CN114951477A - Forming method of high-temperature alloy honeycomb sandwich structure - Google Patents
Forming method of high-temperature alloy honeycomb sandwich structure Download PDFInfo
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- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
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- B21D47/00—Making rigid structural elements or units, e.g. honeycomb structures
- B21D47/04—Making rigid structural elements or units, e.g. honeycomb structures composite sheet metal profiles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
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Abstract
The invention provides a method for forming a high-temperature alloy honeycomb sandwich structure, which comprises the following steps: step S1, forming a high-temperature alloy honeycomb core, and connecting a plurality of layers of high-temperature alloy corrugated plates made of high-temperature alloy foils to form the high-temperature alloy honeycomb core; step S2, the high-temperature alloy skin/skeleton is formed by electric pulse bending, and the high-temperature alloy skin and the high-temperature alloy skeleton are formed by pressing through a multi-point digital mould; and step S3, performing self-resistance heating diffusion brazing on the high-temperature alloy honeycomb sandwich structure, and forming the high-temperature alloy honeycomb sandwich structure by the high-temperature alloy framework, the high-temperature alloy honeycomb core and the high-temperature alloy skin through diffusion brazing. The invention combines the rapid electric pulse heating and the digital flexible shape adjustment of the multi-point die, is beneficial to manufacturing the high-temperature alloy framework and the high-temperature alloy skin with any shapes, and is beneficial to effectively reducing the diffusion brazing time of the high-temperature alloy honeycomb sandwich structure, thereby being beneficial to manufacturing the high-temperature alloy honeycomb sandwich structure with high temperature resistance, light weight and high strength.
Description
Technical Field
The invention relates to the field of part forming, in particular to a method for forming a high-temperature alloy honeycomb sandwich structure.
Background
With the arrival of the air-space integrated era, the exploration, development and utilization of space have become one of the key points for revealing the strength of the country and defending the interests of the country, and although disposable Launch vehicles have been able to mature and deliver targets into space, their high cost increases the financial burden of each country, which is not in line with the current development needs of aerospace, and in the exploration of Launch vehicles, the idea of developing Reusable Launch Vehicles (RLV) has been proposed, which is a far-reaching and strategic technical development in the aerospace field, and which can reduce the space transportation cost, improve the operation efficiency, lay the foundation for large-scale aerospace applications, and thus are valued by aerospace developed countries and regions. The recycling of the X-37B orbit test aircraft after work is successfully completed twice in the United states, so that the development of RLV is emphasized again in countries which always pay attention to the development of aerospace.
The reusable aircraft, when in operation, needs to undergo long-term air flight, from ground to space, at a speed accelerated to several or even more than ten mach number, and particularly, when returning, needs to undergo severe aerodynamic heating. The temperature distribution of all parts of the American space shuttle when passing through the atmospheric layer shows that the temperature of most parts of an engine body, wings, a vertical tail and the like is between 750 and 1450 ℃, and local high-temperature regions close to 1800 ℃ can even appear at the front cone end part of the aircraft, an air inlet and the like. The high temperature generated by severe pneumatic heating during high-speed flight can obviously reduce the strength limit of hypersonic aircraft materials and the bearing capacity of an aircraft structure, so that the structure generates thermal deformation, the pneumatic appearance of parts is damaged, and the safety performance of the aircraft structure is influenced, therefore, the problems of high temperature resistance and heat insulation prevention of the hypersonic aircraft materials and the hypersonic aircraft structure become the key for the development success or failure of the aircraft. In response to this problem, it is one of the key technologies in RLV development to install a light-weight and cost-effective thermal protection system on the aircraft.
At present, the aerospace vehicle thermal protection system mainly comprises two types of ceramic heat-proof tiles and a metal honeycomb sandwich structure. The ceramic heat-proof tile has the defects of brittleness, easy falling off, water absorption, no rain resistance, easy deformation, difficult maintenance and replacement and the like, and two failures of the space shuttle are related to the ceramic heat-proof tile at present. The metal honeycomb sandwich structure has the advantages of large size, light weight, high toughness, good impact resistance, reusability, low life cycle cost, easy integration, modular design and high safety and reliability, is more and more widely applied to the field of aerospace, and is the first choice of a large-area passive heat-proof scheme for a secondary high-temperature area of a reusable spacecraft. The high-temperature alloy honeycomb sandwich structure not only has the traditional honeycomb light weight, but also has the high-temperature resistance, can meet the use requirement under the high-temperature environment condition of 900-1100 ℃, and has a great application prospect in products such as aerospace shuttle aircraft wall plates, hypersonic aircraft rudder wings and the like.
