An automatic press-fitting device and method for an aero-engine rotor

Abstract

This application belongs to the technical field of engine assembly, and particularly relates to an automatic press-fitting device and a press-fitting method for an aero-engine rotor. The device includes: a cross beam (11) having a first protrusion abutting against a first reference plane A at the top end of the engine rotor; a hydraulic cylinder (15) whose adapter plate (151) has a second protrusion abutting against a second reference plane B at the bottom end of the engine rotor; a central fixing rod (17) passing through the cavity of the coupling shaft (7) of the engine rotor; a first laser displacement sensor (14) for measuring the displacement of a reference plane C at the bottom end of the aero-engine rotor; and a second laser displacement sensor (18) fixed to the top end of the central fixing rod (17) and facing the front end face of the coupling shaft (7) of the engine rotor for measuring the displacement of the front end face of the coupling shaft (7). This application can accurately control the press-fitting force and press-fitting displacement of the rotor, and improve the connection tightness of the engine rotor.

Description

Technical Field

[0001] This application belongs to the technical field of engine assembly, and particularly relates to an automatic press-fitting device and method for an aero-engine rotor. Background Art

[0002] As the core component of an aero-engine, the quality of the connection of the rotor directly affects the working performance and reliability of the engine, and is crucial for the working life and safety of the engine. The existing engine rotors often adopt the disk spigot fit and traditional threaded connections. At the same time, there are also some engine rotor disks that adopt the end tooth connection structure, which cannot perform spigot fit. After applying the traditional threaded connection and without press-fitting treatment, the connection tightness is low and the structural stiffness is poor.

[0003] In view of the problem that the conventional assembly method cannot ensure the connection tightness of the engine rotor, it is necessary to press-fit the aero-engine rotor. Summary of the Invention

[0004] To solve one of the above problems, this application provides an automatic press-fitting device and method for an aero-engine rotor. By monitoring the shape and position changes of the rear journal of the rotor, it is judged whether the press-fitting is in place. By monitoring the elongation of the coupling shaft of the rotor, it is judged whether the axial force of the rotor connection is applied in place, accurately controlling the press-fitting force and press-fitting displacement of the engine rotor, and ensuring the high-quality assembly of the engine rotor.

[0005] The first aspect of this application provides an automatic press-fitting device for an aero-engine rotor, which is used to press-fit the aero-engine rotor. The aero-engine rotor includes a first-stage disk, a second-stage disk, and a third-stage disk that are sequentially press-connected through end teeth. The outer ring of the rear journal is press-connected to the rear end of the third-stage disk through end teeth. A rear nut is connected to the inner ring of the rear journal, and the rear nut is press-connected to the rear end of the coupling shaft through a rear wedge block. A front wedge block is arranged between the front end of the coupling shaft and the first-stage disk. The coupling shaft is also provided with an external thread for connecting a nut at the front end of the front wedge block. Among them, a first reference plane A is machined at the position near the front wedge block at the front end of the first-stage disk, a second reference plane B is machined at the rear end of the inner ring of the rear journal, and a reference plane C is formed at the rear end of the outer ring of the rear journal. The press-fitting device includes:

[0006] A cross beam is arranged on the column, and the cross beam has a first protrusion that abuts against the first reference plane A of the aero-engine rotor;

[0007] A hydraulic cylinder, the output end of which is connected to a transfer disk, and the transfer disk has a second protrusion that abuts against the second reference plane B of the aero-engine rotor;

[0008] The central fixing rod has a first part passing through the central cavity of the coupling shaft of the aero-engine rotor. An annular protrusion is provided at the bottom end of the first part. The upper surface of the annular protrusion is crimped on the rear end face of the coupling shaft, and the lower surface of the annular protrusion is crimped on the adapter plate through a compression spring.

[0009] The first laser displacement sensor is fixed on the column and faces the reference plane C for measuring the displacement of the reference plane C.

[0010] The second laser displacement sensor is fixed at the upper end of the first part of the central fixing rod and faces the front end face of the coupling shaft of the aero-engine rotor for measuring the displacement of the front end face of the coupling shaft.

[0011] Preferably, both the first protrusion and the second protrusion are cylindrical structures, and a stop is formed at the front end of the cylindrical structure for docking with the first reference plane A or the second reference plane B.

[0012] Preferably, the column has an external thread and is adaptively connected with a fixing nut. The cross beam has a through hole passing through the column, and the fixing nut is arranged on both sides of the through hole of the cross beam, and the height of the cross beam on the column is adjusted by the fixing nut.

