Aero-engine auxiliary measuring device

Abstract

The aero-engine auxiliary measuring device is suitable for detecting whether the flatness of an aviation product is qualified or not in a rotation test, and comprises an elastic chuck of a hollow structure, a pull rod, a cross beam, a guide shaft and a tensioning mechanism of a conical structure, and the inner ring surface of one end of the elastic chuck is of a horn structure with a preset length; the cross section size of the guide shaft is larger than that of the pull rod, a rectangular hole is formed in the outer ring face of the guide shaft in the axial direction, a fixing rod is arranged on the pull rod in the radial direction, one end of a cross beam is installed at the position, close to the rectangular hole, of the guide shaft, and a detection assembly is installed at the other end of the cross beam. The detection assembly is used for detecting whether the flatness of the side face of the rotating part is qualified or not when the rotating part of the aviation product rotates relative to the inner ring face of the product, and the detection efficiency can be improved.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of flatness detection devices, and particularly relates to an auxiliary measurement device for an aero-engine. BACKGROUND

[0002] When a rotating part of an aero product is detected, a manual dialing method is generally used for recording. For example, when the rotating part is rotated by an external driving device, a person manually measures whether the flatness of one side of the rotating part is qualified by using a dial gauge. This method is low in efficiency and time-consuming.

[0003] Therefore, the application is provided. SUMMARY

[0004] The auxiliary measurement device for an aero-engine provided by the application solves the technical problem of low detection efficiency of the flatness of an aero product in the prior art. The technical scheme of the application has many technical advantages, which are described as follows. The auxiliary measurement device for an aero-engine is suitable for detecting whether the flatness of an aero product is qualified in rotation test. The device comprises an elastic chuck with a hollow structure, a pull rod, a cross beam, a guide shaft and a tensioning mechanism with a conical structure. The inner ring surface of one end of the elastic chuck is provided with a horn structure with a preset length, and the other end is provided with a closed structure. The cross-sectional dimension of the guide shaft is greater than that of the pull rod. The outer ring surface of the guide shaft is provided with a rectangular hole in the axial direction. The pull rod is provided with a fixed rod in the radial direction. The elastic chuck is provided with an open horn structure and is arranged on the inner ring surface of the aero product. The inner ring surface of the large end of the elastic chuck is installed in a contact manner with the tensioning mechanism. The small end side of the elastic chuck is fixedly installed with the guide shaft. The pull rod passes through the tensioning mechanism, the elastic chuck and the guide shaft and has an extension section. A shoulder nut is installed on the extension section. The fixed rod extends out of the rectangular hole to limit the rotation of the pull rod. The shoulder nut is rotated and driven to reciprocate in the axial direction under the action of the force and the counterforce, so as to drive the tensioning mechanism to move in the horizontal direction, thereby deforming the large end of the elastic chuck to tightly press the inner ring surface of the aero product. One end of the cross beam is installed on the guide shaft near the rectangular hole. The other end of the cross beam is installed with a detection assembly. The detection assembly is used to detect whether the flatness of the side of the rotating part of the aero product is qualified when the rotating part rotates relative to the inner ring surface of the product.

[0005] Compared with the prior art, the technical scheme provided by the application has the following advantages: The structure of the present application adopts the inner ring surface of the internal top product, and the external device drives the rotation part of the product to rotate, adopts the semi-automatic detection mode to replace the manual detection mode, and has short time consumption and high detection efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0006] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings required to be used in the embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0007] Figure 1 The front view of the present application; Figure 2 The top view of the guide shaft; Figure 3 Figure 1 The side view of the A-A axis of the present application, 1, elastic chuck; 2, tensioning mechanism; 3, measuring head; 4, anti-rotation pin; 5, measuring rod; 6, pull rod; 7, cross beam; 8, sleeve; 9, table clamp; 10, guide shaft; 11, shoulder nut; 12, limit block; 13, fixed rod; 14, rectangular hole; 17, tangential clamping piece. DETAILED DESCRIPTION

[0008] The embodiments of the present application will be described below through specific concrete examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in the specification. Obviously, the described embodiments are only some of the embodiments of the present application, not all. The present application can also be implemented or applied by other different specific embodiments, and the details in the specification can also be modified or changed based on different views and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0009] ​It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present invention, those skilled in the art will appreciate that an 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 described herein can be used to implement an apparatus and / or practice a method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this apparatus and / or practice this method.

[0010] like Figures 1 to 3 The aircraft engine auxiliary measuring device shown is suitable for testing whether the flatness of aviation products is qualified during rotation testing, generally for testing the casing. It includes an elastic chuck 1 with a hollow structure, a pull rod 6, a crossbeam 7, a guide shaft 10 and a tensioning mechanism 2 with a conical structure. The inner ring surface of one end of the elastic chuck 1 is a trumpet structure with a preset length, and the other end is a closed structure. The cross-sectional size of the guide shaft 10 is larger than that of the pull rod 6. The outer ring surface of the guide shaft 10 is provided with a rectangular hole 14 along the axial direction. The pull rod 6 is radially provided with a fixing rod 13, wherein, The elastic collet 1 is an open trumpet structure and is placed on the inner ring surface of the aviation product. The inner ring surface of the large end of the elastic collet 1 is installed with a tensioning mechanism 2 in a contact manner, and the side surface of the small end of the elastic collet 1 is fixedly installed with a guide shaft 10. The pull rod 6 passes through the tensioning mechanism 2, the elastic collet 1 and the guide shaft 10 and leaves an extended section. A shoulder nut 11 is installed on the extended section, and the fixing rod 13 extends out of the rectangular hole 14 to limit the rotation of the pull rod 6. Rotating the shoulder nut 11 and driving the pull rod 6 to reciprocate in the axial direction under the action of the action force and the release force can drive the tensioning mechanism 2 to move in the horizontal direction, thereby deforming the large end of the elastic collet 1 to press against the inner annular surface of the aviation product; One end of the crossbeam 7 is installed on the guide shaft 10 near the rectangular hole 14, and the other end of the crossbeam 7 is installed with a detection component. The detection component is used to detect whether the flatness of the side of the rotating part of the aviation product is qualified when the rotating part rotates relative to the inner ring surface of the product.

