A three-point positioning + three-point reinforcing quick connecting structure of an aero-engine

Abstract

The application discloses an aero-engine three-point positioning+three-point reinforcing quick connecting structure, which comprises an air inlet casing shell, a diffuser, a guider, a plurality of groups of fixed bolts and adjusting washer assemblies which are uniformly distributed in the circumferential direction; the air inlet casing shell, the diffuser and the guider are fastened in series through the fixed bolts and the adjusting washer assemblies; the adjusting washer assembly is composed of an adjusting sleeve ring and a base sleeve ring; in order to solve the technical problems that the tooling is complex, the time consumption is too long and the relative position is difficult to determine when the air inlet casing, the diffuser and the turbine guider are assembled in the prior art, the three-point positioning principle is utilized, the axial center lines of the three components of the air inlet casing, the diffuser and the guider can be quickly aligned, the centering is completed at one time, the complicated steps of repeated adjustment depending on complex tooling in the traditional mode are omitted, a full-range stable force receiving body is formed through the three-point reinforcing, and the assembly time is reduced.

Description

Technical Field

[0001] This application relates to the field of aero-engine assembly equipment technology, and in particular to a quick connection structure for aero-engines with three-point positioning and three-point reinforcement. Background Technology

[0002] As a highly complex and precise power plant, the assembly quality of an aero engine directly determines the overall performance, safety, and lifespan of the aircraft. The intake casing, diffuser, and turbine guide vanes, as core airflow channel components, require extremely high coaxiality, end-face parallelism, and connection rigidity in their connections to ensure stable and efficient airflow and avoid additional airflow losses and vibrations.

[0003] In the existing technology, in order to ensure the relative positional accuracy of several large components in a free state, especially the center alignment of the shaft, it is necessary to design and manufacture huge special positioning fixtures and adjustment tools. These tools themselves are expensive, have long manufacturing cycles, and occupy valuable assembly line space.

[0004] In other words, existing technologies have the following technical problems: the installation and connection methods of ordinary aero-engine inlet casings, diffusers, and turbine guide vanes are complex, their relative positions are difficult to determine, assembly is time-consuming, and the required tooling is complex. Therefore, to address the above problems, a rapid connection structure for aero-engines with three-point positioning and three-point reinforcement is proposed. Summary of the Invention

[0005] This embodiment provides a quick connection structure for three-point positioning and three-point reinforcement of aero-engines to solve the problems of complex installation and connection methods, difficulty in determining relative positions, long assembly time, and complex tooling required for ordinary aero-engine inlet casings, diffusers, and turbine guide vanes in the prior art.

[0006] According to one aspect of this application, a quick-connect structure for aero-engine with three-point positioning and three-point reinforcement is provided, including an intake casing, a diffuser, a guide, multiple sets of circumferentially distributed fixing bolts and adjusting shim assemblies.

[0007] The intake casing, diffuser, and guide are fastened together in series by the fixing bolts and adjusting shim assembly;

[0008] The adjusting shim assembly consists of an adjusting collar and a base collar.

[0009] Furthermore, the intake casing, diffuser, and guide are provided with six mounting holes evenly distributed circumferentially, of which three mounting holes serve as a positioning hole group and the other three mounting holes serve as a reinforcement hole group.

[0010] Furthermore, the six mounting holes are evenly distributed on the circumference; the three holes in the positioning hole group and the three holes in the reinforcing hole group are staggered on the circumference.

[0011] Furthermore, the central angle between any two adjacent holes in the positioning hole group is 120°, the central angle between any two adjacent holes in the reinforcing hole group is also 120°, and the positioning hole group and the reinforcing hole group are 60° apart on the circumference.

[0012] Furthermore, the adjusting collar and the base collar are slidably sleeved together. The bottom of the adjusting collar is provided with a protrusion to form a support portion, and the arc surface of the base collar is provided with a recess to form a support groove. The support portion extends into the support groove.

[0013] Furthermore, the support groove has a stepped structure.

[0014] Furthermore, the bottom of the support portion is provided with a convex portion, and the stepped surface of the support groove is provided with a concave portion.

[0015] Furthermore, three support parts are provided, which are equidistantly distributed around the circumference of the adjusting collar, and three support grooves are provided, which are equidistantly distributed on the arc surface of the base collar.

