CN103487255B - A kind of experimental cabin with temperature and pressure separating mechanism - Google Patents
A kind of experimental cabin with temperature and pressure separating mechanism Download PDFInfo
- Publication number
- CN103487255B CN103487255B CN201310321719.0A CN201310321719A CN103487255B CN 103487255 B CN103487255 B CN 103487255B CN 201310321719 A CN201310321719 A CN 201310321719A CN 103487255 B CN103487255 B CN 103487255B
- Authority
- CN
- China
- Prior art keywords
- temperature
- cabin
- separating mechanism
- hatchcover
- pressure
- 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
Landscapes
- Testing Of Engines (AREA)
Abstract
The invention discloses a kind of experimental cabin with temperature and pressure separating mechanism, comprise hatchcover, cabin and lower hatchcover; Upper hatchcover center arranges through hole and temperature and pressure separating mechanism, and cabin arranges high-temperature gas valve and venting valve.Temperature and pressure separating mechanism comprises and is arranged at the bottomless box body of via top, is set in the electromagnet outside box body and is positioned at the protective cover in cabin; Three can form seal cavity; Described box body arranged outside gas at normal temperature valve, box body inside top arranges drop suspender.After adopting said structure, cabin can be divided into two spaces by temperature and pressure separating mechanism: normal temperature high voltage space and High Temperature High Pressure space; Ingeniously utilize the electromagnet power-off not magnetic characteristic of tool; after electromagnet power-off; protective cover comes off under deadweight; fuel droplet moment is leaked in predetermined high temperature and high pressure environment cruelly; substantially reduce the time of drop atomization, burning test set-up procedure; solve a volatilization difficult problem for fuel droplet, easy to operate, test accuracy is high.
Description
Technical field
The present invention relates to a kind of test unit, can be applicable to the research fields such as internal combustion engine, rocket engine, gas turbine, boiler and gas jet technique; Particularly a kind of experimental cabin with temperature and pressure separating mechanism.
Background technology
Engine is the fuel chemical energy that the mankind can not directly be utilized is the instrument that can utilize mechanical energy, and it has irreplaceable effect in modern society.A lot of problem is faced in reseach of engine process, particularly unstable combustion is the global problem of puzzlement engine technology developments always, spray atomization, the combustion by evaporation characteristic of engine chamber fuel determine engine performance, are the key factors causing unstable combustion.
Drop evaporation is very complicated physical and chemical process with burning, is extensively present in various engine working process.Propellant spray atomization, combustion by evaporation experimental study are very important links in reseach of engine process.In order to simplify and understand the most basic physical chemical phenomenon, usually start with from the simplest single drop research, wherein wherein the key link to the evaporation of single drop, atomization and combustion process research experiment, by to being in drop evaporation, spray burning characteristic research experiment under high-temperature and high-pressure conditions, the evaporation of accurate assurance drop, combustion process and rule thereof, and then the main excitation mechanism of the generation of announcement engine unstable combustion, for suppression combustion instability, improve engine performance significant.
Because liquid fuel all has stronger volatility at relatively high temperatures, so require during test that setup time must be short as much as possible, but under existence conditions, make experimental cabin meet the requirements of high-temperature and high-pressure conditions still need a period of time, if traditionally directly hang drop under high temperature, the volatility of drop certainly will affect test effect and even can not get significant test figure, so the drop under solution high-temperature and high-pressure conditions hangs problem, avoiding drop to volatilize is an important topic.Domestic and international fewer to the drop combustion by evaporation experimental study under high-temperature and high-pressure conditions at present, existing similar test is generally carry out under simplified condition, although also drawn some results, to compare or there is a big difference with actual engine combustion conditions.
Summary of the invention
The technical problem to be solved in the present invention is for above-mentioned the deficiencies in the prior art, and provide a kind of structure simple, compact in design, easy to operate, test accuracy is high, temperature can be made to be separated with pressure, the experimental cabin with temperature and pressure separating mechanism of the drop volatilization difficult problem under solution high-temperature and high-pressure conditions in drop atomization, burning test set-up procedure.
For solving the problems of the technologies described above, the technical solution used in the present invention is:
There is an experimental cabin for temperature and pressure separating mechanism, comprise hatchcover, cabin and lower hatchcover; Described upper hatchcover center is provided with through hole and temperature and pressure separating mechanism, and this temperature and pressure separating mechanism comprises being arranged at the bottomless box body of via top, being set in outside box body and being embedded in upper-deck cabin and covers the electromagnet on surface and be arranged at via bottoms and be positioned at the protective cover in cabin; This protective cover, upper hatchcover and box body form seal cavity; Described box body arranged outside gas at normal temperature valve, box body inside top arranges drop suspender; Described cabin side plate arranges high-temperature gas valve and venting valve.
Filling with insulation material between described electromagnet and upper hatchcover; Partiting thermal insulation protective layer is set outside described protective cover.
High temperature resistant auxiliary packing material is coated with between described protective cover and upper hatchcover.
Described drop suspender is quartz fibre or thermopair.
Described cabin is also provided with the first pressure transducer can monitoring pressure in cabin.
