Tooling and assembly method for an aeroengine combustion generator rotor

Abstract

This invention discloses a tooling and assembly method for an aero-engine combustion generator rotor. The combustion generator rotor includes a first part and a second part along the axial direction, with the end of the second part being a axial end. The tooling includes: a base for serving as a bottom support; a first positioning component disposed on the base for axial and radial positioning engagement with the end of the first part of the combustion generator rotor; a second positioning component disposed on the base for radial positioning of the axial end of the combustion generator rotor and for applying axial force to the axial end of the generator rotor; and a comparison component disposed on the base for verifying the coaxiality of the first and second positioning components and / or for verifying the coaxiality of the first and second parts of the combustion generator rotor.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and in particular, to a tooling for an aero-engine combustion generator rotor. Furthermore, this invention also relates to a combustion generator rotor assembly method including the aforementioned tooling for an aero-engine combustion generator rotor. Background Technology

[0002] The newly developed aero-engine combustion generator rotor is a critical component, characterized by high machining precision, high assembly precision, and high unit value. One end of the combustion generator rotor has a spline structure, and the other end has a free-end optical shaft structure. The middle part of the rotor has a hole-shaft clearance fit structure. In order to accurately adjust the clearance fit precision (i.e., coaxiality requirement), the half of the component near the optical shaft end needs to meet both rotation and positioning requirements during the assembly process in order to adjust to the required coaxiality assembly requirements. Traditional manual assembly can obviously no longer meet the existing assembly requirements.

[0003] In summary, existing assembly tooling and assembly methods have at least the following problems: 1) The middle part of the rotor is a hole-shaft clearance fit structure. In order to accurately adjust the clearance fit accuracy (i.e., coaxiality requirement), the half of the component near the optical shaft end needs to meet both rotation and positioning requirements during the assembly process in order to adjust the required coaxiality assembly requirements. Traditional manual assembly can obviously no longer meet the existing assembly requirements and the ever-increasing production requirements. 2) The cost of a single combustion generator rotor is relatively high, and manual assembly without auxiliary tooling is prone to risks such as tipping over or scratching. Summary of the Invention

[0004] This invention provides a tooling and assembly method for an aero-engine combustion generator rotor, to solve the technical problems of low efficiency, high strength, and easy damage of combustion generator rotor tooling that rely on manual assembly in the prior art.

[0005] According to one aspect of the present invention, a tooling for an aircraft engine combustion generator rotor is provided, the combustion generator rotor comprising a first portion and a second portion along the axial direction, the end of the second portion being a smooth shaft end, the tooling comprising: The base serves as a bottom support; The first positioning component is disposed on the base and is used for axial positioning and radial positioning engagement with the end of the first part of the combustion generator rotor; The second positioning component is disposed on the base and is used for radial positioning of the optical axis end of the combustion generator rotor and for applying axial force to the optical axis end of the generator rotor; A comparison component, disposed on the base, is used to verify the coaxiality of the first positioning component and the second positioning component and / or to verify the coaxiality of the first part and the second part of the combustion generator rotor.

[0006] As a further improvement to the above technical solution, the first positioning component includes a positioning seat disposed on the base, and the top of the positioning seat is provided with an internal spline for engaging with the external spline of the end of the first part of the combustion generator rotor.

[0007] As a further improvement to the above technical solution, the second positioning component includes a first support rod vertically disposed on the base, a rocker arm assembly disposed on the top of the first support rod, and a spindle vertically disposed on the rocker arm assembly. The circumferential dimension of the spindle gradually increases from the bottom to the top, and the minimum radial dimension of the spindle is smaller than the inner diameter of the optical axis end of the combustion generator rotor.

[0008] As a further improvement to the above technical solution, the rocker arm assembly includes a fixing block sleeved on the first support rod, and a first limiting mechanism is provided on the fixing block to limit the circumferential angle of the fixing block relative to the first support rod; a second support rod for mounting the mandrel is connected to the fixing block in the horizontal direction.

[0009] As a further improvement to the above technical solution, a limiting mating surface is provided on one side of the second support rod, and the fixing block is provided with a first mounting hole that matches the cross-sectional shape of the second support rod to limit the circumferential position of the second support rod.

[0010] As a further improvement to the above technical solution, the second positioning component also includes an L-shaped connecting block. The first right-angled side of the connecting block has a second mounting hole that matches the cross-sectional shape of the second support rod. The free end of the mandrel passes through the second right-angled side of the connecting block and is axially limited by a nut. The distance between the second mounting hole and the second right-angled side is greater than the height of the free end of the mandrel extending from the second right-angled side.

