Inertia friction welding device and method for turbine disk shaft of aircraft engine

Abstract

The present invention discloses an inertia friction welding device and method for an aircraft engine turbine disk shaft, wherein the welding device comprises an inertia friction welding machine main structure and a welding fixture, the inertia friction welding machine main structure comprises a spindle housing assembly and a tailstock housing assembly, and the welding fixture comprises a drum shaft fixture, a turbine disk fixture, a turbine rear shaft fixture, and a combined fixture. Compared with the prior art, the welding device and method disclosed in the present invention ensure the stability, dimensional accuracy, and joint performance of the aircraft engine turbine disk shaft welding process, improve the production rate of the aircraft engine turbine disk shaft assembly, and reduce the production cost.

Description

Technical Field

[0001] The invention relates to the technical field of inertia friction welding, and in particular to an inertia friction welding device and method for an aircraft engine turbine disk shaft. Background Art

[0002] Inertia friction welding is a typical welding method in solid phase welding process. The welding process first stores mechanical kinetic energy through the rotating flywheel, drives one of the components to rotate at high speed, generates heat under the action of axial friction pressure, and plastically deforms and flows the friction interface material under the action of upsetting welding pressure, thereby realizing the welding of the two components. In the process of inertia friction welding, since the temperature of the friction interface does not reach the melting point of the material, and the welding speed is fast and the time is short, the interface material is in a high-temperature plastic state. After welding upsetting, part of the high-temperature metal material on the interface is squeezed out of the weld to form welding flash. The flash extrusion process can remove the oil and oxide slag on the end face of the specimen, has a self-cleaning effect, and can avoid the existence of slag defects. At the same time, the weld is in a closed state during the welding process, preventing the entry of air, and completely avoiding the defects such as pores, slag inclusions, cracks and unfused joints that often appear in fusion welding joints. It is especially suitable for the welding of axisymmetric parts of homogeneous / heterogeneous materials with large differences in mechanical properties, and can obtain high-quality welded joints.

[0003] With the continuous upgrading of high-performance aircraft engines, new high-temperature alloy materials are increasingly used in aircraft engine turbine disk shaft components, especially powder metallurgy high-temperature alloys (such as U720Li, Rene'88DT, RR1000, etc.) with fine grains, uniform structure, no macro segregation, high yield strength, good fatigue performance and other outstanding advantages, has become the best material for aircraft engine turbine disk shaft. However, for the welding of dissimilar high-temperature alloy materials represented by powder metallurgy high-temperature alloys, electron beam welding technology has been difficult to obtain high-quality welded joints, mainly because as a high-energy density fusion welding process, the high volume percentage of γ' strengthening phase components are complex during the welding process of high-temperature alloys, which leads to the formation of crystallization cracks, heat-affected zone liquefaction cracks and strain aging cracks during the welding process; in addition, due to the differences in parameters such as structure, melting point, thermal conductivity, thermal expansion coefficient, etc., dissimilar high-temperature alloy materials are prone to cause structural segregation during welding, and produce large thermal stress, cracks and other defects. In particular, micro cracks caused by grain boundary liquefaction during high-temperature alloy fusion welding are difficult to avoid, but difficult to effectively detect through non-destructive testing methods. Therefore, electron beam and other fusion welding processes are no longer suitable for welding homogeneous and heterogeneous powder high-temperature alloy materials. As a solid-phase welding process, inertia friction welding technology will effectively avoid crack problems and quality inspection problems caused by fusion welding.

[0004] At present, the rotating parts of domestic aircraft engine turbine disk shafts are still mostly connected by bolts or electron beam welding processes, which largely limits the application of high-performance homogeneous / heterogeneous new powder high-temperature alloy materials in aircraft engine turbine disk shaft rotating parts, and also limits the improvement of the overall performance of aircraft engines. Summary of the invention

[0005] The purpose of the present invention is to provide an aircraft engine turbine disk shaft inertia friction welding device and method for ensuring high quality and high precision connection requirements of aircraft engine turbine disk shaft rotating parts.

