Alignment device, alignment method and aeroengine

Abstract

The application discloses an alignment device, an alignment method and an aero-engine, and relates to the technical field of aero-engine assembly, and specifically relates to an alignment device, an alignment method and an aero-engine. The alignment device comprises a base, which is used for positioning and supporting a turbine secondary rotor, and the base is provided with a first mark used for alignment with a first preset mark of the turbine secondary rotor; a mandrel, which is matched with the height of the turbine secondary rotor and is used for being arranged on the base in a preset angular position; and a guide device, which is used for being installed on the mandrel in the preset angular position, and the guide device is provided with a second mark used for matching the position of the first mark after the guide device is installed on the mandrel, and the guide device is provided with a guide structure matched with the position of a shaft neck end surface of the turbine secondary rotor. According to the position of the first mark, a second preset mark matched with the angular position of the first preset mark can be marked on the shaft neck end surface of the turbine secondary rotor through the guide structure, accurate scribing is achieved, manual extension of the mark position is not needed, angular errors caused by manual operation and part structures are reduced, and the position precision of subsequent assembly of the rotor is ensured.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine component assembly technology, and in particular, to an alignment device, an alignment method, and an aircraft engine. Background Technology

[0002] During the assembly of a new type of turboprop engine, it is crucial to control the angular positions of the two-stage turbine rotors to ensure that the angular positions of the two-stage turbine rotors during final engine assembly are consistent with the angular positions determined after rotor dynamic balancing. Figure 1 and Figure 2 As shown, the angular position "X" mark on the second-stage rotor of the power turbine is directly marked on the intake side of the rotor. During final assembly, the intake side faces downwards, making visual inspection impossible. Therefore, the "X" on the intake side needs to be extended to the exhaust side. A temporary marker pen should be used to mark the "X" on the end face of the journal on the exhaust side. Figure 2 As shown, the existing alignment method is as follows: the "X" on the first-stage rotor of the power turbine is aligned with the "X" on the end face of the power turbine shaft; the "X" on the second-stage rotor of the power turbine is aligned with the "X" on the end face of the power turbine shaft, so that the X marks of the two-stage rotors are aligned and the end teeth are engaged.

[0003] Currently, the method of visual manual alignment involves flipping the secondary rotor of the power turbine and extending the "X" mark on the intake side through the twisted blades to the exhaust side journal of the rotor. The marking line needs to cross the blades, and the manual marking has a large error, making it impossible to accurately transfer the "X" marking line. As a result, the angular position accuracy of the turbine rotor cannot be guaranteed during final assembly. Summary of the Invention

[0004] This invention provides an alignment device, an alignment method, and an aero-engine to solve the technical problem in the prior art where the air intake side of the second stage rotor of the power turbine faces downwards, making it impossible to visually inspect and resulting in large errors due to manual operation during the assembly of the two-stage turbine rotor.

[0005] The technical solution adopted in this invention is as follows:

[0006] An alignment device for angular positioning alignment of a turbine rotor with torsion blades, comprising:

[0007] A base is used to position and support the second-stage turbine rotor, and the base is provided with a first mark for alignment with a first preset mark on the second-stage turbine rotor;

[0008] The spindle, with a height matching that of the second-stage turbine rotor, is positioned at a preset angular angle on the base.

[0009] A guide device is used to be installed on the mandrel at a preset angular position. The guide device is provided with a second mark, which is used to match the position of the first mark after the guide device is installed on the mandrel. The guide device is provided with a guide structure that matches the position of the journal end face of the turbine secondary rotor.

[0010] As a further improvement to the above technical solution, the guiding device includes a guide sleeve for mounting on the top end of the mandrel, and the mating end of the guide sleeve and the end of the mandrel are respectively provided with positioning holes for inserting cylindrical pins.

[0011] As a further improvement to the above technical solution, the positioning hole includes a first hole and a second hole opened in the guide sleeve, wherein the second hole is eccentrically arranged relative to the first hole.

[0012] As a further improvement to the above technical solution, the inner diameter of the guide sleeve is smaller than the inner diameter of one end of the exhaust side of the second stage rotor of the power turbine, and the outer diameter of the guide sleeve is larger than the inner diameter of one end of the exhaust side of the second stage rotor of the power turbine.

[0013] As a further improvement to the above technical solution, the top of the base is provided with a positioning structure that matches the shape of one end of the air intake edge of the second-stage blade of the turbine rotor.

