CN110497162B - Machining method of aeroengine case - Google Patents

Machining method of aeroengine case Download PDF

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CN110497162B
CN110497162B CN201910897380.6A CN201910897380A CN110497162B CN 110497162 B CN110497162 B CN 110497162B CN 201910897380 A CN201910897380 A CN 201910897380A CN 110497162 B CN110497162 B CN 110497162B
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finish
hole
small end
face
longitudinal
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CN110497162A (en
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王颖囡
余岩
赵朝刚
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Wuxi Hyatech Technology Co ltd
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Wuxi Hyatech Technology Co ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass

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Abstract

The invention provides a machining method of an aircraft engine casing, which can solve the problems of large casing deformation, low machining precision, long manufacturing period and large machining difficulty of the existing machining method of the casing. Which comprises the following steps: blank size review → rough turning of the large end and the small end → rough milling of the outline of the shape → stress relief heat treatment → correction of the reference of the large end and the reference of the small end → finish milling of the two side faces of the longitudinal mounting side and the longitudinal mounting side hole → cutting → trimming of the grinding line cutting end face → preassembly → semi-finish turning of the large end and the small end → drilling of the angular positioning hole → semi-finish milling of the shape → finish turning of the small end → finish milling of the shape and the small end mounting side hole, finish reaming of the longitudinal mounting side hole → finish turning of the large end → finish milling of the large end mounting side hole → tapping → laser marking → color inspection → fluorescence penetrant inspection → final inspection.

Description

Machining method of aeroengine case
Technical Field
The invention relates to the field of case processing, in particular to a processing method of an aircraft engine case.
Background
In the new generation of aircraft engines, there are many casings, such as inlet casing, bypass casing, fan casing, compressor casing, combustor casing, turbine casing, etc., and the metallurgical, manufacturing quality and performance level thereof have a decisive influence on the improvement of reliability, safety, life and performance of the engine.
The aeroengine casing is mostly made of high-temperature alloy, titanium alloy and other materials. FIG. 1 is a view of an aircraft engine casing made of a high-temperature alloy material, which is a thin-wall annular structure, one end of which has a smaller diameter and is called a small end, the other end of which has a larger diameter and is called a large end, end faces of the small end and the large end are respectively called a small end reference and a large end reference, the small end and the large end are respectively provided with a small end mounting edge 1 and a large end mounting edge 2, and the small end mounting edge and the large end mounting edge are circumferentially provided with precise hole systems (namely a small end mounting edge hole 3 and a large end mounting edge hole 4); the casing is of a split structure, the joint of two half rings is provided with a longitudinal mounting edge 5, a precise hole system (namely a longitudinal mounting edge hole 6) is also processed on the longitudinal mounting edge, and the two half rings are connected together through a bolt and a nut which are mounted on the longitudinal mounting edge; the outer profile of the casing is also distributed with a plurality of characteristic islands, bosses 7, hole systems, grooves, ribs and other characteristics, the bosses 7 are provided with central holes 13, and the bosses 7 are also provided with threaded holes 8.
The aeroengine casing has a complex structure, and the requirements on machining precision of each assembly dimension, tolerance of a mold position and surface machining integrity are very high. The high-temperature alloy material is hard, the thickness of the casing is thin, the plastic deformation is large during processing, and the casing is easily influenced by clamping force, cutting force and residual stress generated in the machining process to cause deformation during the processing process, so that the casing is one of the parts with the largest processing difficulty in the field of aeroengine manufacturing for many years. With the continuous improvement of requirements of an aircraft engine on a casing, the existing casing processing method is difficult to meet the processing requirements of a thin-wall casing, the deformation of the casing is large, the processing precision is low, the manufacturing period is long, and the processing difficulty is large.
Disclosure of Invention
The invention provides a machining method of an aircraft engine casing, aiming at the technical problems of large deformation of the casing, low machining precision, long manufacturing period and large machining difficulty of the existing machining method of the casing.
