CN220649413U - Rotor runout detection device of aero-engine - Google Patents
Rotor runout detection device of aero-engine Download PDFInfo
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- CN220649413U CN220649413U CN202321758631.0U CN202321758631U CN220649413U CN 220649413 U CN220649413 U CN 220649413U CN 202321758631 U CN202321758631 U CN 202321758631U CN 220649413 U CN220649413 U CN 220649413U
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- 238000001514 detection method Methods 0.000 title claims abstract description 77
- 238000009434 installation Methods 0.000 claims abstract description 20
- 230000007246 mechanism Effects 0.000 claims abstract description 12
- 230000009191 jumping Effects 0.000 claims abstract description 8
- 230000006835 compression Effects 0.000 claims description 9
- 238000007906 compression Methods 0.000 claims description 9
- 230000007423 decrease Effects 0.000 claims description 5
- 230000000670 limiting effect Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 abstract description 12
- 230000008569 process Effects 0.000 abstract description 11
- 238000005259 measurement Methods 0.000 abstract description 3
- 230000000694 effects Effects 0.000 description 3
- 239000000523 sample Substances 0.000 description 3
- 230000003247 decreasing effect Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
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- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 238000006073 displacement reaction Methods 0.000 description 1
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- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
The utility model provides an aeroengine rotor runout detection device which comprises a mounting bracket and a detection mechanism, wherein the mounting bracket comprises a mounting shaft and two supports, at least one mounting step is arranged on the mounting shaft and used for placing and mounting to-be-detected pieces of different types, the two supports are positioned on two opposite sides of the mounting shaft, and two opposite ends of the mounting shaft are respectively clamped on the supports on the corresponding sides; the detection mechanism comprises at least one detection head, and the detection head is arranged at the detection position of the to-be-detected piece and used for acquiring a jumping signal of the detection position. The installation shaft is provided with at least one installation step, so that assembly detection of parts of different types is facilitated, two sides of the installation shaft are respectively provided with a support for clamping the installation shaft, the axial direction of the installation shaft is limited, axial movement in the measurement process is avoided, and therefore the runout detection precision of different parts is improved.
Description
Technical Field
The utility model relates to the technical field of aeroengines, in particular to an aeroengine rotor runout detection device.
Background
The assembly quality of each part of the aeroengine determines the overall performance of the engine, the geometric characteristics of each part are the requirements to be ensured in the assembly process of the engine, and in order to detect the geometric characteristics of coaxiality, runout and the like of the parts, key parts to be detected of the engine are required to be placed on a detection table for runout characteristic detection.
The current detection table equipment for runout detection requires higher rotation precision, different parts correspond to one detection table, the required cost is extremely high, and the conventional detection table has the problems of large rotation precision error and low suitability of different parts, and has adverse effects on a measurement structure.
Based on this, the inventor of the present application proposes an aero-engine rotor runout detection device, so as to solve the above technical problems.
Disclosure of Invention
The utility model aims to overcome the defects that in the prior art, the equipment cost of a detection table for detecting runout is high and the rotation precision of a conventional detection table is poor.
The utility model solves the technical problems by the following technical proposal:
the utility model provides an aircraft engine rotor runout detection device, which is characterized by comprising: a mounting bracket and a detection mechanism;
the mounting bracket comprises a mounting shaft and two supports, wherein at least one mounting step is arranged on the mounting shaft and used for placing and mounting pieces to be detected of different types, the two supports are positioned on two opposite sides of the mounting shaft, and two opposite ends of the mounting shaft are respectively clamped on the supports on the corresponding sides;
the detection mechanism comprises at least one detection head, and the detection head is arranged at the detection position of the piece to be detected and used for acquiring the jumping signal of the detection position.
According to one embodiment of the utility model, the radial dimensions of at least two of said mounting steps are increasing or decreasing in the axial direction of said mounting shaft.
According to one embodiment of the utility model, a compression nut is further arranged on the outer side of the mounting step, and the compression nut is in threaded fit with the mounting step so as to limit the position of the part to be detected.
According to one embodiment of the utility model, the support comprises a base and a cover plate, wherein the cover plate is positioned above the base and connected with the base;
and a clamping groove is formed between the base and the cover plate and used for placing and clamping the mounting shaft.
According to one embodiment of the utility model, the clamping groove is formed in one side, facing the cover plate, of the base, and the pressing wheel is arranged on one side, facing the base, of the cover plate and is used for pressing the mounting shaft.
According to one embodiment of the utility model, an elastic piece is further arranged between the pressing wheel and the cover plate, two ends of the elastic piece are respectively connected with the cover plate and the pressing wheel, and the elastic piece is used for elastically driving the pressing wheel to press the mounting shaft.