[0014] As a further improvement to the above technical solution, the guiding structure includes a guiding notch formed on the side wall of the guiding sleeve, the notch being disposed near the mating end of the guiding sleeve, and the second mark being disposed on the outer wall of the guiding sleeve and located between the guiding notch and the free end of the guiding sleeve.

[0015] As a further improvement to the above technical solution, the top of the base is provided with a positioning cavity for embedding the mandrel. The positioning cavity is provided with a threaded hole at a preset angular position, and the mandrel is provided with a through hole for screws to pass through corresponding to the threaded hole.

[0016] The first identifier is disposed on the outer wall of the base along the axial direction.

[0017] According to another aspect of the present invention, an alignment method is also provided, which applies any of the alignment devices described above, the alignment method comprising:

[0018] S1. Place the base and the working plane, with the intake side of the turbine secondary rotor facing the base;

[0019] S2. Adjust the angular position of the turbine second-stage rotor so that the first preset mark on the turbine second-stage rotor is aligned with the first mark on the base;

[0020] S3. The guide device is installed on the mandrel at a preset angular position;

[0021] S4. A second preset mark is made on the journal end face of the turbine secondary rotor according to the second identifier via the guide structure;

[0022] S5. Align the second preset mark and assemble the rotor.

[0023] According to another aspect of the present invention, an aircraft engine is also provided, which incorporates any of the alignment devices described above.

[0024] The present invention has the following beneficial effects:

[0025] This alignment device uses a base to position and support the turbine secondary rotor. A first mark is set on the base to align the first preset mark with the first mark after the turbine secondary rotor is placed. A mandrel is set on the base at a preset angle, and the height of the mandrel matches the height of the turbine secondary rotor, so that the mandrel passes through the turbine secondary rotor when it is placed on the base. Then, a guide device is installed at the top of the mandrel at a preset angle, so that the guide device presses the turbine secondary rotor. At this time, the angle position of the second mark on the guide device matches the angle position of the first mark. Based on the position of the first mark, the guide structure can mark the second preset mark on the journal end face of the turbine secondary rotor, which matches the angle position of the first preset mark. This precise marking eliminates the need to rely on manual extension of the mark position, reduces angular errors caused by manual operation and component structure, and ensures the positional accuracy of the subsequent rotor assembly.

[0026] 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 accompanying drawings. Attached Figure Description

[0027] 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:

[0028] Figure 1 This is a schematic diagram of the existing assembly method. Figure 1 ;

[0029] Figure 2 This is a schematic diagram of the existing assembly method. Figure 2 ;

[0030] Figure 3 This is a reference diagram showing the usage state of the alignment device according to a preferred embodiment of the present invention;

[0031] Figure 4 This is a schematic diagram of the alignment device structure according to a preferred embodiment of the present invention;

[0032] Figure 5 This is a schematic diagram of the alignment device portion of a preferred embodiment of the present invention;

[0033] Figure 6 This is a schematic diagram of the distribution of the first and second holes in a preferred embodiment of the present invention;

[0034] 1. Base 11. First mark 2. Spindle 3. Guide device 31. Second mark 32. Guide structure 4. Cylindrical pin 5. Screw 6. Turbine secondary rotor 61. First preset mark 62. Second preset mark. Detailed Implementation

[0035] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0036] Reference Figures 1 to 6 A preferred embodiment of the present invention provides an alignment device for angular positioning alignment of a turbine rotor with torsion blades, comprising:

[0037] Base 1 is used to position and support the turbine secondary rotor 6. Base 1 is provided with a first mark 11 for alignment with the first preset mark 61 of the turbine secondary rotor 6.

[0038] The spindle 2 is height-matched with the turbine secondary rotor 6 and is set on the base 1 at a preset angular position;

[0039] The guide device 3 is used to be installed on the spindle 2 at a preset angle position. The guide device 3 is provided with a second mark 31, which is used to match the position of the first mark 11 after the guide device 3 is installed on the spindle 2. The guide device 3 is provided with a guide structure 32 that matches the position of the journal end face of the turbine secondary rotor 6.

