A calibration device for an aero-engine axial force measuring structure

Abstract

The present application belongs to the field of axial force measurement of aero-engine thrust bearing, and particularly relates to a calibration device for an axial force measurement structure of an aero-engine, comprising a supporting frame / supporting platform / pressurizing device / pressure head / pressure plate and a bearing platform. The present application can directly connect the axial force measurement structure assembly through the flange edge, and has the adjusting function of the position and posture of the test piece, thereby simplifying the operation steps of the test personnel.

Description

Technical Field

[0001] This invention belongs to the field of axial force measurement of aero-engine thrust bearings, and specifically relates to a calibration device for an aero-engine axial force measurement structure. Background Technology

[0002] During the development of aero-engines, it is necessary to complete the axial force analysis of the thrust bearing to ensure its reliable operation. GJB241 requires that "sufficient measuring devices should be installed at appropriate locations on the main bearing to measure the bearing load and determine that the engine pressure balance system should provide sufficient unidirectional axial load to ensure that the bearing does not slip under all power conditions within the engine's operating envelope."

[0003] There are two methods for measuring engine axial force: indirect and direct. The traditional indirect method involves measuring the pressure in the compressor unloading chamber to indirectly determine the magnitude of the axial force. This method is simple but inaccurate. A commonly used direct method for testing axial force is to use an elastic ring-type measuring structure (also called a force ring) installed inside the engine bearing housing. The stress change experienced by the ring structure reflects its load-bearing capacity. When directly measuring engine axial force using a force ring structure, the measured physical quantity is the output of the strain gauge on the load. Therefore, it is necessary to establish the correspondence between strain and force before the test, i.e., to calibrate the force ring-type axial force measuring structure.

[0004] The typical calibration test involves using a material tensile and compressive testing machine to perform a compression test on the axial force measuring structure. As a general-purpose testing device, the material tensile and compressive testing machine typically has a planar support surface, which facilitates the calibration of individual components of the elastic force measuring ring. However, when the elastic force measuring ring is assembled onto the engine axial force measuring structure, the mounting edge of the structure is the flange edge in the middle of the assembly, making it impossible to directly place the mounting edge on the support plane. Furthermore, during calibration, the component of the axial force measuring structure (referred to as the test piece in this article) requires the force point to be located at the center of the component, with the force direction perpendicular to the force plane; that is, accurate positioning and orientation of the component are necessary. The support plane structure of the material tensile and compressive testing machine is simple and lacks the function of adjusting the position and orientation of the test piece. The placement can only be adjusted manually by the testing personnel, whose experience significantly influences the test results. Summary of the Invention

[0005] In view of this, the present invention provides a calibration device for an axial force measurement structure of an aero-engine, which can directly connect the axial force measurement structure components through the flange edge, and also has the function of adjusting the position and attitude of the test piece, simplifying the operation steps of the test personnel.

[0006] To achieve the above-mentioned technical objectives, the specific technical solution adopted by the present invention is as follows:

[0007] A calibration device for an axial force measurement structure of an aero-engine includes:

[0008] Support frame;

[0009] A support platform, mounted on the support frame, is used to support the axial force measuring structure;

[0010] A pressurizing device, mounted on the support frame and positioned opposite the support platform, is used to generate a measuring load toward the support platform;

[0011] A pressure head, mounted on the pressurizing device, is used to transmit the measuring load. One end of the pressure head facing the support platform is a conical head. The axial direction of the conical head is parallel to or coincides with the load axis of the axial force measuring structure bearing on the support platform.

[0012] The pressure plate has a conical hole at one end facing the pressurizing device; its outer diameter is the same as the upper straight hole of the axial force measuring structure; when the axial force measuring structure is supported on the support platform and the pressure plate is limited in the upper straight hole of the axial force measuring structure, the conical hole is coaxial with the load axis of the axial force measuring structure.

[0013] A support platform is mounted on the support platform; the axial force measuring structure is adjustablely positioned on the support platform.

