WO2023020169A1

WO2023020169A1 - Inertia friction welding device and method for aeroengine compressor disk assembly

Info

Publication number: WO2023020169A1
Application number: PCT/CN2022/105581
Authority: WO
Inventors: 张春波; 梁武; 周军; 赵玉珊; 乌彦全; 李睿; 秦丰; 李运雷; 林跃; 王祁; 杨海峰; 翟利民; 张文瀚; 闫翰林
Original assignee: 哈尔滨焊接研究院有限公司
Priority date: 2021-08-16
Filing date: 2022-07-14
Publication date: 2023-02-23
Also published as: CN113510361A; NL2032715A; NL2032715B1

Abstract

An inertia friction welding device (100) and method for an aeroengine compressor disk assembly. The device (100) comprises a spindle workpiece mounting system, a tailstock workpiece mounting system, and a control system. The spindle workpiece mounting system comprises a driving motor (3), a spindle assembly (5), an inertia disk (6), and a spindle clamp (7). The spindle assembly (5) comprises a housing and a spindle rotatably mounted on the housing. The spindle is transmittingly connected to the driving motor (3). The inertia disk (6) is fixed to the spindle. The spindle clamp (7) is fixed to the spindle. The spindle clamp (7) is configured to clamp a spindle workpiece (8). The tailstock workpiece mounting system comprises an upsetting oil cylinder, a tailstock (11), and a tailstock clamp (10). The upsetting oil cylinder is configured to push the tailstock (11) to be close to or distant from the spindle clamp (7). The tailstock clamp (10) is fixed to the tailstock (11) and is configured to clamp a tailstock workpiece (9). The control system is electrically connected to the driving motor (3) and the upsetting oil cylinder, respectively.

Description

Aeroengine compressor disk component inertia friction welding device and method

technical field

The invention relates to the technical field of manufacturing aero-engine components, in particular to an inertial friction welding device and method for an aero-engine compressor disc assembly.

Background technique

As an important component of an aero-engine, the compressor is a mechanical device that transmits mechanical energy to the gas and completes the compression process of the gas medium in the thermal cycle of the engine to increase the gas pressure. The compressor is mainly composed of a low-pressure compressor and a high-pressure compressor. As an important part of the compressor, the compressor discs are titanium alloys, superalloys and powdered superalloys from the first level to the tenth level. The traditional connections between the disks at all levels are mechanical bolt connection and electron beam welding. However, the mechanical connection causes the compressor disk to be thicker and of higher quality, which increases the overall weight of the engine, which is not conducive to the improvement of the thrust-to-weight ratio of the aeroengine and performance improvement; while the electron beam welding method has higher heat input, larger welding deformation, higher residual stress after welding, and difficult welding of dissimilar materials. Improved overall engine performance.

Therefore, how to improve the welding quality between adjacent stages of the aeroengine compressor and reduce the overall weight of the engine is a technical problem to be solved urgently by those skilled in the art.

Contents of the invention

The object of the present invention is to provide an inertial friction welding device and method for an aero-engine compressor disc assembly, which is used to improve the welding quality between adjacent discs of an aero-engine compressor with a large bypass ratio, and reduce the overall weight of the aero-engine.

To achieve the above object, the present invention provides the following scheme:

The invention discloses an inertial friction welding device for an aero-engine compressor disc assembly, comprising:

A spindle workpiece installation system for driving the spindle workpiece to rotate, the spindle workpiece installation system includes a drive motor, a spindle assembly, an inertial disk and a spindle fixture, the spindle assembly includes a housing and a spindle rotatably mounted on the housing, The main shaft is connected to the driving motor through transmission, the inertia disk is fixed on the main shaft, the main shaft clamp is fixed on the main shaft, and the main shaft clamp is used to clamp the main shaft workpiece;

A tailstock workpiece installation system for driving the tailstock workpiece to approach or move away from the spindle workpiece along a straight line, the tailstock workpiece installation system includes an upsetting oil cylinder, a tailstock and a tailstock fixture, and the upsetting oil cylinder is used to push the The tailstock is close to or away from the spindle clamp, the tailstock clamp is fixed on the tailstock, and the tailstock clamp is used to clamp the tailstock workpiece;

