CN113504051A - Gas-water composite cooling visual probe structure - Google Patents
Gas-water composite cooling visual probe structure Download PDFInfo
- Publication number
- CN113504051A CN113504051A CN202110697329.8A CN202110697329A CN113504051A CN 113504051 A CN113504051 A CN 113504051A CN 202110697329 A CN202110697329 A CN 202110697329A CN 113504051 A CN113504051 A CN 113504051A
- Authority
- CN
- China
- Prior art keywords
- water
- cooling
- protective sleeve
- cavity
- gas
- 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.)
- Pending
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
- G01M15/10—Testing internal-combustion engines by monitoring exhaust gases or combustion flame
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Instruments For Viewing The Inside Of Hollow Bodies (AREA)
Abstract
The invention discloses a gas-water composite cooling visual probe structure which comprises an inner protective sleeve and an outer protective sleeve, wherein the inner protective sleeve is used for providing gas cooling and water cooling media, the outer protective sleeve is arranged at the rear end of the outer part of the inner protective sleeve, a first optical observation hole is formed in the top end of the inner protective sleeve, a gas cooling circulation cavity is formed in the inner protective sleeve, a second optical observation hole is formed in the top end of the gas cooling circulation cavity, a gas cooling valve is connected to one side of the tail part of the gas cooling circulation cavity, a water cooling water inlet cavity is formed in the outer side of the gas cooling circulation cavity and is simultaneously positioned in the inner protective sleeve, and a water cooling water return cavity is formed in the outer side of the water cooling water inlet cavity and is simultaneously positioned in the inner protective sleeve. The probe is internally provided with a hollow structure, two cooling media of gas and water are adopted, the water is a closed loop, a heat exchange enhancing micro-turbulent flow structure is arranged in the water loop, a gas channel is arranged in the central area of the probe, and the gas slowly flows, so that the temperature of the central area of the probe is suitable for placing an optical camera or an optical fiber.
Description
Technical Field
The invention relates to the field of visual probes, in particular to a gas-water composite cooling visual probe structure.
Background
In combustion parts of power devices such as aeroengines, gas turbines and the like, due to the complex structural characteristics and the limitation of high-temperature (above 1600K), high-pressure and high-speed combustion environments, it is extremely difficult to measure cold and hot flow fields, temperature fields and combustion characteristics of a combustion chamber. The contact type measuring methods such as a conventional probe and a hot wire anemometer are adopted, certain interference is often generated on the measured cold-state and hot-state flow fields, and only the parameters of local points can be obtained. Meanwhile, the arrangement of the probe and the heat wire is difficult due to the high temperature and the large air flow velocity in the combustion chamber. In recent years, the visualization probe technology has received great attention from researchers. The basic principle is that based on optical imaging equipment and image processing technology, a CCD camera (or laser and infrared optical fiber probe) captures a flame signal, and then real-time image data is transmitted to a computer for analysis and imaging through an image acquisition card. The visual probe technology can observe the combustion condition, and can also realize imaging and digital monitoring of flame visually and in real time, so as to monitor the propagation process and combustion performance of the combustion flame.
Disclosure of Invention
The invention aims to solve the problems and provide a gas-water composite cooling visualization probe structure.
The invention realizes the purpose through the following technical scheme:
a gas-water composite cooling visual probe structure comprises an inner protective sleeve and an outer protective sleeve, wherein the inner protective sleeve is used for providing gas cooling and water cooling media, the outer protective sleeve is arranged at the rear end of the outer portion of the inner protective sleeve, a first optical observation hole is formed in the top end of the inner protective sleeve, a gas cooling circulation cavity is formed in the inner protective sleeve and a probe center area, a second optical observation hole is formed in the top end of the gas cooling circulation cavity, a gas cooling valve is connected to one side of the tail portion of the gas cooling circulation cavity, a water cooling water inlet cavity is formed in the outer side of the gas cooling circulation cavity and is located in the inner protective sleeve, a water cooling water return cavity is formed in the outer side of the water cooling water inlet cavity and is located in the inner protective sleeve, a micro turbulence structure is arranged in the water cooling water return cavity to improve heat exchange, a water cooling water outlet cavity is formed in the outer side of the water cooling water return cavity and is located in the outer protective sleeve, the water-cooling water inlet cavity with be provided with first backward flow hole between the water-cooling return water chamber, the water-cooling return water chamber with be provided with the second backward flow hole between the water-cooling play water cavity.
Preferably: the inner protective sleeve, the outer protective sleeve and the first optical observation hole are integrally formed.
So set up, integrated into one piece has guaranteed the stability of device, sets up first optics inspection hole is used for improving the detection effect.
