CN215865683U - Aeroengine gas leakage monitoring system - Google Patents
Aeroengine gas leakage monitoring system Download PDFInfo
- Publication number
- CN215865683U CN215865683U CN202121003961.XU CN202121003961U CN215865683U CN 215865683 U CN215865683 U CN 215865683U CN 202121003961 U CN202121003961 U CN 202121003961U CN 215865683 U CN215865683 U CN 215865683U
- Authority
- CN
- China
- Prior art keywords
- processing unit
- aircraft engine
- monitoring system
- display
- image
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012544 monitoring process Methods 0.000 title claims abstract description 43
- 238000012545 processing Methods 0.000 claims abstract description 62
- 238000004891 communication Methods 0.000 claims abstract description 28
- 238000001514 detection method Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000010191 image analysis Methods 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Images
Landscapes
- Examining Or Testing Airtightness (AREA)
Abstract
The utility model provides an aircraft engine gas leakage monitoring system, which comprises an infrared camera, a processing unit and a display, wherein the infrared camera is arranged on the aircraft engine gas leakage monitoring system; the infrared camera is in communication connection with the processing unit, and the processing unit is in communication connection with the display; the infrared camera is arranged outside the aircraft engine and faces the aircraft engine, and is used for acquiring an infrared image of the aircraft engine; the processing unit is used for receiving the infrared image; the processing unit is also used for transmitting the infrared image to the display; the display is used for displaying the infrared image. The utility model provides convenience for monitoring the air leakage of the aero-engine, and the operator can monitor the air leakage in real time without approaching the aero-engine, thereby improving the safety and the monitoring efficiency.
Description
Technical Field
The utility model relates to the technical field of aero-engine gas leakage monitoring, in particular to an aero-engine gas leakage monitoring system.
Background
In the process of development and test run and operation of an aircraft engine, air leakage faults may occur at positions such as a pipeline joint, an air control valve, a mounting seat and the like of the engine, and the air leakage fault detection of the aircraft engine has the following difficulties: firstly, the leaked gas is colorless and transparent, and the leakage fault hardly generates other phenomena and cannot be directly observed; secondly, partial gas leakage fault can only occur in the state above the slow car, and the high temperature and high pressure of the leaked gas can not be close to the personnel for carrying out manual detection due to safety consideration. Although engineers in the current stage adopt several types of manual detection methods, such as surface spraying method, etc., all have obvious disadvantages, the most important of which are: the detection conclusion can be obtained only after the engine test is finished, and the real-time monitoring cannot be realized; in addition, there are other disadvantages: the detection accuracy is not high enough, and the external interference easily causes misjudgment; the manual detection operation is complex, and the detection efficiency is low.
SUMMERY OF THE UTILITY MODEL
The utility model aims to overcome the defect of low air leakage detection efficiency of an aircraft engine in the prior art, and provides an air leakage monitoring system of the aircraft engine.
The utility model solves the technical problems through the following technical scheme:
the utility model provides an aircraft engine gas leakage monitoring system, which comprises an infrared camera, a processing unit and a display, wherein the infrared camera is arranged on the aircraft engine gas leakage monitoring system;
the infrared camera is in communication connection with the processing unit, and the processing unit is in communication connection with the display;
the infrared camera is arranged outside the aircraft engine and faces the aircraft engine, and is used for acquiring an infrared image of the aircraft engine;
the processing unit is used for receiving the infrared image;
the processing unit is also used for transmitting the infrared image to the display;
the display is used for displaying the infrared image.
Preferably, the system for monitoring the air leakage of the aircraft engine further comprises a visible light camera, the visible light camera is in communication connection with the processing unit, the visible light camera is arranged outside the aircraft engine and faces the aircraft engine, and the visible light camera is used for acquiring a visible light image of the aircraft engine;
the processing unit is also used for receiving a visible light image;
the processing unit is further used for transmitting the visible light image to the display;
the display is used for displaying visible light images.
Preferably, the processing unit further stores a normal image, wherein the normal image is an infrared image of a normal aircraft engine;
the processing unit is also used for transmitting the normal image to the display;
the display is also used for simultaneously displaying the infrared image and the normal image.
