problems in engineering that the steel shaft is large in size (high in height), the process control difficulty is high when the steel shaft is axially pressurized, the coaxiality is difficult to control, the performance fluctuation is large, and the like. In patent CN102259217A, the welding method adopts thin-strip brazing filler metal (the thickness of the brazing filler metal is 0.02-0.2mm), the brazing filler metal is the existing commercial nickel-based brazing filler metal, the coaxiality between a turbine and a steel shaft is difficult to ensure by adopting a pressure brazing technology (the welding pressure is 0.1-20MPa), and the rejection rate is high. Or, multiple metal foils are adopted as intermediate layers, such as Ti foil, V foil and Cu foil, in order to promote the interface reaction between titanium aluminum and stainless steel, but the method for stacking multiple foils has very high requirements on the fit clearance between a titanium aluminum turbine and a steel shaft, and the high requirements on the assembly precision are not beneficial to the high-efficiency production of parts. In other documents, high-strength connection between a sample-grade titanium-aluminum material and steel is realized by a friction welding technology, but titanium-aluminum turbine parts are complex in shape and difficult to clamp, and microcracks of the low-plasticity titanium-aluminum material are more easily caused by the friction welding method, so that the potential danger of part fracture is generated. In addition, it has been reported that a brittle compound layer with a large thickness is formed at the interface between a titanium aluminum material and stainless steel by high-frequency induction brazing and a conventional Ag-Cu-Ti brazing filler metal, and the strength of the corresponding joint is low.
In summary, the above problems are solved by taking into account the low plasticity of the titanium-aluminum material, the large difference in thermophysical properties between the titanium-aluminum material and the stainless steel material, the high requirement on the connection strength of the rotating shaft system, the high production efficiency, and other factors.
Disclosure of Invention
The purpose of the invention is: a method for connecting a titanium-aluminum compound turbine and a steel shaft and an auxiliary tool are provided to solve the problem of reliable connection technology of the titanium-aluminum compound turbine and the steel shaft.
In order to solve the technical problem, the technical scheme of the invention is as follows:
a welding method of a titanium-aluminum compound turbine and a steel shaft comprises the following steps:
step one, carrying out structural design on the matching surface of the processed titanium-aluminum turbine and the stainless steel shaft, and designing the matching surface into a zigzag or trapezoidal or zigzag + trapezoidal alternate interface structural form; compared with the mode of plane butt joint in the prior art, the method utilizes the matching surface special-shaped structure design to be beneficial to increasing the connection area, decomposing the stress state and reducing the adverse effect of centrifugal force on the connection interface.
Processing a connecting interface of the titanium-aluminum turbine and the steel shaft, wherein the gap between the two surfaces to be brazed is 0.01-0.09 mm;
step two, intermediate layer material
The intermediate layer is made of a mixture of titanium-aluminum alloy powder and brazing filler metal powder; the weight percentage of the titanium-aluminum alloy powder is 40-50 percent, and the rest is solder powder;
the solder powder is zirconium-titanium-copper or titanium-zirconium-copper-nickel powder;
the titanium-aluminum alloy powder comprises the components with the atomic percentage of Ti- (40-48) Al;
and step three, placing the turbine and the steel shaft in a mode that the turbine is arranged above the steel shaft and the steel shaft is arranged below the steel shaft, wherein the coaxiality requirement of the turbine and the steel shaft is 0.01-0.02 mm. Compared with the mode of horizontally placing left and right in the prior art, the method effectively guarantees the interface attachment by utilizing the self weight of the titanium-aluminum turbine.
And placing an intermediate layer material between the turbine and the steel shaft, heating in a vacuum furnace, and performing transition liquid phase diffusion welding to melt brazing filler metal powder of the intermediate layer material and perform isothermal solidification in the heat preservation process.
The transition liquid phase diffusion welding is to fill an interface gap with liquid brazing filler metal, and the brazing filler metal is solidified isothermally in the heat preservation process; in the process, the titanium-aluminum particles and the liquid brazing filler metal are subjected to chemical reaction, so that the welding strength is ensured; the parameters are set such that the brazing filler metal powder of the interlayer material melts and the titanium aluminium alloy powder is present in the form of particles.
