A method for machining a single piece of annular assembly mounting edge of an aero-engine and a composite fixture.

Abstract

This invention discloses a machining method and a composite fixture for a single ring-shaped assembly mounting edge component of an aero-engine. The composite fixture includes a left side plate, a back plate, and a right side plate. Supports are provided at the upper and lower ends of the left and right side plates, respectively. A tool-setting surface is provided between the supports, and a thread-setting surface is provided between the left side plate and the back plate. This invention utilizes the composite fixture to complete the side grinding and elongated hole machining of the ring-shaped assembly mounting edge component in a single clamping operation, ensuring the positional and dimensional accuracy requirements after machining, meeting the machining consistency requirements of the ring-shaped assembly mounting edge component, allowing multiple ring-shaped assembly mounting edge components to be interchanged, minimizing assembly errors, and improving the assembly efficiency of the ring-shaped assembly.

Description

Technical Field

[0001] This invention belongs to the field of machining technology, specifically a process fixture and its machining method for precise machining of single parts of a ring-shaped assembly. By improving the machining accuracy of single parts, the consistency of the ring-shaped assembly is achieved, while improving the interchangeability of parts. Background Technology

[0002] Ring-shaped assembly mounting edge (e.g.) Figures 1-3 The nozzle is a key connecting component of the nozzle converging section of a turbofan aero-engine. Its main function is to serve as the basic component of the nozzle converging section, installing adjusting plates and sealing plates to realize the nozzle converging function, and transmitting the thrust brought by the high temperature and high pressure gas ejected to the power transmission components of the engine. Therefore, its installation accuracy and strength directly affect the engine thrust conversion effect and the reliability of operation.

[0003] Based on the functional and installation size requirements of the expansion and contraction nozzle, a certain number of end holes with high positional accuracy are distributed on the front and rear faces of the annular assembly mounting edge. Furthermore, the front and rear faces also have high requirements for flatness and parallelism. In order to ensure the dimensional accuracy and consistency of the assembled annular assembly mounting edge, each component of the annular assembly mounting edge also needs to have a certain degree of interchangeability. Therefore, higher requirements are put forward for the profile and positional dimensions of each component.

[0004] The annular assembly mounting edge is annular in shape with a conical wall. The annular assembly mounting edge is formed by mechanically connecting 18 individual precision-cast parts after machining. Each part includes two large-diameter threaded holes, two lugs and lug holes. The lug holes serve as the connecting seat for the nozzle actuator cylinder. Each part has two through holes of different sizes on its side wall. One set of holes and the lug holes together serve as the base for the actuator cylinder. The other set of holes and the threaded holes are used together for connecting and assembling the various parts to form an annular conical shape.

[0005] Based on the composition of the annular assembly edge, it can be seen that due to the large number of parts, the cumulative effect of their combined dimensional tolerances is quite significant. Therefore, the dimensional changes of each individual part will have a great impact on the overall dimensions of the assembly. In order to ensure the stability of the machining process and the dimensional qualification rate after the annular assembly edge is assembled, higher precision requirements are needed for the machining tolerances of individual parts. That is, the functional dimensions of the outer fan-shaped boundary of the individual parts and the hole dimensions connecting the individual parts need to be controlled with very high dimensional accuracy in order to meet the machining requirements of the assembly.

[0006] Because the precision requirements of the ring-shaped assembly are high, the current processing approach is to first mill the front and rear ends of the single piece, then grind them, and drill positioning holes on the end faces as a reference for grinding and drilling the side connection holes.

[0007] In the above process, the outer contour is machined using end face holes for positioning, and the part needs to be clamped and positioned multiple times during single-sided machining. As a result, the dimensional tolerance of the side surface deviates significantly after grinding, leading to instability in the overall dimensions of the assembled annular mounting edge. Multiple alignments and adjustments are required during machining, and it may even be impossible to machine to the required dimensions.

