A method for repairing and adjusting the final forging die of an aircraft engine blade

Abstract

The present invention discloses a method for drop repair and die adjustment of the final forging die of an aero-engine blade, comprising drop milling the final forging die as a whole and installing the final forging die, taking the final forging die before drop milling as a blank, moving the blank in the drop direction for a distance to copy and form a workpiece, and horizontally moving the workpiece for a displacement S, so that a cutting layer greater than the wear depth of the final forging die is formed between the workpiece and the blank in the drop milling direction, and then drop milling is performed; a pad with a thickness equal to the displacement S is used to cooperate with the final forging die that has completed the drop repair, and the horizontal displacement S of the final forging die is compensated in the opposite direction to form the final final forging die. The present invention shortens the milling processing time, reduces the tool consumption cost, and increases the number of times the mold can be repaired, thereby saving production costs and improving the production efficiency of the final forging blank of the blade.

Description

Technical Field

[0001] The invention belongs to the field of die repair and die adjustment of aircraft engine blades, and in particular, relates to a drop repair and die adjustment method for a final forging die of an aircraft engine blade. Background Art

[0002] The final forging process of aircraft engine blades has high requirements for the dimensional control of forgings, especially for small margin blades and precision forged blades. In the final forging process of blades, the violent flow and high temperature of metal can easily cause the final forging mold cavity to wear. Wear will occur after forging hundreds or even just dozens of forgings. Specifically, there are traces and small pits on the surface of the forging. The slight traces can be eliminated by lightly grinding the mold cavity surface with sandpaper. However, after several times of grinding, the outline of the forging will exceed the requirements of the forging drawing. At this time, the mold needs to be milled and repaired.

[0003] like Figure 1 As shown, according to the normal overall falling method (i.e. milling with the tool falling vertically or milling in the vertical direction), it takes several millimeters or even dozens of millimeters to remove the original surface material of the mold cavity. The milling process takes a long time, the tool consumption cost is high, and the mold can be repaired less times. While increasing the production cost, it also restricts the production efficiency of the final forging of the blade. Summary of the invention

[0004] In order to solve the above technical problems, the present invention aims to provide a method for the drop repair and mold adjustment of the final forging die of an aircraft engine blade. The drop milling repair of the final forging model cavity can be completed by dropping 1 mm or even a fraction of a mm. The milling processing time is shortened, the tool consumption cost is reduced, and the number of times the mold can be repaired is increased. While saving production costs, it also improves the production efficiency of the blade final forging blank.

[0005] The present invention adopts the following technical solutions:

[0006] A method for falling, repairing and adjusting the final forging die of an aero-engine blade, comprising:

[0007] Step 1, performing drop milling on the final forging die as a whole, taking the final forging die before drop milling as a blank, moving the blank in the drop direction for a distance to replicate a workpiece, and horizontally moving the workpiece for a displacement S so that a cutting layer greater than the wear depth of the final forging die is formed between the workpiece and the blank in the drop milling direction, and then performing drop milling;

[0008] Step 2, installing the final forging die, using a pad with a thickness equal to the displacement S in step 1 to cooperate with the final forging die that has completed the drop repair, and compensating the horizontal movement displacement S of the final forging die in step 1 in the opposite direction to form the final forging die.

[0009] Furthermore, in step 1, the horizontal movement direction of the workpiece is forward, backward, left or right.

[0010] Furthermore, in step 1, it is determined whether the thickness of the cutting layer meets the requirements through the model design drawing of the final forging die.

[0011] Generally, forgings will be inspected during the final forging process (for example, 1 piece is inspected for every 50 pieces). During the inspection process, it will be found that the forgings are partially thickened by a dimension a compared to before. Dimension a can be considered as the depth of die wear. When the depth exceeds the tolerance of the forging, it needs to be repaired. When the cutting layer is greater than a after the workpiece is moved, it can be determined that there is enough cutting layer between the blank and the workpiece. At the same time, it is easy to judge whether there is a cutting layer between the workpiece and the blank when it is moved. Specifically, when using UG and other software for processing programming, it can be seen from the model whether there is a cutting layer (i.e., machining allowance) after the overall fall, and then analyze and judge the direction and distance of the translation.

[0012] It should be pointed out that the circumferential surfaces of the final forging model cavity in the present invention are mutually perpendicular planes (that is, the mold surfaces other than the final forging model cavity surface are mutually perpendicular planes). This is also the reason why the present invention can reduce the amount of cutting of the final forging model cavity only by simple horizontal translation.

[0013] Compared with the prior art, the present invention has the following characteristics:

[0014] (1) The present invention ensures that the amount of cutting between the workpiece and the blank is small and effective by moving the workpiece left and right, front and back, and up and down by a small distance, so that the final forging model cavity can be repaired by milling by falling only one millimeter or even a fraction of a millimeter. When installing the final forging mold, the displacement caused by the movement of the workpiece during the mold falling repair can be eliminated by adjusting the lateral misalignment shift pad or the longitudinal misalignment shift pad of the mold base. Compared with the normal overall falling method that requires falling several millimeters or even dozens of millimeters to remove the original mold cavity surface material, the final forging mold repair method provided by the present invention shortens the milling processing time, reduces the tool consumption cost, and increases the number of times the mold can be repaired, thereby saving production costs and improving the production efficiency of the blade final forging blank.

[0015] (2) The method of the present invention has been applied in the final forging die drop repair and final forging production of various types of aircraft engine compressor blades. The tool cost for each set of die repair has been reduced from RMB 3,000 to RMB 800, and the die drop repair time has been reduced from 1.5 days to 0.5 days. The final forging production efficiency has also been improved compared with before. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A schematic diagram of a general drop repair of a final forging die before adopting the method of the present invention;

[0017] Figure 2 A schematic diagram of a general drop repair of a final forging die after adopting the method of the present invention;

[0018] Figure 3 A schematic diagram of installing a final forging die on a die base after using the method of the present invention;

[0019] In the figure, 1-blank; 2-workpiece; 3-cutting layer; 4-adjustment pad. DETAILED DESCRIPTION

[0020] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to the common technical knowledge and customary means in the field are included in the scope of the present invention.

[0021] The basic idea of ​​the present invention is to keep the original processing coordinate system unchanged. When the mold is milled, the final forging mold model before falling is used as the blank 1, and the blank 1 is moved a certain distance (generally 0.2-0.6 mm) in the falling direction to copy it into a workpiece 2, and the workpiece 2 is moved left and right and front and back (generally only moved in the front and back directions, and the movement amount s1 is generally 0.1-0.3 mm), so that there is a certain thickness of cutting layer 3 between the workpiece 2 and the blank 1 (the thickness of the cutting layer 3 should be greater than the wear depth of the mold, generally 0.07-0.6 mm); when installing the final forging mold, it is necessary to adjust the lateral adjustment shift pad 4 or the longitudinal adjustment shift pad 4 of the mold base to eliminate the misalignment caused by the movement of the workpiece 2 when the mold falls for repair (correspondingly, generally only the longitudinal adjustment shift pad 4 is adjusted, and the pad thickness is subtracted from the original thickness by s1).

[0022] The method of the present invention controls the maximum cutting amount of the mold falling by moving the blank 1 a certain distance in the direction of the mold falling to copy it into the workpiece 2. And by moving the workpiece 2 left and right and front and back to ensure that there is a cutting layer 3 of a certain thickness between the workpiece 2 and the blank 1, the mold falling repair is completed under the cutting of the smaller cutting amount, the milling processing time is shortened, the tool consumption cost is reduced, and the number of times the mold can be repaired is increased. When installing the final forging mold, by adjusting the lateral misalignment shifting pad 4 or the longitudinal misalignment shifting pad 4 of the mold base, the misalignment caused by the movement of the workpiece 2 during the mold falling repair can be eliminated, and the size control of the forging in the final forging process is not affected. From the perspective of the entire process, the production efficiency of the blade final forging blank is also improved.