[0006] To achieve the above object, the present invention provides the following solutions:

[0007] The invention discloses an inertia friction welding device for a turbine disk shaft of an aero-engine, comprising:

[0008] The main structure of the inertia friction welding machine includes a spindle housing assembly and a tailstock housing assembly;

[0009] A welding fixture, comprising a drum shaft fixture, a turbine disk fixture, a turbine rear shaft fixture and a combined fixture, wherein the drum shaft fixture is used to install the drum shaft on the spindle housing assembly, the turbine disk fixture is used to install the turbine disk on the tailstock housing assembly, the turbine rear shaft fixture is used to install the turbine rear shaft on the spindle housing assembly, and the combined fixture is used to install the first welded assembly of the drum shaft and the turbine disk on the tailstock housing assembly.

[0010] Preferably, the spindle housing assembly comprises a spindle housing, a spindle on the spindle housing side, a spindle on the spindle housing side and a spindle spring chuck, and the spindle spring chuck is fixed to the spindle on the spindle housing side and the spindle housing by bolts.

[0011] Preferably, the tailstock box assembly includes a tailstock box, an inner cylinder on the tailstock box side, a core shaft on the tailstock box side and a tailstock spring chuck, the tailstock spring chuck is threadedly connected to the inner cylinder on the tailstock box side, and the tailstock box spring chuck is fixed to the tailstock box by bolts.

[0012] Preferably, the drum shaft fixture comprises a first welding fixture and a first spring ring, the first welding fixture is fixed to the spindle housing side core shaft by bolts, and the first spring ring is located between the spindle spring chuck and the drum shaft.

[0013] Preferably, the turbine disc tooling fixture comprises a second welding tool, a third welding tool and a second spring ring. The second welding tool is fixed to the inner cylinder body on the tailstock housing side together with the core shaft on the tailstock housing side by bolts. The third welding tool is fixed to the second welding tool by bolts. The second spring ring is located between the tailstock spring chuck and the turbine disc.

[0014] Preferably, the turbine rear shaft fixture comprises a first welding fixture and a third spring ring, the first welding fixture is fixed to the spindle housing side core shaft by bolts, and the third spring ring is located between the spindle spring chuck and the turbine rear shaft.

[0015] Preferably, the combined fixture comprises a fourth welding fixture and a second spring ring, the fourth welding fixture is sleeved on the core shaft on the tailstock housing side, and the second spring ring is located between the tailstock spring chuck and the turbine disc.

[0016] The present invention also discloses an aero-engine turbine disk shaft inertia friction welding method, using the aero-engine turbine disk shaft inertia friction welding device, comprising the following steps:

[0017] S1. Install the drum shaft fixture on the spindle housing assembly, and install the turbine disc fixture on the tailstock housing assembly;

[0018] S2, placing the drum shaft on the spindle housing assembly on which the drum shaft fixture has been installed, the drum shaft is located inside the first spring ring, and the end face of the drum shaft is in contact with the end face of the first welding fixture, and the spindle spring chuck clamps the first spring ring and the drum shaft through radial pressure;

[0019] S3, placing the turbine disc on the tailstock housing assembly on which the turbine disc fixture has been installed, the turbine disc is located inside the second spring ring, the end surface of the turbine disc contacts the end surface of the third welding fixture, and the tailstock spring chuck clamps the second spring ring and the turbine disc by radial pressure;

[0020] S4. Use a dust-free cloth dipped in alcohol or acetone solution to wipe the welding end surface of the drum shaft and the welding end surface of the turbine disk respectively to remove oil and impurities on the welding end surfaces of the drum shaft and the turbine disk;

[0021] S5. The tailstock housing assembly moves toward the spindle housing assembly under the action of the axial force, so that the end face of the drum shaft is in close contact with the end face of the turbine disc and remains stationary. The radial pressure of the spindle spring chuck and the tailstock spring chuck is removed, and then the radial pressure is applied again. Under the action of the axial force, the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly and then remains stationary.