[0008] In addition, each individual piece is installed by alignment through side holes and connected using cylindrical pins, screws, and bolts. To improve the reliability of the connection, the side positioning holes of the parts are designed as deep-cavity circular holes. The hole diameter and the position of the hole relative to the end face have very high requirements. The perpendicularity requirement for the end face of the hole, i.e., the fan-shaped side, is no more than 0.2mm per 100mm, and the parallelism requirement for the threaded connection hole is also no more than 0.2mm per 100mm. Since there are corresponding holes on both sides of the fan shape, the traditional process is to use drilling to process both sides and connect them using a flipping fixture. The current process suffers from mechanical errors due to the flipping surface, particularly the long holes used for positioning on each single surface. These holes exhibit varying degrees of deviation after drilling, resulting in significant height discrepancies between assembled components, making assembly difficult and failing to meet the assembly tolerance requirements for post-assembly machining. Consequently, many unusable individual parts are left unassembled, impacting the processing cost and product delivery efficiency of the annular assembly mounting edge. Based on these reasons, it is necessary to research a high-precision machining scheme for the high-fan-shaped surface and sidewall long holes of the annular assembly mounting edge single-piece precision casting. Summary of the Invention

[0009] The present invention aims to provide a machining method and composite fixture for a single ring-shaped mounting edge component of an aero-engine, achieving precise machining that meets the requirements for component matching. This ensures the accuracy of the side profile dimensions and the diameter of elongated holes, satisfies the vertical accuracy requirements of the side profile and the parallel accuracy requirements of the mounting edge connecting holes (threads), and improves the interchangeability of the components. Furthermore, the machining equipment used is simple and straightforward in structure, easy to operate, and provides stable and reliable machining, thereby improving machining efficiency and reducing component selection time and machining costs.

[0010] To achieve the above objectives, the present invention adopts the following technical solution:

[0011] A ring-shaped mounting edge for an aircraft engine, wherein the ring-shaped mounting edge is circular, and both the inner and outer ring surfaces of the ring-shaped mounting edge are conical. The ring-shaped mounting edge comprises multiple individual components, which are connected sequentially along the same circumference in a clockwise or counterclockwise direction to form the ring-shaped mounting edge. Each individual component constitutes an arc segment on the circular ring of the ring-shaped mounting edge. Each individual component further comprises:

[0012] The front end face and the rear end face are provided with end holes, and the front end face and the rear end face are respectively corresponding to the two end surfaces of the annular assembly mounting edge axis.

[0013] The inner conical surface is part of the inner ring surface that forms the inner ring surface of the annular assembly mounting edge;

[0014] The side surface is the connecting surface of two adjacent individual pieces, and there is an elongated hole with a circular cross-section on the side surface.

[0015] Alternatively, the individual component is a precision casting, and multiple individual components are detachably connected by the sides to form a ring-shaped assembly mounting edge.

[0016] A composite fixture for machining a single piece of annular assembly mounting edge of an aero-engine, comprising:

[0017] The main frame includes a left side plate and a right side plate spaced apart. Positioning holes are provided on the left side plate and the right side plate. The left side plate and the right side plate are connected by a back plate. The left side plate, the back plate and the right side plate form a space for assembling individual parts. The upper end of the left side plate is provided with a first left support leg and a second left support leg, and the lower end of the left side plate is provided with a third left support leg and a fourth left support leg. The upper end of the right side plate is provided with a first right support leg and a second right support leg, and the lower end of the right side plate is provided with a third right support leg and a fourth right support leg. The upper end faces of the first left support leg, the second left support leg, the first right support leg and the second right support leg are in the same plane. The lower end faces of the third left support leg, the fourth left support leg, the third right support leg and the fourth right support leg are in the same plane.

[0018] The four tool-setting surfaces are respectively arranged between the first left support and the second left support, between the third left support and the fourth left support, between the first right support and the second right support, and between the third right support and the fourth right support. The tool-setting surfaces between the first left support and the second left support and between the first right support and the second right support are in the same plane, and the tool-setting surfaces between the third left support and the fourth left support and between the third right support and the fourth right support are in the same plane.

