Continuous fiber reinforced metal matrix composite cylindrical part forming method

Abstract

The invention relates to the technical field of metal matrix composite component forming, in particular to a continuous fiber reinforced metal matrix composite cylindrical part forming method which comprises the following steps: determining the size and spacing of fiber holes of an annular fixing plate according to the fiber volume fraction and hot isostatic pressing shrinkage of a composite material; a powder filling port is reserved in the inner ring of the fixed plate; the fibers sequentially penetrate through the corresponding fiber holes of the two fixing plates till all the fiber holes are filled with the fibers; the wrapping inner cylinder, the fixing plate and the fibers are put into the wrapping outer cylinder as a whole, gaps between the fibers are filled with matrix metal powder through the powder filling opening, and compaction is conducted while filling is conducted; and the wrapping inner cylinder, the wrapping outer cylinder, the shape control graphite mold core and the wrapping cover are assembled, and the continuous fiber reinforced metal matrix composite cylindrical component is obtained through hot isostatic pressing and wrapping removal treatment. The method aims at solving the problem that when a powder metallurgy method is adopted for preparing a metal matrix composite component with long fiber arrangement, the fiber direction is difficult to control.

Description

Technical Field

[0001] The invention relates to the technical field of metal matrix composite material component forming, and in particular to a method for forming a continuous fiber reinforced metal matrix composite material cylindrical component. Background Art

[0002] Continuous fiber reinforced metal matrix composites, such as silicon carbide fiber reinforced titanium matrix composites, boron fiber reinforced aluminum matrix composites, etc., have excellent comprehensive properties due to the addition of high-performance fibers in the metal matrix. Metal matrix composite cylindrical parts with axially arranged fibers have good application prospects in the aviation field, such as landing gear. Continuous fiber reinforced metal matrix composites usually use coarse filament fibers with a diameter of 100 to 140 μm. When the fibers are arranged in a directional manner, local fiber crossing is inevitable, forming defects and affecting the performance of the component. The control of the arrangement direction and uniformity of the fibers in the cylindrical component is the main difficulty in the preparation of such components. There is an urgent need for a composite cylindrical component forming method with simple process, low cost, uniform fiber and high parallelism.

[0003] For the preparation of continuous fiber reinforced metal matrix composite cylindrical components with axially arranged fibers, the foil-fiber-foil method and the fiber coating substrate method are currently mainly used. The fiber volume fraction of the foil-fiber-foil method is limited, and the uniformity of fiber arrangement is difficult to control. The fiber coating substrate method has high cost and extremely low material utilization. When preparing parts such as cylinders, the fibers are prone to local fiber crossing and it is difficult to keep them completely parallel. In the fiber coating substrate method, if an adhesive is used to fix the precursor wire, the adhesive removal process is complicated. If it is not removed completely, defects will be introduced and the performance will be reduced; the inner wall of the sheath is engraved with edges, but there is no fiber arrangement at each edge position, and the fibers are not filled with the required reinforcement area, and the component cannot achieve the expected performance. The powder metallurgy method has the advantages of high material utilization and low cost, but it is difficult to control the fiber direction. Therefore, it is often used in the preparation of short fiber or particle reinforced metal matrix composite components, and is rarely used in the preparation of metal matrix composite components with unidirectional thick filament and long fiber arrangement.

[0004] Therefore, the inventor provides a method for forming a continuous fiber reinforced metal matrix composite cylindrical part. Summary of the invention

[0005] (1) Technical issues to be solved

[0006] The embodiment of the present invention provides a method for forming a continuous fiber reinforced metal matrix composite cylindrical part, which solves the technical problem of difficulty in controlling the fiber direction when preparing a metal matrix composite component with a long fiber arrangement by powder metallurgy.