[0022] S6. Inputting welding process parameters of the drum shaft and the turbine disk into the control system of the inertia friction welding machine, including initial rotation speed, welding rotation speed, friction pressure, and welding pressure;

[0023] S7, start the first welding, start the spindle motor of the inertia friction welding machine, stop supplying power to the spindle motor of the inertia friction welding machine after the rotation speed of the drum shaft reaches the initial rotation speed, and the tailstock housing assembly moves a distance toward the spindle housing assembly under the action of the axial friction pressure, so that the end face of the drum shaft and the end face of the turbine disc are in close contact and friction generates heat, and the axial friction pressure remains unchanged; when the rotation speed of the drum shaft is reduced to the welding speed, the axial friction pressure is converted into welding pressure and remains unchanged until the drum shaft stops rotating, and the axial welding pressure is maintained for a period of time and then removed;

[0024] S8, the radial pressure of the spindle spring chuck is removed, the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly under the axial force and then becomes fixed, the radial pressure of the tailstock spring chuck is removed, and the first welding assembly of the drum shaft and the turbine disc is removed;

[0025] S9, disassembling the drum shaft fixture and turbine disc fixture;

[0026] S10. Install the turbine rear shaft fixture on the spindle housing assembly, and install the combined fixture on the tailstock housing assembly;

[0027] S11, placing the turbine rear shaft inside the third spring ring, the end surface of the turbine rear shaft contacts the end surface of the first welding tool, and the spindle spring chuck clamps the third spring ring and the turbine rear shaft by radial pressure;

[0028] S12, placing the first welded assembly on the tailstock housing assembly, placing the first welded assembly inside the second spring ring, the end face of the drum shaft on the first welded assembly contacts the end face of the core shaft on the tailstock housing side, the end face of the turbine disk on the first welded assembly contacts the end face of the fourth welding fixture, and the tailstock spring chuck clamps the second spring ring and the turbine disk on the first welded assembly by radial pressure;

[0029] S13. Use a dust-free cloth dipped in alcohol or acetone solution to wipe the end surface of the turbine rear shaft and the end surface of the turbine disk on the first welded assembly respectively to remove oil and impurities on the end surface of the turbine rear shaft and the end surface of the turbine disk on the welded assembly;

[0030] S14, the tailstock housing assembly moves a distance toward the spindle housing assembly under the action of the axial force, so that the end face of the turbine rear shaft is in close contact with the end face of the turbine disk on the first welding assembly and remains stationary, the radial pressure of the spindle spring chuck and the tailstock spring chuck is removed, and then the radial pressure is applied again, and the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly under the action of the axial force and then remains stationary;

[0031] S15, inputting welding process parameters of the turbine rear shaft and the turbine disk on the first welding assembly into the control system of the inertia friction welding machine, including initial rotation speed, welding rotation speed, friction pressure, and welding pressure;

[0032] S16, start the second welding, start the spindle motor of the inertia friction welding machine, stop supplying power to the spindle motor of the inertia friction welding machine after the rotation speed of the turbine rear shaft reaches the initial rotation speed, and the tailstock housing assembly moves a distance toward the spindle housing assembly under the action of the axial friction pressure, so that the end face of the turbine rear shaft is in close contact with the end face of the turbine disk on the first welding assembly to generate heat by friction, and when the rotation speed of the turbine rear shaft is reduced to the welding speed, the friction pressure is converted into welding pressure, and the axial welding pressure is maintained for a period of time and then removed after the turbine rear shaft stops rotating;

[0033] S17, the radial pressure of the spindle spring chuck is removed, the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly under the action of the axial force and then becomes fixed, the radial pressure of the tailstock side spring chuck is removed, and the second welding assembly formed by welding the turbine rear shaft and the first welding assembly is removed;

[0034] S18, disassemble the turbine rear shaft fixture and the assembly fixture, turn off the inertia friction welding machine control system, and the entire welding process is completed.

[0035] Compared with the prior art, the present invention has achieved the following technical effects:

[0036] The welding device and method disclosed in the present invention ensure the stability, dimensional accuracy and joint performance during the welding process of aircraft engine turbine disk shaft, improve the production rate of aircraft engine turbine disk shaft components and reduce production costs, and realize high-quality and high-precision welding and manufacturing of turbine disk shaft rotating parts made of homogeneous and heterogeneous high-temperature alloys and powder high-temperature alloy materials for aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0038] Figure 1 It is a front view of the spindle housing assembly and the tailstock housing assembly of this embodiment;

[0039] Figure 2 This is a front view of the first welding tool structure of this embodiment;

[0040] Figure 3 This is a front view of the second welding tool structure of this embodiment;

