Aero-engine bearing pre-tightening force testing device

Abstract

The utility model discloses an aero-engine bearing pre -tightening force testing arrangement relates to aero-engine accessory processing technical field. An aero-engine bearing pre -tightening force testing arrangement, include: base, pressing piece, table stand, dial gauge, standard gauge block, shackle and counterweight. The utility model has simulated the actual working condition of aero-engine angular contact ball bearing through simple mechanical structure, utilizes counterweight to accurately exert design pre -tightening force, and combines dial gauge and standard gauge block measuring system, can accurately calculate the residual thickness of pre -tightening force bearing element under design load, and this result provides direct, reliable quantitative basis for subsequent control pre -tightening force bearing element's compression deformation thickness to accurately control bearing's final assembly pre -tightening force.

Description

Technical Field

[0001] This utility model relates to the field of aero-engine parts processing technology, specifically to an aero-engine bearing preload testing device. Background Technology

[0002] As a type of gas turbine engine, the core rotor structure of an aero turbojet engine consists of a compressor impeller and a turbine. The rotor generates an axial airflow pressure difference through high-speed rotation, achieving stable compression, combustion, and expansion of the incoming airflow. This ultimately produces high-temperature, high-pressure gas that is ejected from the exhaust nozzle, generating reaction thrust. Therefore, stable rotor operation is crucial to ensuring the overall performance and reliability of the engine.

[0003] The stable operation of a rotor largely depends on the stable load-bearing capacity of its bearings, and the performance and lifespan of the bearings directly limit the service life of the engine rotor. This is particularly evident in engines with multi-shaft rotor structures. Among the many types of bearings, angular contact ball bearings have become the preferred choice for aero-engine bearing design due to their ability to simultaneously withstand axial and radial loads, as well as their advantages such as high precision, self-aligning, low frictional resistance, low cost, and adaptability to high-speed operation.

[0004] To ensure the performance of angular contact ball bearings, a tight fit must be maintained between the inner and outer rings and the balls during assembly. In engineering practice, this is typically achieved by applying an axial preload. Common preload-bearing elements include disc springs, wave springs, helical springs, and ring springs. However, the magnitude of the preload has a decisive impact on the bearing's lifespan and reliability: insufficient or excessive preload can trigger a chain reaction leading to performance degradation and catastrophic failure.

[0005] Therefore, precise measurement and control of bearing preload is a core technical aspect for improving the operational stability and reliability of aero-engines. Currently, there is a lack of a device capable of directly and accurately measuring the compression state of preload-bearing components under simulated actual operating loads. Solving this problem is an urgent issue for those skilled in the art.

[0006] The information disclosed in this background section is intended only to enhance the understanding of the overall background of this utility model and should not be construed as an admission or in any way implying that the information constitutes prior art known to those skilled in the art. Utility Model Content

[0007] To address the aforementioned technical problems, this utility model provides an aero-engine bearing preload testing device to solve the problems mentioned in the background section.

[0008] This utility model provides the following technical solution: a test device for the preload force of an aero-engine bearing, comprising: a base, a pressure piece, a gauge holder, a dial indicator, a standard gauge block, a hook ring, and a counterweight; The base includes a cylindrical body and an annular plate fixedly connected to the outer edge of the upper end of the cylindrical body; a sealing plate is fixedly connected to the bottom of the cylindrical body, and a movable hole is opened in the middle of the sealing plate. The dial indicator frame is fixedly connected to the circular plate; the dial indicator is vertically mounted on the frame. The pressure component includes a cylindrical pressure block and a pressure rod fixedly connected to the bottom of the cylindrical pressure block; The cylindrical pressure block is movably fitted into the inner cavity of the cylinder; the pressure rod vertically passes through the movable hole on the sealing plate. The hook and ring are connected to the bottom of the pressure bar; the counterweight is connected to the hook and ring. The standard gauge block is placed on top of the cylindrical pressure block and below the dial indicator measuring head.

[0009] Preferably, a level is provided on the annular plate.

[0010] Preferably, the dial indicator frame is Z-shaped; the base plate of the Z-shaped dial indicator frame is fixedly connected to the annular plate; the dial indicator is vertically mounted on the top plate of the Z-shaped dial indicator frame.

[0011] The bottom of the inner cavity of the cylinder is used to place the preload bearing element; the cylindrical pressure block is pressed on top of the preload bearing element, and the pressure rod passes through the shaft hole of the preload bearing element.

