Snap spring mounting method and structure for high-pressure compressor of aero-engine

Abstract

The invention belongs to the field of aero-engine design, and particularly relates to a clamp spring mounting method and structure for an aero-engine high-pressure compressor, and the clamp spring mounting structure comprises a sleeve, a pushing mechanism, a cone and a protective cover. The cone is inserted into the protecting cover; the pushing mechanism comprises a rotating rod, a rear cover, a pushing rod and a pushing plate; the rear cover is correspondingly arranged at the rear end of the sleeve, and a thin-wall structure is arranged at the front end of the sleeve. The rotating rod is connected with the rear cover through a nut, the rotating rod is connected with the sleeve through threads, the cone and the rotating rod are coaxially arranged, the cone is installed on a front end hole of the sleeve, and the protecting cover is connected with the sleeve through threads. One end of each push rod is in threaded connection with the rear cover, the middle of each push rod is inserted into the sleeve, and the other end of each push rod is in threaded connection with the push plate. Through rapid sleeving of the sleeve and the bolt, pre-loading of the clamp spring by the cone and driving and pushing of the rotating rod, the installation time of a single clamp spring is shortened to be within 10 seconds, one-hand operation is supported, and manpower consumption and time cost are greatly reduced.

Description

Technical Field

[0001] This application belongs to the field of aero-engine design, and specifically relates to a method and structure for installing snap rings for high-pressure compressors of aero-engines. Background Technology

[0002] Snap rings, as an axial locking mechanism, are commonly used for axial positioning of bolts under high load and high speed conditions. During the assembly of a certain type of engine, installing snap rings requires one person to hold the bolt head with one hand while using the other to thread the snap ring through the bolt threads and install it into the bolt's slot; or one person to hold the bolt head while another threaded the snap ring through the bolt threads and installed it into the bolt's slot. This installation process is inconvenient, inefficient, and prone to damaging the snap ring or causing improper installation. Improper installation of the snap ring can lead to anything from incorrect axial bolt positioning to bolt loosening and serious accidents.

[0003] Therefore, how to achieve quick and effective installation of snap rings is a problem that needs to be solved. Summary of the Invention

[0004] To address the aforementioned issues, this application provides a method and structure for installing snap rings in high-pressure compressors of aero engines, thereby resolving the problem of low snap ring installation efficiency in the prior art.

[0005] The technical solution of this application is: a method for installing a retaining ring for a high-pressure compressor of an aero-engine, comprising:

[0006] Fix the swivel rod to the rear cover with a nut, connect the push rod, push plate and rear cover with threads, engage the swivel rod with the rear end of the sleeve through a threaded hole, and fit the front end face of the push rod with the sleeve.

[0007] Install the cone to the thin-walled interface at the front end of the sleeve, and control the bottom circle of the cone's frustum to fit against the front end face of the thin-walled structure of the sleeve;

[0008] Multiple retaining rings are pushed onto the thin-walled structure at the front end of the sleeve using a cone. The cone is then removed, and the sleeve is installed onto the bolt to be assembled. The operator holds the sleeve, rotates the lever n times, pushes the retaining rings into the bolt's slot, and then removes the sleeve.

[0009] Install the sleeve onto the remaining bolts, and repeat the operation of lever 1 to install the specified number of retaining rings.

[0010] Preferably, the inner diameter of the sleeve front end hole is a, the outer diameter of the bolt is b, and a≥b is satisfied; the depth of the sleeve front end hole is c, the length of the bolt is d, and c≥d is satisfied.

[0011] Preferably, the length of the thin wall at the front end of the sleeve is e, which satisfies e=N*D, where N is the number of circlips loaded and D is the diameter of the circlips; the width of the sleeve is m, which satisfies m≤L, where L is the distance between two adjacent bolts.

[0012] Preferably, the tail diameter of the cone is g, satisfying a≥g; the top circle diameter of the frustum at the head of the cone is j, satisfying D1≥j, where D1 is the inner diameter of the snap ring in its free state; the bottom circle diameter of the cone is h, and the outer diameter of the front end of the sleeve is f, satisfying h≥f.

[0013] Preferably, the maximum distance between the back cover and the sleeve is l, and the length of the sleeve threaded hole that is not engaged with the swivel is k, requiring k≥l≥e; the pitch of the swivel is m, and the number of swivel rotations required to install the snap ring is n, so n=D / m.

[0014] Another technical solution of this application is: a snap ring mounting structure for a high-pressure compressor of an aero-engine, including a sleeve, a pushing mechanism, a sleeve, a cone, and a protective cover;

[0015] The cone is inserted into the cover, and the pushing mechanism includes a rotating rod, a rear cover, a push rod, and a push plate; the rear cover is correspondingly located at the rear end of the sleeve, and the front end of the sleeve is provided with a thin-walled structure;

[0016] The swivel rod is connected to the rear cover by a nut, the swivel rod is connected to the sleeve by a thread, the cone is coaxially arranged with the swivel rod, the cone is installed on the front end hole of the sleeve, and the protective cover is connected to the sleeve by a thread.

