Airplane engine blade forging trimming correction device and method

Abstract

The application discloses an aero-engine blade forging trimming correction device and method, the trimming correction device comprises an upper pressing edge structure, a lower pressing edge structure, a reverse material ejecting device and a punch, the pressing edge structure is designed to match the outflow trend of metal flash, and clamping teeth are added when necessary, and the die bore of the reverse material ejecting device and the punch constitutes a correction die bore. The trimming correction device shortens the traditional production process of "heating, trimming, removing protective coating, corrosion, polishing, spraying glass lubricant, heating and correction" to "spraying glass lubricant, heating and correction + trimming", greatly improves production efficiency, reduces production cost and labor intensity, further releases residual stress caused by the elastic-plastic characteristics of the material, and thus reduces subsequent heat treatment deformation.

Description

Technical Field

[0001] This invention belongs to the field of edge trimming and correction technology for aero-engine blades, and in particular, relates to an edge trimming and correction device and method for aero-engine blade forgings. Background Technology

[0002] The current production of aero-engine blade forgings requires two main processes: edge trimming and straightening. Therefore, two sets of molds need to be designed (e.g., Figure 1 , Figure 2 As shown, to match different mold bases, the production process requires two heating cycles. The production flow is: heating → trimming → removing protective coating → corrosion → grinding → spraying glass lubricant → heating → correction. The production process is long, inefficient, costly, and labor-intensive. In addition, the trimming mold lacks a pressing flash structure, which can cause problems such as flanging deformation during trimming, resulting in complex combined cross-stress effects on subsequent correction and heat treatment. Furthermore, the correction process lacks a lower stop pressure holding measure, which is relatively simple. Due to the elastic-plastic characteristics of the forging material, a large residual stress will be generated, causing the forging to deform significantly during the heat treatment process.

[0003] Currently, some blade manufacturers in China use isothermal correction in the correction process, or drag the blade edge on a conventional punch press (the conventionally cut blade edge has no support), which also achieves a certain effect in reducing edge deformation. However, isothermal correction has a slow pressing speed and low efficiency, and it also requires two main processes: edge cutting and correction. Dragging the blade edge on a conventional punch press is more efficient, but the cut flash will get stuck on the mold, which brings a lot of work to removing the flash and also requires a correction process. The long process flow can no longer meet the increasingly refined scientific research and production needs of aero-engine blades. Summary of the Invention

[0004] The present invention aims to provide an edge trimming and correction device and method for aero-engine blade forgings, which combines the two main processes of edge trimming and correction of blade forgings into one main process, thereby reducing the production process, improving production efficiency, reducing production costs and manual labor, and reducing residual stress after blade correction while reducing edge deformation, thereby reducing deformation of the forgings due to the release of residual stress during subsequent heat treatment.

[0005] The technical solution of the present invention is as follows:

[0006] An edge trimming device for aero-engine blade forgings, comprising,

[0007] The upper pressure edge structure has a lower end face that forms the upper pressure edge surface of the aero-engine blade forging, and a first hollow area is opened inside the upper pressure edge surface.

[0008] The lower pressing edge structure has an upper end face that forms the lower pressing edge surface of the aero-engine blade forging, and a second hollow area is opened inside the lower pressing edge surface.

[0009] An anti-ejection device, wherein the anti-ejection device penetrates the first hollow area of ​​the upper pressure edge structure, and the lower end of the anti-ejection device forms an upper correction mold cavity;

[0010] The punch penetrates the second hollow area of ​​the lower pressing edge structure, and the upper end of the punch forms a lower correction die cavity.

[0011] Furthermore, the aero-engine blade forging edge trimming device also includes clamping teeth, which are disposed on the upper pressure edge surface, or the lower pressure edge surface, or simultaneously on both the upper and lower pressure edge surfaces.

[0012] Furthermore, the surface shapes of the upper and lower pressure edge surfaces match the outflow trend of the metal flash of the aero-engine blade forging.

[0013] The method for edge correction of aero-engine blade forgings employs the aforementioned edge correction device and includes the following steps:

[0014] Step 1, feeding: Heat the aero-engine blade forging to the calibration temperature, and then place it on the upper end of the punch and lower pressure edge structure;

[0015] Step 2, Correction and clamping of flash: The lower pressing edge structure moves upward synchronously with the punch. The interaction between the punch and the anti-ejection device completes the shaping of the blade forging. The interaction between the lower pressing edge structure and the upper pressing edge structure completes the clamping of the flash.

[0016] Step 3, trimming: The punch and the anti-ejector device move the blade forging relative to the upper and lower pressure structures to perform precision punching and trimming, thereby separating the blade forging from the flash. During and after the trimming process, the punch and the anti-ejector device maintain pressure on the blade forging for correction.

[0017] Step 4: Remove the forging. When the upper pressure structure and the anti-ejection device return to their original positions, remove the blade forging.

[0018] Step 5: Remove the flash. When the punch returns to its original position, remove the flash left after cutting.