The prior Chinese patent with publication number CN109202204A discloses a method for manufacturing a honeycomb sandwich structure made of dissimilar materials, which has the technical key points that: the panel of the honeycomb sandwich structure is made of titanium alloy, the honeycomb core of the honeycomb sandwich structure is made of stainless steel, foil-shaped Ag-based brazing filler metal with the thickness of 0.1-0.2 mm is adopted for vacuum brazing of the panel and the honeycomb core, the brazing temperature is 810-835 ℃, and the heat preservation time is 5-15 min.
The inventor considers that the problems of large fillet radius of the traditional cold rolling forming of the high-temperature alloy corrugated plate, the need of a special die for hot forming of the high-temperature alloy three-dimensional skin/wall plate, long diffusion brazing time of the high-temperature alloy honeycomb sandwich structure and the like exist in the prior art, and a precise, flexible and rapid forming method needs to be provided.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a method for forming a high-temperature alloy honeycomb sandwich structure.
The invention provides a method for forming a high-temperature alloy honeycomb sandwich structure, which comprises the following steps:
step S1, forming a high-temperature alloy honeycomb core, wherein a high-temperature alloy foil is matched with a first pulse power supply and a roller to form a high-temperature alloy corrugated plate, a plurality of layers of high-temperature alloy corrugated plates are connected through a laser flight welding device to form a high-temperature alloy honeycomb, and the high-temperature alloy honeycomb is processed to form the high-temperature alloy honeycomb core;
s2, forming the high-temperature alloy skin/skeleton by electric pulse bending, pressing a high-temperature alloy plate into the high-temperature alloy skin through a multi-point digital mould, pressing a high-temperature alloy forging into a target curved surface through the multi-point digital mould, and then forming the high-temperature alloy skeleton through matching processing of wire cutting and numerical control processing;
and S3, self-resistance heating diffusion brazing of the high-temperature alloy honeycomb sandwich structure, placing the high-temperature alloy framework, the high-temperature alloy honeycomb core and the high-temperature alloy skin in a diffusion brazing mold, and performing diffusion brazing through a second pulse power supply to form the high-temperature alloy honeycomb sandwich structure.
Preferably, the rollers in step S1 include an upper roller and a lower roller that are engaged with each other, and the number of teeth and the pitch of teeth of both the upper roller and the lower roller are calculated from the half hexagonal side length of the superalloy corrugated sheet.
Preferably, in the step S1, flexible positioning devices are arranged between the two adjacent layers of the high-temperature alloy corrugated board at intervals, each flexible positioning device comprises a plurality of copper bars, and the intervals between the copper bars are matched with the hexagonal intervals of the high-temperature alloy corrugated board.
Preferably, the superalloy honeycomb in the step S1 is primarily processed by wire cutting to a single side with a 1-2mm allowance; and the high-temperature alloy honeycomb core is formed by matching and finish machining of a freezing tool and a milling cutter.
Preferably, the multi-point digital mold in the step S2 includes a plurality of independently adjustable basic bodies; the basic body forms a mold surface through the cooperation of multi-point CAD software, multi-point CAE software and multi-point CAM software.
Preferably, in the step S2, a polyurethane elastic pad is placed between the multi-point digitizing mold and the superalloy sheet.
Preferably, in the step S3, the superalloy honeycomb core is placed inside the superalloy skeleton, and the superalloy skins are disposed on both sides of the superalloy skeleton.
Preferably, the inner surface of any one of the superalloy skins in the step S3 is provided with a diffusion brazing solder.
Preferably, the diffusion brazing mold in the step S3 includes an upper diffusion brazing mold and a lower diffusion brazing mold, which cooperate to form a diffusion brazing mold cavity.