[0007] (2) Technical solution

[0008] The present invention provides a method for forming a continuous fiber reinforced metal matrix composite cylindrical part, comprising the following steps:

[0009] According to the fiber volume fraction and hot isostatic pressing shrinkage of the composite material, the fiber hole size and spacing of the annular fixing plate are determined, and a powder filling port is reserved in the inner ring of the fixing plate;

[0010] The two fixing plates are sequentially mounted on the outer wall of the inner tube of the sheath, and the fibers are sequentially passed through the fiber holes corresponding to the two fixing plates until all the fiber holes are filled;

[0011] Move the lower fixing plate to the bottom end of the sheath inner cylinder, place the sheath inner cylinder, fixing plate and fiber as a whole into the sheath outer cylinder, fill the matrix metal powder into the fiber gap through the powder filling port, and vibrate while filling;

[0012] The sheath inner cylinder, the sheath outer cylinder, the shape-controlling graphite core and the sheath cover are assembled, and subjected to hot isostatic pressing and sheath removal treatment to obtain a continuous fiber reinforced metal matrix composite cylindrical component.

[0013] Furthermore, the fixing plate is provided with a fixing net along its circumference.

[0014] Furthermore, the fixed net is annular, its inner diameter is the sum of the inner diameter of the fiber reinforced area in the component and the internal shrinkage value during hot isostatic pressing, and its outer diameter is the sum of the outer diameter of the fiber reinforced area in the component and the external shrinkage value during hot isostatic pressing.

[0015] Furthermore, the center distance d between two adjacent fiber holes on the fixed net meets the condition: 2.5R 1 ≤d≤4R 1 , R 1 is the fiber diameter.

[0016] Furthermore, the diameter R of the fiber hole 2 Satisfied conditions: R 1 ≤R 2 ≤2R 1 .

[0017] Furthermore, the fixing plate is provided with a plurality of powder filling ports spaced apart along the circumferential direction of the inner circle thereof.

[0018] Furthermore, the material of the sheath inner cylinder and the sheath outer cylinder is the same as the material of the composite material.

[0019] Furthermore, the inner sleeve tube filled with fiber and powder, the outer sleeve tube, the internal graphite shape-controlling core, and the sleeve cover are assembled into a sleeve, and the sleeve is sealed and welded and then baked. After baking, the sleeve is vacuumed to 2×10 -3 Next, weld and seal.

[0020] Furthermore, the sheath is hot isostatically pressed in a hot isostatic pressing furnace, wherein when the substrate is a titanium alloy, the hot isostatic pressing process is 830-920°C / 120-180MPa / 2-3h.

[0021] Further, the jacket is removed by machining, the graphite core is removed by sandblasting, and the cylindrical component is processed to the final size.

[0022] (3) Beneficial effects

[0023] In summary, the present invention achieves the fixation of the fiber direction through the fiber holes of the fixing plate, so that the fibers are arranged uniformly and parallel in the material, and no additional adhesive is introduced during the fixing process, thereby avoiding defects introduced by adhesive residues in the component. At the same time, the fiber spacing and volume fraction can be adjusted by adjusting the fiber hole spacing of the fixing plate, and after the fibers are fixed by the fixing plate, the matrix metal is added in the form of powder to realize the composite material forming, which has the advantages of high material utilization and low cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments of the present invention are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0025] Figure 1 It is a schematic flow chart of a method for forming a continuous fiber reinforced metal matrix composite cylindrical component provided by an embodiment of the present invention;

[0026] Figure 2 is a structural schematic diagram of a fixing plate provided by an embodiment of the present invention;

[0027] Figure 3 It is a schematic diagram of the process of a method for forming a continuous fiber reinforced metal matrix composite cylindrical part provided by an embodiment of the present invention.

[0028] In the figure:

[0029] 1-fixed plate; 101-fiber hole; 102-powder filling port. DETAILED DESCRIPTION

[0030] The following is a further detailed description of the embodiments of the present invention in conjunction with the accompanying drawings and examples. The detailed description of the following embodiments and the accompanying drawings are used to exemplarily illustrate the principles of the present invention, but cannot be used to limit the scope of the present invention, that is, the present invention is not limited to the described embodiments, and covers any modification, replacement and improvement of parts, components and connection modes without departing from the spirit of the present invention.

[0031] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0032] In the description of the present invention, it should be understood that the terms "upper", "lower", "front", "rear", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, or are the orientations or positional relationships in which the products of the present invention are conventionally placed when in use, or are the orientations or positional relationships conventionally understood by those skilled in the art. These are merely for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0033] Figure 1 is a schematic diagram of a process for forming a continuous fiber reinforced metal matrix composite cylindrical member provided by an embodiment of the present invention, see Figure 1 , the method may include the following steps:

[0034] S100, determining the fiber hole size and spacing of the annular fixing plate according to the fiber volume fraction and hot isostatic pressing shrinkage of the composite material, and reserving a powder filling port on the inner circle of the fixing plate.