According to one embodiment of the utility model, the cross-sectional dimension of the clamping groove decreases in a direction away from the cover plate.
According to one embodiment of the utility model, one side of the support is also provided with an axial pinch roller, and one end of the axial pinch roller is used for pressing the mounting shaft, so that the mounting shaft is axially limited.
According to one embodiment of the present utility model, an encoder is further provided on one side of the axial pinch roller, and the encoder is configured to obtain an angular phase signal value of the mounting shaft.
According to one embodiment of the utility model, the detection mechanism further comprises a terminal device, one end of the detection head is connected with the terminal device, and the other end of the detection head is connected with the detection position of the piece to be detected.
The utility model has the positive progress effects that:
the rotor runout detection device of the aero-engine at least has the following advantages:
1. the mounting shaft is provided with at least one mounting step, so that the assembly detection of parts of different types can be conveniently adapted, two sides of the mounting shaft are respectively provided with a support for clamping the mounting shaft, the axial direction of the mounting shaft is limited, the axial line movement in the measuring process is avoided, and the jumping detection precision of different parts is improved;
2. the radial dimension of the at least two mounting steps increases or decreases along the axial direction of the mounting shaft, thereby facilitating unidirectional mounting of the piece to be detected and improving the mounting efficiency of the piece to be detected;
3. the cover plate is provided with the elastic piece and the pressing wheel, when the mounting shaft is mounted in the clamping groove, the pressing wheel is propped against the mounting shaft under the elastic action of the elastic piece, so that the shaft axis movement of the mounting shaft is avoided.
Drawings
The above and other features, properties and advantages of the present utility model will become more apparent from the following description in conjunction with the accompanying drawings and embodiments, in which:
FIG. 1 is a front view of an aircraft engine rotor runout detection device of the present utility model;
fig. 2 is a schematic structural view of a support of the rotor runout detection device of the aero-engine.
10. A mounting bracket; 110. a mounting shaft; 111. mounting steps; 112. a compression nut; 120. a support; 121. a base; 122. a cover plate; 123. a clamping groove; 124. a pinch roller; 125. an elastic member; 130. an axial pinch roller; 140. an encoder;
20. a detection mechanism; 210. a detection head; 220. and a terminal device.
Detailed Description
In order to make the above objects, features and advantages of the present utility model more comprehensible, embodiments accompanied with figures are described in detail below.
Embodiments of the present utility model will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the present utility model, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts. Furthermore, although terms used in the present utility model are selected from publicly known and commonly used terms, some terms mentioned in the present specification may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein. Furthermore, it is required that the present utility model is understood, not simply by the actual terms used but by the meaning of each term lying within.
The utility model provides an aero-engine rotor runout detection device, which comprises a mounting bracket 10 and a detection mechanism 20, wherein the mounting bracket 10 comprises a mounting shaft 110 and two supports 120, at least one mounting step 111 is arranged on the mounting shaft 110 and is used for placing and mounting pieces to be detected of different types, the two supports 120 are positioned on two opposite sides of the mounting shaft 110, and the two opposite ends of the mounting shaft 110 are respectively clamped on the supports 120 on the corresponding sides. The detecting mechanism 20 includes at least one detecting head 210, and the detecting head 210 is disposed at a detecting position of the workpiece to be detected, so as to obtain a beat signal at the detecting position.
The mounting shaft 110 is provided with at least one mounting step 111, so that one mounting shaft 110 can be adapted to mount different types or different models of pieces to be detected, and the application range of the detection device is further improved.
In this case, the high-pressure compressor rotor disk of the aero-engine is described as an example, because at least one mounting step 111 is provided, for rotor disks of different types, mounting steps 111 of different sizes can be correspondingly provided, and further, detection of a plurality of rotor disk runout signals can be realized by designing one mounting shaft 110, thereby improving the application range of the detection device.
Two supports 120 are respectively disposed at two ends of the mounting shaft 110, and are used for limiting the axial direction of the mounting shaft 110 in a clamping manner, so that axial movement of the mounting shaft 110 in the detection process is avoided, and the detection precision of the to-be-detected piece is improved.
In one embodiment, the radial dimension of the at least two mounting steps 111 increases or decreases in the axial direction of the mounting shaft 110.
When the number of the mounting steps 111 exceeds two, the radial dimension of the mounting steps 111 may be increased or decreased in one direction, and thus the mounting direction of the member to be detected may be determined, so as to improve the assembly efficiency of the member to be detected.
Specifically, a compression nut 112 is further disposed on the outer side of the mounting step 111, and the compression nut 112 is in threaded engagement with the mounting step 111 to define the position of the part to be detected.