[0040] Understandably, this alignment device uses a base 1 to position and support the turbine secondary rotor 6, and a first mark 11 is set on the base 1 to align the first preset mark 61 with the first mark 11 after the turbine secondary rotor 6 is placed. A mandrel 2 is set on the base 1 at a preset angle, and the height of the mandrel 2 matches the height of the turbine secondary rotor 6, so that the mandrel 2 passes through the turbine secondary rotor 6 when the turbine secondary rotor 6 is placed on the base 1. Then, a guide device 3 is installed at the top of the mandrel 2 at a preset angle, so that the guide device 3 presses the turbine secondary rotor 6. At this time, the angle position of the second mark 31 on the guide device 3 matches the angle position of the first mark 11. Based on the position of the first mark 11, the guide structure 32 can mark the second preset mark 62 on the journal end face of the turbine secondary rotor 6, which matches the angle position of the first preset mark 61. This precise marking eliminates the need to rely on manual extension of the mark position, reduces angular errors caused by manual operation and component structure, and ensures the positional accuracy of the subsequent rotor assembly.

[0041] In this embodiment, the guiding device 3 includes a guiding sleeve for mounting on the top end of the mandrel 2. The mating end of the guiding sleeve and the end of the mandrel 2 are respectively provided with positioning holes for passing through the cylindrical pin 4. The positioning holes are arranged along the axial direction of the mandrel 2. After the cylindrical pin 4 is pre-set in the positioning hole of the mandrel 2, the positioning hole of the guiding sleeve is aligned with the cylindrical pin 4 and then assembled axially above the mandrel 2 to determine the angular position.

[0042] Specifically, the positioning holes include a first hole and a second hole in the guide sleeve. The second hole is eccentrically arranged relative to the first hole. For example, in this embodiment, the circumferential position of the two holes is 160° apart, which can quickly confirm the installation position, ensure installation efficiency and positioning accuracy, and ensure that the positions of each mark and marker are corresponding.

[0043] In this embodiment, the inner diameter of the guide sleeve is smaller than the inner diameter of one end of the exhaust side of the second stage rotor 6 of the power turbine, and the outer diameter of the guide sleeve is larger than the inner diameter of one end of the exhaust side of the second stage rotor 6 of the power turbine, so that the guide sleeve can be pressed against the end face of the exhaust side of the second stage blade of the turbine rotor, thereby pressing and fixing it on the base 1, and clamping it securely.

[0044] In this embodiment, the top of the base 1 is provided with a positioning structure that matches the shape of one end of the air intake edge of the second-stage blade of the turbine rotor, so as to match and position the end of the air intake edge of the second-stage blade of the turbine rotor for support.

[0045] In this embodiment, the guide structure 32 includes a guide notch formed on the side wall of the guide sleeve. The notch is set near the mating end of the guide sleeve. The second mark 31 is arranged on the outer wall of the guide sleeve and located between the guide notch and the free end of the guide sleeve. By setting the guide notch, it is easy for marking tools such as marking pens to pass through and contact the journal end face of the turbine rotor secondary blade, quickly align and mark, greatly reduce the difficulty of operation and improve efficiency.

[0046] In this embodiment, the top of the base 1 is provided with a positioning cavity for embedding the mandrel 2. The positioning cavity is provided with a threaded hole at a preset angular position. The mandrel 2 is provided with a through hole corresponding to the threaded hole for the screw 5 to pass through. The mandrel 2 is positioned and fixed on the base 1 by the screw 5 passing through the through hole and being fastened to the threaded hole.

[0047] In this embodiment, the first mark 11 is disposed on the outer wall of the base 1 along the axial direction, and similarly, the second mark 31 is disposed on the outer wall of the guide sleeve along the axial direction, so as to facilitate the alignment of the engraving lines;

[0048] The alignment method in this embodiment utilizes the aforementioned alignment device, and the alignment method includes:

[0049] S1. Place the base 1 on the working plane, and place the turbine secondary rotor 6 with the air intake side facing the base 1 on the base 1; specifically, use the front spindle 2 to fix it to the base 1 with screws 5, and install the fixing pin in the positioning hole of the spindle 2 in advance so that the spindle 2 passes through the turbine secondary rotor 6.

[0050] S2. Adjust the angular position of the turbine second-stage rotor 6 so that the first preset mark 61 of the turbine second-stage rotor 6 is aligned with the first mark 11 of the base 1; specifically, adjust the angular position of the turbine second-stage rotor 6 so that the first preset mark 61 is aligned with the first mark 11 of the base 1, and after the adjustment is completed, make the inner end face of the air intake side of the turbine second-stage rotor 6 cooperate with the positioning structure on the base 1 to achieve positioning support.

