Device for determining position of aero-engine blade strain gauge patch

Abstract

The embodiment of the utility model provides a device for determining the position of an aero-engine blade strain gauge patch, and relates to the field of aero-engine measurement. The objective of the utility model is to solve the problem that position detection of an aero-engine blade strain gauge is high in difficulty and not accurate enough. The device comprises a working platform, a clamping tool, a movable bracket, a vertical scale bracket, a transverse scale bracket, an axial reference bracket and a transverse scale, wherein the clamping tool is arranged on a working surface; the movable bracket is adjustably arranged on the working platform in the vertical direction; the vertical scale support is adjustably arranged on the movable support in the normal direction. The transverse scale support is adjustably arranged on the vertical scale support in the vertical direction, the transverse scale is adjustably arranged on the transverse scale support in the transverse direction, and the axial reference support is provided with an axial reference table extending in the vertical direction. The blade is fixed by using the clamping tool to fix the blade tenon, and the three-dimensional coordinate geometric position of the measuring point relative to the reference surface is determined by using the ruler and the sliding structure, so that the position determination precision of the strain gauge is improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aero-engine measurement, and more particularly to a device for determining a aero-engine blade strain gauge patch position. BACKGROUND

[0002] Aero-engine blades are the main working parts of aero-engines and are subjected to complex alternating stress in use. If the magnitude of the vibration stress exceeds the corresponding fatigue limit, the blade will develop fatigue cracks within the designed life, often leading to fatigue fracture in a relatively short time, which seriously affects the safety of the aero-engine. Therefore, during the project development stage, the actual vibration stress level of the blade needs to be determined through blade dynamic stress testing at various stages from the part to the whole machine, thereby providing support for the verification or improvement of the design and process. Generally, the vibration stress testing of the blade is achieved by sticking strain gauges in the specified direction at the specified position on the surface of the blade and connecting them with the corresponding signal acquisition and processing device to output vibration strain information. Due to the limitations of factors such as the natural frequency, geometric size, and strain gauge type of the blade, there are specific requirements for the stress gradient in the range of the surface and the sticking area of the strain gauge sticking position. In actual operation, the strain gauge patch position and direction need to be accurately positioned according to the design requirements to effectively test the vibration stress level of the working blade. Since the size and assembly form of different engine types and different stages of the blade may be different, and the blade surface is complex, there is currently no universal device. Generally, the geometric position and direction of the blade dynamic stress measurement points are determined by using the manual measurement method multiple times, which is time-consuming and labor-intensive. The relative reference is used multiple times, which introduces more human errors and easily causes coordinate confusion, thereby making the determination of the strain gauge sticking position inaccurate and inconsistent. Therefore, how to quickly and accurately determine the sticking position of the strain gauge to monitor the vibration stress level of the blade is the key to the blade vibration stress testing.

[0003] Document CN 207751621 U discloses a device for determining the sticking position of the strain gauge of an aero-engine blade. The device realizes the radial positioning of the blade by sticking the bottom plane of the blade tenon to the base of the device and pressing it at the blade tip end. The chordwise positioning of the blade is realized by using positioning pins. The three-coordinate positioning of the measurement point position is realized by the three-direction ruler and the sliding transverse ruler which are directly or indirectly connected to the base of the device, thereby determining the sticking position of the strain gauge. However, with the development of simulation technology, advanced blade types often make the blade body base stacking axis deviate far from the tenon central axis. The radial pressing device described in this document cannot effectively fix the radial position of the blade due to the additional bending moment. The positioning pin method given in this document will not be able to realize the chordwise positioning of the blade. The vibration principal stress direction of the blade under different positions and different modes is different, and the determination of the direction of the strain gauge is also critical. However, the method for determining the direction of the strain gauge is not given in this document.

[0004] Document CN 107218909 A discloses a method for determining the position and direction of a strain gauge on an engine blade, which utilizes the distance between the leading and trailing edge angle points on the blade tip and the position points and direction reference position points on the blade to determine the geometric position of the patch points and reference points by the intersection of the circular arcs with the angle points as the center, and the direction is determined by the line connecting the patch points and the reference points. The engine blade angle point is an outer corner tip, which is difficult to accurately use as a center in actual operation, so it is difficult to obtain accurate strain gauge patch position using the patent method. Utility model content

[0005] The following presents a simplified summary of one or more aspects in order to provide a basic understanding of such aspects. This summary is not an extensive overview of all contemplated aspects, and is intended to neither identify key or critical elements of all aspects nor delineate the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that is presented later.