Preferably, the display includes a touch screen, and the touch screen is configured to sense a touch operation of a user and display a track corresponding to the touch operation.
Preferably, the processing unit is connected with the infrared camera through a first data connecting line; the processing unit is connected with the visible light camera through a second data connecting line.
Preferably, the aircraft engine gas leakage monitoring system further comprises an alarm device;
the processing unit is also used for generating an alarm instruction to control the alarm device to alarm.
Preferably, the alarm device comprises a buzzer.
Preferably, the processing unit is in wireless communication connection with the infrared camera; the processing unit is in wireless communication connection with the visible light camera.
Preferably, the wireless communication connection comprises at least one of a bluetooth communication connection, a Wi-Fi communication connection, and a ZigBee communication connection.
Preferably, the number of the infrared cameras is several.
The positive progress effects of the utility model are as follows: the utility model provides convenience for monitoring the air leakage of the aero-engine, and the operator can monitor the air leakage in real time without approaching the aero-engine, thereby improving the safety and the monitoring efficiency.
Drawings
Fig. 1 is a schematic structural diagram of an aircraft engine air leakage monitoring system according to embodiment 1 of the present invention.
Detailed Description
The utility model will be more clearly and completely described by the following examples in conjunction with the accompanying drawings.
Example 1
The embodiment provides an aircraft engine air leakage monitoring system. Referring to fig. 1, the aircraft engine air leakage monitoring system comprises an infrared camera 1, a processing unit 2 and a display 3.
The infrared camera 1 is in communication connection with the processing unit 2, and the processing unit 2 is in communication connection with the display 3; the infrared camera 1 is arranged outside the aircraft engine 5 and faces the aircraft engine 5, and the infrared camera 1 is used for acquiring an infrared image of the aircraft engine 5; the processing unit 2 is used for receiving the infrared image; the processing unit 2 is also used for transmitting the infrared image to the display 3; the display 3 is used to display an infrared image.
During specific implementation, the aeroengine gas leakage monitoring system further comprises a visible light camera, the visible light camera is in communication connection with the processing unit 2, the visible light camera is arranged outside the aeroengine and faces the aeroengine, and the visible light camera is used for acquiring a visible light image of the aeroengine; the processing unit 2 is also used for receiving visible light images; the processing unit 2 is also used to transmit the visible light image to the display 3; the display 3 is used to display a visible light image. The arrangement mode of the visible light camera can be realized by referring to the arrangement mode of the infrared camera 1.
As an alternative embodiment, the processing unit 2 also stores a normal image, which is an infrared image of a normal aircraft engine; the processing unit 2 is also used to transmit normal images to the display 3; the display 3 is also used to display the infrared image and the normal image simultaneously. The display 3 simultaneously displays the infrared image and the normal image, and an operator can judge the air leakage area of the aircraft engine by comparing the infrared image with the normal image.
As an alternative embodiment, the display 3 includes a touch screen, and the touch screen is used for sensing a touch operation of a user and displaying a track corresponding to the touch operation. When the air leakage area of the aircraft engine is judged by an operator, the air leakage area can be marked on the infrared image through the touch screen, and the air leakage area on the visible light image can also be marked at the corresponding position.
Furthermore, the aeroengine air leakage monitoring system also comprises an alarm device 4; the processing unit 2 is also used for generating an alarm instruction to control the alarm device 4 to alarm. When the operator finds out the leakage area of the aircraft engine through comparison, an alarm command can be sent to the alarm device 4 through the processing unit 2. And the alarm device 4 gives an alarm after receiving the alarm instruction. As an alternative embodiment, the alarm device 4 comprises a buzzer.
As an alternative embodiment, the infrared image, the visible light image, and the normal image are video images.
In some optional embodiments, the processing unit 2 is connected with the infrared camera 1 through a first data connection line; the processing unit 2 is connected with the visible light camera through a second data connecting line.
In other alternative embodiments, the processing unit 2 is connected with the infrared camera 1 in a wireless communication manner; the processing unit 2 is in wireless communication connection with the visible light camera. The wireless communication connection comprises at least one of Bluetooth communication connection, Wi-Fi communication connection and ZigBee communication connection.
