CN117161695A - Method for machining thin-wall hollow long shaft of aeroengine - Google Patents
Method for machining thin-wall hollow long shaft of aeroengine Download PDFInfo
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- CN117161695A CN117161695A CN202311287449.6A CN202311287449A CN117161695A CN 117161695 A CN117161695 A CN 117161695A CN 202311287449 A CN202311287449 A CN 202311287449A CN 117161695 A CN117161695 A CN 117161695A
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- 238000007514 turning Methods 0.000 claims abstract description 72
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- 230000000171 quenching effect Effects 0.000 claims abstract description 12
- 230000032683 aging Effects 0.000 claims abstract description 9
- 238000003801 milling Methods 0.000 claims abstract description 9
- 238000005496 tempering Methods 0.000 claims abstract description 9
- 238000003672 processing method Methods 0.000 claims abstract description 7
- 238000000227 grinding Methods 0.000 claims abstract description 6
- 238000012545 processing Methods 0.000 claims description 26
- 229910045601 alloy Inorganic materials 0.000 claims description 8
- 239000000956 alloy Substances 0.000 claims description 8
- 238000009966 trimming Methods 0.000 claims description 7
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- 238000001514 detection method Methods 0.000 claims description 3
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- 238000013461 design Methods 0.000 description 8
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- 230000035882 stress Effects 0.000 description 4
- 229910001128 Sn alloy Inorganic materials 0.000 description 3
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Abstract
The invention provides a processing method of a thin-wall hollow long shaft of an aeroengine, which comprises the following steps: s1, roughly turning the appearance of a workpiece to be processed through a machine tool; s2, turning a first end reference and a second end reference of a workpiece to be processed to obtain a first workpiece; step S3: longitudinally machining a central hole; s4, roughly turning the first end part and the second end part; s5, quenching and tempering; s6, repairing a second end reference; s7, semi-finish turning the first end part and the second end part to obtain a workpiece five; s8, naturally aging; s9, repairing a second end reference; s10, finely turning the first end part and the second end part in sequence; s11, turning an outer circle at the first end, and then grinding the outer circle; s12, milling a key groove, milling a large-end spline and inserting a small-end spline to obtain the thin-wall hollow long shaft of the aeroengine. The thin-wall hollow long shaft processed by the invention can effectively solve the problems of high-precision dimension, out-of-tolerance in form and position, deformation, bending and the like of the long shaft.
Description
Technical Field
The invention relates to the technical field of aeroengines, in particular to a method for machining a thin-wall hollow long shaft of an aeroengine.
Background
Engines are known as the heart of aircraft, and shafts are the core components of the engines, so that the importance of the shafts can be known, and the shafts are roughly classified into the following categories according to structures: thin-wall hollow long shafts, shaft necks and drums; the functions can be divided into the following categories: fan shaft, low pressure compressor shaft, high pressure compressor shaft, low pressure turbine shaft, high pressure turbine shaft.
When the engine shaft is a hollow thin-wall shaft, the inner surface is provided with a mounting step hole, the outer surface is composed of a matching surface, a shaft neck, involute splines, key grooves, sealing comb teeth, threads and the like, the large end of the shaft is connected with a blade disc through the involute splines, and the small end is connected with parts such as rear sleeve teeth, balance discs and the like through the splines to form a rotor which is integrally supported on a bearing to rotate at a high speed through a coupling.
The working conditions of the shaft are as follows: the high rotating speed and variable load are required to vibrate little during working, so that the requirements of the dimensional accuracy and form and position tolerance of each fit of the shaft during design are very high, the dimensional accuracy of the main fit surface reaches IT6, the dimensional accuracy of the secondary surface reaches IT7-IT8, the surface runout of the main working surface is required to be within 0.01, and the coaxiality of the inner circle and the outer circle of the working surface is required to be within 0.02.
The thin-wall shaft is easy to deform and bend, and the dimensional accuracy and the form and position tolerance of the thin-wall hollow long shaft processing method of the aero-engine in the prior art are difficult to meet the design requirements.