[0035] Specifically, the fiber is selected from thick silicon carbide fiber, carbon fiber or boron fiber with a diameter of 100 to 150 μm. A fixing plate 1 is prepared, whose material is the same as the composite material matrix and has a thickness of 1 to 2 mm. The diameter of its fiber hole 101 is not less than the fiber diameter and not more than 2 times the fiber diameter. In addition, the hole spacing of the fiber hole is jointly determined by the preset composite material fiber volume fraction and the hot isostatic pressing compression amount prediction.

[0036] Among them, Figure 2 As shown, the fixed plate 1 is provided with a fixed net along its circumference. The fixed net is annular, and its inner diameter is the sum of the inner diameter of the fiber reinforced area in the component and the internal shrinkage value during the hot isostatic pressing process, and its outer diameter is the sum of the outer diameter of the fiber reinforced area in the component and the external shrinkage value during the hot isostatic pressing process.

[0037] Furthermore, if Figure 2 As shown, the center distance d between two adjacent fiber holes 101 on the fixed net meets the condition: 2.5R 1 ≤d≤4R 1 , R 1 The fiber hole 101 diameter R is the fiber diameter. The fiber hole spacing within this range can avoid direct contact between fibers in the final component and correspond to a higher fiber volume fraction to ensure component performance. 2 Satisfied conditions: R 1 ≤R 2 ≤2R 1 .

[0038] Furthermore, if Figure 2 As shown, the fixed plate 1 is provided with a plurality of powder filling ports 102 spaced apart along the circumferential direction of the inner ring thereof. When the cylinder depth of the component is less than 200 mm, the width of the powder filling port 102 is 2 mm; when the cylinder depth of the component is greater than 200 mm, the width of the powder filling port 102 is 5 mm. The powder filling ports 102 within this range can fully fill the powder without wasting too much powder material due to being too large.

[0039] S200, sleeve the two fixing plates on the outer wall of the inner tube of the sheath in sequence, and pass the fibers through the fiber holes corresponding to the two fixing plates in sequence until all the fiber holes are filled.

[0040] Specifically, the fiber is cut according to the cavity height of the sheath, and the surface is cleaned with acetone. Two fixing plates are fixed to the outer wall of the inner tube of the sheath, and the sheath material is the same as the matrix material of the composite material. The fibers are filled into the corresponding holes of the two fixing plates in sequence until all the fiber holes are filled.

[0041] S300, move the lower fixing plate to the bottom end of the sheath inner cylinder, put the sheath inner cylinder, the fixing plate and the fiber into the sheath outer cylinder as a whole, fill the matrix metal powder into the fiber gap through the powder filling port, and vibrate while filling.

[0042] Specifically, the base metal powder is a metal powder such as titanium alloy or aluminum alloy, and its particle size is 10 to 50 μm. At this time, the fibers have been fixed by the upper and lower fixing plates, and are relatively uniform and parallel.

[0043] S400, assembling the sheath inner cylinder, the sheath outer cylinder, the shape-controlling graphite core, and the sheath cover, and performing hot isostatic pressing and sheath removal treatment to obtain a continuous fiber reinforced metal matrix composite cylindrical component.

[0044] Specifically, the inner and outer sheaths filled with fiber and powder are assembled with the internal graphite shape-controlling core and the sheath cover, and the sheath is sealed and welded and then baked. After baking, the sheath is vacuumed to 2×10 -3 Next, weld and seal. The jacket is placed in a hot isostatic pressing furnace for hot isostatic pressing. When the substrate is titanium alloy, the hot isostatic pressing process is 830-920℃ / 120-180MPa / 2-3h. The jacket is removed by machining, the graphite core is removed by sandblasting, and the final size of the cylindrical component is processed.

[0045] Example 1

[0046] Step 1: The fiber is a thick silicon carbide fiber with a diameter of 100 μm. According to the height of the cylindrical component, the continuous fiber is cut into a specified length and the surface is cleaned with acetone. The metal powder is TC18 titanium alloy powder with an average particle size of 30 μm.