[0016] Furthermore, the upper end face of the base collar is provided with a rotatable rotating ring, the bottom surface of the rotating ring is fixedly connected with an annular guide protrusion, the upper end face of the base collar is provided with a sliding groove that cooperates with the annular guide protrusion, a connecting spring is fixedly connected to the upper surface of the rotating ring, the upper end of the adjusting collar extends inward to form a convex edge, and the adjusting collar and the convex edge of the adjusting collar are fixedly connected.

[0017] In order to solve the technical problems of complex tooling, excessive time consumption, and difficulty in determining the relative positions during the assembly of the air intake casing, diffuser, and turbine guide vane of aero-engines in the above embodiments of this application, this application utilizes the "three-point plane fixing" principle to quickly align the centerlines of the three components of the air intake casing, diffuser, and guide vane, and complete the centering in one go. This eliminates the tedious steps of repeated adjustments relying on complex tooling in the traditional method. By reinforcing at three points, a stable load-bearing body is formed in all directions, reducing assembly time and eliminating complex positioning tooling, thus significantly improving the efficiency and reliability of aero-engine assembly. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the overall cross-sectional structure of one embodiment of this application;

[0020] Figure 2 This is a front view structural diagram of one embodiment of this application;

[0021] Figure 3 This is one embodiment of the present application. Figure 1 A magnified structural diagram of point A;

[0022] Figure 4 This is a schematic diagram of the overall structure of an adjustment shim assembly according to an embodiment of this application;

[0023] Figure 5 This is a front structural schematic diagram of an adjustment shim assembly according to an embodiment of this application;

[0024] Figure 6 This is a schematic diagram of the adjustment shim assembly according to an embodiment of this application during adjustment;

[0025] Figure 7 This is a plan view of the adjustment shim assembly according to an embodiment of this application during adjustment;

[0026] Figure 8 This is a schematic diagram of the internal structure of an adjustment shim assembly according to an embodiment of this application;

[0027] Figure 9 This is a cross-sectional structural diagram of an adjustment shim assembly according to an embodiment of this application.

[0028] In the diagram: 1. Intake casing; 2. Diffuser; 3. Guide; 4. Fixing bolt; 5. Adjusting shim assembly; 6. Adjusting collar; 601. Support part; 602. Raised part; 603. Raised edge; 7. Base collar; 701. Support groove; 702. Concave part; 8. Rotating ring; 801. Annular guide protrusion; 9. Connecting spring; 10. Positioning hole group; 11. Reinforcing hole group. Detailed Implementation

[0029] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0030] Please see Figure 1 and Figure 2 As shown, a quick-connect structure for aero-engine with three-point positioning and three-point reinforcement includes an intake casing 1, a diffuser 2, a guide 3, multiple sets of circumferentially distributed fixing bolts 4, and an adjusting shim assembly 5.

[0031] The intake casing 1, diffuser 2 and guide 3 are fastened together in series by the fixing bolts 4 and the adjusting shim assembly 5;

[0032] The adjusting shim assembly 5 is composed of an adjusting collar 6 and a base collar 7.

[0033] This application adopts the "three-point plane" principle, which can quickly align the centerlines of the three components, namely the intake casing, diffuser, and guide vane, and complete the centering in one go. This eliminates the tedious steps of repeated adjustments relying on complex tooling in the traditional method. By reinforcing the three points, a stable load-bearing body is formed in all directions, reducing assembly time. At the same time, it eliminates the need for complex positioning tooling, significantly improving the efficiency and reliability of aero-engine assembly.

[0034] As a preferred technical solution, please refer to Figure 2 As shown, six mounting holes are evenly distributed circumferentially on the intake casing 1, diffuser 2, and guide 3. Three mounting holes serve as a positioning hole group 10, and the other three serve as a reinforcement hole group 11. This technical solution divides the functions of the mounting holes: the three positioning hole groups are used for initial precise alignment and centering, ensuring the coincidence of the axis lines of the three core components; the other three reinforcement hole groups are used to provide the main fastening force after positioning, forming a step-by-step operation of "positioning first, then reinforcement," thereby effectively avoiding mutual interference and component stress deformation caused by simultaneously tightening all bolts in traditional assembly.

[0035] As a further technical solution, the six mounting holes are evenly distributed on the circumference; the three holes in the positioning hole group 10 and the three holes in the reinforcing hole group 11 are staggered on the circumference. This technical solution ensures that the positioning points and reinforcing points are evenly distributed on the circumference, forming a symmetrical and balanced force distribution pattern. The staggered arrangement ensures that the load acting on the component connection surface is evenly distributed during fastening and engine operation, effectively preventing local deformation or loosening caused by concentrated force, thereby improving the stability of the connection and the structural rigidity.

