Spiral-structure fiber-reinforced metal-based composite material and preparation method thereof

Abstract

The invention belongs to the technical field of metal-based composite materials, and particularly relates to a spiral-structure fiber-reinforced metal-based composite material and a preparation method thereof. The spiral-structure fiber-reinforced metal-based composite material is obtained by performing hot isostatic pressing on a preform; the prefabricated body comprises an alloy sheath and fiber tows which are filled in the alloy sheath in a spiral structure; the lead angle of the spiral structure is less than 10 degrees; the fiber tow comprises a plurality of precursor filaments, and each precursor filament comprises a fiber and an alloy coating deposited on the surface of the fiber. The spiral-structure fiber-reinforced metal-based composite material breaks through a vertical filling mode of fibers in a traditional metal-based composite material, compared with a composite material adopting a vertical filling mode, the durable compression resistance of the composite material is remarkably improved, and the safety margin of deformation overload of the composite material when the working condition exceeds a design basic accident is improved. The durable compression resistance of the spiral structure fiber reinforced metal matrix composite material is obviously higher than that of a metal matrix composite material with vertically arranged fibers.

Description

Technical Field

[0001] The present invention belongs to the technical field of metal matrix composites, and particularly relates to a spiral structure fiber reinforced metal matrix composite and a preparation method thereof. Background Art

[0002] Continuous fiber reinforced metal matrix composites have high specific strength and specific stiffness, excellent creep resistance, fatigue resistance, and excellent machining characteristics, and have broad application prospects in high-temperature structural components of aerospace power systems. In practical applications, the vast majority of components have to bear high compressive stresses, such as the piston rod and actuator cylinder of an engine, the support rod of an aircraft landing gear, etc. Therefore, the compressive resistance performance has become a key parameter for evaluating the comprehensive mechanical properties of composites.

[0003] When subjected to load compression, the material generally undergoes an elastic deformation → plastic deformation → failure process, reaching the maximum load to cause fracture. The process in which the bearing capacity gradually decreases from the maximum load until the fracture is completely extended is considered failure, which is generally divided into four failure modes: shear failure, interlayer failure, interface failure, and kink failure. The compression failure of fiber reinforced metal matrix composites is mainly a fracture or even collapse process caused by the instability of fibers with poor local performance under high stress levels to generate shear crack propagation. The key factor to improve the compression performance of composites is to avoid brittle fracture of the reinforcing fiber. However, currently, in fiber reinforced metal matrix composites filled with a vertical structure, fiber fracture is likely to occur inside when the load exceeds the safety margin, resulting in a decrease in compressive resistance performance. Summary of the Invention

[0004] In view of this, the purpose of the present invention is to provide a spiral structure fiber reinforced metal matrix composite and a preparation method thereof. The spiral structure fiber reinforced metal matrix composite of the present invention has fibers that are not easily broken and good persistent compressive resistance performance.

[0005] The present invention provides a spiral structure fiber reinforced metal matrix composite, which is obtained by hot isostatic pressing of a preform;

[0006] The preform includes an alloy sheath and a fiber bundle filled in the alloy sheath in a spiral structure; the helix angle of the spiral structure is below 10°;

[0007] The fiber bundle includes a plurality of precursor filaments, and each precursor filament includes a fiber and a coating deposited on the surface of the fiber, and the coating includes an alloy coating.

[0008] Preferably, the helix angle is 2 - 5°.

[0009] Preferably, the material of the alloy sheath includes one or more of Ni alloy, Ti alloy, Al alloy, Cu alloy, Zr alloy, Mg alloy, and Fe alloy.

[0010] Preferably, the fiber includes one or more of SiC fiber, B fiber, and Al2O3 fiber.

[0011] Preferably, the thickness of the alloy coating is 10 - 40 μm.

[0012] Preferably, when the material of the alloy sheath is Ni alloy, the coating further includes a diffusion barrier coating, and the diffusion barrier coating includes Al film and Y2O3 film periodically deposited on the fiber surface; the thickness of the diffusion barrier coating is 0.5 - 5 μm.

[0013] Preferably, the diameter of the precursor wire is 100 - 200 μm.

