Rotor blisk, rotor assembly, and method of manufacturing the same, and aircraft engine

Abstract

The application discloses a rotor disc, a rotor assembly and a manufacturing method thereof and an aero-engine. The rotor disc is used for constituting the rotor assembly of the engine. The rotor disc comprises a disc body. The disc body has a first side part opposite to an adjacent rotor disc on the rotor assembly. An outer peripheral part of the first side part has a first protruding part and a second protruding part for friction welding with the adjacent rotor disc. The second protruding part is close to an outer edge of the disc body relative to the first protruding part. The application can reduce or even eliminate the disc core deviation caused by the friction bending moment when the two rotor discs are subjected to inertia friction welding, and finally reduce the disc core deformation of the rotor disc, so that the axial precision deviation and the disc core deformation deviation of the rotor disc after welding are prevented from seriously affecting the size precision and dynamic balance of the whole part after multiple superpositions.

Description

Technical Field

[0001] This invention relates to a rotor bladed disk, a rotor assembly, a method for manufacturing the same, and an aero-engine. Background Technology

[0002] With advancements in aero-engine technology, high-pressure compressors and high-pressure turbine rotor assemblies in aero-engines have adopted inertial friction welding (IFW) technology using novel high-temperature alloys such as powder metallurgy. Compared to traditional electron beam welding, IFW, as an advanced welding process, produces a forged weld structure, offering advantages such as superior joint performance, high material utilization, and environmental friendliness. It is currently the most feasible method for welding dissimilar materials and joining advanced high-temperature alloys like powder metallurgy. To further improve turbine efficiency and reliability, advanced aero-engines demand increasingly higher dimensional accuracy in rotor assemblies. Currently, the dimensional accuracy of IFW rotor assemblies in aero-engines is mainly reflected in the axial shrinkage accuracy and post-weld disc deformation.

[0003] The aero-engine rotor assembly is an integral structure composed of multi-stage bladed disks. With the continuous improvement of aero-engine performance indicators, higher requirements are placed on the overall precision and welding quality of the rotor assembly. Especially for multi-stage disk welded assemblies, after multiple welding processes, the cumulative effects of post-weld axial precision deviations and disk center deformation offsets can severely affect the dimensional accuracy and dynamic balance of the entire component. Post-weld disk center deformation in aero-engine rotor assemblies mainly manifests as flexural deformation of the compressor disk or turbine disk flanges after welding, exhibiting a conical deformation (e.g., ...). Figure 1 As shown in the figure, this causes changes in the center-to-center distance of the disc and exceeds the overall dynamic balance of the rotor assembly, resulting in abnormal vibrations affecting the engine. Summary of the Invention

[0004] The technical problem to be solved by the present invention is that the rotor blade disk in the rotor assembly of the aero-engine is prone to core deformation after being welded by inertial friction welding in the prior art. The present invention provides a rotor blade disk, a rotor assembly, a method for manufacturing the same, and an aero-engine.

[0005] The present invention solves the above-mentioned technical problems through the following technical solution:

[0006] The present invention provides a rotor disk for constituting a rotor assembly of an engine. The rotor disk includes a disk body having a first side portion opposite to an adjacent rotor disk on the rotor assembly. The outer periphery of the first side portion has a first protrusion and a second protrusion for friction welding with the adjacent rotor disk. The second protrusion is closer to the outer edge of the disk body than the first protrusion.

[0007] In this solution, by setting a first protrusion and a second protrusion at different radial positions on the side of the rotor blade disk body, the disk center offset caused by the frictional bending moment generated during the inertial friction welding of the two rotor blade disks can be reduced or even eliminated, and the disk center deformation of the rotor blade disk can be reduced. This avoids the serious impact on the dimensional accuracy and dynamic balance of the entire part of the aero-engine rotor assembly due to the multiple superposition of axial accuracy deviation and disk center deformation offset after rotor blade disk welding, thereby improving the axial accuracy of the aero-engine rotor assembly.

[0008] Preferably, the first protrusion has a first welding friction surface facing the adjacent rotor blade disk, and the second protrusion has a second welding friction surface facing the adjacent rotor blade disk, wherein the first welding friction surface is closer to the adjacent rotor blade disk than the second welding friction surface.