[0011] As a further improvement to the above technical solution, the rocker arm assembly includes a lifting mechanism disposed between the rocker arm assembly and the first support rod.

[0012] As a further improvement to the above technical solution, the first support rod has a threaded section, the lifting mechanism includes a positioning wheel threadedly connected to the first support rod, and the fixing block is sleeved on the first support rod and located on the positioning wheel.

[0013] As a further improvement to the above technical solution, the tooling also includes a movable component disposed on the base, for moving the tooling based on the movable component.

[0014] According to another aspect of the present invention, a method for assembling a combustion generator rotor is also provided, comprising the tooling described above for an aero-engine combustion generator rotor, the assembly method comprising: S1. Loosen the fastener and adjust the position of the first positioning component to be coaxial with the second positioning component; S2. Position the first part of the combustion generator rotor in conjunction with the first positioning assembly; S3. Install the second part of the combustion generator rotor onto the first part of the combustion generator rotor, and the second positioning assembly applies an axial clamping force to the second part; S4. Rotate the second part of the combustion generator rotor to adjust the coaxiality between the second part and the first part of the combustion generator; S5. Lock after adjustment.

[0015] The present invention has the following beneficial effects: This fixture uses a base as the bottom structural support, and a first positioning component and a second positioning component are respectively installed on the base. The first positioning component cooperates with the end of the first part of the combustion generator rotor to perform axial and radial positioning, fixing the combustion generator rotor to the base. This allows the second part with the optical axis end to be installed after the first part of the combustion generator rotor is fixed, avoiding the problems of tilting and scratching that are easily caused by manual assembly. Based on the positioning function of the second positioning component, the first part is rotated and adjusted, thereby adjusting the coaxiality of the first and second parts. The second positioning component then radially positions and fixes the optical axis end of the combustion generator rotor and applies axial force to achieve positioning and clamping, effectively shortening the rotor assembly time, improving assembly efficiency, and ensuring coaxiality accuracy, which can effectively meet the production requirements of aero-engines. On the other hand, the coaxiality can be checked by comparing the components before and / or after assembly. By checking the coaxiality of the first and second positioning components, the coaxiality between the first and second parts of the rotor after positioning and assembly can be guaranteed. The coaxiality of the first and second parts can also be checked and adjusted directly during the assembly process, effectively ensuring the coaxiality accuracy of the combustion generator rotor.

[0016] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0017] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1This is a front view of the tooling in use according to a preferred embodiment of the present invention; Figure 2 This is a side view of the tooling in use according to a preferred embodiment of the present invention; Figure 3 This is a top view of the tooling in use according to a preferred embodiment of the present invention; Figure 4 This is a schematic diagram of the rocker arm assembly according to a preferred embodiment of the present invention. Figure 1 ; Figure 5 This is a schematic diagram of the rocker arm assembly according to a preferred embodiment of the present invention. Figure 2 ; Figure 6 This is a schematic diagram of the positioning block according to a preferred embodiment of the present invention. Figure 1 ; Figure 7 This is a schematic diagram of the positioning block according to a preferred embodiment of the present invention. Figure 2 ; Figure 8 This is a schematic diagram of the mandrel structure according to a preferred embodiment of the present invention; Figure 9 This is a schematic diagram of the positioning wheel according to a preferred embodiment of the present invention.

[0018] Legend: 100. Base; 200. First positioning component; 210. Positioning seat; 211. Fixing bolt; 300. Second positioning component; 310. First support rod; 320. Fixing block; 321. First mounting hole; 322. Locking bolt; 330. Second support rod; 331. Limiting mating surface; 340. Mandrel; 350. Connecting block; 351. Second mounting hole; 360. Locking screw; 370. Positioning wheel; 400. Combustion generator; 410. First part; 420. Second part; 500. Frame; 510. Traveling wheel; 520. Push rod; 530. Fixture box. Detailed Implementation

[0019] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.