[0047] Step 2: Prepare two 100 mesh TC18 titanium alloy fixing plates with a thickness of 1 mm. The diameter of the small holes is 150 μm. The small hole spacing is 200 μm (small hole center spacing). The small hole arrangement area is calculated based on the inner and outer contours of the fiber arrangement area in the cylindrical component combined with the subsequent hot isostatic pressing shrinkage prediction compensation calculation, as shown in formulas (1)-(2). Reserve multiple powder filling ports inside the fixing plate.

[0048] R 网内 =R 增内 +R 收缩内 (1)

[0049] R 网外 =R 增外 +R 收缩外 (2)

[0050] In the formula, R 网内 , R 网外 is the inner and outer diameter of the fixed net, R 增内 , R 增外 R is the inner and outer diameter of the fiber-reinforced area of ​​the component. 收缩内 , R 收缩外 It is the shrinkage value of the hot isostatic pressing process predicted by finite element simulation, that is, the difference between the size of the fiber arrangement area of ​​the preform and the size of the fiber reinforcement area of ​​the furnace sample.

[0051] Step 3: Fix two fixing plates on the outer wall of the inner tube of the TC18 titanium alloy sheath. Fill the fibers into the corresponding holes of the two fixing plates in turn until all the small holes are filled. Then move one of the fixing plates to the other side of the inner tube, and then put the inner tube, fixing plate, and fibers into the outer tube of the TC18 titanium alloy sheath. At this time, the fibers are fixed by the upper and lower fixing plates, and are relatively uniform and parallel. Fill the powder into the gap between the fibers, and vibrate while filling until the gap is filled.

[0052] Step 4: Assemble the inner and outer sheaths filled with fiber and powder, the internal graphite shape-controlling core, and the sheath cover, seal and weld the sheath, evacuate the sheath, and bake it in a baking furnace. After it comes out of the furnace, weld and seal it.

[0053] Step 5: Place the package in a hot isostatic pressing furnace for hot isostatic pressing. When the substrate is a titanium alloy, the hot isostatic pressing process is 900°C / 140MPa / 3h.

[0054] Step 6: Remove the jacket by machining, remove the graphite core by sandblasting, and process to the final size of the cylindrical component.

[0055] Example 2

[0056] Step 1: The fiber is a coarse boron fiber with a diameter of 140 μm. According to the height of the cylindrical component, the continuous fiber is cut into a specified length and the surface is cleaned with acetone. The metal powder is 2024 aluminum alloy powder with an average particle size of 10 μm.

[0057] Step 2: Prepare two 100 mesh T2024 aluminum alloy fixing plates with a thickness of 1 mm. The diameter of the small holes is 200 μm. The small hole spacing is 250 μm. The small hole arrangement area is calculated based on the inner and outer contours of the fiber arrangement area in the cylindrical component combined with the subsequent hot isostatic pressing shrinkage prediction compensation calculation, as shown in formulas (3)-(4). Reserve multiple powder filling ports inside the fixing plate.

[0058] R 网内 =R 增内 +R 收缩内 (3)

[0059] R 网外 =R 增外 +R 收缩外 (4)

[0060] In the formula, R 网内 , R 网外 is the inner and outer diameter of the fixed net, R 增内 , R 增外 R is the inner and outer diameter of the fiber-reinforced area of ​​the component. 收缩内 , R 收缩外 It is the shrinkage value of the hot isostatic pressing process predicted by finite element simulation, that is, the difference between the size of the fiber arrangement area of ​​the preform and the size of the fiber reinforcement area of ​​the furnace sample.

[0061] Step 3: Fix two fixing plates on the outer wall of the 2024 aluminum alloy sheath inner cylinder. Fill the fibers into the corresponding holes of the two fixing plates in turn until all the mesh holes are filled. Then move one of the fixing plates to the other side of the inner cylinder, and then put the inner cylinder, fixing plate, and fibers into the 2024 aluminum alloy sheath outer cylinder. At this time, the fibers are fixed by the upper and lower fixing plates, and are relatively uniform and parallel. Fill the powder into the gaps between the fibers, and vibrate while filling until the gaps are filled.

[0062] Step 4: Assemble the inner and outer sheaths filled with fiber and powder, the internal graphite shape-controlling core, and the sheath cover, and evacuate the sheath to 2×10 -3 Next, weld and seal.