[0014] Wherein: the shape of the conical head is the same as the shape of the conical hole; the tail of the conical hole faces the end of the conical head; a force sensor is provided between the pressurizing device and the pressure head.

[0015] Furthermore, a plurality of adjusting top posts are provided between the bearing platform and the support platform; each adjusting top post is located at the end of the support platform away from the pressure head, and is used to adjust the position of the support platform based on its own extension and retraction.

[0016] Furthermore, the support platform includes a tray, a flange mounting plate, and multiple screw-slider assemblies; the bottom surface of the tray is supported by each of the adjusting top columns, and multiple mounting holes of the screw-slider assemblies are evenly distributed on the circumference of the tray; the flange mounting plate is used to fix the test piece, and is slidably mounted on the tray, achieving planar sliding on the tray based on each of the screw-slider assemblies.

[0017] Furthermore, the screw-slider assembly includes a screw, a slider, a rotating handle, and a spring; the screw is threaded into the mounting hole; the rotating handle drives the screw to rotate; the slider is disposed at the end of the screw near the flange mounting plate; the slider contacts the flange mounting plate; the spring is disposed between the slider and the screw to maintain the contact between the screw and the slider.

[0018] Furthermore, the adjusting top column includes a support sleeve, a ball head bolt, a spherical top block, and a clamping nut; the support sleeve is fixedly connected to the support platform; the ball head bolt is connected to the support sleeve based on the clamping nut; the bottom surface of the spherical top block and the ball head bolt are engaged through spherical contact, and the top surface supports the support platform.

[0019] Furthermore, the support frame is also provided with a crossbeam guide rail; the pressurizing device is provided with a movable crossbeam; the pressurizing device is mounted on the crossbeam guide rail based on the movable crossbeam; the crossbeam guide rail is used to provide motion guidance for the movable crossbeam. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the overall structure of a calibration device for measuring axial force of an aero-engine, according to a specific embodiment of the present invention.

[0022] Figure 2 This is a schematic diagram of the support structure of the adjusting top column and the bearing platform in a specific embodiment of the present invention;

[0023] Figure 3 This is a schematic diagram of the planar movement of the support platform in a specific embodiment of the present invention;

[0024] Figure 4 This is a schematic diagram showing the contact between the pressure head and one side of the pressure plate during the pressing process in a specific embodiment of the present invention;

[0025] The components include: 1. Fixed frame; 2. Pressurizing device; 3. Adjustable top column; 4. Support platform; 1-1. Support frame; 1-2. Support platform; 2-1. Moving crossbeam; 2-2. Force sensor; 2-3. Pressure head; 2-4. Pressure plate; 3-1. Support sleeve; 3-2. Ball head bolt; 3-3. Spherical top block; 3-4. Compression nut; 4-1. Tray; 4-2. Flange mounting plate; 4-3. Screw and slider assembly; 4-4. Screw; 4-5. Slider; 4-6. Rotating handle; 4-7. Spring; 5. Axial force measuring structure assembly. Detailed Implementation

[0026] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0027] The following specific examples illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this disclosure, and not all of them. This disclosure can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this disclosure. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. All other embodiments obtained by those skilled in the art based on the embodiments of this disclosure without creative effort are within the scope of protection of this disclosure.

[0028] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this disclosure, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using other structures and / or functionalities besides one or more of the aspects set forth herein.

[0029] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this disclosure. The drawings only show the components related to this disclosure and are not drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0030] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0031] In one embodiment of the present invention, a calibration device for an aero-engine axial force measurement structure is provided, such as... Figures 1 to 4 As shown, it includes:

[0032] Support frame;

[0033] The support platform, mounted on the support frame, is used to support the axial force measurement structure.

[0034] The pressurizing device 2 is installed on the support frame and is positioned opposite the support platform to generate a measuring load toward the support platform.

