Guiding device for assembling parts of aero-engine

Abstract

The utility model relates to the technical field of aero-engine assembly, in particular to a guide device for assembling parts of an aero-engine, which comprises a flange arranged on the aero-engine and a plurality of through holes arranged on the flange, and is characterized in that a locking seat and a guide seat are arranged in an up-and-down opposite manner, a guide pin is fixed on the guide seat, and the guide pin is fixed on the locking seat. A locking assembly is arranged on the locking seat, and the locking assembly is used for installing the guide seat and the locking seat on the flange through hole; in practical application, the guide seat and the locking seat are fixed on the flange through hole through the locking assembly, so that the guide pin on the guide seat is fixed on the flange through hole; the utility model overcomes the defect that the guide pin is inconvenient to install in the through hole of the aero-engine component in the prior art.

Description

Technical Field

[0001] The utility model relates to the technical field of aero-engine assembly, in particular to a guiding device for assembling components of an aero-engine. Background Art

[0002] The low-pressure turbine rotating and stationary stator unit of an aero-engine consists of two parts, a rotor and a stator. Its assembly mode is vertical assembly. The rotor and stator adopt a honeycomb labyrinth seal structure for sealing. To ensure good sealing performance, the radial clearance between the honeycomb on the stator and the labyrinth teeth on the rotor is relatively small, with the minimum being only 0.2 mm. During the installation process of the rotating and stationary stator, the labyrinth teeth and honeycomb are in an invisible state. Without good centering guidance, during the installation process, the stator and the rotor often collide and scrape against each other, resulting in damage to the sealing structure and further causing attenuation of the engine performance. Since the bolt mounting holes on the casing are through holes, it is difficult to directly fix the guiding pins. Content of the Utility Model

[0003] The purpose of the utility model is to provide a guiding device for assembling components of an aero-engine in view of the above deficiencies, which overcomes the above-mentioned defect that it is inconvenient to install guiding pins in the through holes of aero-engine components in the prior art.

[0004] To achieve the above purpose, the utility model adopts the following technical solutions:

[0005] A guiding device for assembling components of an aero-engine includes a flange arranged on the aero-engine and a plurality of through holes arranged on the flange. It is characterized in that: a locking seat and a guiding seat are arranged opposite to each other up and down. A guiding pin is fixed on the guiding seat, and a locking component is arranged on the locking seat. The locking component is used to install the guiding seat and the locking seat on the through holes of the flange.

[0006] Furthermore, a blind hole is arranged at the bottom end of the guiding seat, and a cylindrical cavity is arranged at the bottom of the blind hole. The locking component includes a plurality of locking columns inserted into the through holes and a driving structure used to drive the plurality of locking columns to move away from each other. The driving structure is installed on the locking seat, and a locking block is arranged at the top end of the locking column.

[0007] Furthermore, the inner diameter of the cylindrical cavity is larger than the inner diameter of the blind hole.

[0008] Further, the locking seat is a cylindrical seat body, and a cylindrical hollow rotating cavity is arranged inside the seat body. A plurality of locking straight grooves communicating with the rotating cavity are formed at the top of the seat body. The plurality of locking straight grooves are distributed radially outward with the axis of the seat body as the center. A slider is slidably connected in the locking straight groove, and the bottom end of the locking column is fixed on the slider; the driving structure includes a rotating disk rotatably connected in the rotating cavity, and a plurality of spiral guiding grooves arranged on the rotating disk. The plurality of spiral guiding grooves are spirally distributed radially outward with the axis of the seat body as the center. A knob is rotatably connected to the bottom of the seat body, and the knob is connected to the rotating disk through a connecting shaft. One end of the slider is slidably connected in the spiral guiding groove.

[0009] Further, a plurality of convex strips are arranged on the knob, and the convex strips are arranged perpendicular to the rotation direction of the knob.

[0010] The beneficial effects of the present utility model are as follows:

[0011] In practical applications, the guiding seat and the locking seat are fixed on the flange through hole by the locking assembly, so that the guiding pin on the guiding seat is fixed on the flange through hole; the present utility model overcomes the above-mentioned defect that it is inconvenient to install the guiding pin in the through hole of the aero-engine components in the prior art. Description of the Drawings

[0012] Figure 1 is the overall structural schematic diagram of the present utility model;

[0013] Figure 2 is the front view of the present utility model in use;

[0014] Figure 3 is the partial cross-sectional view at A-A;

[0015] Figure 4 is the structural schematic diagram of the locking seat in the present utility model;

[0016] Figure 5 is the top view of the rotating disk in the present utility model;

[0017] Reference numerals: flange 101; through hole 102; locking seat 2; rotating cavity 21; locking straight groove 22; slider 23; guiding seat 3; blind hole 31; cylindrical cavity 32; guiding pin 4; locking column 51; locking block 52; rotating disk 531; spiral guiding groove 5311; knob 532; convex strip 5321; connecting shaft 533. Detailed Embodiments

[0018] Such as Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 and Figure 5As shown in the figure, a guiding device for assembling components of an aero-engine includes a flange 101 provided on the aero-engine, and a plurality of through holes 102 provided on the flange 101. It is characterized in that a locking seat 2 and a guiding seat 3 are arranged opposite to each other up and down. A guiding pin 4 is fixed on the guiding seat 3, and a locking assembly is arranged on the locking seat 2. The locking assembly is used to install the guiding seat 3 and the locking seat 2 on the through hole 102 of the flange 101.

[0019] During use, the guiding seat 3 and the locking seat 2 are fixed on the through hole 102 of the flange 101 through the locking assembly, so that the guiding pin 4 on the guiding seat 3 is fixed on the through hole 102 of the flange 101. The utility model overcomes the above-mentioned defect that it is inconvenient to install the guiding pin 4 in the through hole 102 of the components of the aero-engine in the prior art.