[0006] The purpose of the utility model includes, for example, providing a device for determining the position of a strain gauge patch on an aero-engine blade, which can improve the problem of high difficulty and inaccuracy in detecting the position of the strain gauge on the aero-engine blade.

[0007] Embodiments of the utility model can be implemented as follows:

[0008] The device for determining the position of a strain gauge patch on an aero-engine blade provided by the embodiments of the utility model comprises a working platform, a clamping tool, a moving support, a vertical scale support, a horizontal scale support, an axial reference support and a horizontal scale, the working platform is provided with a working surface extending in the horizontal direction, the clamping tool is arranged on the working surface, and the clamping tool is used for mounting and fixing the tenon of the engine blade on the working surface, the moving support is adjustably arranged on the working platform in the vertical direction, the vertical scale support is adjustably arranged on the moving support in the normal direction, the vertical scale support is provided with a radial reference table extending in the horizontal direction, the horizontal scale support is adjustably arranged on the vertical scale support in the vertical direction, the horizontal scale is adjustably arranged on the horizontal scale support in the horizontal direction, the axial reference support is fixed with the horizontal scale, the axial reference support is provided with an axial reference table extending in the vertical direction, and the horizontal scale is used for indicating the position of the strain gauge during the movement of the horizontal scale support, wherein the horizontal direction, the vertical direction and the normal direction are perpendicular to each other, and the radial reference table and the axial reference table are respectively used for abutting against two surfaces on the tenon of the engine blade.

[0009] In addition, the device for determining the position of the strain gauge patch of the aero-engine blade provided by the embodiment of the utility model can also have the following additional technical features.

[0010] Optionally, the clamping tool comprises a first clamping plate and a second clamping plate, the first clamping plate and the second clamping plate are rotatably arranged on the working surface, the first clamping plate and the second clamping plate are used to form an installation space for placing the engine tenon between them during rotation, and the first clamping plate and the second clamping plate are used to abut and press the outer side of the engine tenon located in the installation space during rotation to fix.

[0011] Optionally, the clamping tool further comprises a third clamping plate, the third clamping plate is rotatably arranged on the working surface, and the third clamping plate is located between the first clamping plate and the second clamping plate, the third clamping plate is used to support the bottom surface of the engine tenon in the installation space during rotation, so that the included angle of the engine blade tenon relative to the working surface is equal to the included angle of the engine blade tenon relative to the axial direction of the aero-engine.

[0012] Optionally, the working platform further comprises a first supporting rod arranged in the vertical direction, the first supporting rod is vertically fixed on the working surface; the moving support comprises a second supporting rod extending in the normal direction, the second supporting rod is vertically and slidably arranged on the first supporting rod, and the vertical position of the second supporting rod relative to the first supporting rod is adjustable; the vertical scale support is slidably arranged on the second supporting rod in the normal direction, and the normal position of the vertical scale support relative to the second supporting rod is adjustable.

[0013] Optionally, the vertical scale support comprises a third supporting rod extending in the vertical direction and a fourth supporting rod extending in the horizontal direction, the third supporting rod and the fourth supporting rod are fixed, the third supporting rod is slidably arranged on the second supporting rod in the normal direction, and the normal position of the third supporting rod relative to the second supporting rod is adjustable; the radial reference table is arranged on the upper surface of the end of the fourth supporting rod away from the third supporting rod.

[0014] Optionally, the horizontal scale support comprises a fifth supporting rod arranged in the horizontal direction; the fifth supporting rod is vertically and slidably arranged on the third supporting rod, and the vertical position of the fifth supporting rod relative to the third supporting rod is adjustable.

[0015] Optionally, the horizontal scale is arranged in the horizontal direction, the horizontal scale is slidably arranged on the fifth supporting rod in the horizontal direction, and the horizontal position of the horizontal scale relative to the fifth supporting rod is adjustable.

[0016] Optionally, the axial reference support comprises a sixth support rod; the sixth support rod is fixed on the transverse scale in the vertical direction; one side of the sixth support rod is provided with the axial reference table; the axial reference table is used for abutting against one surface of the engine tenon during movement of the transverse scale.

[0017] Optionally, the device for determining the position of the strain gauge patch of the aero-engine blade further comprises two normal auxiliary fixing supports; the two normal auxiliary fixing supports are movably arranged on the working surface in the normal direction; the two normal auxiliary fixing supports are used for moving towards or away from each other in the normal direction to limit the normal position of the engine blade.

[0018] Optionally, the device for determining the position of the strain gauge patch of the aero-engine blade further comprises a direction protractor; the direction protractor is fixed on the transverse scale; the direction protractor is used for measuring the included angle of the strain gauge patch relative to the vertical direction or the horizontal direction.

[0019] The device for determining the position of the strain gauge patch of the aero-engine blade has the following beneficial effects, for example:

[0020] The device for determining the position of the strain gauge patch of the aero-engine blade comprises a working platform, a clamping tool, a moving support, a vertical scale support, a transverse scale support, an axial reference support and a transverse scale; the working platform is provided with a working surface extending in the horizontal direction; the clamping tool is arranged on the working surface; the clamping tool is used for mounting and fixing the engine blade tenon on the working surface; the moving support is movably arranged on the working platform in the vertical direction; the vertical scale support is movably arranged on the moving support in the normal direction; the vertical scale support is provided with a radial reference table extending in the horizontal direction; the transverse scale support is movably arranged on the vertical scale support in the vertical direction; the transverse scale is movably arranged on the transverse scale support in the horizontal direction; the axial reference support is fixed with the transverse scale; the axial reference support is provided with an axial reference table extending in the vertical direction; the transverse scale is used for indicating the position of the strain gauge during movement of the transverse scale support; wherein the horizontal direction, the vertical direction and the normal direction are perpendicular to each other; the radial reference table and the axial reference table are respectively used for abutting against two surfaces of the engine blade tenon.

[0021] Through the blade clamping and size measuring structure, the different working surface angles of the engine blade can be fixed, the position and direction of the strain gauge patch of the to-be-measured blade can be quickly and accurately positioned, human interference can be reduced, the accuracy and consistency of the determination of the measuring point position can be improved, the work efficiency can be improved, and the cost is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0022] The above features and advantages of the present application can be better understood by reading the following detailed description of embodiments of the present application in conjunction with the drawings, in which: In the drawings, components are not necessarily drawn to scale, and components of similar or identical function or structure can have identical or similar reference numbers.

[0023] Figure 1 The device for determining the position of the strain gauge patch of the aero-engine blade provided by the embodiments of the present application provides a general structure form and an application example schematic diagram of the device.

[0024] Figure 2 The device for determining the position of the strain gauge patch of the aero-engine blade provided by the embodiments of the present application provides a left view and an additional fixed structure schematic diagram of the device.

[0025] Figure 3 The device for determining the position of the strain gauge patch of the aero-engine blade provided by the embodiments of the present application provides an application example schematic diagram of different tenon forms of the device.

[0026] Figure: device for determining the position of the strain gauge patch of the aero-engine blade-10; engine blade-11; tenon-12; work platform-100; working surface-110; first supporting rod-120; clamping tool-200; first clamping plate-210; second clamping plate-220; third clamping plate-230; second supporting rod-300; seventh supporting rod-310; third supporting rod-400; fourth supporting rod-410; radial reference table-411; fifth supporting rod-500; sixth supporting rod-600; axial reference table-610; transverse scale-700; normal auxiliary fixed support-800; direction protractor-900. DETAILED DESCRIPTION

[0027] The present application will be described in detail below in conjunction with the drawings and specific embodiments. Note that the aspects described below in conjunction with the drawings and specific embodiments are only exemplary and should not be understood as limiting the scope of protection of the present application.

[0028] In the description of the present application, it should be noted that if the terms "upper", "lower", "inner", "outer", "vertical" and the like indicate the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the present application is usually placed, and not the orientation or positional relationship of the device or element indicated or implied, therefore, it cannot be understood as a limitation on the present application.

[0029] At the same time, it should be noted that if the terms "first", "second" and the like are used only for differentiation and description, and cannot be understood as indicating or implying relative importance.

[0030] In the description of the utility model, still need to explain, unless another explicit provision or limitation, term '' install '' '' link '' '' connection '' should do broad sense understanding, for example can be fixed connection, can be integrally connected, or can be detachably connected, can be mechanical connection, also can be electrical connection, can be direct connection, also can be indirectly connected through intermediate medium, or two element internal communication etc.

[0031] The following will be described in detail Figures 1 to 3 The device 10 for determining the position of the strain gauge patch of the aero-engine blade provided by the embodiment is described in detail.

[0032] Please refer to Figure 1 And Figure 3 The embodiment of the utility model provides a kind of device 10 for determining the position of the strain gauge patch of the aero-engine blade, including work platform 100, clamping tool 200, mobile support, vertical scale support, horizontal scale 700 support, axial reference support and horizontal scale 700, work platform 100 is provided with the working surface 110 extending along horizontal direction;Clamping tool 200 is set on working surface 110, and clamping tool 200 is used to install and fix engine blade tenon on working surface 110;Mobile support is vertically adjustable and set on work platform 100;Vertical scale support is normal adjustable and set on mobile support, and vertical scale support is provided with the radial reference table 411 extending along horizontal direction;Horizontal scale 700 support is vertically adjustable and set on vertical scale support, and horizontal scale 700 is horizontally adjustable and set on horizontal scale 700 support, axial reference support is fixed with horizontal scale 700, and axial reference support is provided with the axial reference table 610 extending along vertical direction, and horizontal scale 700 is used to indicate the position of strain gauge during the movement of horizontal scale 700 support;Wherein, horizontal direction, vertical direction and normal direction are perpendicular to each other, and radial reference table 411 and axial reference table 610 are used to abut on two faces of engine blade tenon respectively.

[0033] It should be noted that: engine blade refers to the part for converting gas energy arranged uniformly along circumference in the compressor and turbine main flow passage of aero-engine and having certain airfoil. Strain gauge is used to measure the surface strain of specific direction of measured position. Location needs to measure the geometric position of blade surface. Direction needs to measure the strain direction of blade surface position. Installation is the combined structure for assisting to determine the position and direction of blade strain measuring point.

[0034] After the engine blade is fixed on the working surface 110 by the clamping tool 200, the moving support drives the vertical scale support, the horizontal scale 700 support, the axial reference support and the horizontal scale 700 to move synchronously in the vertical direction until the radial reference table 411 on the vertical scale support abuts against one face of the tenon of the engine blade; then the vertical scale support drives the horizontal scale 700 support, the axial reference support and the horizontal scale 700 to move synchronously in the normal direction, in this process, the vertical position of the radial reference table 411 is determined, and the radial reference table 411 can still abut against the tenon of the engine blade during the sliding process in the normal direction; then the horizontal scale 700 support drives the axial reference support and the horizontal scale 700 to move in the vertical direction, and moves to the position corresponding to the strain gauge of the horizontal scale 700; then the axial reference support drives the horizontal scale 700 to move in the horizontal direction until the axial reference table 610 of the axial reference support abuts against one face of the tenon of the engine blade, at this time, the coordinates of the position corresponding to the strain gauge of the horizontal scale 700 are the position coordinates of the strain gauge.

[0035] The "radial direction" in the radial reference table 411 and the axial reference table 610 refers to the radial direction of the engine, and the "axial direction" refers to the axial direction of the engine, the radial reference table 411 abuts against the tenon of the engine blade from bottom to top, and determines the reference point of the radial direction of the engine, the axial reference table 610 abuts against the tenon of the engine blade from the side, and determines the reference point of the axial direction of the engine, through the reference determined by the radial reference table 411 and the axial reference table 610, the coordinates of the position corresponding to the strain gauge of the horizontal scale 700 relative to the coordinates of the reference can also be obtained, so that the position of the strain gauge can be quickly and accurately measured.

[0036] With reference to Figure 1 and Figure 3 In the embodiment, the clamping tool 200 includes a first clamping plate 210 and a second clamping plate 220, the first clamping plate 210 and the second clamping plate 220 are rotatably arranged on the working surface 110, and the first clamping plate 210 and the second clamping plate 220 are used to form an installation space for placing the tenon of the engine during the rotation process, and are used to abut and press the outer side of the tenon of the engine located in the installation space during the rotation process to fix the tenon of the engine.

[0037] The tenon of the engine blade is placed between the first clamping plate 210 and the second clamping plate 220, and the first clamping plate 210 and the second clamping plate 220 press the tenon of the engine from both sides of the tenon of the engine blade during the rotation process, so as to fix the engine blade.