[0013] Preferably, a rocker arm is arranged on the column. The rocker arm extends horizontally to the bottom of the reference plane C of the aero-engine rotor, and the first laser displacement sensor is arranged on the rocker arm.

[0014] Preferably, one end of the rocker arm connecting the column is hinged to a fixing device to rotate in the horizontal plane, and the fixing device is installed on the column with adjustable height.

[0015] Preferably, the central fixing rod further has a second part at the lower end of the annular protrusion, and the second part has a notch for accommodating the upper end of the compression spring.

[0016] Preferably, a vertical guide post is further arranged on the adapter plate. The upper end of the guide post extends into the notch of the second part of the central fixing rod, and the guide post has a central cavity for accommodating the lower end of the compression spring.

[0017] In the second aspect of the present application, an automatic press-fitting method for an aero-engine rotor is provided. Based on the above automatic press-fitting device for an aero-engine rotor, the aero-engine rotor is press-fitted. The press-fitting method includes:

[0018] Step S1: Install the aero-engine rotor without the front nut on the stop of the adapter plate of the hydraulic cylinder, so that the central fixing rod passes through the central cavity of the coupling shaft, and press the cross beam on the first reference plane A of the aero-engine rotor.

[0019] Step S2: Align the first laser displacement sensor with the reference surface C, record the initial position of the reference surface C, align the second laser displacement sensor with the front end face D of the coupling shaft, and record the initial position of the front end face of the coupling shaft.

[0020] Step S3: Apply the press-fitting force P through the hydraulic cylinder 15 until the displacement of the reference surface C reaches the set value.

[0021] Step S4: Install the front nut and apply the predetermined tightening limit force F.

[0022] Step S5: Unload the press-fitting force P to reset the reference surface C, and determine whether the press-fitting is completed according to whether the change displacement of the front end face D of the coupling shaft reaches the theoretical value.

[0023] This application can accurately control the rotor press-fitting force and press-fitting displacement, has a higher connection tightness, better structural stiffness, and further improves the working reliability of the engine. Description of the Drawings

[0024] Figure 1 It is a schematic diagram of the engine rotor structure of this application.

[0025] Figure 2 It is a schematic diagram of the force analysis of the coupling shaft of the engine of this application.

[0026] Figure 3 It is an installation schematic diagram of a preferred embodiment of the automatic press-fitting device for the aero-engine rotor of this application.

[0027] Wherein, 1 - first-stage disk, 2 - second-stage disk, 3 - third-stage disk, 4 - rear journal, 5 - rear nut, 6 - rear wedge, 7 - coupling shaft, 8 - front wedge, 9 - nut, 10 - fixing nut, 11 - cross beam, 12 - column, 13 - rocker arm, 14 - first laser displacement sensor, 15 - hydraulic cylinder, 151 - adapter plate, 16 - aero-engine rotor, 17 - central fixing rod, 171 - first part, 172 - annular protrusion, 173 - second part, 18 - second laser displacement sensor, 19 - guide post, 20 - compression spring. Detailed Embodiments

[0028] To make the objectives, technical solutions, and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below in conjunction with the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions from beginning to end. The described embodiments are part of the embodiments of the present application, rather than all of the embodiments. The embodiments described below by referring to the accompanying drawings are exemplary and are intended to explain the present application, and should not be construed as a limitation to the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts belong to the scope of protection of the present application. The embodiments of the present application will be described in detail below in conjunction with the accompanying drawings.

[0029] The present application first provides an automated press-fitting device for an aero-engine rotor, which is used for press-fitting the aero-engine rotor. First, refer to Figure 1 and Figure 2 , the aero-engine rotor 16 includes a first-stage disk 1, a second-stage disk 2, and a third-stage disk 3 that are press-fitted in sequence through end teeth. The outer ring of the rear journal 4 is press-fitted to the rear end of the third-stage disk 3 through end teeth. The inner ring of the rear journal 4 is connected to a rear nut 5. The rear nut 5 is press-fitted to the rear end of the coupling shaft 7 through a rear wedge 6. A front wedge 8 is provided between the front end of the coupling shaft 7 and the first-stage disk 1. The coupling shaft 7 is also provided with an external thread for connecting a nut 9 at the front end of the front wedge 8. Among them, a first reference plane A is machined at the front end of the first-stage disk 1 near the front wedge 8, a second reference plane B is machined at the rear end of the inner ring of the rear journal 4, and a reference plane C is formed at the rear end of the outer ring of the rear journal 4.