That is, the outer sides of the different mounting steps 111 are respectively provided with a corresponding compression nut 112 which is adapted to be mounted, and after the to-be-detected member is assembled to the corresponding mounting step 111, the position of the to-be-detected member can be limited by clamping the compression nut 112, so that the relative displacement between the to-be-detected member and the mounting shaft 110 is avoided.
After the installation of the installation shaft 110 and the part to be detected is completed, the installation shaft 110 and the part to be detected form a whole to rotate, and under the clamping effect of the supports 120 at two sides of the installation shaft 110, the installation shaft 110 cannot move along the radial direction of the installation shaft, so that the influence of the outside on the jumping detection of the part to be detected is reduced, and the jumping detection precision of the part to be detected is improved.
In one embodiment, the support 120 includes a base 121 and a cover 122, the cover 122 is located above the base 121 and connected to the base 121, and a clamping groove 123 is formed between the base 121 and the cover 122, and the clamping groove 123 is used for placing the clamping installation shaft 110.
The installation axle 110 is clamped in the clamping groove 123, so that the radial direction of the installation axle 110 can be limited, the installation stability of the installation axle 110 is improved, and meanwhile, the influence of the radial runout of the installation axle 110 on the detection precision of the part to be detected in the rotation process is eliminated.
In one embodiment, a clamping groove 123 is formed on a side of the base 121 facing the cover plate 122, a pressing wheel 124 is formed on a side of the cover plate 122 facing the base 121, and the pressing wheel 124 is used for pressing the mounting shaft 110.
When the to-be-detected piece is assembled on the mounting shaft 110, two ends of the mounting shaft 110 are respectively clamped in the clamping grooves 123 of the base 121 at the corresponding side, and meanwhile, the pressing wheel 124 arranged on the cover plate 122 presses against the surface of the mounting shaft 110, so that the jumping detection precision of the to-be-detected piece is prevented from being influenced due to radial movement in the rotation process of the mounting shaft 110.
Specifically, an elastic member 125 is further disposed between the pressing wheel 124 and the cover 122, two ends of the elastic member 125 are respectively connected with the cover 122 and the pressing wheel 124, and the elastic member 125 is used for elastically driving the pressing wheel 124 to press the mounting shaft 110.
When the cover plate 122 is covered above the base 121, the pressing wheel 124 abuts against the outer wall surface of the mounting shaft 110 and compresses the elastic member 125 until the cover plate 122 is connected with the base 121, and the pressing wheel 124 is pressed on the mounting shaft 110 by the elastic force of the elastic member 125, so that the mounting shaft 110 does not radially move during rotation to ensure the runout detection precision of the workpiece to be detected.
In one embodiment, the snap groove 123 decreases in cross-sectional dimension in a direction away from the cover plate 122.
That is, the clamping groove 123 is V-shaped, which is beneficial to improving the clamping stability of the mounting shaft 110.
An axial pinch roller 130 is further disposed on one side of the support 120, and one end of the axial pinch roller 130 is used for pressing the mounting shaft 110.
The axial pinch roller 130 is used for limiting the mounting shaft 110 axially, so that the influence on the detection accuracy caused by the axial movement of the mounting shaft 110 in the jumping detection process of the to-be-detected piece is avoided.
That is, the axial pinch roller 130 and the radial pinch roller 124 can respectively limit the axial direction and the radial direction of the mounting shaft 110, so as to avoid the influence on the runout detection of the workpiece to be detected caused by the axial or radial movement of the mounting shaft 110 in the rotation process.
Further, an encoder 140 is further disposed on one side of the axial pinch roller 130, and the encoder 140 is used for acquiring an angular phase signal value of the mounting shaft 110.
In the process of detecting the runout of the workpiece to be detected, the workpiece to be detected rotates along with the mounting shaft 110, and the encoder 140 can record the angular phase signal value of the mounting shaft 110, so that when the runout value of a certain position of the workpiece to be detected is abnormal, the position of the workpiece to be detected, at which the abnormality occurs, can be quickly found according to the decoding result of the encoder 140.
In one embodiment, the detecting mechanism 20 further includes a terminal device 220, and the detecting head 210 has one end connected to the terminal device 220 and the other end connected to the detecting position of the workpiece to be detected.
The encoder 140 and the plurality of detection heads 210 are connected with the terminal device 220, the terminal device 220 is used for displaying and processing data, and the terminal device 220 includes, but is not limited to, a mobile phone, a tablet computer, a notebook computer, etc., and the processing procedure of the terminal device 220 on the data belongs to technical means well known to those skilled in the art, and is not described herein.
The types of the detecting heads 210 include, but are not limited to, lever heads, electric sensing heads, etc., and the number of the detecting heads can be adjusted according to the needs, and are not limited herein. Here, two lever probes and two inductance probes are described as an example, and four probes interfere with the rotation of the mounting shaft 110.
