CN113670822A

CN113670822A - Aeroengine blade detecting system

Info

Publication number: CN113670822A
Application number: CN202111138786.XA
Authority: CN
Inventors: 郑云东; 赖桂林; 刘后勇; 柏洪进; 吴民真; 叶水凌; 姜进
Original assignee: Shenzhen Coantec Automation Technology Co ltd
Current assignee: Shenzhen Coantec Automation Technology Co ltd
Priority date: 2021-09-27
Filing date: 2021-09-27
Publication date: 2021-11-19

Abstract

The invention discloses an aircraft engine blade detection system, which comprises a host and a plurality of detection devices, wherein the detection devices are connected with the host and are provided with at least two imaging modules; the detection device is used for being inserted into the aircraft engine and imaging the blade in the aircraft engine through the imaging module; the host computer is used for receiving and processing the image of the detection device. According to the blade detection system of the aircraft engine, the plurality of detection devices are arranged, so that a dozen of circles of blades can be detected by the plurality of detection devices simultaneously when the blade detection system is used, at least two imaging modules are arranged on each detection device, different blades in the current circle are imaged simultaneously, one-time imaging of the blades can be realized through one-time operation, repeated imaging operation is reduced, the efficiency is high, the task amount is small, and the operation is simple.

Description

Aeroengine blade detecting system

Technical Field

The invention relates to the technical field of blade detection of aero-engines, in particular to a blade detection system of an aero-engine.

Background

An aircraft engine is a highly complex and precise thermal machine that serves as the heart of an aircraft and is the motive force for aircraft flight. Currently, aircraft engines have been developed as mature products with extremely high reliability, and the common aircraft engines include various types of turbojet/turbofan engines, turboshaft/turboprop engines, and the like. The aero-engine not only serves as power for military and civil aircrafts, unmanned planes and cruise missiles with various purposes, but also is widely applied to the fields of ground power generation, marine power, mobile power stations, natural gas and petroleum pipeline pump stations and the like by utilizing a gas turbine derived and developed by the aero-engine.

Dozens of circles of blades are arranged on a transmission shaft of the aero-engine, each circle of blades has four or fifty blades, and the blades are different in length. The blade needs to be detected irregularly, and the damaged part is found through the imaging of a detection probe so as to be repaired in time. When the conventional probe is used for imaging detection, the blade needs to be shot three times from inside to outside, and then the picture is synthesized into a complete blade picture, so that the efficiency is low, the task load is large, and the operation is complicated.

Disclosure of Invention

The invention aims to provide a blade detection system of an aircraft engine, which has the advantages of high imaging efficiency, small task load and simplicity in operation.

The invention discloses an aircraft engine blade detection system, which comprises a host and a plurality of detection devices, wherein the detection devices are connected with the host and are provided with at least two imaging modules; the detection device is used for being inserted into the aircraft engine and imaging the blade in the aircraft engine through the imaging module; the host computer is used for receiving and processing the image of the detection device.

Optionally, the detection device comprises a handle and a rod body; the imaging module sets up on the body of rod, and the imaging module arranges the setting along the axial of the body of rod.

Optionally, there are 3 imaging modules.

Optionally, the rod body comprises a front rod part, a rear rod part and a connecting piece; the imaging module is arranged on the front rod part, the front rod part is connected with the rear rod part through a connecting piece, and the rear rod part is connected with the handle; the connecting piece is used for being matched and fixed with a detection hole position on the aero-engine, so that the front rod part extends into the aero-engine through the detection hole position, and then the detection device is fixed on the aero-engine.

Optionally, a first sinking groove is formed in the end part, connected with the front rod part, of the connecting piece, and a limiting bump is arranged in the first sinking groove; the front rod part comprises a first shell and a second shell, and the first shell and the second shell are mutually covered; the end part of the first shell connected with the connecting piece extends out of the end part of the second shell connected with the connecting piece and is provided with an opening; the end part of the first shell connected with the connecting piece is inserted into the first sinking groove, and the limiting lug is embedded into the opening.

Optionally, the end of the connecting member connected to the rear rod portion is provided with a second sinking groove, and the rear rod portion is connected to the second sinking groove.

