Additive and deformation composite manufacturing device and composite component interface regulation and control method

Abstract

The invention discloses an additive and deformation composite manufacturing device and a composite component interface regulation and control method. Comprising a working cavity capable of sliding and being sealed, a female die assembly is arranged in the working cavity, a top cavity area is used for being matched with an additive tool head of additive equipment in a first time period, and the top cavity area is further used for being matched with a male die assembly of extrusion forming equipment in a second time period; and the working cavity is moved to a material adding station corresponding to the material adding tool head for material adding, and the working cavity is moved to an extrusion forming station corresponding to the male die assembly for extrusion forming. According to the method, the bonding strength of the transition layer of the dissimilar material component is improved, the compactness of the transition layer of the dissimilar material component is optimized, diffusion of the transition layer is promoted, and the strength of the additive area and the transition layer of the manufactured product is high, and the structure compactness is good.

Description

Technical Field

[0001] This invention belongs to the field of composite component interface control technology, specifically relating to an additive and deformable composite manufacturing device and a composite component interface control method. Background Technology

[0002] With increasingly stringent requirements for lightweight, multifunctional, and integrated equipment structures, there is a widespread demand for high-performance materials such as steel, titanium, and aluminum, as well as their integrated applications and the manufacture of high-performance components. For dissimilar material components such as steel / titanium and steel / aluminum, surface modification methods are currently commonly used to prepare a transition layer at the interface to block metallurgical reactions of alloying elements such as Fe, Ti, and Al. However, due to element diffusion in the transition layer, intermetallic compounds such as FeTi and FeAl can still easily form, resulting in low bonding strength and easy interface cracking, failing to meet the performance requirements of steel / titanium and steel / aluminum dissimilar material component designs.

[0003] While it's possible to manufacture dissimilar material components using modular manufacturing methods (such as laser additive manufacturing and friction stir additive manufacturing), the resulting products exhibit poor performance consistency and low material utilization, making it difficult to meet the requirements for manufacturing precision, high-performance components. Furthermore, the transition layer still suffers from low bonding strength and poor microstructure density. In addition, current technological approaches, considering the connection strength of dissimilar material components, typically require the transition layer to be designed in the non-abrupt transition region (the region where dimensions do not change), but this cannot meet the structural layout requirements of certain precision, high-performance dissimilar material components. Summary of the Invention

[0004] At least in response to the problems mentioned in the background art, the present invention aims to provide an additive and deformable composite manufacturing apparatus and a method for controlling the interface of composite components.

[0005] The present invention adopts the following technical solution.

[0006] An additive and deformable composite manufacturing apparatus includes a sliding and sealing working chamber. A die assembly is disposed in the working chamber. The cavity of the die assembly includes, from bottom to top, a laterally variable cavity region, a diameter-reducing cavity region, and a top cavity region. The top cavity region is used to cooperate with the additive tool head of the additive equipment in a first time period, and the top cavity region is also used to cooperate with the punch assembly of the extrusion molding equipment in a second time period.

[0007] Furthermore, the die assembly includes a base plate, two pads, a lower die, a left die, a right die, an upper die, and a pressure plate arranged sequentially from bottom to top. The two pads are located on the left and right sides of the transversely variable cavity area, and the left and right dies are located on the left and right sides of the diameter-reducing cavity area.

[0008] Furthermore, limit plates are provided on the outer sides of the left and right dies; the punch assembly includes an outer punch and a core punch.

[0009] A method for controlling the interface of a composite component using the aforementioned additive and deformable composite manufacturing apparatus, comprising the following steps: Step 1: Place the component base in the cavity of the die assembly. At this time, the upper end of the component base is close to the middle of the cavity area with reduced diameter. Step 2: Move the working chamber to the additive manufacturing station corresponding to the additive manufacturing tool head, and then fix it in place; Step 3: Turn on the additive manufacturing equipment, set the additive manufacturing process, and perform additive forming on the top of the component substrate. After the additive manufacturing is completed, a composite component is obtained. The joint between the additive area and the component substrate is a transition layer. Step 4: Move the working chamber to the extrusion forming station corresponding to the punch assembly, and then fix it. Step 5: Under vacuum, heat the composite component to the target temperature, then turn on the extrusion molding equipment and control the outer punch and core punch to move down synchronously to the top of the composite component to perform static pressure treatment on the composite component. Step 6: Turn on the extrusion molding equipment and extrude the composite component according to the set extrusion method to complete the interface control of the composite component.

