NL2032714A - Inertia friction welding device and method for turbine disc shaft of aircraft engine - Google Patents
Inertia friction welding device and method for turbine disc shaft of aircraft engine Download PDFInfo
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- NL2032714A NL2032714A NL2032714A NL2032714A NL2032714A NL 2032714 A NL2032714 A NL 2032714A NL 2032714 A NL2032714 A NL 2032714A NL 2032714 A NL2032714 A NL 2032714A NL 2032714 A NL2032714 A NL 2032714A
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- end surface
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
- B23K20/122—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding using a non-consumable tool, e.g. friction stir welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
- B23K20/129—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding specially adapted for particular articles or workpieces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
- B23K20/26—Auxiliary equipment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K37/00—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups
- B23K37/04—Auxiliary devices or processes, not specially adapted to a procedure covered by only one of the preceding main groups for holding or positioning work
- B23K37/0426—Fixtures for other work
- B23K37/0435—Clamps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2101/00—Articles made by soldering, welding or cutting
- B23K2101/001—Turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The invention discloses an aircraft engine turbine disc shaft inertia friction welding device, wherein the welding device comprises an inertia friction welding machine main body 5 structure and a welding tooling fixture, the main body structure of the inertia friction welding machine comprises a main shaft box body assembly and a tailstock box body assembly, and the welding tooling fixture comprises a drum shaft tooling fixture, a turbine disc tooling fixture, a turbine rear shaft tooling fixture and a combination tooling fixture. Compared with the prior art, the welding device and method disclosed in the present 10 invention ensure the stability, dimensional accuracy and joint performance in the welding process of the aircraft engine turbine disc shaft, improve the production rate of the aircraft engine turbine disc shaft assembly and reduce the production cost.
Description
INERTIA FRICTION WELDING DEVICE AND METHOD FOR TURBINE DISC
SHAFT OF AIRCRAFT ENGINE
[OI] The present invention relates to the field of inertia friction welding, and more particularly to an aircraft engine turbine disc shaft inertia friction welding device and method.
[02] Inertial friction welding is a typical welding method in the solid phase welding process. In the welding process, the mechanical kinetic energy is stored by the rotating flywheel, which drives one of the parts to rotate at high speed. Under the action of axial friction pressure, heat is generated by friction with the other stationary part. Under the action of upsetting welding pressure, plastic deformation and flow of friction interface material occur, and the welding of the two parts is realized. In the inertia friction welding process, because the friction interface temperature does not reach the melting point of the material, and the welding speed is fast and the welding time is short, the interface material is in a high-temperature plastic state, after the welding upsetting, part of the high-temperature metal material on the interface is extruded out of the weld seam to form a welding flash, which can eliminate the oil stain and oxide inclusion in the end surface of the test piece during the flash extrusion process, and has a self-cleaning function, which can avoid the existence of inclusion defects. At the same time, the weld seam is in a closed state during the welding process, which prevents the entry of air, and completely avoids the air holes, inclusion, cracks and non-fusion defects which often occur in the fusion welding head. It is especially suitable for the welding of axisymmetric parts of homogeneous/heterogeneous materials with large difference in mechanical properties, and can obtain high quality welded joints.
[03] With the development of high performance aircraft engine, new superalloy materials have been used more and more in aircraft engine turbine disc shaft assembly.
Especially, powder metallurgy superalloy (such as U720Li, Rene’88DT, RR1000, etc.) has many outstanding advantages, such as fine grain, uniform structure, no macro-segregation, high yield strength, good fatigue performance, etc. which has become the best material for aircraft engine turbine disc shaft. However, it is difficult to obtain high-quality welded joints by electron beam welding for the welding of dissimilar high-temperature alloy materials represented by powder metallurgy high-temperature alloy, mainly because the high volume percentage of y’ strengthening phase composition is complex in the welding process of high-temperature alloy as a high-energy density fusion welding process, which results in the formation of crystallization cracks, heat affected zone liquefaction cracks and strain aging cracks in the welding process. In addition, because of the difference of microstructure, melting point, thermal conductivity, thermal expansion coefficient and other parameters, the dissimilar high-temperature alloy materials in the welding process tend to cause microstructure segregation, and generate large thermal stress, resulting in cracks and other defects. In particular, the microcracks caused by grain boundary liquefaction during melting and welding of high temperature alloys are difficult to avoid, but difficult to effectively detect by non-destructive testing method. Therefore, fusion welding processes such as electron beam welding are not suitable for the welding of homogeneous and heterogeneous powder superalloy materials. Inertial friction welding, as a solid phase welding process, will avoid the problem of cracks and quality detection in fusion welding.