Optionally, the front rod part comprises a first shell, a second shell and a lighting module, the first shell and the second shell are mutually covered and connected with the connecting piece, and the lighting module is arranged in the first shell and the second shell; the second shell is provided with an opening, and the imaging module and the lighting module are located in the opening.

Optionally, the front rod part further comprises a first circuit board disposed in the first housing and the second housing; a through hole is formed in the first circuit board, and the imaging module penetrates out of the through hole; the lighting module is arranged on the first circuit board and is positioned at two sides of the imaging module.

Optionally, the front rod part comprises a first shell, a second shell and a lighting module, and the first shell and the second shell are mutually covered and connected with the connecting piece; the second shell is provided with a mounting hole, and the lighting module and the imaging module are respectively mounted in the mounting hole.

Optionally, the length is different between the plurality of detection devices.

According to the blade detection system of the aircraft engine, the plurality of detection devices are arranged, so that a dozen of circles of blades can be detected by the plurality of detection devices simultaneously when the blade detection system is used, at least two imaging modules are arranged on each detection device, different blades in the current circle are imaged simultaneously, one-time imaging of the blades can be realized through one-time operation, repeated imaging operation is reduced, the efficiency is high, the task amount is small, and the operation is simple.

Drawings

The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort. In the drawings:

FIG. 1 is a schematic diagram of a host according to an embodiment of the invention;

FIG. 2 is a schematic view of a detection apparatus according to an embodiment of the present invention;

fig. 3 is a partially enlarged view of a portion a in fig. 2;

FIG. 4 is a schematic view of a connector according to an embodiment of the present invention;

FIG. 5 is another schematic view of a connector according to an embodiment of the present invention;

FIG. 6 is another schematic view of a detection device according to an embodiment of the present invention;

fig. 7 is a schematic view of a front rod portion of an embodiment of the present invention.

Wherein, 1, a host; 11. a first data interface; 12. a keyboard; 13. a screen; 14. heat dissipation holes; 2. a detection device; 21. a handle; 22. a second data interface; 23. a rod body; 231. a front rod part; 231a, a first housing; 231a1, opening; 231b, a second housing; 231b1, open pore; 231b2, mounting holes; 231c, a lighting module; 231d, a first circuit board; 231d1, through-holes; 231e, an imaging module; 232. a rear rod portion; 233. a connecting member; 233a, a first sink tank; 233b, a limit bump; 233c, a second sink tank.

Detailed Description

It is to be understood that the terminology, the specific structural and functional details disclosed herein are for the purpose of describing particular embodiments only, and are representative, but that the present invention may be embodied in many alternate forms and should not be construed as limited to only the embodiments set forth herein.

The invention is described in detail below with reference to the figures and alternative embodiments.

As shown in fig. 1 to 3, as an embodiment of the present invention, an aircraft engine blade detection system is disclosed, which includes a host 1 and a plurality of detection devices 2, wherein the detection devices 2 are connected to the host 1, and the detection devices 2 are provided with at least two imaging modules 231 e; the detection device 2 is used for being inserted into an aircraft engine and imaging blades in the aircraft engine through an imaging module 231 e; the host 1 is used for receiving and processing images of the detection device 2.

According to the blade detection system of the aircraft engine, the plurality of detection devices 2 are arranged, so that a dozen or more circles of blades can be detected by the plurality of detection devices 2 simultaneously when the blade detection system is used, and each detection device 2 is provided with at least two imaging modules 231e, so that different blades in the current circle can be imaged simultaneously, one-time imaging of the blades can be realized through one-time operation, repeated imaging operation is reduced, the efficiency is high, the task amount is small, and the operation is simple. After receiving the images of the respective inspection devices 2, the host computer 1 processes the images, such as synthesizing the images, so that the inspector can know the condition of the blades inside the engine.

Specifically, a detection hole site specially used for detection is arranged on the engine, and the detection device 2 can be inserted into the engine from the detection hole site to image the blade. The connection between the detection device 2 and the host 1 may be a wired connection or a wireless connection.