[0010] Furthermore, during the extrusion forming process of the composite component according to the set extrusion method, axial load is applied to the composite component through the outer punch and the core punch, while the left die and the right die remain stationary. Both pads are attached to the component substrate and remain stationary, and the thickness and height of the transition layer of the composite component remain unchanged at all times.

[0011] In this invention, the transition layer has an inverted frustum-shaped structure that is thicker at the top and thinner at the bottom.

[0012] To further improve the connection strength of dissimilar material components and further enhance the density of the optimized microstructure, the steps of extruding the composite component according to the set extrusion method include: Step 61: Adjust the outer punch to the target height one, and control the core punch to continue to move downward, so that the additive area becomes an intermediate concave structure; Step 62: Then adjust the core punch to the target height two, control the outer punch to continue moving downward, and the additive area becomes an intermediate convex structure; Step 63 involves repeatedly performing steps 51 and 52, ultimately extruding the additive region into a standard cylindrical structure in its initial state.

[0013] Preferably, during the extrusion molding process, the speed of metal volume transfer meets the following requirements: The conditions, among which, h 0 The initial height of the billet (mm). Material strain rate (s) -1 ), t The cumulative time (s) for the billet to deform from its initial state to its intermediate state, and the strain rate. Within 0.01 to 1 s -1 between.

[0014] To better achieve densification of the transition layer structure and element diffusion, the pressure is controlled at 50–300 MPa during the static pressing process.

[0015] In one embodiment of the present invention, the component matrix material is Al2O3, and the transition layer material is Fe. 1.7 -CrCuVNi 0.3 The additive manufacturing area uses TC21 material.

[0016] Beneficial effects: The solution of the present invention not only improves the bonding strength of the transition layer of dissimilar material components, but also optimizes the density of the transition layer of dissimilar material components and promotes the diffusion of the transition layer. The resulting product has high strength in the additive region and the transition layer, and good microstructure density. For dissimilar material components with the transition layer designed in a non-abrupt change region, the present invention can ensure that the connection strength of the transition layer meets the requirements. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the additive and deformable composite manufacturing apparatus in the embodiment (before placing the component substrate). Figure 2 This is a schematic diagram of the additive and deformable composite manufacturing apparatus in the embodiment. Figure 2 (Additive manufacturing tool head corresponds to additive manufacturing station); Figure 3 This is a schematic diagram of the additive and deformable composite manufacturing apparatus in the embodiment. Figure 3 (The punch assembly corresponds to the extrusion forming station). Figure 4 This is a schematic diagram of the interface control process of the composite component in the embodiment (application scheme 1). Figure 5 This is a schematic diagram of the interface control process of the composite component in the embodiment (application scheme 2). Detailed Implementation

[0018] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention. It should be noted that the composite component outline dimensions involved in this embodiment and the comparative embodiment are exactly the same. Example

[0019] Combination Figures 1 to 3 As shown, an additive and deformable composite manufacturing apparatus includes a sliding and sealing working chamber 13. A die assembly is disposed in the working chamber 13. The cavity of the die assembly includes, from bottom to top, a laterally variable cavity region 20, a diameter-reducing cavity region 21, and a top cavity region 22. The top cavity region 22 is used to cooperate with the additive tool head 15 of the additive equipment in a first time period. The top cavity region 22 is also used to cooperate with the punch assembly of the extrusion molding equipment in a second time period. Multiple temperature sensors 16 are disposed on the sidewall of the cavity. The die assembly includes, from bottom to top, a base plate 8, two pads 7, a lower die 6, a left die 9, a right die 10, an upper die 4, and a pressure plate 3. The two pads 7 are located on the left and right sides of the laterally variable cavity area 20, and the left die 9 and right die 10 are located on the left and right sides of the diameter-reducing cavity area 21. A left punch 11 and a right punch 12 are arranged inside the two pads 7. The left punch 11 can be laterally adjusted to the left punch closed state 11a and the left punch open state, and the right punch 12 can be laterally adjusted to the right punch closed state 12a and the right punch open state. Limiting plates 5 are provided on the outside of the left die 9 and the right die 10. The punch assembly includes an outer punch 1 and a core punch 2.