[0020] As Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown in the figure, a blind hole 31 is provided at the bottom end of the guiding seat 3, and a cylindrical cavity 32 is provided at the bottom of the blind hole 31. The locking assembly includes a plurality of locking columns 51 inserted into the through hole 102, and a driving structure for driving the plurality of locking columns 51 to move away from each other. The driving structure is installed on the locking seat 2, and a locking block 52 is provided at the top end of the locking column 51. In this embodiment, during use, the plurality of locking columns 51 are passed through the bottom end of the through hole 102 and inserted into the blind hole 31, and the plurality of locking columns 51 are driven to move away from each other through the driving structure until the locking block 52 is inserted into the cylindrical cavity 32, then the guiding seat 3 and the locking seat 2 can be fixed on the through hole 102 of the flange 101, so that the guiding pin 4 on the guiding seat 3 is fixed on the through hole 102 of the flange 101.

[0021] As Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown in the figure, the inner diameter of the cylindrical cavity 32 is larger than the inner diameter of the blind hole 31. In this embodiment, when the inner diameter of the cylindrical cavity 32 is larger than the inner diameter of the blind hole 31, the locking block 52 can be inserted into the cylindrical cavity 32 to prevent the guiding seat 3 and the locking seat 2 from falling off from both ends of the through hole 102 of the flange 101.

[0022] As Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5As shown, the locking seat 2 is a cylindrical seat body. A cylindrical hollow rotating cavity 21 is provided inside the seat body. A plurality of locking straight grooves 22 communicating with the rotating cavity 21 are formed at the top of the seat body. The plurality of locking straight grooves 22 are distributed divergently outward with the axis of the seat body as the center. A slider 23 is slidably connected in the locking straight groove 22. The bottom end of the locking column 51 is fixed on the slider 23. The driving structure includes a rotating disk 531 rotatably connected in the rotating cavity 21, and a plurality of spiral guiding grooves 5311 provided on the rotating disk 531. The plurality of spiral guiding grooves 5311 are spirally distributed outward with the axis of the seat body as the center. A knob 532 is rotatably connected to the bottom of the seat body. The knob 532 and the rotating disk 531 are connected by a connecting shaft 533. One end of the slider 23 is slidably connected in the spiral guiding groove 5311. In this embodiment, during use, a plurality of locking columns 51 are passed through from the bottom end of the through hole 102 and inserted into the blind hole 31. The knob 532 is manually rotated. The rotating disk 531 is driven to rotate by the knob 532 and the connecting shaft 533. The slider 23 is driven to slide along the locking straight groove 22 through the spiral guiding groove 5311 on the rotating disk 531, so that the plurality of locking columns 51 approach or move away from each other.

[0023] As Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown, a plurality of ridges 5321 are provided on the knob 532. The ridges 5321 are arranged perpendicular to the rotation direction of the knob 532. In this embodiment, the ridges 5321 can increase the friction between the hand and the knob 532, making it more convenient to turn.

[0024] The specific embodiments described herein are merely illustrative of the spirit of the present invention. Those skilled in the art of the present invention can make various modifications or supplements to the described specific embodiments or use similar methods for substitution, but will not deviate from the scope defined by the spirit of the present invention.

Claims

1. A guide device for assembling components of an aircraft engine, comprising a flange (101) arranged on the aircraft engine, and a plurality of through holes (102) arranged on the flange (101), characterized in that: A locking seat (2) and a guide seat (3) are arranged vertically opposite to each other, a guide pin (4) is fixed on the guide seat (3), and a locking assembly is arranged on the locking seat (2), and the locking assembly is used to install the guide seat (3) and the locking seat (2) on the through hole (102) of the flange (101).

2. A guide device for assembling components of an aircraft engine according to claim 1, characterized in that: The bottom end of the guide seat (3) is provided with a blind hole (31), and the bottom of the blind hole (31) is provided with a cylindrical cavity (32); the locking assembly comprises a plurality of locking columns (51) plugged into the through hole (102), and a driving structure is used to drive the plurality of locking columns (51) to move away from each other, the driving structure is installed on the locking seat (2), and a locking block (52) is provided at the top end of the locking column (51).

3. A guide device for assembling components of an aircraft engine according to claim 2, characterized in that: The inner diameter of the cylindrical cavity (32) is greater than the inner diameter of the blind hole (31).

4. A guide device for assembling components of an aircraft engine according to claim 2, characterized in that: The locking seat (2) is a cylindrical seat body, a cylindrical hollow rotating cavity (21) is arranged in the seat body, a plurality of locking straight grooves (22) connected to the rotating cavity (21) are arranged on the top of the seat body, the plurality of locking straight grooves (22) are distributed outwardly with the axis of the seat body as the center, a slider (23) is slidably connected in the locking straight groove (22), and the bottom end of the locking column (51) is fixed on the slider (23); the driving structure includes a rotatable connection on A rotating disk (531) in the rotating chamber (21) is provided with a plurality of spiral guide grooves (5311) on the rotating disk (531), the plurality of spiral guide grooves (5311) being distributed spirally outward with the axis of the seat body as the center, a knob (532) being rotatably connected to the bottom of the seat body, the knob (532) being connected to the rotating disk (531) via a connecting shaft (533), and one end of the slider (23) being slidably connected to the spiral guide groove (5311).

5. A guide device for assembling components of an aircraft engine according to claim 4, characterized in that: The knob (532) is provided with a plurality of convex strips (5321), and the convex strips (5321) are arranged perpendicular to the rotation direction of the knob (532).

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