[0035] The pressure head 2-3 is installed on the pressurizing device 2 and is used to transmit the measuring load. The end facing the support platform is a conical head. The axial direction of the conical head is parallel to or coincides with the load center axis of the axial force measuring structure bearing on the support platform.

[0036] The pressure plate 2-4 has a conical hole at one end facing the pressure device 2; the outer diameter of the conical hole is the same as the upper straight hole of the axial force measuring structure; when the axial force measuring structure is supported on the support platform and the pressure plate 2-4 is limited in the upper straight hole of the axial force measuring structure, the conical hole is coaxial with the load axis of the axial force measuring structure.

[0037] The bearing platform 4 is installed on the support platform; the axial force measuring structure is set on the bearing platform 4 in an adjustable position.

[0038] Wherein: the shape of the conical head is the same as the shape of the conical hole; the tail of the conical hole faces the end of the conical head; a force sensor 2-2 is set between the pressurizing device 2 and the pressure head 2-3.

[0039] In this embodiment, multiple adjusting top columns 3 are provided between the bearing platform 4 and the support platform; each adjusting top column 3 is located at the end of the support platform away from the pressure head 2-3, and is used to adjust the position of the support platform based on its own extension and retraction.

[0040] In this embodiment, the support platform 4 includes a tray 4-1, a flange mounting plate 4-2, and multiple screw-slider assemblies 4-3; the bottom surface of the tray 4-1 is supported by each adjusting top column 3, and multiple mounting holes of the screw-slider assemblies 4-3 are evenly distributed on the circumference of the tray 4-1; the flange mounting plate 4-2 is used to fix the test piece and is slidably mounted on the tray 4-1, and the planar sliding on the tray 4-1 is realized based on each screw-slider assembly 4-3.

[0041] In this embodiment, the screw-slider assembly 4-3 includes a screw 4-4, a slider 4-5, a rotating handle 4-6, and a spring 4-7; the screw 4-4 is threaded into the mounting hole; the rotating handle 4-6 drives the screw 4-4 to rotate; the slider 4-5 is disposed at the end of the screw 4-4 near the flange mounting plate 4-2; the slider 4-5 contacts the flange mounting plate 4-2; the spring 4-7 is disposed between the slider 4-5 and the screw 4-4 to maintain the contact between the screw 4-4 and the slider 4-5.

[0042] In this embodiment, the adjusting top column 3 includes a support sleeve 3-1, a ball head bolt 3-2, a spherical top block 3-3, and a clamping nut 3-4; the support sleeve 3-1 is fixedly connected to the support platform 1-2; the ball head bolt 3-2 is connected to the support sleeve 3-1 based on the clamping nut 3-4; the bottom surface of the spherical top block 3-3 and the ball head bolt 3-2 are engaged through spherical contact, and the top surface supports the support platform 4.

[0043] In this embodiment, a crossbeam guide rail is also provided on the support frame; a movable crossbeam 2-1 is provided on the pressurizing device 2; the pressurizing device 2 is mounted on the crossbeam guide rail based on the movable crossbeam 2-1; the crossbeam guide rail is used to provide motion guidance for the movable crossbeam 2-1.

[0044] The calibration device for the aero-engine axial force measurement structure in this embodiment includes: a fixed frame 1, a pressurizing device 2, an adjusting top column 3, and a support platform 4.

[0045] The fixed frame 1 includes a support frame 1-1 and a support platform 1-2. This structure is the fixed part of the device, and its main purpose is to provide guidance for the movement of the device and to bear the load.

[0046] The pressurizing device 2 is located on the support frame 1-1 and includes: a movable crossbeam 2-1, a force sensor 2-2, a pressure head 2-3, and a pressure plate 2-4. Its function is to apply a load force to the test piece. The force sensor 2-2 is located on the movable crossbeam 2-1. The pressure head 2-3 is connected to the force sensor 2-2. The pressure plate 2-4 is placed on the test piece. During the application of the load force, the pressure head 2-3 comes into contact with the pressure plate 2-4.