[0041] Figure 4 This is a front view of the third welding tool structure of this embodiment;

[0042] Figure 5 This is a front view of the fourth welding tool structure of this embodiment;

[0043] Figure 6 This is a front view of the first spring coil structure of this embodiment;

[0044] Figure 7 This is a front view of the second spring coil structure of this embodiment;

[0045] Figure 8 This is a front view of the third spring coil structure of this embodiment;

[0046] Fig. 9 This is a front view of the first bolt structure of this embodiment;

[0047] Fig.10 This is a front view of the second bolt structure of this embodiment;

[0048] Fig.11 This is a front view of the third bolt structure of this embodiment;

[0049] Fig.12 This is a front view of the fourth bolt structure of this embodiment;

[0050] Fig.13 It is a front view of the drum shaft of this embodiment;

[0051] Fig.14 is a front view of the turbine disc of this embodiment;

[0052] Fig.15 This is a front view of the turbine rear shaft of this embodiment;

[0053] Fig.16 It is an assembly drawing of the drum shaft fixture and turbine disc fixture of this embodiment;

[0054] Fig.17 This is a welding assembly diagram of the drum shaft and turbine disc of this embodiment;

[0055] Fig.18 This is a front view of the first welding assembly of this embodiment;

[0056] Fig.19 It is an assembly drawing of the turbine rear shaft fixture and the assembly fixture of this embodiment;

[0057] Fig. 20 This is a welding assembly drawing of the turbine rear shaft and the first welding assembly of this embodiment;

[0058] Fig.21 A turbine disc shaft welding assembly formed by welding the turbine rear shaft to the first welding assembly;

[0059] Explanation of the accompanying drawings: 1-spindle housing; 2-tailstock housing; 3-spindle on the spindle housing side; 4-inner cylinder on the tailstock housing side; 5-external threaded section; 6-mandrel on the spindle housing side; 7-mandrel on the tailstock housing side; 8-spindle spring chuck; 9-tailstock spring chuck; 10-first welding tool; 11-second welding tool; 12-third welding tool; 13-fourth welding tool; 14-first spring ring; 15-third spring ring; 16-second spring ring; 17-first bolt; 18-second bolt; 19-third bolt; 20-fourth bolt; a-drum shaft; b-turbine disk; c-turbine rear shaft; d-first welding assembly; e-second welding assembly. DETAILED DESCRIPTION

[0060] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0061] The purpose of the present invention is to provide an aircraft engine turbine disk shaft inertia friction welding device and method for ensuring high quality and high precision connection requirements of aircraft engine turbine disk shaft rotating parts.

[0062] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0063] like Figure 1-21 As shown, this embodiment provides an aircraft engine turbine disk shaft inertia friction welding device, including an inertia friction welding machine main structure and a welding fixture.

[0064] The main structure of the inertia friction welding machine includes a spindle housing assembly and a tailstock housing assembly, and the welding fixtures include a drum shaft fixture, a turbine disc fixture, a turbine rear shaft fixture, and a combined fixture. The drum shaft fixture is used to install the drum shaft a on the spindle housing assembly, the turbine disc fixture is used to install the turbine disc b on the tailstock housing assembly, the turbine rear shaft fixture is used to install the turbine rear shaft c on the spindle housing assembly, and the combined fixture is used to install the first welded assembly d of the drum shaft a and the turbine disc b on the tailstock housing assembly.

[0065] When the inertia friction welding device of the aircraft engine turbine disc b of this embodiment is in use, the drum shaft a is installed on the main shaft housing assembly by means of a drum shaft fixture, the turbine disc b is installed on the tailstock housing assembly by means of a turbine disc fixture, the drum shaft a and the turbine disc b are subjected to the first inertia friction welding to form a first welded assembly d; then, the turbine rear shaft c is installed on the main shaft housing 1 by means of a turbine rear shaft fixture, the first welded assembly d is installed on the tailstock housing assembly by means of an assembly fixture, the turbine rear shaft c and the first welded assembly d are subjected to the second inertia friction welding to form a second welded assembly e.