Disclosure of Invention
The invention aims to overcome and supplement the defects existing in the prior art, and provides a processing method of a thin-wall hollow long shaft of an aeroengine, wherein the deformation of a thin-wall part is controlled to finally meet the design drawing requirement by removing large allowance through rough machining, releasing internal stress through heat treatment, pouring tin-out alloy through a semi-finishing correction deformation special fixture, and the like.
The technical scheme adopted by the invention is as follows:
a processing method of a thin-wall hollow long shaft of an aeroengine comprises the following steps: the thin-wall hollow long shaft of the aeroengine is processed by the following steps:
s1, clamping a first end part of a workpiece to be processed through a chuck of a spindle box in a machine tool, propping up a second end part of the workpiece to be processed through a tailstock in the machine tool, supporting the workpiece to be processed through a center frame in the machine tool, roughly turning the appearance of the workpiece to be processed through the machine tool, and controlling the diameter of a flat bottom hole in the workpiece to be processed to be less than or equal to 1.2 through ultrasonic detection;
s2, turning a first end reference and a second end reference of a workpiece to be processed through a machine tool to obtain a first workpiece;
step S3: longitudinally processing a center hole of a workpiece through a deep hole drilling machine;
s4, roughly turning the first end and the second end of the workpiece I in the step S3 through a machine tool to obtain a workpiece II;
s5, quenching the second workpiece after being charged into the furnace, and tempering to obtain a third workpiece;
s6, repairing a second end reference of the workpiece three-way through a machine tool to obtain a workpiece four;
s7, sequentially semi-finish turning the first end part and the second end part of the workpiece IV to obtain a workpiece V;
s8, naturally aging the workpiece five, wherein the natural aging time is controlled to be more than 48 hours;
s9, repairing a second end reference of the workpiece five through a machine tool to obtain a workpiece six;
s10, sequentially finish turning a first end part and a second end part of a workpiece six to obtain a workpiece seven;
s11, turning an outer circle of the first end of the workpiece seven, and then grinding the outer circle;
s12, milling a key groove, milling a large-end spline and inserting a small-end spline on the workpiece to obtain the thin-wall hollow long shaft of the aeroengine.
Rough machining: the clamping scheme mainly adopts one end to clamp, one end to tightly prop up by a tip, and the clamping scheme is combined with a center frame and a follower rest to carry out turning processing; the cutting state cannot be observed during deep hole machining, only cutting sound can be heard, the change of the machine tool load is observed, and the cutting state and the cutter abrasion degree are judged according to experience; because the inner cavity is deep and the diameter is small, the inner hole boring cutter must be small in diameter and long, and in order to enhance the rigidity of the boring cutter and solve the problems of cutter bar vibration and the like, a hard alloy cutter bar is selected for the cutter during design.
The quenching and tempering treatment is to reach the design hardness HBS 321-375, and is generally arranged before semi-finishing after rough machining, so that the cutting efficiency of rough machining can be improved, better hardenability can be obtained, and enough margin is provided for eliminating deformation of heat treatment air.
The semi-finishing stage is mainly used for eliminating deformation caused by rough machining and heat treatment of air entraining, so that finishing allowance is more uniform and preparation is made for subsequent finishing.
The main purpose of the finishing stage is to meet the requirements of the design drawing, so that high-precision equipment and a special fixture are required to be selected in the machining process; because the wall thickness of the small end of the thin-wall shaft is only 1.2mm, the thin-wall shaft is extremely flexible and deformed, and the clamping by the conventional method cannot be processed, a special core rod is designed, a spigot is adopted between the large end of the shaft and the core rod for positioning, and a low-melting-point tin alloy is poured in a gap between the small end core rod and the shaft to enhance the rigidity; cutting amount during finish machining: constant linear velocity s=35-40 m/min, feed rate f=0.1-0.2 mm/r, cutting depth a p =0.05-0.1 mm. The clamping scheme adopts the clamping mandrel big end, the center is tightly propped against the small end, the center frame is used for supporting the middle section in an auxiliary mode, and the clamping scheme can finish a plurality of working procedures of turning, grinding, milling grooves, milling splines and the like.