[0017] There are two push rods located on both sides of the rotating rod. One end of the push rod is threaded to the rear cover, the middle part is inserted into the sleeve, and the other end is threaded to the push plate.

[0018] The snap ring mounting method and structure for high-pressure compressors in aero engines disclosed in this application have the following advantages:

[0019] By using a quick-assembly sleeve and bolt, a pre-loaded snap ring on a cone, and a rotary drive, the installation time for a single snap ring is reduced to within 10 seconds, and it supports one-handed operation (simply hold the sleeve and rotate the rotary rod), significantly reducing manpower consumption and time costs.

[0020] It enables a single person to quickly, conveniently, and accurately install the snap ring into the bolt slot with one hand. It is safe, reliable, simple to operate, time-saving, labor-saving, highly efficient, and low in operating cost, and has broad application prospects. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the overall structure of this application;

[0022] Figure 2This is a schematic diagram of the assembly structure of the retaining ring and bolt in this application.

[0023] 1. Rotary rod; 2. Rear cover; 3. Nut; 4. Sleeve; 5. Push rod; 6. Push plate; 7. Cone; 8. Snap ring; 9. Bolt; 10. Protective cover. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0025] The first aspect of this application provides a snap ring mounting structure for a high-pressure compressor of an aero-engine, such as... Figures 1-2 It includes a sleeve 4, a pushing mechanism, a sleeve 4, a cone 7, and a cover 10.

[0026] The cone 7 is inserted into the cover 10. The pushing mechanism includes a rotating rod 1, a rear cover 2, a push rod 5 and a push plate 6. The rear cover 2 is located at the rear end of the sleeve 4, and the front end of the sleeve 4 is provided with a thin-walled structure.

[0027] The rotating rod 1 is connected to the rear cover 2 by a nut 3, and the rotating rod 1 is connected to the sleeve 4 by a thread. The cone 7 is coaxially arranged with the rotating rod 1 and is installed on the front end hole of the sleeve 4. The protective cover 10 is connected to the sleeve 4 by a thread.

[0028] There are two push rods 5 located on both sides of the rotating rod 1. One end of the push rod 5 is threaded to the rear cover 2, the middle part is inserted into the sleeve 4, and the other end is threaded to the push plate 6.

[0029] By designing the front end of the sleeve 4 as a thin-walled structure and the front end of the cone 7 as a frustum structure, the retaining ring 8 can be easily fitted onto the sleeve 4, and the thin-wall thickness ensures that no plastic deformation occurs during installation.

[0030] In use, the retaining ring 8 is positioned by the sleeve 4, and then the sleeve 4 is connected with the bolt 9 to be assembled. The retaining ring 8 is then screwed into the retaining groove by the rotating rod 1, thereby achieving quick and accurate installation of the retaining ring 8.

[0031] The second aspect of this application provides a method for mounting a retaining ring 8 for a high-pressure compressor in an aero-engine. Based on the above-mentioned mounting structure, the specific design is as follows:

[0032] Step 1: Fix the rotating rod 1 to the rear cover 2 with the nut 3, connect the push rod 5, push plate 6 and rear cover 2 with threads, and engage the rotating rod 1 with the rear end of the sleeve 4 through the threaded hole, and fit the front end face of the push rod 5 with the sleeve 4.

[0033] Step 2: Install the cone 7 to the thin-walled interface at the front end of the sleeve 4, and control the bottom circle of the cone 7 to fit with the front end face of the thin-walled structure of the sleeve 4.

[0034] Step 3: Push multiple retaining rings 8 onto the thin-walled structure at the front end of the sleeve 4 using the cone 7, remove the cone 7, and install the sleeve 4 onto the bolt 9 to be assembled; the operator holds the sleeve 4, rotates the rotating rod 1 n times, pushes the retaining rings 8 into the retaining groove of the bolt 9, and removes the sleeve 4.

[0035] Step 4: Install the sleeve 4 onto the remaining bolts 9, and repeat the operation of the rotating rod 11 to install the specified number of retaining rings 8.

[0036] Preferably, the inner diameter of the front end hole of the sleeve 4 is a, the outer diameter of the bolt 9 is b, and a≥b is satisfied; the depth of the front end hole of the sleeve 4 is c, and the length of the bolt 9 is d, and c≥d is satisfied.

[0037] Preferably, the length of the thin wall at the front end of the sleeve 4 is e, which satisfies e=N*D, where N is the number of circlips 8 loaded and D is the diameter of the circlips 8; the width of the sleeve 4 is m, which satisfies m≤L, where L is the distance between two adjacent bolts 9.