[0038] With reference to Figure 1 and Figure 3In this embodiment, the clamping tool 200 further includes a third clamping plate 230, which is rotatably disposed on the working surface 110 and located between the first clamping plate 210 and the second clamping plate 220. The third clamping plate 230 is used to support the bottom surface of the engine tenon in the installation space during rotation, so that the angle between the engine blade tenon and the working surface 110 is equal to the angle between the engine blade tenon and the axial direction of the aero-engine.

[0039] The third clamp 230 can support the engine blade tenon or not. When not supported, the bottom surface of the engine blade tenon is flush with the working surface 110. In this case, the position coordinates of the strain gauge patch measured do not take into account the position coordinates of the angle between the engine blade and the engine axis. When supported, the position coordinates of the angle between the engine blade tenon and the aero-engine axis after installation are taken into account.

[0040] Reference Figure 1 and Figure 3 In this embodiment, the working platform 100 further includes a first support rod 120 arranged vertically, which is vertically fixed on the working surface 110; the movable bracket includes a second support rod 300 extending along the normal direction, which is slidably arranged vertically on the first support rod 120 and its vertical position relative to the first support rod 120 is adjustable; the vertical ruler bracket is slidably arranged along the normal direction on the second support rod 300 and its normal position relative to the second support rod 300 is adjustable.

[0041] The first support rod 120 is perpendicular to the working surface 110. The second support rod 300 slides vertically, causing the vertical scale support, the horizontal scale support 700, the axial reference support, and the horizontal scale 700 to move synchronously vertically. The position of the second support rod 300 is fixed when the radial reference platform 411 abuts against the bottom of the engine blade tenon.

[0042] Reference Figure 1 and Figure 3 In this embodiment, the movable support also includes a seventh support rod 310, which extends along the normal direction and is slidably mounted on the first support rod 120 along the vertical direction. The seventh support rod 310 and the second support rod 300 are arranged side by side, and the vertical scale support is slidably mounted on the second support and the seventh support rod 310 along the normal direction.

[0043] The seventh support rod 310 can move vertically along the first support rod 120 independently and can also be fixed. The seventh support rod 310 is used to assist the vertical ruler support in moving along the normal direction and plays the role of supporting the vertical ruler support.

[0044] Reference Figure 1 andFigure 3 In this embodiment, the vertical ruler support includes a third support rod 400 extending vertically and a fourth support rod 410 extending laterally. The third support rod 400 and the fourth support rod 410 are fixed. The third support rod 400 is slidably disposed on the second support rod 300 along the normal direction, and the normal position of the third support rod 400 relative to the second support rod 300 is adjustable. A radial reference platform 411 is provided on the upper surface of the end of the fourth support rod 410 away from the third support rod 400.

[0045] The third support rod 400 simultaneously slides in normal direction with the second support rod 300 and the seventh support rod 310. During the vertical movement of the first support rod 120, it drives the third support rod 400 and the fourth support rod 410 to move synchronously vertically. The seventh support rod 310 plays a guiding and supporting role.

[0046] Specifically, the third support rod 400 is vertically positioned, and the fourth support rod 410 is horizontally positioned, so as... Figure 1 The relative positions are explained in the diagram. The upper right surface of the fourth support rod 410 forms a radial reference platform 411.

[0047] Reference Figure 1 and Figure 3 In this embodiment, the horizontal scale 700 bracket includes a fifth support rod 500 arranged horizontally; the fifth support rod 500 is slidably arranged vertically on the third support rod 400, and the vertical position of the fifth support rod 500 relative to the third support rod 400 is adjustable.

[0048] The fifth support rod 500 drives the axial reference bracket and the transverse scale 700 to move vertically until the transverse scale 700 indicates the position of the strain gauge patch. At this time, the vertical coordinate of the strain gauge is determined. Then, the axial reference bracket and the transverse scale 700 are adjusted laterally until the axial reference bracket abuts against the engine blade tenon. Then, the three-dimensional coordinates of the strain gauge patch corresponding to the transverse scale 700 are read.

[0049] Reference Figure 1 and Figure 3 In this embodiment, the horizontal scale 700 is set horizontally and is slidably set on the fifth support rod 500 along the horizontal direction. The horizontal position of the horizontal scale 700 relative to the fifth support rod 500 is adjustable.