[0047] The adjusting top post 3 is located on the support platform 1-2 and includes: a support sleeve 3-1, a ball head bolt 3-2, a spherical top block 3-3, and a clamping nut 3-4. The support sleeve 3-1 has internal threads, and the ball head bolt 3-2 is bolted to the support sleeve 3-1. The clamping nut 3-4 is used to secure the bolt and the support sleeve 3-1 together. The top surface of the spherical top block 3-3 supports the support platform 4, and its angle and orientation are consistent with the support platform 4. The bottom surface of the spherical top block 3-3 is a concave spherical surface that mates with the ball head bolt 3-2, enabling the ball head bolt 3-2 to indirectly support the support platform 4 through spherical contact.

[0048] The support platform 4 includes: a tray 4-1, a screw-slider assembly 4-3, and a flange mounting plate 4-2. The bottom of the tray 4-1 is supported by an adjusting top column 3, and the top surface supports the flange mounting plate 4-2. Four mounting holes for the screw-slider assembly 4-3 are evenly distributed around the circumference of the tray 4-1. The flange mounting plate 4-2 is used to fix the axial force measuring structure assembly 5; the test piece and the mounting plate can be fixed together by bolts on the flange edge. The screw-slider assembly 4-3 is installed around the tray 4-1 and consists of a screw 4-4, a rotating handle 4-6, a slider 4-5, and a spring 4-7. The position of the slider 4-5 can be adjusted by rotating the screw 4-4.

[0049] In this embodiment, the inner diameter of the flange mounting plate 4-2 is slightly larger than the inner diameter of the flange edge of the axial force measuring structure component 5, so the mounting plate will not interfere with the test piece. The test piece can be mounted upright or upside down on the mounting plate, or it can mate with the bottom surface of the mounting plate. The effect achieved is that the connection method between the test piece and the flange mounting plate 4-2 can be determined according to the direction of the test load and the actual load-bearing surface of the test piece inside the engine.

[0050] In this invention, the flange mounting plate 4-2 is placed on the tray 4-1 by its own weight. The outer circle of the flange mounting plate 4-2 contacts the slider 4-5 of the screw slider assembly 4-3. The movement of the slider 4-5 can push the flange mounting plate 4-2 to slide on the contact plane with the tray 4-1, thereby realizing the function of adjusting the position of the flange mounting plate 4-2.

[0051] The pressure head 2-3 and pressure plate 2-4 of this invention have graduations. During the downward pressing process of the pressure head 2-3, the alignment of the rotation centers of the contact areas of the pressure head 2-3 and pressure plate 2-4 can be confirmed through the graduations. By adjusting the position of the flange mounting plate 4-2, the axial force measuring structure component 5 and pressure plate 2-4 are moved, thereby aligning the pressure head 2-3 and pressure plate 2-4 and ensuring that the load force application point is located at the center of the test piece.

[0052] In the calibration device of this invention, the support platform 4 is supported by multiple adjusting top columns 3. Each adjusting top column 3 can adjust the length of the ball head bolt 3-2 by adjusting the bolt engagement, thereby adjusting the height of the support point of the support platform 4. By adjusting the height of multiple support points of the support platform 4, the angular attitude of the support platform 4 can be adjusted.

[0053] See attached document Figure 1 This is a schematic diagram of one embodiment of the calibration device for measuring axial force in an aero-engine according to the present invention. In this embodiment, the calibration device includes a fixed frame 1, a pressurizing device 2, an adjusting top column 3, and a support platform 4.

[0054] The fixed frame includes 1: a support frame 1-1 and a support platform 1-2. The support frame 1-1 has a crossbeam guide rail inside, which can provide guidance for the movement of the pressurizing device 2.