The powder particle size of the interlayer material is 100-150 meshes.
The interlayer material may be prepared in one of the following ways:
uniformly mixing titanium-aluminum alloy powder and brazing filler metal powder by using acetone to prepare paste, and coating the paste between a turbine and a steel shaft;
uniformly mixing titanium-aluminum alloy powder and brazing filler metal powder, and performing hot pressing in a die to prepare a cake blank; placing the cake blank between a turbine and a steel shaft; the thickness of the cake blank is 20-50 μm.
Setting process parameters in the third step: setting the heating temperature of the vacuum furnace according to the melting point of the brazing filler metal powder; vacuum degree of 1X 10-3Pa～7×10-3Pa; the heating temperature is 20-40 ℃ higher than the melting point of the brazing filler metal powder; the heat preservation time is 90-150 min; and cooling to room temperature along with the furnace after welding.
In the third step, the brazing filler metal powder is titanium-zirconium-copper-nickel alloy powder, the heating temperature is 950 ℃ and the heat preservation is carried out for 100 min.
Preferably, chamfering treatment is carried out on each bending part contained in the matching surface of the turbine and the steel shaft by 30-45 degrees; the roughness of the matching surface of the turbine and the steel shaft is 1.6-0.8 μm.
If the matching surface of the turbine and the steel shaft is zigzag, the height is 3-4 mm; the width is 2-3 mm; if the trapezoid shape is adopted, the height is 3-4 mm; the width of the top part is 2-2.5 mm.
On the other hand, an auxiliary tool for connecting a titanium-aluminum compound turbine and a steel shaft is provided, the auxiliary tool is a triangular support with double seats and double holes coaxial and concentric, a turbine blade back is positioned in an upper end seat hole, and the tail end of the steel shaft is positioned in a base hole; the upper end seat hole and the base seat hole are coaxial and concentric, and the upper end seat and the periphery of the base seat are vertically connected through three supporting rods and are kept parallel. The auxiliary tool is made of stainless steel or high-temperature alloy.
And isolation paper is also filled between the turbine blade back and the upper end seat hole, and the isolation paper is made of mica paper.
The method of the invention is suitable for: homogeneous welding between titanium aluminum compounds; heterogeneous welding between titanium aluminum compounds; the connection between the titanium aluminide turbine and the stainless steel shaft.
The invention has the beneficial effects that:
the method removes the high-temperature alloy transition body part and the corresponding interference connection process step, thereby not only reducing the material waste, reducing the process quantity and reducing the structural weight of the whole shafting; the connection strength level and the strength stability of the titanium-aluminum material and the steel shaft at high temperature are improved, the strength of the titanium-aluminum material and the steel shaft at 500 ℃ is 400-430MPa, and the high-cycle fatigue strength of the titanium-aluminum material and the steel shaft at 500 ℃ reaches 240 MPa. Compared with interference connection, the method for powder metallurgy and transition liquid phase diffusion welding changes the physical bonding state of the material connection interface into the interface metallurgical bonding state; through the structural design of the special-shaped interface, the complex stress states such as high temperature, high-speed centrifugation, vibration and the like are decomposed, and the stability and the reliability of the shafting connecting part are improved.
The invention provides a joint microstructure form for improving the stress state of a plane connecting part in order to solve the problem of low connecting strength of a brittle titanium-aluminum material, and the shear stress state of a rotating shafting connecting joint is changed into a shearing and tension-shearing composite stress state, so that the damage risk of parts is reduced, and the fracture load is improved; meanwhile, a method for filling the zigzag gaps by using a low-melting solder liquid phase is provided, so that the welding rate of the parts is ensured.
Drawings
In order to more clearly illustrate the technical solution of the present invention, the drawings used in the embodiment of the present invention will be briefly explained. It is obvious that the drawings described below are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be obtained from these drawings without inventive effort.