[0050] As the horizontal scale moves 700 degrees, it drives the axial reference bracket to move horizontally in sync.

[0051] Reference Figure 1 and Figure 3In this embodiment, the axial reference bracket includes a sixth support rod 600; the sixth support rod 600 is fixed vertically on the horizontal scale 700, and an axial reference platform 610 is provided on one side of the sixth support rod 600. The axial reference platform 610 is used to abut against one side of the engine tenon during the movement of the horizontal scale 700.

[0052] During the movement of the sixth support rod 600 driven by the transverse scale 700, the transverse scale 700 always coincides with the strain gauge patch in the transverse direction. When adjusted so that the axial reference platform 610 abuts against the engine tenon, the corresponding transverse coordinate is obtained.

[0053] Reference Figure 1 and Figure 3 In this embodiment, the device 10 for determining the position of the strain gauge patch on the aero-engine blade further includes a direction protractor 900, which is fixed on the horizontal scale 700 and is used to measure the angle between the strain gauge patch and the vertical or horizontal direction.

[0054] A directional protractor 900 is added to the tip of the horizontal scale 700. This flexible protractor can maintain a certain shape and measure the angle with the horizontal or vertical direction, which is recorded as the patch direction.

[0055] Reference Figure 2 In this embodiment, the device 10 for determining the position of the strain gauge patch on the aero-engine blade further includes two normal auxiliary fixing brackets 800. The two normal auxiliary fixing brackets 800 are movably disposed on the working surface 110 along the normal direction. The two normal auxiliary fixing brackets 800 are used to move closer to or further away from each other along the normal direction to limit the normal position of the engine blade.

[0056] Two normal auxiliary fixing brackets 800 are used to limit the normal position of the engine blades. The clamping tool 200 provides vertical and lateral limiting and fixing, while the normal auxiliary fixing brackets 800 fix the normal position, ensuring accurate subsequent readings.

[0057] According to the embodiment of the present invention, a device 10 for determining the position of a strain gauge patch on an aero-engine blade is provided. The working principle of the device 10 for determining the position of a strain gauge patch on an aero-engine blade includes:

[0058] The level of blade vibration stress directly affects the blade's lifespan, which in turn affects the engine's safety and reliability. Accurately measuring the blade vibration stress level is crucial for determining the blade's operating vibration stress level, and accurately determining the strain gauge mounting position is a key step in this process.

[0059] This embodiment combines the structural characteristics of the blade to design a universal adjustable clamping and measuring integrated device. The blade is fixed by using the clamping tool 200 to fix the blade tenon. The three-dimensional coordinate geometric position of the measuring point relative to the reference plane is determined by the scale and sliding structure. The strain gauge direction angle of the measuring point is measured, and finally the accurate position and direction of the strain gauge is determined, thereby improving the accuracy and consistency of the strain gauge position determination.

[0060] The process includes:

[0061] Reference Figure 1 , Figure 2 and Figure 3 The blade to be tested is clamped onto the working plane of the device as needed;

[0062] Reference Figure 1 The origin of the scale is aligned with the axial reference platform 610 and the radial reference platform 411 respectively. The vertical and horizontal scales 700 are adjusted to make the values ​​meet the design requirements.

[0063] Reference Figure 1 and Figure 2 Move the transverse scale 700 along the normal direction until the tip of the transverse scale 700 contacts the surface of the blade to be measured, and mark the center of the strain gauge contact position.

[0064] Reference Figure 1 and Figure 2 A directional protractor 900 is added to the tip of the horizontal scale 700. This flexible protractor can maintain a certain shape and measure the angle with the horizontal or vertical direction, which is recorded as the patch direction.

[0065] The device 10 provided in this embodiment for determining the position of strain gauge patches on aero-engine blades has at least the following advantages:

[0066] The blade clamping and dimensional measurement structure can fix the engine blade at different working surfaces with 110° angles and at the bottom of the tenon. It can also quickly and accurately position the strain gauge patch on the blade under test, reduce human interference, improve the accuracy and consistency of the measurement point location, increase work efficiency, and reduce costs.

[0067] The above description is only a specific embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present utility model should be included within the protection scope of the present utility model.

