Auxiliary measuring device for an aero-engine

Abstract

The auxiliary measuring device of the aero-engine is suitable for detecting whether the flatness of an aero-product is qualified in rotation test, and 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, the other end is provided with a closed structure, the cross section size of the guide shaft is larger 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, one end of the cross beam is installed on the guide shaft near the position of the rectangular hole, the other end of the cross beam is provided with a detection assembly, the detection assembly is used for detecting whether the flatness of the side surface of the rotating part of the aero-product is qualified when the rotating part of the aero-product rotates relative to the inner ring surface of the product, and the detection efficiency can be improved.

Description

Technical Field

[0001] This invention belongs to the technical field of flatness detection devices, and particularly relates to an auxiliary measurement device for aero-engines. Background Technology

[0002] When inspecting rotating parts of aviation products, manual measurement is generally used. For example, when an external drive device rotates the rotating part, a dial indicator is used to manually measure whether the flatness of one side of the rotating part is up to standard. This method is inefficient and time-consuming.

[0003] In view of this, the present invention is hereby proposed. Summary of the Invention

[0004] The auxiliary measurement device for aero-engines provided by this invention solves the technical problem of low efficiency in detecting the flatness of aero-related products using traditional methods. The technical solution of this invention has many beneficial effects, as described below:

[0005] An auxiliary measuring device for aero-engines is provided, suitable for detecting the flatness of aero-products during rotational testing. It includes a hollow elastic clamp, a pull rod, a crossbeam, a guide shaft, and a tapered tensioning mechanism. One end of the elastic clamp has a pre-defined flared inner ring surface, while the other end is closed. The guide shaft has a cross-sectional dimension larger than that of the pull rod, and its outer ring surface has a rectangular hole along the axial direction. The pull rod has a radially arranged fixing rod.

[0006] The elastic clamp is an open-type horn structure and is placed on the inner ring surface of the aviation product. The tensioning mechanism is installed on the inner ring surface of the large end of the elastic clamp in a contact manner, and the guide shaft is fixedly installed on the side of the small end of the elastic clamp.

[0007] The pull rod passes through the tensioning mechanism, the elastic clamp, and the guide shaft, and has an extension section. A shoulder nut is installed on the extension section, and the fixed rod extends out of the rectangular hole to limit the rotation of the pull rod. Rotating the shoulder nut and under the action of action and reaction forces, the pull rod can reciprocate along the axial direction, which can drive the tensioning mechanism to move in the horizontal direction, thereby deforming the large end of the elastic clamp to press against the inner ring surface of the aerospace product.

[0008] 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 is qualified when the rotating part of the aerospace product rotates relative to the inner ring surface of the aerospace product.

[0009] Compared with the prior art, the technical solution provided by the present invention has the following beneficial effects:

[0010] The structure of this invention uses an internal clamping device to tighten the inner ring surface of the product, and an external device to drive the rotating part of the product to rotate. It adopts a semi-automatic method to replace manual inspection, which is time-saving and has high inspection efficiency. Attached Figure Description

[0011] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0012] Figure 1 Front sectional view of the invention;

[0013] Figure 2 This is a top view of the guide axis;

[0014] Figure 3 for Figure 1 Axial sectional view of the middle AA axis, wherein,

[0015] 1. Elastic chuck; 2. Tensioning mechanism; 3. Measuring head; 4. Anti-rotation pin; 5. Measuring rod; 6. Pull rod; 7. Crossbeam; 8. Sleeve; 9. Gauge clamp; 10. Guide shaft; 11. Shoulder nut; 12. Limiting block; 13. Fixing rod; 14. Rectangular hole; 17. Tangential clamping component. Detailed Implementation

[0016] 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 the present invention, and not all of them. The present invention 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 the present invention. 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 the present invention without creative effort are within the scope of protection of the present invention.

[0017] 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 invention, 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 structures and / or functionalities other than one or more of the aspects set forth herein.

[0018] like Figures 1 to 3 The aero-engine auxiliary measuring device shown is suitable for detecting the flatness of aero-engine products during rotational testing, typically for the casing. It includes a hollow elastic chuck 1, a pull rod 6, a crossbeam 7, a guide shaft 10, and a tapered tensioning mechanism 2. One end of the elastic chuck 1 has a pre-defined flared inner ring, while the other end is closed. The guide shaft 10 has a larger cross-sectional dimension than the pull rod 6. The outer ring of the guide shaft 10 has a rectangular hole 14 along its axial direction. The pull rod 6 has a radially arranged fixing rod 13.