[0063] Step 5: Place the package in a hot isostatic pressing furnace for hot isostatic pressing. When the substrate is a titanium alloy, the hot isostatic pressing process is 550°C / 140MPa / 3h.

[0064] Step 6: Remove the jacket by machining, remove the graphite core by sandblasting, and process to the final size of the cylindrical component.

[0065] It should be clear that the various embodiments in this specification are described in a progressive manner, and the same or similar parts between the various embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. The present invention is not limited to the specific steps and structures described above and shown in the figures. In addition, for the sake of brevity, a detailed description of known methods and technologies is omitted here.

[0066] The above are only embodiments of the present application and are not limited to the present application. For those skilled in the art, the present application may have various changes and variations without departing from the scope of the present invention. Any modification, equivalent substitution, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.

Claims

1. A method for forming a continuous fiber reinforced metal matrix composite cylindrical part, characterized in that: The method comprises the following steps: According to the fiber volume fraction and hot isostatic pressing shrinkage of the composite material, the fiber hole size and spacing of the annular fixing plate are determined, and a powder filling port is reserved in the inner ring of the fixing plate; The two fixing plates are sequentially mounted on the outer wall of the inner tube of the sheath, and the fibers are sequentially passed through the fiber holes corresponding to the two fixing plates until all the fiber holes are filled; Move the lower fixing plate to the bottom end of the sheath inner cylinder, place the sheath inner cylinder, fixing plate and fiber as a whole into the sheath outer cylinder, fill the matrix metal powder into the fiber gap through the powder filling port, and vibrate while filling; The sheath inner cylinder, the sheath outer cylinder, the shape-controlling graphite core and the sheath cover are assembled, and subjected to hot isostatic pressing and sheath removal treatment to obtain a continuous fiber reinforced metal matrix composite cylindrical component.

2. The method for forming a continuous fiber reinforced metal matrix composite cylindrical part according to claim 1, characterized in that: The fixing plate is provided with a fixing net along its circumference.

3. The method for forming a continuous fiber reinforced metal matrix composite cylindrical part according to claim 2, characterized in that: The fixed net is annular, and its inner diameter is the sum of the inner diameter of the fiber reinforced area in the component and the internal shrinkage value during hot isostatic pressing, and its outer diameter is the sum of the outer diameter of the fiber reinforced area in the component and the external shrinkage value during hot isostatic pressing.

4. The method for forming a continuous fiber reinforced metal matrix composite cylindrical part according to claim 2 or 3, characterized in that: The center distance d between two adjacent fiber holes on the fixed net meets the condition: 2.5R1≤d≤4R1, where R1 is the fiber diameter.

5. The method for forming a continuous fiber reinforced metal matrix composite cylindrical part according to claim 4, characterized in that: The diameter R2 of the fiber hole satisfies the condition: R1≤R2≤2R1.

6. The method for forming a continuous fiber reinforced metal matrix composite cylindrical part according to claim 1, characterized in that: The fixing plate is provided with a plurality of powder filling ports spaced apart along the circumferential direction of the inner circle thereof.

7. The method for forming a continuous fiber reinforced metal matrix composite cylindrical part according to claim 1, characterized in that: The material of the sheathing inner cylinder and the sheathing outer cylinder is the same as the material of the composite material.

8. The method for forming a continuous fiber reinforced metal matrix composite cylindrical part according to claim 1, characterized in that: The inner sleeve tube filled with fiber and powder, the outer sleeve tube, the internal graphite shape-controlling core, and the sleeve cover are assembled into a sleeve, and the sleeve is sealed and welded and then baked. After baking, the sleeve is vacuumed to 2×10 -3 Next, weld and seal.

9. The method for forming a continuous fiber reinforced metal matrix composite cylindrical part according to claim 8, characterized in that: The sheath is hot isostatically pressed in a hot isostatic pressing furnace, wherein when the substrate is a titanium alloy, the hot isostatic pressing process is 830-920°C / 120-180MPa / 2-3h.

10. The method for forming a continuous fiber reinforced metal matrix composite cylindrical part according to claim 1, characterized in that: The jacket is removed by machining, the graphite core is removed by sandblasting, and the cylindrical component is machined to its final size.

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