As an alternative embodiment, the number of the infrared cameras 1 is several. A plurality of infrared cameras 1 are installed at appropriate positions around the aircraft engine to obtain a more comprehensive monitoring angle.
Based on this aeroengine gas leakage monitoring system, operating personnel can carry out aeroengine gas leakage monitoring long-rangely, and operating personnel need not to be close to aeroengine and can real-time supervision, has improved security and monitoring efficiency.
Example 2
The present embodiment provides an aircraft engine air leakage monitoring system having substantially the same structure as the aircraft engine air leakage monitoring system of embodiment 1.
In this embodiment, the infrared camera 1 and the visible light camera are integrated in the same imaging device. The camera device is used as an information acquisition device of the aero-engine air leakage real-time monitoring system, and the camera device can acquire visible light and infrared rays.
In this embodiment, a plurality of cameras may be installed at appropriate positions around the aircraft engine according to the monitored area, and the cameras will sense the visible light and infrared light on the surface of the aircraft engine and its surroundings in real time, convert the visible light and infrared light into processable electrical signals, and transmit the processed electrical signals to the processing unit 2 through the data line.
The processing unit 2 processes the electric signal transmitted by the infrared detector, converts the electric signal into a video image, compares and analyzes the video image with a normal engine image stored in the system by using an image processing algorithm, automatically identifies an air leakage fault, realizes positioning and identification of the air leakage fault on the visible light image by combining the visible light image, and simultaneously outputs the processing result to the display 3. If an air leakage fault is detected, the processing unit 2 triggers the alarm device 4 to generate an alarm. In addition, the processed video image data is automatically saved to a memory in the processing unit 2 for the monitoring personnel to check and analyze at other times as required.
The display 3 is used for displaying video images for relevant personnel to check the air leakage fault and the occurrence position thereof.
The alarm device 4 is used for generating an alarm when the system monitors an air leakage fault and prompting related personnel.
The working principle of the aero-engine gas leakage monitoring system of the embodiment is as follows:
before the monitoring task is executed, an infrared thermal image of a normal aircraft engine needs to be recorded and stored in the processing unit 2, and the infrared thermal image is used as a standard and a base line for judgment of the processing unit 2. In the monitoring process, the camera collects real-time infrared information of the aircraft engine to form an infrared thermal image, if an air leakage fault is generated at a certain position of the aircraft engine, the temperature of the air at the position is increased, and the color at the position in the thermal image can be changed. The processing unit 2 compares and analyzes the real-time monitored thermal image with a normal aircraft engine infrared thermal image, and then whether a gas leakage fault exists can be judged. If there is an air leakage fault, the processing unit 2 further combines the visible light image analysis and identifies the air leakage position on the visible light image, and outputs all the monitored results to the display 3. When the air leakage fault is monitored, the processing unit 2 sends an instruction to trigger the alarm device 4 to give an alarm, and related personnel are prompted to check the alarm.
While specific embodiments of the utility model have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the utility model is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the utility model, and these changes and modifications are within the scope of the utility model.
Claims (10)
1. An aircraft engine gas leakage monitoring system is characterized by comprising an infrared camera, a processing unit and a display;
the infrared camera is in communication connection with the processing unit, and the processing unit is in communication connection with the display;
the infrared camera is arranged outside the aircraft engine and faces the aircraft engine, and is used for acquiring an infrared image of the aircraft engine;
the processing unit is used for receiving the infrared image;
the processing unit is further configured to transmit the infrared image to the display;
the display is used for displaying the infrared image.
2. The aircraft engine gas leakage monitoring system according to claim 1, further comprising a visible light camera communicatively connected to the processing unit, the visible light camera being disposed outside the aircraft engine and facing the aircraft engine, the visible light camera being configured to acquire a visible light image of the aircraft engine;
the processing unit is further configured to receive the visible light image;
the processing unit is further configured to transmit the visible light image to the display;
the display is used for displaying the visible light image.
