Machining method for multi-welding-seam anti-deformation control cavity protection wall of aero-engine coupler

Abstract

According to the machining method for the multi-welding-seam anti-deformation control cavity protection wall of the aero-engine coupler, the aero-engine coupler is formed by splicing a front flange, a rear flange and four half membrane disc pieces into a front membrane disc and a rear membrane disc and welding the front membrane disc and the rear membrane disc through five electron beam welding seams. Wherein the front flange shaft neck and the front membrane disc shaft neck, the front membrane disc shaft neck and the rear membrane disc shaft neck, and the rear flange shaft neck and the rear membrane disc shaft neck are three electron beam welding seams; when the outer disc of the front film disc semi-film disc piece and the outer disc of the rear film disc semi-film disc piece are spliced into two film discs, two electron beams are used for welding, and the outer disc of the front film disc semi-film disc piece and the rear film disc semi-film disc piece can be self-centered during assembly before welding, so that an assembly joint of the semi-film disc piece needs to be designed to be in interference fit with a spigot with a lock bottom; the inner sides of two welding seams spliced by the front membrane disc and the rear membrane disc are positioned in the concave cavity; and the inner side surfaces of the other three welding seams are machined through a combination machine after being welded, so that the precision is ensured, and a locking opening can be formed in an inner hole before the three welding seams are welded and is used for aligning the welding seams to ensure self-centering.

Description

Technical Field

[0001] The present invention relates to a processing method for an aero-engine coupling, and involves the machining process of the coupling, the design of the electron beam welding process structure, the machining of the anti-deformation control cavity wall, and the electron beam welding method. Background Art

[0002] CN201911151702.9 discloses a perforated diaphragm coupling and its design method. The perforated diaphragm coupling includes an intermediate shaft and diaphragm groups arranged at both ends of the intermediate shaft. The diaphragm group includes one or more perforated diaphragms. When the diaphragm group includes multiple perforated diaphragms, the multiple perforated diaphragms are connected in parallel, and the thicknesses of the multiple perforated diaphragms are equal. The perforated diaphragm is provided with a plurality of through holes. The perforated diaphragm coupling and its design method are special diaphragm couplings that can be used on heavy-duty rotating shaft systems.

[0003] CN201810631513.0 discloses an elastic coupling with a composite material diaphragm. The elastic coupling includes an elastic element, a flange, and a diaphragm. The diaphragm is made of a composite material, and at least a part of the diaphragm is located between the elastic element and the flange in the axial direction of the elastic coupling. The diaphragm includes a first extension section, a second extension section, and a deformation section. The first extension section is used to connect with the flange. The second extension section is arranged radially outside relative to the first extension section and is used to connect with the elastic element. The deformation section connects the first extension section and the second extension section, and the deformation section is configured as a corrugated shape and can undergo elastic deformation.

[0004] CN201110258743.5 relates to a high-elasticity diaphragm coupling structure, including a spacer shaft, double diaphragms symmetrically installed at both ends of the spacer shaft, and a mounting disc. The characteristics are: the profile of the double diaphragms is a curved profile. The profiles of the double diaphragms are integrally connected to form a U-shaped structure. Both sides of the double diaphragms are diaphragm sheets. The top of the diaphragm sheet is a diaphragm flange. The bottoms of the diaphragm sheets on both sides are connected into a whole by a diaphragm body. The double diaphragms are connected to the mounting disc through the diaphragm flange on one side and transmit torque through the first bolt assembly. The diaphragm flange on the other side of the double diaphragms is positioned with the spacer shaft by a convex and concave stop, and transmits torque through the second bolt assembly. A first guard plate and a second guard plate are arranged outside the double diaphragms. The present invention adopts a double-diaphragm high-elasticity structure, which can achieve a large compensation amount; it is convenient for installation and disassembly, and is beneficial to maintenance. However, the prior art does not involve the special structure and processing of aero-engine couplings.