[0066] Specifically, the spindle box assembly includes a spindle box 1, a spindle 3 on the spindle box side, a spindle 6 on the spindle box side and a spindle spring chuck 8. The spindle spring chuck 8 is fixed to the spindle 3 on the spindle box side and the spindle box 1 by a first bolt 17 and a third bolt 19. The spindle spring chuck 8 is used to apply a radial clamping force to the parts on the inside. The spindle 3 on the spindle box side is fixedly connected to the spindle box side core shaft 6, that is, the two rotate synchronously.

[0067] The tailstock box assembly includes a tailstock box 2, an inner cylinder 4 on the tailstock box side, a core shaft 7 on the tailstock box side and a tailstock spring chuck 9. The inner cylinder 4 on the tailstock box side has an external thread section 5. The tailstock spring chuck 9 is threadedly connected to the inner cylinder 4 on the tailstock box side. The spring chuck of the tailstock box 2 is fixed to the tailstock box 2 by a second bolt 18. The tailstock spring chuck 9 is used to apply radial clamping force to the parts on the inside.

[0068] The drum shaft fixture includes a first welding fixture 10 and a first spring ring 14. The first welding fixture 10 is fixed to the spindle housing side core shaft 6 by a third bolt 19. The first spring ring 14 is located between the spindle spring chuck 8 and the drum shaft a. The first welding fixture 10 is used to axially position the drum shaft a, and the first spring ring 14 is used to transmit the clamping force applied by the spindle spring chuck 8 to radially position the drum shaft a.

[0069] The turbine disk fixture includes a second welding fixture 11, a third welding fixture 12 and a second spring ring 16. The second welding fixture 11 is fixed to the inner cylinder body 4 on the tailstock housing side together with the core shaft 7 on the tailstock housing side by a fourth bolt 20. The third welding fixture 12 is fixed to the second welding fixture 11 by a third bolt 19. The second spring ring 16 is located between the tailstock spring chuck 9 and the turbine disk b. The second welding fixture 11 and the third welding fixture 12 are sequentially arranged and coaxial along the axial direction, and are used to axially position the turbine disk b. The second spring ring 16 is used to transmit the clamping force applied by the tailstock spring chuck 9 to radially position the turbine disk b.

[0070] The turbine rear shaft fixture includes a first welding fixture 10 and a third spring ring 15. The first welding fixture 10 is fixed to the spindle housing side mandrel 6 by a third bolt 19. The third spring ring 15 is located between the spindle spring chuck 8 and the turbine rear shaft c. The first welding fixture 10 is used to axially position the turbine rear shaft c, and the third spring ring 15 is used to transmit the clamping force applied by the spindle spring chuck 8 to radially position the turbine rear shaft c.

[0071] The assembly fixture includes a fourth welding fixture 13 and a second spring ring 16. The fourth welding fixture 13 is sleeved on the tailstock housing side mandrel 7, and the second spring ring 16 is located between the tailstock spring chuck 9 and the turbine disk b. The fourth welding fixture 13 is used to axially position the first welded assembly d, and the second spring ring 16 is used to transmit the clamping force applied by the tailstock spring chuck 9 to radially position the turbine disk b in the first welded assembly d.

[0072] This embodiment also provides an aeroengine turbine disk b-axis inertia friction welding method, using the aeroengine turbine disk b-axis inertia friction welding device, comprising the following steps:

[0073] S1. Install the drum shaft fixture on the spindle housing assembly, and install the turbine disc fixture on the tailstock housing assembly;

[0074] S2, placing the drum shaft a on the spindle housing assembly on which the drum shaft fixture has been installed, the drum shaft a is located inside the first spring ring 14, and the end face F of the drum shaft a is in contact with the end face B of the first welding fixture 10, and the spindle spring chuck 8 clamps the first spring ring 14 and the drum shaft a by radial pressure;

[0075] S3, placing the turbine disc b on the tailstock housing assembly on which the turbine disc fixture has been installed, the turbine disc b is located inside the second spring ring 16, the end surface J of the turbine disc b contacts the end surface D of the third welding fixture 12, the end surface I of the turbine disc b contacts the end surface C of the third welding fixture 12, and the tailstock spring chuck 9 clamps the second spring ring 16 and the turbine disc b by radial pressure;

[0076] S4. Use a dust-free cloth dipped in alcohol or acetone solution to wipe the welding end surface G of the drum shaft a and the welding end surface H of the turbine disk b respectively to remove oil and impurities on the welding end surfaces of the drum shaft a and the turbine disk b;

[0077] S5. The tailstock housing assembly moves toward the spindle housing assembly under the action of the axial force, so that the end surface G of the drum shaft a is in close contact with the end surface H of the turbine disc b and remains stationary. The radial pressure of the spindle spring chuck 8 and the tailstock spring chuck 9 is removed, and then the radial pressure is applied again. Under the action of the axial force, the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly and then remains stationary.