[0020] Figure 1 This is a front view of the tooling in use according to a preferred embodiment of the present invention; Figure 2 This is a side view of the tooling in use according to a preferred embodiment of the present invention; Figure 3 This is a top view of the tooling in use according to a preferred embodiment of the present invention; Figure 4 This is a schematic diagram of the rocker arm assembly according to a preferred embodiment of the present invention. Figure 1 ; Figure 5 This is a schematic diagram of the rocker arm assembly according to a preferred embodiment of the present invention. Figure 2 ; Figure 6 This is a schematic diagram of the positioning block according to a preferred embodiment of the present invention. Figure 1 ; Figure 7 This is a schematic diagram of the positioning block according to a preferred embodiment of the present invention. Figure 2 ; Figure 8 This is a schematic diagram of the mandrel structure according to a preferred embodiment of the present invention; Figure 9 This is a schematic diagram of the positioning wheel according to a preferred embodiment of the present invention.

[0021] like Figures 1 to 8 As shown, this embodiment describes a tooling for the rotor of an aero-engine combustion generator 400. The combustion generator 400 rotor includes a first part 410 and a second part 420 along the axial direction. The end of the second part 420 is a smooth shaft end. The tooling includes: Base 100, used as a bottom support; The first positioning component 200 is disposed on the base 100 and is used for axial positioning and radial positioning engagement with the end of the first part 410 of the combustion generator 400 rotor. The second positioning component 300 is disposed on the base 100 and is used for radial positioning of the optical axis end of the combustion generator 400 rotor and for applying axial force to the optical axis end of the generator rotor. A comparison component, mounted on the base 100, is used to check the coaxiality of the first positioning component 200 and the second positioning component 300 and / or to check the coaxiality of the first part 410 and the second part 420 of the rotor of the combustion generator 400.

[0022] In this embodiment, the first part 410 and the second part 420 of the rotor of the combustion generator 400 are only used to refer to the two parts that do not have a sequential relationship. Based on this tooling, the first part 410 is the lower half of the figure and the second part 420 is the upper half of the figure with the optical axis end. The comparison component can be a measuring tool or a reference piece with multiple measuring points. The coaxiality is determined by the spacing between multiple preset points and the reference piece. Understandably, this fixture uses a base 100 as a structural support at the bottom, and a first positioning component 200 and a second positioning component 300 are respectively installed on the base 100. The first positioning component 200 engages with the end of the first part 410 of the combustion generator 400 rotor to perform axial and radial positioning, thus fixing the combustion generator 400 rotor to the base 100. This allows the second part 420 with an optical axis end to be installed after the first part 410 of the combustion generator 400 rotor is fixed, avoiding the problems of tipping over and scratching that are easily caused by manual assembly. Based on the positioning function of the second positioning component 300, the first part 410 is rotated and adjusted, thereby adjusting the coaxiality of the first part 410 and the second part 420. Then, the second positioning component 300 radially positions and fixes the optical axis end of the rotor of the combustion generator 400 and applies axial force to achieve positioning and clamping, which effectively shortens the rotor assembly time, improves assembly efficiency, and effectively guarantees the coaxiality accuracy, thus effectively ensuring the production requirements of aero-engines. On the other hand, the coaxiality can be checked by comparison components before and / or after assembly. By checking the coaxiality of the first positioning component 200 and the second positioning component 300, the coaxiality between the first part 410 and the second part 420 of the rotor after positioning and assembly can be guaranteed. The coaxiality of the first part 410 and the second part 420 can also be directly checked and adjusted during the assembly process, effectively ensuring the coaxiality accuracy of the rotor of the combustion generator 400.

[0023] In some preferred embodiments, the first positioning component 200 includes a positioning seat 210 disposed on the base 100, and the positioning seat 210 is fixed to the base 100 by fixing bolts 211; the top of the positioning seat 210 is provided with an internal spline for engaging with the external spline of the end of the first part 410 of the combustion generator rotor. It can be understood that by setting the positioning seat 210 and setting the internal spline to engage with the external spline of the end of the combustion generator rotor, vertical support of the first part 410 of the combustion generator rotor is achieved, and the upper part is installed in a relatively fixed state, avoiding tilting and workpiece scratches during assembly; at the same time, the upper part can be rotated and positioned simultaneously in a relatively fixed state to meet the coaxiality assembly requirements.

