A forming die and forming method for a multi-wave-ridge structure part of an aero-engine

Abstract

The application relates to a multi-wave-ridge structure part forming die and forming method for an aero-engine, and belongs to the technical field of sheet metal forming. The die comprises: an upper die assembly, which comprises a split structure upper die; a lower die assembly, which comprises a lower die and forms a multi-wave-ridge part by closing with the upper die. The lower die is a whole concave die, and the upper die is a split convex die, which comprises a plurality of parallel arranged convex die units, each of which is provided with a separate driving device, and the driving device is a nitrogen spring, so as to drive the convex die unit to form a ladder shape. When the part is formed, the split convex die is a ladder structure, so that the whole concave die forms a multi-wave-ridge part. The upper die, that is, the convex die in the application adopts a multi-point floating split convex die structure, so that the material can flow more smoothly at the gap of the convex die unit, and the forming difficulty is solved.

Description

Technical Field

[0001] This invention belongs to the field of sheet metal forming technology, and in particular relates to a forming mold and forming method for multi-corrugated structural parts for aero-engines. Background Technology

[0002] Heat shields are critical components of aircraft engines, primarily used for heat insulation and protection in high-temperature environments. This part is made of high-temperature alloy sheet metal and is a typical sheet metal component, featuring a continuous corrugated structure, such as... Figure 1-2 As shown. However, due to the large surface area and complex structure of the parts, the following technical challenges exist in traditional forming processes:

[0003] First, material flow is difficult, resulting in a high cracking rate during forming: the corrugated structure in the middle area of ​​the part does not receive enough material during the forming process, leading to stress concentration and a high cracking rate during one-time forming, making it impossible to directly process qualified products.

[0004] Secondly, the processing efficiency is low: the existing process can only adopt a step-by-step forming method, and can only form 3 continuous corrugations at a time. The production cycle is long and cannot meet the needs of mass production of aero engines.

[0005] Therefore, there is an urgent need for a new mold and forming method that can realize multi-wave structure in order to improve the part qualification rate and production efficiency, and meet the high performance and high reliability manufacturing requirements of aero-engines. Summary of the Invention

[0006] To address the shortcomings of existing technologies, this invention provides a forming mold and forming method for multi-wave structure parts for aero engines, thereby improving product quality and efficiency.

[0007] A forming mold for a multi-corrugated structural part for an aero-engine, comprising:

[0008] Upper mold assembly, including a split-structure upper mold;

[0009] The lower mold assembly includes a lower mold, which is molded together with the split-structure upper mold to form a multi-ribbed structural part.

[0010] The upper die is a split punch, which includes multiple punch units arranged in parallel. Each punch unit is equipped with a separate driving device. When forming multi-corrugated parts, the split punch has a stepped structure.

[0011] The driving device is a nitrogen spring.

[0012] The upper mold assembly also includes an upper mold base and an upper mold connected sequentially from top to bottom, with a split punch installed at the bottom of the upper mold.

[0013] The lower mold is an integral concave mold.

[0014] The lower mold assembly also includes a lower mold base disposed opposite to the upper mold base, and the lower mold base is mounted on the forming equipment; a lower mold is mounted on the lower mold base, and the lower mold is mounted on the lower mold and disposed opposite to the upper mold.

[0015] A limit component is provided between the upper mold assembly and the lower mold assembly to limit the displacement of the upper mold assembly and the lower mold assembly.

[0016] A guide component is provided between the upper mold assembly and the lower mold assembly.

[0017] It includes an inner guide pillar and an outer guide pillar. The inner guide pillar is set on the upper mold assembly, and the lower mold assembly has a guide hole corresponding to the inner guide pillar. The outer guide pillar is set on the outside of the inner guide pillar and installed on the lower mold assembly. The upper mold assembly has a guide hole corresponding to the outer guide pillar, and a guide sleeve is installed in the guide hole to guide the mold closing.