A control system, the control system is electrically connected to the drive motor and the upsetting oil cylinder respectively;

Wherein, the spindle workpiece includes a first-stage disk, the tailstock workpiece includes a second-stage disk, and the tailstock workpiece mounting system can make the second-stage disk contact the first-stage disk, and the second-stage disk can contact the first-stage disk. The contact surface between the secondary disk and the first stage disk is the welding end surface of two adjacent stage disks in the aeroengine compressor disk assembly.

Preferably, an air cooler is also included, and the air cooler is arranged adjacent to the driving motor for cooling the driving motor.

Preferably, it also includes a bed and a base, the drive motor is fixed on the bed, the upsetting oil cylinder includes a cylinder body and a piston rod, and the protruding end of the piston rod is fixed on the base, the The base is fixed on the bed.

Preferably, the tailstock is slidably mounted on the bed.

The present invention also discloses an inertial friction welding method for an aero-engine compressor disc assembly, using the above-mentioned inertial friction welding device for an aero-engine compressor disc assembly, comprising the following steps:

S1. Wipe the workpiece to be welded with acetone, remove oil, oxides, iron filings and burrs on the spindle workpiece and tailstock workpiece, clamp the spindle workpiece to be welded in the spindle fixture, and clamp the tailstock workpiece to be welded on the tailstock in the fixture;

S2. The upsetting oil cylinder drives the tailstock workpiece to move, so that the welding end surface of the tailstock workpiece is in contact with the welding end surface of the spindle workpiece, and then the tailstock workpiece is separated from the spindle workpiece by a certain distance, and the tailstock workpiece is centered and adjusted relative to the spindle workpiece ;

S3. Determine the corresponding spindle speed, moment of inertia of the spindle workpiece, and friction pressure through the physical, chemical and mechanical properties of the materials to be welded, and input them into the control system;

S4. The upsetting oil cylinder drives the tailstock workpiece to move, so that the welding end surface of the tailstock workpiece and the welding end surface of the spindle workpiece are in contact, and then the tailstock workpiece is separated from the spindle workpiece for a certain distance and then stops moving;

S5. The drive motor drives the spindle workpiece to rotate, and the speed rises from 0 to the spindle speed and remains stable;

S6. The drive motor no longer outputs power, and the upsetting oil cylinder drives the tailstock workpiece to move, so that the welding end surface of the tailstock workpiece and the welding end surface of the spindle workpiece are in contact, and frictional pressure is applied;

S7, the main shaft workpiece stops rotating, keep the friction pressure for a period of time, then loosen the main shaft clamp and the tailstock clamp, and take off the welded workpiece welded by the main shaft workpiece and the tailstock workpiece.

The present invention also discloses another method for inertial friction welding of an aero-engine compressor disc assembly, using the above-mentioned inertial friction welding device for an aero-engine compressor disc assembly, comprising the following steps:

S3. Determine the corresponding spindle speed, moment of inertia of the spindle workpiece, friction pressure, conversion speed and upsetting pressure through the physical, chemical and mechanical properties of the materials to be welded, and input them into the control system. The upsetting pressure is greater than the friction pressure;

S7. After the rotation speed of the main shaft workpiece is reduced to the conversion speed, the upsetting oil cylinder applies upsetting pressure, maintains the upsetting pressure for a period of time, and then releases the main shaft clamp and tailstock clamp, and removes the welded joint between the main shaft workpiece and the tailstock workpiece. welding workpiece.

Compared with the prior art, the present invention has achieved the following technical effects:

The invention adopts the inertial friction welding method to weld and manufacture the engine compressor discs. After welding, the radial deviation of the disc centers of each level is small, the axial shortening deviation is small, the welded joints are high in quality, small in deformation, and welded without slag inclusions, pores, cracks, etc. defect. It is not only suitable for the welding of titanium alloy and superalloy compressor disks, but also for the high-quality connection between compressor disks of dissimilar materials. It can effectively reduce the weight of the engine and increase the thrust-to-weight ratio of the engine.