[0014] The present invention also provides a method for preparing the spiral structure fiber reinforced metal matrix composite material described in the above technical solution, including the following steps:

[0015] Deposit an alloy coating on the fiber to obtain a precursor wire;

[0016] Bundle the precursor wires, and fill the obtained precursor wire bundle in the alloy sheath in a spiral structure to obtain a preform;

[0017] Perform hot isostatic pressing on the preform to obtain a spiral structure fiber reinforced metal matrix composite material.

[0018] Preferably, before performing hot isostatic pressing, it further includes: welding and encapsulating the preform.

[0019] Preferably, when the material of the alloy sheath is Ni alloy or Fe alloy, the temperature of the hot isostatic pressing is 1000 - 1200 °C, the pressure is 140 - 180 MPa, and the holding time under pressure is 100 - 150 min; when the material of the alloy sheath is Ti alloy, the temperature of the hot isostatic pressing is 900 - 1000 °C, the pressure is 135 - 170 MPa, and the holding time under pressure is 100 - 150 min; when the material of the alloy sheath is Al alloy, Cu alloy, Zr alloy, or Mg alloy, the temperature of the hot isostatic pressing is 550 - 750 °C, the pressure is 115 - 150 MPa, and the holding time under pressure is 100 - 150 min.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] The present invention provides a spiral-structured fiber-reinforced metal matrix composite material, which is obtained by hot isostatic pressing of a preform; the preform includes an alloy sheath and a fiber bundle filled in the alloy sheath in a spiral structure; the spiral angle of the spiral structure is below 10°; the fiber bundle includes a plurality of precursor filaments, and each precursor filament includes a fiber and a coating deposited on the surface of the fiber, and the coating includes an alloy coating.

[0022] The spiral-structured fiber-reinforced metal matrix composite material of the present invention is obtained by hot isostatic pressing of a fiber bundle arranged in a spiral structure and an alloy sheath. The spiral-structured fiber-reinforced metal matrix composite material of the present invention breaks the traditional vertical filling method of fibers inside metal matrix composite materials. Compared with the composite material with a vertical filling method, the compressive resistance performance is significantly improved, and the safety margin of the deformation overload when the working condition exceeds the design basic accident of the composite material is increased. The results of the examples show that the internal fibers of the compressive-resistant spiral-structured fiber-reinforced metal matrix composite material of the present invention still maintain a complete structure when the compressive strain is 22%, and the persistent compressive resistance performance is significantly higher than that of the metal matrix composite material with vertically arranged fibers.

[0023] The present invention also provides a preparation method of the spiral-structured fiber-reinforced metal matrix composite material. The prepared composite material has excellent compressive resistance performance, meets the requirements of high compressive resistance performance of materials such as the piston rod and actuator cylinder of the engine, and the support rod of the aircraft landing gear, and has important significance for the research and development of new composite materials. Moreover, the preparation method provided by the present invention has simple process and high repeatability, and can be mass-produced industrially. Description of the Drawings

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required to be used in the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0025] Figure 1 It is a flowchart for preparing the spiral-structured fiber-reinforced metal matrix composite material of the present invention;

[0026] Figure 2 It is a schematic diagram of the spiral-structured fiber of the present invention forming a continuous elastic rigid body;

[0027] Figure 3 It is the stress-strain curve of the test specimens of Comparative Examples 1-2 and Example 1;

[0028] Figure 4 It is the CT non-destructive detection image of the specimen filled with a vertical structure for Comparative Specimen 2;

[0029] Figure 5CT non-destructive testing diagram of the specimen filled with a spiral structure for Example 1. Detailed implementation manners

[0030] The present invention provides a spiral structure fiber-reinforced metal matrix composite material, which is obtained by hot isostatic pressing of a preform;

[0031] The preform includes an alloy sheath and a fiber bundle filled in the alloy sheath in a spiral structure; the helix angle of the spiral structure is 10° or less;

[0032] The fiber bundle includes a plurality of precursor filaments, and each precursor filament includes a fiber and a coating deposited on the surface of the fiber, and the coating includes an alloy coating.

[0033] In the present invention, unless otherwise specified, the materials and equipment used are all commercially available products in the art.

[0034] In the present invention, the material of the alloy sheath preferably includes one or more of Ni alloy, Ti alloy, Al alloy, Cu alloy, Zr alloy, Mg alloy and Fe alloy.