[0019] The wire-faced surfaces are a pair of mutually perpendicular planes disposed between the left side plate and the back plate.

[0020] A method for machining a single component of an annular assembly mounting edge for an aero-engine includes the following steps:

[0021] Step 1: Prepare a single-piece blank using precision casting.

[0022] Step 2: Mill the front and rear faces of the single blank obtained in Step 1, and drill process reference holes on the front and rear faces.

[0023] Step 3: Assemble and position the single piece processed in Step 2 using a composite fixture that includes both the grinding tool face and the wire cutting wire face. Grind the two sides of the single piece on a grinding machine.

[0024] Step four: After completing step three, without disassembling the individual piece in the composite fixture, install the composite fixture containing the individual piece onto the wire cutting equipment. By adjusting the coordinates of the wire surface, the cutting wire is then inserted into the pre-made hole on the side of the precision-cast individual piece corresponding to the position of the long hole, and the size of the long hole is cut out.

[0025] Furthermore, in step two, the front and rear faces of the single part are milled to remove the casting allowance. While ensuring that the wall thickness conforms to the part drawing, the single part is supported and pressed by the inner conical surface. The front and rear faces of the single part are ground, and the allowance is retained on the outer surface of each end. The reference point specified in the design drawing is used as the positioning basis at the end hole position of the front and rear faces. The process reference hole for part processing is drilled. The diameter of the process reference hole is smaller than the final part hole size at the corresponding position.

[0026] Furthermore, in step two, the position corresponding to the design drawing on the inner conical surface of the single piece is used as a reference point for support and clamping.

[0027] Further, in step three, the single piece of raw material with the process reference hole machined is installed into the aforementioned composite fixture. Pins are inserted into the positioning holes on the right side plate and the end face holes on the rear end face of the single piece to position it. Hook bolts are used in the positioning holes on the left side plate to press the front end face of the single piece tightly against the inner wall of the left side plate. Then, screws are inserted into the positioning holes on the right side plate and pressed against the single piece towards the left side plate. The end faces of the eight legs on the composite fixture are checked; the first left leg, the second left leg, the first right leg, and the second right leg form a group, and the third... The left support leg, the fourth left support leg, the third right support leg, and the fourth right support leg form another set. Ensure that the end faces of both sets of support legs are in contact with the grinding machine table. Check the flatness of the tool setting face on the compound fixture. If the flatness is less than the set requirement, fix the compound fixture. Then, perform surface grinding on one side of the single piece. Stop grinding when the distance between the side and the tool setting face reaches the preset size. Check the flatness of the ground surface. If it meets the requirements, flip the compound fixture so that the other set of support legs are in contact with the grinding machine table. Use the same method to complete the grinding work on the other side of the single piece.

[0028] As an alternative, the flatness of the tool face of the fixture can be checked using a push-table method.

[0029] Alternatively, when the flatness is less than 0.02 mm, the composite fixture is fixed; the flatness of the grinding surface is checked, and if it is not greater than 0.02 mm, the composite fixture is flipped so that the other set of legs fits into the grinding table, and the grinding work on the other side of the single piece is completed in the same way.

[0030] Alternatively, in step four, the composite fixture for grinding the single-piece side in step three is not disassembled. The single piece is kept in the assembled state in the composite fixture. The composite fixture is installed on the wire EDM machine. The flatness of the two sides of the single piece is checked. If it is not greater than the flatness of the side after grinding in step three, the wire EDM wire is moved to the wire-aligning surface. After adjusting the coordinates, the wire EDM wire is inserted into the pre-made hole on the single piece corresponding to the position of the long hole during precision casting, and the wire EDM of the long hole is performed.