Description of drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the accompanying drawings required in the embodiments. Obviously, the accompanying drawings in the following description are only some of the present invention. Embodiments, for those of ordinary skill in the art, other drawings can also be obtained based on these drawings without any creative effort.

Fig. 1 is the schematic diagram of the inertial friction welding device of the aeroengine compressor disc assembly of the present embodiment;

Fig. 2 is the welding schematic diagram of the nine-stage disk as the spindle workpiece and the ten-stage disk as the tailstock workpiece;

Fig. 3 is the welded workpiece schematic diagram that Fig. 2 obtains;

Fig. 4 is a schematic diagram of welding of the eight-stage disk as the spindle workpiece and the nine-stage disk and the ten-stage disk assembly as the tailstock workpiece;

Fig. 5 is the schematic diagram of the welded workpiece obtained in Fig. 4;

Fig. 6 is a schematic diagram of the welding of the seven-stage disc as the spindle workpiece and the eight-stage disc, nine-stage disc, and ten-stage disc assembly as the tailstock workpiece;

Fig. 7 is the schematic diagram of the welded workpiece obtained in Fig. 6;

Fig. 8 is a schematic diagram of the welding of the six-stage disc as the spindle workpiece and the seven-stage disc, eight-stage disc, ninth-stage disc, and ten-stage disc assembly as the tailstock workpiece;

Fig. 9 is the schematic diagram of the welded workpiece obtained in Fig. 8;

Explanation of reference signs: 100-inertial friction welding device for aero-engine compressor disc assembly; 1-bed; 2-air cooler; 3-drive motor; 4-coupling; 5-main shaft assembly; -spindle fixture; 8-spindle workpiece; 9-tailstock workpiece; 10-tailstock fixture; 11-tailstock; 12-oil cylinder body; 13-piston rod; 14-base; disc; 17-eight-level disc; 18-nine-level disc; 19-tenth-level disc; 20-welding seam; 21-positioning pad.

Detailed ways

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

The object of the present invention is to provide an inertial friction welding device and method for an aero-engine compressor disk assembly, which is used to improve the welding quality between adjacent stage disks of an aero-engine compressor with a large bypass ratio.

In order to make the above objects, features and advantages of the present invention more comprehensible, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

As shown in Figures 1-9, the present embodiment provides an inertial friction welding device 100 for an aero-engine compressor disc assembly, including a spindle workpiece mounting system for driving the spindle workpiece 8 to rotate, and a spindle workpiece mounting system for driving the tailstock workpiece 9 to approach along a straight line. Or the tailstock workpiece installation system and control system away from the spindle workpiece 8.

Wherein, the spindle workpiece mounting system includes a drive motor 3 , a spindle assembly 5 , an inertia disk 6 and a spindle fixture 7 . The main shaft assembly 5 includes a housing and a main shaft rotatably mounted on the housing, and the main shaft is in transmission connection with the drive motor 3 . The inertia disk 6 is fixed on the main shaft, and is used to increase the moment of inertia of the main shaft. The spindle clamp 7 is fixed on the spindle, and the spindle clamp 7 is used for clamping the spindle workpiece 8 . The tailstock workpiece mounting system includes an upsetting oil cylinder, a tailstock 11 and a tailstock clamp 10. The upsetting oil cylinder is used to push the tailstock 11 close to or away from the main shaft fixture 7, the tailstock fixture 10 is fixed on the tailstock 11, and the tailstock fixture 10 is used to clamp the tailstock workpiece 9. The control system is electrically connected with the driving motor 3 and the upsetting oil cylinder respectively, and is used to control the output speed of the driving motor 3 and the output pressure of the upsetting oil cylinder. In this embodiment, the main shaft and the output shaft of the drive motor 3 are fixedly connected through the shaft coupling 4. Those skilled in the art can also use other common transmission connection methods, such as the way the main shaft and the output shaft of the drive motor 3 are driven by gears. Drive connection. In addition, in order to facilitate the positioning of the tailstock workpiece 9 , a positioning pad 21 is provided between the tailstock workpiece 9 and the tailstock fixture 10 in this embodiment.