[0038] Preferably, the tail diameter of the cone 7 is g, satisfying a≥g; the top circle diameter of the frustum at the head of the cone 7 is j, satisfying D1≥j, where D1 is the inner diameter of the snap ring 8 in its free state; the bottom circle diameter of the cone 7 is h, and the outer diameter of the front end of the sleeve 4 is f, satisfying h≥f.

[0039] Preferably, the maximum distance between the back cover 2 and the sleeve 4 is l, and the length of the threaded hole of the sleeve 4 that is not engaged with the rotating rod 1 is k, requiring k≥l≥e; the pitch of the rotating rod 1 is m, and the number of rotations of the rotating rod 1 required to install the snap ring 8 is n, so n=D / m.

[0040] In summary, this application has the following advantages:

[0041] By using a quick-assembly sleeve and bolt, a pre-loaded snap ring on a cone, and a rotary drive, the installation time for a single snap ring is reduced to within 10 seconds, and it supports one-handed operation (simply hold the sleeve and rotate the rotary rod), significantly reducing manpower consumption and time costs.

[0042] It enables a single person to quickly, conveniently, and accurately install the snap ring into the bolt slot with one hand. It is safe, reliable, simple to operate, time-saving, labor-saving, highly efficient, and low in operating cost, and has broad application prospects.

[0043] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for installing a retaining ring (8) for a high-pressure compressor of an aero-engine, characterized in that, include; Fix the swivel rod (1) and the back cover (2) with the nut (3), connect the push rod (5), the push plate (6) and the back cover (2) with threads, and engage the swivel rod (1) with the rear end of the sleeve (4) through the threaded hole, and fit the front end face of the push rod (5) with the sleeve (4). Install the cone (7) to the thin-walled interface at the front end of the sleeve (4) and control the bottom circle of the cone (7) to fit with the front end face of the thin-walled structure of the sleeve (4); Multiple retaining rings (8) are pushed onto the thin-walled structure at the front end of the sleeve (4) by the cone (7), the cone (7) is removed, and the sleeve (4) is installed onto the bolt (9) to be assembled; the operator holds the sleeve (4), rotates the rotating rod (1) n times, pushes the retaining rings (8) to be installed into the retaining groove of the bolt (9), and removes the sleeve (4); Install the sleeve (4) onto the remaining bolts (9), repeat the operation of the rotating rod (1) 1, and install the specified number of snap rings (8).

2. The method for installing the retaining ring (8) for a high-pressure compressor of an aero-engine as described in claim 1, characterized in that, The inner diameter of the front end hole of the sleeve (4) is a, and the outer diameter of the bolt (9) is b, satisfying a≥b; the depth of the front end hole of the sleeve (4) is c, and the length of the bolt (9) is d, satisfying c≥d.

3. The method for installing the retaining ring (8) for a high-pressure compressor of an aero-engine as described in claim 1, characterized in that, The sleeve (4) has a thin wall length of e at the front end, which satisfies e=N*D, where N is the number of circlips (8) loaded and D is the diameter of the circlips (8); the sleeve (4) has a width of m, which satisfies m≤L, where L is the distance between two adjacent bolts (9).

4. The method for installing the retaining ring (8) for a high-pressure compressor of an aero-engine as described in claim 1, characterized in that, The tail diameter of the cone (7) is g, which satisfies a≥g; the top circle diameter of the frustum at the head of the cone (7) is j, which satisfies D1≥j, where D1 is the inner diameter of the snap ring (8) in its free state; the bottom circle diameter of the cone (7) is h, and the outer diameter of the front end of the sleeve (4) is f, which satisfies h≥f.

5. The method for installing the retaining ring (8) for a high-pressure compressor of an aero-engine as described in claim 1, characterized in that, The maximum distance between the back cover (2) and the sleeve (4) is l. At this time, the length of the threaded hole of the sleeve (4) that is not engaged with the swivel rod (1) is k, and k≥l≥e is required. The pitch of the swivel rod (1) is m, and the number of rotations of the swivel rod (1) required to install the snap ring (8) is n, so n=D / m.

6. A retaining ring (8) mounting structure for a high-pressure compressor of an aero-engine, characterized in that: Includes a sleeve (4), a pushing mechanism, a sleeve (4), a cone (7), and a cover (10); The cone (7) is inserted into the cover (10). The pushing mechanism includes a rotating rod (1), a rear cover (2), a push rod (5), and a push plate (6). The rear cover (2) is located at the rear end of the sleeve (4), and the front end of the sleeve (4) is provided with a thin-walled structure. The swivel rod (1) is connected to the rear cover (2) by a nut (3), the swivel rod (1) is connected to the sleeve (4) by a thread, the cone (7) is coaxially arranged with the swivel rod (1), the cone (7) is installed on the front end hole of the sleeve (4), and the protective cover (10) is connected to the sleeve (4) by a thread. There are two push rods (5) located on both sides of the rotating rod (1). One end of the push rod (5) is threaded to the rear cover (2), the middle part is inserted into the sleeve (4), and the other end is threaded to the push plate (6).

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