[0024] In some preferred embodiments, the second positioning assembly 300 includes a first support rod 310 vertically disposed on the base 100, a rocker arm assembly disposed on the top of the first support rod 310, and a spindle 340 vertically disposed on the rocker arm assembly. The circumferential dimension of the spindle 340 gradually increases from the bottom to the top, and the minimum radial dimension of the spindle 340 is smaller than the inner diameter of the optical axis end of the rotor of the combustion generator 400. It is understood that the first support rod 310 is located on one side of the positioning seat 210, the rocker arm assembly can swing based on the first support rod 310 as an axis, and the spindle 340 can move along the length of the rocker arm assembly, thereby adjusting the horizontal position of the spindle 340. After the position matches the axial position of the positioning seat 210, the mandrel 340 is locked and fixed, which allows the coaxiality of the first part 410 and the second part 420 of the rotor to be controlled during assembly. The mandrel 340 has a certain taper. After assembly, the mandrel 340 is inserted into the optical shaft end by controlling the lifting and lowering of the rocker arm assembly, thereby applying axial clamping force to clamp and secure the rotor of the combustion generator 400. Based on the fixing method of the mandrel 340, it is only necessary to observe the gap between the mandrel 340 and the inner cavity of the rotor after assembly, and then rotate the second part 420 to make the second part 420 of the rotor rotate circumferentially relative to the first part 410 to adjust the coaxiality. After the adjustment is completed, the locking fixture can complete the clamping and at the same time ensure the coaxiality accuracy of the rotor.

[0025] It should be understood that the spindle 340 or the outer wall of the spindle 340 is made of a material with a certain degree of elasticity, preferably fluoroplastic, to avoid damage to the inner cavity of the rotor shaft end; the free end of the spindle 340 can be provided with a screw that passes through the connecting plate and cooperates with the nut; In some preferred embodiments, the rocker arm assembly includes a fixing block 320 sleeved on the first support rod 310. The fixing block 320 is provided with a first limiting mechanism to limit the circumferential angle of the fixing block 320 relative to the first support rod 310. A second support rod 330 for mounting the spindle 340 is connected to the fixing block 320 in the horizontal direction. Rotating the rocker arm assembly causes the spindle 340 to swing. At the same time, the length position of the spindle 340 on the second support rod 330 can be adjusted, thereby adjusting the horizontal position of the spindle 340. On the other hand, by setting the rocker arm assembly to mount the spindle 340, the rocker arm assembly can be rotated before and after assembly to swing the second support rod 330 to the original mounting position, avoiding interference. It should be noted that the fixing block 320 is a clamping block. The first limiting mechanism includes a locking bolt 322 passing through the clamping block. The locking bolt 322 locks and retracts the clamping block, thereby fixing the circumferential angle and axial position of the clamping block relative to the second support rod 330, thereby fixing the position of the spindle 340. In some preferred embodiments, a limiting mating surface 331 is provided on one side of the second support rod 330, and the fixing block 320 has a first mounting hole 321 that matches the cross-sectional shape of the second support rod 330 to limit the circumferential position of the second support rod 330. It can be understood that the second support rod 330 is a circular rod. By machining the limiting mating surface 331 on the side wall of the second support rod 330, and the shape of the first mounting hole 321 matches its cross-sectional shape, the second support rod 330 can be prevented from rotating circumferentially after passing through the fixing block 320, thereby preventing the mandrel 340 from swinging and keeping the mandrel 340 always vertically arranged.

[0026] In some preferred embodiments, the second positioning component 300 further includes an L-shaped connecting block 350. The first right-angled side of the connecting block 350 has a second mounting hole 351 that matches the cross-sectional shape of the second support rod 330. The free end of the spindle 340 passes through the second right-angled side of the connecting block 350 and is axially limited by a nut, allowing the spindle 340 to rotate circumferentially. The distance between the second mounting hole 351 and the second right-angled side is greater than the height of the free end of the spindle 340 extending from the second right-angled side. It is understood that by setting the L-shaped connecting block 350 to connect the spindle 340 and the second support rod 330 respectively, the connecting block 350 can move along the second support rod 330 based on the second mounting hole 351. A locking screw 360 is provided on the connecting block 350 to limit the movement of the second support rod 330 within the second mounting hole 351. The mating surface 331 is used to fix the connecting block 350 to the position of the second support rod 330. The distance between the second mounting hole 351 and the second right-angled side is greater than the height of the free end of the spindle 340 extending from the second right-angled side. This ensures that the free end of the spindle 340 does not interfere with the second support rod 330 during the movement of the connecting block 350. Through the structure of the connecting block 350 and the above-mentioned connection method, the structure is simplified, ensuring the position adjustment and fixing ability of the spindle 340. At the same time, it ensures that the spindle 340 can rotate circumferentially. During assembly, after the spindle 340 is axially pressed against the optical shaft end, when the second part 420 is rotated circumferentially to adjust the coaxiality, the spindle 340 can rotate synchronously with the second part 420, avoiding rotor damage, ensuring coaxiality accuracy and greatly improving assembly efficiency. Moreover, the overall tooling structure is simplified, resulting in low cost.

