Aeroturbine bearing seat assembly axial movement measuring device

Abstract

The utility model discloses an aviation turbine bearing seat assembly axial movement measuring device. The device comprises a pull rod, a left thrust chuck, a right thrust chuck, a gasket and a locking nut. The left thrust chuck and the right thrust chuck are inserted into the axial left end and the axial right end of the bearing seat assembly respectively, then the left thrust chuck, the right thrust chuck and the bearing seat assembly are fastened into a whole through the pull rod, the gasket and the locking nut, and finally the left thrust chuck, the right thrust chuck and the bearing seat assembly are used for testing the axial displacement. The device is high in concentricity, is not liable to loosen, can accurately measure the axial displacement relative to the housing assembly, is simple and rapid in operation process, avoids repeated cold mounting of a turbine impeller, a gas compressor impeller, a bearing and a shaft, and improves the detection precision. Therefore, an accurate basis is provided for solving the technical problems of bearing abrasion, heating, overlarge noise and the like caused by overlarge or oversmall axial displacement of the existing turbine product.

Description

Technical Field

[0001] The utility model relates to the measurement of the axial movement of the bearing of an aviation turbine product, in particular to a device for measuring the axial movement of a bearing seat assembly in an aviation turbine. Background Art

[0002] like Figure 7 As shown, an aviation turbine product is mainly composed of a turbine volute 12, a turbine impeller 13, a fairing window 14, an air baffle 15, a housing assembly 16, a bearing seat assembly 17, a diffuser 18, a compressor impeller 19 and a compressor housing 20. The bearing 21 is mounted on the shaft 22 and then assembled inside the bearing seat assembly 17. The bearing seat assembly 17 is mounted inside the housing assembly 16. The turbine impeller 13 and the compressor impeller 19 are respectively mounted at both ends of the shaft 22. After the complete flow window 14 and the diffuser 18 are assembled inside the turbine volute 12 and the compressor housing 20, they are respectively mounted on the outside of the turbine impeller 13 and the compressor impeller 19 and connected to the housing assembly 16. During the actual assembly process, the axial assembly clearance between the housing assembly 16 and the bearing seat assembly 17 has the greatest impact on the axial movement of the turbine during operation. Once the axial clearance between the housing assembly 16 and the bearing seat assembly 17 does not meet the requirements, collision will occur, resulting in severe axial wear and affecting the engine power output, causing large vibrations and other problems. Therefore, correct measurement is required.

[0003] At present, the limitations and complexity of measuring the axial movement of aviation turbine products are mainly reflected in the lack of specific detection equipment. When measuring, the components need to be disassembled repeatedly, and then the axial clearance distance of the bearings needs to be ensured by installing adjustment gaskets. This adjustment process is very time-consuming and difficult to operate. For example, the turbine impeller 13 and the compressor impeller 19 need to be cold-installed on the shaft 22. If they are repeatedly disassembled and assembled, the process will be very difficult. For the above reasons, it is necessary to design a turbine product axial movement measurement device to solve the above problems. Among them, the axial movement measurement device needs to overcome the following three problems:

[0004] 1. The measuring device as a whole must have high concentricity;

[0005] 2. The measuring device is not easy to loosen after repeated disassembly and installation;

[0006] 3. The measuring device is not easily damaged or worn when subjected to axial load and has a long service life. Summary of the invention

[0007] In response to the problems recorded in the background technology, the utility model aims to provide an axial movement measuring device for an aviation turbine bearing seat assembly, which has high concentricity with the bearing seat assembly and is not easy to loosen. It can accurately measure the axial movement of the relative housing assembly, and the operation process is simple and quick, avoiding repeated cold installation of turbine impellers, compressor impellers, bearings and shafts.

[0008] In order to solve the above problems, the utility model adopts the following technical solutions:

[0009] An axial movement measurement device for an aviation turbine bearing seat assembly comprises a pull rod, a left thrust chuck, a right thrust chuck, a gasket and a locking nut, wherein:

[0010] The left thrust chuck is a disc with an axial through hole, and the left thrust chuck has at least two different outer diameters, and an annular step surface perpendicular to the axial direction of the left thrust chuck is formed at the outer diameter change position, and the outer diameter gradually decreases along the axial direction of the left thrust chuck;

[0011] The right thrust chuck is a disc with an axial through hole, and the right thrust chuck has at least two different outer diameters, where the outer diameter changes to form an annular step surface perpendicular to the axial direction of the right thrust chuck, and the outer diameter gradually decreases along the axial direction of the right thrust chuck;

[0012] The pull rod is a stepped shaft with at least three different outer diameters, and the outer diameter gradually decreases from the first axial end to the second axial end, the outer diameter of one of the three places is equal to the diameter of the axial through holes on the left thrust chuck and the right thrust chuck, and an annular step surface perpendicular to the axial direction of the pull rod is formed at the place where the outer diameter changes, and the surface of the second axial end of the pull rod is processed with an external thread, and the pull rod passes through the axial through holes of the left thrust chuck and the right thrust chuck at the same time;

[0013] The washer and the locking nut are sleeved on the pull rod, and the washer is located between the axial end surface of the locking nut and the axial end surface of the right thrust chuck away from the left thrust chuck.

