CN116517637A - Rotor disk, rotor assembly, method for manufacturing rotor disk and rotor assembly, and aeroengine - Google Patents
Rotor disk, rotor assembly, method for manufacturing rotor disk and rotor assembly, and aeroengine Download PDFInfo
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- CN116517637A CN116517637A CN202210079122.9A CN202210079122A CN116517637A CN 116517637 A CN116517637 A CN 116517637A CN 202210079122 A CN202210079122 A CN 202210079122A CN 116517637 A CN116517637 A CN 116517637A
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 12
- 238000000034 method Methods 0.000 title description 20
- 238000003466 welding Methods 0.000 claims abstract description 136
- 238000006073 displacement reaction Methods 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 5
- 230000009467 reduction Effects 0.000 claims description 4
- 238000005452 bending Methods 0.000 abstract description 20
- 230000008569 process Effects 0.000 description 13
- 230000009471 action Effects 0.000 description 8
- 238000004904 shortening Methods 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 230000002159 abnormal effect Effects 0.000 description 3
- 229910045601 alloy Inorganic materials 0.000 description 3
- 239000000956 alloy Substances 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 239000011324 bead Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- SYHGEUNFJIGTRX-UHFFFAOYSA-N methylenedioxypyrovalerone Chemical compound C=1C=C2OCOC2=CC=1C(=O)C(CCC)N1CCCC1 SYHGEUNFJIGTRX-UHFFFAOYSA-N 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Classifications
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
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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
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/027—Arrangements for balancing
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
Abstract
The invention discloses a rotor blade disc, a rotor assembly, a manufacturing method thereof and an aeroengine. According to the invention, the first protruding part and the second protruding part which are positioned at different radial positions are arranged on the side part of the blade disc body of the rotor blade disc, so that the disc center deflection caused by friction bending moment generated when two rotor blade discs are subjected to inertia friction welding can be reduced or even eliminated, and finally, the disc center deformation of the rotor blade disc is reduced, and the dimensional precision and dynamic balance of the whole part are seriously influenced by the rotor assembly of the aeroengine due to the axial precision deviation of the rotor blade discs after welding and the disc center deformation deflection after repeated superposition.
Description
Technical Field
The invention relates to a rotor blade disc, a rotor assembly, a manufacturing method of the rotor assembly and an aeroengine.
Background
With the progress of aero-engine technology, the high-pressure compressor and the high-pressure turbine rotor assembly of the aero-engine all adopt novel high-temperature alloy inertia friction welding processes such as powder alloy and the like. Compared with the traditional electron beam welding process, the inertia friction welding is used as an advanced welding process, the welding seam is of a forged structure, the welding seam has the advantages of good joint performance, high material utilization rate, environmental protection and the like, and is the most feasible method for realizing advanced high-temperature alloy connection such as dissimilar material welding, powder superalloy and the like at present. In order to further increase turbine efficiency and operational reliability, advanced aero-engines are also increasingly more dimensionally accurate to rotor assemblies. The dimensional accuracy of the inertial friction welding rotor assembly of the current aeroengine is mainly reflected in the welding axial shrinkage accuracy and the deformation of the post-welding disk core.
The aeroengine rotor assembly is an integral structure formed by a plurality of stages of blades, and along with the continuous improvement of the performance index of the aeroengine, higher requirements are put on the integral precision and welding quality of the rotor assembly. In particular to a multistage disc welding assembly, after repeated welding, the axial precision deviation after welding and disc core deformation deviation are overlapped for a plurality of times, and the dimensional precision and dynamic balance of the whole part can be seriously influenced. The deformation of the disc center of the aircraft engine rotor assembly after welding is mainly reflected in the deformation of the disc web of the compressor disc or the turbine disc after welding, and the disc center is in conical deformation (shown in figure 1), so that the gap between the disc centers is changed and the overall dynamic balance of the rotor assembly exceeds the standard, and the abnormal vibration of the engine is affected.
Disclosure of Invention
The invention aims to solve the technical problem that a rotor blade disc in a rotor assembly of an aeroengine is easy to generate disc core deformation after being welded by inertia friction welding in the prior art, and provides the rotor blade disc, the rotor assembly, a manufacturing method of the rotor assembly and the aeroengine.
The invention solves the technical problems by the following technical scheme:
a rotor disk for constructing a rotor assembly of an engine includes a disk body having a first side opposite an adjacent rotor disk on the rotor assembly, an outer periphery of the first side having a first projection and a second projection for friction welding with the adjacent rotor disk, the second projection being proximate an outer edge of the disk body relative to the first projection.
In this scheme, through set up the first bulge and the second bulge that are located different radial positions at the lateral part of rotor leaf disc's leaf disc body, can reduce even eliminate the disk heart skew that produces frictional force moment of flexure and lead to when two rotor leaf discs carry out inertia friction welding to finally reduce the disk heart deformation of rotor leaf disc, thereby avoid aeroengine's rotor subassembly to seriously influence the dimensional accuracy and the dynamic balance of whole part after the rotor leaf disc post-weld axial accuracy deviation and disk heart deformation skew stack many times, improve aeroengine rotor subassembly axial accuracy.
Preferably, the first projection has a first welding friction surface facing the adjacent rotor disk, and the second projection has a second welding friction surface facing the adjacent rotor disk, the first welding friction surface being closer to the adjacent rotor disk than the second welding friction surface.
In the scheme, the first convex parts of the two rotor blade discs firstly generate friction, the second convex parts generate friction, in the initial friction stage of inertia friction welding, the friction pressure (the friction pressure is generally 1/2-1/4 of the final upsetting pressure) of the first convex parts of the two rotor blade discs can form a certain bending moment, and at the final welding stage, the second convex parts start to rub, and at the moment, the second convex parts are still in a low-temperature state compared with the welding seam between the first convex parts, and the yield strength is high, so that the main friction is concentrated on the second convex parts, the second convex parts can be regarded as main bearing points, the direction of the bending moment generated at the moment is opposite to the direction of the initial torque, and the deformation offset of the disc center generated by the initial torque can be compensated, so that the adjustment of the disc center offset is realized, and the disc center deformation of the rotor blade discs is reduced or even eliminated.
Preferably, the first protruding portion is of a circular ring structure, and the first protruding portion and the leaf disc body have the same axis.
In this scheme, adopt above-mentioned structure, can guarantee two rotor blade dish welded connection's fastness.
Preferably, the second protruding portion is of a circular ring structure, and the second protruding portion and the leaf disc body have the same axis.
In the scheme, the structure is adopted, so that the firmness of welding connection of the two rotor blade discs is further improved, meanwhile, the two second protruding parts can be always in a friction contact state at the end of welding, the rest energy of the flywheel of the inertia friction welding machine is completely consumed by the second protruding parts, and the deformation of the disc center of the rotor blade disc is reduced.
Preferably, the first protruding portion and/or the second protruding portion has a plurality of, and the plurality of first protruding portions and/or the second protruding portion are arranged at intervals along the circumferential direction of the blisk body.
Preferably, along the radial direction of the blisk body, the thicknesses of the bosses of the first protruding part and the second protruding part are h 1 The distance between the first convex part and the second convex part is h 2 Wherein: f is the upsetting pressure of friction welding, sigma is the material yield strength of the rotor disc at the welding temperature, and R is the inner diameter of the first bulge.
In this embodiment, the boss thickness h of the first and second protruding portions 1 Mainly determined by the residual energy of the flywheel (i.e. the instability of the residual energy), when the possible residual energy is large, a proper thickness h of the boss should be selected to ensure the complete consumption of the residual energy 1 The method comprises the steps of carrying out a first treatment on the surface of the Distance h between first and second protrusions 2 Mainly determined by the bending moment generated by a clamp for clamping the rotor disk, when the bending moment is larger, a larger distance h should be adopted for balancing the torque 2 The method comprises the steps of carrying out a first treatment on the surface of the First and second protrusionsBoss thickness h of the projection 1 And a distance h between the first projection and the second projection 2 The above relation of the rotor blade disc can ensure that when the residual energy of the flywheel is completely consumed by the first protruding part or the second protruding part, the welding seams of the first protruding part and the second protruding part have synchronous friction bearing force until the final welding is finished, thereby ensuring the axial precision of the welding of the rotor blade disc and effectively avoiding the deformation of the disc center.
The invention provides a rotor assembly, which comprises a plurality of rotor blades, wherein the rotor blades are welded and fixed by welding friction welding, and the first convex part and the second convex part which correspond to the two adjacent rotor blades are welded and fixed by welding friction welding.
In this scheme, adopt above-mentioned rotor subassembly of rotor leaf dish, rotor leaf dish's hub interval changes little, and rotor subassembly whole dynamic balance is good, can not cause influencing engine abnormal vibration, further improves aeroengine's turbine efficiency and reliability in use.
The invention provides a manufacturing method of a rotor assembly, wherein the rotor assembly is the rotor assembly, and the manufacturing method comprises the following steps:
s1, respectively mounting two rotor blade discs at a rotating end and a moving end of an inertia friction welding machine;
s2, adjusting the displacement of the rotor blade disc on the moving end to enable the convex parts which are later in friction welding in the first convex part and the second convex part which are opposite to each other to generate friction welding to generate axial displacement of 0.02-0.05 mm;
s3, starting an inertia friction welding machine, and welding two rotor blade discs;
s4, repeating the steps S1-S3 to obtain a rotor blade disc assembly, and assembling the rotor blade disc assembly with other parts of the rotor assembly to obtain the rotor assembly.
In the scheme, the flywheel residual moment of inertia is lower before friction welding occurs to the bulge which later generates friction welding in the first bulge and the second bulge, the welding seam of the bulge which earlier generates friction welding is in a plastic softening state after friction, the bulge which later generates friction welding is still in an initial friction state due to the fact that the bulge just steps into a friction stage, and the flywheel residual energy main action area is converted from a welding seam area to a friction area of the bulge which later generates friction welding. The protruding part which generates friction welding later has little change of axial shortening due to the initial friction state, and the protruding part which generates friction welding later generates friction welding of the two rotor disks is enabled to generate axial displacement of 0.02-0.05 mm after friction welding, when the residual energy of the flywheel is completely consumed by the protruding part which generates friction welding later, the protruding part which generates friction welding later completes welding after 0.02-0.05 mm of abrasion, thereby ensuring the axial precision of welding.
Preferably, in step S2, the two opposite first protrusions are friction welded first, and the two opposite second protrusions are friction welded later, and the step S2 further includes the following steps:
s21, determining the axial friction reduction d of the two opposite first convex parts when the two opposite second convex parts are in welding friction 1 ；
S22, adjusting a moving end of the inertia friction welding machine to enable the displacement of the rotor blade disc on the moving end moving towards the direction of the rotor blade disc on the rotating end to be L+d 1 And + (0.02-0.05 mm), wherein L is the initial spacing between the two opposite first protrusions before the moving end moves.
The present invention provides an aeroengine comprising a rotor blade disc as described above.
The invention has the positive progress effects that: according to the invention, the first protruding part and the second protruding part which are positioned at different radial positions are arranged on the side part of the blade disc body of the rotor blade disc, so that the disc center deflection caused by friction bending moment generated when two rotor blade discs are subjected to inertia friction welding can be reduced or even eliminated, and finally the disc center deformation of the rotor blade disc is reduced, thereby avoiding that the dimensional precision and dynamic balance of the whole part are seriously influenced by the axial precision deviation of the rotor blade discs after welding and the disc center deformation deflection after repeated superposition of the rotor assembly of the aeroengine, and improving the axial precision of the rotor assembly of the aeroengine.
Drawings
FIG. 1 is a schematic illustration of a post-weld rotor disk core deflection of a rotor disk of an aircraft engine rotor assembly of the prior art.
Fig. 2 is a schematic diagram showing the variation of parameters of a rotor disk in the prior art at different stages in the inertia friction welding process.
FIG. 3 is a schematic diagram of a prior art rotor disk clamping in an inertia friction welder.
FIG. 4 is a schematic diagram of bending moments experienced by a rotor disk in a prior art inertia friction welding process.
FIG. 5 is a schematic view of a rotor assembly of a preferred embodiment of the present invention prior to welding of two rotor disks.
Fig. 6 is a schematic view of a partial structure at a in fig. 5.
FIG. 7 is a diagram illustrating the stress state of two rotor disks during inertia friction welding in accordance with the present invention.
Reference numerals illustrate:
rotor disk 100
First projection 101
Second projection 102
Clamp 200
Detailed Description
The invention will now be more fully described by way of example only and with reference to the accompanying drawings, but the invention is not thereby limited to the scope of this example.
The conventional inertia friction welding process is that a welding line generates friction heat under the action of rotational inertia and friction pressure so as to axially shorten, and finally, final welding is completed under the action of upsetting force, the whole axial shortening process cannot be regulated and controlled, and the welding process is shown in fig. 2.