FIG. 1 is a schematic view of a connection structure of a turbine and a steel shaft;
FIG. 2 is a schematic structural diagram of a matching surface between a turbine and a steel shaft;
FIG. 3 is a schematic view of the auxiliary tool in use;
FIG. 4 is a schematic view of the position of the mica paper in FIG. 3;
in the figure, 1-turbine, 2-steel shaft, 3-upper end seat, 4-base, 5-turbine blade back and 6-mica paper.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features of various aspects of embodiments of the invention will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without these specific details. The following description of the embodiments is merely intended to better understand the present invention by illustrating examples thereof. The present invention is not limited to any particular arrangement or method provided below, but rather covers all product structures, any modifications, alterations, etc. of the method covered without departing from the spirit of the invention.
In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
Example 1
Carrying out matching surface structure design on the processed titanium-aluminum turbine and the stainless steel shaft, and designing the titanium-aluminum turbine and the stainless steel shaft into a zigzag interface; chamfering the sawteeth by 30 degrees; the sawtooth height H is 3.5 mm; the width W was 2.5 mm. The mating surface clearance is 0.03 mm. Designing the alloy powder to be Zr-25Ti-25Cu and the titanium-aluminum powder to be Ti- (45-46) Al (atomic percentage); the proportion of the two is 40% + 60%; the granularity of the powder is 120 meshes; the Zr-25Ti-25Cu alloy powder and the titanium-aluminum powder are evenly mixed and hot pressed in a mould to prepare an intermediate layer material with the thickness of 36 microns. And (3) prefabricating the intermediate layer material to a zigzag interface of the titanium-aluminum turbine I and the stainless steel shaft II. The turbine and the steel shaft are placed in a mode that the turbine is arranged above the steel shaft and the steel shaft is arranged below the steel shaft. And an auxiliary tool is adopted, the turbine blade back is positioned in the upper end seat hole, and the tail end of the steel shaft is positioned in the base hole. Heating in a vacuum furnace to melt the intermediate layer material, and filling the melt into gaps of the sawtooth-shaped interface in the heat preservation process. Heating at 900 deg.C, and maintaining for 100 min. The strength of the obtained titanium-aluminum and stainless steel joint reaches 410MPa at 500 ℃, and the high cycle fatigue strength of the joint reaches 235MPa at 500 ℃. The coaxiality of the turbine and the steel shaft is 0.01 mm.
Example 2
Carrying out matching surface structure design on the processed titanium-aluminum turbine and the stainless steel shaft, and designing the titanium-aluminum turbine and the stainless steel shaft into a zigzag + trapezoidal interface; chamfering the sawteeth by 40 degrees; the zigzag height H1 is 3.0 mm; width W1 is 2.2 mm; the height H2 of the trapezoid is 3.5 mm; width W2 is 2.4 mm; the spacing W3 between the two was 2.0 mm. The mating surface clearance is 0.06 mm. Titanium-based solder powder Ti-37.5Zr-15Cu-9Ni and titanium-aluminum alloy powder are prepared into Ti-47.2Al (atomic percentage); the proportion of the two is 50% + 50%; the two are uniformly mixed and hot-pressed in a mould to form an intermediate layer material with the thickness of 42 microns; and prefabricating the intermediate layer material to the special-shaped interface of the titanium-aluminum turbine I and the stainless steel shaft II. The turbine and the steel shaft are placed in a mode that the turbine is arranged above the steel shaft and the steel shaft is arranged below the steel shaft. And an auxiliary tool is adopted, the turbine blade back is positioned in the upper end seat hole, and the tail end of the steel shaft is positioned in the base hole. And (4) performing transition liquid phase diffusion welding in a vacuum furnace to melt the intermediate layer material at the interface part and connect the interfaces at the two sides. Heating to 895 deg.C, and maintaining for 115 min. The strength of the obtained titanium-aluminum and stainless steel joint at 500 ℃ is 405MPa, and the high cycle fatigue strength of the joint at 500 ℃ is 218 MPa. The turbine and the steel shaft are coaxial with each other at 0.012 mm.