[0009] In this scheme, the first protrusions of the two rotor disks generate friction first, followed by the second protrusions. In the initial friction stage of inertial friction welding, the friction pressure of the first protrusions of the two rotor disks (the friction pressure is generally 1 / 2 to 1 / 4 of the final upsetting pressure) will generate a certain bending moment. At the end of the welding process, the second protrusion begins to rub. At this time, the weld between the second protrusion and the first protrusion is still at a low temperature and has a high yield strength. Therefore, the main friction is concentrated on the second protrusion, which can be regarded as the main load-bearing fulcrum. The direction of the bending moment generated at this time is opposite to the direction of the initial torque, which can compensate for the disk center deformation offset caused by the initial torque, thereby realizing the adjustment of the disk center offset and reducing or even eliminating the disk center deformation of the rotor disk.

[0010] Preferably, the first protrusion is a ring structure, and the first protrusion has the same axis as the bladed disk body.

[0011] In this solution, the above structure ensures the robustness of the welded connection between the two rotor blade disks.

[0012] Preferably, the second protrusion is a ring structure, and the second protrusion has the same axis as the bladed disk body.

[0013] In this solution, the above structure is adopted to further improve the robustness of the welded connection between the two rotor disks. At the same time, it ensures that the two second protrusions are always in frictional contact at the end of the welding process, so that the remaining energy of the flywheel of the inertial friction welding machine is completely consumed by the second protrusions, which helps to reduce the deformation of the rotor disk center.

[0014] Preferably, there are multiple first protrusions and / or second protrusions, and the multiple first protrusions and / or second protrusions are spaced apart along the circumferential direction of the bladed disk body.

[0015] Preferably, along the radial direction of the bladed disk body, the thickness of the bosses of the first protrusion and the second protrusion is h1, and the distance between the first protrusion and the second protrusion is h2, wherein: F is the upsetting pressure of friction welding, σ is the yield strength of the rotor blade disk material at the welding temperature, and R is the inner diameter of the first protrusion.

[0016] In this design, the boss thickness h1 of the first and second protrusions is mainly determined by the amount of remaining energy in the flywheel (i.e., the instability of the remaining energy). When the possible remaining energy is large, a suitable boss thickness h1 should be selected to ensure the complete consumption of the remaining energy. The distance h2 between the first and second protrusions is mainly determined by the bending moment generated by the clamps holding the rotor disk. When the bending moment is large, a larger distance h2 should be used to balance the torque. The above relationship between the boss thickness h1 of the first and second protrusions and the distance h2 between the first and second protrusions ensures that when the remaining energy of the flywheel is completely consumed by the first or second protrusion, the weld of the first and second protrusions has synchronous frictional bearing until the final welding is completed, thereby ensuring the axial accuracy of the rotor disk welding and effectively avoiding disk core deformation.

[0017] The present invention provides a rotor assembly comprising a plurality of rotor blades as described above, wherein the first protrusion and the second protrusion corresponding to two adjacent rotor blades are fixed by friction welding.

[0018] In this scheme, the rotor assembly using the aforementioned rotor blade disk has a small change in the center-to-center distance of the rotor blade disk, and the overall dynamic balance of the rotor assembly is good, which will not cause abnormal vibrations affecting the engine, and further improves the turbine efficiency and reliability of the aero-engine.

[0019] This invention provides a method for manufacturing a rotor assembly, wherein the rotor assembly is the aforementioned rotor assembly, and the manufacturing method includes the following steps:

[0020] S1. Install the two rotor blades on the rotating end and the moving end of the inertial friction welding machine, respectively;

[0021] S2. Adjust the displacement of the rotor blade disk on the moving end so that the protrusion that is later to be friction welded in the first and second protrusions of the two rotor blade disks is axially displaced by 0.02 to 0.05 mm after friction welding.

[0022] S3. Start the inertia friction welding machine and weld the two rotor blades;

[0023] S4. Repeat steps S1-S3 to obtain the rotor bladed disk assembly, and then assemble the rotor bladed disk assembly with other components of the rotor assembly to obtain the rotor assembly.