[0035] In the present invention, the inner diameter of the alloy sheath is preferably 1-4 mm, specifically 2 mm or 3 mm. The size of the alloy sheath is preferably: outer diameter 6 mm, inner diameter 2 mm, depth 40 mm; the alloy sheath includes a plug, and the size of the plug is preferably: diameter 2 mm, length 5 mm.

[0036] In the present invention, the helix angle of the spiral structure is preferably 2-5°.

[0037] In the present invention, the fiber preferably includes one or more of SiC fiber, B fiber and Al2O3 fiber. The diameter of the fiber is preferably 50-150 μm, specifically 98.5 μm or 100 μm.

[0038] In the present invention, the composition of the alloy coating is preferably the same as or similar to that of the alloy sheath, which will not be elaborated here. The thickness of the alloy coating is preferably 10-40 μm, specifically 25 μm.

[0039] In the present invention, when the material of the alloy sheath is Ni alloy, the coating further includes a diffusion barrier coating. The diffusion barrier coating is disposed between the fiber and the alloy coating. The diffusion barrier coating preferably includes Al films and Y2O3 films periodically deposited on the surface of the fiber, and the cycle period of the Al films and Y2O3 films is preferably 10. The thickness of the diffusion barrier coating is preferably 0.5-5 μm, specifically 1.5 μm. The diffusion barrier coating can inhibit the interfacial reaction between the fiber and the alloy coating or change the wettability to improve the interfacial strength.

[0040] In the present invention, the diameter of the precursor wire is preferably 100 to 200 μm, and specifically may be 150 μm.

[0041] The present invention also provides a method for preparing the spiral structure fiber-reinforced metal matrix composite material according to the above technical solution, including the following steps:

[0042] Deposit an alloy coating on the surface of the fiber to obtain a precursor wire;

[0043] Bundle the precursor wires, and fill the obtained precursor wire bundle into an alloy sheath in a spiral structure to obtain a preform;

[0044] Perform hot isostatic pressing on the preform to obtain a spiral structure fiber-reinforced metal matrix composite material.

[0045] In the present invention, an alloy coating is deposited on the surface of the fiber to obtain a precursor wire.

[0046] In the present invention, the deposition is preferably physical vapor deposition (PVD). The present invention has no special requirements for the physical vapor deposition, and specifically, an alloy coating can be obtained by sputtering an alloy target.

[0047] In the present invention, preferably before the deposition, it further includes: depositing a diffusion barrier coating on the surface of the fiber; the deposition is preferably performed by physical vapor deposition.

[0048] After obtaining the precursor wire, the present invention bundles the precursor wires, fills the obtained precursor wire bundle into an alloy sheath in a spiral structure, and performs hot isostatic pressing to obtain a spiral structure fiber-reinforced metal matrix composite material.

[0049] In the present invention, when the inner diameter of the alloy sheath is 2 mm, the precursor wire bundle preferably includes 150 to 250 precursor wires; when the inner diameter of the alloy sheath is 3 mm, the precursor wire bundle preferably includes 300 to 450 precursor wires.

[0050] In the present invention, the fiber wire bundle filled into the alloy sheath in a spiral structure is obtained by spirally twisting the precursor wire bundle.

[0051] In the present invention, preferably before performing hot isostatic pressing, it further includes: welding and encapsulating the preform; the welding is preferably electron beam welding.

[0052] In the present invention, the parameters of hot isostatic pressing are adjusted according to the material of the alloy sheath. When the material of the alloy sheath is Ni alloy or Fe alloy, the temperature of hot isostatic pressing is preferably 1000 - 1200 °C, specifically it can be 1050 °C, the pressure is preferably 140 - 180 MPa, specifically it can be 150 MPa, and the holding time under pressure is preferably 100 - 150 min, specifically it can be 120 min; when the material of the alloy sheath is Ti alloy, the temperature of hot isostatic pressing is preferably 900 - 1000 °C, the pressure is preferably 135 - 170 MPa, and the holding time under pressure is preferably 100 - 150 min; when the material of the alloy sheath is Al alloy, Cu alloy, Zr alloy or Mg alloy, the temperature of hot isostatic pressing is preferably 550 - 750 °C, the pressure is preferably 115 - 150 MPa, and the holding time under pressure is preferably 100 - 150 min. During the hot isostatic pressing process, dense bonding is achieved between the precursor filaments, between the precursor filaments and the alloy sheath.