[0005] The diaphragm coupling involved in the present invention is a difficult-to-machine component of a high-end aero-engine. Based on the comprehensive production process and the results of finished product inspection, the processing method of the coupling assembly is determined, especially the processing method of the electron beam welding process to ensure that the welding quality and the post-weld dimensions meet the design requirements. Summary of the Invention

[0006] The object of the present invention is to propose a processing technology for a new aero-engine coupling, which can process a coupling that meets the design requirements.

[0007] The test piece of the aero-engine coupling of the present invention has been produced. Based on the comprehensive production process and the results of finished product inspection, the processing method of the coupling assembly is determined, especially the processing method of the electron beam welding process to ensure that the welding quality and the dimensions after welding meet the design requirements.

[0008] The technical solution of the present invention is a processing method for preventing deformation and controlling the cavity wall of multiple welds of an aero-engine coupling. The structure of the aero-engine coupling is composed of a front flange, a rear flange and 4 semi-diaphragm parts that are assembled into two front and rear diaphragms and welded by 5 electron beam welds. Among them, the shaft neck of the front flange and the shaft neck of the front diaphragm, the shaft neck of the front diaphragm and the shaft neck of the rear diaphragm, and the shaft neck of the rear flange and the shaft neck of the rear diaphragm are three electron beam welds, namely welds 1, 3, and 5; when the outer discs of the front diaphragm semi-diaphragm parts and the outer discs of the rear diaphragm semi-diaphragm parts are assembled into two diaphragms, there are two electron beam welds, namely weld 2 and weld 4.

[0009] The outer discs of the front diaphragm semi-diaphragm parts and the rear diaphragm semi-diaphragm parts, a total of 4 parts, need to be self-centering during pre-welding assembly. Therefore, the assembly joint of the semi-diaphragm parts needs to be designed as an interference fit with a bottom-locked rabbet; the inner sides of the splicing welds 2 and 4 of the front diaphragm and the rear diaphragm are in a concave cavity, and the inner cavity of the diaphragm needs to be machined in place before welding; when welding these two welds, namely welds 2 and 4, it is necessary to process the outer edge side of the semi-diaphragm parts for process self-centering locking to align the welds to ensure self-centering; for the other three welds, namely welds 1, 3, and 5, the inner sides can ensure the accuracy through combined machining after welding. Therefore, lock grooves can be set in the inner hole before welding for welds 1, 3, and 5 to align the welds to ensure self-centering.

[0010] First, machine the front flange, rear flange with shaft necks and 4 semi-diaphragm parts with shaft necks. First, weld welds 2 and 4, and then weld the three welds 1, 3, and 5.

[0011] There are runout requirements for the final state of the machined and welded assembly with respect to the reference AB (including the rotational plane accuracy with very high dynamic balance requirements).

[0012] Since there are 5 welds in the coupling assembly, it is difficult to ensure the runout of the inner hole and the end face of the disc with respect to the references A and B. The drum assembly to which the coupling assembly is connected and fixed is a high-speed rotating rotor component. Large radial and end face runouts will cause engine vibration and unstable operation. Therefore, in order to ensure the runout of the inner hole and the end face with respect to the references A and B, the outer discs of the front diaphragm semi-diaphragm parts and the rear diaphragm semi-diaphragm parts, a total of 4 parts, need to be self-centering during pre-welding assembly. Therefore, the assembly joint of the semi-diaphragm parts needs to be designed as an interference fit with a bottom-locked rabbet (considering the shrinkage during electron beam welding).

[0013] As can be seen from the figure, the inner sides of the splicing welds 2 and 4 between the front membrane disc and the rear membrane disc are in the concave cavity, and machining cannot be carried out after welding. Therefore, the inner cavity of the membrane disc needs to be machined in place before welding. When welding these two welds, it is necessary to design and machine the process self-centering lock on the outer edge side of the semi-membrane disc part (for aligning the welds) to ensure self-centering; for the other three welds 1, 3, and 5, the inner sides can ensure the accuracy through combined machining after welding. Therefore, lock mouths can be set in the inner hole before welding for weld 1, 3, and 5 to align the welds to ensure self-centering.