Preferably, the method for processing the thin-wall hollow long shaft of the aeroengine comprises the following steps: the step S4 specifically includes: roughly turning a first end part of a first workpiece, removing redundant allowance, roughly turning an inner hole of the first end, and machining an inner hole and an end face chamfer; rough turning a second end part of the workpiece, removing redundant allowance of the second end part, rough turning an inner hole of the second end part, and machining the inner hole and the end face chamfer.
Preferably, the method for processing the thin-wall hollow long shaft of the aeroengine comprises the following steps: the quenching temperature in the step S5 is heated to 840-860 ℃ for 60-80min, the oil cooling is carried out after quenching, the tempering temperature is 550-570 ℃ and the time is 150-180min.
Preferably, the method for processing the thin-wall hollow long shaft of the aeroengine comprises the following steps: in step S6, the second end portion repairing reference specifically includes: and processing the outer end surface of the second end part, so that the length of the workpiece IV is 0.5-1mm smaller than that of the workpiece III, and sequentially arranging a first straightening part, a second straightening part, a third straightening part and a fourth straightening part from right to left from the outer end surface of the second end part, and processing the peripheries of the first straightening part, the second straightening part, the third straightening part and the fourth straightening part, so that the outer diameter is sequentially increased.
Preferably, the method for processing the thin-wall hollow long shaft of the aeroengine comprises the following steps: in step S7, the semi-finish turning of the first end and the second end is specifically: semi-finish turning the first end part of the first workpiece, removing redundant allowance, and semi-finish turning an inner hole of the first end; semi-finish turning a second end part of a workpiece, removing redundant allowance of the second end part, and semi-finish turning an inner hole of the second end part, wherein the outer diameter of a fifth workpiece is 6-7mm smaller than that of a first end part of a second workpiece, and the aperture of the fifth workpiece is 3.5-4.5 larger than that of the inner hole of the first end part of the second workpiece; the outer diameter of the second end part of the workpiece five is 6-7mm smaller than that of the second end part of the workpiece two, and the aperture of the second end part inner hole of the workpiece five is 3.5-4.5 larger than that of the second end part inner hole of the workpiece two.
Preferably, the method for processing the thin-wall hollow long shaft of the aeroengine comprises the following steps: in step S9, the second end portion repairing reference specifically includes: the outer end face of the second end part is processed, so that the workpiece six is 6-7mm smaller than the length of the workpiece four, the outer peripheries of the straightening part I, the straightening part II, the straightening part III and the straightening part IV are processed from right to left in sequence from the outer end face of the second end part, the workpiece six is 6-7mm smaller than the straightening part I of the workpiece four, the workpiece six is 3.5-4.5mm smaller than the straightening part II of the workpiece four, the workpiece six is 3.5-4.5mm smaller than the straightening part III of the workpiece four, and the workpiece six is 8.5-9.5mm smaller than the straightening part IV of the workpiece four.
Preferably, the method for processing the thin-wall hollow long shaft of the aeroengine comprises the following steps: in step S10, the finish turning of the first end portion and the second end portion specifically includes: finely turning a first end part of a first workpiece, removing redundant allowance, and finely turning an inner hole of the first end; finely turning a second end part of the workpiece, removing excess allowance of the second end part, finely turning an inner hole of the second end part, wherein the outer diameter of the seventh workpiece is 2.8-3mm smaller than that of the first end part of the fifth workpiece, and the bore diameter of the seventh workpiece is 2.8-3.2 larger than that of the inner hole of the first end part of the fifth workpiece; the outer diameter of the second end part of the workpiece seven is 1.9-2.1mm smaller than that of the second end part of the workpiece five, and the aperture of the second end part of the workpiece seven is 1.9-2.1 larger than that of the inner hole of the second end part of the workpiece five.
Preferably, the method for processing the thin-wall hollow long shaft of the aeroengine comprises the following steps: in the step S11, a key groove I and a key groove II are arranged on the peripheral surface close to the first end part, wherein the width of the key groove I is 9.1-9.25, and the depth of the key groove is 3.8-4; the width of the key groove II is 9.1-9.25, and the groove depth is 4.2-4.35.