[0078] S6. Inputting welding process parameters of the drum shaft a and the turbine disc b into the control system of the inertia friction welding machine, including initial rotation speed, welding rotation speed, friction pressure, and welding pressure;

[0079] S7, start the first welding, start the spindle motor of the inertia friction welding machine, stop supplying power to the spindle motor of the inertia friction welding machine after the rotation speed of the drum shaft a reaches the initial rotation speed, and the tailstock housing assembly moves a distance toward the spindle housing assembly under the action of the axial friction pressure, so that the end face G of the drum shaft a and the end face H of the turbine disk b are in close contact and generate heat by friction, and the axial friction pressure remains unchanged; when the rotation speed of the drum shaft a is reduced to the welding rotation speed, the axial friction pressure is converted into welding pressure and remains unchanged until the drum shaft a stops rotating, and the axial welding pressure is maintained for a period of time and then the axial welding pressure is removed;

[0080] S8, the radial pressure of the spindle spring chuck 8 is removed, the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly under the axial force and then becomes fixed, the radial pressure of the tailstock spring chuck 9 is removed, and the first welding assembly d of the drum shaft a and the turbine disk b is removed;

[0081] S9, disassembling the drum shaft fixture and turbine disc fixture;

[0082] S10. Install the turbine rear shaft fixture on the spindle housing assembly, and install the combined fixture on the tailstock housing assembly;

[0083] S11, placing the turbine rear shaft c inside the third spring ring 15, the end surface L of the turbine rear shaft c contacts the end surface B of the first welding tool 10, and the spindle spring chuck 8 clamps the third spring ring 15 and the turbine rear shaft c by radial pressure;

[0084] S12, placing the first welded assembly d on the tailstock housing assembly, the first welded assembly d is placed inside the second spring ring 16, the end face F of the drum shaft a on the first welded assembly d contacts the end face A of the core shaft 7 on the tailstock housing side, the end face K of the turbine disk b on the first welded assembly d contacts the end face E of the fourth welding fixture 13, and the tailstock spring chuck 9 clamps the second spring ring 16 and the turbine disk b on the first welded assembly d by radial pressure;

[0085] S13, using a dust-free cloth dipped in alcohol or acetone solution to wipe the end surface M of the turbine rear shaft c and the end surface J of the turbine disk b on the first welded assembly d, respectively, to remove oil and impurities on the end surface M of the turbine rear shaft c and the end surface J of the turbine disk b on the welded assembly;

[0086] S14, the tailstock housing assembly moves a distance toward the spindle housing assembly under the action of the axial force, so that the end surface M of the turbine rear shaft c is in close contact with the end surface J of the turbine disk b on the first welded assembly d and remains stationary, the radial pressure of the spindle spring chuck 8 and the tailstock spring chuck 9 is removed, and then the radial pressure is applied again, and the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly under the action of the axial force and then remains stationary;

[0087] S15, inputting welding process parameters of the turbine rear shaft c and the turbine disk b on the first welding assembly d into the control system of the inertia friction welding machine, including initial rotation speed, welding rotation speed, friction pressure, and welding pressure;

[0088] S16, start the second welding, start the spindle motor of the inertia friction welding machine, stop supplying power to the spindle motor of the inertia friction welding machine after the rotation speed of the turbine rear shaft c reaches the initial rotation speed, and the tailstock housing assembly moves a distance toward the spindle housing assembly under the action of the axial friction pressure, so that the end face M of the turbine rear shaft c is in close contact with the end face J of the turbine disk b on the first welding assembly d, and friction generates heat. When the rotation speed of the turbine rear shaft c is reduced to the welding rotation speed, the friction pressure is converted into welding pressure. After the turbine rear shaft c stops rotating, the axial welding pressure is maintained for a period of time and then removed;

[0089] S17, the radial pressure of the spindle spring chuck 8 is removed, the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly under the action of the axial force and then becomes fixed, the radial pressure of the tailstock side spring chuck is removed, and the second welding assembly e formed by welding the turbine rear shaft c and the first welding assembly d is removed;

[0090] S18, disassemble the turbine rear shaft fixture and the assembly fixture, turn off the inertia friction welding machine control system, and the entire welding process is completed.