[0031] Compared with the prior art, the processing method and composite fixture of the present invention have the following advantages: (1) The process improvement of using a single mold (composite fixture) for two purposes (grinding and wire cutting) and one assembly for two-sided grinding avoids the assembly error caused by secondary assembly, improves the grinding accuracy and processing reliability, and ensures the size of the grinding parts by strictly controlling the position of the mounting reference surface (support end face) and the grinding tool setting surface, avoiding the phenomenon of poor processing accuracy and low processing efficiency caused by the existing grinding relying on grinding and measuring and adjusting the position of the grinding surface during the processing. The single-piece lug hole, end face through hole, threaded hole, etc. processed by it meet the design requirements.

[0032] (2) This invention improves the processing method of long holes on the side of a single piece. The change from drilling to wire cutting is another key innovation in the processing of long holes on the side of a single piece. It makes full use of the stress-free cutting processing method of wire cutting and, with the help of a high-precision composite fixture, achieves high-precision positioning without disassembly. It ensures the high precision requirements of the processing size and position size of the long hole in one go, and perfectly solves the problem of long cycle, low efficiency and continuous waste parts caused by selective assembly such as repeated installation and measurement of single pieces over a long period of time. Attached Figure Description

[0033] Figure 1 This is a partial schematic diagram of the ring-shaped assembly edge;

[0034] Figure 2 yes Figure 1 Rotated view of section AA;

[0035] Figure 3 This is an isometric view of the entire ring-shaped assembly edge;

[0036] Figure 4 This is a diagram showing the grinding process of the front and rear ends of a single piece in a ring-shaped assembly assembly.

[0037] Figure 5 This is a structural diagram of the machining of the long hole on the side of a single piece in a ring-shaped assembly installation;

[0038] Figure 6 This is an isometric drawing of a grinding and cutting compound fixture;

[0039] Figure 7 It corresponds Figure 6Right view of the compound fixture;

[0040] Figure 8 It corresponds Figure 6 Top view of the composite fixture;

[0041] Figure 9 yes Figure 8 Sectional view AA;

[0042] Figure 10 yes Figure 7 Partial view in the S-direction;

[0043] Figure 11 This is a schematic diagram showing the positions of four reference points on the inner conical surface of a single component in a ring-shaped assembly installation.

[0044] In the diagram, 1-left side panel, 2-right side panel, 3-back panel. Detailed Implementation

[0045] 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.

[0046] The key problems to be solved by this invention include:

[0047] First, how to ensure the accurate fixing of the side of a single part (single piece of ring-shaped assembly) during grinding and ensure that the machined surface can be accurately positioned according to its precision requirements, the precision and dimensional control of the tool surface during grinding, and the avoidance of machining deviations caused by assembly errors due to secondary assembly.

[0048] Second, the machining method for the long holes on the side of a single part (single piece of ring-shaped assembly) is improved by using wire cutting instead of long drill bit drilling, which avoids the deviation of long hole size and hole position perpendicularity caused by drill bit oscillation and small positioning surface in the machining of long holes with small plane positioning.

[0049] The technical requirements of this invention are achieved through the following technical solutions:

[0050] First, the machining process is integrated, and a set of composite tooling fixtures for grinding and wire cutting is designed. The composite fixture is a one-time clamping fixture, in which the part (a single piece of the ring-shaped assembly mounting edge) is accurately mounted and fixed in the middle of the composite fixture. The cutting surface on the composite fixture is set with a tool setting face with very accurate shape and position. The tool setting face has a strict positional relationship with the mounting base during machining, which ensures that a very accurate measurement reference can be obtained during grinding. At the same time, the use of this composite fixture eliminates the need for secondary assembly of parts, and the parts can be flipped for grinding, which improves the surface machining accuracy of the parts after grinding.

