A method for machining aircraft engine rectifiers

Abstract

This invention belongs to the field of rectifier turning technology and discloses a method for turning aero-engine rectifiers. After rectifier assembly, an alternating clamping method using inner and outer pressure plates solves the problems of narrow clamping areas and unstable clamping in traditional methods. By casting alloy between the blades to form a temporary support structure, the rigidity of thin-walled blades is effectively enhanced, preventing deformation during turning. The specially designed alloy casting process covers the entire blade, and precise turning and finishing ensures a flat support surface, providing a stable reference for subsequent machining. The application of dynamic clamping technology ensures optimal clamping at different machining stages. The outer pressure plate is used for alloy casting, finishing, and blade tip machining, while the inner pressure plate is used for critical outer ring turning. This alternating clamping method significantly improves machining stability. The final alloy melting and removal process ensures no residue on the parts, fully preserving the rectifier's design features.

Description

Technical Field

[0001] This invention belongs to the field of rectifier turning technology, specifically a turning method for aero-engine rectifiers. Background Technology

[0002] See the structure of a certain type of aircraft engine rectifier. Figure 1 and Figure 2 The rectifier consists of an outer ring 1 and rectifier blades 2. The outer ring 1 consists of an inlet side 3, a groove 4, and an exhaust side 5. The rectifier blades consist of a blade body 6 and a blade tip 7. The inlet side 3, exhaust side 5, and blade tip 7 on the outer ring 1 are machined in combination, while the groove 4 on the outer ring 1 is the final surface before combined machining. The cross-section of the rectifier before machining is shown below. Figure 2 The section after turning is shown Figure 3 The traditional method for machining this type of rectifier by combined turning is as follows: (1) Press one side surface B of the groove 4 with a pressure plate and turn the air intake side 3 of the outer ring 1; (2) Turn the blade tip 7; (3) Press the other side surface A of the groove 4 with a pressure plate and turn the exhaust side 5 of the outer ring 1.

[0003] When turning rectifiers, the clamping area of ​​the pressure plate is narrow, the clamping force is small, and the clamping stability is poor. After turning, the structure is thin-walled, with weak rigidity and easy deformation, resulting in poor turning stability. Turning the blade tip is a chip-breaking cut, and the rectifier blade body is in a cantilever state, which is easy to deform during turning. Turning efficiency and pass rate are low. Summary of the Invention

[0004] This invention provides a turning method for aero-engine rectifiers, which solves the problem that the turning blade tip is a chip-breaking cut and the rectifier blade body is in a cantilever state, making it prone to deformation during turning.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] A method for machining an aero-engine rectifier by turning, comprising:

[0007] Assemble and align the rectifier;

[0008] Use the outer pressure plate of the lathe to press the upper surface of the outer ring, and remove the inner pressure plate of the lathe;

[0009] Install an inner retaining ring at the blade tip, pour alloy between the blade body of the rectifier blade, pour the alloy to the outer ring on the outer side of the blade body, and pour the alloy to the inner retaining ring on the inner side of the blade body, with the pouring height covering the blade body and leaving room for trimming.

[0010] Turn and repair the upper surface of the alloy until it is flat, press the upper surface of the alloy with the inner pressure plate, and remove the outer pressure plate;

[0011] The intake side of the outer ring is machined by turning, and the upper surface of the alloy is pressed with the outer pressure plate. The inner pressure plate is then removed.

[0012] The blade tip is machined by turning, the outer pressure plate is removed, and the alloy is heated and melted after the pressure plate is removed to complete the machining.

[0013] Preferably, the rectifier is assembled by clamping it onto a lathe fixture and pressing the upper surface of the outer ring with the inner pressure plate of the lathe fixture.

[0014] Preferably, aligning the rectifier specifically involves aligning the outer circumference and upper surface of the rectifier.

[0015] Preferably, the alloy is cast between the blades of the rectifier blade, with a casting height allowance of 3mm to 5mm for finishing.

[0016] Preferably, when machining the upper surface of the alloy to a flat surface, it is important to ensure that the blade body is not machined.

[0017] Preferably, the lathe fixture is equipped with an inner pressure plate and an outer pressure plate that can be used alternately to switch the clamping position at different processing stages.

[0018] Preferably, after removing the pressure plate, the alloy is heated and melted. Once the alloy is completely melted, the rectifier is removed to complete the processing.

[0019] Preferably, the alloy is cast in an in-machine casting process.

[0020] Preferably, it further includes repeatedly machining the exhaust side using the intake side of the machined rectifier outer ring as the positioning point.