[0091] The present specification uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core idea of ​​the present invention. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. An inertia friction welding device for an aircraft engine turbine disk shaft, characterized in that: include: The main structure of the inertia friction welding machine includes a spindle housing assembly and a tailstock housing assembly; A welding fixture, wherein the welding fixture comprises a drum shaft fixture, a turbine disk fixture, a turbine rear shaft fixture and a combined fixture, wherein the drum shaft fixture is used to install the drum shaft on the spindle housing assembly, the turbine disk fixture is used to install the turbine disk on the tailstock housing assembly, the turbine rear shaft fixture is used to install the turbine rear shaft on the spindle housing assembly, and the combined fixture is used to install the first welded assembly of the drum shaft and the turbine disk on the tailstock housing assembly; The spindle housing assembly comprises a spindle housing, a spindle on the spindle housing side, a spindle on the spindle housing side and a spindle spring chuck, wherein the spindle spring chuck is fixed to the spindle on the spindle housing side and the spindle housing by bolts; The tailstock box assembly comprises a tailstock box, a tailstock box inner cylinder, a tailstock box side spindle and a tailstock spring chuck. The tailstock spring chuck is connected to the tailstock box inner cylinder through threads, and the tailstock spring chuck is fixed to the tailstock box through bolts.

2. The inertia friction welding device for a turbine disk shaft of an aircraft engine according to claim 1, characterized in that: The drum shaft fixture comprises a first welding fixture and a first spring ring. The first welding fixture is fixed to the spindle housing side core shaft by bolts. The first spring ring is located between the spindle spring chuck and the drum shaft.

3. The inertia friction welding device for a turbine disk shaft of an aircraft engine according to claim 2, characterized in that: The turbine disk tooling fixture includes a second welding tool, a third welding tool and a second spring ring. The second welding tool and the tailstock housing side core shaft are fixed to the inner cylinder body of the tailstock housing by bolts. The third welding tool is fixed to the second welding tool by bolts. The second spring ring is located between the tailstock spring chuck and the turbine disk.

4. The inertia friction welding device for a turbine disk shaft of an aircraft engine according to claim 3, characterized in that: The turbine rear shaft fixture comprises a first welding fixture and a third spring ring. The first welding fixture is fixed to the spindle housing side core shaft by bolts. The third spring ring is located between the spindle spring chuck and the turbine rear shaft.

5. The inertia friction welding device for a turbine disk shaft of an aircraft engine according to claim 4, characterized in that: The combined fixture comprises a fourth welding fixture and a second spring ring. The fourth welding fixture is sleeved on the core shaft on the tailstock housing side. The second spring ring is located between the tailstock spring chuck and the turbine disc.