[04] At present, the bolting or electron beam welding process is still more used in the rotating parts of turbine disc shaft of aircraft engine in China, which greatly limits the application of high-performance homogeneous/heterogeneous powder superalloy materials in the rotating parts of turbine disc shaft of aircraft engine, and also limits the improvement of the overall performance of aircraft engine.
[05] It is an object of the present invention to provide an aircraft engine turbine disc shaft inertia friction welding device and method for ensuring high quality and high precision connection requirements for rotating parts of an aircraft engine turbine disc shaft.
[06] In order to achieve the above object, the present invention provides the following scheme:
[07] An aircraft engine turbine disc shaft inertia friction welding device is disclosed comprising:
[08] an inertia friction welding machine main body structure, the inertia friction welding machine main body structure comprising a main shaft box body assembly and a tailstock box body assembly;
[09] a welding tooling fixture, the welding tooling fixture comprising a drum shaft tooling fixture, a turbine disc tooling fixture, a turbine rear shaft tooling fixture and a combination tooling fixture, wherein the drum shaft tooling fixture is used for mounting a drum shaft on the main shaft box body assembly, the turbine disc tooling fixture is used for mounting a turbine disc on the tailstock box body assembly, the turbine rear shaft tooling fixture is used for mounting a turbine rear shaft on the main shaft box body assembly, and the combination tooling fixture is used for mounting a first welding combination of a drum shaft and a turbine disc on the tailstock box body assembly.
[10] Preferably, the main shaft box body assembly includes a main shaft box body, a main shaft box body side spindle, a main shaft box body side mandrel and a main shaft spring chuck, wherein the main shatt spring chuck is fixed on the spindle box side spindle and the main shaft box body by bolts.
[11] Preferably, the tailstock box body assembly comprises a tailstock box body, a tailstock box body inner cylinder body, a tailstock box body side mandrel, and a tailstock spring chuck, wherein the tailstock spring chuck is threadedly connected to the tailstock box body inner cylinder body, and the tailstock box body spring chuck is bolted to the tailstock box body.
[12] Preferably, the drum shaft tooling fixture comprises a first welding tooling bolted to the main shaft box body side mandrel and a first spring ring positioned between the main shaft spring chuck and the drum shaft.
[13] Preferably, the turbine disc tooling fixture comprises a second welding tooling, a third welding tooling and a second spring ring, wherein the second welding tooling is bolted together with the tailstock box body side mandrel to the tailstock box body inner cylinder body, the third welding tooling is bolted to the second welding tooling, and the second spring ring is located between the tailstock spring chuck and turbine disc. |14] Preferably, the turbine rear shaft tooling fixture comprises a first welding tooling bolted to the main shaft box body side mandrel and a third spring ring positioned between the main shaft spring chuck and turbine rear shaft.
[15] Preferably, the combination tooling fixture comprises a fourth welding tooling and a third spring ring, wherein the fourth welding tooling is sleeved on the tailstock box body side mandrel, and the third spring ring is positioned between the tailstock spring chuck and turbine disc.