[0051] In addition, the composite fixture also has the function of clamping and positioning the long hole on the side of a single piece of wire-cutting without disassembling the parts (the ring-shaped assembly mounting edge single piece). By using the wire alignment surface on the composite fixture as a reference and moving the corresponding dimensions, it is possible to ensure that the cutting line is in the processing position required for the long hole. By pre-drilling small holes before processing, and by taking advantage of the precise base of the composite fixture and the vertical position relationship of the wire cutting, as well as the inorganic force-free characteristics of wire cutting, the processing of the long hole on the side of the single piece can be completed, ensuring the dimensional accuracy and positional accuracy of the long hole.

[0052] like Figure 6 As shown, the composite fixture designed in this invention includes a main frame, a tool setting surface, and a wire setting surface, wherein:

[0053] The main frame includes a left side plate 1 and a right side plate 2 spaced apart. Positioning holes are provided on the left side plate 1 and the right side plate 2. The left side plate 1 and the right side plate 2 are connected by a back plate 3. The left side plate 1, the back plate 3, and the right side plate 2 form a space for assembling individual components. The upper end of the left side plate 1 is provided with a first left support leg and a second left support leg, and the lower end of the left side plate 1 is provided with a third left support leg and a fourth left support leg. The upper end of the right side plate 2 is provided with a first right support leg and a second right support leg, and the lower end of the right side plate 2 is provided with a third right support leg and a fourth right support leg. The upper surfaces of the first left support leg, the second left support leg, the first right support leg, and the second right support leg are all in the same plane (e.g., ...). Figure 7 (As shown in the diagram, the lower end faces of the third left support, the fourth left support, the third right support, and the fourth right support are all on the same plane). Figure 7 (The four locations shown are on the same plane);

[0054] The four blade-setting surfaces are respectively positioned between the first left support and the second left support, between the third left support and the fourth left support, between the first right support and the second right support, and between the third right support and the fourth right support (e.g., Figure 6 (The positions indicated by the four arrows in the middle), and the tool-setting faces between the first left support and the second left support, and between the first right support and the second right support, are in the same plane; the tool-setting faces between the third left support and the fourth left support, and between the third right support and the fourth right support, are in the same plane; the shape of the tool-setting face is a plane, and the position is very accurate, requiring that every two faces be within the plane of the compound fixture with a tolerance of 0.01 and an inclination of 0.02, and are in line with... Figure 7 The references in the middle are in an accurate positional relationship (the inclination band is the reference source). The inclination of the tool face is based on A / B, and the inclination of the support foot is also based on A / B. This ensures the positional relationship between the support foot and the tool face.

[0055] The silk surface is a pair of mutually perpendicular planes set between the left side plate 1 and the back plate 3 (e.g., Figure 10 (The positions indicated by the two arrows).

[0056] like Figures 1-3 As shown, this is a single component of the ring-shaped assembly mounting edge of an aero-engine that needs to be processed according to the present invention. Figures 4 to 11 The diagram shows the composite fixture used for machining the ring-shaped assembly edge piece, as well as the assembly state diagram of the main machining process. When machining the ring-shaped assembly edge piece, a blank is first prepared using precision casting.

[0057] To meet the high-precision contour and hole size requirements of the ring-shaped assembly mounting edge piece, the front and rear faces of the ring-shaped assembly mounting edge piece are first milled to remove the casting allowance. While ensuring that the wall thickness conforms to the part drawing, the four points specified on the inner conical surface of the mounting edge piece are used. Figure 11 Use the positions indicated by the four arrows as reference points for support and tightening, as shown in the image. Figure 4 (Using four reference points as the references for the front and rear ends of the ring-shaped mounting edge and the two sides, as well as other features on the part, the front and rear ends and the end holes are first machined using the reference points as references as the fine references for subsequent machining. Then, other process steps are used to complete the machining of the surface and holes of the part.) Grind the front and rear ends of the mounting edge, leaving a 1mm allowance on the outer surface of each end. At the end hole position of the front and rear ends, the reference points specified in the design drawing are used as the positioning basis. The process reference holes for the part machining are drilled by drilling, and the hole diameter is 2mm smaller than the part hole size.