The technical scheme is as follows: a machining method of an aircraft engine case is characterized by comprising the following steps:
step 1, checking the size of a blank: measuring the size of the annular blank, ensuring that each processing surface is provided with allowance, and checking whether the surface quality of the blank is free of defects;
step 2, rough turning of a large end and a small end: turning to remove most of machining allowance of the blank, reserving uniform allowance for semi-finish turning and finish turning procedures, and reserving a process boss when machining a large-end inner hole;
step 3, roughly milling the profile: the large-end inner hole is used for positioning by supporting the large-end face of the part, the process boss is pressed tightly, the inner wall face of the part is supported in an auxiliary mode, and the outline, the boss and the longitudinal installation edge of the part are roughly milled;
step 4, stress relief heat treatment;
step 5, repairing the big end reference and the small end reference: removing a small amount of allowance from the end face of the large end and the end face of the small end of the part, and correcting the rest structures on the large end and the small end to ensure the parallelism and the verticality of the large end reference and the small end reference;
step 6, finely milling two side surfaces of the longitudinal installation edge and a longitudinal installation edge hole: the large end face of the part is supported, the large end inner hole is used for positioning, the process boss is pressed tightly, and the two side faces of the longitudinal installation edge and the longitudinal installation edge hole are subjected to finish milling;
and 7, cutting: finding two sides of the two longitudinal mounting edges, aligning centers of the two longitudinal mounting edges, and uniformly cutting the part into two halves along a bisector of the longitudinal mounting edges by using a wire-moving cutting machine;
step 8, grinding and repairing the wire-cut end face: inspecting and grinding the linear cutting end face in the step 7 by using a coloring method, wherein the linear cutting end face is required to be continuous and not less than 80% in area;
step 9, preassembly: mounting a process bolt and a nut in the longitudinal mounting side hole, combining the two half ring parts together and screwing down;
step 10, semi-finish turning a large end and a small end: the small end face of the part is supported and positioned by the excircle of the small end, the large end of the part is semi-finish turned, and meanwhile, uniform allowance is reserved for the finish turning process; the large end face of the part is supported and positioned by the excircle of the large end, the small end of the part is semi-finish turned, and meanwhile, uniform allowance is reserved for the finish turning process;
step 11, drilling an angular positioning hole: drilling a precision hole on the process boss to serve as an angular positioning hole of the next procedure;
step 12, semi-finish milling the shape: during clamping, fixing the angular position of the part by using a pin matched with the angular positioning hole, supporting the part against the large-end face of the part, positioning by using a large-end inner hole, assisting in supporting the inner wall face of the part, semi-finish milling the outline of the part, the central holes of a boss and the boss, and semi-finish milling the outer side face of a longitudinal mounting edge;
step 13, finely turning the small end: during clamping, the bottom surface of the process boss is supported, the process boss is positioned by the inner hole of the process boss, the top surface of the process boss is tightly pressed, and the small end is subjected to finish turning to reach the size required by a design drawing;
step 14, finish milling the outer shape and the small end mounting side hole, and finish reaming the longitudinal mounting side hole: the part clamping mode is the same as the step 13, and auxiliary supports are added on the inner profile of the part; finish milling a small end mounting edge hole, finish milling an outline, a boss and a center hole of the boss, avoiding a longitudinal mounting edge and the interference position of the process bolt, and finish milling the position of the longitudinal mounting edge and a finish reaming longitudinal mounting edge hole;
step 15, finish turning the big end: during clamping, the bottom surface of the small end mounting edge of the part is supported, the excircle of the small end is positioned, the top surface of the small end mounting edge is pressed, and the large end is subjected to finish turning processing to reach the size required by a design drawing;
step 16, finish milling a large-end mounting side hole: the part clamping mode is the same as the step 15, and a large-end mounting side hole is finely milled;
step 17, tapping: manually tapping on a boss in the shape of the part with the aid of a tapping guide sleeve clamp;
step 18, laser marking: carrying out laser marking on the part at a designated position according to design requirements;
step 19, coloring inspection: coloring and checking the large-end mounting edge face and the small-end mounting edge face of the casing according to the requirements of a design drawing, and repairing the casing if the casing is unqualified until the casing is qualified;
step 20, fluorescence penetrant inspection: checking whether the machined surface of the part has defects such as cracks;
step 21, final inspection: and (4) carrying out three-coordinate detection on the part to see whether the design requirement of the casing is completely met.
It is further characterized in that:
in step 2, the allowance reserved when the large end and the small end are roughly turned is as follows: the large end outer circle and the small end outer circle are reserved with 4mm allowance in diameter, the large end inner circle is in diameter, 4mm allowance is reserved on the basis of the process boss, the small end inner circle is reserved with 4mm allowance, and the part is reserved with 6mm allowance in the height direction.
And 5, removing 1mm of allowance from the end face of the large end and the end face of the small end of the part respectively.
In step 10, the allowance left for the finish turning process is 1 mm.