Referring to FIG. 3, a prior art rotor plate 100 is schematically shown in an inertia friction welder. Because of the design accuracy requirements, the outer edge tenon side of the rotor disc 100 (or the turbine disc) is often used as a clamping reference surface of the clamp 200, and because the tenon side is used as a reference surface, the tenon side is preferably used as a positioning surface of the clamp 200, however, such positioning and clamping necessarily causes bending moment, as shown in fig. 4. During the welding process, the direction of force applied by the clamp 200 is not in the same horizontal plane as the direction of the weld, so that the part is subjected to a bending moment Γ, which is in direct proportion to the applied friction force F and the horizontal spacing l, i.e., Γ=f×l. Under the effect of this bending moment, the weld will have two consequences: 1) The weld joint interface is uneven in stress, the outer side is large in stress, the inner side is small in stress, so that the outer side is shortened greatly, the inner side is contracted little, and under the action of uneven deformation, large stress exists in the weld joint, so that the hub of the rotor blade disc 100 is subjected to conical deformation; 2) The part forms a 'teeterboard' action by taking the welding seam as a fulcrum under the action of the bending moment, so that the center of the rotor disc 100 is caused to deviate. Both of these results result in a hub deflection of the rotor disc 100 as shown in fig. 1.
As shown in fig. 5 and 6, in order to avoid the phenomenon that the rotor disk 100 is deformed and deflected during welding, an embodiment of the present invention provides a rotor disk 100 for constituting a rotor assembly of an engine. The rotor blade disc 100 includes a blade disc body having a first side opposite to an adjacent rotor blade disc 100 on the rotor assembly, an outer peripheral portion of the first side having a first projection 101 and a second projection 102 for friction welding with the adjacent rotor blade disc 100, the second projection 102 being adjacent to an outer edge of the blade disc body relative to the first projection 101.
Through set up the first bulge 101 and the second bulge 102 that are located different radial positions at the lateral part of the leaf disc body of rotor leaf disc 100, can reduce or even eliminate the disk heart skew that produces frictional force moment of flexure and lead to when two rotor leaf discs 100 carry out inertia friction welding to finally reduce the disk heart deformation of rotor leaf disc 100, thereby avoid aircraft engine's rotor subassembly to seriously influence the dimensional accuracy and the dynamic balance of whole part after the axial accuracy deviation and disk heart deformation skew overlap many times behind rotor leaf disc 100 weld, improve aircraft engine rotor subassembly axial accuracy.
In fig. 5 and 6, only two protrusions (i.e., the first protrusion 101 and the second protrusion 102) are illustrated at one side of the rotor blade disc 100, and it should be understood by those skilled in the art that the rotor assembly has a plurality of rotor blade discs 100, and other rotor blade discs 100 are welded to the rotor blade discs 100 at both sides except that only one side of the two rotor blade discs 100 at the outermost end of the rotor assembly is welded, so that the opposite sides of the rotor blade disc 100 have the first protrusion 101 and the second protrusion 102 welded to the other rotor blade discs 100. The region between the first protrusion 101 and the second protrusion 102 may serve as a clamping portion of the jig 200. Of course, both sides of the two rotor disks 100 located at the outermost ends of the rotor assembly may also have a first protrusion 101 and a second protrusion 102.
In the present embodiment, the first projection 101 has a first welding friction surface facing the adjacent rotor disk 100, and the second projection 102 has a second welding friction surface facing the adjacent rotor disk 100, the first welding friction surface being closer to the adjacent rotor disk 100 than the second welding friction surface.
In this embodiment, the first protrusion 101 of the two rotor blades 100 generates friction first, the second protrusion 102 generates friction later, and in the initial friction stage of inertia friction welding, the friction pressure (the friction pressure is generally 1/2-1/4 of the final upsetting pressure) of the first protrusion 101 of the two rotor blades 100 forms a certain bending moment, and at the end of welding, the second protrusion 102 starts to rub, and at this moment, the second protrusion 102 is still in a low temperature state compared with the welding seam between the first protrusions 101, and the yield strength is high, so that the main friction is concentrated on the second protrusion 102, the second protrusion 102 can be regarded as a main bearing fulcrum, and the generated bending moment direction is opposite to the initial torque direction, so that the disc center deformation offset generated by the initial torque can be compensated, thereby realizing the adjustment of the disc center offset, and reducing or even eliminating the disc center deformation of the rotor blade 100.