[0018] A method for forming a multi-wave structure part for an aero-engine, using the aforementioned forming mold for a multi-wave structure part for an aero-engine, specifically includes the following steps:

[0019] Place the forming mold for the multi-corrugated structure parts of the aero-engine onto the forming equipment;

[0020] Correct;

[0021] The forming mold for multi-corrugated structural parts of aero engines is fixed on the forming equipment by a pressure plate;

[0022] Drive the forming equipment and open the mold;

[0023] Clean the working surface of the forming mold for multi-corrugated structural parts for aircraft engines;

[0024] The cut raw material is placed on the concave mold of the forming mold for multi-corrugated structural parts for aero engines and positioned by the positioning block;

[0025] The forming equipment is operated, the upper mold assembly moves downward, the split punches contact the blank in sequence, and finally the mold is closed to complete the forming of the multi-corrugated structure part;

[0026] Remove the multi-faceted structure parts and complete the dimensional inspection.

[0027] By employing the above technical solution, the present invention has at least the following beneficial effects:

[0028] The upper die, i.e. the punch, in this invention adopts a multi-point floating split punch structure, which allows the material to flow more smoothly in the gaps between the punch units, thus solving the forming problem.

[0029] The technical solution of this invention is applied to heat shield parts for aero-engines. It utilizes a stepped, split-die die to form the heat shield parts sequentially from the center corrugated edge outwards, ensuring smooth material flow during the forming of each corrugated edge. This improves part processing efficiency and meets design drawing requirements. The forming mold and method provided by this invention are applied to the forming process of heat shield parts for aero-engines, solving the forming quality problem of heat shield parts, reducing the tight matching cycle caused by single-piece issues, and improving product quality, efficiency, and forming qualification rate. Attached Figure Description

[0030] Figure 1 This is the front view of the heat insulation screen component;

[0031] Figure 2 This is a top view of the heat insulation screen components;

[0032] Figure 3 The front view of the heat shield part processed by the forming mold for the multi-corrugated structure part of the aero-engine provided by the present invention;

[0033] Figure 4 A cross-sectional view of a heat shield part being machined using a forming mold for a multi-corrugated structure part of an aero-engine, provided by the present invention.

[0034] in:

[0035] 1-Upper mold base, 2-Lower mold base, 3-Upper mold, 4-Lower mold, 5-Outer guide pillar, 6-Inner guide pillar, 7-Guide sleeve, 8-Guide pillar spring, 9-Separate punch, 10-Integral die, 11-Positioning block, 12-Upper limit block, 13-Lower limit block, 14-Nitrogen spring. Detailed Implementation

[0036] To better explain and facilitate understanding of the present invention, the technical solution and effects of the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0037] Example 1

[0038] A forming mold for a multi-corrugated structural parts for aero-engines includes an upper mold assembly and a lower mold assembly arranged opposite each other. The upper mold assembly includes an upper mold base 1, and the lower mold assembly includes a lower mold base 2 arranged opposite to the upper mold base 1. The upper mold base 1 serves as the basic support for the upper mold 3, used to fix the upper mold 3, withstand the pressure during the forming process, and maintain stability. The upper mold 3 is installed at the bottom of the upper mold base 1 by screws to fix the punch. The lower mold base 2 serves as the main support and connecting component, used to connect to the lower platform of the machine tool and fix the lower mold 4, and cooperates with the upper mold base 1. The lower mold 4 is installed on the upper part of the lower mold base 2 by screws to fix the die, and is arranged opposite to the upper mold 3.

[0039] The upper mold 3 has a split punch 9 installed at its bottom for forming multi-wave structure, specifically in the middle position of the upper mold 3. Opposite to the split punch 9 is an integral die 10 for forming multi-wave structure. In this embodiment, the integral die 10 is installed on the lower mold 4 via precision bolts, specifically in the middle position of the lower mold 4. The split punch 9 and the integral die 10 form a forming cavity. The lower mold 4 is provided with positioning blocks 11 for fixing the part blank. In this embodiment, four positioning blocks 11 are distributed on the lower mold 4 and connected to the lower mold 4 via screws.