[0021] Compared with existing technologies, this invention has the following advantages: This invention provides a method for machining aero-engine rectifiers. After rectifier assembly, an alternating clamping method using inner and outer pressure plates solves the problems of narrow clamping areas and unstable clamping in traditional methods. By casting alloy between the blades to form a temporary support structure, the rigidity of thin-walled blades is effectively enhanced, preventing deformation during machining. The specially designed alloy casting process covers the entire blade, and precise machining ensures a flat support surface, providing a stable reference for subsequent machining. The application of dynamic clamping technology maintains optimal clamping at different machining stages. The outer pressure plate is used for alloy casting, finishing, and blade tip machining, while the inner pressure plate is used for critical outer ring machining. This alternating clamping method significantly improves machining stability. The final alloy melting and removal process ensures no residue on the parts, fully preserving the rectifier's design features. The entire process, by optimizing the clamping position and enhancing structural rigidity, effectively solves common problems in aero-engine rectifier machining such as chatter and deformation, significantly improving machining accuracy and product yield. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of an aero-engine rectifier before machining, which is an application of the present invention.

[0023] Figure 2 This is a schematic diagram of the cross-section of an aero-engine rectifier before machining, which is an application of the present invention.

[0024] Figure 3 This is a schematic diagram of a cross-section of an aero-engine rectifier after machining, which is an application of the present invention.

[0025] Figure 4 This is a schematic diagram of the cross-section of the machined outer ring intake side and blade tip of an aero-engine rectifier, which is an application of the present invention.

[0026] Figure 5 This is a flowchart of a machining method for an aero-engine rectifier according to the present invention;

[0027] Among them, 1-outer ring, 2-rectifier blade, 3-intake side, 4-groove, 5-exhaust side, 6-blade body, 7-blade tip, A-the other side surface of groove 4, B-one side surface of groove 4, C-alloy upper surface, D-upper surface of rectifier outer ring, E-outer circle of rectifier, F-flow channel surface, G-positioning surface of turning fixture, H-inner retaining ring. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments 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. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0029] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0030] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0031] To enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings.

[0032] like Figure 5As shown, this embodiment of the invention provides a method for turning an aero-engine rectifier, including:

[0033] S101 assembles and aligns the rectifier;

[0034] S102 uses the outer pressure plate of the lathe to press the upper surface of the outer ring 1, and removes the inner pressure plate of the lathe;

[0035] S103 installs an inner retaining ring at the blade tip 7, and pours alloy between the blade body 6 of the rectifier blade. The outer side of the blade body 6 is poured to the outer ring 1, and the inner side of the blade body is poured to the inner retaining ring. The pouring height covers the blade body 6 and leaves room for trimming.

[0036] S104 is turned and repaired to make the upper surface of the alloy flat. The inner pressure plate is used to press the upper surface of the alloy, and the outer pressure plate is removed.

[0037] S105 is used to machine the intake side 3 of the outer ring 1, and the outer pressure plate is used to press the upper surface of the alloy, and the inner pressure plate is removed.

[0038] S106 is used to machine the blade tip 7. The outer pressure plate is removed. After removing the pressure plate, the alloy is heated and melted to complete the machining.

[0039] The detailed steps are as follows:

[0040] (1) Assembly: Clamp the rectifier on the lathe fixture and press the upper surface of the outer ring 1 with the inner pressure plate of the lathe fixture;

[0041] (2) Alignment: Align the outer circle and upper surface of the rectifier;

[0042] (3) Replace the pressure plate: Press the outer pressure plate to the upper surface of the outer ring 1, and remove the inner pressure plate;

[0043] (4) Casting: Install an inner retaining ring at the tip 7, and cast the alloy between the blade body 6 of the rectifier blade. Cast the outer side of the blade body to the outer ring 1, and the inner side of the blade body to the inner retaining ring. The casting height should cover the entire blade body 6, and leave room for trimming. After the alloy cools down, remove the inner retaining ring.

[0044] (5) Repair the pressing surface: Turn and repair the upper surface of the alloy poured on the blade body 6 to ensure that the alloy surface is flat, and control the amount of material removed by turning to ensure that the blade body 6 is not turned.

[0045] (6) Replace the pressure plate: Use the inner pressure plate to press the upper surface of the alloy, and remove the outer pressure plate;

[0046] (7) Turning the outer ring: Turning the intake side 3 of the outer ring 1;

[0047] (8) Replace the pressure plate: Use the outer pressure plate to press the upper surface of the alloy block, and remove the inner pressure plate;

[0048] (9) Turning the blade tip: Turning the blade tip 7;

[0049] (10) Melting: Remove the outer pressure plate, take the rectifier out of the lathe fixture, place the rectifier in the heating melting furnace, and take out the rectifier after the alloy is completely melted.

[0050] Position the outer ring 1 of the rectifier on the intake side 3 after turning, and repeat steps 1 to 10 to turn the exhaust side 5 of the outer ring 1.