[0024] In this scheme, the flywheel's remaining rotational inertia is lower before the friction welding occurs on the protrusions that are friction welded later in the first and second protrusions. The weld of the protrusion that is friction welded earlier is in a plastically softened state after friction, while the protrusion that is friction welded later is still in the initial friction state as it has just entered the friction stage. The main area of ​​action of the flywheel's remaining energy shifts from the weld area to the friction area of ​​the protrusion that is friction welded later. Because the protrusion that is friction welded later is in the initial friction state, the axial shortening of the protrusion that is friction welded later changes very little. By causing the two rotor blades to undergo friction welding on the protrusions that are friction welded later, and then axially displacing them by 0.02 to 0.05 mm, when all the remaining energy of the flywheel is consumed by the protrusion that is friction welded later, the protrusion that is friction welded later completes the welding after 0.02 to 0.05 mm of wear, thus ensuring the axial accuracy of the welding.

[0025] Preferably, in step S2, the two opposing first protrusions first undergo friction welding, and the two opposing second protrusions then undergo friction welding. Step S2 further includes the following steps:

[0026] S21. Determine the axial frictional shortening amount d1 of the two opposite first protrusions during the welding friction of the two opposite second protrusions;

[0027] S22. Adjust the moving end of the inertial friction welding machine so that the displacement of the rotor blade disk on the moving end toward the rotor blade disk on the rotating end is L+d1+(0.02~0.05mm), where L is the initial distance between the two opposing first protrusions before the moving end moves.

[0028] The present invention provides an aircraft engine, the aircraft engine comprising a rotor disk as described above.

[0029] The positive and progressive effects of this invention are as follows: By setting a first protrusion and a second protrusion at different radial positions on the side of the rotor blade disk body, this invention can reduce or even eliminate the disk center offset caused by the frictional bending moment generated during the inertial friction welding of the two rotor blade disks, and ultimately reduce the disk center deformation of the rotor blade disk. This avoids the serious impact on the dimensional accuracy and dynamic balance of the entire part of the aero-engine rotor assembly due to the multiple superposition of axial accuracy deviation and disk center deformation offset after rotor blade disk welding, thereby improving the axial accuracy of the aero-engine rotor assembly. Attached Figure Description

[0030] Figure 1This is a schematic diagram of the deformation and displacement of the rotor disk center after welding in the rotor assembly of an aero-engine in the prior art.

[0031] Figure 2 This is a schematic diagram showing the changes of various parameters at different stages during the inertial friction welding process of a rotor bladed disk in the existing technology.

[0032] Figure 3 This is a schematic diagram of the clamping of a rotor bladed disk in an inertial friction welding machine in the prior art.

[0033] Figure 4 This is a schematic diagram of the bending moment experienced by a rotor blade disk during inertial friction welding in the prior art.

[0034] Figure 5 This is a schematic diagram of the structure of the rotor assembly before welding of the two rotor blades in a preferred embodiment of the present invention.

[0035] Figure 6 for Figure 5 A schematic diagram of the partial structure at point A in the middle.

[0036] Figure 7 This is a diagram showing the stress state of the two rotor blades during the inertial friction welding process in this invention.

[0037] Explanation of reference numerals in the attached figures:

[0038] Rotor blade disk 100

[0039] First protrusion 101

[0040] Second protrusion 102

[0041] Fixture 200 Detailed Implementation

[0042] The present invention will be described more clearly and completely below by way of embodiments and in conjunction with the accompanying drawings, but the present invention is not limited to the scope of the embodiments thereon.

[0043] Traditional inertial friction welding involves a weld seam undergoing axial shortening due to frictional heat generated by rotational inertia and frictional pressure, ultimately completed under upsetting force. The entire axial shortening process is uncontrollable, and the welding process is as follows: Figure 2 As shown.