[0012] Preferably, the preload bearing element includes one of a disc spring, a wave spring, a helical spring, and a ring spring.

[0013] The present invention provides an aero-engine bearing preload testing device with the following advantages: The present invention simulates the actual working conditions of an aero-engine angular contact ball bearing through a simple mechanical structure. By using a counterweight to accurately apply the designed preload, and combining a dial indicator and a standard gauge block measurement system, the remaining thickness of the preload bearing element under the design load can be accurately calculated. This result provides a direct and reliable quantitative basis for subsequently controlling the final assembly preload of the bearing by controlling the compression deformation thickness of the preload bearing element. Attached Figure Description

[0014] Figure 1 This is a structural schematic diagram of the present invention from angle one; Figure 2 This is a schematic diagram of the structure of this utility model from angle two; Figure 3 This is a cross-sectional structural diagram of the present invention; Figure 4 A schematic diagram showing the cross-sectional effect of a preload-bearing element assembled in an angular contact ball bearing. Detailed Implementation

[0015] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0016] See Figures 1-4 To address the problems mentioned in the background section, this utility model provides an aero-engine bearing preload testing device to solve the aforementioned technical problems. The technical solution is as follows: An aero-engine bearing preload testing device includes: a base 150, a pressure piece, a gauge holder 120, a dial indicator 110, a standard gauge block 130, a hook 170, and a counterweight 180. The base 150 includes a cylindrical body 152 and an annular plate 151 fixedly connected to the outer edge of the upper end of the cylindrical body 152; a sealing plate is fixedly connected to the bottom of the cylindrical body 152, and a movable hole is opened in the middle of the sealing plate. The dial indicator 120 is fixedly connected to the annular plate 151; the dial indicator 110 is vertically mounted on the dial indicator 120. The pressure component includes a cylindrical pressure block 162 and a pressure rod 161 fixedly connected to the bottom of the cylindrical pressure block 162; The cylindrical pressure block 162 is movably sleeved in the inner cylinder cavity 153 of the cylinder body 152; the pressure rod 161 vertically passes through the movable hole on the sealing plate; Hook 170 is connected to the bottom of pressure bar 161; counterweight 180 is connected to hook 170; The standard gauge block 130 is movably placed on top of the cylindrical pressure block 162 and located below the measuring head of the dial indicator 110.

[0017] In this embodiment, a level 140 is provided on the annular plate 151.

[0018] In this embodiment, the meter holder 120 is Z-shaped; the base plate of the Z-shaped meter holder 120 is fixedly connected to the annular plate 151; the dial gauge 110 is vertically mounted on the top plate of the Z-shaped meter holder 120.

[0019] In this embodiment, the bottom of the inner cylinder cavity 153 of the cylinder 152 is used to place the preload bearing element 190; the cylindrical pressure block 162 is pressed on the preload bearing element 190, and the pressure rod 161 passes through the shaft hole of the preload bearing element 190.

[0020] In this embodiment, the preload bearing element 190 includes one of a disc spring, a wave spring, a helical spring, and a ring spring.

[0021] Figure 4 The image shown is a schematic cross-sectional view of the preload bearing element 190 assembled in an angular contact ball bearing. Figure 4 The components include: 210 shaft; 220 angular contact ball bearing; 230 support ring; 240 adjusting shim; 250 bearing support.

[0022] The method for performing a test on the aero-engine bearing preload testing device provided in this embodiment of the invention is as follows: (1) Base fixing and leveling: Fix the base 150 with an independent bracket (or other fixed structure) to ensure the overall position of the base is stable. Observe the bubble state of the level 140 on the annular plate 151, and adjust the bracket or base support point to make the base 150 level, so as to avoid affecting the measurement accuracy due to tilt.

[0023] (2) Placement of preload bearing element: Select a preload bearing element 190 that matches the actual application; according to the actual assembly state of the aero-engine bearing, place the preload bearing element 190 at the bottom of the inner cavity 153 of the cylinder 152 to ensure that the element is placed in the center without deviation.

[0024] (3) Installation and friction control of the pressure components: Assemble the pressure components in place: make the cylindrical pressure block 162 movably sleeved in the inner cavity 153 of the cylinder 152, and make the pressure rod 161 vertically pass through the movable hole of the bottom sealing plate of the cylinder 152. Ensure that the cylindrical pressure block 162 is pressed tightly against the preload bearing element 190 below by its own weight; a small amount of lubricating oil can be added at the mating point between the pressure rod 161 and the movable hole of the sealing plate to reduce the frictional resistance between the two and avoid friction affecting the pressure transmission accuracy.