Preferably, the method for processing the thin-wall hollow long shaft of the aeroengine comprises the following steps: in the step S10, a workpiece six is fixed on the machine tool through a clamp during finish turning, the clamp comprises a connecting disc, a core rod is arranged at one end of the connecting disc, the other end of the connecting disc is connected with a main shaft of the machine tool, and the periphery of the core rod is sleeved with the workpiece six.
Preferably, the method for processing the thin-wall hollow long shaft of the aeroengine comprises the following steps: the core rod comprises a core rod I and a core rod II, wherein a positioning piece I is arranged at one end of the core rod I, a positioning piece II is arranged between the core rod I and the core rod II, one end of the core rod II, which is far away from the core rod I, extends out of the workpiece six, a gap is formed between the core rod and the workpiece six, and tin-free alloy is injected into the gap through a second end of the workpiece six.
The invention has the advantages that:
(1) According to the method for processing the thin-wall hollow long shaft of the aeroengine, disclosed by the invention, the conventional process comprises the steps of modulating treatment and rough machining, and the modulated material has high hardness, is not easy to cut, and has high cutter cost and low processing efficiency; the invention reduces the cost and the processing efficiency of the cutter through rough processing and then modulation processing; semi-finishing work fully releases internal stress through natural aging to reduce deformation; the thin wall deformation and bending are controlled by positioning the core rod and pouring tin alloy to fill the inner cavity; the high-precision dimension meets the requirement by grinding.
(2) According to the processing method of the thin-wall hollow long shaft of the aeroengine, provided by the invention, the large allowance is removed through rough machining, the internal stress is released through heat treatment, the deformation is corrected through semi-finishing, the deformation of the thin-wall part is controlled by pouring the tin-urinary alloy through the special fixture for finishing design, and finally the deformation of the thin-wall part is required to meet the design drawing, so that the problems of high-precision size, out-of-tolerance in form and position, deformation, bending and the like of the long shaft can be effectively solved.
Drawings
FIG. 1 is a schematic view of the structure of a workpiece to be processed according to the present invention.
Fig. 2 is a schematic view of a part of the structure in which a workpiece to be processed is provided on a machine tool.
Fig. 3 is a schematic view of the structure of the first workpiece.
Fig. 4 is a schematic view of a structure of a workpiece with a central hole.
Fig. 5 is a schematic diagram of the structure of the second workpiece.
Fig. 6 is a schematic view of the structure of the fourth workpiece.
Fig. 7 is a schematic view of the structure of the fourth workpiece.
Fig. 8 is a schematic view of the structure of the work sixth.
Fig. 9 is a schematic structural view of a work seventh.
Fig. 10 is a schematic structural view of the jig.
Fig. 11 is a schematic diagram of the structure of the workpiece after seven outer circles are turned.
Fig. 12 is a schematic diagram of the structure of the workpiece after seven outer circles are ground.
Fig. 13 is a schematic view of a seven-key slot configuration of a workpiece.
Fig. 14 is a schematic structural view of a thin-walled hollow long shaft of an aeroengine.
Detailed Description
The invention will be further described with reference to specific examples and figures.