[0044] like Figure 3 The diagram shows the clamping of the rotor disk 100 in an inertial friction welding machine in the prior art. Due to design accuracy requirements, the side of the tenon on the outer edge of the rotor disk 100 (or turbine disk) is often used as the clamping reference surface of the fixture 200. Since the side of the tenon is the reference surface, it is preferred as the positioning surface of the fixture 200. However, this positioning clamping inevitably leads to bending moment, such as... Figure 4As shown. During the welding process, because the force direction of the fixture 200 is not on the same horizontal plane as the weld direction, the part is subjected to a bending moment of magnitude Γ. This bending moment Γ is proportional to the applied frictional force F and the horizontal distance l, i.e., Γ = F * l. Under the action of this bending moment, the weld will have two consequences: 1) The weld interface is subjected to uneven stress, with a large force on the outside and a small force on the inside, resulting in a large shortening on the outside and a small contraction on the inside. Under the action of uneven deformation, there is a large stress inside the weld, causing the center of the rotor disk 100 to undergo conical deformation; 2) Under the action of the bending moment, the part forms a "seesaw" effect with the weld as the fulcrum, causing the center of the rotor disk 100 to shift. Both of these consequences will lead to the center of the rotor disk 100 shifting. Figure 1 The disk center deformation and offset are shown.

[0045] like Figure 5 and Figure 6 As shown, to avoid the phenomenon of disk center deformation and displacement during the welding process of the rotor disk 100, this embodiment of the invention provides a rotor disk 100 for constituting a rotor assembly of an engine. The rotor disk 100 includes a disk body, the disk body having a first side portion opposite to an adjacent rotor disk 100 on the rotor assembly, the outer periphery of the first side portion having a first protrusion 101 and a second protrusion 102 for friction welding with the adjacent rotor disk 100, the second protrusion 102 being closer to the outer edge of the disk body relative to the first protrusion 101.

[0046] By providing a first protrusion 101 and a second protrusion 102 at different radial positions on the side of the rotor disk 100, the disk center offset caused by the frictional bending moment generated during the inertial friction welding of the two rotor disks 100 can be reduced or even eliminated, and the disk center deformation of the rotor disk 100 can be reduced. This avoids the serious impact on the dimensional accuracy and dynamic balance of the entire part of the aero-engine rotor assembly due to the multiple superposition of axial accuracy deviation and disk center deformation offset after the rotor disk 100 is welded, thereby improving the axial accuracy of the aero-engine rotor assembly.

[0047] Figure 5 and Figure 6Only two protrusions (i.e., the first protrusion 101 and the second protrusion 102) are shown on one side of the rotor disk 100. Those skilled in the art will understand that the rotor assembly has multiple rotor disks 100. Except for the two rotor disks 100 located at the outermost end of the rotor assembly, which only require welding fixation on one side, all other rotor disks 100 need to be welded and fixed to the rotor disks 100 on both sides. Therefore, the two opposite sides of the rotor disk 100 each have a first protrusion 101 and a second protrusion 102 that are welded and fixed to the other rotor disks 100. The area between the first protrusion 101 and the second protrusion 102 can serve as a clamping portion for the clamp 200. Of course, the two sides of the two rotor disks 100 located at the outermost end of the rotor assembly can also each have a first protrusion 101 and a second protrusion 102.

[0048] In this embodiment, the first protrusion 101 has a first welding friction surface facing the adjacent rotor disk 100, and the second protrusion 102 has a second welding friction surface facing the adjacent rotor disk 100. The first welding friction surface is closer to the adjacent rotor disk 100 than the second welding friction surface.

[0049] In this embodiment, the first protrusion 101 of the two rotor disks 100 generates friction first, followed by the second protrusion 102. In the initial friction stage of inertial friction welding, the friction pressure of the first protrusion 101 of the two rotor disks 100 (the friction pressure is generally 1 / 2 to 1 / 4 of the final upsetting pressure) will generate a certain bending moment. At the end of the welding process, the second protrusion 102 begins to rub. At this time, the weld between the second protrusion 102 and the first protrusion 101 is still at a low temperature and has a high yield strength. Therefore, the main friction is concentrated on the second protrusion 102. The second protrusion 102 can be regarded as the main load-bearing fulcrum. The direction of the bending moment generated at this time is opposite to the direction of the initial torque, which can compensate for the disk center deformation offset caused by the initial torque, thereby realizing the adjustment of the disk center offset and reducing or even eliminating the disk center deformation of the rotor disk 100.