[0027] In some preferred embodiments, the rocker arm assembly includes a lifting mechanism disposed between the rocker arm assembly and the first support rod 310. The lifting mechanism controls the rocker arm assembly to rise and fall on the first support rod 310. Based on this, the rocker arm assembly rises and falls, causing the spindle 340 to apply a clamping force to the rotor and the positioning seat 210 to clamp and fix the rotor.

[0028] In some preferred embodiments, the first support rod 310 has a threaded section, and the lifting mechanism includes a positioning wheel 370 threadedly connected to the first support rod 310. The fixing block 320 is sleeved on the first support rod 310 and located on the positioning wheel 370. It can be understood that by setting the first support rod 310 as a screw or a threaded section of a certain length, and threadedly connecting the positioning wheel 370 to the threaded section, the positioning wheel 370 provides vertical support for the fixing block 320. Rotating the positioning wheel 370 causes it to move along the axial direction of the first support rod 310, thereby causing the fixing block 320 on the positioning wheel 370 to rise and fall. This, in turn, drives the spindle 340 to rise and fall via the rocker arm assembly. This lifting mechanism can maintain the circumferential rotation of the fixing block 320, has a simplified structure, and effectively simplifies operation.

[0029] In some embodiments, to ensure the clamping effect, the positioning wheel 370 is rotatably connected to the fixing block 320, so that the positioning wheel 370 can drive the fixing block 320 to rise and fall, ensuring the axial clamping force during clamping.

[0030] In some preferred embodiments, the tooling also includes a movable component disposed on the base 100, which is used to move the tooling based on the movable component. By setting the movable component to support the tooling, on the one hand, it is convenient to transfer and use the tooling, and on the other hand, it can maintain the assembled state after the combustion generator 400 rotor is assembled, and store the rotor at a designated work station or transfer it between work stations in the process. It has mobility, can be transported and stored in other factories, effectively utilizes the space, and has convenience. Specifically, the moving component includes a frame 500, wheels 510 located at the bottom of the frame 500, and a push rod 520 located on one side of the top surface of the frame 500. The base 100 is mounted on the frame 500, and the push rod 520 pushes the frame 500 to move based on the wheels 510. The wheels 510 can be swivel casters or a combination of swivel casters and straight casters. The frame 500 is equipped with a clamp box 530 for matching and replacing according to the model.

[0031] Understandably, a handle is radially provided at the end of the locking screw 360 for tightening and loosening. Similarly, a locking handle is provided on one side of the locking bolt 322 for applying force to lock or loosen the fixing block 320.

[0032] On the other hand, a preferred embodiment of the present invention also provides a method for assembling a combustion generator 400 rotor, which utilizes the aforementioned tooling for an aero-engine combustion generator 400 rotor, and the assembly method includes: S1. Loosen the fasteners and adjust the position of the first positioning component 200 to be coaxial with the second positioning component 300; Specifically, loosen the locking screw 360 and locking bolt 322, move the connecting block 350 and the circumferential rotating fixing block 320 to adjust the position of the spindle 340 to be coaxial with the positioning seat 210, and use the comparison component as a reference during the adjustment process; after adjustment, the locking screw 360 can be locked. S2. Position the first part 410 of the combustion generator 400 rotor in conjunction with the first positioning assembly 200; Specifically, the external spline of the first part 410 of the combustion generator rotor 400 is inserted into the positioning seat 210 and engages with its internal spline to achieve vertical support; S3. Install the second part 420 of the combustion generator 400 rotor onto the first part 410 of the combustion generator 400 rotor, and the second positioning assembly 300 applies an axial clamping force to the second part 420; Specifically, after installing the second part 420, rotate the rocker arm assembly so that the spindle 340 is above the optical axis end of the combustion generator 400, and rotate the positioning handwheel to lower the spindle 340 until it is inserted into the inner wall of the optical axis end. S4. Rotate the second part 420 of the combustion generator 400 rotor to adjust the coaxiality between the second part 420 and the first part 410 of the combustion generator 400; Specifically, adjust the second part 420 by rotating according to the gap between the mandrel 340 and the inner wall of the optical axis until the gap is uniform or there is no gap, so as to ensure coaxiality accuracy. S5. After adjustment, tighten; specifically, tighten all bolts, screws, etc. The overall clamping operation is simple and effectively ensures coaxiality accuracy.