A processing method of a thin-wall hollow long shaft of an aeroengine comprises the following steps: the thin-wall hollow long shaft of the aeroengine to be processed has the length of 567mm, the minimum diameter of 34mm, the shaft diameter ratio of the thin-wall hollow long shaft to 17:1, and the minimum wall thickness of only 1.2mm, and the shaft material has good hardenability after being subjected to tempering by 40CrNiMoA, can obtain uniform and good strength and toughness, and has good cutting performance; the thin-wall hollow long shaft of the aeroengine is processed by the following steps:
step S1, as shown in FIG. 1, providing a workpiece 5 to be processed with phi 90 multiplied by 585mm, as shown in FIG. 2, clamping a first end 51 of the workpiece 5 to be processed by a chuck 2 of a spindle box 1 in a machine tool, propping up a second end 52 of the workpiece 5 to be processed by a tailstock 4 in the machine tool, supporting the workpiece 5 to be processed by a center frame 3 in the machine tool, roughly turning the appearance of the workpiece 5 to phi 85 multiplied by 580mm by the machine tool, arranging the spindle box 1, the center frame 3 and the tailstock 4 in the machine tool on a machine tool slide rail 10, and controlling the diameter of a defect hole in the workpiece 5 to be processed to be less than or equal to 1.2 by ultrasonic detection;
s2, as shown in FIG. 3, turning a second end 52 reference phi 83 multiplied by 577mm and a first end 51 reference phi 83 multiplied by 575mm of the workpiece 5 to be processed through a machine tool, and straightening the workpiece to obtain a first workpiece;
step S3: as shown in fig. 4, a first workpiece is longitudinally processed into a central hole 11 through a deep hole drilling machine, and the central hole is drilled to phi 25;
s4, as shown in FIG. 5, roughly turning the first end 51 to phi 80.4 x phi 49.6 x 574 and the second end 52 to phi 56.2 x phi 28 x 573 of the workpiece I in the step S3 by a machine tool to obtain a workpiece II; roughly turning a first end 51 of a first workpiece, removing excessive allowance, roughly turning an inner hole 53 of the first end, and machining the inner hole 53 and an end face chamfer; roughly turning the second end 52 of the workpiece, removing redundant allowance of the second end, roughly turning an inner hole 54 of the second end, and machining inner holes and end face chamfers;
s5, quenching the second workpiece after being charged into the furnace, and tempering to obtain a third workpiece; the quenching temperature is heated to 850 ℃ for 70min, the quenching oil is cooled, the tempering temperature is 560 ℃ and the quenching time is 160min, and the hardness is required to reach HBS 321-375;
s6, as shown in FIG. 6, repairing a second end 52 of the workpiece III by a machine tool to obtain a workpiece IV; the second end 52 is trimmed to a reference of: machining the outer end face of the second end part 52 so that the length of the fourth workpiece is 0.5-1mm smaller than that of the third workpiece, and sequentially arranging a first straightening part 521, a second straightening part 522, a third straightening part 523 and a fourth straightening part 524 from right to left from the outer end face of the second end part 52, and machining the peripheries of the first straightening part 521, the second straightening part 522, the third straightening part 523 and the fourth straightening part 524 so that the outer diameters are sequentially increased; trimming the end face at the second end 52 to ensure that the total length of the four parts of the workpiece is 572.5mm, trimming 521 the outer circle to phi 55.2, trimming 522 the outer circle to phi 71, trimming 523 the outer circle to phi 79.4 and trimming 524 the outer circle to phi 84;
s7, as shown in FIG. 7, sequentially semi-finish turning a first end 51 and a second end 52 of a workpiece IV to obtain a workpiece V; the semi-finish turning first end 51 and the second end 52 are specifically: semi-finish turning the first end 51 to phi 74.19 x phi 53.6 x 570.5 of the first workpiece, removing excess stock, and semi-finish turning the end bore 53; semi-finish turning the second end 52 to phi 49.63 x phi 32 x 569 of the workpiece, removing excess allowance of the second end 52, semi-finish turning the inner hole 54 of the end, wherein the fifth workpiece is 6-7mm smaller than the outer diameter of the first end 51 of the second workpiece, and the fifth workpiece is 3.5-4.5 larger than the aperture of the inner hole of the first end 51 of the second workpiece; the outer diameter of the workpiece five is 6-7mm smaller than that of the second end 52 of the workpiece two, and the aperture of the workpiece five is 3.5-4.5 larger than that of the inner hole of the second end 52 of the workpiece two;
s8, naturally aging the workpiece five, wherein the natural aging time is controlled to be more than 48 hours;