[0058] like Figure 6 , 7 8 and Figure 9 Using the pre-machined process reference holes as positioning, the annular assembly edge piece blank to be processed is installed onto the grinding and cutting composite fixture. The pins in the positioning holes of the two right side plates are positioned into a set of end holes of the annular assembly edge piece, and hook bolts (such as...) are used. Figure 8 The hook-shaped bolt shown on the right presses the part tightly against the positioning surface (inner wall surface of the left side plate 1) of the left side plate 1. A screw (such as...) located in the positioning hole on the right side plate 2 is used on the rear end face of the annular assembly mounting piece. Figure 8 (As shown on the left) Tighten the clamp, and check the end faces of the eight legs on the composite fixture (four in a group, such as...) Figure 7 Ensure that the end faces of the same set of support legs are in contact with the grinding machine table, and check the flatness of the tool face of the composite fixture using a dial indicator (e.g., ...). Figure 7(As indicated by the tool setting markings), when the flatness is less than 0.02mm, fix the composite fixture with the ring-shaped assembly mounting edge piece, and then perform surface grinding on the side of the ring-shaped assembly mounting edge piece. Stop grinding when the distance between the side of the ring-shaped assembly mounting edge piece and the tool setting surface is 0.5mm. Check that the flatness of the ground surface is not greater than 0.02mm, flip the composite fixture, and complete the grinding work on the other side using the same method.

[0059] Install the composite fixture with the annular assembly side piece onto the wire EDM machine. Fix the composite fixture on the table of the wire EDM machine. Check the flatness of the fan-shaped side of the machined annular assembly side piece. Ensure that the surface flatness is no greater than 0.02mm. Then move the wire EDM wire to the wire-aligning surface of the composite fixture (e.g., Figure 10 The two mutually perpendicular planes corresponding to the positions indicated by the two arrows (located on the surfaces of the left side plate 1 and the back plate 3, respectively) are used as the wire-aligning surfaces. Adjust the equipment coordinates to the initial values, and then move the equipment head to the position of the elongated hole on the annular assembly mounting edge (according to...). Figure 10 (Move the cutting wire at two points in the middle), thread the cutting wire through the pre-made hole in the single piece of the annular assembly, and adjust the program after threading the wire. Figure 5 Cut the wall of the elongated hole to the dimensions shown until the elongated hole is cut. Remove the cutting wire from the elongated hole to complete the wire cutting of the elongated hole on the side of the single piece of the ring assembly.

[0060] 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 composite fixture for machining a single piece of annular assembly mounting edge of an aero-engine, characterized in that: include, The main frame includes a left side plate (1) and a right side plate (2) spaced apart. Positioning holes are opened on the left side plate (1) and the right side plate (2). The left side plate (1) and the right side plate (2) are connected by a back plate (3). The left side plate (1), the back plate (3) and the right side plate (2) form a space for assembling individual parts. The upper end of the left side plate (1) is provided with a first left support leg and a second left support leg. The lower end of the left side plate (1) is provided with a third left support leg and a fourth left support leg. The upper end of the right side plate (2) is provided with a first right support leg and a second right support leg. The lower end of the right side plate (2) is provided with a third right support leg and a fourth right support leg. The upper end face of the first left support leg, the upper end face of the second left support leg, the upper end face of the first right support leg and the upper end face of the second right support leg are in the same plane. The lower end face of the third left support leg, the lower end face of the fourth left support leg, the lower end face of the third right support leg and the lower end face of the fourth right support leg are in the same plane. The four tool-setting surfaces are respectively arranged between the first left support and the second left support, between the third left support and the fourth left support, between the first right support and the second right support, and between the third right support and the fourth right support. The tool-setting surfaces between the first left support and the second left support and between the first right support and the second right support are in the same plane, and the tool-setting surfaces between the third left support and the fourth left support and between the third right support and the fourth right support are in the same plane. The pair of wire surfaces are a pair of mutually perpendicular planes disposed between the left side plate (1) and the back plate (3).