[0011] In a specific embodiment, the tensioning mechanism 2 is arranged in a mountain-shaped structure, and the mountain-shaped opening is placed in the direction shown in the figure as a reference. Its detection assembly includes a sleeve 8, a measuring rod 5, a measuring head 3, a table clamp 9 and a detection table. The measuring head 3 contacts the surface to be tested of the aviation product, and an anti-rotation pin 4 is installed on the measuring head 3, wherein, The sleeve 8 is horizontally installed at one end of the beam 7, and a meter clamp 9 is installed at one end of the sleeve 8 principle product, and a test meter is installed in the meter clamp 9; One end of the measuring rod 5 is installed with the measuring head 3, and the other end is connected with the measuring table. When the rotating part of the aviation product rotates, the displacement degree of the measuring rod 5 in the horizontal direction is read through the detecting table under the action of the measuring head 3, so as to determine whether the flatness of the product is qualified.

[0012] Further, the cross beam 7 is installed with the tangential clamping part 17, the tangential clamping part 17 can fasten the sleeve 8, the limiting block 12 is installed between the elastic chuck 1 and the tensioning mechanism 2 on the pull rod 6, and the limiting block 12 is used for preventing the pull rod 6 from being separated from the tensioning mechanism 2.

[0013] The product provided by the application is described in detail above. The principle and implementation mode of the application are described by applying specific examples in the text, and the above embodiment is only used for helping to understand the core idea of the application. It should be pointed out that, for ordinary skilled persons in the technical field, some improvements and modifications can be made to the application without departing from the principle of the application, and these improvements and modifications also fall within the protection scope of the application claims.

Claims

1. An auxiliary measuring device for aircraft engines, suitable for detecting whether the flatness of aircraft products is qualified during rotation testing, characterized in that: The invention comprises an elastic chuck with a hollow structure, a pull rod, a crossbeam, a guide shaft and a tensioning mechanism with a conical structure. The inner ring surface at one end of the elastic chuck is a trumpet structure with a preset length, and the other end is a closed structure. The cross-sectional size of the guide shaft is larger than that of the pull rod. A rectangular hole is opened in the outer ring surface of the guide shaft along the axial direction. The pull rod is radially provided with a fixing rod, wherein, The elastic collet is an open horn structure and is placed on the inner ring surface of the aviation product. The inner ring surface of the large end of the elastic collet is mounted with the tensioning mechanism in a contact manner, and the side surface of the small end of the elastic collet is fixedly mounted with the guide shaft. The pull rod passes through the tensioning mechanism, the elastic collet and the guide shaft and leaves an extended section, a shoulder nut is installed on the extended section, and the fixing rod extends out of the rectangular hole to limit the rotation of the pull rod, and the shoulder nut is rotated and the pull rod is driven to reciprocate along the axial direction under the action of the working force and the generating force, which can drive the tensioning mechanism to move in the horizontal direction, so that the large end of the elastic collet is deformed to tighten the inner annular surface of the aviation product; One end of a crossbeam is installed on the guide shaft near the rectangular hole, and a detection component is installed on the other end of the crossbeam. The detection component is used to detect whether the flatness of the side of the rotating part of the aviation product is qualified when the rotating part rotates relative to the inner ring surface of the product.

2. The aircraft engine auxiliary measurement device according to claim 1, characterized in that: The tensioning mechanism is arranged in a mountain-shaped structure.

3. The aircraft engine auxiliary measurement device according to claim 1, characterized in that: The detection assembly includes a sleeve, a measuring rod, a measuring head, a gauge clamp and a detection gauge, wherein the measuring head contacts the surface to be detected of the aviation product, The sleeve is horizontally mounted on one end of the beam, the meter clip is mounted on one end of the sleeve principle product, and the test meter is mounted in the meter clip; The measuring head is installed at one end of the measuring rod, and the other end is connected to the measuring meter. When the rotating part of the aviation product rotates, the horizontal displacement of the measuring rod is read through the detection meter under the action of the measuring head to determine whether the flatness of the product is qualified.

4. The aircraft engine auxiliary measurement device according to claim 3, characterized in that: A tangential clamping piece is mounted on the crossbeam and can fasten the sleeve.

5. The aircraft engine auxiliary measurement device according to claim 4, characterized in that: A limit block is installed on the pull rod between the elastic clamp and the tensioning mechanism, and the limit block is used to prevent the pull rod from being separated from the tensioning mechanism.

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