[0040] The split punch 9 is a multi-point floating split punch structure to form a stepped structure, thereby forming a multi-wave structure part with the integral die 10. Specifically, the split punch 9 includes multiple punch units arranged in parallel. A nitrogen spring 14 is provided between the upper end face of each punch unit and the upper die 3 to drive the split punch 9. The multi-point floating split punch structure can design the material flow path according to the shape and forming requirements of the part, effectively avoiding local material accumulation or poor flow that may occur with the integral punch structure during the forming process. Simultaneously, the punch units of the split punch structure can disperse the stress generated during the forming process, allowing stress to be transmitted and distributed over a larger area, reducing local stress peaks, and thus reducing the possibility of part breakage. Furthermore, the split structure provides elastic deformation space between each punch unit. Under forming pressure, the split punch 9 can undergo a certain degree of elastic displacement or deformation. This local elastic deformation can adapt to the material flow requirements, ensuring good contact between the die and the material, and preventing part breakage due to local separation or excessive compression between the die and the material.

[0041] like Figure 3-4 As shown, in this embodiment, for processing heat shield parts for aero-engines, a nitrogen spring 14 drives the punch unit, causing the split punch 9 to form a stepped structure with a lower center and higher sides. The punch at the center corrugated edge contacts the material surface first and forms the corrugated edge sequentially from the center corrugated edge to the sides, ensuring smooth material flow during the forming of each corrugated edge. Each punch unit is designed with an individual nitrogen spring at the top. After the center corrugated edge is formed, the nitrogen spring is compressed as the die descends, causing the punch units on both sides to contact the material sequentially, forming each corrugated edge in sequence. This ensures smooth material flow during each forming process, guaranteeing the forming accuracy of the heat shield parts, simplifying the operation process, and improving production efficiency.

[0042] To limit the displacement of the upper and lower mold assemblies, a limiting component is provided between them, including an upper limit block 12 located at the bottom of the upper mold base 1 and a lower limit block 13 located on the upper part of the lower mold base 2, with the upper limit block 12 and lower limit block 13 positioned opposite each other. In this embodiment, the upper limit blocks 12 are mounted on the upper mold base 1 with screws, symmetrically installed on both sides, two on each side, for a total of four; the lower limit blocks 13 are mounted on the lower mold base 2 at positions corresponding to the upper limit blocks 12, and there are also four lower limit blocks 13. The limiting component also serves as a safety device, preventing violent collisions between the upper and lower molds when the drive mechanism malfunctions. The limiting component can withstand unexpected impact forces to a certain extent, preventing damage to the mold and forming equipment.

[0043] To ensure precise alignment of the upper and lower mold components and improve forming accuracy, a guide assembly, including inner guide pillars 6 and outer guide pillars 5, is provided between the upper and lower mold components. The inner guide pillars 6 are mounted on the upper mold 3 and installed in connecting holes on the bottom surface of the upper mold 3 by screws. There are four inner guide pillars 6, symmetrically distributed left and right. The lower mold 4 has guide holes corresponding to the inner guide pillars 6. During mold closing, the inner guide pillars 6 move along the guide holes, guiding the split punch 9 and the integral die 10 to close, ensuring mold closing stability and improving forming accuracy. The outer guide pillars 5 are located outside the inner guide pillars 6 and installed in connecting holes on the upper surface of the lower mold 4 by screws. There are four outer guide pillars 5, symmetrically distributed left and right. The upper mold 3 has guide holes corresponding to the outer guide pillars 5, and guide sleeves 7 are installed in the guide holes. During the downward movement of the upper mold component, the outer guide pillars 5 move within the guide sleeves 7, and the guide sleeves 7 and outer guide pillars 5 cooperate to guide the upper mold 3 and lower mold 4 to close. The outer guide post 5 is equipped with a guide post spring 8, which is used to separate the upper mold 3 and the lower mold 4 when the hydraulic pressure is removed.

[0044] A method for forming a multi-corrugated structural part for an aero-engine, using the aforementioned forming mold for the multi-corrugated structural part for an aero-engine, specifically includes the following steps:

[0045] The forming mold for multi-corrugated structure parts of aero engines is placed on the lower platform of the machine tool;

[0046] Align the forming mold for multi-wave structure parts for aero engines to ensure that the position of the forming mold meets the machine tool requirements;

[0047] A pressure plate is used to fix the forming mold of the multi-corrugated structure part of the aircraft engine onto the lower platform of the machine tool.