Wherein, the spindle workpiece 8 includes a first-level disk, and the tailstock workpiece 9 includes a second-level disk. The tailstock workpiece mounting system can make the second-level disk contact the first-level disk, and the contact between the second-level disk and the first-level disk The surface is the welding end surface of two adjacent stage disks in the aero-engine compressor disk assembly, and the two welding end surfaces form a weld 20 after the welding is completed. For example, in Fig. 2, the spindle workpiece 8 is a nine-stage disc 18, and the tailstock workpiece 9 is a ten-stage disc 19; among Fig. Components; spindle workpiece 8 is a seven-stage disc 16 among Fig. , the tailstock workpiece 9 is an assembly of seven-level disc 16, eight-level disc 17, nine-level disc 18, and ten-level disc 19.

In order to prevent the drive motor 3 from being damaged due to overheating, this embodiment also includes an air cooler 2 , which is arranged adjacent to the drive motor 3 for cooling the drive motor 3 .

During use, both the drive motor 3 and the upsetting oil cylinder need to be fixed. In this embodiment, the bed 1 and the base 14 are also included, and the driving motor 3 is fixed on the bed 1 . The upsetting oil cylinder includes an oil cylinder body 12 and a piston rod 13 , the protruding end of the piston rod 13 is fixed on the base 14 , and the base 14 is fixed on the bed 1 .

In order to prevent the piston rod 13 from bearing excessive radial force, the tailstock 11 is slidably installed on the bed 1 in this embodiment.

This embodiment also discloses an inertial friction welding method for an aero-engine compressor disc assembly, using the above-mentioned inertial friction welding device 100 for an aero-engine compressor disc assembly, including the following steps:

S1. Wipe the workpiece to be welded with acetone, remove oil, oxides, iron filings and burrs on the spindle workpiece 8 and tailstock workpiece 9, clamp the spindle workpiece 8 to be welded in the spindle fixture 7, and place the tailstock to be welded The workpiece 9 is clamped in a tailstock fixture 10 .

S2. The upsetting oil cylinder drives the tailstock workpiece 9 to move, so that the welding end surface of the tailstock workpiece 9 and the welding end surface of the spindle workpiece 8 are in contact, and then the tailstock workpiece 9 is separated from the spindle workpiece 8 for a certain distance, and the tailstock workpiece 9 is aligned. Medium adjustment, so that the beating of the center of the tailstock workpiece 9 relative to the spindle workpiece 8 is less than 0.05mm.

S3. According to the physical, chemical and mechanical properties of the materials to be welded, determine the corresponding spindle speed, moment of inertia of the spindle workpiece, and friction pressure, and input them into the control system.

S4, upsetting oil cylinder drives tailstock workpiece 9 to move, makes the welding end face of tailstock workpiece 9 and the welding end face of main shaft workpiece 8 contact, then makes tailstock workpiece 9 leave main shaft workpiece 8 and stop after at least 2mm.

S5. The drive motor 3 drives the spindle workpiece 8 to rotate, and the speed rises from 0 to the spindle speed and remains stable.

S6. The drive motor 3 no longer outputs power, and the upsetting oil cylinder drives the tailstock workpiece 9 to move, so that the welding end surface of the tailstock workpiece 9 and the welding end surface of the spindle workpiece 8 are in contact, and frictional pressure is applied. Under the action of frictional pressure, the rotational speed of the spindle workpiece 8 decreases, and the welding end surface of the spindle workpiece 8 and the welding end surface of the tailstock workpiece 9 rub against each other to generate heat, so that the material near the welding end surface is heated to a viscoplastic state, and the high-speed rotating inertial disk 6 The energy stored in the cylinder is gradually converted into heat energy of the welding end surface, so that a layer of high-temperature viscoplastic metal is formed between the welding end surface of the spindle workpiece 8 and the welding end surface of the tailstock workpiece 9 .

S7, the spindle workpiece 8 stops rotating, keep the friction pressure for more than 30s, then loosen the spindle clamp 7 and the tailstock clamp 10, take off the welding workpiece welded by the spindle workpiece 8 and the tailstock workpiece 9, clean the welding site, and end all welding process. During the pressure-holding process, the high-temperature metal on the welding end surface forms a high-quality welded joint through element diffusion and recovery and recrystallization under the action of pressure.

This embodiment also discloses another inertial friction welding method for an aero-engine compressor disk assembly, using the above-mentioned inertial friction welding device 100 for an aero-engine compressor disk assembly, including the following steps:

S3. According to the physical, chemical and mechanical properties of the materials to be welded, determine the corresponding spindle speed, moment of inertia of the spindle workpiece, friction pressure, conversion speed and upsetting pressure, and input them into the control system. The upsetting pressure is greater than the friction pressure.

S7. After the rotating speed of the main shaft workpiece 8 drops to the switching speed, the upsetting oil cylinder applies upsetting pressure, and keeps the upsetting pressure for more than 30s, and then loosens the main shaft clamp 7 and the tailstock clamp 10, and removes the main shaft workpiece 8 and the tailstock workpiece. 9 Welded workpieces made by welding. During the pressure-holding process, the high-temperature metal on the welding end surface forms a high-quality welded joint through element diffusion and recovery and recrystallization under the action of pressure.

It should be noted that the main difference between the above two inertial friction welding methods is that in steps S6 to S7, during the process of decelerating the spindle workpiece 8 from the spindle speed to stop, one continuously applies friction pressure, and the other applies friction pressure first, Finally, the upsetting pressure is applied, and the upsetting pressure is greater than the friction pressure.

In this description, specific examples are used to illustrate the principle and implementation of the present invention. The description of the above embodiments is only used to help understand the method and core idea of the present invention; meanwhile, for those of ordinary skill in the art, according to this The idea of the invention will have changes in the specific implementation and scope of application. In summary, the contents of this specification should not be construed as limiting the present invention.

Claims

An inertial friction welding device for an aero-engine compressor disc assembly, characterized in that it comprises:

A spindle workpiece installation system for driving the spindle workpiece to rotate, the spindle workpiece installation system includes a drive motor, a spindle assembly, an inertial disk and a spindle fixture, the spindle assembly includes a housing and a spindle rotatably mounted on the housing, The main shaft is connected to the driving motor through transmission, the inertia disk is fixed on the main shaft, the main shaft clamp is fixed on the main shaft, and the main shaft clamp is used to clamp the main shaft workpiece;

A tailstock workpiece installation system for driving the tailstock workpiece to approach or move away from the spindle workpiece along a straight line, the tailstock workpiece installation system includes an upsetting oil cylinder, a tailstock and a tailstock fixture, and the upsetting oil cylinder is used to push the The tailstock is close to or away from the spindle clamp, the tailstock clamp is fixed on the tailstock, and the tailstock clamp is used to clamp the tailstock workpiece;

A control system, the control system is electrically connected to the drive motor and the upsetting oil cylinder respectively;

Wherein, the spindle workpiece includes a first-stage disk, the tailstock workpiece includes a second-stage disk, and the tailstock workpiece mounting system can make the second-stage disk contact the first-stage disk, and the second-stage disk can contact the first-stage disk. The contact surface between the secondary disk and the first stage disk is the welding end surface of two adjacent stage disks in the aeroengine compressor disk assembly.
The inertial friction welding device for the aero-engine compressor disc assembly according to claim 1, further comprising an air cooler, the air cooler is arranged adjacent to the driving motor for cooling the driving motor.
The inertial friction welding device for an aero-engine compressor disc assembly according to claim 1, further comprising a bed and a base, the driving motor is fixed on the bed, and the upsetting cylinder includes a cylinder body and a piston rod, the protruding end of the piston rod is fixed on the base, and the base is fixed on the bed.
The inertial friction welding device for an aero-engine compressor disc assembly according to claim 3, wherein the tailstock is slidably mounted on the bed.
An aero-engine compressor disk assembly inertial friction welding method, using the aero-engine compressor disk assembly inertial friction welding device as claimed in any one of claims 1-4, is characterized in that, comprises the steps:

S1. Wipe the workpiece to be welded with acetone, remove oil, oxides, iron filings and burrs on the spindle workpiece and tailstock workpiece, clamp the spindle workpiece to be welded in the spindle fixture, and clamp the tailstock workpiece to be welded on the tailstock in the fixture;

S2. The upsetting oil cylinder drives the tailstock workpiece to move, so that the welding end surface of the tailstock workpiece is in contact with the welding end surface of the spindle workpiece, and then the tailstock workpiece is separated from the spindle workpiece by a certain distance, and the tailstock workpiece is centered and adjusted relative to the spindle workpiece ;

S3. Determine the corresponding spindle speed, moment of inertia of the spindle workpiece, and friction pressure through the physical, chemical and mechanical properties of the materials to be welded, and input them into the control system;

S4. The upsetting oil cylinder drives the tailstock workpiece to move, so that the welding end surface of the tailstock workpiece and the welding end surface of the spindle workpiece are in contact, and then the tailstock workpiece is separated from the spindle workpiece for a certain distance and then stops moving;

S5. The drive motor drives the spindle workpiece to rotate, and the speed rises from 0 to the spindle speed and remains stable;

S6. The driving motor no longer outputs power, and the upsetting oil cylinder drives the tailstock workpiece to move, so that the welding end surface of the tailstock workpiece and the welding end surface of the spindle workpiece are in contact, and frictional pressure is applied;

S7, the main shaft workpiece stops rotating, keep the friction pressure for a period of time, then loosen the main shaft clamp and the tailstock clamp, and take off the welded workpiece welded by the main shaft workpiece and the tailstock workpiece.
An aero-engine compressor disk assembly inertial friction welding method, using the aero-engine compressor disk assembly inertial friction welding device as claimed in any one of claims 1-4, characterized in that it comprises the following steps:

S1. Wipe the workpiece to be welded with acetone, remove oil, oxides, iron filings and burrs on the spindle workpiece and tailstock workpiece, clamp the spindle workpiece to be welded in the spindle fixture, and clamp the tailstock workpiece to be welded on the tailstock in the fixture;

S2. The upsetting oil cylinder drives the tailstock workpiece to move, so that the welding end surface of the tailstock workpiece is in contact with the welding end surface of the spindle workpiece, and then the tailstock workpiece is separated from the spindle workpiece by a certain distance, and the tailstock workpiece is centered and adjusted relative to the spindle workpiece ;

S3. Determine the corresponding spindle speed, moment of inertia of the spindle workpiece, friction pressure, conversion speed and upsetting pressure through the physical, chemical and mechanical properties of the materials to be welded, and input them into the control system. The upsetting pressure is greater than the friction pressure;

S4. The upsetting oil cylinder drives the tailstock workpiece to move, so that the welding end surface of the tailstock workpiece and the welding end surface of the spindle workpiece are in contact, and then the tailstock workpiece is separated from the spindle workpiece for a certain distance and then stops moving;

S5. The drive motor drives the spindle workpiece to rotate, and the speed rises from 0 to the spindle speed and remains stable;

S6. The driving motor no longer outputs power, and the upsetting oil cylinder drives the tailstock workpiece to move, so that the welding end surface of the tailstock workpiece and the welding end surface of the spindle workpiece are in contact, and frictional pressure is applied;

S7. After the rotation speed of the main shaft workpiece is reduced to the conversion speed, the upsetting oil cylinder applies upsetting pressure and maintains the upsetting pressure for a period of time, then loosens the main shaft clamp and the tailstock clamp, and removes the welded joint of the main shaft workpiece and the tailstock workpiece. welding workpiece.