s9, as shown in FIG. 8, repairing a second end 52 of a workpiece five by a machine tool to obtain a workpiece six; the second end 52 is trimmed to a reference of: machining the outer end face of the second end part 52, namely enabling the length of the workpiece six to be 6-7mm smaller than that of the workpiece four, and sequentially machining the peripheries of a first straightening part 521, a second straightening part 522, a third straightening part 523 and a fourth straightening part 524 from right to left from the outer end face of the second end part 52, repairing the end face of the second end part 52, namely enabling the total length of the workpiece six to be 568.5mm, repairing the outer circle of the first straightening part 521 to phi 48.63, repairing the outer circle of the second straightening part 522 to phi 67, repairing the outer circle of the third straightening part 523 to phi 75.35 and repairing the outer circle of the fourth straightening part 524 to phi 75;
s10, as shown in FIG. 9, sequentially finish turning a first end 51 and a second end 52 of a workpiece six to obtain a workpiece seven; the finish turning first end 51 and the second end 52 are specifically: finish turning the first end 51 to phi 71.27 x phi 55.6 x 567.5 of the first workpiece, removing excess allowance, and finish turning the inner hole of the first end; finish turning the second end 52 to phi 47.63 x phi 34 x 567 of the workpiece, removing excess allowance of the second end 52, finish turning the inner hole of the end, wherein the seventh of the workpiece is 2.8-3mm smaller than the outer diameter of the first end 51 of the fifth of the workpiece, and the seventh of the workpiece is 2.8-3.2 larger than the aperture of the inner hole of the first end 51 of the fifth of the workpiece; the outer diameter of the workpiece seven is 1.9-2.1mm smaller than that of the second end 52 of the workpiece five, and the aperture of the workpiece seven is 1.9-2.1 larger than that of the inner hole of the second end 52 of the workpiece five;
as shown in fig. 10, a workpiece six is fixed on a machine tool through a clamp during finish turning, the clamp comprises a connecting disc 6, a core rod 7 is arranged at one end of the connecting disc 6, the other end of the connecting disc 6 is connected with a main shaft of the machine tool, and the periphery of the core rod is sleeved with the workpiece six; the mandrel 7 comprises a first mandrel 71 and a second mandrel 72, wherein a positioning piece 8 is arranged at one end of the first mandrel 72, a positioning piece 9 is arranged between the first mandrel 71 and the second mandrel 72, one end of the second mandrel 72, which is far away from the first mandrel 71, extends out of the workpiece six, a gap is formed between the mandrel 7 and the workpiece six, a tin-free alloy is injected into the gap through a second end 52 of the workpiece six, and 12 is a tin-free alloy filler; 13 is a nut, the connecting disc 6 is connected with a main shaft of the machine tool, the workpiece six 5 and the core rod 7 are positioned through a first positioning piece 8 and a second positioning piece 9, tin-free alloy is injected into the inner cavity from the second end 52, the nut 13 is locked from the end face of the second end, and the tailstock of the machine tool is tightly propped against the second end;
s11, turning the outer circle of the first end 51 of the workpiece seven as shown in FIG. 11, and ensuring that the wall thickness at the position, close to the outer periphery 14 of the second end, is 1.2+/-0.05; the outer circumference 15 adjacent the first end 51 is then ground to phi 74.01 as in fig. 12;
step S12, milling key grooves, first end splines 57 and second end splines 58 of a workpiece seven, and obtaining a thin-wall hollow long shaft of the aero-engine; the key slot is that a key slot I and a key slot II are arranged on the peripheral surface close to the first end part 51, the width of the key slot I is 9.1-9.25, and the depth of the key slot is 3.8-4; the width of the key groove II is 9.1-9.25, and the groove depth is 4.2-4.35.
According to the method for processing the thin-wall hollow long shaft of the aeroengine, disclosed by the invention, the conventional process comprises the steps of modulating treatment and then rough machining, and the modulated material has high hardness, is not easy to cut, has high cutter cost and has low processing efficiency; the invention reduces the cost and the processing efficiency of the cutter through rough processing and then modulation processing; semi-finishing work fully releases internal stress through natural aging to reduce deformation; the thin wall deformation and bending are controlled by positioning the core rod and pouring tin alloy to fill the inner cavity; the high-precision dimension meets the requirement by grinding.