[16] The present invention also discloses an aircraft engine turbine disc shaft inertia friction welding method using the above-mentioned aircraft engine turbine disc shaft inertia friction welding device, which comprises the steps of:
[17] SI, mounting a drum shaft tooling fixture on the main shaft box body assembly, and mounting a turbine disc tooling fixture on the tailstock box body assembly;
[18] SZ, placing the drum shaft on the main shaft box body assembly on which the drum shaft tooling fixture has been mounted, locating the drum shaft inside the first spring ring, and making the end surface of the drum shaft contact the end surface of the first welding tooling, and clamping, by the main shaft spring chuck, the first spring ring and the drum shaft by means of radial pressure;
[19] S3, placing the turbine on the tailstock box body assembly on which the turbine disc tooling fixture has been mounted, locating the turbine disc inside the second spring ring, contacting the end surface of the turbine disc with the end surface of the third welding tooling, and clamping, by the tailstock spring chuck, the second spring ring and the turbine disc by means of radial pressure;
[20] S4, wiping the welding end surface of the drum shaft and the welding end surface of the turbine disc by dipping an alcohol or acetone solution with a dust-free cloth, respectively, to remove oily impurities on the welding end surface of the drum shaft and the turbine disc;
[21] S5, moving the tailstock box body assembly towards the main shaft box body assembly under the action of an axial force, so that the end surface of the drum shaft is in close contact with the end surface of the turbine disc and keeping stationary, removing the 5 radial pressure from the main shaft spring chuck and the tailstock spring chuck, and then applying the radial pressure again, and moving the tailstock box body assembly towards the opposite direction of the main shaft box body assembly by a distance under the action of the axial force and then keeping stationary;
[22] So, inputting welding process parameters of the drum shaft and the turbine disc to a control system of the inertia friction welding machine, including an initial rotation speed, a welding rotation speed, a friction pressure and a welding pressure;
[23] S7, starting the first welding, starting the main shaft motor of the inertia friction welding machine, so as to stop supplying power to the main shaft motor of the inertia friction welding machine after the rotation speed of the drum shaft reaches the initial rotation speed, and moving the tailstock box body side assembly by a distance to the main shaft box body side assembly under the action of the axial friction pressure, so that the end surface of the drum shaft is in close contact with the end surface of the turbine disc to generate friction heat, and keeping the axial friction pressure unchanged; when the rotation speed of the drum shaft decreases to the welding rotation speed, the axial friction pressure changes into the welding pressure and remains unchanged until after the drum shaft stops rotating, keeping the axial welding pressure for a period of time and then withdrawing the axial welding pressure;
[24] S8, removing the radial pressure from the main shaft spring chuck, fixing the tailstock box body assembly after moving a distance in the opposite direction of the main shaft box body assembly under the axial force, removing the radial pressure from the tailstock spring chuck, and removing the first welding combination of the drum shaft and the turbine disc;
[25] S9, disassembling the drum shaft tooling fixture and the turbine disc tooling fixture;
[26] S10, mounting a turbine rear shaft tooling fixture on the main shaft box body assembly, and mounting a combination tooling fixture on the tailstock box body assembly;
[27] S11, placing the turbine rear shaft inside the third spring ring, contacting an end surface of the turbine rear shaft with an end surface of the first welding tooling, and clamping, by the main shaft spring chuck, the third spring ring and the turbine rear shaft by radial pressure;
[28] S12, placing the first welding combination on the tailstock box body assembly, placing the first welding combination inside the second spring ring, contacting the end surface of the turbine disc on the first welding combination with the end surface of the tailstock box body side mandrel, contacting the end surface of the turbine disc on the first welding combination with the end surface of the fourth welding tooling, and clamping, by the tailstock spring chuck, the second spring ring and the turbine disc on the first welding combination by means of radial pressure;
[29] S13, respectively wiping the end surface of the turbine rear shaft and the end surface of the turbine disc on the first welding combination by dipping an alcohol or acetone solution with a dust-free cloth to remove oily impurities on the end surface of the turbine rear shaft and the end surface of the turbine disc on the welding combination;
[30] S14, moving the tailstock box body assembly by a distance to the main shaft box body assembly under the action of the axial force, so that the end surface of the turbine rear shaft is in close contact with the end surface of the turbine disc on the first welding combination and keeping stationary, removing the radial pressure from the main shaft spring chuck and the tailstock spring chuck, and then applying the radial pressure again, and moving the tailstock box body assembly by a distance in the opposite direction to the main shaft box body assembly under the action of the axial force and then keeping stationary;
[31] S15, inputting the welding process parameters of the turbine rear shaft and the turbine disc on the first welding combination to the control system of the inertia friction welding machine, comprising an initial rotation speed, a welding rotation speed, a friction pressure and a welding pressure;
[32] S16, starting the second welding, starting the main shaft motor of the inertia friction welding machine, so that after the rotation speed of the turbine rear shaft reaches the initial rotation speed, stopping supplying power to the main shaft motor of the inertia friction welding machine, moving, by the tailstock box body assembly, a distance to the main shaft box body assembly under the action of the axial friction pressure, so that the end surface of the turbine rear shaft is in close contact with the end surface of the turbine disc on the first welding combination to generate friction heat, and when the rotation speed of the turbine rear shaft decreases to the welding rotation speed, converting the friction pressure to the welding pressure until after the turbine rear shaft stops rotating, removing the axial welding pressure after maintaining the axial welding pressure for a period of time;
[33] S17, removing the radial pressure from the main shaft spring chuck, fixing the tailstock box body assembly after moving a distance in the opposite direction of the main shaft box body assembly under the action of the axial force, removing the radial pressure from the tailstock side spring chuck, and discharging the second welding combination formed by welding the turbine rear shaft and the first welding combination;
[34] S18, disassembling the turbine rear shaft tooling fixture and the combination tooling fixture, closing the control system of the inertia friction welding machine, and finishing all the welding processes.