In step 11, the diameter of the angular positioning hole is 6 mm.
In step 14, the method for finish milling the position of the longitudinal mounting edge and finish reaming the longitudinal mounting edge hole comprises the following steps: firstly, milling a longitudinal installation edge on one side, sequentially taking down one process bolt from top to bottom to perform finish milling of the longitudinal installation edge of a corresponding region and finish reaming of a longitudinal installation edge hole, after the corresponding region of one process bolt is machined, installing the process bolt and the nut back and screwing, then taking down one process bolt to perform machining of the corresponding region until the machining of the longitudinal installation edge on one side is finished, and then machining the longitudinal installation edge on the other side by using the same method.
The invention has the beneficial effects that:
according to the processing method of the casing, the process boss is reserved when the large end is roughly turned, and the angular positioning hole is drilled in the process boss, so that the subsequent rough milling, semi-finish milling, finish milling and finish turning processing are facilitated to clamp the part, clamping interference in the processing process is effectively avoided, the processing is more convenient, the processing efficiency is higher, the stress removing treatment is carried out after the appearance is roughly milled, the finish processing procedure is carried out after the stress is released, and the splitting procedure is arranged before the semi-finish processing, so that the processing deformation of the casing is small, and the processing precision is greatly improved.
Drawings
FIG. 1 is a schematic view of the overall structure of an aircraft engine case;
FIG. 2 is a front cross-sectional view of a blank for use in the present invention;
FIG. 3 is a schematic view of the rough turned large end of the present invention;
FIG. 4 is a schematic view of the rough turned small end of the present invention;
FIG. 5 is a top view of the rough milled profile of the present invention;
FIG. 6 is a cross-sectional view taken along line A-A of FIG. 5;
FIG. 7 is a schematic view of a trimming end reference according to the present invention;
FIG. 8 is a schematic view of a modified end datum of the present invention;
FIG. 9 is a schematic view of the finish milling of both sides of the longitudinal mounting edge and the longitudinal mounting edge hole of the present invention;
FIG. 10 is a cross-sectional view taken along line B-B of FIG. 9;
FIG. 11 is a schematic cut-away view of the present invention;
FIG. 12 is a pre-assembly view of the present invention;
FIG. 13 is a schematic view of a semi-finished small end of the present invention;
FIG. 14 is a schematic view of a semi-finished large end of the present invention;
FIG. 15 is a schematic view of an angular positioning hole of the present invention;
FIG. 16 is a top view of a semi-finish milled profile of the present invention;
FIG. 17 is a cross-sectional view taken along line C-C of FIG. 16;
FIG. 18 is a cross-sectional view taken along line D-D of FIG. 16;
FIG. 19 is a schematic view of a finish turning small end of the present invention;
FIG. 20 is a schematic view of a finishing big end of the present invention.
Reference numerals: 1-small end mounting edge; 2-large end mounting edge; 3-installing a side hole at the small end; 4-installing side holes at the big end; 5-longitudinal installation edges; 6-longitudinally installing side holes; 7-a boss; 8-a threaded hole; 9-processing a boss; 10-process bolt; 11-a nut; 12-angular positioning holes; 13-center hole.