[0014] Figure 2 It is a schematic diagram of the part state before electron beam welding. The red (dark) filled area is the combined machining allowance left before part welding, and combined machining is carried out after electron beam welding to obtain a finished product that meets the design requirements.

[0015] Beneficial effects: The processed membrane disc coupling of the present invention requires extremely high dynamic balance when rotating at a high speed (more than 10,000 revolutions per minute), and works at a very high temperature. The transmission of the membrane disc coupling also needs to withstand a certain amount of toughness. Especially when applied to an aero-engine, it requires low mass and high strength. Therefore, the membrane disc is designed to be extremely thin and has a complex shape, so the process requirements are extremely high. The prior art has not disclosed this preparation technology. The present invention proposes more refined machining and better welding processes to solve this problem. The 4 semi-membrane disc parts can be easily obtained through turning (plus milling); when providing the stop, the processability of electron beam welding is good, including welding penetration and other process conditions, temperature, current, etc. Description of the Drawings

[0016] Figure 1 It is a schematic structural diagram (cross-sectional view) of the workpiece of the present invention;

[0017] Figure 2 It is a schematic structural diagram of the workpiece of the present invention with allowance left before welding;

[0018] Figure 3 It is a schematic diagram of the stop of the 2nd and 4th welds where the 4 semi-membrane disc parts of the workpiece of the present invention are assembled into two front and rear membrane discs;

[0019] Figure 4 It is a schematic diagram of an end face groove cutter. Detailed Embodiments

[0020] Regarding Figure 1 the structure of the workpiece of the present invention, a new processing technology of the present invention is given, which is a processing method capable of machining a coupling that meets the design requirements.

[0021] Front flange 11, rear flange 12, (first to fourth) four semi-membrane discs 13, 14, 15, 16, (first to fifth) five weld seams 1, 2, 3, 4, 5; spacer block 6, tie rod 7, disc spring 8, nut 9; welded fixed base 10.

[0022] Figure 2 It is a schematic diagram of the part state before electron beam welding. The red filled area (dark color) is the combined machining allowance left before part welding, and combined machining is carried out after electron beam welding to achieve a finished product that meets the design requirements.

[0023] Processing flow of the coupling assembly:

[0024] After the semi-membrane disc parts and the front and rear flanges are individually machined, collect the parts → clean → trial assembly of welding fixtures → electron beam welding → vacuum heat treatment → non-destructive inspection of weld seams → semi-finish turning → finish turning → drill and mill bolt holes at both ends → bench repair → fluorescence inspection → dynamic balance → marking → final inspection.

[0025] The key processes in the processing flow are set as: process, tooling, electron beam welding, finish turning;

[0026] The facilities for the electron beam welding process need to consider welding deformation, and the finish turning process needs to consider chatter during machining of the thin-walled component walls, deep concave cavities on the outer side, and deep concave cavities in the inner hole.

[0027] For the assembly of each part before electron beam welding, the concentricity requirements of each part after assembly need to be ensured. Therefore, the machining locking and mating structures of each part before welding are as Figure 3 shown;

[0028] Key points during welding of weld seams 2 and 4:

[0029] 1. Use a welding fixture with a central tie rod (shaft) structure for the semi-membrane disc parts and the front and rear flanges. Install the front flange with a shaft neck, rear flange, and 4 semi-membrane disc parts with shaft necks according to the structure. The front flange, rear flange, and 4 semi-membrane disc parts are assembled into two front and rear membrane discs, and are fixed on the central tie rod shaft using a disc spring. During the welding shrinkage process, it can shrink axially and is in a stressed state throughout the process, avoiding loosening of the pressure plate due to shrinkage;

[0030] 2. Since weld seams 2 and 4 need to penetrate the inner cavity surface from the outside, the inner cavity surface of the membrane disc needs to be protected to prevent splashing onto the inner cavity surface;

[0031] 3. Set a protective ring of the same material at the central tie rod to prevent gas generated by the electron beam hitting the tie rod of different materials from contaminating the material at the weld of the membrane disc; For the welding of these 3 weld seams 1, 3, and 5, the clamping can be carried out as shown in the figure:

[0032] Key points during welding of weld seams 1, 3, and 5:

[0033] 1. The membrane disc welding tooling needs to use a disc spring. During the welding shrinkage process, when it shrinks axially, it is in a stressed state throughout the process, avoiding the loosening of the pressure plate due to shrinkage.