[35] The present invention achieves the following technical effects with respect to the prior art:
[36] The welding device and method disclosed in the present invention ensure the stability, dimensional accuracy and joint performance in the welding process of the turbine disc shaft of an aircraft engine, improve the production rate of the turbine disc shaft assembly of an aircraft engine and reduce the production cost, and realize the high-quality and high-precision welding production of the rotating parts of the turbine disc shaft of homogeneous and heterogeneous high-temperature alloy and powder high-temperature alloy materials for an aircraft engine.
[37] In order to explain the embodiments of the present invention or the technical solutions in the prior art more clearly, a brief description will be given below of the drawings which need to be used in the embodiments. It is obvious that the drawings in the following description are only some embodiments of the present invention, and it would have been obvious for a person skilled in the art to obtain other drawings according to these drawings without involving any inventive effort.
[38] Fig. 1 is a front view of a main shaft box body assembly and a tailstock box body assembly according to the embodiment;
[39] Fig. 2 is a front view showing a structure of a first welding tooling according to the embodiment;
[40] Fig. 3 is a front view of a second welding tooling structure according to the embodiment;
[41] Fig. 4 is a front view of a third welding tooling structure according to the embodiment;
[42] Fig. 5 is a front view showing a structure of a fourth welding tooling according to the embodiment;
[43] Fig 61s a front view of a first spring ring structure according to the embodiment;
[44] Fig. 7 is a front view of a second spring ring structure according to the embodiment;
[45] Fig. 8 is a front view of a third spring ring structure according to the embodiment;
[46] Fig. 9 is a front view of a first bolt structure according to the embodiment;
[47] Fig. 101s a front view of a second bolt structure according to the embodiment;
[48] Fig. 11 is a front view of a third bolt structure according to the embodiment;
[49] Fig. 12 is a front view of a fourth bolt structure according to the embodiment;
[50] Fig. 13 is a front view of a drum shaft according to the embodiment;
[51] Fig. 14 is a front view of a turbine disc according to the embodiment;
[52] Fig. 1515 a front view of a turbine rear shaft according to the embodiment;
[53] Fig. 16 is an assembly view of a drum shaft tooling fixture and a turbine disc tooling fixture according to the embodiment;
[54] Fig 171s a welded assembly view of the drum shaft and the turbine disc according to the embodiment;
[55] Fig. 18 is a front view of a first welding combination according to the embodiment;
[56] Fig. 19 is an assembly view of a turbine rear shaft tooling fixture and a combination tooling fixture according to the embodiment;
[57] Fig. 20 is a welding assembly view of the turbine rear shaft and the first welding combination according to the embodiment;
[58] Fig. 21 is a turbine disc shaft welding assembly formed by welding a turbine rear shaft to a first welding combination;
[59] Description of Reference Numerals: 1-main shaft box body; 2-tailstock box body; 3-Spindle box side spindle; 4-tailstock box side inner cylinder body; S-external thread section; 6-Spindle box side mandrel; 7-tailstock box side mandrel; 8-main shaft spring chuck; 9-tailstock spring chuck; 10-first welding tooling; 11-second welding tooling; 12-third welding tooling; 13-a fourth welding tool; 14-first coil; 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 discs; c-turbine rear shaft; d-first welding combination; e-second welding combination.