Detailed Description
Referring to fig. 1 to 20, the processing method of the aeroengine case of the present invention includes the following steps:
step 1, checking the size of a blank: measuring the size of the annular blank, ensuring that allowance is reserved on each processing surface, checking the surface quality of the blank, and avoiding forging defects such as slag inclusion, cracks, defects and the like, wherein the structure of the blank is shown in figure 2, and the shape of parts inside a section line in figure 2 represents the shape of a finished casing;
step 2, rough turning of a large end and a small end: on a numerical control lathe, supporting against one end face of a blank, positioning the excircle of the blank, roughly turning a large end, removing most of machining allowance of the large end of the blank, and reserving a process boss 9 when machining the inner hole of the large end, as shown by the thick-line part in fig. 3; then, the large end face of the blank is supported, the large end inner hole is used for positioning, the small end is roughly turned, and most of machining allowance of the small end of the blank is removed, as shown by a thick line part in the figure 4; the method comprises the following steps of roughly turning a large end and a small end, reserving uniform allowance for semi-finish turning and finish turning, specifically, reserving 4mm allowance on the diameter of an outer circle of the large end and an outer circle of the small end, reserving 4mm allowance on the diameter of the inner circle of the large end on the basis of a process boss, reserving 4mm allowance on the diameter of the inner circle of the small end, and reserving 6mm allowance in the height direction of a part;
step 3, roughly milling the profile: the large-end face of the part is supported, the large-end inner hole is used for positioning, the process boss 9 is pressed tightly, the inner wall face of the part is supported in an auxiliary mode, the outline of the part, the boss 7 and the longitudinal installation edge 5 are roughly milled by a five-axis numerical control machining center (all holes comprise a small-end installation edge hole, a large-end installation edge hole, a longitudinal installation edge hole and a central hole of the boss which are not machined), and the method is shown in the figures 1, 5 and 6;
step 4, stress relief heat treatment, namely performing stress relief treatment after rough machining is finished, wherein the stress relief treatment is mainly based on the consideration of eliminating internal stress generated in the rough machining stage, so that errors generated in machining are reduced, and the machining precision of parts is ensured;
step 5, repairing the big end reference and the small end reference: based on the deformation of stress release after aging, the large-end datum and the small-end datum need to be revised again, the parallelism and the perpendicularity of the large-end datum and the small-end datum are ensured, and a datum plane is provided for subsequent processing; when the small end is repaired, the small end is supported against the end face of the large end of the part, the excircle of the large end is used for positioning, the allowance of 1mm is removed from the end face of the small end of the part, and other structures on the small end are modified, as shown by the thick line part in fig. 7; when the end is repaired, the end face of the small end of the part is supported, the excircle of the small end is used for positioning, the allowance of 1mm is removed from the end face of the large end of the part, and other structures on the large end are modified, as shown by a thick line part in fig. 8;
step 6, finely milling two side surfaces of the longitudinal installation edge 5 and a longitudinal installation edge hole 6: the large end face of the part is supported and supported, the large end inner hole is used for positioning, the process boss 9 is pressed tightly, and the two side faces of the longitudinal mounting edge 5 and the longitudinal mounting edge hole 6 are subjected to finish milling by using a five-axis numerical control machining center, as shown in a thick line part added in fig. 9 and fig. 10;
and 7, cutting: finding two sides of the two longitudinal mounting edges 5, aligning the centers of the two longitudinal mounting edges, and uniformly cutting the part into two halves along the bisector of the longitudinal mounting edges by using the wire-moving cutting machine, as shown in fig. 11;
step 8, grinding and repairing the wire-cut end face: checking and grinding the linear cutting end face in the step 7 by using a coloring method, wherein the continuous uninterrupted area is required, and the area is not less than 80%, so that the two half rings after cutting can be better combined together;
step 9, preassembly: installing a technical bolt 10 and a nut 11 into the longitudinal installation side hole 5, combining the two half ring parts together and screwing the two half ring parts together, as shown in figure 12;
step 10, semi-finish turning a large end and a small end: semi-finish turning is to remove the stress deformation allowance of the combined casing; the large end face of the part is supported and positioned by the excircle of the large end, the small end of the part is semi-finish turned, and meanwhile, 1mm of allowance is reserved for the finish turning process, as shown by the thick line part in FIG. 13; the small end face of the part is supported and positioned by the excircle of the small end, the large end of the part is semi-finish turned, and meanwhile, 1mm allowance is reserved for the finish turning process, as shown by the thick line part in FIG. 14;
step 11, drilling an angular positioning hole 12: drilling a precision hole with the diameter of 6mm on the process boss 9 as an angular positioning hole 12 of the next process, as shown in FIG. 15;