[0020] Combination Figures 1 to 4 As shown, a method for controlling the interface of a composite component using the additive and deformable composite manufacturing apparatus in this embodiment includes the following steps: Step 1: Place the component base 14a in the cavity of the die assembly. At this time, the upper end of the component base 14a is close to the middle of the cavity region 21 with a reduced diameter. Step 2: Move the working chamber 13 to the additive manufacturing station corresponding to the additive manufacturing tool head 15, and then fix it. Step 3: Turn on the additive manufacturing equipment, set the additive manufacturing process, and perform additive forming on the top of the component substrate 14a (using laser cladding additive manufacturing equipment, first add the transition layer 23, and then add the part above the transition layer 23). After the additive manufacturing is completed, a composite component is obtained. The joint between the additive region 24 and the component substrate 14a is the transition layer 23. The transition layer 23 has an inverted frustum-shaped structure that is thicker at the top and thinner at the bottom. Step 4: Move the working chamber 13 to the extrusion forming station corresponding to the punch assembly, and then fix it. Step 5: Under vacuum, heat the composite component to the target temperature, then turn on the extrusion molding equipment and control the outer punch 1 and the core punch 2 to move down synchronously to the top of the composite component to perform static pressure treatment on the composite component. During the static pressure treatment, the pressure is controlled to be 50-300MPa. Step 6: Turn on the extrusion molding equipment and extrude the composite component according to the set extrusion method to complete the interface control of the composite component. During the extrusion molding of the composite component according to the set extrusion method, the outer punch 1 and the core punch 2 apply axial load to the composite component, while the left die 9 and the right die 10 remain stationary. Both pads 7 are attached to the component substrate 14a and remain stationary. The thickness and height of the transition layer 23 of the composite component remain unchanged.

[0021] The steps of extruding the composite component according to the set extrusion method include: Step 61: Adjust the outer punch 1 to the target height 1, and control the core punch 2 to continue to move downward, so that the additive region 24 becomes a concave structure in the intermediate state, until the distance between the lower end of the core punch 2 and the top surface of the material transition layer 23 is 20±2mm. Step 62, then adjust the core punch 2 to the target height two, control the outer punch 1 to continue to move downward, and the additive region 24 becomes an intermediate convex structure until the distance between the lower end of the outer punch 1 and the top surface of the material transition layer 23 is 20±2mm; Step 63 involves repeatedly performing steps 51 and 52, finally extruding the additive region 24 into a standard columnar structure in its initial state.

[0022] During the extrusion molding process, the speed of metal volume transfer meets the following requirements. The conditions, among which, h 0 The initial height of the billet (mm). Material strain rate (s) -1 ), t The cumulative time (s) for the billet to deform from its initial state to its intermediate state, and the strain rate. Within 0.01 to 1 s -1 between.

[0023] In application scheme one of this embodiment, it is necessary to prepare such as Figure 4 The composite component shown (requiring the transition layer 23 to be positioned above the necked area of ​​the composite component, and its tensile strength not to exceed 525 MPa) has a matrix 14a made of A100 material and a transition layer 23 made of Fe material. 1.7 -CrCuVNi 0.3 The additive manufacturing region 24 is made of TC21 material. The transition layer 23 uses... Figure 4 The inverted frustum-shaped structure shown has a dovetail groove at the top. The transition layer 23 is added layer by layer according to the material composition after distribution, proceeding from bottom to top in N layers. When the length of the added layer (i.e., the width / diameter of the transition layer) is greater than the length of the previous layer, the specific dimensions are determined based on the slope of the inclined surface of the transition layer 23, and the strain rate... Controlled to 0.2s -1 After the additive forming of transition layer 23 is completed, additive manufacturing continues according to the material formulation and additive path of additive region 24 until a composite component of the designed shape is formed.