[60] The embodiments of the present invention will now be described more fully hereinafter with reference to the accompanying drawings, in which embodiments of the invention are shown. It is to be understood that the embodiments described are only a few, but not all embodiments of the invention. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without inventive effort fall within the scope of the present invention.
[61] It is an object of the present invention to provide an aircraft engine turbine disc shaft inertia friction welding device and method for ensuring high quality and high precision connection requirements for rotating parts of an aircraft engine turbine disc shaft.
[62] The above objects, features and advantages of the present invention will be more clearly understood from the following detailed description taken in conjunction with the accompanying drawings. |63] As shown in Figs. 1-21, the embodiment provides an aircraft engine turbine disc shaft inertia friction welding device including an inertia friction welding machine main body structure and a welding tooling fixture.
[64] The main body structure of the inertia friction welding machine comprises a main shaft box body assembly and a tailstock box body assembly, and the welding tooling fixture comprises a drum shaft tooling fixture, a turbine disc tooling fixture, a turbine rear shaft tooling fixture and a combination tooling fixture. The drum shaft tooling fixture is used for mounting a drum shaft a on the main shaft box body assembly, the turbine disc tooling fixture is used for mounting a turbine disc b on the tailstock box body assembly, the turbine rear shaft tooling fixture is used for mounting a turbine rear shaft c on the main shaft box body assembly, and the combination tooling fixture is used for mounting a first welding combination d of the drum shaft a and the turbine disc b on the tailstock box body assembly.
[65] When the inertia friction welding device for an aircraft engine turbine disc b of the embodiment is used, the drum shaft a is mounted on the main shaft box body assembly via the drum shaft tooling fixture, the turbine disc b is mounted on the tailstock box body assembly via the turbine disc tooling fixture, and the drum shaft a and the turbine disc b are subjected to a first inertia friction welding to form a first welding combination d; then, the turbine rear shaft c is mounted on the main shaft box body 1 via the turbine rear shaft tooling fixture, the first welding combination d is mounted on the tailstock box body assembly via the combination tooling fixture, and the turbine rear shaft c and the first welding combination d are subjected to a second inertia friction welding to form a second welding combination e.
[66] Specifically, the main shaft box body assembly comprises a main shaft box body 1, a main shaft box body side spindle 3, a main shaft box body side mandrel 6 and a main shaft spring chuck 8, wherein the main shaft spring chuck 8 is fixed on the main shaft box body side spindle 3 and the main shaft box body 1 via a first bolt 17 and a third bolt 19, the main shaft spring chuck 8 is used for applying a radial clamping force to an inner part, and the main shaft box body side spindle 3 is fixedly connected to the main shaft box body side spindle 6, i.e., the two rotate synchronously.
[67] The tailstock box body assembly comprises a tailstock box 2, a tailstock box-side inner cylinder body 4, a tailstock box-side mandrel 7 and a tailstock spring chuck 9, wherein the tailstock box-side inner cylinder body 4 has an external thread section 5, the tailstock spring chuck 9 is in threaded connection with the tailstock box-side inner cylinder body 4, the tailstock box 2 spring chuck is fixed on the tailstock box 2 via a second bolt 18, and the tailstock spring chuck 9 is used for applying a radial clamping force to an inner part.
[68] The drum shaft tooling fixture comprises a first welding tooling 10 and a first spring ring 14, wherein the first welding tooling 10 is fixed on the main shaft box body-side mandrel 6 via a third bolt 19, and the first spring ring 14 is located between the main shaft spring chuck 8 and the drum shaft a. The first welding tooling 10 is used for axially positioning the drum shaft a, and the first spring ring 14 is used for transmitting the clamping force applied by the main shaft spring chuck 8 for radially positioning the drum shaft a.