Preferably: the water outlet valve, the water inlet valve and the air cooling valve are connected with the inner protective sleeve through threads.
By the arrangement, the water outlet valve, the water inlet valve and the air cooling valve play a role in controlling on-off, and the tightness is ensured through threaded connection.
Preferably: the refrigerant passing through the air-cooled circulation cavity is low-temperature cooling air.
By the arrangement, the air-cooling circulation cavity plays a role in installing the camera or the optical fiber and transmitting gas media, and the cooling air is transmitted, so that the camera or the optical fiber can be cooled rapidly.
Preferably: the air cooling circulation cavity, the water cooling water inlet cavity, the water cooling water return cavity, the first return hole and the second return hole are integrally formed in the inner protective sleeve.
So set up, water-cooling return water intracavity portion is provided with the vortex structure, thereby it is right the probe reinforces the heat transfer, improves the cooling effect.
Compared with the prior art, the invention has the following beneficial effects:
1. the probe is internally of a hollow structure and adopts two cooling media of gas and water;
2. the water is a closed loop, a heat exchange enhancing micro turbulent flow structure is arranged in the water loop, the gas channel is arranged in the central area of the probe, and the gas slowly flows;
3. the temperature of the central area of the probe is suitable for placing an optical camera or an optical fiber.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic diagram of the external structure of a gas-water composite cooling visualization probe structure according to the present invention;
FIG. 2 is a schematic diagram of the internal structure of a gas-water composite cooling visualization probe structure according to the present invention;
FIG. 3 is a cross-sectional view of a gas-water composite cooling visualization probe structure according to the present invention.
The reference numerals are explained below:
1. an inner protective sheath; 2. an outer protective sheath; 3. a first optical viewport; 4. a water outlet valve; 5. a water inlet valve; 6. an air-cooled valve; 7. a second optical observation; 8. an air-cooled circulation cavity; 9. water cooling the water inlet cavity; 10. a water-cooling water return cavity; 11. a water-cooling water outlet cavity; 12. a first return orifice; 13. a second return orifice.
Detailed Description
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The invention will be further described with reference to the accompanying drawings in which:
example 1
As shown in fig. 1-3, a gas-water composite cooling visual probe structure comprises an inner protective sleeve 1 for providing gas-cooling and water-cooling media and an outer protective sleeve 2 for replacing water return, the outer rear end of the outer protective sleeve 1 is provided with the outer protective sleeve 2, the top end of the inner protective sleeve 1 is provided with a first optical observation hole 3, the inner protective sleeve 1 and the probe center region are provided with a gas-cooling circulation cavity 8, the top end of the gas-cooling circulation cavity 8 is provided with a second optical observation 7, one side of the tail part of the gas-cooling circulation cavity 8 is connected with a gas-cooling valve 6, the outer side of the gas-cooling circulation cavity 8 and the inner protective sleeve 1 are provided with a water-cooling inlet cavity 9, the outer side of the water-cooling inlet cavity 9 and the inner protective sleeve 1 are provided with a water-cooling return cavity 10, the inner side of the water-cooling return cavity 10 and the outer protective sleeve 2 are provided with a water-cooling outlet cavity 11, a first return hole 12 is arranged between the water-cooling water inlet cavity 9 and the water-cooling water return cavity 10, and a second return hole 13 is arranged between the water-cooling water return cavity 10 and the water-cooling water outlet cavity 11.
Preferably: the inner protective sleeve 1, the outer protective sleeve 2 and the first optical observation hole 3 are integrally formed, the stability of the device is guaranteed through the integral forming, and the first optical observation hole 3 is arranged for improving the detection effect; the water outlet valve 4, the water inlet valve 5 and the air-cooled valve 6 are connected with the inner protective sleeve 1 through threads, the water outlet valve 4, the water inlet valve 5 and the air-cooled valve 6 play a role in controlling on-off, and the tightness is ensured through threaded connection; the coolant in the air-cooled circulation cavity 8 is low-temperature cooling air, the air-cooled circulation cavity 8 plays a role in installing a camera or an optical fiber and transmitting a gas medium, and the camera or the optical fiber is quickly cooled by transmitting the cooling air; air-cooled circulation chamber 8, water-cooling intake chamber 9, water-cooling return water chamber 10, first backward flow hole 12, second backward flow hole 13 integrated into one piece are provided with the vortex structure in interior protective sheath 1, water-cooling return water chamber 10 is inside to strengthen the heat transfer to the probe, improve the cooling effect.