Example 3
Carrying out matching surface structure design on the processed titanium-aluminum turbine and the stainless steel shaft, and designing the titanium-aluminum turbine and the stainless steel shaft into a zigzag + trapezoidal interface; chamfering the sawteeth by 45 degrees; the zigzag height H1 is 3.5 mm; width W1 is 2.5 mm; the height H2 of the trapezoid is 3.8 mm; width W2 is 2.6 mm; the spacing W3 between the two was 2.2 mm. The mating surface clearance is 0.09 mm. Titanium-based solder powder Ti-9.5Zr-22Cu-8Ni and titanium-aluminum alloy powder are prepared into Ti-45.7Al (atomic percentage); the proportion of the two is 47% + 53%; mixing the two materials uniformly, and hot-pressing in a mould to prepare an intermediate layer material with the thickness of 38 micrometers; and (3) prefabricating the interlayer material to the special-shaped interface of the titanium-aluminum turbine I and the stainless steel shaft II, and placing the turbine and the steel shaft in a mode that the turbine is arranged above and the steel shaft is arranged below. And an auxiliary tool is adopted, the turbine blade back is positioned in the upper end seat hole, and the tail end of the steel shaft is positioned in the base hole. And (4) performing transition liquid phase diffusion welding in a vacuum furnace to melt the intermediate layer material at the interface part and connect the interfaces at the two sides. Heating to 920 deg.C, and maintaining for 110 min. The strength of the obtained titanium-aluminum and stainless steel joint at 500 ℃ is 420MPa, and the high cycle fatigue strength of the joint at 500 ℃ is 242 MPa. The turbine is 0.018mm coaxial to the steel shaft.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (10)
1. A titanium aluminide turbine and steel shaft connecting method and auxiliary tool are characterized in that: the connecting method comprises the following steps:
step one, carrying out matching surface structure design on the processed titanium-aluminum turbine and the stainless steel shaft, and designing the matching surface structure into a zigzag or trapezoidal or zigzag + trapezoidal alternate interface structure form;
processing a connecting interface of the titanium-aluminum turbine and the steel shaft, wherein the gap between the two surfaces to be brazed is 0.01-0.09 mm;
step two, intermediate layer material
The intermediate layer is made of a mixture of titanium-aluminum alloy powder and brazing filler metal powder; the weight percentage of the titanium-aluminum alloy powder is 40-50 percent, and the rest is solder powder; the titanium-aluminum alloy powder comprises the components with the atomic percentage of Ti- (40-48) Al;
the solder powder is zirconium-titanium-copper or titanium-zirconium-copper-nickel powder;
step three, the turbine and the steel shaft are placed in a matching mode in which the turbine is arranged above the steel shaft and the steel shaft is arranged below the steel shaft, and the coaxiality requirement of the turbine and the steel shaft is 0.01-0.02 mm:
and placing an intermediate layer material between the turbine and the steel shaft, heating in a vacuum furnace, and performing transition liquid phase diffusion welding to melt brazing filler metal powder in the intermediate layer material and perform isothermal solidification in the heat preservation process.
2. The connecting method according to claim 1, characterized in that: the granularity of the interlayer material is 100-150 meshes.
3. The connecting method according to claim 1, characterized in that: the interlayer material may be prepared in one of the following ways:
uniformly mixing titanium-aluminum alloy powder and brazing filler metal powder by using acetone to prepare paste, and coating the paste between a turbine and a steel shaft;
uniformly mixing titanium-aluminum alloy powder and brazing filler metal powder, and performing hot pressing in a die to prepare a cake blank; the biscuit was placed between the turbine and the steel shaft.
4. The connecting method according to claim 3, characterized in that: the thickness of the cake blank is 20-50 μm.
5. The connecting method according to claim 1, characterized in that: setting process parameters in the third step: setting the heating temperature of the vacuum furnace according to the melting point of the brazing filler metal powder; vacuum degree of 1X 10-3Pa～7×10-3Pa; the heating temperature is 20-40 ℃ higher than the melting point of the brazing filler metal powder; the heat preservation time is 90-150 min; and cooling to room temperature along with the furnace after welding.
6. The connecting method according to claim 1, characterized in that: and each bending part contained in the matching surface is chamfered at an angle of 30-45 degrees.