[0019] The elastic chuck 1 has an open horn structure and is placed on the inner ring surface of the aviation product. The tensioning mechanism 2 is installed on the inner ring surface of the large end of the elastic chuck 1 in a contact manner, and the guide shaft 10 is fixedly installed on the side of the small end of the elastic chuck 1.

[0020] The pull rod 6 passes through the tensioning mechanism 2, the elastic chuck 1, and the guide shaft 10, with 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 under the action of action and reaction forces, the pull rod 6 can reciprocate along the axial direction, which can drive the tensioning mechanism 2 to move in the horizontal direction, thereby deforming the large end of the elastic chuck 1 to press against the inner ring surface of the aerospace product.

[0021] One end of a crossbeam 7 is installed on the guide shaft 10 near the rectangular hole 14. The other end of the crossbeam 7 is equipped with a detection component. The detection component is used to detect whether the flatness of the side of the rotating part is up to standard when the rotating part of the aerospace product rotates relative to the inner ring surface of the aerospace product.

[0022] In one specific embodiment, the tensioning mechanism 2 is arranged in a mountain-shaped structure, with the orientation of the mountain-shaped opening as shown in the diagram as a reference. Its detection components include a sleeve 8, a measuring rod 5, a measuring head 3, a gauge clamp 9, and a detection gauge. The measuring head 3 contacts the surface of the aerospace product to be tested, and an anti-rotation pin 4 is installed on the measuring head 3.

[0023] The sleeve 8 is horizontally installed at one end of the crossbeam 7, and the end of the sleeve 8 away from the product is installed with the gauge clamp 9, and the gauge is installed in the gauge clamp 9.

[0024] One end of the measuring rod 5 is equipped with a measuring head 3, and the other end is connected to a test gauge. When the rotating part of the aviation product rotates, the flatness of the product is judged by reading the displacement of the measuring rod 5 in the horizontal direction under the action of the measuring head 3.

[0025] Furthermore, a tangential clamping member 17 is installed on the crossbeam 7, which can fasten the sleeve 8. A limit block 12 is installed on the pull rod 6 between the elastic clamp 1 and the tensioning mechanism 2. The limit block 12 is used to prevent the pull rod 6 from disengaging from the tensioning mechanism 2.

[0026] The product provided by this invention has been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the embodiments above are merely for the purpose of helping to understand the core ideas of this invention. It should be noted that those skilled in the art can make various improvements and modifications to the invention without departing from the principles of the invention, and these improvements and modifications also fall within the protection scope of the invention claims.

Claims

1. An auxiliary measuring device for aircraft engines, suitable for detecting the flatness of aircraft products during rotational testing, characterized in that, The device includes a hollow elastic clamp, a tie rod, a crossbeam, a guide shaft, and a tapered tensioning mechanism. One end of the elastic clamp has a pre-defined flared inner ring, while the other end is closed. The guide shaft has a larger cross-sectional dimension than the tie rod, and its outer ring has a rectangular hole along the axial direction. The tie rod has a radially arranged fixing rod. The elastic clamp is an open-type horn structure and is placed on the inner ring surface of the aviation product. The tensioning mechanism is installed on the inner ring surface of the large end of the elastic clamp in a contact manner, and the guide shaft is fixedly installed on the side of the small end of the elastic clamp. The pull rod passes through the tensioning mechanism, the elastic clamp, and the guide shaft, and has an extension section. A shoulder nut is installed on the extension section, and the fixed rod extends out of the rectangular hole to limit the rotation of the pull rod. Rotating the shoulder nut and under the action of action and reaction forces, the pull rod can reciprocate along the axial direction, which can drive the tensioning mechanism to move in the horizontal direction, thereby deforming the large end of the elastic clamp to press against the inner ring surface of the aerospace 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 is qualified when the rotating part of the aerospace product rotates relative to the inner ring surface of the aerospace product.

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

3. The aero-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. The measuring head contacts the surface of the aerospace product to be tested. The sleeve is horizontally installed at one end of the crossbeam, and the gauge clamp is installed at the end of the sleeve away from the product, and the test gauge is installed inside the gauge clamp; The measuring rod is equipped with the measuring head at one end and connected to the test gauge at the other end. When the rotating part of the aviation product rotates, the flatness of the product is judged by reading the horizontal displacement of the measuring rod under the action of the measuring head through the test gauge.

4. The aero-engine auxiliary measurement device according to claim 3, characterized in that, A tangential clamping element is installed on the crossbeam, which can fasten the sleeve.

5. The aero-engine auxiliary measuring 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. The limit block is used to prevent the pull rod from detaching from the tensioning mechanism.

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