[0050] In other embodiments, the second protrusions 102 of the two rotor blade disks 100 generate friction first, and the first protrusions 101 generate friction later. Please refer to the above description for the specific process, which will not be repeated here.

[0051] In this embodiment, the first protrusion 101 is a ring structure, and the first protrusion 101 has the same axis as the bladed disk body. This structure ensures the robustness of the welded connection between the two rotor bladed disks 100.

[0052] In this embodiment, the second protrusion 102 is a ring structure, and the second protrusion 102 has the same axis as the impeller body. The above-described structure of the second protrusion 102 further improves the robustness of the welded connection between the two rotor impellers 100. Simultaneously, it ensures that the two second protrusions 102 remain in frictional contact at the end of the welding process, allowing all the remaining energy of the flywheel in the inertial friction welding machine to be consumed by the second protrusions 102, thus helping to reduce the deformation of the rotor impeller 100's center.

[0053] In other embodiments, there are multiple first protrusions 101 and / or second protrusions 102, and the multiple first protrusions 101 and / or second protrusions 102 are spaced apart along the circumferential direction of the impeller body. For example, the first protrusion 101 is a plurality of arc blocks with the same structure, each arc block forming an annular structure with the same axis as the rotor impeller 100, and there are gaps between the arc blocks.

[0054] In this embodiment, along the radial direction of the bladed disk body, the thickness of the boss of the first protrusion 101 and the second protrusion 102 is h1, and the distance between the first protrusion 101 and the second protrusion 102 is h2, wherein: In this formula, F is the upsetting pressure of friction welding, σ is the yield strength of the rotor blade disk 100 material at the welding temperature, and R is the inner diameter of the first protrusion 101.

[0055] In this design, the boss thickness h1 of the first protrusion 101 and the second protrusion 102 is mainly determined by the amount of remaining energy of the flywheel (i.e., the instability of the remaining energy). When the possible remaining energy is large, a suitable boss thickness h1 should be selected to ensure the complete consumption of the remaining energy. The distance h2 between the first protrusion 101 and the second protrusion 102 is mainly determined by the bending moment generated by the clamp 200 that holds the rotor disk 100. When the bending moment is large, a larger distance h2 should be used to balance the torque. The above relationship between the boss thickness h1 of the first protrusion 101 and the second protrusion 102 and the distance h2 between the first protrusion 101 and the second protrusion 102 can ensure that when the remaining energy of the flywheel is completely consumed by the first protrusion 101 or the second protrusion 102, the weld of the first protrusion 101 and the second protrusion 102 has synchronous frictional bearing force until the final welding is completed, thereby ensuring the axial accuracy of the rotor disk 100 welding and effectively avoiding disk core deformation.

[0056] This invention also provides a rotor assembly comprising multiple rotor bladed disks 100 as described above. The first protrusion 101 and the second protrusion 102 of two adjacent rotor bladed disks 100 are fixed together by friction welding. Using the rotor assembly with the aforementioned rotor bladed disks 100 results in minimal variation in the center-to-center distance between the disks, good overall dynamic balance of the rotor assembly, and prevents abnormal vibrations affecting the engine, further improving the turbine efficiency and reliability of the aero-engine.

[0057] This invention also provides a method for manufacturing the above-mentioned rotor assembly, comprising the following steps:

[0058] S1. Install the two rotor blade disks 100 on the rotating end and the moving end of the inertial friction welding machine, respectively;

[0059] S2. Adjust the displacement of the rotor blade disk 100 on the moving end so that the protrusion of the first protrusion 101 and the second protrusion 102 of the two rotor blade disks 100 that are relatively late to be friction welded is friction welded and then axially displaced by 0.02 to 0.05 mm.

[0060] S3. Start the inertial friction welding machine and weld two rotor blades 100mm apart.

[0061] S4. Repeat steps S1-S3 to obtain rotor blade disk 100 assembly, and then assemble rotor blade disk 100 assembly with other parts of rotor assembly to obtain rotor assembly.