3. The aircraft engine air leak monitoring system of claim 1, wherein said processing unit further stores a normal image, said normal image being an infrared image of a normal aircraft engine;
the processing unit is further configured to transmit the normal image to the display;
the display is also used for simultaneously displaying the infrared image and the normal image.
4. The aircraft engine air leakage monitoring system according to claim 3, wherein the display comprises a touch screen, and the touch screen is used for sensing touch operation of a user and displaying a track corresponding to the touch operation.
5. The aircraft engine air leakage monitoring system of claim 2, wherein said processing unit is connected to said infrared camera via a first data link; the processing unit is connected with the visible light camera through a second data connecting line.
6. The aircraft engine air leakage monitoring system according to claim 1, wherein said aircraft engine air leakage monitoring system further comprises an alarm device;
the processing unit is also used for generating an alarm instruction to control the alarm device to alarm.
7. An aircraft engine air leakage monitoring system according to claim 6, wherein said alarm means comprises a buzzer.
8. The aircraft engine air leakage monitoring system of claim 2, wherein said processing unit is in wireless communication with said infrared camera; the processing unit is in wireless communication connection with the visible light camera.
9. The aircraft engine air leak monitoring system of claim 8, wherein said wireless communication connection comprises at least one of a bluetooth communication connection, a Wi-Fi communication connection, a ZigBee communication connection.
10. The aircraft engine air leakage monitoring system of claim 1, wherein the number of said infrared cameras is several.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121003961.XU CN215865683U (en) | 2021-05-10 | 2021-05-10 | Aeroengine gas leakage monitoring system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121003961.XU CN215865683U (en) | 2021-05-10 | 2021-05-10 | Aeroengine gas leakage monitoring system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215865683U true CN215865683U (en) | 2022-02-18 |
Family
ID=80316113
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121003961.XU Active CN215865683U (en) | 2021-05-10 | 2021-05-10 | Aeroengine gas leakage monitoring system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215865683U (en) |
-
2021
- 2021-05-10 CN CN202121003961.XU patent/CN215865683U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US12084946B2 (en) | Monitoring system and method for wellsite equipment | |
| CN108038917B (en) | Target observation method and inspection system based on MR or AR technology | |
| WO2018036554A1 (en) | Apparatus fault detection system, and fault detection device | |
| CN109961157A (en) | Inspection method and system for solar photovoltaic power generation system | |
| CN102938540B (en) | A kind of substation equipment detection system | |
| CN111198040B (en) | Electrical equipment state monitoring and fault early warning system | |
| KR102516839B1 (en) | System and method for detecting leakage | |
| CN106003040A (en) | Transformer substation inspection robot system with obstacle avoidance function | |
| US11861820B1 (en) | Repetitive video monitoring of industrial equipment by mobile data acquisition units | |
| CN108986385A (en) | Electrical intelligent fire disaster early warning system in a kind of passenger train | |
| KR20150101861A (en) | Apparatus for Monitoring the Blade of Wind Power Generator using Quadcopter | |
| CN111899211A (en) | Transformer oil leakage fault detection system and method based on images and smell | |
| KR20230077368A (en) | Apparatus and system for detecting partial discharge of gas insulated switchgear | |
| CN215865683U (en) | Aeroengine gas leakage monitoring system | |
| CN107358675A (en) | A kind of method for inspecting, system and the crusing robot in piping lane synthesis cabin | |
| KR20150042425A (en) | On-line partial discharge detector | |
| CN117853295B (en) | A safety and environmental protection emergency system based on industrial interconnection and digital panorama | |
| CN108020872B (en) | Gate passing sensor detection device and method | |
| CN117274697A (en) | Method and system for automatically identifying pipeline thermal leakage based on image | |
| CN106226625B (en) | Automatic diagnosis device for electric system of tower crane and use method thereof | |
| CN209055603U (en) | Crusing robot | |
| CN206610161U (en) | A kind of drainage system under coal mine fault diagnosis and debugging apparatus | |
| JP2011007294A (en) | Valve monitoring method and system | |
| CN113625676B (en) | Engineering machinery fault diagnosis method and system, field diagnosis device and storage medium | |
| CN119805501A (en) | A vehicle-mounted satellite positioning system testing method suitable for vehicle off-line testing |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |