Method for Controlling Machining Deformation of Mortise Groove of Turbine Disk and Specimen
The method of measuring deformation through try-cutting and creating stress relief slots in turbine discs addresses the deformation issue, improving machining precision and yield.
Patent Information
- Application Number
- CN202110672812.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2021-06-17
- Publication Date
- 2025-07-15
- Estimated Expiration
- 2041-06-17
AI Technical Summary
In the prior art, the powder alloy turbine disc has large deformation due to residual stress imbalance during the online cutting process, which affects the processing accuracy and product qualification rate, and has a high cost, resulting in high parts scrapping rate.
The amount of cutting deformation is measured by trial cutting method, and the stress relief groove is processed on the outer periphery of the turbine disc, the appropriate cross-sectional shape is selected to release stress, and the deformation is controlled with specific processing paths, including rectangular, V-shaped and narrow-slit stress relief grooves, ensuring that the cutting stress is fully released without affecting the tongue and groove size.
It significantly improves the processing accuracy and one-time pass rate of powder metallurgy turbine discs, reduces processing costs, and reduces parts scrapping, especially for turbine discs with complex characteristics.
Smart Images
Figure CN115488583B_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the field of aeroengines, and in particular to a machining deformation control method and a test piece for a mortise and tenon groove of a turbine disk. Background Art
[0002] Because powder alloy has high yield strength, excellent mechanical properties, good high-temperature fatigue performance, and an operating temperature range of 650-850°C, it has become the preferred material for domestic and foreign aircraft engine and gas turbine turbine discs.
[0003] The turbine disc blank of powder metallurgy is formed through a series of complex hot processing processes such as canning, hot isostatic pressing, isothermal forging, and heat treatment. The residual stress inside the blank is relatively large. During the wire cutting process, the relative balance of the residual stress inside the material is destroyed due to cutting on the entire piece of material and removing a large area of metal, resulting in a large deformation, resulting in the parts failing to achieve the design accuracy, and even making the processing impossible. In addition, the cost of powder metallurgy materials is high, and wire cutting is the last forming process. Once the tolerance is seriously exceeded or the margin is insufficient, the parts will be scrapped.
[0004] In addition, the powder metallurgy parts blanks have a complex forming process and many uncontrollable factors in the forming process, and the stability of each batch is quite different. Because of the above reasons, the scrap rate of turbine disk parts is high during the engine development stage. In order to ensure the development node, the production organization mode of "invest two to protect one, invest three to protect two" is often adopted, resulting in a huge waste of funds.
[0005] Therefore, how to reduce the deformation of the turbine disk caused by processing and improve the product qualification rate is a technical problem that needs to be solved urgently in this field. Summary of the invention
[0006] The technical problem to be solved by the present invention is to overcome the defect in the prior art that the turbine disk is greatly deformed due to processing, resulting in a low product qualification rate, and to provide a method and a test piece for controlling the processing deformation of the mortise and tenon of the turbine disk.
[0007] The present invention solves the above technical problems through the following technical solutions:
[0008] The present invention provides a method for controlling machining deformation of a tenon groove of a turbine disk, wherein the method comprises the following steps:
[0009] S1: cutting the specimen by a test cutting method, and measuring the cutting deformation of the specimen after cutting;
[0010] S2: Select the cross-sectional shape of the stress relief groove according to the cutting deformation amount, and machine the stress relief groove on the outer periphery of the to-be-machined turbine disk. The stress relief groove is located within the dovetail groove formed in the subsequent steps.
[0011] S3: Machine the dovetail groove on the outer periphery of the to-be-machined turbine disk.
[0012] In this technical solution, through the above process steps, it is possible to solve the loss of machining accuracy of parts caused by the deformation resulting from the release of residual stress in the to-be-machined turbine disk (turbine disk blank), especially for turbine disks made of powder metallurgy. Moreover, especially for parts with complex machining features and a relatively large number of features, the machining accuracy and the first-pass qualification rate can be significantly improved.
[0013] Preferably, in step S1, the test piece is machined in the same furnace batch as the to-be-machined turbine disk.
[0014] In this technical solution, the test piece is machined in the same furnace batch as the to-be-machined turbine disk, so as to ensure that all aspects of the test piece and the to-be-machined turbine disk are the same, thereby ensuring the accuracy of the cutting deformation amount obtained on the test piece.
[0015] Preferably, in step S1, the test piece is the waste material cut from the central position of the to-be-machined turbine disk, or the test piece is a component independent of the to-be-machined turbine disk.
[0016] In this technical solution, by using the waste material cut from the central position of the to-be-machined turbine disk as the test piece, the beneficial effect of saving the raw material of the test piece can be achieved.
[0017] Preferably, in step S1, when the cutting deformation amount is greater than 0.5 mm, in step S2, select the cross-sectional shape of the stress relief groove to be rectangular.
[0018] In step S1, when the cutting deformation amount is greater than 0.1 mm and less than or equal to 0.5 mm, in step S2, select the cross-sectional shape of the stress relief groove to be V-shaped.
[0019] In step S1, when the cutting deformation amount is less than or equal to 0.1 mm, in step S2, select the cross-sectional shape of the stress relief groove to be narrow-slit-shaped.
[0020] In this technical solution, by measuring the cutting deformation amount to select the cross-sectional shape of the stress relief groove, the machining efficiency of the turbine disk can be improved.
[0021] Preferably, when the cross-sectional shape of the stress relief groove is narrow-slit-shaped, the width of the opening of the stress relief groove is 0.2 mm to 1 mm.
[0022] In this technical solution, by setting the opening width range of the stress relief groove with a narrow slit-shaped cross-sectional shape, it is possible to ensure the full release of cutting stress and ensure that the workpiece can still meet the requirements of the tenon groove dimensions after deformation.
[0023] Preferably, the height of the stress relief groove is less than or equal to the height of the tenon groove.
[0024] In this technical solution, by setting the height range of the stress relief groove, it is possible to ensure the full release of cutting stress and ensure that the workpiece can still meet the requirements of the tenon groove dimensions after deformation.
[0025] Preferably, the turbine disk includes a symmetric first half disk and a second half disk. The tenon groove machined on the first half disk to be machined is the first tenon groove, and the tenon groove machined on the second half disk to be machined is the second tenon groove. In step S3, the following steps are included:
[0026] Step S31: Machine any two adjacent first tenon grooves on the outer periphery of the first half disk to be machined;
[0027] Step S32: Machine two adjacent second tenon grooves at positions symmetric to the two adjacent first tenon grooves on the outer periphery of the second half disk to be machined;
[0028] Step S33: Machine one first tenon groove on each of the two outer sides in the circumferential direction of the two adjacent first tenon grooves that have been machined on the outer periphery of the first half disk to be machined;
[0029] Step S34: Machine one second tenon groove at each position symmetric to the two first tenon grooves formed in the previous step on the outer periphery of the second half disk to be machined;
[0030] Step S35: Machine one first tenon groove on each of the outer sides in the circumferential direction of the two outermost first tenon grooves that have been machined on the outer periphery of the first half disk to be machined;
[0031] Step S36: Machine one second tenon groove at each position symmetric to the two first tenon grooves formed in the previous step on the outer periphery of the second half disk to be machined;
[0032] Repeat step S35 and step S36 until all the first tenon grooves and the second tenon grooves are machined.
[0033] In this technical solution, by specifically planning a specific machining path, that is, planning and adjusting the machining path according to the order of symmetric machining, so as to evenly release the machining stress and offset the deformation.
[0034] Preferably, the materials of the specimen and the turbine disk to be machined are both powder alloy.
[0035] In this technical solution, by setting the materials of the specimen and the turbine disk to be machined as powder alloy, that is, the turbine disk to be machined has the beneficial technical effects of high yield strength, excellent mechanical properties, good high-temperature fatigue performance of the powder alloy, and the service temperature range can reach 650 - 850 °C.
[0036] The present invention also provides a specimen, characterized in that the specimen is applied to the machining deformation control method of the dovetail groove of the turbine disk as described above, the thickness of the specimen is equal to the thickness of the dovetail groove, the specimen includes two sides oppositely arranged along the width direction, one side is the reference side and the other side is the deformation side;
[0037] A deformation release slot is opened at the top of the specimen along the width direction of the specimen, the deformation release slot penetrates the specimen along the thickness direction, the height of the deformation release slot is the same as the height of the dovetail groove, and the distance from the reference side to the deformation release slot is greater than three times the distance from the deformation side to the deformation release slot;
[0038] The distance from the deformation side to the deformation release slot is equal to the width of the root of the dovetail tooth formed by two adjacent dovetail grooves;
[0039] The width difference between the bottom and the top of the specimen is the cutting deformation amount.
[0040] In this technical solution, by setting the specific structure of the specimen, a reliable basis can be provided for accurately measuring the cutting deformation amount.
[0041] Preferably, the width of the deformation release slot is 2 mm - 3 mm, and setting this width can facilitate the evaluation of the cutting deformation amount.
[0042] The positive and progressive effects of the present invention are as follows:
[0043] The machining deformation control method of the dovetail groove of the turbine disk of the present invention can solve the loss of machining accuracy of parts caused by the deformation due to the release of residual stress of the turbine disk (turbine disk blank) to be machined, especially for turbine disks made of powder metallurgy; moreover, especially for parts with complex machining features and a relatively large number of features, it can significantly improve the machining accuracy and the first-pass qualification rate.
[0044] By setting the specific structure of the specimen, the present invention can provide a reliable basis for accurately measuring the cutting deformation amount. BRIEF DESCRIPTION OF THE DRAWINGS
[0045] Figure 1 It is a process step diagram of the machining deformation control method of the dovetail groove of the turbine disk in a preferred embodiment of the present invention.
[0046] Figure 2 Schematic structural view of cutting a test piece on a turbine disk to be machined in a method for controlling machining deformation of a dovetail groove of a turbine disk according to a preferred embodiment of the present invention.
[0047] Figure 3 Schematic three-dimensional structure view of a test piece in a method for controlling machining deformation of a dovetail groove of a turbine disk according to a preferred embodiment of the present invention.
[0048] Figure 4 Schematic three-dimensional structure view of a dovetail groove of a turbine disk machined by a method for controlling machining deformation of a dovetail groove of a turbine disk according to a preferred embodiment of the present invention.
[0049] Figure 5 Schematic view of a cross-sectional shape of a stress relief groove in a method for controlling machining deformation of a dovetail groove of a turbine disk according to a preferred embodiment of the present invention.
[0050] Figure 6 Schematic view of another embodiment of a cross-sectional shape of a stress relief groove in a method for controlling machining deformation of a dovetail groove of a turbine disk according to a preferred embodiment of the present invention.
[0051] Figure 7 Schematic view of yet another embodiment of a cross-sectional shape of a stress relief groove in a method for controlling machining deformation of a dovetail groove of a turbine disk according to a preferred embodiment of the present invention.
[0052] Figure 8 Schematic structural view of a turbine disk to be machined after machining a stress relief groove in a method for controlling machining deformation of a dovetail groove of a turbine disk according to a preferred embodiment of the present invention.
[0053] Figure 9 Schematic view of a machining path for machining a dovetail groove on a turbine disk to be machined in a method for controlling machining deformation of a dovetail groove of a turbine disk according to a preferred embodiment of the present invention.
[0054] Figure 10 Schematic three-dimensional structure view of a machined turbine disk in a method for controlling machining deformation of a dovetail groove of a turbine disk according to a preferred embodiment of the present invention. Detailed implementation manners
[0055] The present invention will be further described below by way of examples, but the present invention is not limited to the scope of the examples accordingly.
[0056] Please refer to Figure 1 for understanding. This embodiment provides a method for controlling machining deformation of a dovetail groove of a turbine disk. The machining deformation control method includes the following steps:
[0057] Step 100: Cut a test piece by a trial cutting method, and measure the cutting deformation amount of the cut test piece.
[0058] Step 200: Select the cross-sectional shape of the stress relief groove according to the cutting deformation amount, and machine the stress relief groove on the outer periphery of the turbine disk to be machined. The stress relief groove is located within the dovetail groove formed in the subsequent step.
[0059] Step 300: Machine the dovetail groove on the outer periphery of the turbine disk to be machined.
[0060] In this embodiment, through the above process steps, it is possible to solve the loss of machining accuracy of the part caused by the deformation resulting from the release of the residual stress of the turbine disk to be machined (turbine disk blank), especially for the turbine disk made of powder metallurgy. Moreover, especially for parts with complex machining features and a relatively large number of features, the machining accuracy and the first-pass qualification rate can be significantly improved.
[0061] In the above steps, the materials of the test piece and the turbine disk to be machined are both powder alloys. In this way, by setting the materials of the test piece and the turbine disk to be machined as powder alloys, that is, the turbine disk to be machined has the beneficial technical effects of high yield strength, excellent mechanical properties, good high-temperature fatigue performance of the powder alloy, and a service temperature range of up to 650 - 850 °C.
[0062] Specifically, in step 100, the test piece and the turbine disk to be machined are processed in the same furnace batch. In this way, by processing the test piece and the turbine disk to be machined in the same furnace batch, the various characteristics of the test piece and the turbine disk to be machined are ensured to be the same, thereby ensuring the accuracy of the cutting deformation amount obtained on the test piece.
[0063] Preferably, in step 100, as Figure 2 shown, the test piece 20 is the waste material cut from the central position of the turbine disk 40 to be machined. Since the turbine disk 40 to be machined is a hollow structure, the waste material at the central position can just be used as the raw material source required for the test piece 20, thereby achieving the beneficial effect of saving the raw material of the test piece 20, and at the same time ensuring that the material of the test piece 20 and the turbine disk 40 to be machined are processed in the same furnace batch. However, it is not limited to this, and the test piece 20 can also be a component independent of the turbine disk 40 to be machined.
[0064] The specific structure of the test piece 20 is as Figure 3 shown, and the structural diagram after machining the dovetail groove 50 of the turbine disk 40 is as Figure 4As shown, the thickness t of the test piece 20 is equal to the thickness T of the mortise groove 50. The test piece 20 includes two sides oppositely arranged along the width direction W'. One side is the reference side 21, and the other side is the deformed side 22. A deformation release slit 25 is formed at the top 23 of the test piece 20 along the width direction W' of the test piece 20, and the deformation release slit 25 penetrates the test piece 20 along the thickness direction T'. The height h of the deformation release slit 25 is the same as the height H of the mortise groove 50, and the distance w from the reference side 21 to the deformation release slit 25 is greater than three times the distance d from the deformed side 22 to the deformation release slit 25. Preferably, the width s of the deformation release slit 25 is 2 mm to 3 mm to facilitate the evaluation of the cutting deformation amount. More preferably, the width s of the deformation release slit 25 is 2.5 mm. The distance d from the deformed side 22 to the deformation release slit 25 is equal to the width D of the root of the mortise tooth 60 formed by two adjacent mortise grooves 50.
[0065] The difference between the width L of the bottom 24 of the test piece 20 and the width L' of the top 23 of the test piece 20 is the cutting deformation amount (i.e., the residual stress release deformation amount) δ, that is, δ = L - L'.
[0066] In step 200, the cross-sectional shape of the stress release groove 70 is selected according to the cutting deformation amount δ. Specifically, when the cutting deformation amount is greater than 0.5 mm, in step 200, the cross-sectional shape of the stress release groove 70 is selected as a rectangle, as Figure 5 shown, which can ensure the full release of the cutting stress.
[0067] When the cutting deformation amount is greater than 0.1 mm and less than or equal to 0.5 mm, in step 200, the cross-sectional shape of the stress release groove 70 is selected as a V shape, as Figure 6 shown, which can not only ensure the full release of the cutting stress but also improve the processing efficiency compared with using a rectangular groove.
[0068] When the cross-sectional shape of the stress release groove 70 is a rectangle or a V shape, the width of the opening of the stress release groove 70 is adjusted according to the shape, spacing of the processed mortise groove and the cutting deformation amount.
[0069] When the cutting deformation amount is less than or equal to 0.1 mm, in step S200, the cross-sectional shape of the stress release groove 70 is selected as a narrow slit shape, as Figure 7 shown, which greatly improves the processing efficiency of the release groove.
[0070] When the cross-sectional shape of the stress release groove 70 is a narrow slit shape, the width w1 of the opening of the stress release groove 70 is 0.2 mm to 1 mm. In this way, by setting the opening width range of the stress release groove with a narrow slit shape, it can not only ensure the full release of the cutting stress but also ensure that the workpiece can still meet the requirements of the mortise groove size after deformation.
[0071] In this way, selecting the cross-sectional shape of the stress release groove 70 according to the measured cutting deformation amount can improve the processing efficiency of the turbine disk.
[0072] The height of the stress relief groove 70 is determined by the height of the tenon to be machined and the cutting deformation amount, and does not exceed the height of the mortise groove 50, that is, the height h1 of the stress relief groove 70 is less than or equal to the height H of the mortise groove 50. By setting the height range of the stress relief groove, it can not only ensure the full release of the cutting stress, but also ensure that the workpiece can still meet the requirements of the mortise groove size after deformation.
[0073] After selecting the cross-sectional shape of the stress relief groove 70 according to the cutting deformation amount, as Figure 8 shown, the stress relief groove 70 is machined on the outer peripheral edge of the turbine disk 40 to be machined, and the stress relief groove 70 is located in the mortise groove formed in the subsequent step.
[0074] It should be noted that for the turbine disk to be machined with relatively large residual stress and the cutting deformation amount during the trial cutting specimen process being greater than or equal to 0.1 mm, it has the beneficial effect of significantly reducing stress deformation.
[0075] In step 300, the turbine disk 40 to be machined includes a symmetric first half disk 41 and a second half disk 42. The mortise groove machined on the first half disk 41 to be machined is the first mortise groove, and the mortise groove machined on the second half disk 42 to be machined is the second mortise groove. Among them, in order to better describe the machining path planning of the mortise groove, the turbine disk 40 is divided into a symmetric first half disk 41 and a second half disk 42 for description. The turbine disk 40 is an integrally formed structure, and the structures of the first mortise groove and the second mortise groove are the same.
[0076] Specifically, as Figure 9 shown, it includes the following steps:
[0077] Step 310: Machine any two adjacent first mortise grooves on the outer peripheral edge of the first half disk 41 to be machined to form a tenon tooth 70, marked as the first mortise groove 1 and the first mortise groove 2;
[0078] Step 320: Machine two adjacent second mortise grooves at positions symmetric to the two adjacent first mortise grooves (i.e., the first mortise groove 1 and the first mortise groove 2) on the outer peripheral edge of the second half disk 42 to be machined, marked as the second mortise groove 3 and the second mortise groove 4;
[0079] Step 330: Machine a first mortise groove on each of the circumferentially outer sides of the two adjacent first mortise grooves (i.e., the first mortise groove 1 and the first mortise groove 2) that have been machined on the outer peripheral edge of the first half disk 41 to be machined, marked as the first mortise groove 5 and the first mortise groove 6;
[0080] Step 340: Machine a second mortise groove at each position symmetric to the two first mortise grooves (i.e., the first mortise groove 5 and the first mortise groove 6) formed in the previous step on the outer peripheral edge of the second half disk 42 to be machined, marked as the second mortise groove 7 and the second mortise groove 8;
[0081] Step 350: On the outer sides of the outermost two first tenon grooves that have been processed on the outer peripheral edge of the first half-disk 41 to be processed (i.e., the first tenon groove 5 and the first tenon groove 6), respectively process a first tenon groove along the circumferential direction, marked as the first tenon groove 9 and the first tenon groove 10;
[0082] Step 360: At positions symmetric to the two first tenon grooves (i.e., the first tenon groove 9 and the first tenon groove 10) formed in the previous step on the outer peripheral edge of the second half-disk 42 to be processed, respectively process a second tenon groove, marked as the second tenon groove 11 and the second tenon groove 12;
[0083] Repeat Step 350 and Step 360 until all the first tenon grooves and the second tenon grooves are processed.
[0084] Through the above steps, it is possible to plan and adjust the machining path according to the symmetric machining sequence so as to evenly release the machining stress to offset the deformation. By adopting the machining methods of symmetric cutting and sequential cutting, it is possible to evenly release the machining stress to offset the deformation, that is, to make the deformation smaller, thus achieving the beneficial technical effect of effectively controlling the deformation.
[0085] It should be noted that when machining two tenon grooves on the same half-disk, they can all be machined in the clockwise direction, that is, sequentially machining the first tenon groove 1, the first tenon groove 2, the second tenon groove 3, the second tenon groove 4, the first tenon groove 5, the first tenon groove 6, the second tenon groove 7, the second tenon groove 8, the first tenon groove 9, the first tenon groove 10, the second tenon groove 11 and the second tenon groove 12, and so on until all the first tenon grooves and the second tenon grooves are processed, as Figure 9 shown. However, it is not limited to this, and they can also all be machined in the counterclockwise direction.
[0086] The specific structure of the machined turbine disk 40 is as Figure 10 shown. After machining a plurality of tenon grooves 50 on the outer peripheral edge of the turbine disk 40, a tenon tooth 60 is formed between two adjacent tenon grooves 50.
[0087] As before, this embodiment also provides a specimen 20 for applying the method for controlling the machining deformation of the tenon grooves of the turbine disk 40 as above.
[0088] Please refer back to Figure 3 the three-dimensional structure schematic diagram of the specimen 20 in Figure 4The three-dimensional structure diagram after the dovetail groove 50 of the turbine disk 40 in [description] is processed. The thickness t of the specimen 20 is equal to the thickness T of the dovetail groove 50. The specimen 20 includes two sides oppositely arranged along the width direction W'. One side is the reference side 21, and the other side is the deformation side 22. A deformation release slot 25 is provided at the top 23 of the specimen 20 along the width direction W' of the specimen 20. The deformation release slot 25 penetrates the specimen 20 along the thickness direction T'. The height h of the deformation release slot 25 is the same as the height H of the dovetail groove 50. The distance w from the reference side 21 to the deformation release slot 25 is greater than three times the distance d from the deformation side 22 to the deformation release slot 25. Preferably, the width s of the deformation release slot 25 is 2.5 mm. The distance d from the deformation side 22 to the deformation release slot 25 is equal to the width D of the root of the dovetail tooth 60 formed by two adjacent dovetail grooves 50.
[0089] The difference between the width L of the bottom 24 of the specimen 20 and the width L' of the top 23 of the specimen 20 is the cutting deformation amount (i.e., the residual stress release deformation amount) δ, that is, δ = L - L'.
[0090] In this embodiment, by setting the specific structure of the specimen 20, a reliable basis can be provided for accurately measuring the cutting deformation amount.
[0091] Although the specific implementation manners of the present invention have been described above, those skilled in the art should understand that this is only an example. The protection scope of the present invention is defined by the appended claims. Without departing from the principles and essence of the present invention, those skilled in the art can make various changes or modifications to these implementation manners, but these changes and modifications all fall within the protection scope of the present invention.
Claims
1. A method for controlling the machining deformation of the dovetail groove of a turbine disk, characterized in that, The machining deformation control method includes the following steps: S1: Cut the test piece by the trial cutting method, measure the cutting deformation amount of the cut test piece, and the test piece is processed in the same furnace batch as the turbine disk to be machined; S2: Select the cross-sectional shape of the stress relief groove according to the cutting deformation amount, and machine the stress relief groove on the outer peripheral edge of the turbine disk to be machined, and the stress relief groove is located in the tenon groove formed in the subsequent steps; S3: Machine the tenon groove on the outer peripheral edge of the turbine disk to be machined.
2. The machining deformation control method of the tenon groove of the turbine disk as claimed in claim 1, in step S1, the test piece is the waste material cut from the central position of the turbine disk to be machined, or the test piece is a component independent of the turbine disk to be machined.
3. The machining deformation control method of the tenon groove of the turbine disk as claimed in claim 1, characterized in that, in step S1, when the cutting deformation amount is greater than 0.5 mm, in step S2, select the cross-sectional shape of the stress relief groove to be rectangular; in step S1, when the cutting deformation amount is greater than 0.1 mm and less than or equal to 0.5 mm, in step S2, select the cross-sectional shape of the stress relief groove to be V-shaped; in step S1, when the cutting deformation amount is less than or equal to 0.1 mm, in step S2, select the cross-sectional shape of the stress relief groove to be narrow-slit-shaped.
4. The method for controlling the machining deformation of the dovetail groove of the turbine disk according to claim 3, wherein, The cross-sectional shape of the stress relief groove is narrow-slit-shaped, and the width of the opening of the stress relief groove is 0.2 mm to 1 mm.
5. The machining deformation control method of the tenon groove of the turbine disk as claimed in claim 1, the height of the stress relief groove is less than or equal to the height of the tenon groove.
6. The method for controlling the machining deformation of the dovetail groove of the turbine disk according to any one of claims 1 to 5, characterized in that, The turbine disk includes a symmetric first half disk and a second half disk. The tenon groove machined on the first half disk to be machined is the first tenon groove, and the tenon groove machined on the second half disk to be machined is the second tenon groove. In step S3, it includes the following steps: Step S31: Machine any two adjacent first tenon grooves on the outer peripheral edge of the first half disk to be machined; Step S32: Machine two adjacent second tenon grooves at positions symmetric to the two adjacent first tenon grooves on the outer peripheral edge of the second half disk to be machined; Step S33: Machine a first tenon groove on each of the two outer sides in the circumferential direction of the two adjacent first tenon grooves that have been machined on the outer peripheral edge of the first half disk to be machined; Step S34: Machine a second tenon groove at each position symmetric to the two first tenon grooves formed in the previous step on the outer peripheral edge of the second half disk to be machined; Step S35: Machine a first tenon groove on each of the outer sides in the circumferential direction of the two outermost first tenon grooves that have been machined on the outer peripheral edge of the first half disk to be machined; Step S36: Machine a second tenon groove at each position symmetric to the two first tenon grooves formed in the previous step on the outer peripheral edge of the second half disk to be machined; Repeat step S35 and step S36 until all the first tenon grooves and the second tenon grooves are machined.
7. The method for controlling the machining deformation of the dovetail groove of the turbine disk according to claim 1, characterized in that, The materials of the test piece and the turbine disk to be machined are both powder alloy.
8. A test piece, characterized in that, The test piece is applied to the method for controlling the machining deformation of the dovetail groove of the turbine disk as described in any one of claims 1-7. The thickness of the test piece is equal to the thickness of the dovetail groove. The test piece includes two sides oppositely arranged in the width direction, one side is the reference side, and the other side is the deformation side; A deformation release slot is opened at the top of the test piece along the width direction of the test piece. The deformation release slot penetrates the test piece along the thickness direction. The height of the deformation release slot is the same as the height of the dovetail groove. The distance from the reference side to the deformation release slot is greater than three times the distance from the deformation side to the deformation release slot; The distance from the deformation side to the deformation release slot is equal to the width of the root of the dovetail tooth formed by two adjacent dovetail grooves; The difference between the width of the bottom of the test piece and the width of the top of the test piece is the cutting deformation amount.
9. The test piece according to claim 8, wherein, The width of the deformation release slot is 2 mm to 3 mm.
Citation Information
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