[0030] The press-fitting principle is as follows: First, assemble the engine rotor according to Figure 1 , but do not install the front nut 9. Then, with the first reference plane A as the fixed reference and without moving, apply an axial pressure P to the second reference plane B. The rear journal 4 is designed as a thin-walled elastic member, and the reference plane C of the rear journal 4 will undergo an axial displacement t forward. It is required that this displacement t occurs within the elastic change range of the rear journal 4 and no plastic and non-recoverable displacement should be generated. At this time, install the front nut 9 to limit the force on the front nut 9. The front nut 9 generates an axial pressure F on the front wedge 8 in front of the first-stage disk 1. At this time, as Figure 2 shows, the left end of the coupling shaft 7 is subjected to a reaction axial tension F1 = F from the front nut 9, and at the same time, the axial pressure P applied to the second reference plane B is unloaded. The rear journal 4 will generate a reaction force P1 = P on the coupling shaft 7. The second reference plane B of the rear journal will recover the elastic deformation backward and undergo a displacement, thereby driving the rear nut 5 to move backward and pulling the right end of the coupling shaft 7 to become longer. Assume that the coupling shaft 7 is a straight cylinder structure with a length-to-diameter ratio greater than 10, an outer diameter of D, and an inner diameter of d. Assume the yield stress is δ. The coupling shaft 7 should be within the elastic deformation range, and calculate the elongation stress σ:

[0031]

[0032] According to Hooke's law, stress σ = Eε, where E is the elastic modulus and ε is the strain. Calculate the strain ε:

[0033]

[0034] Let the length of the connecting shaft 7 be L, and calculate the elongation Δ:

[0035]

[0036] According to the above principle, the press-fitting device provided in this application is as Figure 3 shown, and mainly includes:

[0037] A cross beam 11, which is arranged on a column 12. The cross beam 11 has a first protrusion that abuts against the first reference plane A of the aero-engine rotor 16;

[0038] A hydraulic cylinder 15, whose output end is connected with an adapter plate 151. The adapter plate 151 has a second protrusion that abuts against the second reference plane B of the aero-engine rotor 16;

[0039] A central fixing rod 17, which has a first part 171 passing through the middle cavity of the connecting shaft 7 of the aero-engine rotor 16. At the bottom end of the first part 171, there is an annular protrusion 172. The upper surface of the annular protrusion 172 is press-connected to the rear end face of the connecting shaft 7, and the lower surface of the annular protrusion 172 is press-connected to the adapter plate 151 through a compression spring 20;

[0040] A first laser displacement sensor 14, which is fixed on the column 12 and faces the reference plane C, and is used to measure the displacement of the reference plane C;

[0041] A second laser displacement sensor 18, which is fixed at the upper end of the first part 171 of the central fixing rod 17 and faces the front end face of the connecting shaft 7 of the aero-engine rotor 16, and is used to measure the displacement of the front end face of the connecting shaft 7.

[0042] In this embodiment, the hydraulic cylinder 15 is used to apply and unload the axial press-fitting force P of the aero-engine rotor 16. The displacement t of the reference plane C is measured by the first laser displacement sensor 14, and the elongation Δ of the front end measurement surface D of the connecting shaft 7 is measured by the second laser displacement sensor 18, which is the total elongation of the connecting shaft 7. Among them, the compression spring 20 can push the annular protrusion 172 of the central fixing rod 17 upward, so that the upper surface of the annular protrusion 172 always fits against the rear end of the connecting shaft 7, that is, Figure 3 the bottom end in , to ensure that the second laser displacement sensor 18 installed at the upper end of the central fixing rod 17 can accurately measure the elongation of the front end measurement surface D of the connecting shaft 7.

[0043] In some alternative embodiments, both the first protrusion and the second protrusion are cylindrical structures. A stop is formed at the front end of the cylindrical structure for docking with the first reference plane A or the second reference plane B. The stop of the adapter plate 151 on the hydraulic cylinder 15 is used for the axial positioning and circumferential positioning of the second reference plane B of the rear journal 4 of the aero-engine rotor 16. The front end of the cross beam 11 is provided with a stop for the axial positioning and circumferential positioning of the first reference plane A in front of the first-stage disk of the aero-engine rotor 16.

[0044] In some alternative embodiments, the column 12 has an external thread and is adaptively connected with a fixing nut 10. The cross beam 11 has a through hole passing through the column 12. The fixing nut 10 is arranged on both sides of the through hole of the cross beam 11, and the height of the cross beam 11 on the column 12 is adjusted by the fixing nut 10. In this embodiment, the cross beam 11 is positioned by the left and right columns 12 and locked and fixed by the left and right fixing nuts 10.