[0034] 2. Since the welds 1, 3, and 5 need to be struck from the outside to the inside and the thickness of the bottom locking (locking) is thickened on the inside, the welding parameters can be better tested through the welding parameter test plate, ensuring that the weld can be penetrated during welding without penetrating the bottom lock.

[0035] 3. The rough machining of a circle of bolt holes on the rear flange of the part is screwed together with the upper cover plate as a whole. The height difference of the pressing surface of the upper cover plate matches the part, ensuring that during the welding process, when the welds 1, 3, and 5 shrink, the outer and inner sides of the flange deform axially at the same time, preventing the inner side from drooping relative to the outer side after welding; the bolt holes of the front flange are not rough machined. In this way, only the rear flange of the whole set of parts is machined with bolt holes, and the angular orientation problem does not need to be considered during welding assembly. Therefore, the front flange is pressed on the chassis through the pressure plate, which can also prevent the inner side from protruding relative to the outer side after welding.

[0036] 4. Since there is a clearance in the inner side of the membrane disc welding assembly, it is easy to deform when the upper pressure plate is pressed. Therefore, a clearance pad is designed at the position shown in the figure. The thickness is based on the clearance thickness of the welding finished drawing. The annular groove at weld 5 is relatively narrow, so the pad needs to be designed as a circular arc and inserted into the annular groove and then screwed into the clearance. The pad is not removed after welding and is heat-treated together with the part.

[0037] 5. The welding sequence of welds 1, 3, and 5 is in the order of 1, 5, 3.

[0038] 6. The upper cover plate and the chassis are in clearance fit with the mating spigot of the part to avoid difficulty in removing the part after welding; post-welding processing:

[0039] Since the wall of the component is thin after welding and there is a clearance in the inner cavity, at least chatter occurs during tool cutting. During processing, wax is poured on the outside or purple sand mud is wrapped to reduce chatter; the annular groove in the inner cavity is relatively deep from the end face and the hole diameter is small, and a special end face grooving tool shown in the following figure is made for processing.

[0040] Since the wall of the component is thin after welding and there is a clearance in the inner cavity, at least chatter occurs during tool cutting. During processing, wax is poured on the outside or purple sand mud is wrapped to reduce chatter; the annular groove in the inner cavity is relatively deep from the end face and the hole diameter is small, and a special end face grooving tool shown in the following figure is made for processing.

[0041] The front flange journal of the workpiece of the present invention, the front membrane disc journal, the front membrane disc journal and the rear membrane disc journal, and the rear flange journal and the rear membrane disc journal are three electron beam welds, that is, the welds 1, 3, and 5 are provided with similar spigots.

[0042] For the assembly of each part before electron beam welding, the concentricity requirements of each part after assembly must be ensured. Therefore, the machining lock joint matching structure of each part before welding has a stop (the lap step of one side of the diaphragm part is used to position the welding of the diaphragm and is cut off after completion): During electron beam welding, there will be a shrinkage amount in the weld seam. For the structural part before welding, machining allowance needs to be increased at this weld seam;

[0043] Electron beam welding process: Inspect parts → Demagnetize → Grind → Clean → Assemble → Verify welding parameters → Electron beam welding → Visual inspection → Repair welding → Post-weld dimensional inspection → Clean parts → Grind → Clean → Assemble → Verify welding parameters → Electron beam welding → Visual inspection → Fluorescent inspection → Repair welding → Post-weld dimensional inspection → Clean parts → Load into furnace → Vacuum heat treatment → Inspect → Post-heat treatment dimensional inspection

[0044] Welds 2 and 4 are first welded into two components respectively, and then combined with the front and rear flanges to weld the welds at 1, 3, and 5 to form the final component.

[0045] Welding of welds 2 and 4 (first welding): Figure 2 As shown, the key points during the welding of welds 2 and 4:

[0046] 1. Anti-deformation:

[0047] The electron beam goes from the outside to the inside. The outer weld is wider than the inner weld, and the outer shrinkage amount is larger than the inner one. Moreover, the inner hole of the two diaphragms has an open structure, which is likely to cause the deformation of the disk center in the direction shown in the figure ( Figure 1 ), that is, the disk center bulges to both sides.

[0048] The inner cavity is a closed cavity. The tooling is provided with exhaust grooves to avoid weld defects caused by the thermal expansion of the gas in the cavity.

[0049] When the welding tooling is clamped, according to the dimensions of the height differences H1 and H2 between the inner and outer sides of the diaphragm, the corresponding height differences are designed for the tooling chassis and the pressing plate, so that during the welding process, when welds 2 and 4 shrink, the deformation of the disk center along the axial direction to the outside is restricted.

[0050] Axial shrinkage will occur after welding. According to the material thickness, the shrinkage amount is about 0.25 mm. Therefore, a disc spring is used under the compression nut. The disc spring can keep the pressing plate in a stressed state throughout the welding process, avoiding the loosening of the pressing plate caused by shrinkage and resulting in part deformation.

[0051] 2. Control cavity wall protection:

[0052] Figure 2, since the weld thickness at welds 2 and 4 is 7.8 mm, it is necessary to penetrate welds 2 and 4 from the outside to the inside. As the wall thickness of the web part of the membrane disc is the thinnest at 0.8 mm, it cannot be machined after welding with internal flow. If allowances are left only on the outside and machining is done after welding deformation, the wall thickness of the web cannot be guaranteed. Therefore, allowances cannot be left on both the inside and outside of the web for combined machining, and the inner cavity surface should be machined in place before welding. Thus, the inner cavity surface of the membrane disc needs to be protected to prevent it from being splashed by the electron beam penetration. The inner cavity surface of the membrane disc is protected by pasting high-temperature resistant adhesive tape before welding and pulled out from the inner cavity opening after welding; the difficulty of this method lies in that the opening is narrow and it is difficult to take out. In the later stage, hexagonal boron nitride paste liquid can be selected to brush the inner cavity surface and washed off with clean water after welding.

[0053] Since welds 2 and 4 are penetrated from the outside to the inside, a protective ring of the same material is set at the central tie rod to make the electron beam hit the protective ring of the same material, preventing gas generated by the electron beam hitting different material tie rods from contaminating the material at the weld of the membrane disc.

[0054] Welding parameters for welds 2 and 4:

[0055]

[0056] Welding of welds 1, 3, and 5 (the second welding):

[0057] Figure 3 As shown, the key points during welding of welds 1, 3, and 5:

[0058] 1. Anti-deformation:

[0059] During welding of welds 1, 3, and 5 (when the tie rod shaft rotates), the outside weld is wider than the inside weld, and the shrinkage amount on the outside is larger than that on the inside. For the upper and lower flanges, it belongs to single-sided welding, and the deformation direction of the flange surface is as shown in the figure ( Figure 3 ) as shown; while for the membrane disc, it belongs to double-sided welding, so the deformation of the membrane disc will be theoretically offset by the shrinkage of the welds on both sides. Therefore, for the second welding, the deformation of the two end flanges is mainly solved.

[0060] From the pre-welding state diagram of the upper and lower flanges, it can be seen that the entire surface of the flange has machining allowances for combined machining after welding. The allowances are taken larger than the welding deformation amount. Theoretically, deformation control is not required, but considering the subsequent machining reference, the deformation of the flange still needs to be controlled during the actual machining process. Figure 3 The structural tooling is also given. The upper flange is machined with a tooling according to the height difference between the inner and outer sides. When the inner side of the flange is pressed tightly, the outer side of the flange is tightened with the tooling through bolts to form a whole, avoiding the upper flange from turning down; the lower flange is pressed tightly against the chassis through a pressing plate to avoid the lower flange from turning up.

[0061] In addition, the inner side of the middle membrane disc is an open structure. During welding, the gland is tightened, which easily causes axial shrinkage and deformation of the parts. Therefore, the design of the welding fixture also needs to solve the problem of open structure deformation. A gasket with a thickness of 4 mm is inserted at the open part of the membrane disc, fixed by energy storage spot welding, and then taken out after welding.

[0062] Axial shrinkage will occur during welding. According to the material thickness, the shrinkage of welds 1, 3, and 5 is about 0.75 mm (0.25 mm for each weld). Therefore, a disc spring is used under the compression nut. The disc spring can keep the pressure plate under force during the whole welding process, avoiding the loosening of the pressure plate caused by shrinkage and resulting in part deformation.

[0063] Welding parameters for electron welding of welds 1, 3, and 5:

[0064]

[0065] Differences from similar structural parts:

[0066] 1. At present, the thickness of the welds of similar parts is relatively thin. The wall thickness at welds 2 and 4 of the membrane disc is 2.7 mm. In the structure of the present invention, a thin stop is designed on the outer circle. Concentricity can be determined during assembly before welding, while similar parts ensure concentricity through butt spot welding correction, with low efficiency.

[0067] 2. As much machining allowance as possible is left for the parts before welding in the present invention. For the web of the membrane disc, since the inner cavity cannot be machined, it is machined in place before welding, and the rest are all left with machining allowance. Compared with the machining scheme of similar structural parts, only the combined machining allowance of the outer circle and the end face of the two end flanges is left, which can effectively reduce the deformation of the parts caused by welding. During subsequent dynamic balancing, the amount of balance removal is relatively large. The influence of deformation on balance in the present invention only exists in the machined web surface of the membrane disc, while for the scheme of only leaving the stop allowance, the cumulative deformation of the machined surface of the welded parts has a greater impact on balance.

[0068] 3. All surfaces are machined in place before welding, and some assembly precision dimensions will affect the assembly quality due to welding deformation.

[0069] Machining after welding: Since the wall thickness of the component is thin and there is an open structure in the inner cavity, at least chatter occurs during tool cutting. During machining, wax is poured on the outside or purple sand mud is wrapped to reduce chatter; the inner cavity ring groove is relatively deep from the end face and the hole diameter is small, and a self-made Figure 4 end face grooving tool is used for machining.

[0070] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention without departing from the principles and purposes of the present invention.

Claims

1. A method for processing a multi-weld anti-deformation control cavity wall of an aircraft engine coupling, characterized in that: The front and rear diaphragms are assembled from the front flange, the rear flange and four semi-diaphragm discs, and are welded by five electron beam welding seams, of which the front flange journal and the front diaphragm journal, the front diaphragm journal and the rear diaphragm journal, and the rear flange journal and the rear diaphragm journal are three electron beam welding seams; and there are two electron beam welding seams when the outer disk of the front diaphragm semi-diaphragm disc and the outer disk of the rear diaphragm semi-diaphragm disc are assembled into two diaphragm discs. The outer disk of the front diaphragm semi-diaphragm disc and the rear diaphragm disc semi-diaphragm disc, a total of four parts, need to be self-centered during assembly before welding, so the semi-diaphragm disc assembly joint needs to be designed as a stop interference fit with a locking bottom. The inner sides of the two welds where the front diaphragm disc and the rear diaphragm disc are spliced ​​are in the concave cavity, and the inner cavity of the diaphragm disc needs to be processed in place before welding; when welding these two welds, the outer edge side of the semi-diaphragm disc needs to be processed with a self-centering lock to align the welds to ensure self-centering; the inner sides of the other three welds are processed by a combination machine after welding to ensure accuracy, so the three welds can be provided with a lock at the inner hole before welding to align the welds to ensure self-centering; first machine the front flange with a shaft neck, the rear flange and the four semi-diaphragm disc parts with a shaft neck, perform two welds, and then perform three welds.