Described box body and upper hatchcover are structure as a whole, and this box body is also provided with the second pressure transducer can monitoring pressure in temperature and pressure separating mechanism.
Described lower hatchcover arranges base, and this base is provided with pulley.
The side in described protective cover and cabin is respectively arranged with the transparent window of several deads in line.
Described transparent window is outside equipped with optical image capturing device and light source.
After the present invention adopts said structure, structure is simple, compact in design, and cabin can be divided into two spaces by above-mentioned temperature and pressure separating mechanism, and one is normal temperature high voltage space, and one is High Temperature High Pressure space; Ingeniously utilize the electromagnet power-off not magnetic characteristic of tool; after electromagnet power-off; protective cover comes off under deadweight; fuel droplet moment is leaked in predetermined high temperature and high pressure gas environment cruelly; substantially reduce the time of drop atomization, burning test set-up procedure; solve a volatilization difficult problem for fuel droplet, easy to operate, test accuracy is high.
Accompanying drawing explanation
Fig. 1 is the structural representation that the present invention has the experimental cabin of temperature and pressure separating mechanism;
Fig. 2 is drop hanging integral structural representation of the present invention;
Fig. 3 is Test Data Collecting schematic diagram of the present invention;
Fig. 4 is protective cover schematic diagram of the present invention;
Fig. 5 is hatchcover and box body schematic diagram in the present invention;
Fig. 6 is hatchcover and protective cover scheme of installation in the present invention;
Fig. 7 is that drop of the present invention hangs schematic diagram in cabin;
Fig. 8 is that protective cover of the present invention falls schematic diagram in cabin.
Wherein have: 1. bolt; 2. gas at normal temperature valve; 3. cabin; 4. the first pressure transducer; 5. descend hatchcover; 6. base; 7. venting valve; 8. high-temperature gas valve; 9. transparent window; 10. protective cover; Hatchcover on 11.; 12. electromagnet; 13. second pressure transducers; 14. box bodys; 15. drop suspenders; 16. fuel droplet; 17. optical image capturing devices; 18. light sources; 19. through holes.
Embodiment
Below in conjunction with accompanying drawing and concrete preferred implementation, the present invention is further detailed explanation.
As shown in Figure 1, Figure 4 and Figure 5, a kind of experimental cabin with temperature and pressure separating mechanism, comprises hatchcover 11, cabin 3 and lower hatchcover 5; Described upper hatchcover 11 center is provided with through hole 19 and temperature and pressure separating mechanism, this temperature and pressure separating mechanism comprise be arranged at through hole 19 top outwardly convex bottomless box body 14, to be set in outside box body 14 and to be embedded in the electromagnet 12 of hatchcover 11 upper surface and to be arranged at bottom through hole 19 and to be positioned at the protective cover 10 in cabin 3; This protective cover 10, upper hatchcover 11 and box body 14 form seal cavity, and cabin 3 is divided into normal temperature high voltage space and High Temperature High Pressure space by sealing space; Described box body 14 is structure as a whole with upper hatchcover 11, sealing effectiveness is better, this box body 14 arranged outside gas at normal temperature valve 2 and second pressure transducer 13, be convenient to be filled with the pressure in gas at normal temperature and monitoring temperature and pressure separating mechanism, box body 14 inside top arranges drop suspender 15, and this drop suspender 15 is quartz fibre (as shown in Figure 8).
Above-mentioned cabin 3 side plate arranges high-temperature gas valve 8, venting valve 7 and the first pressure transducer 13, and be convenient to the pressure in inflation/deflation and monitoring cabin 3, described lower hatchcover 5 arranges base 6, and this base 6 can install pulley, convenient mobile.
Filling with insulation material between above-mentioned electromagnet 12 and upper hatchcover 11; Outside described protective cover 10, partiting thermal insulation protective layer is set.Protective cover 10 is higher with the sealing surface machining precision of electromagnet 12, is coated with thermostable heat-isolating coating during installation; Ensure that thermal insulation and the sealing of the seal cavity that temperature and pressure separating mechanism is formed, improve test accuracy.
Two opposite faces of cabin 3 and protective cover 10 are respectively arranged with transparent window 9, ensure the dead in line of four transparent windows 9 during installation, light can be passed through, be convenient to observe the Test condition in cabin 3; Meanwhile, optical image capturing device 17 and light source 18(are set outside transparent window 9 as shown in Figure 3) so that acquisition test data and carry out case study.
The test preparatory stage one, fuel droplet 16 hangs:
One end of drop suspender 15 is fixed on box body 14, after hang up fuel droplet 16, fuel droplet 16 hangs rear state as shown in Figure 2 and Figure 7; Install protective cover 10, as shown in Figure 6, protective cover 10 and upper hatchcover 11 are adjacent to by sealing surface sealing, and electromagnet 12 is energized, and protective cover 10 and box body 14 form confined space under magneticaction, then is fixed on cabin 3 by bolt 1 by upper hatchcover 11.