[0045] In some alternative embodiments, a rocker arm 13 is arranged on the column 12. The rocker arm 13 extends horizontally to the bottom of the reference plane C of the aero-engine rotor 16. The first laser displacement sensor 14 is arranged on the rocker arm 13.

[0046] In some alternative embodiments, one end of the rocker arm 13 connected to the column 12 is hinged to a fixing device to rotate in the horizontal plane. The fixing device is installed on the column 12 with adjustable height. It should be noted that the rocker arm 13 usually needs to be adjusted in the height direction and circumferential rotation. In terms of height adjustment, the rocker arm 13 can move up and down on the column 12 together with the fixing device. For example, it moves through a track and is locked by a screw, or a plurality of jacks are arranged on the column 12 for installing the fixing device at different heights. In terms of circumferential rotation adjustment, usually, the rocker arm 13 and the fixing device are hinged by a pin shaft. The pin shaft is vertically arranged, and the rocker arm can rotate in the horizontal plane during the rotation around the pin shaft.

[0047] In some alternative embodiments, the central fixing rod 17 further has a second part 173 at the lower end of the annular protrusion 172. The second part 173 has a notch for accommodating the upper end of the compression spring 20. In this embodiment, the telescopic direction of the compression spring 20 is ensured by the notch of the second part 173, preventing the top of the compression spring from running off during the compression process. In some alternative embodiments, in order to prevent the lower end of the compression spring 20 from running off, a limiting mechanism can also be arranged at the lower end of the compression spring 20, that is, a vertical guide post 19 is further arranged on the adapter plate 151. The upper end of the guide post 19 extends into the notch of the second part 173 of the central fixing rod 17. The guide post 19 has a central cavity for accommodating the lower end of the compression spring 20.

[0048] On the other hand, the structure of the central fixing rod 17 and the setting of the guide post 19 further ensure that the central fixing rod 17, the adapter plate on the hydraulic cylinder 15, and the center lines of the guide posts 19 coincide with the axis of the engine rotor 16, avoiding deviation in the measurement results caused by the inclination of each structure.

[0049] The second aspect of this application provides an automatic press-fitting method for an aero-engine rotor. Based on the above-mentioned automatic press-fitting device for an aero-engine rotor, the aero-engine rotor is press-fitted. This press-fitting method includes:

[0050] Step S1: Install the aero-engine rotor 16 without the front nut 9 on the stop of the adapter plate 151 of the hydraulic cylinder 15, so that the central fixing rod 17 passes through the middle cavity of the coupling shaft 7, and press the cross beam 11 against the first reference surface A of the aero-engine rotor 16.

[0051] Step S2: Install the cross beam 11 on the left and right columns 12, confirm the axial positioning and circumferential positioning of the front stop of the cross beam 11 and the first reference surface A in front of the first-stage disk of the aero-engine rotor 16. Install the fixing nuts 10 on the left and right columns and lock them tightly; move the rocker arm 13 to adjust the first laser displacement sensor 14 to a state where it can measure the displacement of the reference surface C. Align the first laser displacement sensor 14 with the reference surface C and record the initial position of the reference surface C; install the second laser displacement sensor 18 at the upper end of the central fixing rod 17, adjust the second laser displacement sensor 18 to align with the front end face D of the coupling shaft 7, and record the initial position of the front end face of the coupling shaft 7.

[0052] Step S3: Apply the press-fitting force P through the hydraulic cylinder 15 until the displacement of the reference surface C reaches the set value; that is, monitor whether the displacement of the reference surface C reaches t. If the specified displacement is not reached, the engine rotor must be disassembled and inspected.

[0053] Step S4: When the displacement of the reference surface reaches t, install the front nut 9 and apply a predetermined tightening limit force F.

[0054] Step S5: Unload the press-fitting force P to reset the reference surface C, and determine whether the press-fitting is completed according to whether the change displacement of the front end face D of the coupling shaft 7 reaches the theoretical value. This theoretical value is the elongation Δ calculated above.

[0055] Although the present application has been described in detail with general descriptions and specific implementation examples above, based on the present application, some modifications or improvements can be made, which are obvious to those skilled in the art. Therefore, these modifications or improvements made without departing from the spirit of the present application all fall within the scope of protection required by the present application.