[69] The turbine disc tooling fixture comprises a second welding tooling 11, a third welding tooling 12 and a second spring ring 16, wherein the second welding tooling 11 and the tailstock box body-side mandrel 7 are fixed together on the tailstock box body-side inner cylinder body 4 via a fourth bolt 20, the third welding tooling 12 is fixed on the second welding tooling 11 via a third bolt 19, and the second spring ring 16 is located between the tailstock spring chuck 9 and the turbine disc b. The second welding tooling 11 and the third welding tooling 12 are arranged in sequence and coaxial in the axial direction for axially positioning the turbine disc b, and the second spring ring 16 is used for transmitting the clamping force applied by the tailstock spring chuck 9 and radially positioning the turbine disc b.
[70] The turbine rear shaft tooling fixture comprises a first welding tooling 10 and a third spring ring 15, wherein the first welding tooling 10 is fixed on the main shaft box body-side mandrel 6 via a third bolt 19, and the first spring ring 15 is located between the main shaft spring chuck 8 and the turbine rear shaft c. The first welding tooling 10 is used for axially positioning the turbine rear shaft c, and the third spring ring 15 is used for transmitting the clamping force applied by the main shaft spring chuck 8 for radially positioning the turbine rear shaft c.
[71] The combination tooling fixture comprises a fourth welding tooling 13 and a third spring ring 15, wherein the fourth welding tooling 13 is sleeved on the tailstock box body side mandrel 7, and the third spring ring 15 is positioned between the tailstock spring chuck 9 and turbine disc b. The fourth welding tooling 13 is used for axially positioning the first welding combination d, and the third spring ring 15 is used for transmitting the clamping force applied by the tailstock spring chuck 9 for radially positioning the turbine disc b in the first welding combination d.
[72] The embodiment also discloses an aircraft engine turbine disc shaft inertia friction welding method using the above-mentioned aircraft engine turbine disc shaft inertia friction welding device, which comprises the steps of:
[73] Sl, mounting a drum shaft tooling fixture on the main shaft box body assembly, and mounting a turbine disc tooling fixture on the tailstock box body assembly;
[74] S2, placing the drum shaft a on the main shaft box body assembly on which the drum shaft tooling fixture has been mounted, locating the drum shaft a inside the first spring ring 14, and contacting the end surface F of the drum shaft a with the end surface B of the first welding tooling 10, and clamping, by the main shaft spring chuck 8, the first spring ring 14 and the drum shaft a by means of radial pressure;
[75] S3, placing the turbine b on the tailstock box body assembly on which the turbine disc tooling fixture has been mounted, locating the turbine disc b inside the second spring ring 16, contacting the end surface J of the turbine disc b with the end surface D of the third welding tooling 12, and clamping, by the tailstock spring chuck 9, the second spring ring 16 and the turbine disc b by means of radial pressure;
[76] S4, wiping the welding end surface G of the drum shaft a and the welding end surface H of the turbine disc b by dipping an alcohol or acetone solution with a dust-free cloth, respectively, to remove oily impurities on the welding end surface of the drum shaft a and the turbine disc b;
[77] SS, moving the tailstock box body assembly towards the main shaft box body assembly under the action of an 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 keeping same stationary, removing the radial pressure from the main shaft spring chuck 8 and the tailstock spring chuck 9, and then applying the radial pressure again, and moving the tailstock box body assembly towards the opposite direction of the main shaft box body assembly by a distance under the action of the axial force and then keeping same stationary;
[78] 56, inputting welding process parameters of the drum shaft a and the turbine disc b to a control system of the inertia friction welding machine, including an initial rotation speed, a welding rotation speed, a friction pressure and a welding pressure;
[79] S7, starting the first welding, starting the main shaft motor of the inertia friction welding machine, so as to stop supplying power to the main shaft motor of the inertia friction welding machine after the rotation speed of the drum shaft a reaches the initial rotation speed, and moving the tailstock box body side assembly by a distance to the main shaft box body side assembly under the action of the axial friction pressure, 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 to generate friction heat, and keeping the axial friction pressure unchanged; when the rotation speed of the drum shaft a decreases to the welding rotation speed, the axial friction pressure changes into the welding pressure and remains unchanged until after the drum shaft a stops rotating, keeping the axial welding pressure for a period of time and then withdrawing the axial welding pressure;
[80] S8, removing the radial pressure from the main shaft spring chuck 8, fixing the tailstock box body assembly after moving a distance in the opposite direction of the main shaft box body assembly under the axial force, removing the radial pressure from the tailstock spring chuck 9, and removing the first welding combination a of the drum shaft a and the turbine disc b;