Preferably, in the step S3, the diffusion brazing mold cavity is vacuumized to 5 × 10 -3 And Pa, heating the high-temperature alloy honeycomb sandwich structure to be welded to 1050 ℃ by adopting a second pulse power supply rapid heating and step heating mode, then applying uniform pressure of 0.8MPa to the diffusion brazing die, keeping the temperature for 30min, cooling the diffusion brazing die by a furnace cooling mode, opening a furnace door when the temperature of the workpiece is lower than 250 ℃, cooling the workpiece to 50 ℃ by air, and taking out the workpiece to obtain the high-temperature alloy honeycomb sandwich structure.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention combines the rapid electric pulse heating and the digital flexible shape adjustment of the multi-point die, is beneficial to preparing the high-temperature alloy corrugated plate with smaller fillet radius, is beneficial to preparing the high-temperature alloy framework and the high-temperature alloy skin with any shapes, and is beneficial to effectively reducing the diffusion brazing time of the high-temperature alloy honeycomb sandwich structure, thereby being beneficial to preparing the high-temperature alloy honeycomb sandwich structure with high temperature resistance, light weight and high strength.
2. According to the invention, the high-temperature alloy honeycomb core is placed in the high-temperature alloy framework, and the high-temperature alloy skins are arranged on both sides of the high-temperature alloy framework, so that the weight of the high-temperature alloy honeycomb sandwich structure is reduced, and the structural strength and rigidity are improved.
3. The invention is beneficial to realizing flexible forming and precision compensation of any three-dimensional curved surface part by adopting the multi-point digital mould with a plurality of independently adjustable basic bodies.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic view of electric pulse heating diffusion brazing of a high temperature alloy honeycomb sandwich structure according to the present invention;
FIG. 2 is a schematic view of the electric pulse rolling forming of the high temperature alloy corrugated board according to the present invention;
FIG. 3 is a schematic view of laser flying welding of a high temperature alloy honeycomb according to the present invention;
FIG. 4 is a schematic view of a cryogenic milling process for a superalloy honeycomb embodying the present invention;
FIG. 5 is a schematic view of the multi-point die flexible forming of the three-dimensional curved surface of the high-temperature alloy according to the present invention;
FIG. 6 is a graph of an electrical pulse assisted diffusion brazing process embodying primarily the high temperature alloy honeycomb sandwich structure of the present invention.
Shown in the figure:
high-temperature alloy foil 1 upper roller 2 lower roller 3
A first pulse power supply 6 for the driving shaft 4 and the driven shaft 5
Laser flight welding device 9 for high-temperature alloy corrugated plate 7 flexible positioning device 8
High-temperature alloy plate 13 polyurethane elastic cushion 14 multi-point digital mould 15
High-temperature alloy framework 16 high-temperature alloy honeycomb core 17 high-temperature alloy skin 18
Diffusion brazing filler metal 19 diffusion brazing upper die 20 diffusion brazing lower die 21
Second pulse power supply 22
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1 to 5, the method for forming a superalloy honeycomb sandwich structure according to the present invention comprises the following steps:
step S1, forming a high-temperature alloy honeycomb core, matching the high-temperature alloy foil 1 with a first pulse power supply 6 and a roller to form a high-temperature alloy corrugated plate 7, connecting the multiple layers of high-temperature alloy corrugated plates 7 through a laser flight welding device 9 to form a high-temperature alloy honeycomb 10, and processing the high-temperature alloy honeycomb 10 to form a high-temperature alloy honeycomb core 17;
step S2, the high-temperature alloy skin/skeleton is formed by electric pulse bending, the high-temperature alloy sheet 13 is pressed into the high-temperature alloy skin 18 through the multi-point digital mould 15, and the high-temperature alloy forging is pressed into a target curved surface through the multi-point digital mould 15 and then is matched with the wire cutting and numerical control processing to form the high-temperature alloy skeleton 16;
step S3, the high-temperature alloy honeycomb sandwich structure is subjected to self-resistance heating diffusion brazing, the high-temperature alloy framework 16, the high-temperature alloy honeycomb core 17 and the high-temperature alloy skin 18 are placed in a diffusion brazing mold, and the high-temperature alloy honeycomb sandwich structure is formed through diffusion brazing by the second pulse power supply 22.
The core of the invention is that the method combines the rapid electric pulse heating and the digital flexible shape adjustment of a multi-point die, so that the high-temperature alloy corrugated board 7 with smaller fillet radius can be manufactured, the high-temperature alloy framework 16 and the high-temperature alloy skin 18 are pressed and formed without special dies, and can be manufactured into any shape, thereby effectively reducing the diffusion brazing time of the high-temperature alloy honeycomb sandwich structure and providing a precise, flexible and rapid forming method for the high-temperature alloy honeycomb sandwich structure of the air vehicle to and fro in the sky.