[0051] S3. The installation guide device 3 is mounted on the spindle 2 at a preset angle position; specifically, the guide sleeve is fitted onto the top of the spindle 2, and the first hole and the second hole of the guide sleeve are aligned with the fixing pin for assembly, and the guide sleeve is moved axially to abut against the turbine secondary rotor 6.

[0052] S4. A second preset mark 62 is made on the journal end face of the turbine secondary rotor 6 according to the second mark 31 via the guide structure 32; specifically, by passing a marking pen through the guide notch to the journal end face of the turbine secondary rotor 6, aligning with the second mark 31 to make the second preset mark 62, the conversion mark of the scribing position can be completed.

[0053] S5. Align the second preset mark 62 and assemble the rotor.

[0054] Specifically, the turbine first-stage rotor and turbine second-stage rotor 6 are assembled according to the existing assembly method, so that the end teeth of the second-stage rotor mesh. The angular position accuracy is observed through the second preset mark 62, which effectively improves the angular position accuracy of the assembly, avoids visual deviation and angular error caused by blade torsion, and avoids workpiece damage and high operational intensity caused by repeated rotor flipping during alignment.

[0055] 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. An alignment device for angular positioning alignment of a turbine rotor with torsion blades, characterized in that, include: A base (1) is used to position and support the turbine secondary rotor (6). The base (1) is provided with a first mark (11) for alignment with a first preset mark (61) of the turbine secondary rotor (6). The spindle (2) is height-matched with the turbine secondary rotor (6) and is positioned at a preset angle on the base (1); A guide device (3) is installed on the spindle (2) at a preset angular position. The guide device (3) is provided with a second mark (31) for matching the position of the first mark (11) after the guide device (3) is installed on the spindle (2). The guide device (3) is provided with a guide structure (32) that matches the position of the journal end face of the turbine secondary rotor (6).

2. The alignment device according to claim 1, characterized in that, The guiding device (3) includes a guide sleeve for mounting on the top end of the mandrel (2), and the mating end of the guide sleeve and the end of the mandrel (2) are respectively provided with positioning holes for inserting cylindrical pins (4).

3. The alignment device according to claim 2, characterized in that, The positioning hole includes a first hole and a second hole formed in the guide sleeve, with the second hole being eccentrically arranged relative to the first hole.

4. The alignment device according to claim 2, characterized in that, The inner diameter of the guide sleeve is smaller than the inner diameter of one end of the exhaust side of the turbine secondary rotor (6), and the outer diameter of the guide sleeve is larger than the inner diameter of one end of the exhaust side of the turbine secondary rotor (6).

5. The alignment device according to claim 1, characterized in that, The top of the base (1) is provided with a positioning structure that matches the shape of one end of the air intake side of the second-stage blade of the turbine rotor.

6. The alignment device according to claim 2, characterized in that, The guide structure (32) includes a guide notch formed on the side wall of the guide sleeve, the notch being located near the mating end of the guide sleeve, and the second mark (31) being disposed on the outer wall of the guide sleeve and located between the guide notch and the free end of the guide sleeve.

7. The alignment device according to claim 1, characterized in that, The top of the base (1) is provided with a positioning cavity for embedding the mandrel (2). The positioning cavity is provided with a threaded hole at a preset angular position. The mandrel (2) is provided with a through hole corresponding to the threaded hole for the screw (5) to pass through.

8. The alignment device according to claim 1, characterized in that, The first mark (11) is disposed on the outer wall of the base (1) along the axial direction.

9. An alignment method for angular position alignment of a turbine rotor with torsion blades, characterized in that, The application has the alignment device according to any one of claims 1-8, the alignment method comprising: S1. Place the base and the working plane, with the intake side of the turbine secondary rotor facing the base; S2. Adjust the angular position of the turbine second-stage rotor so that the first preset mark on the turbine second-stage rotor is aligned with the first mark on the base; S3. The guide device is installed on the mandrel at a preset angular position; S4. A second preset mark is made on the journal end face of the turbine secondary rotor according to the second identifier via the guide structure; S5. Align the second preset mark and assemble the rotor.

10. An aircraft engine, characterized in that, The application has the alignment device as described in any one of claims 1-8.

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