[0053] Figure 1 FIG. is a flow chart for preparing the spiral - structured fiber - reinforced metal - matrix composite material of the present invention. After depositing an alloy coating on the fiber surface, a precursor filament bundle is obtained by bundling. It is filled in the alloy sheath (sleeve) in a spiral structure, encapsulated and hot - pressed to obtain the composite material. The anti - compression spiral - structured fiber - reinforced metal - matrix composite material provided by the present invention breaks the traditional vertical filling method of fibers inside the metal - matrix composite material. Compared with the composite material with the vertical filling method, its persistent anti - compression performance is significantly improved, and the safety margin for the deformation overload of the traditional composite material when the working condition exceeds the design - based accident is increased.

[0054] During the forming and processing of the fiber - reinforced metal - matrix composite material, due to the filling of the precursor filaments and hot isostatic pressing (non - uniform shrinkage of the matrix), the fibers are prone to undergo a certain degree of torsion, and an angle (i.e., the misalignment angle (θ)) is easily formed between the fibers and the loading direction. When θ = 0, the compressive strength of the composite material is the largest. When θ>0, the compressive strength of the composite material gradually decreases as the θ angle increases. Therefore, it is generally considered that the presence of a misalignment angle in the fibers of the composite material will deteriorate its compressive performance. However, compared with the vertical - structured filling of fibers in the composite material, when all the fibers have the same - direction misalignment angle θ (i.e., the helix angle), the overall morphology of the fiber filament bundle shows a spiral structure. In this spiral structure, a single fiber can be regarded as a rigid "spring", and a circle of helically - tightly - fitted fibers at the same distance from the axis forms a multi - level reinforced "spring", and multiple circles of "springs" at different distances from the axis form a continuous elastic rigid body (such as Figure 2As shown. Although introducing the misalignment angle θ may sacrifice some of the strength enhancement advantages, during the compression loading process, the elastic continuous rigid body composed of helical structure fibers, depending on the loading angle, composition, and interface characteristics, remains elastic while adapting to plastic deformation when the alloy matrix undergoes plastic deformation. At the same time, under the axial load, additional force support in the helical direction is added between adjacent fibers, which can avoid a large number of shear yields and interface slips parallel to the fiber axis, thus preventing the fibers from being crushed and resulting in a collapse fracture, and can significantly enhance the sustained compression performance of the composite material.

[0055] To further illustrate the present invention, the helical structure fiber-reinforced metal matrix composite material and its preparation method provided by the present invention will be described in detail below with reference to the accompanying drawings and embodiments, but they should not be construed as limiting the protection scope of the present invention.

[0056] Comparative Example 1

[0057] A pure alloy was used for compression testing. The pure alloy was a Ni alloy with the grade GH4738.

[0058] The dimensions of the alloy specimen were: Φ4mm×8mm, the compression deformation was 22%, the compression rate was 0.1mm / min, and the holding time was 30s.

[0059] The stress-strain curve of the pure alloy specimen during the compression process is as Figure 2 shown. Its compression strength showed an increasing trend. The compression strength increased rapidly in the 0% - 10% stage and increased slowly in the 10% - 22% stage, and the maximum compression strength was ~2100MPa.

[0060] Comparative Example 2

[0061] A fiber-reinforced metal matrix composite material with a vertical structure filling was used. The fibers were SiC fibers provided by Beijing Institute of Aeronautical Materials, AECC. The alloy was a Ni alloy with the grade GH4738, and the diffusion barrier coating was an Al / Y2O3 multilayer film. The specific preparation method was as follows:

[0062] 1. The SiC fibers were woven into a ribbon of 150mm×75mm (spacing 0.5mm) and then installed in a PVD device to start coating.

[0063] 2. An Al / Y2O3 multilayer film (coating) was deposited on the surface of the SiC fiber ribbon in step 1, with Al:Y2O3 = 50nm:100nm, and 10 cycles were repeated.