[0025] (4) Assembly of hook and counterweight: Connect hook 170 to the bottom of pressure rod 161. According to the bearing capacity design requirements of the aero-engine bearing, select a counterweight 180 of the corresponding weight and connect it to hook 170. At this time, the total preload applied by the device is the total weight G of pressure rod 161, cylindrical pressure block 162, hook 170 and counterweight 180, and G must match the bearing design preload.

[0026] (5) Installation of measuring components and zeroing of dial indicator: Fix the base plate of Z-type gauge holder 120 to the annular plate 151; then install dial indicator 110 vertically on the top plate of Z-type gauge holder 120, with the measuring head of dial indicator 110 facing downwards. Place standard gauge block 130 movably on top of cylindrical pressure block 162, and ensure that standard gauge block 130 is directly below the measuring head of dial indicator 110; adjust the height of dial indicator 110 so that the measuring head contacts the surface of standard gauge block 130, and then zero dial indicator 110 to establish a measurement reference.

[0027] (6) Measurement of key parameters: Carefully remove the standard gauge block 130 from the top of the cylindrical pressure block 162. At this time, the measuring head of the dial indicator 110 will directly contact the top of the cylindrical pressure block 162. After the dial indicator 110 reading stabilizes, record the current measurement value as H1.

[0028] (7) Calculation of remaining thickness and control of preload: Calculate the remaining thickness d of the preload bearing element 190 under the design preload G state according to the formula d=H2-H3-(H1-d0); where H2 is the depth of the inner cavity 153 of the cylinder 152, H3 is the height of the cylindrical pressure block 162, and d0 is the thickness of the standard gauge block 130.

[0029] In angular contact ball bearings (such as Figure 4 In the actual assembly process of (220), an adjustment shim 240 of corresponding thickness is selected according to the calculated remaining thickness d; the final remaining thickness of the preload bearing element 190 is controlled by the adjustment shim 240 to ensure that the inner and outer rings of the angular contact ball bearing can meet the design preload G requirements after installation.

[0030] The device embodiments described above are merely illustrative. The structures described as separate components may or may not be physically separate. The components shown as structures may or may not be physical structures; they may be located in one place or distributed across multiple network structures. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs.

[0031] In this utility model, unless otherwise explicitly specified and limited, the terms "installation", "setting", "connection", "fixing", "screw connection", etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal connection of two components or the interaction between two components. Unless otherwise explicitly limited, those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0032] It is understood that those skilled in the art can make equivalent substitutions or changes based on the technical solution and concept of this utility model, and all such substitutions or changes should fall within the protection scope of the appended claims.

Claims

1. A device for testing the preload force of an aero-engine bearing, characterized in that, include: Base, pressure piece, dial indicator holder, dial indicator, standard gauge block, hook and ring, and counterweight; The base includes a cylindrical body and an annular plate fixedly connected to the outer edge of the upper end of the cylindrical body; A sealing plate is fixedly connected to the bottom of the cylinder, and a movable hole is opened in the middle of the sealing plate; The dial indicator frame is fixedly connected to the circular plate; the dial indicator is vertically mounted on the frame. The pressure component includes a cylindrical pressure block and a pressure rod fixedly connected to the bottom of the cylindrical pressure block; The cylindrical pressure block is movably fitted into the inner cavity of the cylinder; the pressure rod vertically passes through the movable hole on the sealing plate. The hook and ring are connected to the bottom of the pressure bar; the counterweight is connected to the hook and ring. The standard gauge block is placed on top of the cylindrical pressure block and below the dial indicator measuring head.

2. The aero-engine bearing preload testing device according to claim 1, characterized in that, A level is installed on the circular plate.

3. The aero-engine bearing preload testing device according to claim 1, characterized in that, The dial indicator frame is Z-shaped; the base plate of the Z-shaped frame is fixedly connected to the ring plate; the dial indicator is vertically mounted on the top plate of the Z-shaped frame.

4. The aero-engine bearing preload testing device according to claim 1, characterized in that, The bottom of the inner cavity of the cylinder is used to place the preload bearing element; the cylindrical pressure block is pressed on top of the preload bearing element, and the pressure rod passes through the shaft hole of the preload bearing element.

5. The aero-engine bearing preload testing device according to claim 4, characterized in that, The preload bearing element includes one of the following: disc spring, wave spring, helical spring, and ring spring.

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