[0024] In the second application scheme of this embodiment, it is necessary to prepare such as Figure 5 The composite component shown (requiring the transition layer 23 to be positioned above the necked area of ​​the composite component, and its tensile strength not to exceed 525 MPa) has a matrix 14a made of A100 material and a transition layer 23 made of Fe material. 1.6 -CrCuVNi 0.4 The additive manufacturing region 24 is made of TC21 material. The transition layer 23 uses... Figure 5 The inverted frustum-shaped structure shown has an additive manufacturing method for the transition layer 23: after the material composition of the transition layer 23 is determined, additive manufacturing is performed layer by layer from bottom to top (N layers). When the additive length of a layer (i.e., the width / diameter of the transition layer) is greater than the additive length of the previous layer, the specific dimensions are determined based on the slope of the inclined surface of the transition layer 23, and the strain rate is calculated. Controlled to 0.3s -1 After the additive forming of transition layer 23 is completed, additive manufacturing continues according to the material formulation and additive path of additive region 24 until a composite component of the designed shape is formed.

[0025] In comparison scheme 1, the following is adopted: Figure 4 The rightmost small image shows a composite component structure. The component matrix 14a is made of A100 material, and the transition layer 23 is made of Fe. 1.7 -CrCuVNi 0.3 The additive region 24 is made of TC21, and the corresponding part of the additive region 24 is formed by casting, and step 6 in Example 1 is omitted.

[0026] In comparison scheme 2, the following is adopted: Figure 4 The rightmost small image shows a composite component structure. The component matrix 14a is made of A100 material, and the transition layer 23 is made of Fe. 1.7 -CrCuVNi 0.3 The additive region 24 is made of TC21, and the corresponding part of the additive region 24 is formed by casting, and steps 5 and 6 in Example 1 are omitted.

[0027] In comparison scheme 3, the following is adopted: Figure 4 The rightmost small image shows a composite component structure. The component matrix 14a is made of A100 material, and the transition layer 23 is made of Fe. 1.7 -CrCuVNi 0.3The additive region 24 is made of TC21. The upper end of the transition layer 23 is located on the side of the center of the upper die 4, and the lower end of the transition layer 23 is located on the side of the bottom wall of the upper die 4. The forming method of the additive region 24 and the transition layer 23 is the same as that of application scheme one.

[0028] In comparison scheme 4, the following is adopted: Figure 5 The rightmost small image shows a composite component structure. The component matrix 14a is made of A100 material, and the transition layer 23 is made of Fe. 1.7 -CrCuVNi 0.3 The additive region 24 is made of TC21, and the corresponding part of the additive region 24 is formed by casting, and step 6 in Example 1 is omitted.

[0029] In comparison scheme 5, the following is adopted: Figure 5 The rightmost small image shows a composite component structure. The component matrix 14a is made of A100 material, and the transition layer 23 is made of Fe. 1.7 -CrCuVNi 0.3 The additive region 24 is made of TC21, and the corresponding part of the additive region 24 is formed by casting, and steps 5 and 6 in Example 1 are omitted.

[0030] In comparison scheme 6, the following is adopted: Figure 5 The rightmost small image shows a composite component structure. The component matrix 14a is made of A100 material, and the transition layer 23 is made of Fe. 1.7 -CrCuVNi 0.3 The additive region 24 is made of TC21. The upper end of the transition layer 23 is located on the side of the center of the upper die 4, and the lower end of the transition layer 23 is located on the side of the bottom wall of the upper die 4. The forming method of the additive region 24 and the transition layer 23 is the same as that of application scheme 2.

[0031] In comparison scheme 7, the difference from application scheme 2 is that step 6 is omitted.

[0032] In comparison scheme 8, the difference from application scheme 2 is that step 5 is omitted.

[0033] In comparison scheme 9, the difference from application scheme 2 is that steps 5 and 6 are omitted.

[0034] Mechanical properties and grain size were tested on the composite component samples obtained from this application scheme and the comparative application scheme. The results are shown in Table 1.