[0019] Alternatively, in step 1, the correction temperature is 30°C lower than the forging temperature of the blade forging.

[0020] Alternatively, in step 2, the reduction in the shape of the blade forging is 0.1 mm to 0.2 mm.

[0021] Alternatively, in step 3, the punch and the anti-ejection device maintain pressure on the blade forging during the trimming process and after the trimming is completed, for a duration of 5s to 30s.

[0022] Alternatively, step 1 can be repeated after step 5 to perform edge correction on the next blade forging.

[0023] Compared with existing technologies, this invention, through innovative design and optimized integration of traditional trimming and straightening tooling, combines the two main processes of trimming and straightening into one main process. The original production process of "heating → trimming → removing protective coating → etching → grinding → spraying glass lubricant → heating → straightening" is reduced to "spraying glass lubricant → heating → straightening + trimming" (since each main forging process basically involves the steps of removing protective coating → etching → grinding → spraying glass lubricant, reducing one main forging process reduces these steps accordingly), which greatly improves production efficiency and reduces production costs and manual labor.

[0024] The edge-correcting device of the present invention has an edge-pressing structure and a support device on the back of the forging, which can prevent the flash from turning over and deforming during the edge-cutting process.

[0025] The edge trimming correction device and method of the present invention maintains pressure on the blade forging after the edge trimming is completed by the punch and the anti-ejection device, which can release the residual stress caused by the reduction of the material's elastic-plastic properties, thereby reducing the deformation of subsequent heat treatment. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of a commonly used edge trimming die in the industry.

[0027] Figure 2 This is a schematic diagram of a commonly used calibration model in the industry.

[0028] Figure 3 This is a schematic diagram of the blade forging edge trimming and straightening tooling and device of the present invention;

[0029] Figure 4 This is a schematic diagram of the forging placed on the device before trimming and straightening in this invention;

[0030] Figure 5 This is a schematic diagram of the forging correction and flash clamping process in this invention;

[0031] Figure 6 This is a schematic diagram of the forging process during edge trimming in this invention;

[0032] Figure 7 This is a schematic diagram of the device for removing the forging after trimming in this invention;

[0033] Figure 8This is a schematic diagram of the device state after the flash has been removed in this invention;

[0034] In the diagram, 1-upper pressing edge structure, 2-lower pressing edge structure, 3-anti-ejection device, 4-punch. Detailed Implementation

[0035] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. However, it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0036] like Figures 3-8 As shown, the basic idea of ​​this invention is to optimize and integrate the traditional trimming die and the correction die into a set of tooling devices, add a flash clamping device and a forging back support device (i.e., punch 4 and anti-ejection device 3) to the trimming die, and apply additional pressure during the correction process. The device mainly includes an upper pressing structure 1, a lower pressing structure 2, an anti-ejection device 3 and a punch 4.

[0037] During the trimming and straightening process, the blade forging is first straightened. When the deformation reaches the required amount (generally 0.1mm to 0.2mm), the flash pressing structure (upper pressing structure 1 and lower pressing structure 2) in the device presses the flash. Then, the punch 4 and the anti-ejector device 3 drive the blade forging to move between the pressing structures (upper pressing structure 1 and lower pressing structure 2) to trim the flash. Because the flash is pressed by the pressing structures above and below and the forging has a support device on the back of the forging, the forging can be prevented from turning over during the trimming process. After the trimming is completed, the punch 4 and the anti-ejector device 3 maintain the pressure on the blade forging for a duration of 5s to 30s (depending on the size of the blade; the larger the blade, the longer the pressure holding time, and vice versa). At this time, the residual stress caused by the elastic-plastic properties of the material is released, thereby reducing the deformation of subsequent heat treatment. The entire process combines the two main steps of edge trimming and shaping into one main step. The original large amount of work and workflow can be simplified to: spraying glass lubricant → heating → straightening + edge trimming, which greatly reduces the production process, improves production efficiency, and reduces production costs and manual labor.

[0038] The aero-engine blade forging edge trimming and straightening device of the present invention is as follows: Figure 3 As shown, it mainly includes an upper pressing structure 1, a lower pressing structure 2, an anti-ejection device 3, and a punch 4. The pressing surfaces of the upper pressing structure 1 and the lower pressing structure 2 are designed to match the outflow trend of the metal flash. Clamping teeth are added if necessary. The die cavity of the anti-ejection device 3 and the punch 4 constitutes the correction die cavity. The process of the blade forging edge correction method is as follows:

[0039] 1. Discharge material. For example... Figure 4As shown, before correction and trimming, the blade forging is heated to its correction temperature (generally 30°C lower than the forging temperature) and placed on the correction die cavity formed by the lower pressure edge structure 2 and the punch 4.

[0040] 2. Correct and clamp the flash. For example... Figure 5 As shown, the lower pressing edge structure 2 moves upward synchronously with the punch 4. The punch 4 interacts with the anti-ejection device 3 to complete the shaping of the blade forging (the pressing amount of the shaping is generally 0.1mm to 0.2mm). The interaction between the lower pressing edge structure 2 and the upper pressing edge structure 1 completes the clamping of the flash.