[0014] Furthermore, a pulling circular hole is formed at the first axial end and the second axial end of the pull rod.

[0015] Furthermore, the multiple different outer diameters of the left thrust chuck and the right thrust chuck include an outer diameter that is consistent with the diameter of the inner hole of the bearing seat assembly.

[0016] Compared with the prior art, the axial movement measurement device of the aluminum aviation turbine bearing seat assembly of the utility model has the following characteristics:

[0017] 1. The measuring device effectively simulates the assembly relationship of the turbine impeller, compressor impeller, shaft and bearing in the bearing seat assembly, so that the axial movement of the bearing seat assembly can be measured under the premise of close to the real assembly relationship, which helps to accurately measure the axial movement value;

[0018] 2. The measuring device and the bearing seat assembly are concentric through the circumferential outer surface of the left thrust chuck and the right thrust chuck; 3. The measuring device and the bearing seat assembly are integrated through the axial end surfaces of the left thrust chuck and the right thrust chuck and the threads on the locking nut, gasket and pull rod, which is convenient for subsequent movement measurement, avoids the complicated operation of cold assembly of real turbine impellers, compressor impellers, shafts and bearings, and reduces the difficulty of measurement;

[0019] 4. In the measuring device, the annular step surfaces of the left thrust chuck and the right thrust chuck interact with the bearing seat assembly to evenly transmit the axial load;

[0020] 5. By opening holes at both ends of the pull rod to facilitate the application of load, the traditional method of transferring load through threaded connection is eliminated, the wear on the thread is reduced, and the service life of the measuring device is extended. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of a device for measuring the axial movement of an aviation turbine bearing seat assembly;

[0022] Figure 2 It is a diagram of the pull rod;

[0023] Figure 3 It is a schematic diagram of the left thrust chuck;

[0024] Figure 4 It is a schematic diagram of the right thrust chuck;

[0025] Figure 5 is a schematic diagram of the gasket;

[0026] Figure 6 It is a schematic diagram of the locking nut;

[0027] Figure 7 It is a schematic diagram of the structure of aviation turbine products;

[0028] In the figure: 1-tie rod; 2-left thrust chuck; 3-right thrust chuck; 4-gasket; 5-locking nut; 12-turbine volute; 13-turbine impeller; 14-rectifier window; 15-air baffle; 16-housing assembly; 17-bearing seat assembly; 18-diffuser; 19-compressor impeller; 20-compressor housing; 21-bearing; 22-mounted on the shaft. DETAILED DESCRIPTION

[0029] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to the common technical knowledge and customary means in the field are included in the scope of the present invention.

[0030] like Figure 1 to Figure 6 As shown, the axial movement measurement device of the aviation turbine bearing seat assembly designed in this embodiment includes a pull rod 1, a left thrust chuck 2, a right thrust chuck 3, a gasket 4 and a locking nut 5, wherein: the left thrust chuck 2 is a disc with an axial through hole, and the left thrust chuck 2 has two different outer diameters, and the outer diameter changes to form an annular step surface perpendicular to the axial direction of the left thrust chuck 2, and the outer diameter gradually decreases along the axial direction of the left thrust chuck 2. The right thrust chuck 3 is a disc with an axial through hole, and the right thrust chuck 3 has three different outer diameters, and the outer diameter changes to form an annular step surface perpendicular to the axial direction of the right thrust chuck 3, and the outer diameter gradually decreases along the axial direction of the right thrust chuck 3. Among the multiple different outer diameters of the left thrust chuck 2 and the right thrust chuck 3, one outer diameter is consistent with the inner hole diameter of the bearing seat assembly 17. The pull rod 1 is a stepped shaft with three different outer diameters, and the outer diameter gradually decreases from the first axial end to the second axial end. The outer diameter at the middle position is equal to the diameter of the axial through holes on the left thrust chuck 2 and the right thrust chuck 3. An annular step surface perpendicular to the axial direction of the pull rod 1 is formed at the outer diameter change position. The surface of the second axial end of the pull rod 1 is processed with an external thread. The pull rod 1 passes through the axial through holes of the left thrust chuck 2 and the right thrust chuck 3 at the same time. The first axial end and the second axial end of the pull rod 1 are both provided with a pulling circular hole. The washer 4 and the locking nut 5 are sleeved on the pull rod 1, and the washer 4 is located between the axial end face of the locking nut 5 and the axial end face of the right thrust chuck 3 away from the left thrust chuck 2.