The working principle is as follows: after the device is installed in a proper area, the device is detected by using an internal camera or an optical fiber, when the device needs to be cooled, cooling air is blown into the air-cooled circulation cavity 8 through the air-cooled valve 6, meanwhile, air flow is carried out by using the air-cooled valve 6, so that gas cooling is achieved, cooling water is injected into the water-cooled water inlet cavity 9 through the water inlet valve 5, the heat at the top end of the inner protective sleeve 1 is replaced through a turbulent flow mechanism in the water-cooled water return cavity 10, the replaced water flows into the water-cooled water return cavity 10 through the first backflow hole 12, flows into the water-cooled water outlet cavity 11 through the second backflow hole 13, is discharged from the water outlet valve 4, and cold water is continuously supplied to the water inlet valve 5, so that the probe is cooled by water.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed.
Claims (5)
1. The utility model provides a visual probe structure of gas, water complex cooling which characterized in that: the probe comprises an inner protective sleeve (1) used for providing air cooling and water cooling media and an outer protective sleeve (2) used for replacing backwater, wherein the outer protective sleeve (2) is arranged at the rear end of the outer portion of the inner protective sleeve (1), a first optical observation hole (3) is formed in the top end of the inner protective sleeve (1), an air cooling circulation cavity (8) is formed in the inner portion of the inner protective sleeve (1) and in the probe center area, a second optical observation hole (7) is formed in the top end of the air cooling circulation cavity (8), an air cooling valve (6) is connected to one side of the tail portion of the air cooling circulation cavity (8), a water cooling inlet cavity (9) is formed in the outer side of the air cooling circulation cavity (8) and is located in the inner protective sleeve (1), a water cooling backwater cavity (10) is formed in the outer side of the water cooling inlet cavity (9) and is located in the inner protective sleeve (1) at the same time, and a micro turbulence structure is arranged in the water cooling backwater cavity (10), the water-cooling return water cavity (10) outside just is located simultaneously outer protective sheath (2) inside is provided with water-cooling play water cavity (11), water-cooling intake antrum (9) with be provided with first backward flow hole (12) between water-cooling return water cavity (10), water-cooling return water cavity (10) with be provided with second backward flow hole (13) between water-cooling play water cavity (11).
2. A gas and water composite cooling visualization probe structure according to claim 1, characterized in that: the inner protective sleeve (1), the outer protective sleeve (2) and the first optical observation hole (3) are integrally formed.
3. A gas and water composite cooling visualization probe structure according to claim 1, characterized in that: the water outlet valve (4), the water inlet valve (5) and the air cooling valve (6) are connected with the inner protective sleeve (1) through threads.
4. A gas and water composite cooling visualization probe structure according to claim 1, characterized in that: the refrigerant passing through the air-cooled circulation cavity (8) is low-temperature cooling air.
5. A gas and water composite cooling visualization probe structure according to claim 1, characterized in that: the air cooling circulation cavity (8), the water cooling water inlet cavity (9), the water cooling water return cavity (10), the first return hole (12) and the second return hole (13) are integrally formed in the inner protective sleeve (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110697329.8A CN113504051A (en) | 2021-06-23 | 2021-06-23 | Gas-water composite cooling visual probe structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110697329.8A CN113504051A (en) | 2021-06-23 | 2021-06-23 | Gas-water composite cooling visual probe structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113504051A true CN113504051A (en) | 2021-10-15 |
Family
ID=78010714
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110697329.8A Pending CN113504051A (en) | 2021-06-23 | 2021-06-23 | Gas-water composite cooling visual probe structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113504051A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114136647A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Supersonic speed high-temperature three-dimensional flow field measuring device |
| CN115371999A (en) * | 2022-10-24 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Inlet flow field parameter measuring device in high-temperature and high-pressure test |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201170830Y (en) * | 2008-03-10 | 2008-12-24 | 高波 | Equipment for protecting monitoring probe of high temperature furnace |
| CN203163928U (en) * | 2013-04-18 | 2013-08-28 | 北京航空航天大学 | Liquid-cooled high-temperature pressure probe |
| CN203613207U (en) * | 2013-12-18 | 2014-05-28 | 天津市一诺天地科技有限公司 | Blast furnace infrared imaging system |