Claims

1. A device for determining the position of strain gauge patches on aero-engine blades, characterized in that, include: The work platform has a working surface that extends laterally; A clamping tool is disposed on the working surface and is used to install and fix the engine blade tenon on the working surface; A movable support, which is vertically adjustable and mounted on the working platform; A vertical ruler support, which is adjustable along the normal direction on the movable support, and the vertical ruler support is provided with a radial reference platform extending laterally. The system includes a horizontal scale support, an axial reference support, and a horizontal scale. The horizontal scale support is vertically adjustable on the vertical scale support, and the horizontal scale is horizontally adjustable on the horizontal scale support. The axial reference support is fixed to the horizontal scale, and the axial reference support is provided with an axial reference platform extending vertically. The horizontal scale is used to indicate the position of the strain gauge as it moves with the horizontal scale support. Wherein, the lateral direction, the vertical direction, and the normal direction are perpendicular to each other, and the radial reference platform and the axial reference platform are respectively used to abut against two surfaces on the tenon of the engine blade.

2. The apparatus for determining the position of strain gauge patches on aero-engine blades according to claim 1, characterized in that: The clamping tool includes a first clamping plate and a second clamping plate, which are rotatably disposed on the working surface. The first clamping plate and the second clamping plate are used to form an installation space between them for placing the engine tenon during rotation. The first clamping plate and the second clamping plate are used to press against and fix the outer side of the engine tenon located in the installation space during rotation.

3. The apparatus for determining the position of strain gauge patches on aero-engine blades according to claim 2, characterized in that: The clamping tool further includes a third clamping plate, which is rotatably disposed on the working surface and located between the first clamping plate and the second clamping plate. The third clamping plate is used to support the bottom surface of the engine tenon in the installation space during rotation, so that the angle between the engine blade tenon and the working surface is equal to the angle between the engine blade tenon and the axial direction of the aero-engine.

4. The apparatus for determining the position of strain gauge patches on aero-engine blades according to any one of claims 1-3, characterized in that: The working platform further includes a first support rod arranged vertically and fixed vertically on the working surface; the movable support includes a second support rod extending along the normal direction, the second support rod being slidably arranged vertically on the first support rod and its vertical position relative to the first support rod being adjustable; the vertical ruler support is slidably arranged along the normal direction on the second support rod and its normal position relative to the second support rod is adjustable.

5. The apparatus for determining the position of strain gauge patches on aero-engine blades according to claim 4, characterized in that: The vertical scale support includes a third support extending vertically and a fourth support extending laterally. The third support and the fourth support are fixed. The third support is slidably mounted on the second support along the normal direction, and the normal position of the third support relative to the second support is adjustable. The radial reference platform is provided on the upper surface of the end of the fourth support away from the third support.

6. The apparatus for determining the position of strain gauge patches on aero-engine blades according to claim 5, characterized in that: The horizontal scale support includes a fifth support rod arranged horizontally; the fifth support rod is slidably arranged vertically on the third support rod, and the vertical position of the fifth support rod relative to the third support rod is adjustable.

7. The apparatus for determining the position of strain gauge patches on aero-engine blades according to claim 6, characterized in that: The horizontal scale is set horizontally and is slidably mounted on the fifth support rod. The horizontal position of the horizontal scale relative to the fifth support rod is adjustable.

8. The apparatus for determining the position of strain gauge patches on aero-engine blades according to claim 7, characterized in that: The axial reference bracket includes a sixth support rod; the sixth support rod is fixed vertically to the horizontal scale, and the axial reference platform is provided on one side of the sixth support rod. The axial reference platform is used to abut against one side of the engine tenon as it moves with the horizontal scale.

9. The apparatus for determining the position of strain gauge patches on aero-engine blades according to any one of claims 1-3, characterized in that: The device for determining the position of the strain gauge patch on the aero-engine blade further includes two normal auxiliary fixing brackets. The two normal auxiliary fixing brackets are movably disposed on the working surface along the normal direction. The two normal auxiliary fixing brackets are used to move closer to or further away from each other along the normal direction to limit the normal position of the engine blade.

10. The apparatus for determining the position of strain gauge patches on an aero-engine blade according to any one of claims 1-3, characterized in that: The device for determining the position of the strain gauge patch on the aero-engine blade further includes a direction protractor, which is fixed on the horizontal scale and is used to measure the angle between the strain gauge patch and the vertical or horizontal direction.

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