step 12, semi-finish milling the shape: during clamping, a pin with the diameter of 6mm is inserted into the angular positioning hole 12 to fix the angular position of the part, the part is supported against the end face of the large end of the part and positioned by an inner hole of the large end, the inner wall face of the part is supported in an auxiliary mode, the outline of the part, the boss 7 and the central hole 13 of the boss 7 are semi-finish-milled by a five-axis numerical control machining center, and the outer side face of the longitudinal mounting edge 5 is semi-finish-milled, as shown in fig. 1, 16 to 18; the angular positioning is added, so that the part is prevented from being loosened due to cutting force when the longitudinal mounting edge is machined; because the center hole of the boss is larger, the processing quality can be further ensured by firstly performing semi-finish milling processing and then performing subsequent finish milling processing;
step 13, finely turning the small end: during clamping, the bottom surface of the process boss 9 is supported, the inner hole of the process boss 9 is used for positioning, the top surface of the process boss 9 is tightly pressed, and the small end is subjected to finish turning to reach the size required by a design drawing, as shown by adding a thick line in fig. 19;
step 14, finish milling the outer shape and the small end mounting side hole 3, and finish reaming the longitudinal mounting side hole 6: after the machining of the previous procedure is finished, the fixture and the part are transferred to a five-axis numerical control machining center together, and an auxiliary support is added on an inner profile for milling, so that the situation that the part is not easy to clamp due to deformation of the mounting edge surface of the part after the turning is finished can be prevented; finish milling tip installation limit hole 3 earlier, finish milling profile, boss 7 and boss 7's centre bore 13 and avoid vertical installation limit 5 and technology bolt 10 to interfere the position again, finish milling vertical installation limit 5 position and the vertical installation limit hole 6 of finish reaming at last, wherein, the method of finish milling vertical installation limit position and the vertical installation limit hole of finish reaming is: firstly, milling a longitudinal installation edge 5 on one side, sequentially taking down a process bolt 10 from top to bottom to finish milling the longitudinal installation edge 5 in a corresponding area and finish reaming a longitudinal installation edge hole 6, after the corresponding area of the process bolt 10 is machined, installing the process bolt 10 and a nut 11 back and tightly, then taking down the process bolt 10 to machine the corresponding area until the longitudinal installation edge 5 on one side is machined, and machining the longitudinal installation edge 5 on the other side by using the same method, so that the machining precision and the machining quality can be effectively ensured;
step 15, finish turning the big end: during clamping, the bottom surface of the small end mounting edge 3 of the part is supported, the excircle of the small end is positioned, the top surface of the small end mounting edge 3 is compressed, the large end is subjected to finish turning and the process boss 9 is removed, and the size required by a design drawing is achieved, as shown by adding a thick line in a drawing 20;
step 16, finish milling the large end mounting side hole 4: after the machining of the previous procedure is finished, the fixture and the part are transferred to a five-axis numerical control machining center together, and a large-end mounting side hole 4 is subjected to finish milling, namely, the large-end mounting side hole is subjected to finish turning and finish milling through one-time clamping, so that the requirement on the position degree of the part mounting side hole is met;
step 17, tapping: under the assistance of a tapping guide sleeve clamp (belonging to the conventional clamp), a threaded hole 8 is manually tapped on a boss 7 of the part appearance, and because the inner diameter of the screw thread of a casing is smaller, manual tapping is mainly used;
step 18, laser marking: carrying out laser marking on the part at a designated position according to design requirements;
step 19, coloring inspection: coloring and checking the large-end mounting edge face and the small-end mounting edge face of the casing according to the requirements of a design drawing, and repairing the casing if the casing is unqualified until the casing is qualified;
step 20, fluorescence penetrant inspection: checking whether the machined surface of the part has defects such as cracks;
step 21, final inspection: and (4) carrying out three-coordinate detection on the part to see whether the design requirement of the casing is completely met.

Claims (6)

1. A machining method of an aircraft engine case is characterized by comprising the following steps:
step 1, checking the size of a blank: measuring the size of the annular blank, ensuring that each processing surface is provided with allowance, and checking whether the surface quality of the blank is free of defects;
step 2, rough turning of a large end and a small end: turning to remove most of machining allowance of the blank, reserving uniform allowance for semi-finish turning and finish turning procedures, and reserving a process boss when machining a large-end inner hole;
step 3, roughly milling the profile: the large-end inner hole is used for positioning by supporting the large-end face of the part, the process boss is pressed tightly, the inner wall face of the part is supported in an auxiliary mode, and the outline, the boss and the longitudinal installation edge of the part are roughly milled;
step 4, stress relief heat treatment;
step 5, repairing the big end reference and the small end reference: removing a small amount of allowance from the end face of the large end and the end face of the small end of the part, and correcting the rest structures on the large end and the small end to ensure the parallelism and the verticality of the large end reference and the small end reference;
step 6, finely milling two side surfaces of the longitudinal installation edge and a longitudinal installation edge hole: the large end face of the part is supported, the large end inner hole is used for positioning, the process boss is pressed tightly, and the two side faces of the longitudinal installation edge and the longitudinal installation edge hole are subjected to finish milling;