7. The connecting method according to claim 1, characterized in that: the roughness of the matching surface of the turbine and the steel shaft is 1.6-0.8 μm.
8. The connecting method according to claim 1, characterized in that: matching surfaces in step one
If the saw-tooth shape is zigzag, the height is 3.0-4.0 mm; the width is 2.0-3.0 mm;
if the trapezoid shape is adopted, the height is 3.0-4.0 mm; the width of the top part is 2.0-2.5 mm.
9. A connecting method and an auxiliary tool for the titanium-aluminum compound turbine and the steel shaft of claim 1 are characterized in that: the auxiliary tool is a triangular support with double seats and double holes which are coaxial and concentric, the turbine blade back is positioned in the upper end seat hole, and the tail end of the steel shaft is positioned in the base hole; the upper end seat hole and the base seat hole are coaxial and concentric.
10. The auxiliary tool according to claim 9, wherein: isolation paper is further padded between the turbine blade back and the upper end seat hole, and the isolation paper is made of mica paper; the auxiliary tool is made of stainless steel or high-temperature alloy.
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102343468A (en) * | 2011-02-15 | 2012-02-08 | 洛阳双瑞精铸钛业有限公司 | Welding method of rotor and steel shaft of titanium-aluminum alloy turbocharger |
| CN102825354A (en) * | 2012-09-20 | 2012-12-19 | 北京科技大学 | Composite-diffusion brazing method of Cf/SiC ceramic based composite materials and titanium alloy |
| CN103302371A (en) * | 2013-06-26 | 2013-09-18 | 哈尔滨工业大学 | Diffusion bonding method of hard alloy and metal |
| CN104625389A (en) * | 2014-12-22 | 2015-05-20 | 有研亿金新材料有限公司 | Welding method of aluminum alloy sputtering target material for integrated circuit package material |
| JP2016167561A (en) * | 2015-03-10 | 2016-09-15 | 株式会社タムラ製作所 | Method for bonding electronic component, and solder composition and pretreatment agent used in the method |
| CN110666396A (en) * | 2019-10-21 | 2020-01-10 | 中国航发北京航空材料研究院 | Strip-shaped brazing material for titanium alloy medium-low temperature brazing, preparation method and brazing method |
| CN212599921U (en) * | 2020-06-06 | 2021-02-26 | 浙江金象科技有限公司 | End socket and support welding auxiliary device |
| CN213351320U (en) * | 2020-06-30 | 2021-06-04 | 合肥和安机械制造有限公司 | Welding device for flange air inlet pipe |
-
2021
- 2021-09-08 CN CN202111053049.XA patent/CN113714584B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102343468A (en) * | 2011-02-15 | 2012-02-08 | 洛阳双瑞精铸钛业有限公司 | Welding method of rotor and steel shaft of titanium-aluminum alloy turbocharger |
| CN102825354A (en) * | 2012-09-20 | 2012-12-19 | 北京科技大学 | Composite-diffusion brazing method of Cf/SiC ceramic based composite materials and titanium alloy |
| CN103302371A (en) * | 2013-06-26 | 2013-09-18 | 哈尔滨工业大学 | Diffusion bonding method of hard alloy and metal |
| CN104625389A (en) * | 2014-12-22 | 2015-05-20 | 有研亿金新材料有限公司 | Welding method of aluminum alloy sputtering target material for integrated circuit package material |
| JP2016167561A (en) * | 2015-03-10 | 2016-09-15 | 株式会社タムラ製作所 | Method for bonding electronic component, and solder composition and pretreatment agent used in the method |
| CN110666396A (en) * | 2019-10-21 | 2020-01-10 | 中国航发北京航空材料研究院 | Strip-shaped brazing material for titanium alloy medium-low temperature brazing, preparation method and brazing method |
| CN212599921U (en) * | 2020-06-06 | 2021-02-26 | 浙江金象科技有限公司 | End socket and support welding auxiliary device |
| CN213351320U (en) * | 2020-06-30 | 2021-06-04 | 合肥和安机械制造有限公司 | Welding device for flange air inlet pipe |
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