[0041] 3. Trim the edges. For example... Figure 6 As shown, punch 4 and anti-ejection device 3 move the blade forging relative to the blank holder structure to perform precision punching and trimming, thus separating the blade forging from the flash. During and after the trimming process, punch 4 and anti-ejection device 3 maintain pressure on the blade forging for a duration of 5s to 30s (depending on the size of the blade forging; the larger the blade forging, the longer the pressure holding time, and vice versa).

[0042] 4. Remove the forging. For example... Figure 7 As shown, at this time, the upper pressing structure 1 and the anti-top material device 3 return to their original positions, and there is enough space to remove the blade forging.

[0043] 5. Remove the burr. For example... Figure 8 As shown, punch 4 returns to its original position, separating from the flash, which can then be removed. When correcting and trimming the next blade forging, the blade forging is placed in the correction die cavity formed by the lower pressure structure 2 and punch 4, as shown. Figure 4 As shown, proceed with the subsequent steps.

[0044] This invention provides a device and method for trimming and straightening forged aero-engine blades. Through innovative design and optimized integration, the two main processes of trimming and straightening are combined into one main process, reducing the production flow, improving production efficiency, and lowering production costs and labor. The device has a pressing structure and a support device on the back of the forging, which prevents the flash from turning over during the trimming process. After trimming, the device and process maintain pressure on the blade forging through the punch 4 and the anti-ejection device 3, releasing residual stress caused by reduced material elasticity and plasticity, thereby reducing deformation during subsequent heat treatment.

[0045] Contents not described in detail in this specification are prior art known to those skilled in the art. Although illustrative specific embodiments of the invention have been described above to facilitate understanding by those skilled in the art, it should be understood that the invention is not limited to the scope of the specific embodiments. Various modifications are readily apparent to those skilled in the art as long as they fall within the spirit and scope of the invention as defined and determined by the appended claims, and all inventions utilizing the concept of this invention are protected.

Claims

1. A method for correcting the trimmed edges of aero-engine blade forgings, characterized in that: The edge correction device used includes, Upper pressure edge structure (1), the lower end face of the upper pressure edge structure (1) forms the upper pressure edge surface of the aero-engine blade forging, and the upper pressure edge surface has a first hollow area inside; The lower pressure edge structure (2) forms the lower pressure edge surface of the aero-engine blade forging on its upper end surface, and a second hollow area is opened inside the lower pressure edge surface. The anti-ejection device (3) penetrates the first hollow area of ​​the upper pressing structure (1), and the lower end of the anti-ejection device (3) forms the upper correction mold cavity; Punch (4), the punch (4) penetrates the second hollow area of ​​the lower pressing edge structure (2), and the upper end of the punch (4) forms a lower correction die cavity; The surface shapes of the upper and lower pressure edge surfaces match the outflow trend of the metal flash of the aero-engine blade forging; The edge correction method includes the following steps: Step 1, feeding: heat the aero-engine blade forging to the calibration temperature and then place it on the upper end of the punch (4) and the lower pressure edge structure (2); Step 2, Correction and clamping of flash: The lower pressing edge structure (2) and the punch (4) move upward synchronously together. The punch (4) and the anti-ejection device (3) interact to complete the shaping of the blade forging. The interaction between the lower pressing edge structure (2) and the upper pressing edge structure (1) completes the clamping of flash. Step 3, trimming: The punch (4) and the anti-ejection device (3) move the blade forging upward relative to the upper pressing structure (1) and the lower pressing structure (2) to perform precision punching and trimming, thereby separating the blade forging from the flash. During the trimming process and after the trimming is completed, the punch (4) and the anti-ejection device (3) maintain pressure on the blade forging for a duration of 5s to 30s. The duration depends on the size of the blade forging. The larger the blade forging, the longer the pressure holding time, and vice versa. Step 4: Remove the forging. The lower pressing structure (2) and punch (4) move downwards. When the anti-top material device (3) returns to its original position, remove the blade forging. Step 5: Remove the flash. When the punch (4) returns to its original position, remove the flash left by the cutting edge.

2. The method for edge correction of aero-engine blade forgings according to claim 1, characterized in that: The edge correction device further includes clamping teeth, which are disposed on the upper pressing edge surface, or the lower pressing edge surface, or simultaneously on both the upper pressing edge surface and the lower pressing edge surface.

3. The method for edge correction of aero-engine blade forgings according to claim 1, characterized in that: In step 1, the correction temperature is 30°C lower than the forging temperature of the blade forging.

4. The method for edge correction of aero-engine blade forgings according to claim 1, characterized in that: In step 2, the reduction in the shape of the blade forging is 0.1 mm to 0.2 mm.

5. The method for edge correction of aero-engine blade forgings according to claim 1, characterized in that: After step 5, step 1 is repeated to perform edge correction on the next blade forging.

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