[0062] In the aforementioned rotor assembly manufacturing method, before the friction welding occurs on the protrusions of the first protrusion 101 and the second protrusion 102, the remaining rotational inertia of the flywheel is low. The weld of the protrusion that undergoes friction welding earlier is in a plastically softened state after friction, while the protrusion that undergoes friction welding later is still in the initial friction state as it has just entered the friction stage. The main area of ​​action of the flywheel's remaining energy shifts from the weld area to the friction area of ​​the protrusion that undergoes friction welding later. Since the protrusion that undergoes friction welding later is in the initial friction state, the axial shortening of the protrusion that undergoes friction welding later changes very little. By causing the two rotor blade disks 100 to undergo friction welding on the protrusions that undergo friction welding later, and then axially displacing them by 0.02 to 0.05 mm, when all the remaining energy of the flywheel is consumed by the protrusion that undergoes friction welding later, the protrusion that undergoes friction welding later completes the welding after 0.02 to 0.05 mm of wear, thereby ensuring the axial accuracy of the welding.

[0063] In this embodiment, taking the example of two opposing first protrusions 101 undergoing friction welding first, followed by two opposing second protrusions 102 undergoing friction welding, step S2 further includes the following steps:

[0064] S21. Determine the axial frictional shortening d1 of the two opposing first protrusions 101 during the welding friction of the two opposing second protrusions 102;

[0065] S22. Adjust the moving end of the inertial friction welding machine so that the displacement of the rotor blade disk 100 on the moving end toward the rotor blade disk 100 on the rotating end is L+d1+(0.02~0.05mm), where L is the initial distance between the two opposite first protrusions 101 before the moving end moves.

[0066] Assuming that after the two rotor disks 100 are welded, the total design shortening of the first protrusion is d0, and the distance between the two second protrusions before the two opposing first protrusions make contact by welding friction is d1, then d1 = d0 - (0.02~0.05mm). d1 is 0.02~0.05mm smaller than d0, which is used to consume the remaining flywheel energy. The specific difference is related to the required axial accuracy. When the required axial accuracy of each rotor disk 100 in the rotor assembly is large, the difference from the design shortening d0 should be minimized. It is also closely related to the thickness h1 of the second protrusion. The thickness h1 of the second protrusion is mainly determined by the amount of remaining flywheel energy (i.e., the instability of remaining energy). When the possible remaining energy is large, since d1 is close to d0, a larger thickness h1 should be chosen for the second protrusion. The weld distance h2 between the second protrusion and the first protrusion is mainly determined by the bending moment Γ generated by the fixture 200. When the bending moment is large, a larger distance h2 should be used to balance the torque.

[0067] The manufacturing method of the rotor assembly of this invention adds a secondary friction process through a second protrusion to the traditional inertial friction welding process: when the axial shortening of the first protrusion reaches d1, the second protrusions of the two rotor disks 100 come into contact with each other. At this time, the difference between the shortening amount d1 and the designed shortening amount d0 of the first protrusion is approximately 0.02-0.05 mm. At this time, the remaining rotational inertia of the flywheel is low, and the weld of the first protrusion is in a plastically softened state after friction, while the second protrusion is still in the initial friction state because it has just entered the friction stage. The main area of ​​action of the flywheel's remaining energy shifts from the weld area of ​​the first protrusion to the area of ​​the second protrusion. Figure 2 It can be seen that the second protrusion has a very small change in axial shortening under the initial friction state. Therefore, when the remaining energy of the flywheel is completely consumed by the boss, the second protrusion is welded after 0.02 to 0.05 mm of wear, thus ensuring the axial accuracy of the welding of the two rotor blade disks 100.