In other embodiments, the second protrusions 102 of the two rotor disks 100 generate friction first, and the first protrusions 101 generate friction later, and the specific process is referred to the above description and will not be repeated here.
In this embodiment, the first protruding portion 101 has a circular ring structure, and the first protruding portion 101 and the blade body have the same axis. With the above structure, the welding connection firmness of the two rotor blade discs 100 can be ensured.
In this embodiment, the second protruding portion 102 has a circular ring structure, and the second protruding portion 102 and the blade body have the same axis. The second protruding part 102 adopts the structure, so that the welding connection firmness of the two rotor blade discs 100 is further improved, meanwhile, the two second protruding parts 102 can be always in a friction contact state at the end of welding, the rest energy of the flywheel of the inertia friction welding machine is completely consumed by the second protruding parts 102, and the deformation of the disc center of the rotor blade disc 100 is reduced.
In other embodiments, the first protrusion 101 and/or the second protrusion 102 have a plurality of first protrusions 101 and/or second protrusions 102 that are disposed at intervals along the circumferential direction of the blisk body. For example, the first protruding portion 101 is a plurality of circular arc blocks having the same structure, each circular arc block encloses a circular ring structure having the same axis as the rotor blade disc 100, and a gap is provided between each circular arc blocks.
In the present embodiment, the boss thicknesses of the first protrusion 101 and the second protrusion 102 are h along the radial direction of the blisk body 1 The first protrusion 101 and the second protrusion 102 have a distance h 2 Wherein:where F is the upset pressure of the friction weld, σ is the material yield strength of rotor blade disc 100 at the welding temperature, and R is the inner diameter of first projection 101.
In this embodiment, the boss thickness h of the first and second protruding portions 101 and 102 1 Mainly determined by the residual energy of the flywheel (i.e. the instability of the residual energy), when the possible residual energy is large, a proper thickness h of the boss should be selected to ensure the complete consumption of the residual energy 1 The method comprises the steps of carrying out a first treatment on the surface of the Distance h between first projection 101 and second projection 102 2 Mainly determined by the bending moment generated by the clamp 200 clamping the rotor disc 100, when the bending moment is large, a large distance h should be used for balancing the torque 2 The method comprises the steps of carrying out a first treatment on the surface of the Boss thickness h of first projection 101 and second projection 102 1 And a distance h between the first protrusion 101 and the second protrusion 102 2 The above relation of (2) can ensure the surplus of the flywheelWhen the energy is completely consumed by the first protruding part 101 or the second protruding part 102, the welding seam of the first protruding part 101 and the second protruding part 102 has synchronous friction bearing force until the final welding is completed, so that the axial precision of the welding of the rotor blade disc 100 is ensured, and the deformation of the disc center is effectively avoided.
The embodiment of the present invention further provides a rotor assembly, where the rotor assembly includes a plurality of rotor blade discs 100 as described above, and the first protruding portion 101 and the second protruding portion 102 corresponding to two adjacent rotor blade discs 100 are welded and fixed by welding friction welding. By adopting the rotor assembly of the rotor blade disc 100, the rotor blade disc 100 has small disc center interval change, the rotor assembly is good in overall dynamic balance, abnormal vibration of the engine cannot be influenced, and the turbine efficiency and the use reliability of the aeroengine are further improved.
The embodiment of the invention also provides a manufacturing method of the rotor assembly, which comprises the following steps:
s1, respectively installing two rotor blade discs 100 at a rotating end and a moving end of an inertia friction welding machine;
s2, adjusting the displacement of the rotor blade disc 100 on the moving end, so that the convex parts which are in friction welding later in the first convex part 101 and the second convex part 102 opposite to each other of the two rotor blade discs 100 are subjected to friction welding and then axially displaced by 0.02-0.05 mm;
s3, starting an inertia friction welding machine, and welding two rotor blade discs 100;
s4, repeating the steps S1-S3 to obtain a rotor blade disc 100 assembly, and assembling the rotor blade disc 100 assembly and other parts of the rotor assembly to obtain the rotor assembly.