2. A method for processing a single component of an annular assembly mounting edge of an aero-engine, characterized in that: Includes the following steps, Step 1: Prepare a single-piece blank using precision casting. Step 2: Mill the front and rear faces of the single blank obtained in Step 1, and drill process reference holes on the front and rear faces. Step 3: Assemble and position the single piece processed in Step 2 using the composite fixture in claim 1, and grind the two sides of the single piece on a grinding machine respectively. Step four: After completing step three, without disassembling the individual piece in the composite fixture, install the composite fixture containing the individual piece onto the wire cutting equipment. By adjusting the coordinates of the wire surface, the cutting wire is then inserted into the pre-made hole on the side of the precision-cast individual piece corresponding to the position of the long hole, and the size of the long hole is cut out.

3. The processing method for a single component of the annular assembly mounting edge of an aero-engine according to claim 2, characterized in that: In step two, the front and rear faces of the single part are milled to remove the casting allowance. While ensuring that the wall thickness conforms to the part drawing, the single part is supported and pressed by the inner conical surface. The front and rear faces of the single part are ground, and the allowance is retained on the outer surface of each end. The reference point specified in the design drawing is used as the positioning basis at the end hole position of the front and rear faces. The process reference hole for part processing is drilled. The diameter of the process reference hole is smaller than the final part hole size at the corresponding position.

4. The processing method for a single component of the annular assembly mounting edge of an aero-engine according to claim 3, characterized in that: In step two, the position corresponding to the design drawing of the single piece on the inner conical surface of the single piece is used as a reference point for support and clamping.

5. The processing method for a single component of the annular assembly mounting edge of an aero-engine according to claim 2, characterized in that: In step three, the single piece of raw material with the process reference hole machined is installed into the composite fixture. A pin is inserted into the positioning hole on the right side plate (2) and the end face hole on the rear end face of the single piece to position it. A hook bolt is used in the positioning hole on the left side plate (1) to press the front end face of the single piece tightly against the inner wall of the left side plate (1). Then, a screw is inserted into the positioning hole on the right side plate (2) and pressed against the left side plate (1). The end faces of the eight legs on the composite fixture are checked; the first left leg, the second left leg, the first right leg, and the second right leg are one... The third left support, the fourth left support, the third right support, and the fourth right support form another group. Ensure that the end faces of both groups of supports are in contact with the grinding machine table. Check the flatness of the tool setting face on the compound fixture. If the flatness is less than the set requirement, fix the compound fixture. Then, perform surface grinding on one side of the single piece. Stop grinding when the distance between the side and the tool setting face reaches the preset size. Check the flatness of the ground surface. If it meets the requirements, flip the compound fixture so that the other group of supports is in contact with the grinding machine table. Use the same method to complete the grinding work on the other side of the single piece.

6. The processing method for a single piece of the annular assembly mounting edge of an aero-engine according to claim 5, characterized in that: The flatness of the tool face of the fixture is checked using a push-table method.

7. The processing method for a single piece of the annular assembly mounting edge of an aero-engine according to claim 5, characterized in that: The fixed composite clamp is used when the flatness is less than 0.02 mm. Check the flatness of the grinding surface. If it is not greater than 0.02mm, flip the compound fixture so that the other set of legs fits into the grinding table. Use the same method to complete the grinding work on the other side of the single piece.

8. The processing method for a single component of the annular assembly mounting edge of an aero-engine according to claim 2, characterized in that: In step four, the composite fixture for grinding the side of the single piece in step three is not disassembled. The single piece is kept in the assembled state in the composite fixture. The composite fixture is installed on the wire EDM machine. The flatness of the two sides of the single piece is checked. If it is not greater than the flatness of the side after grinding in step three, the wire EDM wire is moved to the wire-aligning surface. After adjusting the coordinates, the wire EDM wire is inserted into the pre-made hole on the single piece corresponding to the position of the long hole during precision casting, and the wire EDM of the long hole is performed.

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