6. An inertia friction welding method for an aircraft engine turbine disk shaft, using the inertia friction welding device for an aircraft engine turbine disk shaft according to claim 5, characterized in that: The steps include: S1. Install the drum shaft fixture on the spindle housing assembly, and install the turbine disc fixture on the tailstock housing assembly; S2, placing the drum shaft on the spindle housing assembly on which the drum shaft fixture has been installed, the drum shaft is located inside the first spring ring, and the end face of the drum shaft is in contact with the end face of the first welding fixture, and the spindle spring chuck clamps the first spring ring and the drum shaft through radial pressure; S3, placing the turbine disc on the tailstock housing assembly on which the turbine disc fixture has been installed, the turbine disc is located inside the second spring ring, the end surface of the turbine disc contacts the end surface of the third welding fixture, and the tailstock spring chuck clamps the second spring ring and the turbine disc by radial pressure; S4. Use a dust-free cloth dipped in alcohol or acetone solution to wipe the welding end surface of the drum shaft and the welding end surface of the turbine disk respectively to remove oil and impurities on the welding end surfaces of the drum shaft and the turbine disk; S5. The tailstock housing assembly moves toward the spindle housing assembly under the action of the axial force, so that the end face of the drum shaft is in close contact with the end face of the turbine disc and remains stationary. The radial pressure of the spindle spring chuck and the tailstock spring chuck is removed, and then the radial pressure is applied again. Under the action of the axial force, the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly and then remains stationary. S6. Inputting welding process parameters of the drum shaft and the turbine disk into the control system of the inertia friction welding machine, including initial rotation speed, welding rotation speed, friction pressure, and welding pressure; S7, start the first welding, start the spindle motor of the inertia friction welding machine, stop supplying power to the spindle motor of the inertia friction welding machine after the rotation speed of the drum shaft reaches the initial rotation speed, and the tailstock housing assembly moves a distance toward the spindle housing assembly under the action of the axial friction pressure, so that the end face of the drum shaft and the end face of the turbine disc are in close contact and friction generates heat, and the axial friction pressure remains unchanged; when the rotation speed of the drum shaft is reduced to the welding speed, the axial friction pressure is converted into welding pressure and remains unchanged until the drum shaft stops rotating, and the axial welding pressure is maintained for a period of time and then removed; S8, the radial pressure of the spindle spring chuck is removed, and the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly under the action of the axial force and then becomes fixed, the radial pressure of the tailstock spring chuck is removed, and the first welding assembly of the drum shaft and the turbine disk is removed; S9, disassembling the drum shaft fixture and turbine disc fixture; S10. Install the turbine rear shaft fixture on the spindle housing assembly, and install the combined fixture on the tailstock housing assembly; S11, placing the turbine rear shaft inside the third spring ring, the end surface of the turbine rear shaft contacts the end surface of the first welding tool, and the spindle spring chuck clamps the third spring ring and the turbine rear shaft by radial pressure; S12, placing the first welded assembly on the tailstock housing assembly, placing the first welded assembly inside the second spring ring, the end face of the drum shaft on the first welded assembly contacts the end face of the core shaft on the tailstock housing side, the end face of the turbine disk on the first welded assembly contacts the end face of the fourth welding fixture, and the tailstock spring chuck clamps the second spring ring and the turbine disk on the first welded assembly by radial pressure; S13. Use a dust-free cloth dipped in alcohol or acetone solution to wipe the end surface of the turbine rear shaft and the end surface of the turbine disk on the first welded assembly respectively to remove oil and impurities on the end surface of the turbine rear shaft and the end surface of the turbine disk on the welded assembly; S14, the tailstock housing assembly moves a distance toward the spindle housing assembly under the action of the axial force, so that the end face of the turbine rear shaft is in close contact with the end face of the turbine disk on the first welding assembly and remains stationary, the radial pressure of the spindle spring chuck and the tailstock spring chuck is removed, and then the radial pressure is applied again, and the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly under the action of the axial force and then remains stationary; S15, inputting welding process parameters of the turbine rear shaft and the turbine disk on the first welding assembly into the control system of the inertia friction welding machine, including initial rotation speed, welding rotation speed, friction pressure, and welding pressure; S16, start the second welding, start the spindle motor of the inertia friction welding machine, make the rotation speed of the turbine rear shaft on the spindle housing side reach the initial speed, then stop powering the spindle motor of the inertia friction welding machine, the tailstock housing assembly moves a distance toward the spindle housing assembly under the action of axial friction pressure, so that the end face of the turbine rear shaft is in close contact with the end face of the turbine disk on the first welding assembly to generate heat by friction, when the rotation speed of the turbine rear shaft is reduced to the welding speed, the friction pressure is converted into welding pressure, until the turbine rear shaft stops rotating, the axial welding pressure is maintained for a period of time and then the axial welding pressure is removed; S17, the radial pressure of the spindle spring chuck is removed, the tailstock housing assembly moves a distance in the opposite direction of the spindle housing assembly under the action of the axial force and then becomes fixed, the radial pressure of the spring chuck on the tailstock housing side is removed, and the second welding assembly formed by welding the turbine rear shaft and the first welding assembly is removed; S18, disassemble the turbine rear shaft fixture and the assembly fixture, turn off the inertia friction welding machine control system, and the entire welding process is completed.

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