[0064] 3. A GH4738 alloy coating was continuously deposited on the surface of the multilayer film obtained in step 2 to obtain a precursor wire. The thickness of the GH4738 alloy coating was ~25μm, and the diameter of the precursor wire was ~150μm.

[0065] 4. Cut the precursor fiber prepared in step 3 into small segments of 35 mm, and neatly arrange them into a precursor fiber bundle to be filled in a GH4738 alloy sheath in a vertical structure to obtain a preform. Sheath dimensions: outer diameter 6 mm, inner diameter 2 mm, depth 40 mm. Sheath plug: diameter 2 mm, length 5 mm.

[0066] 5. Weld the preform prepared in step 4 by electron beam welding.

[0067] 6. Obtain a composite material by hot isostatic pressing of the preform welded in step 5. Hot isostatic pressing parameters: 1050 °C / 150 MPa / 120 min.

[0068] 7. Process the composite material into a compression specimen of Φ4 mm × 8 mm for axial compression testing. Compression deformation 22%, compression rate 0.1 mm / min, holding time 30 s. <s

[0069] The stress-strain curve during the compression process is as Figure 2 shown. The compression strength increases rapidly in the 0 - 8.5% stage, increases slowly in the 8.5% - 17.5% stage, and the stress shows a significant decrease when the compression amount reaches 17.5%. The maximum compression strength is ~3000 MPa.

[0070] Perform CT non-destructive testing on the compressed specimen of Comparative Example 2. The results are as Figure 4 shown, where a1 is the overall distribution diagram of the internal fibers, a2 is the bird's-eye view of the internal fibers along Plane 1, a3 is the bird's-eye view of the internal fibers along Plane 2, b1 is the overall rendering diagram of the internal fibers, b2 is the axial section of the overall rendering diagram of the internal fibers, and b3 is the double-section of the local area of the overall rendering diagram of the internal fibers. It can be clearly seen that although the maximum compression strength can reach ~3000 MPa, the internal fibers of the composite material break after compression, resulting in a significant decrease in the compression strength of this sample.

[0071] Example 1

[0072] For the fiber-reinforced metal matrix composite material filled with a spiral structure, the fiber is SiC fiber provided by Beijing Institute of Aeronautical Materials, AECC, the alloy is Ni alloy with the grade GH4738, and the diffusion barrier coating is an Al / Y2O3 multi-layer film. The specific preparation method is as follows:

[0073] 1. Weave the SiC fiber into a ribbon of 150 mm × 75 mm (spacing 0.5 mm), and then install it in the PVD equipment to start coating.

[0074] 2. Deposit an Al / Y2O3 multi-layer film on the surface of the SiC fiber tape in step 1, with Al:Y2O3 = 50 nm:100 nm, and cycle 10 times.

[0075] 3. Continuously deposit a GH4738 alloy coating on the surface of the multi-layer film obtained in Step 2 to obtain a precursor wire, with the thickness of the GH4738 alloy coating being ~25 μm and the diameter of the precursor wire being ~150 μm.

[0076] 4. Cut the precursor wire prepared in Step 3 into small segments of 35 mm, neatly arrange them into a precursor wire bundle, and fill it in the GH4738 alloy sheath in a helical structure. The helix angle is 2 - 5°. Sheath dimensions: outer diameter 6 mm, inner diameter 2 mm, depth 40 mm. Sheath plug: diameter 2 mm, length 5 mm.

[0077] 5. Weld the sheath prepared in Step 4 by electron beam welding.

[0078] 6. Obtain a composite material by hot isostatic pressing the welded sheath in Step 5. Hot isostatic pressing parameters: 1050 °C / 150 MPa / 120 min.

[0079] 7. Process the composite material into a compression specimen of Φ4 mm × 8 mm for axial compression testing, with a compression deformation of 22%, a compression rate of 0.1 mm / min, and a holding time of 30 s.

[0080] The stress-strain curve during the compression process is as Figure 2 shown. The compression strength rapidly increases in the 0 - 7.5% stage, and continuously slowly increases in the 7.5% - 22% stage. No fracture occurs during the whole process, and the maximum compression strength is ~3000 MPa.