The measurement process is illustrated as follows:
the first step: the part to be inspected is first mounted to the mounting shaft 110 at the mating mounting step 111 and is then locked using a lock nut.
And a second step of: the mounting shaft 110 and the member to be detected are placed on the base 121, the mounting shaft 110 is limited by the cover plate 122, and then the axial pinch roller 130 is mounted.
And a third step of: after the installation, one end of the plurality of detecting heads 210 is adjusted to the detecting position of the workpiece to be detected, and the other end of the detecting heads is connected to the terminal device 220, and the encoder 140 is synchronously installed on one side of the axial pinch roller 130.
Fourth step: the mounting shaft 110 is manually rotated or the motor is used to drive the mounting shaft 110 to rotate, the mounting shaft 110 drives the workpiece to be detected to synchronously rotate, and the terminal device 220 displays and processes signals detected by the encoder 140 and the detecting head 210, so that the runout detection of the workpiece to be detected is finally realized.
For different shaft parts, different steps can be designed for matching, other structures such as the support 120 are not required to be changed, so that the universality of the detection device is stronger, the cost is saved, and under the limiting effect of the support 120, the axial direction and the radial direction of the mounting shaft 110 are limited, so that the influence of the outside on the runout detection precision of the part to be detected can be reduced.
This application uses specific words to describe embodiments of the application. Reference to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the present application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the present application may be combined as suitable.
While the utility model has been described in terms of preferred embodiments, it is not intended to be limiting, but rather to the utility model, as will occur to those skilled in the art, without departing from the spirit and scope of the utility model. Therefore, any modification, equivalent variation and modification of the above embodiments according to the technical substance of the present utility model fall within the protection scope defined by the claims of the present utility model.
Claims (10)
1. An aeroengine rotor runout detection device, comprising: a mounting bracket and a detection mechanism;
the mounting bracket comprises a mounting shaft and two supports, wherein at least one mounting step is arranged on the mounting shaft and used for placing and mounting pieces to be detected of different types, the two supports are positioned on two opposite sides of the mounting shaft, and two opposite ends of the mounting shaft are respectively clamped on the supports on the corresponding sides;
the detection mechanism comprises at least one detection head, and the detection head is arranged at the detection position of the piece to be detected and used for acquiring the jumping signal of the detection position.
2. The aircraft engine rotor runout detection device of claim 1, wherein the radial dimensions of at least two of the mounting steps are incremented or decremented along the axial direction of the mounting shaft.
3. The aircraft engine rotor runout detection device according to claim 2, wherein a compression nut is further arranged on the outer side of the installation step, and the compression nut is in threaded fit with the installation step so as to limit the position of a piece to be detected.
4. The aircraft engine rotor runout detection device of claim 1, wherein the support comprises a base and a cover plate, the cover plate being located above and connected to the base;
and a clamping groove is formed between the base and the cover plate and used for placing and clamping the mounting shaft.
5. The aircraft engine rotor runout detection device according to claim 4, wherein the clamping groove is formed in one side of the base, facing the cover plate, and a pressing wheel is arranged on one side of the cover plate, facing the base, and is used for pressing the mounting shaft.
6. The aircraft engine rotor runout detection device according to claim 5, wherein an elastic member is further arranged between the pressing wheel and the cover plate, two ends of the elastic member are respectively connected with the cover plate and the pressing wheel, and the elastic member is used for elastically driving the pressing wheel to press the mounting shaft.
7. The aircraft engine rotor runout detection device of claim 4, wherein the snap-in groove decreases in cross-sectional dimension in a direction away from the cover plate.
8. The aircraft engine rotor runout detection device according to any one of claims 1-7, wherein an axial pinch roller is further arranged on one side of the support, and one end of the axial pinch roller is used for pressing a mounting shaft, and limiting the mounting shaft axially.
9. The aircraft engine rotor runout detection device of claim 8, wherein an encoder is further provided on one side of the axial pinch roller, and the encoder is configured to obtain an angular phase signal value of the mounting shaft.
10. The aircraft engine rotor runout detection device according to any one of claims 1 to 7, wherein the detection mechanism further comprises a terminal device, one end of the detection head is connected to the terminal device, and the other end is connected to a detection position of the member to be detected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321758631.0U CN220649413U (en) | 2023-07-05 | 2023-07-05 | Rotor runout detection device of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321758631.0U CN220649413U (en) | 2023-07-05 | 2023-07-05 | Rotor runout detection device of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220649413U true CN220649413U (en) | 2024-03-22 |
Family
ID=90264594
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321758631.0U Active CN220649413U (en) | 2023-07-05 | 2023-07-05 | Rotor runout detection device of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220649413U (en) |
-
2023
- 2023-07-05 CN CN202321758631.0U patent/CN220649413U/en active Active
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