[0031] like Figure 1 When in use, insert the pull rod 1 from the large outer diameter end of the left thrust chuck 2 until the annular step surface and axial end surface of the two fit together, and insert the assembled pull rod 1 from the corresponding power turbine end of the bearing seat assembly 17 (i.e., the turbine impeller 13 side) until the annular step surface of the left thrust chuck 2 fits with the axial end surface of the bearing seat assembly 17; assemble the small outer diameter end of the right thrust chuck 3 to the refrigeration turbine end of the bearing seat assembly 17 (i.e., the compressor impeller 19 side) until the annular step surface of the right thrust chuck 3 fits with the axial end surface of the bearing seat assembly 17; then insert the gasket 4 and the locking nut 5 into the threaded part of the pull rod 1 in turn and assemble them, use heavy blocks to pull the pulling holes at both ends of the pull rod 1 respectively, pull the pull rod 1 in turn, and measure the axial movement value of the bearing seat assembly 17 relative to the housing assembly 16.

[0032] The following steps are included when the above-mentioned measuring device is used to measure the axial movement of the aircraft turbine bearing seat assembly:

[0033] Step 1: Insert the pull rod 1 from the end with the largest outer diameter of the left thrust chuck 2 into the axial through hole until the annular step surface on the pull rod 1 fits with the axial end surface of the left thrust chuck 2;

[0034] Step 2: Remove the pull rod 1 and the left thrust chuck 2 assembled in step 1 from the bearing seat assembly 17 corresponding to the end of the power turbine (i.e. corresponding to the end of the power turbine Figure 7 The left thrust chuck 2 is inserted into the inner hole of the bearing seat assembly 17 until the outer cylindrical surface of the small outer diameter end of the left thrust chuck 2 is inserted into the inner hole of the bearing seat assembly 17 and the annular step surface of the left thrust chuck 2 is in contact with the axial end surface of the bearing seat assembly 17;

[0035] Step 3: Remove the right thrust chuck 3 from the end of the bearing seat assembly 17 corresponding to the refrigeration turbine (i.e. Figure 7 The right thrust chuck 3 is inserted into the inner hole of the bearing seat assembly 17 until the outer surface of the small outer diameter end of the right thrust chuck 3 is inserted into the inner hole of the bearing seat assembly 17 and the annular step surface of the right thrust chuck 3 is in contact with the axial end surface of the bearing seat assembly 17;

[0036] Step 4: insert the gasket 4 and the locking nut 5 into the tie rod 1 from the end of the right thrust chuck 3 away from the bearing seat assembly 17 in sequence, and assemble and tighten the locking nut 5 on the external thread of the tie rod 1, so that the tie rod 1, the left thrust chuck 2, the right thrust chuck 3, the gasket 4, the locking nut 5 and the bearing seat assembly 17 form a whole;

[0037] Step five, fix the housing assembly 16 on the test bench in a vertical state according to the axis, then put the measuring device and bearing seat assembly 17 assembled in step four into the housing assembly 16 as a whole, bind a weight that meets the axial load at the pulling circular hole at the axial first end of the pulling rod 1, observe and measure the axial movement of the bearing seat assembly 17 relative to the housing assembly 16, after completion, remove the weight, take out the measuring device and the bearing seat assembly 17, then turn them over 180° and put them into the housing assembly 16 as a whole again, bind a weight that meets the axial load at the pulling circular hole at the axial second end of the pulling rod 1, observe and measure the axial movement value.

[0038] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A device for measuring the axial movement of an aviation turbine bearing seat assembly, characterized in that: It comprises a pull rod (1), a left thrust chuck (2), a right thrust chuck (3), a gasket (4) and a locking nut (5), wherein: The left thrust chuck (2) is a disc with an axial through hole. The left thrust chuck (2) has at least two different outer diameters. The outer diameter change position forms an annular step surface perpendicular to the axial direction of the left thrust chuck (2), and the outer diameter gradually decreases along the axial direction of the left thrust chuck (2). The right thrust chuck (3) is a disc with an axial through hole. The right thrust chuck (3) has at least two different outer diameters. The outer diameter change position forms an annular step surface perpendicular to the axial direction of the right thrust chuck (3), and the outer diameter gradually decreases along the axial direction of the right thrust chuck (3). The pull rod (1) is a stepped shaft having at least three different outer diameters, and the outer diameter gradually decreases from the first axial end to the second axial end, the outer diameter of one of the three places being equal to the diameter of the axial through holes on the left thrust chuck (2) and the right thrust chuck (3), and an annular step surface perpendicular to the axial direction of the pull rod (1) is formed at the place where the outer diameter changes, and the surface of the second axial end of the pull rod (1) is processed with an external thread, and the pull rod (1) simultaneously passes through the axial through holes of the left thrust chuck (2) and the right thrust chuck (3); The gasket (4) and the locking nut (5) are sleeved on the pull rod (1), and the gasket (4) is located between the axial end surface of the locking nut (5) and the axial end surface of the right thrust chuck (3) away from the left thrust chuck (2).

2. The device for measuring the axial movement of an aircraft turbine bearing seat assembly according to claim 1, characterized in that: The pull rod (1) has a first axial end and a second axial end formed with a pulling circular hole.

3. The device for measuring the axial movement of an aircraft turbine bearing seat assembly according to claim 1, characterized in that: The multiple different outer diameters of the left thrust chuck (2) and the right thrust chuck (3) include an outer diameter that is consistent with the inner hole diameter of the bearing seat assembly (17).

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