In the above-described method of manufacturing the rotor assembly, the flywheel remaining moment of inertia is low before friction welding occurs to the later friction-welded one of the first and second protrusions 101 and 102, the weld bead of the earlier friction-welded one is in a plastic softened state after friction, and the later friction-welded one is still in an initial friction state due to the just-stepped friction stage, and the flywheel remaining energy main action region is converted from the weld bead region to the friction region of the later friction-welded one. The protrusion part which generates friction welding later has little change in the axial shortening amount due to the initial friction state, and the protrusion part which generates friction welding later generates friction welding of the two rotor disks 100 is axially displaced by 0.02-0.05 mm after friction welding, so that when the residual energy of the flywheel is completely consumed by the protrusion part which generates friction welding later, the protrusion part which generates friction welding later completes welding after 0.02-0.05 mm of abrasion, thereby ensuring the axial precision of welding.
In this embodiment, taking the case that the two opposite first protrusions 101 are first friction welded and the two opposite second protrusions 102 are then friction welded, the step S2 further includes the following steps:
s21, determining the axial friction reduction d of the two opposite first convex parts 101 when the two opposite second convex parts 102 are in welding friction 1 ；
S22, adjusting the moving end of the inertia friction welding machine to enable the displacement of the rotor disc 100 on the moving end to move towards the rotor disc 100 on the rotating end to be L+d 1 + (0.02-0.05 mm), where L is the initial spacing between the first two opposing projections 101 before the moving end moves.
Assuming that the total design reduction of the first lobe is d after welding of the two rotor disks 100 is complete 0 The interval between the two second convex parts before the two opposite first convex parts are in friction contact is d 1 D is then 1 ＝d 0 -(0.02～0.05mm)，d 1 Ratio d 0 The minimum of 0.02-0.05 mm is used for consuming the energy of the residual flywheel, the specific difference is related to the axial required precision, and when the axial precision of each rotor blade disc 100 of the rotor assembly is required to be larger, the design shortening amount d is required to be equal to the design shortening amount d 0 The difference is as small as possible and is also equal to the boss thickness h of the second protruding part 1 Closely related, boss thickness h of the second boss 1 Mainly determined by the magnitude of the remaining energy of the flywheel (i.e. the instability of the remaining energy), when the possible remaining energy is large, due to d 1 And d 0 The second convex part is more similar to the first convex part, and the second convex part is more than the first convex part 1 . The weld distance h between the second protruding part and the first protruding part 2 Mainly determined by the bending moment Γ generated by the clamp 200. When the bending moment is relatively highWhen the torque is large, a large distance h should be adopted for balancing the torque 2 。
The manufacturing method of the rotor assembly adds the process of secondary friction through the second protruding part on the basis of the traditional inertia friction welding process: when the axial shortening of the first protruding portion reaches d 1 At this time, the second convex portions of the two rotor disks 100 are in contact with each other, and the first convex portion is shortened by an amount d 1 And design shortening d 0 The difference is about 0.02-0.05 mm, at the moment, the residual moment of inertia of the flywheel is lower, the welding seam of the first protruding part is in a plastic softening state after friction, and the second protruding part is in an initial friction state due to the fact that the second protruding part just steps into a friction stage. The flywheel surplus energy primary region of action is transferred from the weld region of the first lobe to the second lobe region. As can be seen from fig. 2, the second protrusion has little variation in axial shortening due to the initial friction state, so when the remaining energy of the flywheel is completely consumed by the boss, the second protrusion completes welding after 0.02-0.05 mm of wear, thereby ensuring the axial accuracy of welding the two rotor blade discs 100.
As shown in fig. 2, 4 and 7, the stress state of the rotor blade disc 100 in the initial friction stage is consistent with that of the conventional welding process, at this time, the friction pressure F (the friction pressure is generally 1/2-1/4 of the final upsetting pressure) forms a certain bending moment, at the end of welding, the second bulge on the outer side starts to rub, at this time, the second bulge is still in a low temperature state compared with the welding seam of the first bulge, and the yield strength is high, so that the main friction is concentrated on the second bulge, and the second bulge can be regarded as a main bearing fulcrum. At this time, the bending moment generated by the rotor disk 100 is opposite to the initial torque, and the deflection of the disk center due to the initial torque can be compensated. With the friction heating softening of the second bulge and the deformation offset compensation of the disk center, the magnitudes of the welding seam friction normal force F1 and F2 of the first bulge are gradually close, the upsetting force F, the welding seam friction normal force F1 of the first bulge and the friction normal force F2 of the second bulge form a simple support structure, the disk center of the rotor disk 100 is not subjected to obvious bending moment, then the welding seam of the second bulge and the first bulge synchronously rubs and bears force, and finally the welding is completed, so that the adjustment of the disk center offset is realized.