2. The method for processing the multi-weld anti-deformation control cavity wall of an aircraft engine coupling according to claim 1 is characterized in that: When welding the two welds, the semi-diaphragm discs and the front and rear flanges are welded with a welding tool with a center tie rod shaft structure. The front flange with a journal, the rear flange and four semi-diaphragm discs with a journal are installed according to the structure. The four semi-diaphragm discs are assembled into two front and rear diaphragm discs, which are fixed on the center tie rod shaft with a butterfly spring. During the welding shrinkage process, they can shrink along the axial direction. They are under stress throughout the process to avoid loosening of the pressure plate due to shrinkage.

3. The method for processing the multi-weld anti-deformation control cavity wall of an aircraft engine coupling according to claim 2 is characterized in that The two welds need to penetrate the inner cavity surface from the outside to the inside, so the inner cavity surface of the diaphragm disc needs to be protected to prevent spattering to the inner cavity surface; the inner cavity surface of the diaphragm disc needs to be protected to prevent the electron beam from penetrating and spattering to the inner cavity surface. The inner cavity surface of the diaphragm disc is protected with high-temperature resistant adhesive tape before welding, and then pulled out from the inner cavity opening after welding; or the inner cavity surface can be brushed with hexagonal boron nitride paste liquid, and then rinsed off with clean water after welding; a protective ring of the same material is set at the center pull rod to prevent the gas generated by the electron beam hitting the pull rod of different materials from contaminating the material at the weld of the diaphragm disc.

4. The method for processing the multi-weld anti-deformation control cavity wall of an aircraft engine coupling according to claim 1 is characterized in that: The three welds need to be struck from the outside to the inside, and the thickness of the bottom lock on the inside of the weld should be thickened.

5. The method for processing the multi-weld anti-deformation control cavity wall of an aircraft engine coupling according to claim 1, characterized in that: The rear flange is roughly machined with a circle of bolt holes and screwed into a whole with the upper cover plate. The height difference of the pressing surface of the upper cover plate matches the parts to ensure that during the welding process, when the three welds shrink, the outer and inner sides of the flange are deformed axially at the same time to prevent the inner side from falling relative to the outer side after welding; the front flange is pressed on the chassis by a pressing plate to prevent the inner side from convex relative to the outer side after welding.

6. The method for processing the multi-weld anti-deformation control cavity wall of an aircraft engine coupling according to claim 1 or 2, characterized in that There is an opening on the inner side of the diaphragm disc welding assembly. The gasket is designed to be an arc shape, which is inserted into the ring groove and then screwed into the opening. After welding, the gasket is not removed and is heat treated together with the parts.

7. The method for processing the multi-weld anti-deformation control cavity wall of an aircraft engine coupling according to claim 1, characterized in that: The welding order of the three welds is the first, fifth, and third weld.

8. The method for processing the multi-weld anti-deformation control cavity wall of an aircraft engine coupling according to claim 1, characterized in that: Because the wall of the component is thin after welding and there is an opening in the inner cavity, which may cause the tool to vibrate during cutting, wax is poured on the outside or purple clay is wrapped around it during processing to reduce vibration.

9. The method for processing the multi-weld anti-deformation control cavity wall of an aircraft engine coupling according to claim 1, characterized in that: During welding, the material will shrink axially. According to the material thickness, the shrinkage of the three welds is 0.75mm, and each weld is 0.25mm. Therefore, a butterfly spring is used under the clamping nut. The butterfly spring keeps the pressure plate under stress during the entire welding process to avoid loosening of the pressure plate due to shrinkage, which may cause deformation of the parts.

10. The method for processing the multi-weld anti-deformation control cavity wall of an aircraft engine coupling according to claim 1, characterized in that: The welding order of welds 1, 3, and 5 is 1, 5, and 3; that is, the middle weld is welded last.

Images