Alternatively, as shown in fig. 2 and 3, the detection device 2 device includes a handle 21 and a rod 23; the imaging modules 231e are disposed on the rod body 23, and the imaging modules 231e are arranged in an axial direction of the rod body 23. The imaging modules 231e are arranged along the axial direction of the rod body 23, and when the rod body 23 extends into the detection hole position, each imaging module 231e is opposite to the blades at different positions of the current ring, so that the blades at different positions can be conveniently imaged. In addition, in this scheme, divide into handle 21 and the body of rod 23 with detection device 2, handle 21 can make things convenient for the person who detects to grasp detection device 2, stretches into the engine inside with detection device 2 from the detection hole site, or takes out from the inside. And imaging module 231e sets up on the body of rod 23, conveniently stretches into engine inside with imaging module 231e from detecting the hole site. The specific position of the imaging module 231e may be set to correspond to the position of the blade to be detected. The engine is internally provided with more than ten circles of blades, each circle of blades can correspond to a specific detection device 2 in the plurality of detection devices 2 for detection, and the specific position of the imaging module 231e on the detection device 2 is set according to the corresponding blade.

The imaging modules 231e may be provided in two, three, four, or even more as needed. Specifically, there are 3 imaging modules 231 e. In the scheme, the number of the imaging modules 231e is 3, and three positions can be imaged, so that a complete blade image can be synthesized, and the efficiency is high.

Optionally, the lever 23 comprises a front lever 231, a rear lever 232 and a connector 233; the imaging module 231e is arranged on the front rod 231, the front rod 231 is connected with the rear rod 232 through a connecting piece 233, and the rear rod 232 is connected with the handle 21; the connecting member 233 is used for being fixed in a matching manner with a detection hole on the aircraft engine, so that the detection device 2 is fixed on the aircraft engine after the front rod 231 extends into the aircraft engine through the detection hole. The connecting piece 233 is matched with a detection hole position on the engine, during detection, the detection device 2 can be fixed on the aero-engine, and when a plurality of detection devices 2 are used for detection at the same time, the detection devices 2 can be sequentially fixed on the aero-engine, so that the operation is convenient.

Optionally, as shown in fig. 4 and 7, a first sinking groove 233a is formed at an end of the connecting member 233 connected to the front rod 231, and a limiting protrusion 233b is disposed in the first sinking groove 233 a; the front rod 231 includes a first housing 231a and a second housing 231b, and the first housing 231a and the second housing 231b are covered with each other; the end of the first shell 231a connected with the connecting piece 233 extends out of the end of the second shell 231b connected with the connecting piece 233, and the end of the first shell 231a connected with the connecting piece 233 is provided with an opening 231a 1; the end of the first housing 231a connected to the link 233 is inserted into the first sinking groove 233a, and the restricting projection 233b is inserted into the opening 231a 1. In this scheme, through the spacing of first heavy groove 233a and spacing lug 233b, first heavy groove 233a can play the location and spacing first casing 231a tip, can prevent that front rod portion 231 from rotating, also can play the effect of holding first casing 231a tip, makes things convenient for front rod portion 231 to install. The engagement between the opening 231a1 and the limit projection 233b can serve to position and limit the rotation of the front rod 231.

Alternatively, as shown in fig. 5, the end of the connecting member 233 connected to the rear rod part 232 is provided with a second sunken groove 233c, and the rear rod part 232 is connected in the second sunken groove 233 c. The second sink groove 233c may limit the rear rod part 232.

Alternatively, as shown in fig. 3, the front lever 231 includes a first housing 231a, a second housing 231b, and an illumination module 231c, the first housing 231a and the second housing 231b are covered with each other and connected with the connection member 233, and the illumination module 231c is disposed in the first housing 231a and the second housing 231 b; the second housing 231b is formed with an opening 231b1, and the imaging module 231e and the illumination module 231c are disposed in the opening 231b 1. The illumination module 231c can illuminate the imaging part, and the imaging effect is better. In addition, the imaging module 231e and the illumination module 231c are located in the opening 231b1, so that the heat dissipation effect is good.