and 7, cutting: finding two sides of the two longitudinal mounting edges, aligning centers of the two longitudinal mounting edges, and uniformly cutting the part into two halves along a bisector of the longitudinal mounting edges by using a wire-moving cutting machine;
step 8, grinding and repairing the wire-cut end face: inspecting and grinding the linear cutting end face in the step 7 by using a coloring method, wherein the linear cutting end face is required to be continuous and not less than 80% in area;
step 9, preassembly: mounting a process bolt and a nut in the longitudinal mounting side hole, combining the two half ring parts together and screwing down;
step 10, semi-finish turning a large end and a small end: the small end face of the part is supported and positioned by the excircle of the small end, the large end of the part is semi-finish turned, and meanwhile, uniform allowance is reserved for the finish turning process; the large end face of the part is supported and positioned by the excircle of the large end, the small end of the part is semi-finish turned, and meanwhile, uniform allowance is reserved for the finish turning process;
step 11, drilling an angular positioning hole: drilling a precision hole on the process boss to serve as an angular positioning hole of the next procedure;
step 12, semi-finish milling the shape: during clamping, fixing the angular position of the part by using a pin matched with the angular positioning hole, supporting the part against the large-end face of the part, positioning by using a large-end inner hole, assisting in supporting the inner wall face of the part, semi-finish milling the outline of the part, the central holes of a boss and the boss, and semi-finish milling the outer side face of a longitudinal mounting edge;
step 13, finely turning the small end: during clamping, the bottom surface of the process boss is supported, the process boss is positioned by the inner hole of the process boss, the top surface of the process boss is tightly pressed, and the small end is subjected to finish turning to reach the size required by a design drawing;
step 14, finish milling the outer shape and the small end mounting side hole, and finish reaming the longitudinal mounting side hole: the part clamping mode is the same as the step 13, and auxiliary supports are added on the inner profile of the part; finish milling a small end mounting edge hole, finish milling an outline, a boss and a center hole of the boss, avoiding a longitudinal mounting edge and the interference position of the process bolt, and finish milling the position of the longitudinal mounting edge and a finish reaming longitudinal mounting edge hole;
step 15, finish turning the big end: during clamping, the bottom surface of the small end mounting edge of the part is supported, the excircle of the small end is positioned, the top surface of the small end mounting edge is pressed, and the large end is subjected to finish turning processing to reach the size required by a design drawing;
step 16, finish milling a large-end mounting side hole: the part clamping mode is the same as the step 15, and a large-end mounting side hole is finely milled;
step 17, tapping: manually tapping on a boss in the shape of the part with the aid of a tapping guide sleeve clamp;
step 18, laser marking: carrying out laser marking on the part at a designated position according to design requirements;
step 19, coloring inspection: coloring and checking the large-end mounting edge face and the small-end mounting edge face of the casing according to the requirements of a design drawing, and repairing the casing if the casing is unqualified until the casing is qualified;
step 20, fluorescence penetrant inspection: checking whether the machined surface of the part has defects;
step 21, final inspection: and (4) carrying out three-coordinate detection on the part to see whether the design requirement of the casing is completely met.
2. The machining method of the aero-engine case according to claim 1, wherein the machining method comprises the following steps: in step 2, the allowance reserved when the large end and the small end are roughly turned is as follows: the large end outer circle and the small end outer circle are reserved with 4mm allowance in diameter, the large end inner circle is in diameter, 4mm allowance is reserved on the basis of the process boss, the small end inner circle is reserved with 4mm allowance, and the part is reserved with 6mm allowance in the height direction.
3. The machining method of the aero-engine case according to claim 1, wherein the machining method comprises the following steps: and 5, removing 1mm of allowance from the end face of the large end and the end face of the small end of the part respectively.
4. The machining method of the aero-engine case according to claim 1, wherein the machining method comprises the following steps: in step 10, the allowance left for the finish turning process is 1 mm.
5. The machining method of the aero-engine case according to claim 1, wherein the machining method comprises the following steps: in step 11, the diameter of the angular positioning hole is 6 mm.
6. The machining method of the aero-engine case according to claim 1, wherein the machining method comprises the following steps: in step 14, the method for finish milling the position of the longitudinal mounting edge and finish reaming the longitudinal mounting edge hole comprises the following steps: firstly, milling a longitudinal installation edge on one side, sequentially taking down one process bolt from top to bottom to perform finish milling of the longitudinal installation edge of a corresponding region and finish reaming of a longitudinal installation edge hole, after the corresponding region of one process bolt is machined, installing the process bolt and the nut back and screwing, then taking down one process bolt to perform machining of the corresponding region until the machining of the longitudinal installation edge on one side is finished, and then machining the longitudinal installation edge on the other side by using the same method.
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