Claims

1. An automatic press-fitting device for an aero-engine rotor, which is used for press-fitting the aero-engine rotor. The aero-engine rotor (16) includes a first-stage disk (1), a second-stage disk (2), and a third-stage disk (3) that are sequentially press-fitted through end teeth. The outer ring of the rear journal (4) is press-fitted to the rear end of the third-stage disk (3) through end teeth. The inner ring of the rear journal (4) is connected with a rear nut (5). The rear nut (5) is press-fitted to the rear end of the coupling shaft (7) through a rear wedge block (6). A front wedge block (8) is arranged between the front end of the coupling shaft (7) and the first-stage disk (1). The coupling shaft (7) is also provided with an external thread for connecting a nut (9) at the front end of the front wedge block (8). Among them, At the front end of the first-level disk (1) near the front wedge block (8), a first reference plane A is machined, and at the rear end of the inner ring of the rear journal (4), a second reference plane B is machined. At the rear end of the outer ring of the rear journal (4), a reference plane C is formed. It is characterized in that the press-fitting device includes: A cross beam (11) is arranged on the column (12), and the cross beam (11) has a first protrusion that abuts against the first reference plane A of the aero-engine rotor (16); A hydraulic cylinder (15), the output end of which is connected with an adapter plate (151), and the adapter plate (151) has a second protrusion that abuts against the second reference plane B of the aero-engine rotor (16); A central fixing rod (17) has a first part (171) passing through the middle cavity of the coupling shaft (7) of the aero-engine rotor (16). At the bottom end of the first part (171), an annular protrusion (172) is arranged. The upper surface of the annular protrusion (172) is press-connected to the rear end face of the coupling shaft (7), and the lower surface of the annular protrusion (172) is press-connected to the adapter plate (151) through a compression spring (20); A first laser displacement sensor (14) is fixed on the column (12) and is directly opposite to the reference plane C for measuring the displacement of the reference plane C; A second laser displacement sensor (18) is fixed at the upper end of the first part (171) of the central fixing rod (17) and faces the front end face of the coupling shaft (7) of the aero-engine rotor (16) for measuring the displacement of the front end face of the coupling shaft (7).

2. The automated press-fitting device for an aero-engine rotor according to claim 1, wherein, Both the first protrusion and the second protrusion are cylindrical structures, and a stop is formed at the front end of the cylindrical structure for docking with the first reference plane A or the second reference plane B.

3. The automated press-fitting device for an aero-engine rotor according to claim 2, wherein, The column (12) has an external thread and is adaptively connected with a fixing nut (10). The cross beam (11) has a through hole passing through the column (12). The fixing nut (10) is arranged on both sides of the through hole of the cross beam (11), and the height of the cross beam (11) on the column (12) is adjusted through the fixing nut (10).

4. The automated press-fitting device for an aero-engine rotor according to claim 1, characterized in that, A rocker arm (13) is arranged on the column (12). The rocker arm (13) extends horizontally to the bottom of the reference plane C of the aero-engine rotor (16), and the first laser displacement sensor (14) is arranged on the rocker arm (13).

5. The automated press-fitting device for an aero-engine rotor according to claim 4, characterized in that, One end of the rocker arm (13) connecting the column (12) is hinged to a fixing device to rotate in the horizontal plane, and the fixing device is installed on the column (12) with adjustable height.

6. The automated press-fitting device for an aero-engine rotor according to claim 1, characterized in that, The central fixing rod (17) also has a second part (173) at the lower end of the annular protrusion (172), and the second part (173) has a notch for accommodating the upper end of the compression spring (20).

7. The automated press-fitting device for an aero-engine rotor according to claim 6, wherein A vertical guide post (19) is further arranged on the adapter plate (151). The upper end of the guide post (19) extends into the notch of the second part (173) of the central fixing rod (17), and the guide post (19) has a central cavity for accommodating the lower end of the compression spring (20).

8. An automatic press-fitting method for an aero-engine rotor, characterized in that, Press-fitting the aero-engine rotor based on the aero-engine rotor automatic press-fitting device according to any one of claims 1 to 7, and the press-fitting method includes: Step S1: Install the aero-engine rotor (16) without the pre-installed nut (9) on the stop of the adapter plate (151) of the hydraulic cylinder (15), so that the central fixing rod (17) passes through the middle cavity of the coupling shaft (7), and press the cross beam (11) against the first reference plane A of the aero-engine rotor (16). Step S2: Align the first laser displacement sensor (14) with the reference plane C and record the initial position of the reference plane C. Align the second laser displacement sensor (18) with the front end face D of the coupling shaft (7) and record the initial position of the front end face of the coupling shaft (7). Step S3: Apply a press-fitting force P through the hydraulic cylinder 15 until the displacement of the reference plane C reaches the set value. Step S4: Install the pre-installed nut (9) and apply a predetermined tightening limit force F. Step S5: Unload the press-fitting force P to reset the reference plane C, and determine whether the press-fitting is completed according to whether the change displacement of the front end face D of the coupling shaft (7) reaches the theoretical value.

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