An aeroengine is also provided in an embodiment of the present invention, and the aeroengine includes the rotor disc 100 or the rotor assembly described above.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (10)
1. A rotor disk for constructing a rotor assembly of an engine, the rotor disk comprising a disk body having a first side opposite an adjacent rotor disk on the rotor assembly, an outer periphery of the first side having a first projection and a second projection for friction welding with the adjacent rotor disk, the second projection being proximate an outer edge of the disk body relative to the first projection.
2. The rotor disk as recited in claim 1 wherein the first projection has a first weld friction surface facing the adjacent rotor disk and the second projection has a second weld friction surface facing the adjacent rotor disk, the first weld friction surface being closer to the adjacent rotor disk than the second weld friction surface.
3. The rotor blade disc as recited in claim 1 wherein the first projection is of annular configuration, the first projection having the same axis as the blade disc body.
4. The rotor blade disc as recited in claim 3 wherein the second projection is of annular configuration, the second projection having the same axis as the blade disc body.
5. The rotor blade disc as claimed in claim 1, wherein the first projection and/or the second projection has a plurality, and the plurality of first projections and/or the second projections are arranged at intervals in the circumferential direction of the blade disc body.
6. The rotor disk of any one of claims 3-5 wherein the boss thickness of the first and second projections is h in the radial direction of the disk body 1 The distance between the first convex part and the second convex part is h 2 Wherein:f is the upsetting pressure of friction welding, sigma is the material yield strength of the rotor disc at the welding temperature, and R is the inner diameter of the first bulge.
7. A rotor assembly comprising a plurality of rotor blades as claimed in any one of claims 1 to 6, wherein the first and second protrusions of two adjacent rotor blades are welded together by welding friction welding.
8. A method of manufacturing a rotor assembly according to claim 7, comprising the steps of:
s1, respectively mounting two rotor blade discs at a rotating end and a moving end of an inertia friction welding machine;
s2, adjusting the displacement of the rotor blade disc on the moving end to enable the convex parts which are later in friction welding in the first convex part and the second convex part which are opposite to each other to generate friction welding to generate axial displacement of 0.02-0.05 mm;
s3, starting an inertia friction welding machine, and welding two rotor blade discs;
s4, repeating the steps S1-S3 to obtain a rotor blade disc assembly, and assembling the rotor blade disc assembly with other parts of the rotor assembly to obtain the rotor assembly.
9. The method of manufacturing a rotor assembly as set forth in claim 8, wherein in step S2, friction welding occurs first with two opposing first protrusions and friction welding occurs later with two opposing second protrusions, said step S2 further comprising the steps of:
s21, determining the axial friction reduction d of the two opposite first convex parts when the two opposite second convex parts are in welding friction 1 ；
S22, adjusting a moving end of the inertia friction welding machine to enable the displacement of the rotor blade disc on the moving end moving towards the direction of the rotor blade disc on the rotating end to be L+d 1 And + (0.02-0.05 mm), wherein L is the initial spacing between the two opposite first protrusions before the moving end moves.
10. An aircraft engine, characterized in that it comprises a rotor blade disc according to any one of claims 1-6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210079122.9A CN116517637A (en) | 2022-01-24 | 2022-01-24 | Rotor disk, rotor assembly, method for manufacturing rotor disk and rotor assembly, and aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210079122.9A CN116517637A (en) | 2022-01-24 | 2022-01-24 | Rotor disk, rotor assembly, method for manufacturing rotor disk and rotor assembly, and aeroengine |
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| Publication Number | Publication Date |
|---|---|
| CN116517637A true CN116517637A (en) | 2023-08-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210079122.9A Pending CN116517637A (en) | 2022-01-24 | 2022-01-24 | Rotor disk, rotor assembly, method for manufacturing rotor disk and rotor assembly, and aeroengine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117722235A (en) * | 2024-02-18 | 2024-03-19 | 中国航发四川燃气涡轮研究院 | Double-radial-plate turbine disc |
-
2022
- 2022-01-24 CN CN202210079122.9A patent/CN116517637A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117722235A (en) * | 2024-02-18 | 2024-03-19 | 中国航发四川燃气涡轮研究院 | Double-radial-plate turbine disc |
| CN117722235B (en) * | 2024-02-18 | 2024-05-17 | 中国航发四川燃气涡轮研究院 | Double-radial-plate turbine disc |
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