[0068] like Figure 2 , Figure 4 and Figure 7As shown, the rotor disk 100 in this embodiment experiences the same stress state during the initial friction stage as in a conventional welding process. At this time, the friction pressure F (generally 1 / 2 to 1 / 4 of the final upsetting pressure) generates a certain bending moment. Towards the end of the welding process, the second protrusion on the outer side begins to rub. At this point, the weld of the second protrusion is still at a lower temperature than that of the first protrusion, resulting in a higher yield strength. Therefore, the main friction is concentrated on the second protrusion, which can be considered the main load-bearing point. The bending moment generated by the rotor disk 100 at this time is opposite to the direction of the initial torque, which can compensate for the disk center deformation offset caused by the initial torque. As the friction of the second protrusion softens due to heat and the deformation of the disk center compensates for the shift, the normal friction forces F1 and F2 of the weld of the first protrusion gradually approach each other. At this point, the upsetting force F, the normal friction force F1 of the weld of the first protrusion, and the normal friction force F2 of the second protrusion form a simply supported structure. At this point, the disk center of the rotor disk 100 does not bear a significant bending moment. Subsequently, the welds of the second protrusion and the first protrusion bear friction forces synchronously, and finally the welding is completed, realizing the adjustment of the disk center shift.

[0069] This invention also provides an aero-engine, which includes the rotor disk 100 or rotor assembly described above.

[0070] While specific embodiments of the present invention have been described above, those skilled in the art should understand that these are merely illustrative examples, and the scope of protection of the present invention is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of the present invention, but all such changes and modifications fall within the scope of protection of the present invention.

Claims

1. A rotor disk for constituting a rotor assembly of an engine, characterized in that, The rotor disk includes a disk body, the disk body having a first side portion opposite to an adjacent rotor disk on the rotor assembly, the outer periphery of the first side portion having a first protrusion and a second protrusion for friction welding with the adjacent rotor disk, the second protrusion being closer to the outer edge of the disk body relative to the first protrusion. The first protrusion has a first welding friction surface facing the adjacent rotor blade disk, and the second protrusion has a second welding friction surface facing the adjacent rotor blade disk. The first welding friction surface is closer to the adjacent rotor blade disk than the second welding friction surface. Along the radial direction of the bladed disk body, the thickness of the bosses of the first protrusion and the second protrusion is h1, and the distance between the first protrusion and the second protrusion is h2, wherein: F is the upsetting pressure of friction welding, σ is the yield strength of the rotor blade disk material at the welding temperature, and R is the inner diameter of the first protrusion.

2. The rotor bladed disk as described in claim 1, characterized in that, The first protrusion is a ring structure, and the first protrusion has the same axis as the bladed disk body.

3. The rotor bladed disk as described in claim 2, characterized in that, The second protrusion is a ring structure and has the same axis as the bladed disk body.

4. The rotor bladed disk as described in claim 1, characterized in that, The first protrusion and / or the second protrusion are multiple, and the multiple first protrusions and / or the second protrusions are spaced apart along the circumferential direction of the bladed disk body.

5. A rotor assembly, characterized in that, The rotor assembly includes a plurality of rotor blades as described in any one of claims 1-4, wherein the first protrusion and the second protrusion corresponding to two adjacent rotor blades are fixed by friction welding.

6. A method for manufacturing a rotor assembly, characterized in that, The rotor assembly is the rotor assembly according to claim 5, and the manufacturing method includes the following steps: S1. Install the two rotor blades on the rotating end and the moving end of the inertial friction welding machine, respectively; S2. Adjust the displacement of the rotor blade disk on the moving end so that the protrusion that is later to be friction welded in the first and second protrusions of the two rotor blade disks is axially displaced by 0.02 to 0.05 mm after friction welding. S3. Start the inertia friction welding machine and weld the two rotor blades; S4. Repeat steps S1-S3 to obtain the rotor bladed disk assembly, and then assemble the rotor bladed disk assembly with other components of the rotor assembly to obtain the rotor assembly.

7. The method for manufacturing the rotor assembly as described in claim 6, characterized in that, In step S2, the two opposing first protrusions first undergo friction welding, followed by the two opposing second protrusions undergoing friction welding. Step S2 also includes the following steps: S21. Determine the axial frictional shortening amount d1 of the two opposite first protrusions during the welding friction of the two opposite second protrusions; S22. Adjust the moving end of the inertial friction welding machine so that the displacement of the rotor blade disk on the moving end toward the rotor blade disk on the rotating end is L+d1+(0.02~0.05mm), where L is the initial distance between the two opposing first protrusions before the moving end moves.

8. An aircraft engine, characterized in that, The aero-engine includes a rotor disk as described in any one of claims 1-4.

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