[0033] In the description of this invention, it should be noted that the terms "upper", "lower", "front", "rear", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0034] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0035] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A tooling for an aeroengine combustion generator (400) rotor, the combustion generator (400) rotor comprising in the axial direction a first portion (410) and a second portion (420), the end of said second portion (420) being a lightened end, characterized in that, The tooling includes: The base (100) serves as a bottom support; The first positioning component (200) is disposed on the base (100) and is used for axial positioning and radial positioning engagement with the end of the first part (410) of the combustion generator (400) rotor; The second positioning component (300) is disposed on the base (100) and is used for radial positioning of the optical axis end of the combustion generator (400) rotor and for applying axial force to the optical axis end of the generator rotor; A comparison component, disposed on the base (100), is used to check the coaxiality of the first positioning component (200) and the second positioning component (300) and / or to check the coaxiality of the first part (410) and the second part (420) of the rotor of the combustion generator (400).

2. The tooling for an aeroengine combustion generator (400) rotor according to claim 1, characterized in that, The first positioning component (200) includes a positioning seat (210) disposed on the base (100), the top of the positioning seat (210) having an internal spline for engaging with the external spline of the end of the first part (410) of the combustion generator (400) rotor.

3. The tooling for an aeroengine combustion generator (400) rotor according to claim 1, characterized in that, The second positioning component (300) includes a first support rod (310) vertically disposed on the base (100), a rocker arm assembly disposed on the top of the first support rod (310), and a spindle (340) vertically disposed on the rocker arm assembly. The circumferential dimension of the spindle (340) gradually increases from the bottom to the top, and the minimum radial dimension of the spindle (340) is smaller than the inner diameter of the optical axis end of the rotor of the combustion generator (400).

4. The tooling for an aero-engine combustion generator (400) rotor according to claim 3, characterized in that, The rocker arm assembly includes a fixing block (320) sleeved on the first support rod (310), and a first limiting mechanism is provided on the fixing block (320) to limit the circumferential angle of the fixing block (320) relative to the first support rod (310); a second support rod (330) for mounting the mandrel (340) is connected to the fixing block (320) in the horizontal direction.

5. The tooling for an aero-engine combustion generator (400) rotor according to claim 4, characterized in that, The second support rod (330) has a limiting mating surface (331) on one side, and the fixing block (320) has a first mounting hole (321) that matches the cross-sectional shape of the second support rod (330) to limit the circumferential position of the second support rod (330).

6. The tooling for an aero-engine combustion generator (400) rotor according to claim 5, characterized in that, The second positioning component (300) further includes an L-shaped connecting block (350). The first right-angled side of the connecting block (350) has a second mounting hole (351) that matches the cross-sectional shape of the second support rod (330). The free end of the spindle (340) passes through the second right-angled side of the connecting block (350) and is axially limited by a nut. The distance between the second mounting hole (351) and the second right-angled side is greater than the height of the free end of the spindle (340) extending from the second right-angled side.

7. The tooling for an aero-engine combustion generator (400) rotor according to claim 4, characterized in that, The rocker arm assembly includes a lifting mechanism disposed between the rocker arm assembly and the first support rod (310).

8. The tooling for an aero-engine combustion generator (400) rotor according to claim 7, characterized in that, The first support rod (310) has a threaded section, and the lifting mechanism includes a positioning wheel (370) threadedly connected to the first support rod (310). The fixing block (320) is sleeved on the first support rod (310) and located on the positioning wheel (370).

9. The tooling for an aero-engine combustion generator (400) rotor according to claim 1, characterized in that, The tooling also includes a movable component disposed on the base (100) for moving the tooling based on the movable component.

10. A method for assembling a rotor of a combustion generator (400), characterized in that, The tooling for an aero-engine combustion generator (400) rotor according to any one of claims 1-9 is applied, the assembly method comprising: S1. Loosen the fasteners and adjust the position of the first positioning component (200) to be coaxial with the second positioning component (300); S2. Position the first part (410) of the combustion generator (400) rotor in conjunction with the first positioning assembly (200); S3. Install the second part (420) of the combustion generator (400) rotor onto the first part (410) of the combustion generator (400) rotor, and the second positioning assembly (300) applies an axial clamping force to the second part (420); S4. Rotate the second part (420) of the combustion generator (400) rotor to adjust the coaxiality between the second part (420) and the first part (410) of the combustion generator (400); S5. Lock after adjustment.

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