[0035] Table 1 Test results of composite component samples

[0036] It is evident that, through the combined use of specific additive manufacturing, static pressing, extrusion, and transition layer placement, not only is the bonding strength of the transition layer in dissimilar material components improved, but the density of the transition layer is also optimized, promoting the diffusion of the transition layer. The resulting product exhibits high strength in both the additive manufacturing region and the transition layer, along with good microstructure density. For dissimilar material components where the transition layer is designed in a non-abrupt transition region, the connection strength of the transition layer can meet the requirements.

Claims

1. An additive and deformable composite manufacturing apparatus, comprising a sliding and sealing working chamber (13), characterized in that: A die assembly is provided in the working chamber (13). The cavity of the die assembly includes, from bottom to top, a transversely variable cavity area (20), a reduced-diameter cavity area (21), and a top cavity area (22). The top cavity area (22) is used to cooperate with the additive tool head (15) of the additive equipment in the first time period. The top cavity area (22) is also used to cooperate with the punch assembly of the extrusion molding equipment in the second time period.

2. The additive and deformable composite manufacturing apparatus according to claim 1, characterized in that: The die assembly includes a base plate (8), two pads (7), a lower die (6), a left die (9), a right die (10), an upper die (4), and a pressure plate (3) arranged sequentially from bottom to top. The two pads (7) are located on the left and right sides of the transverse variable cavity area (20), and the left die (9) and right die (10) are located on the left and right sides of the diameter reduction cavity area (21).

3. The additive and deformable composite manufacturing apparatus according to claim 2, characterized in that: Limiting plates (5) are provided on the outer sides of the left die (9) and the right die (10); the punch assembly includes an outer punch (1) and a core punch (2).

4. A method for controlling the interface of a composite component using the additive and deformable composite manufacturing apparatus of claim 3, characterized in that the steps include... include: Step 1: Place the component base (14a) in the cavity of the die assembly. At this time, the upper end of the component base (14a) is close to the middle of the cavity area (21) with a reduced diameter. Step 2: Move the working chamber (13) to the additive manufacturing station corresponding to the additive manufacturing tool head (15), and then fix it; Step 3: Turn on the additive manufacturing equipment, set the additive manufacturing process, and perform additive forming on the top of the component substrate (14a). After the additive manufacturing is completed, a composite component is obtained. The joint between the additive region (24) and the component substrate (14a) is a transition layer (23). Step 4: Move the working chamber (13) to the extrusion forming station corresponding to the punch assembly, and then fix it; Step 5: Under vacuum, heat the composite component to the target temperature, then turn on the extrusion molding equipment and control the outer punch (1) and the core punch (2) to move down to the top of the composite component to perform static pressure treatment on the composite component; Step 6: Turn on the extrusion molding equipment and extrude the composite component according to the set extrusion method to complete the interface control of the composite component.

5. The composite component interface control method according to claim 4, characterized in that: During the extrusion forming process of the composite component according to the set extrusion method, the axial load is applied to the composite component through the outer punch (1) and the core punch (2), and the left die (9) and the right die (10) remain stationary. Both pads (7) are attached to the component substrate (14a) and remain stationary. The thickness and height of the transition layer (23) of the composite component remain unchanged.

6. The composite component interface control method according to claim 5, characterized in that: The transition layer (23) has an inverted frustum-shaped structure that is thicker at the top and thinner at the bottom.

7. The composite component interface control method according to claim 6, characterized in that, The steps for extruding composite components according to a set extrusion method include: Step 61: Adjust the outer punch (1) to the target height one, and control the core punch (2) to move down continuously, so that the additive region (24) becomes a concave structure in the intermediate state; Step 62, then adjust the core punch (2) to the target height two, control the outer punch (1) to continue to move down, and the additive region (24) becomes an intermediate convex structure; Step 63, repeat steps 51 and 52 multiple times, and finally extrude the additive region (24) into a standard columnar structure in the initial state.

8. The composite component interface control method according to claim 7, characterized in that: During the extrusion deformation process, the rate of metal volume transfer must meet the following requirements. The conditions, among which, h 0 The initial height of the billet (mm). Material strain rate (s) -1 ), t The cumulative time (s) for the billet to deform from its initial state to its intermediate state, and the strain rate. Within 0.01 to 1 s -1 between.

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