Alternatively, as shown in fig. 3, the front lever 231 further includes a first circuit board 231d, the first circuit board 231d being disposed in the first and

second housings

231a and 231 b; a through hole 231d1 is formed in the first circuit board 231d, and the imaging module 231e penetrates out of the through hole 231d 1; the illumination module 231c is disposed on the first circuit board 231d and is positioned at both sides of the imaging module 231 e. The through hole 231d1 can also function as a stopper for the imaging module 231e while avoiding the imaging module 231 e. The illumination module 231c has a wide illumination angle at both sides of the entertainment imaging module 231e, so that shadow can be prevented from being generated, and an imaging effect is good. In addition, the first circuit board 231d may also dissipate heat through the opening 231b 1. In another embodiment, as shown in fig. 6 and 7, the front lever 231 includes a first housing 231a, a second housing 231b, and an illumination module 231c, the first housing 231a and the second housing 231b cover each other and are connected with the connection member 233; the second housing 231b is opened with a mounting hole 231b2, and the illumination module 231c and the imaging module 231e are respectively mounted in the mounting hole 231b 2. In this embodiment, the illumination module 231c and the imaging module 231e are respectively mounted in the respective mounting holes 231b2, and are firmly mounted.

Alternatively, the lengths of the plurality of detection devices 2 are different from each other. The diameter of each circle of blades in the engine is different, and the lengths of the plurality of detection devices 2 are different, so that the blades with different diameters can be applied. The specific length of the detecting device 2 can be set according to the corresponding blade diameter. More specifically, the handles 21 of the respective detecting devices 2 are the same length, and the front rod portions 231 are different in length.

Optionally, as shown in fig. 1, the host 1 includes a first data interface 11, a keyboard 12, a screen 13, a heat dissipation hole 14, and the like, and a second data interface 22 is disposed at an end of a handle 21 of the detection device 2 and is used for connecting with the first data interface 11. The second data interface 22 is arranged at the end of the handle 21, so that a data wire can be conveniently connected, and the data wire is not easy to interfere with the operation of a detector.

The foregoing is a more detailed description of the invention in connection with specific alternative embodiments, and the practice of the invention should not be construed as limited to those descriptions. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.

Claims

1. The blade detection system of the aircraft engine is characterized by comprising a host and a plurality of detection devices, wherein the detection devices are connected with the host and are provided with at least two imaging modules; the detection device is used for being inserted into the aircraft engine and imaging the blade in the aircraft engine through the imaging module; the host is used for receiving and processing the image of the detection device.

2. The detection system of claim 1, wherein the detection device comprises a handle and a shaft; the imaging module is arranged on the rod body, and the imaging module is arranged along the axial direction of the rod body.

3. The inspection system of claim 2, wherein there are 3 imaging modules.

4. The detection system of claim 2, wherein the shaft includes a front shaft portion, a rear shaft portion, and a connector; the imaging module is arranged on the front rod part, the front rod part is connected with the rear rod part through the connecting piece, and the rear rod part is connected with the handle; the connecting piece is used for being matched and fixed with a detection hole position on the aircraft engine, so that the front rod part extends into the interior of the aircraft engine through the detection hole position, and the detection device is fixed on the aircraft engine.

5. The detection system as claimed in claim 4, wherein the end of the connecting piece connected with the front rod part is provided with a first sunken groove, and a limit bump is arranged in the first sunken groove; the front rod part comprises a first shell and a second shell, and the first shell and the second shell are mutually covered; the end part of the first shell connected with the connecting piece extends out of the end part of the second shell connected with the connecting piece and is provided with an opening; the end part of the first shell connected with the connecting piece is inserted into the first sinking groove, and the limiting lug is embedded into the opening.

6. The inspection system of claim 4, wherein the end of the connector that is connected to the rear rod portion is provided with a second sunken groove in which the rear rod portion is connected.

7. The detection system according to claim 4 or 5, wherein the front lever portion includes a first housing, a second housing, and an illumination module, the first housing and the second housing being mutually covered and connected with the connecting member, the illumination module being provided in the first housing and the second housing; the second shell is provided with an opening, and the imaging module and the lighting module are located in the opening.

8. The detection system of claim 7, wherein the front stem portion further comprises a first circuit board disposed in the first housing and the second housing; a through hole is formed in the first circuit board, and the imaging module penetrates out of the through hole; the lighting module is arranged on the first circuit board and positioned on two sides of the imaging module.

9. The detection system according to claim 4 or 5, wherein the front rod portion includes a first housing, a second housing, and an illumination module, the first housing and the second housing being mutually covered and connected with the connecting member; the second shell is provided with a mounting hole, and the lighting module and the imaging module are respectively mounted in the mounting hole.

10. The detection system according to any one of claims 1 to 6, wherein the lengths of the plurality of detection devices are different from one another.