As shown in fig. 2, the rollers in step S1 include an upper roller 2 and a lower roller 3 that are engaged with each other, and the number of teeth and the pitch of teeth of both the upper roller 2 and the lower roller 3 are calculated from the half hexagonal side length of the superalloy corrugated sheet 7. The high-temperature alloy foil 1 is formed by cutting a wide high-temperature alloy foil into a narrow high-temperature alloy foil in a wire cutting mode, building the narrow high-temperature alloy foil into a target length through scissors, cleaning oil stains on the surface of the narrow high-temperature alloy foil through ultrasonic waves, and rolling the narrow high-temperature alloy foil through an upper roller 2 and a lower roller 3 which are meshed with each other.
The roller still includes driving shaft 4 and driven shaft 5, and driving shaft 4 and driven shaft 5 are linked with last roller 2 and lower roller 3 respectively through spline structure to connect the two poles of the earth of first pulse power supply 6 respectively. After meshing, the fit clearance between the upper roller 2 and the lower roller 3 is 0.1mm, the upper roller 2 is matched with the driving shaft 4, the lower roller 3 is matched with the driven shaft 5 and is driven by a motor lead screw structure, the rotating directions of the lower roller and the driven shaft are opposite, and the linear speed direction of a meshing point of the lower roller is consistent with the feeding direction of the high-temperature alloy foil.
The rapid and precise forming of the high-temperature alloy corrugated plate 7 is to design the tooth number and the tooth pitch of a rolling forming die through expansion calculation, realize the precise rolling forming of the high-temperature alloy foil 1 through an electric pulse auxiliary rolling forming mode, form a semi-hexagonal corrugated plate with a small circular corner radius, and obviously improve the strength of a honeycomb. After the high-temperature alloy corrugated board 7 is manufactured by rolling the high-temperature alloy foil 1, the blanking of the half hexagonal corrugated board with any length is realized by adopting a laser cutting mode.
As shown in fig. 3, in step S1, flexible positioning devices 8 are arranged between two adjacent layers of superalloy corrugated boards 7 at intervals, each flexible positioning device 8 includes a plurality of discrete copper bars, the distance between the copper bars matches with the hexagonal interval of the superalloy corrugated board 7, and the flexible positioning devices are used for supporting the superalloy corrugated board 7, and simultaneously, another superalloy corrugated board 7 is compressed by a compression block, so that the high-temperature alloy corrugated board 7 is accurately assembled, and thus layer-by-layer assembly and spot welding connection of the superalloy corrugated board 7 are achieved.
The laser flight welding device 9 has the function of accurately adjusting the coaxial laser light source heat input proportion, can realize accurate control of welding seam macroscopic structure and mechanical property, connects adjacent layers of the high-temperature alloy corrugated plate 7 in a laser quick sweeping mode, removes oil and impurities from the high-temperature alloy corrugated plate 7 before laser flight welding, wipes the high-temperature alloy corrugated plate 7 by 75% of alcohol solution, optimally designs the welding seam interval before welding to obtain proper spot welding strength, and obtains optimal technological parameters based on a pull-off test.
The connection of the high-temperature alloy honeycomb 10 is that high-temperature alloy corrugated plates 7 punched to the target size are stacked layer by layer, the assembly of the high-temperature alloy corrugated plates 7 is realized by arranging the interval type flexible positioning device 8, and then the quick high-strength connection between the upper-layer high-temperature alloy corrugated plates 7 and the lower-layer high-temperature alloy corrugated plates 7 is realized by utilizing a laser flight welding mode.
As shown in fig. 4, the high temperature alloy honeycomb 10 is initially processed by wire cutting to a single side with a 1-2mm margin in step S1. The high-temperature alloy honeycomb 10 is matched with a milling cutter 12 through a freezing tool 11 to be finely processed to form a high-temperature alloy honeycomb core 17. The freezing tool 11 is used for cooling and freezing the high-temperature alloy honeycomb 10 after preliminary processing, improving rigidity and fixing and supporting subsequent numerical control milling. The milling cutter 12 is a special hard alloy cutter and is used for milling the reserved allowance of the profile of the thin-wall weak-rigidity high-temperature alloy honeycomb 10 until the target profile is reached, and the high-temperature alloy honeycomb core 17 without a heat influence area is obtained.