| CN205281011U (en) * | 2015-12-16 | 2016-06-01 | 鞍钢股份有限公司 | Peep camera device in high temperature resistant preventing dust |
| CN208399148U (en) * | 2018-07-19 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of air cooling total pressure probe and combustor exit high-temperature fuel gas stagnation pressure test macro |
| CN111879848A (en) * | 2020-07-16 | 2020-11-03 | 南昌航空大学 | High-temperature eddy current detection probe |
| CN111947830A (en) * | 2020-07-31 | 2020-11-17 | 中国航发贵阳发动机设计研究所 | High-temperature dynamic pressure probe structure of main combustion chamber of aircraft engine |
| CN213515127U (en) * | 2020-10-21 | 2021-06-22 | 常州市东升检测仪器有限公司 | Cooling protection device for furnace high-temperature industrial television |
-
2021
- 2021-06-23 CN CN202110697329.8A patent/CN113504051A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201170830Y (en) * | 2008-03-10 | 2008-12-24 | 高波 | Equipment for protecting monitoring probe of high temperature furnace |
| CN203163928U (en) * | 2013-04-18 | 2013-08-28 | 北京航空航天大学 | Liquid-cooled high-temperature pressure probe |
| CN203613207U (en) * | 2013-12-18 | 2014-05-28 | 天津市一诺天地科技有限公司 | Blast furnace infrared imaging system |
| CN205281011U (en) * | 2015-12-16 | 2016-06-01 | 鞍钢股份有限公司 | Peep camera device in high temperature resistant preventing dust |
| CN208399148U (en) * | 2018-07-19 | 2019-01-18 | 中国航发沈阳发动机研究所 | A kind of air cooling total pressure probe and combustor exit high-temperature fuel gas stagnation pressure test macro |
| CN111879848A (en) * | 2020-07-16 | 2020-11-03 | 南昌航空大学 | High-temperature eddy current detection probe |
| CN111947830A (en) * | 2020-07-31 | 2020-11-17 | 中国航发贵阳发动机设计研究所 | High-temperature dynamic pressure probe structure of main combustion chamber of aircraft engine |
| CN213515127U (en) * | 2020-10-21 | 2021-06-22 | 常州市东升检测仪器有限公司 | Cooling protection device for furnace high-temperature industrial television |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114136647A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Supersonic speed high-temperature three-dimensional flow field measuring device |
| CN114136647B (en) * | 2021-10-20 | 2023-10-03 | 中国航发四川燃气涡轮研究院 | Supersonic high-temperature three-dimensional flow field measuring device |
| CN115371999A (en) * | 2022-10-24 | 2022-11-22 | 中国航发四川燃气涡轮研究院 | Inlet flow field parameter measuring device in high-temperature and high-pressure test |
| CN115371999B (en) * | 2022-10-24 | 2023-03-24 | 中国航发四川燃气涡轮研究院 | Inlet flow field parameter measuring device in high-temperature and high-pressure test |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113504051A (en) | Gas-water composite cooling visual probe structure | |
| CN208399148U (en) | A kind of air cooling total pressure probe and combustor exit high-temperature fuel gas stagnation pressure test macro | |
| CN109827794B (en) | A kind of high enthalpy dissociating gas cooler thermodynamic property test platform, system and method | |
| CN206601351U (en) | A kind of finned tube heat exchange performance testing system | |
| CN109613053A (en) | Integral sintered Narrow Rectangular Channel critical heat flux density visualization measurement experimental provision | |
| CN103983458B (en) | A kind of engines tail class session field method of testing | |
| CN107036758A (en) | A kind of air cooling high temperature dynamic pressure probe | |
| CN104697352B (en) | A kind of temperature field real-time monitoring device of air cooling tubes condenser | |
| Lange et al. | Time-resolved PIV measurements of the effect of freestream turbulence on horseshoe vortex dynamics | |
| CN110361087A (en) | A kind of high temperature optical fiber Tip timing sensor of reaction type active cooling | |
| CN108645523A (en) | A kind of Direct Air-Cooled temperature field on-Line Monitor Device and method | |
| WO2021223387A1 (en) | Automatic control method and system for air cooling condenser fan | |
| CN208476415U (en) | A kind of indirect air cooling system temperature field on-Line Monitor Device | |
| CN218503288U (en) | Continuous temperature measuring device for tundish | |
| CN108007667B (en) | High-temperature gas wind tunnel Mach number measuring device and method | |
| CN208046061U (en) | Heat sink and low-tension switch cabinet for low-tension switch cabinet | |
| CN211700911U (en) | Working gas cooling device for rapid axial flow carbon dioxide laser | |
| CN112345529B (en) | Image processing-based experimental test system and method for rectangular thermal state temperature difference mixing layer | |
| CN2729668Y (en) | Apparatus for measuring temp. of high-temp. liquid | |
| CN104931146A (en) | Device for measuring furnace flue gas temperature | |
| CN208085475U (en) | A kind of novel new-energy automobile air duct cooling device | |
| CN218629731U (en) | High-temperature-resistant plug-in type gas sensor probe assembly | |
| CN218442264U (en) | Slag falling pipe convenient for sampling | |
| CN221280291U (en) | Industrial detection probe adopting semiconductor refrigeration technology | |
| CN206059900U (en) | A kind of circulating water cooling device for semiconductor laser |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20211015 |