[0055] The pressurizing device 2 includes: a movable crossbeam 2-1, a force sensor 2-2, a pressure head 2-3, and a pressure plate 2-4. The movable crossbeam 2-1 is driven by a motor screw arranged inside the support frame 1-1 and can move up and down along the crossbeam guide column of the support frame 1-1. The force sensor 2-2 is connected to the pressure head 2-3 and is located below the movable crossbeam 2-1. As the movable crossbeam 2-1 moves downward, it can apply and measure the downward load force.

[0056] Reference Figure 2 The adjusting top column 3 includes: a support sleeve 3-1, a ball head bolt 3-2, a spherical top block 3-3, and a clamping nut 3-4. The support sleeve 3-1 is bolted to the support platform 1-2. The ball head bolt 3-2 is bolted to the support sleeve 3-1, and the clamping nut 3-4 secures the ball head bolt 3-2 and the support sleeve 3-1 together. The bottom surface of the spherical top block 3-3 engages with the ball head bolt 3-2 through spherical contact, and its top surface supports the support platform 4, with its angle and orientation matching that of the support platform 4.

[0057] In this embodiment of the invention, four adjusting top columns 3 support the bearing platform 4. Each adjusting top column can adjust the length of the ball head bolt 3-2 protruding from the bearing sleeve 3-1 by adjusting the engagement of the ball head bolt 3-2, thereby adjusting the height of the support point of the bearing platform 4. By adjusting the height of the four support points of the bearing platform 4, the angle and posture of the bearing platform 4 can be adjusted.

[0058] See attached document Figure 2 and attached Figure 3 The support platform 4 includes: a tray 4-1, a flange mounting plate 4-2, and a screw-slider assembly 4-3. The bottom surface of the tray 4-1 is supported by an adjusting top column 3, and four mounting holes for the screw-slider assembly 4-3 are evenly distributed on the circumference of the tray 4-1. The flange mounting plate is used to fix the test specimen, and the axial force measuring structure assembly 5 and the flange mounting plate 4-2 are fixed together by bolt assembly 6.

[0059] See attached document Figure 3 The screw-slider assembly 4-3 is mounted around the tray 4-1 and consists of a screw 4-4, a slider 4-5, a rotating handle 4-6, and a spring 4-7. Rotating the rotating handle 4-6 rotates the screw 4-4, adjusting its extension distance to move the slider 4-5. The spring 4-7 maintains contact between the screw 4-4 and the slider 4-5. The flange mounting plate 4-2 rests on the tray 4-1 under its own weight. The outer circumference of the flange mounting plate 4-2 contacts the slider 4-5, and the movement of the slider 4-5 pushes the flange mounting plate 4-2 to slide on the plane.

[0060] In this embodiment of the invention, the pressure head 2-3 has a conical surface below it. The pressure plate 2-4 has an inner conical hole above it, which mates with the conical surface below the pressure head 2-3. The center of rotation of the conical surface is the point of application of the load force. (See attached diagram.) Figure 4 The cone surface of the pressure head 2-3 has graduations. During the downward pressing process of the pressure head 2-3, if the center of the pressure head 2-3 and the pressure plate 2-4 are not aligned, one side of the cone surface will make contact first. The location of the contact point is the offset position of the axial force measuring structure component 5. The offset distance can be determined by observing the graduations corresponding to the contact point. By rotating the screw slider assembly 4-3, the flange mounting plate 4-2, the axial force measuring structure component 5, and the pressure plate 2-4 are driven to move along the offset, so that the cone surface changes from one-sided contact to full-circle contact, realizing the alignment of the pressure head 2-3 and the pressure plate 2-4, and ensuring that the load force application point is located at the center of the axial force measuring structure component 5.

[0061] The above description is merely a specific embodiment of this disclosure, but the scope of protection of this disclosure is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this disclosure should be included within the scope of protection of this disclosure. Therefore, the scope of protection of this disclosure should be determined by the scope of the claims.