[0081] Perform CT non-destructive testing on the specimen after compression in Example 1. The results are as Figure 5 shown, where a1 is the overall distribution diagram of internal fibers, a2 is the inclined distribution diagram of internal fibers, a3 is the bird's-eye view of internal fibers, b1 is the overall rendering diagram of internal fibers, b2 is the local rendering diagram of internal fibers, and b3 is the double-section of the local rendering diagram of internal fibers. It can be clearly seen that no fracture similar to that in Comparative Example 2 occurs inside the composite material after compression. During the compression process, the internal fibers adapt to plastic deformation through their own torsion, and the greater the compression amount, the higher the degree of torsion, showing good compression resistance.

[0082] The present invention adopts magnetron sputtering technology, deposits an alloy coating on the fiber surface with a metal alloy as the sputtering target to obtain a precursor wire, then fills the precursor wire bundle in the alloy sheath in a helical structure, and after electron beam welding and encapsulation, performs hot isostatic pressing to obtain a fiber-reinforced metal matrix composite material with a helical structure, improving the long-term compression resistance of the composite material.

[0083] Although the above embodiments have described the present invention in detail, they are only a part of the embodiments of the present invention, rather than all embodiments. People can also obtain other embodiments according to the embodiments of the present invention without creative work, and these embodiments all fall within the protection scope of the present invention.

Claims

1. A spiral structure fiber-reinforced metal matrix composite material, characterized in that, Obtained from a preform by hot isostatic pressing; The preform includes an alloy sheath and a fiber tow filled in the alloy sheath in a helical structure; the helix angle of the helical structure is 10° or less; The fiber tow includes a plurality of precursor filaments, and each precursor filament includes a fiber and a coating deposited on the surface of the fiber, and the coating includes an alloy coating.

2. The spiral structure fiber-reinforced metal matrix composite material according to claim 1, wherein, The helix angle is 2 - 5°.

3. The spiral structure fiber reinforced metal matrix composite material according to claim 1, characterized in that, The material of the alloy sheath includes one or more of Ni alloy, Ti alloy, Al alloy, Cu alloy, Zr alloy, Mg alloy, and Fe alloy.

4. The spiral structure fiber-reinforced metal matrix composite material according to claim 1, characterized in that The fiber includes one or more of SiC fiber, B fiber, and Al2O3 fiber.

5. The spiral structure fiber reinforced metal matrix composite material according to claim 1 or 4, characterized in that, The thickness of the alloy coating is 10 - 40 μm.

6. The spiral structure fiber reinforced metal matrix composite material according to claim 1, wherein When the material of the alloy sheath is Ni alloy, the coating further includes a diffusion barrier coating, and the diffusion barrier coating includes an Al film and a Y2O3 film periodically deposited on the surface of the fiber; the thickness of the diffusion barrier coating is 0.5 - 5 μm.

7. The spiral structure fiber reinforced metal matrix composite material according to claim 1, characterized in that, The diameter of the precursor filament is 100 - 200 μm.

8. The preparation method of the spiral structure fiber reinforced metal matrix composite material according to any one of claims 1 to 7, characterized in that, Including the following steps: Depositing an alloy coating on the surface of the fiber to obtain a precursor filament; Clustering the precursor filaments, and filling the obtained precursor filament bundle in the alloy sheath in a helical structure to obtain a preform; Performing hot isostatic pressing on the preform to obtain a helical structure fiber reinforced metal matrix composite.

9. The preparation method according to claim 8, characterized in that, Before performing hot isostatic pressing, it further includes: welding and encapsulating the preform.

10. The preparation method according to claim 8, characterized in that, When the material of the alloy sheath is Ni alloy or Fe alloy, the temperature of the hot isostatic pressing is 1000 - 1200 °C, the pressure is 140 - 180 MPa, and the holding time under pressure is 100 - 150 min; when the material of the alloy sheath is Ti alloy, the temperature of the hot isostatic pressing is 900 - 1000 °C, the pressure is 135 - 170 MPa, and the holding time under pressure is 100 - 150 min; when the material of the alloy sheath is Al alloy, Cu alloy, Zr alloy, or Mg alloy, the temperature of the hot isostatic pressing is 550 - 750 °C, the pressure is 115 - 150 MPa, and the holding time under pressure is 100 - 150 min.

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