Finally, it should be noted that the above-mentioned embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to examples, it should be understood by those skilled in the art that modifications and equivalents may be made to the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention, and all such modifications and equivalents are intended to be encompassed in the scope of the claims of the present invention.
Claims (10)
1. A processing method of a thin-wall hollow long shaft of an aeroengine is characterized by comprising the following steps of: the thin-wall hollow long shaft of the aeroengine is processed by the following steps:
s1, clamping a first end (51) of a workpiece (5) to be processed through a chuck (2) of a spindle box (1) in a machine tool, propping up a second end (52) of the workpiece (5) to be processed through a tailstock (4) in the machine tool, supporting the workpiece (5) to be processed through a center frame (3) in the machine tool, roughly turning the appearance of the workpiece (5) to be processed through the machine tool, and controlling the diameter of a defect hole in the workpiece (5) to be processed to be less than or equal to 1.2 through ultrasonic detection;
s2, turning a first end (51) reference and a second end (52) reference of a workpiece (5) to be processed through a machine tool to obtain a first workpiece;
step S3: longitudinally processing a center hole of a workpiece through a deep hole drilling machine;
s4, roughly turning a first end (51) and a second end (52) of the workpiece I in the step S3 through a machine tool to obtain a workpiece II;
s5, quenching the second workpiece after being charged into the furnace, and tempering to obtain a third workpiece;
s6, repairing a second end (52) reference of the workpiece three times through a machine tool to obtain a workpiece four;
s7, sequentially semi-finish turning a first end (51) and a second end (52) of a workpiece IV to obtain a workpiece V;
s8, naturally aging the workpiece five, wherein the natural aging time is controlled to be more than 48 hours;
s9, repairing a second end (52) reference of the workpiece five through a machine tool to obtain a workpiece six;
s10, sequentially finish turning a first end (51) and a second end (52) of a workpiece six to obtain a workpiece seven;
s11, turning an outer circle of a first end (51) of a workpiece seven, and then grinding the outer circle;
s12, milling a key groove, milling a large-end spline and inserting a small-end spline on the workpiece to obtain the thin-wall hollow long shaft of the aeroengine.
2. The method for machining the thin-wall hollow long shaft of the aeroengine, according to claim 1, is characterized in that: the step S4 specifically includes: roughly turning a first end (51) of the first workpiece, removing redundant allowance, roughly turning an inner hole of the first end, and machining an inner hole and an end face chamfer; and roughly turning a second end (52) of the workpiece, removing redundant allowance of the second end, roughly turning an inner hole of the end, and machining the inner hole and the end face chamfer.
3. The method for machining the thin-wall hollow long shaft of the aeroengine, according to claim 1, is characterized in that: the quenching temperature in the step S5 is heated to 840-860 ℃ for 60-80min, the oil cooling is carried out after quenching, the tempering temperature is 550-570 ℃ and the time is 150-180min.
4. The method for machining the thin-wall hollow long shaft of the aeroengine, according to claim 1, is characterized in that: in step S6, the second end (52) trimming reference is specifically: and processing the outer end surface of the second end part (52) so that the length of the workpiece IV is 0.5-1mm smaller than that of the workpiece III, and sequentially arranging a first straightening part (521), a second straightening part (522), a third straightening part (523) and a fourth straightening part (524) from right to left from the outer end surface of the second end part (52), and processing the peripheries of the first straightening part (521), the second straightening part (522), the third straightening part (523) and the fourth straightening part (524) so that the outer diameter is sequentially increased.
5. The method for machining the thin-wall hollow long shaft of the aeroengine, according to claim 1, is characterized in that: in step S7, the semi-finish turning of the first end (51) and the second end (52) is specifically: a first end (51) of the first semi-finish turning workpiece is subjected to semi-finish turning, surplus allowance is removed, and an inner hole of the first end is subjected to semi-finish turning; semi-finish turning a second end part (52) of the workpiece, removing redundant allowance of the second end part (52), and semi-finish turning an inner hole of the end, wherein the outer diameter of a fifth workpiece is 6-7mm smaller than that of a first end part (51) of a second workpiece, and the aperture of the fifth workpiece is 3.5-4.5 larger than that of the inner hole of the first end part (51) of the second workpiece; the outer diameter of the workpiece five is 6-7mm smaller than that of the second end (52) of the workpiece two, and the aperture of the workpiece five is 3.5-4.5 larger than that of the inner hole of the second end (52) of the workpiece two.