The precision machining of the high-temperature alloy honeycomb core 17 is to perform profile primary machining on the high-temperature alloy honeycomb 9 formed by spot welding in a wire cutting mode and then realize the three-dimensional profile finish machining of the high-temperature alloy honeycomb core 17 in a freezing and milling mode.
As shown in fig. 5, the multi-point digitizing mold 15 in step S2 includes a plurality of independently adjustable basic bodies; the basic body forms a mold surface through the cooperation of multi-point CAD software, multi-point CAE software and multi-point CAM software. The multipoint digital mould 15 replaces the traditional integral mould by a plurality of independently adjustable basic bodies, the mould realization process is based on the three-dimensional digital analogy of a target part, the fast adjustment of the height position of the basic body of the multipoint digital mould 15 is realized by multipoint CAD/CAE/CAM software, so as to form different mould profiles, then the mould attachment is realized by the multipoint digital mould 15 under the driving of a press, the flexible forming and precision compensation of any three-dimensional curved surface part can be realized, and the fast forming of different three-dimensional curved surface parts is realized.
The rapid shape adjustment of the multipoint digital mold 15 is to introduce the three-dimensional digital models of the high-temperature alloy framework 16 and the high-temperature alloy skin 18 into multipoint CAD software, automatically adjust the height of the basic body punch through the multipoint CAE software, and then realize the rapid flexible shape adjustment of the multipoint digital mold 15 through the formed height data of the basic body punch through the multipoint CAM software.
The high-temperature alloy sheet material 13 is obtained by unfolding and calculating a high-temperature alloy skin 18 to obtain the shape and the size of a specific blank and by a laser cutting mode. In the step S2, a polyurethane elastic pad 14 is placed between the multi-point digital mold 15 and the superalloy sheet 13, and is mainly used for suppressing indentation defects caused by discontinuity of the profile of the multi-point digital mold 15.
The multipoint digital mould 15 is driven by an upper platform of a press to realize mould attachment, so that high-temperature alloy skin/framework electric pulse rapid bending forming is realized, and part precision forming is realized through multipoint mould profile springback compensation.
After the high-temperature alloy sheet 13 is pressed and formed by a multi-point digital mould 15, the high-temperature alloy skin 18 is manufactured by cutting a target shape in a laser cutting mode. After the high-temperature alloy forging is pressed and formed through a multi-point digital die 15, redundant materials in the framework are cut off through linear cutting preliminary machining, then a thin-wall narrow-rib grid framework is obtained after fine machining through a numerical control machining center, and the high-temperature alloy framework 16 is precisely machined.
As shown in fig. 1, in step S3, the superalloy honeycomb core 17 is placed inside the superalloy skeleton 16, and the superalloy skin 18 is disposed on both sides of the superalloy skeleton 16. The high-temperature alloy honeycomb core 17 is arranged in a framework lattice of the high-temperature alloy framework 16 and used for reducing the structural weight and playing a role in improving the structural strength and rigidity.
Any one of the superalloy skins 18 in step S3 is provided with diffusion braze solder 19 on its inner surface. The diffusion brazing solder 19 is made of high-temperature resistant BNi-1 solder, so that the high-temperature alloy honeycomb sandwich structure can resist the high temperature of more than 1000 ℃.
The diffusion brazing mold in step S3 includes an upper diffusion brazing mold 20 and a lower diffusion brazing mold 21, which cooperate to form a diffusion brazing mold cavity. The upper diffusion brazing die 20 and the lower diffusion brazing die 21 are used for ensuring the external dimension precision of diffusion brazing of the high-temperature alloy honeycomb sandwich structure. The second pulse power source 22 is used for rapidly heating the diffusion brazing upper die 20 and the diffusion brazing lower die 21, and simultaneously rapidly transferring heat to a part to be welded of the high-temperature alloy honeycomb sandwich structure, so that rapid heating is realized.
As shown in fig. 6, in a curve of the electric pulse heating diffusion brazing process for the superalloy honeycomb sandwich structure, in step S3, the processing process for the parts to be welded of the superalloy honeycomb sandwich structure mainly includes the steps of vacuumizing, heating, diffusion brazing, cooling, and the like.