[0051] Another embodiment of the present invention provides a turning method for an aero-engine rectifier. The structure of a certain type of aero-engine rectifier is shown below. Figure 1 The rectifier consists of an outer ring 1 and rectifier blades 2. The outer ring 1 is composed of an inlet side 3, a groove 4, and an exhaust side 5. The rectifier blades are composed of a blade body 6 and a blade tip 7. The inlet side 3, exhaust side 5, and blade tip 7 of the outer ring 1 are machined in combination, and the groove 4 on the outer ring 1 is the final surface before the combination machining. The cross-section of the rectifier before machining is shown in the figure. Figure 2 The section after turning is shown Figure 3 The cross-sections of the rectifier's machined outer ring inlet side and blade tips are shown below. Figure 4 During turning, a lathe fixture is used to fix and clamp the rectifier onto a vertical lathe. The lathe fixture is equipped with an outer clamping plate and an inner clamping plate. The turning procedure is as follows:

[0052] (1) Assembly: Clamp the rectifier on the lathe fixture and press the upper surface D of the outer ring 1 with the inner pressure plate of the lathe fixture;

[0053] (2) Alignment: Align the outer circle E and the upper surface D of the rectifier;

[0054] (3) Replace the pressure plate: Use the outer pressure plate to press the upper surface D of the outer ring 1, and remove the inner pressure plate;

[0055] (4) Casting: Install the inner retaining ring H at the blade tip 7, and cast the alloy between the blade body 6 of the rectifier blade. Cast the outer side of the blade body to the flow channel surface F, and cast the inner side of the blade body to the inner retaining ring H. The casting height should completely cover the blade body 6, and leave a trimming allowance of 3mm to 5mm. After the alloy cools down, remove the inner retaining ring H.

[0056] (5) Repair the pressing surface: Turn and trim the alloy upper surface C cast on the blade body 6 to ensure that the alloy upper surface C is flat, and control the amount of material removed by turning to ensure that the blade body 6 is not turned.

[0057] (6) Replace the pressure plate: Use the inner pressure plate to press the upper surface C of the alloy, and remove the outer pressure plate;

[0058] (7) Turning the outer ring: Turning the intake side 3 of the outer ring 1;

[0059] (8) Replace the pressure plate: Use the outer pressure plate to press the upper surface C of the alloy block, and remove the inner pressure plate;

[0060] (9) Turning the blade tip: Turning the blade tip 7;

[0061] (10) Melting: Remove the outer pressure plate, take the rectifier out of the lathe fixture, place the rectifier in the heating melting furnace, and take out the rectifier after the alloy is completely melted.

[0062] Position the outer ring 1 of the rectifier on the intake side 3 after turning, and repeat steps 1 to 10 to turn the exhaust side 5 of the outer ring 1.

[0063] Although embodiments of the present invention have been described above in conjunction with the accompanying drawings, the present invention is not limited to the specific embodiments and application fields described above. The specific embodiments described above are merely illustrative and instructive, and not restrictive. Those skilled in the art, guided by the specification, can make many other modifications without departing from the scope of the claims of the present invention, and all of these modifications are within the scope of protection of the present invention.

Claims

1. A method for turning an aero-engine rectifier, characterized in that, include: Assemble and align the rectifier; Press the outer edge of the lathe against the upper surface of the outer ring (1), and remove the inner edge of the lathe. Install an inner retaining ring at the tip (7), pour alloy between the blade body (6) of the rectifier blade, pour the outer side of the blade body (6) to the outer ring (1), pour the inner side of the blade body to the inner retaining ring, and pour the height to cover the blade body (6) and leave a trimming allowance. Turn and repair the upper surface of the alloy until it is flat, press the upper surface of the alloy with the inner pressure plate, and remove the outer pressure plate; The intake side (3) of the outer ring (1) is machined by turning, the upper surface of the alloy is pressed by the outer pressure plate, and the inner pressure plate is removed; The blade tip (7) is machined by turning. The outer pressure plate is removed. After removing the pressure plate, the alloy is heated and melted to complete the machining.

2. The method for machining an aero-engine rectifier according to claim 1, characterized in that, The rectifier is assembled by clamping it onto a lathe fixture and pressing the upper surface of the outer ring (1) with the inner pressure plate of the lathe fixture.

3. The method for machining an aero-engine rectifier according to claim 1, characterized in that, Aligning the rectifier specifically involves aligning the outer circumference and upper surface of the rectifier.

4. The method for machining an aero-engine rectifier according to claim 1, characterized in that, The alloy is poured between the blades (6) of the rectifier blade, with a pre-reserved trimming allowance of 3mm~5mm for the pouring height.

5. The method for machining an aero-engine rectifier according to claim 1, characterized in that, When machining the upper surface of the integrated metal to a flat surface, ensure that the blade body is not machined (6).

6. The method for machining an aero-engine rectifier according to claim 1, characterized in that, The lathe is equipped with alternating inner and outer pressure plates to switch the clamping position at different machining stages.

7. The method for machining an aero-engine rectifier according to claim 1, characterized in that, After removing the pressure plate, heat and melt the alloy. Once the alloy is completely melted, remove the rectifier to complete the processing.

8. The method for machining an aero-engine rectifier according to claim 1, characterized in that, The alloy is cast in an in-machine casting process.

9. A method for machining an aero-engine rectifier according to claim 1, characterized in that, It also includes repeatedly machining the exhaust side (5) with the intake side (3) of the machined rectifier outer ring (1) positioned.

Images