[81] S9, disassembling the drum shaft tooling fixture and the turbine disc tooling fixture;
[82] S10, mounting a turbine rear shaft tooling fixture on the main shaft box body assembly, and mounting a combination tooling fixture on the tailstock box body assembly;
[83] S11, placing the turbine rear shaft c inside the third spring ring 15, contacting an end surface L of the turbine rear shaft c with an end surface B of the first welding tooling 10, and clamping, by the main shaft spring chuck 8, the third spring ring 15 and the turbine rear shaft c by radial pressure;
[84] S12, placing the first welding combination a on the tailstock box body assembly, placing the first welding combination d inside the second spring ring 16, contacting the end surface F of the drum shaft a on the first welding combination d with the end surface A of the tailstock box body side mandrel 7, contacting the end surface K of the turbine disc b on the first welding combination d with the end surface E of the fourth welding tooling 13, and clamping, by the tailstock spring chuck 9, the second spring ring 16 and the turbine disc b on the first welding combination d by means of radial pressure;
[85] S13, respectively wiping the end surface M of the turbine rear shaft ¢ and the end surface J of the turbine disc b on the first welding combination d by dipping an alcohol or acetone solution with a dust-free cloth to remove oily impurities on the end surface M of the turbine rear shaft c and the end surface J of the turbine disc b on the welding combination;
[86] S14, moving the tailstock box body assembly by a distance to the main shaft box body 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 disc b on the first welding combination d and keeping same stationary, removing the radial pressure from the main shaft spring chuck 8 and the tailstock spring chuck 9, and then applying the radial pressure again, and moving the tailstock box body assembly by a distance in the opposite direction to the main shaft box body assembly under the action of the axial force and then keeping same stationary;
[87] S15, inputting the welding process parameters of the turbine rear shaft c and the turbine disc b on the first welding combination a to the control system of the inertia friction welding machine, comprising an initial rotation speed, a welding rotation speed, a friction pressure and a welding pressure;
[88] S16, starting the second welding, starting the main shaft motor of the inertia friction welding machine, so that after the rotation speed of the turbine rear shaft c reaches the initial rotation speed, stopping supplying power to the main shaft motor of the inertia friction welding machine, moving, by the tailstock box body assembly, a distance to the main shaft box body assembly under the action of the axial friction pressure, so that the end surface M of the turbine rear shaft c is in close contact with the end surface J of the turbine disc b on the first welding combination d to generate friction heat, and when the rotation speed of the turbine rear shaft c decreases to the welding rotation speed, converting the friction pressure to the welding pressure until after the turbine rear shaft c stops rotating, removing the axial welding pressure after maintaining the axial welding pressure for a period of time;
[89] S17, removing the radial pressure from the main shaft spring chuck 8, fixing the tailstock box body assembly after moving a distance in the opposite direction of the main shaft box body assembly under the action of the axial force, removing the radial pressure from the tailstock side spring chuck, and discharging the second welding combination e formed by welding the turbine rear shaft c and the first welding combination d;
[90] S18, disassembling the turbine rear shaft tooling fixture and the combination tooling fixture, closing the control system of the inertia friction welding machine, and finishing all the welding processes.
[91] While the principles and embodiments of the description have been described herein with reference to specific examples, the foregoing description of the examples has been presented only to aid in the understanding of the methods and principles of the invention. At the same time, a person skilled in the art will appreciate that many changes can be made in the specific embodiments and applications of the present invention in light of the above teachings. In view of the above, this description should not be construed as limiting the invention.
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CN101224522B (en) * | 2008-01-30 | 2010-07-28 | 中国兵器工业第五九研究所 | Inertia friction welding machine |
CN104400210B (en) * | 2014-10-28 | 2016-07-20 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of inertia friction weld method of aero-engine turbine disk and axle |
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CN215824521U (en) * | 2021-08-16 | 2022-02-15 | 哈尔滨焊接研究院有限公司 | Inertia friction welding device for turbine disc shaft of aircraft engine |
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CN104400210B (en) * | 2014-10-28 | 2016-07-20 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of inertia friction weld method of aero-engine turbine disk and axle |
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