The vacuum pumping is to send the assembled high temperature alloy honeycomb sandwich structure into a vacuum thermal creep furnace and then to pump the diffusion brazing mold cavity to 5 x 10 -3 Pa。
The high-temperature alloy honeycomb sandwich structure to be welded is heated to 1050 ℃ by adopting a second pulse power supply 22 for rapid heating and a step temperature rise mode. The heating step is carried out in multiple stages, the heating is carried out for 5min in the first stage, and the temperature is kept for 5min when the temperature of the die is stable and reaches 600 ℃; heating for 10min in the second stage, and keeping the temperature for 10min when the temperature of the die is stabilized to 900 ℃; and heating for 10min in the third stage until the temperature of the mold is stabilized to 1050 ℃.
In the diffusion brazing, when the temperature of the mold stably reaches 1050 ℃, uniform pressure of 0.8MPa is applied to the diffusion brazing mold through a pressure head on vacuum equipment, and heat preservation is carried out for 30min to ensure that diffusion brazing welding flux 19 is completely wetted and spread, so that the connection among the high-temperature alloy framework 16, the high-temperature alloy honeycomb core 17 and the high-temperature alloy skin 18 is realized.
And cooling the workpiece in a furnace cooling mode, opening a furnace door when the temperature of the workpiece is lower than 250 ℃, naturally cooling the workpiece to 50 ℃, and taking out the workpiece to obtain the high-temperature alloy honeycomb sandwich structure.
The invention aims to overcome the problems of insufficient heat strength, large brittleness, poor thermal vibration resistance and the like of the traditional high-temperature titanium alloy material, and combines the high-temperature resistance of the high-temperature alloy with the light-weight high-strength performance of a honeycomb structure. The invention provides a method for forming a high-temperature alloy honeycomb sandwich structure, which is characterized in that the method integrates electric pulse rapid heating and multi-point die digital flexible shape adjustment, so that a high-temperature alloy corrugated plate 7 with a smaller fillet radius can be prepared, a high-temperature alloy framework 16 and a high-temperature alloy skin 18 are pressed and formed without a special die, the high-temperature alloy honeycomb sandwich structure can be prepared into any shape, the diffusion brazing time of the high-temperature alloy honeycomb sandwich structure can be effectively reduced, and a precise, flexible and rapid forming method is provided for the high-temperature alloy honeycomb sandwich structure of a shuttle aircraft in the sky.
Principle of operation
The rapid and precise forming of the high-temperature alloy corrugated plate 7 is to design the tooth number and the tooth pitch of a rolling forming die through expansion calculation, realize the precise rolling forming of the high-temperature alloy foil 1 through an electric pulse auxiliary rolling forming mode, form a semi-hexagonal corrugated plate with a small circular corner radius, and obviously improve the strength of a honeycomb. After the high-temperature alloy corrugated board 7 is manufactured by rolling the high-temperature alloy foil 1, the blanking of the half hexagonal corrugated board with any length is realized by adopting a laser cutting mode. The connection of the high-temperature alloy honeycomb 10 is that high-temperature alloy corrugated plates 7 punched to the target size are stacked layer by layer, the assembly of the high-temperature alloy corrugated plates 7 is realized by arranging the interval type flexible positioning device 8, and then the quick high-strength connection between the upper-layer high-temperature alloy corrugated plates 7 and the lower-layer high-temperature alloy corrugated plates 7 is realized by utilizing a laser flight welding mode. The precision machining of the high-temperature alloy honeycomb core 17 is to perform profile primary machining on the high-temperature alloy honeycomb 9 formed by spot welding in a wire cutting mode and then realize the three-dimensional profile finish machining of the high-temperature alloy honeycomb core 17 in a freezing and milling mode. After the high-temperature alloy sheet 13 is pressed and formed by a multi-point digital mould 15, the high-temperature alloy skin 18 is manufactured by cutting a target shape in a laser cutting mode. After the high-temperature alloy forging is pressed and formed through a multi-point digital die 15, redundant materials in the framework are cut off through linear cutting preliminary machining, then a thin-wall narrow-rib grid framework is obtained after fine machining through a numerical control machining center, and the high-temperature alloy framework 16 is precisely machined. The high-temperature alloy honeycomb core 17 is placed inside the high-temperature alloy framework 16, the high-temperature alloy skins 18 are arranged on two sides of the high-temperature alloy framework 16, the high-temperature alloy honeycomb core 17 and the high-temperature alloy skins 18 are placed in a diffusion brazing mold, and a second pulse power supply 22 is used for diffusion brazing to form a high-temperature alloy honeycomb sandwich structure. The processing technology of the parts to be welded with the high-temperature alloy honeycomb sandwich structure mainly comprises the steps of vacuumizing, heating, diffusion brazing, cooling and the like.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A method for forming a high-temperature alloy honeycomb sandwich structure is characterized by comprising the following steps:
step S1, forming a high-temperature alloy honeycomb core, matching a high-temperature alloy foil (1) with a roller through a first pulse power supply (6) to form a high-temperature alloy corrugated plate (7), connecting a plurality of layers of high-temperature alloy corrugated plates (7) through a laser flight welding device (9) to form a high-temperature alloy honeycomb (10), and processing the high-temperature alloy honeycomb (10) to form a high-temperature alloy honeycomb core (17);
s2, forming the high-temperature alloy skin/skeleton by electric pulse bending, pressing a high-temperature alloy plate (13) into the high-temperature alloy skin (18) through a multi-point digital mould (15), pressing a high-temperature alloy forging into a target curved surface through the multi-point digital mould (15), and then forming the high-temperature alloy skeleton (16) through matching processing of wire cutting and numerical control processing;
and S3, self-resistance heating diffusion brazing of the high-temperature alloy honeycomb sandwich structure, namely placing the high-temperature alloy framework (16), the high-temperature alloy honeycomb core (17) and the high-temperature alloy skin (18) in a diffusion brazing mold, and performing diffusion brazing by using a second pulse power supply (22) to form the high-temperature alloy honeycomb sandwich structure.
2. The method for forming a superalloy honeycomb sandwich structure according to claim 1, wherein the rollers in step S1 include an upper roller (2) and a lower roller (3) which are engaged with each other, and the number of teeth and pitch of both the upper roller (2) and the lower roller (3) are calculated from the length of the half hexagonal side of the superalloy corrugated sheet (7).
3. The method for forming the superalloy honeycomb sandwich structure according to claim 1, wherein a flexible positioning device (8) is arranged between two adjacent layers of the superalloy corrugated sheet (7) at intervals in the step S1, the flexible positioning device (8) comprises a plurality of copper bars, and the intervals between the copper bars are matched with the hexagonal intervals of the superalloy corrugated sheet (7).
4. The method of claim 1, wherein the superalloy honeycomb sandwich structure (10) in step S1 is initially machined by wire cutting to a single side with 1-2mm of margin;
the high-temperature alloy honeycomb (10) is matched with a milling cutter (12) through a freezing tool (11) to be finely processed to form the high-temperature alloy honeycomb core (17).
5. The method of claim 1, wherein the multi-point digitizing mold (15) of step S2 comprises a plurality of independently adjustable base bodies;
the basic body forms a mold surface through the cooperation of multi-point CAD software, multi-point CAE software and multi-point CAM software.
6. The method of claim 1, wherein a polyurethane elastic pad (14) is placed between the multi-point digitizing mold (15) and the superalloy sheet material (13) in step S2.
7. The method of claim 1, wherein the superalloy honeycomb sandwich structure forming step S3 is performed by placing the superalloy honeycomb core (17) inside the superalloy skeleton (16), and the superalloy skin (18) is disposed on both sides of the superalloy skeleton (16).
8. The method of claim 7, wherein the superalloy honeycomb sandwich structure forming method of any of the steps S3 is characterized in that the inner surface of the superalloy skin (18) is provided with diffusion braze filler (19).
9. The method of claim 1, wherein the diffusion brazing mold of step S3 includes an upper diffusion brazing mold (20) and a lower diffusion brazing mold (21) that cooperate to form a diffusion brazing mold cavity.
10. The method of forming a superalloy honeycomb sandwich structure according to claim 9, wherein the step S3 is performed by evacuating the diffusion braze mold cavity to 5 x 10 -3 Pa, heating the high-temperature alloy honeycomb sandwich structure to be welded to 1050 ℃ by adopting a rapid heating and stepped temperature rising mode of the second pulse power supply (22), then applying uniform pressure of 0.8MPa to the diffusion brazing mould, keeping the temperature for 30min, cooling the diffusion brazing mould by a furnace cooling mode, opening a furnace door when the temperature of a workpiece is lower than 250 ℃, and keeping the temperature of the furnace door at the same timeAnd after the high-temperature alloy honeycomb sandwich structure is cooled to 50 ℃ in air, taking out the high-temperature alloy honeycomb sandwich structure to obtain the high-temperature alloy honeycomb sandwich structure.
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