[0036] Furthermore, the central angle between any two adjacent holes in the positioning hole group 10 is 120°, and the central angle between any two adjacent holes in the reinforcing hole group 11 is also 120°. Moreover, the positioning hole group 10 and the reinforcing hole group 11 are 60° apart on the circumference. Through this technical solution, an equilateral triangle distribution is achieved, that is, the positioning point and the reinforcing point each form an equilateral triangle, and the two triangles are completely intersecting. Through the above-mentioned "double triangle" distribution, a highly symmetrical constraint positioning effect can be provided.

[0037] For specific technical solutions, please refer to Figure 4 and Figure 6 As shown, the adjusting collar 6 and the base collar 7 are slidably sleeved together. The bottom of the adjusting collar 6 is provided with a protrusion forming a support part 601, and the arc surface of the base collar 7 is provided with a recess forming a support groove 701. The support part 601 extends into the support groove 701. Through this technical solution, the sliding of the support part 601 in the support groove 701 converts the rotational motion of the adjusting collar 6 into axial linear motion, thereby realizing the adjustment of the gap.

[0038] As a preferred technical solution, such as Figure 5 and Figure 7 As shown, in order to achieve the function of adjusting the overall thickness of the shim assembly 5, the support groove 701 has a stepped structure. Through this technical solution, the stepped support groove 701 provides precise stroke limits and multiple predetermined support planes for the axial movement of the support part 601; when the support part 601 moves from the first step to the next step, the overall thickness of the shim assembly changes, realizing a continuous fine-tuning function, thereby enabling the shim assembly of this application to adapt to a wider range of assembly gap errors and making it more versatile.

[0039] As a specific technical solution, the bottom of the support part 601 is provided with a convex part 602, and the stepped surface of the support groove 701 is provided with a concave part 702. Through this technical solution, the arc surfaces of the convex part 602 and the concave part 702 cooperate to form a good contact stress distribution and reduce local wear. At the same time, this curved surface cooperation has a self-guiding effect, which enables the support part 601 to automatically center when falling into the step, ensuring uniform force. Furthermore, after tightening the bolts, it can produce a certain self-locking effect to prevent accidental rotation in a vibration environment and improve the stability after adjustment.

[0040] Furthermore, to ensure stability after adjustment, three support parts 601 are provided, equidistantly distributed around the circumference of the adjusting collar 6, and three support grooves 701 are provided, equidistantly distributed on the arc surface of the base collar 7. Through this technical solution, the three evenly distributed support parts and support grooves constitute a stable three-point support structure. As is generally known, three points define a plane, thus ensuring that the adjusting collar 6 remains parallel to the base collar 7 during adjustment and stress application, avoiding overturning moments that may occur with unilateral or bilateral support, and ensuring uniform load transfer and overall rigidity of the connection.

[0041] For a preferred technical solution, please refer to Figure 8 and Figure 9 As shown, a rotatable rotating ring 8 is provided on the upper end face of the base collar 7. An annular guide protrusion 801 is fixedly connected to the bottom surface of the rotating ring 8. A sliding groove that mates with the annular guide protrusion 801 is provided on the upper end face of the base collar 7. A connecting spring 9 is fixedly connected to the upper surface of the rotating ring 8. The upper end of the adjusting collar 6 extends inward to form a raised edge 603. The adjusting collar 6 and the raised edge 603 are fixedly connected. Through this technical solution, the rotating ring 8 applies a continuous axial preload to the adjusting collar 6 through the connecting spring 9. This preload causes the support part 601 to always have a downward tendency, thereby pressing it tightly against the stepped surface of the support groove 701, forming an anti-loosening structure; avoiding frequent relative rotation during adjustment, thus achieving a self-locking function after adjustment.

[0042] The specific assembly process for this application must follow the principle of "positioning first, then reinforcement," and the specific steps are as follows:

[0043] A. Clean the connecting surfaces and all mounting holes of the intake casing 1, diffuser 2, and guide 3, ensuring they are free of oil and burrs; fix the intake casing 1 to the assembly station and calibrate its reference; hoist the diffuser 2 and guide 3 in sequence, so that the six mounting holes on them are initially aligned with the corresponding mounting holes on the intake casing 1; temporary locating pins can be used to assist in the initial fixation.