[0023] A method for the drop repair and die adjustment of the final forging die of an aircraft engine blade ensures that the drop cutting amount between the workpiece 2 and the blank 1 is small and effective by moving the workpiece 2 left and right, front and back, and up and down by a small distance, so that the drop milling repair of the final forging mold cavity can be completed with only a small drop cutting amount. When installing the final forging die, the lateral misalignment shifting pad 4 or the longitudinal misalignment shifting pad 4 of the die base is adjusted to eliminate the misalignment caused by the movement of the workpiece 2 during the drop repair of the die.

[0024] The following is combined with Figure 1 , 2 3. The specific embodiments of the present invention are described in detail so that the advantages and features of the present invention can be more easily understood by those skilled in the art.

[0025] like Figure 1 As shown, according to the normal overall falling method, it is necessary to fall at least 4.5mm to remove the original surface material of the final forging model cavity; Figure 1 The position indicated by the letter A in the middle indicates that according to the traditional method, after the overall drop of 4.5mm, there is still not enough cutting allowance at this position, and it needs to continue to drop by about 0.5mm to have cutting allowance.

[0026] According to the method of the present invention, before the milling and repairing of the mold, the original machining coordinate system is kept unchanged, the final forging mold model before falling is taken as the blank 1, the blank 1 is moved 0.5mm in the direction of the mold falling and copied as the workpiece 2, and the workpiece 2 is moved forward (toward the blade tip) by 0.1mm. Figure 2 At this time, there is a certain thickness of cutting layer 3 between the workpiece 2 and the blank 1 (at Figure 2 The thickness of the thinnest cutting layer 3 not injected is 0.09. Figure 2 The thickness of the thickest cutting layer 3 injected is 0.5. Figure 2 The position indicated by the letter B in the middle represents the cutting allowance at this time. This position corresponds to Figure 1 The mold after falling is as follows Figure 3 shown.

[0027] When installing the final forging die, adjust the longitudinal offset of the die base to shift the pad 4 to reduce the thickness by 0.1 mm. Figure 3 As shown, the misalignment caused by the workpiece 2 moving toward the blade tip when the mold is dropped for repair has been eliminated. Figure 3 The h-0.1 at C can be understood as the selection of a longitudinal adjustment pad 4 that is 0.1mm thinner than the original one to compensate for the offset during mold processing, and the 0.1mm at D can be understood as the workpiece 2 model being deviated to the right by 0.1mm during processing.

[0028] Comparison Figure 1 The drop of 4.5mm, such as Figure 2 , 3The final forging die drop repair and die adjustment method shown in the figure only needs to drop 0.5mm to complete the repair of the final forging die without affecting the final forging size control, shortening the milling processing time, reducing the tool consumption cost, and increasing the number of times the die can be repaired.

[0029] The contents not described in detail in the specification of the present invention belong to the prior art known to the professional and technical personnel in the field. Although the illustrative specific embodiments of the present invention are described above to facilitate the understanding of the present invention by the technical personnel in the field, it should be clear that the present invention is not limited to the scope of the specific embodiments. For ordinary technicians in the field of this technology, as long as various changes are within the spirit and scope of the present invention defined and determined by the attached claims, these changes are obvious, and all inventions and creations using the concept of the present invention are protected.

Claims

1. A method for falling, repairing and adjusting the final forging die of an aero-engine blade, characterized in that: include, Step 1, performing drop milling on the final forging die as a whole, taking the final forging die before drop milling as a blank, moving the blank in the drop direction for a distance to replicate a workpiece, and horizontally moving the workpiece for a displacement S so that a cutting layer greater than the wear depth of the final forging die is formed between the workpiece and the blank in the drop milling direction, and then performing drop milling; Step 2, installing the final forging die, using a pad with a thickness equal to the displacement S in step 1 to cooperate with the final forging die that has completed the drop repair, and compensating the horizontal movement displacement S of the final forging die in step 1 in the opposite direction to form the final forging die.

2. The method for falling, repairing and adjusting the final forging die of an aircraft engine blade according to claim 1, characterized in that: In step 1, the workpiece moves horizontally in a direction of forward, backward, left or right.

3. The method for falling, repairing and adjusting the final forging die of an aircraft engine blade according to claim 1, characterized in that: In the step 1, whether the thickness of the cutting layer meets the requirements is determined by the model design drawing of the final forging die.

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