6. The method for machining the thin-wall hollow long shaft of the aeroengine, according to claim 4, is characterized in that: in step S9, the second end (52) trimming reference is specifically: the outer end face of the second end part (52) is processed so that the workpiece six is 6-7mm smaller than the length of the workpiece four, and the peripheries of the straightening part I (521), the straightening part II (522), the straightening part III (523) and the straightening part IV (524) are processed from right to left in sequence from the outer end face of the second end part (52), the workpiece six is 6-7mm smaller than the straightening part I (521) of the workpiece four, the workpiece six is 3.5-4.5mm smaller than the straightening part II (522) of the workpiece four, the workpiece six is 3.5-4.5mm smaller than the straightening part III (523) of the workpiece four, and the workpiece six is 8.5-9.5mm smaller than the straightening part IV (524) of the workpiece four.
7. The method for machining the thin-wall hollow long shaft of the aeroengine, according to claim 4, is characterized in that: in step S10, the finish turning of the first end (51) and the second end (52) is specifically: finely turning a first end (51) of the first workpiece, removing excess allowance, finely turning an inner hole of the first end; finish turning a second end part (52) of the workpiece, removing redundant allowance of the second end part (52), finish turning an inner hole of the end, wherein the outer diameter of a seventh workpiece is 2.8-3mm smaller than that of a first end part (51) of a fifth workpiece, and the bore diameter of the seventh workpiece is 2.8-3.2 larger than that of the inner hole of the first end part (51) of the fifth workpiece; the outer diameter of the workpiece seven is 1.9-2.1mm smaller than that of the second end (52) of the workpiece five, and the aperture of the workpiece seven is 1.9-2.1 larger than that of the inner hole of the second end (52) of the workpiece five.
8. The method for machining the thin-wall hollow long shaft of the aeroengine, according to claim 4, is characterized in that: in the step S11, a key groove I (55) and a key groove II (56) are arranged on the peripheral surface close to the first end part (51), the width of the key groove I (51) is 9.1-9.25, and the groove depth is 3.8-4; the width of the key groove II (56) is 9.1-9.25, and the groove depth is 4.2-4.35.
9. The method for machining the thin-wall hollow long shaft of the aeroengine, according to claim 1, is characterized in that: in the step S10, a workpiece six is fixed on the machine tool through a clamp during finish turning, the clamp comprises a connecting disc (6), a core rod (7) is arranged at one end of the connecting disc (6), the other end of the connecting disc (6) is connected with a main shaft of the machine tool, and the periphery of the core rod is sleeved with the workpiece six.
10. The method for machining the thin-wall hollow long shaft of the aeroengine, according to claim 9, is characterized in that: the core rod (7) comprises a first core rod (71) and a second core rod (72), one end of the first core rod (72) is provided with a first positioning piece (8), a second positioning piece (9) is arranged between the first core rod (71) and the second core rod (72), one end, far away from the first core rod (71), of the second core rod (72) extends out of the workpiece six, a gap is reserved between the core rod (7) and the workpiece six, and tin-free alloy is injected into the gap through a second end (52) of the workpiece six.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311287449.6A CN117161695A (en) | 2023-10-08 | 2023-10-08 | Method for machining thin-wall hollow long shaft of aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311287449.6A CN117161695A (en) | 2023-10-08 | 2023-10-08 | Method for machining thin-wall hollow long shaft of aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117161695A true CN117161695A (en) | 2023-12-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311287449.6A Pending CN117161695A (en) | 2023-10-08 | 2023-10-08 | Method for machining thin-wall hollow long shaft of aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117161695A (en) |
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2023
- 2023-10-08 CN CN202311287449.6A patent/CN117161695A/en active Pending
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