[0044] B. Select three mounting holes arranged in an equilateral triangle (central angles of 120° to each other) as positioning hole group 10; place adjusting shim assembly 5 on the bolt connection path of each positioning hole group 10. At this time, the adjusting collar 6 and the base collar 7 are in the initial unadjusted position. Pass the fixing bolt 4 through the above assembly and initially tighten the nut, but do not tighten it. At this time, the three positioning points have formed a stable reference plane, which initially constrains the relative positions of the three components;

[0045] C. Measure the gap and parallelism between components. By rotating the adjusting collar 6, the support part 601 is driven to move within the stepped support groove 701. At this time, the thickness of the gasket assembly changes, realizing fine adjustment of the gap; repeat this operation until the gap is uniform and meets the design requirements.

[0046] D. After the gap adjustment is qualified, use a torque wrench to pre-tighten the nuts on the three positioning points in steps to 30%-50% of the specified torque to ensure that the position of the component is initially locked after fine adjustment.

[0047] E. Select three other mounting holes that are staggered with the positioning point as the reinforcement hole group 11. Install the remaining fixing bolts 4 and adjusting shim assembly 5 in the same way. Tighten the nuts on the reinforcement points to the specified torque in a diagonal sequence.

[0048] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A quick-connect structure for aero-engines with three-point positioning and three-point reinforcement, characterized in that: It includes an intake casing (1), a diffuser (2), a guide (3), multiple sets of circumferentially distributed fixing bolts (4), and an adjusting shim assembly (5); The intake casing (1), diffuser (2) and guide (3) are fastened in series by the fixing bolts (4) and adjusting shim assembly (5); The adjusting shim assembly (5) is composed of an adjusting collar (6) and a base collar (7).

2. The quick-connect structure for three-point positioning and three-point reinforcement of an aero-engine according to claim 1, characterized in that: The intake casing (1), diffuser (2) and guide (3) are provided with six mounting holes circumferentially distributed, of which three mounting holes are used as a positioning hole group (10) and the other three mounting holes are used as a reinforcement hole group (11).

3. The quick-connect structure for three-point positioning and three-point reinforcement of aero-engines according to claim 2, characterized in that: The six mounting holes are evenly distributed on the circumference; the three holes in the positioning hole group (10) and the three holes in the reinforcing hole group (11) are staggered on the circumference.

4. The quick-connect structure for three-point positioning and three-point reinforcement of an aero-engine according to claim 3, characterized in that: The central angle between any two adjacent holes in the positioning hole group (10) is 120°, and the central angle between any two adjacent holes in the reinforcing hole group (11) is also 120°. The positioning hole group (10) and the reinforcing hole group (11) are 60° apart on the circumference.

5. The quick-connect structure for three-point positioning and three-point reinforcement of an aero-engine according to claim 1, characterized in that: The adjusting collar (6) and the base collar (7) are slidably sleeved together. The bottom of the adjusting collar (6) is provided with a protrusion forming a support part (601), and the arc surface of the base collar (7) is provided with a recess forming a support groove (701). The support part (601) extends into the support groove (701).

6. The quick-connect structure for three-point positioning and three-point reinforcement of an aero-engine according to claim 5, characterized in that: The support groove (701) has a stepped structure.

7. The quick-connect structure for three-point positioning and three-point reinforcement of an aero-engine according to claim 5, characterized in that: The bottom of the support part (601) is provided with a convex part (602), and the stepped surface of the support groove (701) is provided with a concave part (702).

8. The quick-connect structure for three-point positioning and three-point reinforcement of an aero-engine according to claim 6, characterized in that: The support part (601) is provided in three parts, which are equidistantly distributed around the circumference of the adjusting collar (6), and the support groove (701) is provided in three parts, which are equidistantly distributed on the arc surface of the base collar (7).

9. The quick-connect structure for three-point positioning and three-point reinforcement of an aero-engine according to claim 6, characterized in that: The upper end face of the base collar (7) is provided with a rotatable rotating ring (8), and a connecting spring (9) is fixedly connected to the upper surface of the rotating ring (8). The upper end of the adjusting collar (6) extends inward to form a convex edge (603), and the adjusting collar (6) is fixedly connected to the convex edge (603) of the adjusting collar (6).

10. The quick-connect structure for three-point positioning and three-point reinforcement of an aero-engine according to claim 9, characterized in that: The bottom surface of the rotating ring (8) is fixedly connected with an annular guide protrusion (801), and the upper end surface of the base collar (7) is provided with a sliding groove that cooperates with the annular guide protrusion (801).

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