Claims

1. A calibration device for an axial force measurement structure of an aero-engine, characterized in that, include: A fixed frame (1) includes a support frame (1-1) and a support platform (1-2), wherein the support platform (1-2) is mounted on the support frame (1-1) and is used to bear the axial force measuring structure assembly (5); A pressurizing device (2) is mounted on the support frame (1-1) and is positioned opposite to the support platform (1-2) to generate a measuring load toward the support platform (1-2). The pressurizing device (2) is provided with a pressure head (2-3) and a pressure plate (2-4). The pressure head (2-3) is used to transmit the measuring load, and one end of the pressure head (2-3) facing the support platform (1-2) is a conical head. The axial direction of the conical head is the same as the axial force borne on the support platform (1-2). The load axis of the measuring structure assembly (5) is parallel or coincident; a conical hole is provided at one end of the pressure plate (2-4) facing the pressure head (2-3); the outer diameter of the pressure plate (2-4) is the same as the upper straight hole of the axial force measuring structure assembly (5); when the axial force measuring structure assembly (5) is supported on the support platform (1-2) and the pressure plate (2-4) is limited in the upper straight hole of the axial force measuring structure assembly (5), the conical hole is coaxial with the load axis of the axial force measuring structure assembly (5); A support platform (4) is mounted on the support platform (1-2); the axial force measuring structure component (5) is oriented adjustablely on the support platform (4); multiple adjusting top columns (3) are provided between the support platform (4) and the support platform (1-2), and one end of each adjusting top column (3) connected to the support platform (4) is used to adjust the orientation of the support platform (1-2) based on its own extension and retraction; the adjusting top column (3) includes a support sleeve (3-1), a ball head bolt (3-2), a spherical top block (3-3), and a clamping nut (3-4); the support sleeve (3-1) is fixedly connected to the support platform (1-2); the ball head bolt (3-2) is connected to the support sleeve (3-1) based on the clamping nut (3-4); the bottom surface of the spherical top block (3-3) is in spherical contact with the ball head bolt (3-2), and the top surface supports the support platform (4); Wherein: the shape of the conical head is the same as the shape of the conical hole; the tail of the conical hole faces the end of the conical head; a force sensor (2-2) is provided between the pressurizing device (2) and the pressure head (2-3).

2. The calibration device for the axial force measurement structure of an aero-engine according to claim 1, characterized in that, The support platform (4) includes a tray (4-1), a flange mounting plate (4-2), and multiple screw-slider assemblies (4-3); the bottom surface of the tray (4-1) is supported by each of the adjusting top columns (3), and multiple mounting holes for mounting the screw-slider assemblies (4-3) are evenly distributed on the circumference of the tray (4-1); the flange mounting plate (4-2) is used to fix the axial force measuring structure assembly (5), and the flange mounting plate (4-2) is slidably mounted on the tray (4-1), and the planar sliding on the tray (4-1) is realized based on each of the screw-slider assemblies (4-3).

3. The calibration device for the axial force measurement structure of an aero-engine according to claim 2, characterized in that, The screw-slider assembly (4-3) includes a screw (4-4), a slider (4-5), a rotating handle (4-6), and a spring (4-7); the screw (4-4) is threaded into the mounting hole; the rotating handle (4-6) drives the screw (4-4) to rotate; the slider (4-5) is disposed at one end of the screw (4-4) near the flange mounting plate (4-2); the slider (4-5) contacts the flange mounting plate (4-2); the spring (4-7) is disposed between the screw (4-4) and the slider (4-5) to maintain the contact between the screw (4-4) and the slider (4-5).

4. The calibration device for the axial force measurement structure of an aero-engine according to claim 1, characterized in that, The support frame (1-1) is also provided with a crossbeam guide rail; the pressurizing device (2) is provided with a movable crossbeam (2-1), and the pressurizing device (2) is mounted on the crossbeam guide rail based on the movable crossbeam (2-1); the crossbeam guide rail is used to provide motion guidance for the movable crossbeam (2-1).

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