[0048] Drive the machine tool to open the forming mold for the multi-corrugated structure parts of the aero-engine;

[0049] Clean the working surfaces of the upper mold 3 and lower mold 4 of the forming mold for multi-corrugated structural parts for aero engines to prevent foreign objects from entering the working area of ​​the forming mold for multi-corrugated structural parts for aero engines.

[0050] The cut raw material is placed on the integral cavity 10 of the forming mold for multi-corrugated structural parts of aero-engines, and positioned by the positioning block 11 to prevent the part from shifting or rotating.

[0051] As the machine tool is running, the upper mold assembly moves downward. As the split punches 9 contact the blank in sequence, the nitrogen springs 14 are also compressed in sequence. Finally, the mold closes to complete the sheet metal forming.

[0052] Remove the part and complete the dimensional inspection.

[0053] Example 2

[0054] In this embodiment, the punch unit is driven by a nitrogen spring 14. The split punch 9 forms a stepped structure with one side higher than the other. During the downward movement of the upper die, the split punch 9 contacts the blank sequentially from the lowest side. The remaining structural settings and forming methods of this embodiment are exactly the same as those of Embodiment 1.

Claims

1. A forming mold for a multi-corrugated structural part for an aero-engine, characterized in that, include: Upper mold assembly, including a split-structure upper mold; The lower mold assembly includes a lower mold, which is molded together with the split-structure upper mold to form a multi-ribbed structural part; The upper die is a split punch, which includes multiple punch units arranged in parallel. Each punch unit is equipped with a separate driving device. When forming multi-corrugated parts, the split punch has a stepped structure.

2. The forming mold for a multi-wave structure part for an aero-engine according to claim 1, characterized in that: The driving device is a nitrogen spring.

3. The forming mold for a multi-wave-shaped structural part for an aero-engine according to claim 1, characterized in that: The upper mold assembly also includes an upper mold base and an upper mold connected sequentially from top to bottom, with a split punch installed at the bottom of the upper mold.

4. The forming mold for a multi-wave-shaped part for an aero-engine according to claim 1, characterized in that: The lower mold is an integral concave mold.

5. A forming mold for a multi-wave-shaped structural part for an aero-engine according to claim 3, characterized in that: The lower mold assembly also includes a lower mold base disposed opposite to the upper mold base, and the lower mold base is mounted on the forming equipment; a lower mold is mounted on the lower mold base, and the lower mold is mounted on the lower mold and disposed opposite to the upper mold.

6. The forming mold for a multi-wave structure part for an aero-engine according to claim 1, characterized in that: A limit component is provided between the upper mold assembly and the lower mold assembly to limit the displacement of the upper mold assembly and the lower mold assembly.

7. A forming mold for a multi-wave-shaped structural part for an aero-engine according to claim 1, characterized in that: A guide component is provided between the upper mold assembly and the lower mold assembly.

8. A forming mold for a multi-wave-shaped structural part for an aero-engine according to claim 7, characterized in that: It includes an inner guide pillar and an outer guide pillar. The inner guide pillar is set on the upper mold assembly, and the lower mold assembly has a guide hole corresponding to the inner guide pillar. The outer guide pillar is set on the outside of the inner guide pillar and installed on the lower mold assembly. The upper mold assembly has a guide hole corresponding to the outer guide pillar, and a guide sleeve is installed in the guide hole to guide the mold closing.

9. A method for forming a multi-corrugated structural part for an aero-engine, comprising using a forming mold for a multi-corrugated structural part for an aero-engine as described in any one of claims 1-8, characterized in that, Specifically, the following steps are included: Place the forming mold for the multi-corrugated structure parts of the aero-engine onto the forming equipment; Correct; The forming mold for multi-corrugated structural parts of aero engines is fixed on the forming equipment by a pressure plate; Drive the forming equipment and open the mold; Clean the working surface of the forming mold for multi-corrugated structural parts for aircraft engines; The cut raw material is placed on the concave mold of the forming mold for multi-corrugated structural parts for aero engines and positioned by the positioning block; The forming equipment is operated, the upper mold assembly moves downward, the split punches contact the blank in sequence, and finally the mold is closed to complete the forming of the multi-corrugated structure part; Remove the multi-faceted structure parts and complete the dimensional inspection.

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