The test preparatory stage two, gas is filled with:
In cabin 3, high-temperature gas is injected by high-temperature gas valve 8; in protective cover 10, slowly inject gas at normal temperature by the gas at normal temperature valve 2 on box body 14 simultaneously; period should keep gas pressure intensity in protective cover 10 to be less than the pressure in cabin 3; protective cover 10 is prevented to be separated with upper hatchcover 11; after gas pressure intensity reaches predetermined value in cabin 3, close high-temperature gas valve 8.Continue slowly to inject gas at normal temperature to protective cover 10,
The test preparatory stage three, predetermined high temperature high pressure gas environment:
When the first pressure transducer 4 and the second pressure transducer 13 monitor that inside and outside protective cover 10, pressure is equal, by signal transmission to controller, can will close gas at normal temperature valve 2, and the power supply of tripping magnet 12; Electromagnet 12 loses magnetism, and electromagnet 12 disappears with the suction of protective cover 10; Protective cover 10, under Gravitative Loads, will fall on lower hatchcover 5, and fuel droplet 16 is exposed in predetermined high temperature high pressure gas environment.
Experimental stage: start to test, is bled off the gas in cabin 3 by venting valve 7 after test.
In the present embodiment, box body 14 and upper hatchcover 11 are structure as a whole, and also can be Split type structure; Drop suspender 15 have employed quartz fibre, also usable thermocouple or other hanging method, all within protection scope of the present invention; In the present embodiment, high temperature resistant auxiliary packing material have employed thermostable heat-isolating coating, also can be thickness colloidal liquid or other material that is high temperature resistant and that can seal that dag and water glass is mixed into.
In addition, in the present embodiment, upper hatchcover 11 is fixed on cabin 3 by bolt 1, also can with clamping or welding, after in the mode of cabin 3 side plate upward-acting door, but to be not limited thereto.
Further, in the present embodiment, transparent window 9 is provided with four altogether, also can arrange two or more.
Claims (9)
1. one kind has the experimental cabin of temperature and pressure separating mechanism, comprise hatchcover (11), cabin (3) and lower hatchcover (5), it is characterized in that: described upper hatchcover (11) center is provided with through hole (19) and temperature and pressure separating mechanism, this temperature and pressure separating mechanism comprises and is arranged at the bottomless box body (14) in through hole (19) top, is set in box body (14) outside and is embedded in the electromagnet (12) of hatchcover (11) upper surface and is arranged at bottom through hole (19) and is positioned at the protective cover (10) of cabin (3); When electromagnet (12) is energized, protective cover (10), upper hatchcover (11) and box body (14) form a seal cavity; When after electromagnet (12) power-off, protective cover (10) will drop on lower hatchcover (5) under deadweight; Described box body (14) arranged outside gas at normal temperature valve (2), box body (14) inside top arranges drop suspender (15); Described cabin (3) side plate arranges high-temperature gas valve (8) and venting valve (7).
2. the experimental cabin with temperature and pressure separating mechanism according to claim 1, is characterized in that: filling with insulation material between described electromagnet (12) and upper hatchcover (11); Described protective cover arranges partiting thermal insulation protective layer outside (10).
3. the experimental cabin with temperature and pressure separating mechanism according to claim 1, is characterized in that: described drop suspender (15) is quartz fibre or thermopair.
4. the experimental cabin with temperature and pressure separating mechanism according to claim 1, is characterized in that: described cabin (3) are also provided with the first pressure transducer (4) can monitoring cabin (3) interior pressure.
5. the experimental cabin with temperature and pressure separating mechanism according to claim 1, it is characterized in that: described box body (14) and upper hatchcover (11) are structure as a whole, and this box body (14) is also provided with the second pressure transducer (13) can monitoring pressure in temperature and pressure separating mechanism.
6. the experimental cabin with temperature and pressure separating mechanism according to claim 1, is characterized in that: described lower hatchcover arranges base (6), and (6) are provided with pulley to this base.
7. the experimental cabin with temperature and pressure separating mechanism according to claim 1 and 2, is characterized in that: be coated with high temperature resistant auxiliary packing material between described protective cover (10) and upper hatchcover (11).
8. the experimental cabin with temperature and pressure separating mechanism according to claim 7, is characterized in that: the side of described protective cover (10) and cabin (3) is respectively arranged with the transparent window (9) of several deads in line.
9. the experimental cabin with temperature and pressure separating mechanism according to claim 8, is characterized in that: described transparent window (9) is outside equipped with optical image capturing device (17) and light source (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310321719.0A CN103487255B (en) | 2013-07-29 | 2013-07-29 | A kind of experimental cabin with temperature and pressure separating mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310321719.0A CN103487255B (en) | 2013-07-29 | 2013-07-29 | A kind of experimental cabin with temperature and pressure separating mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103487255A CN103487255A (en) | 2014-01-01 |
| CN103487255B true CN103487255B (en) | 2015-09-30 |
Family
ID=49827651
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310321719.0A Active CN103487255B (en) | 2013-07-29 | 2013-07-29 | A kind of experimental cabin with temperature and pressure separating mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103487255B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108169406A (en) * | 2017-12-15 | 2018-06-15 | 大连理工大学 | A kind of high temperature and pressure lubricating oil list drop evaporation and catch fire device and its application method |
| CN108458877B (en) * | 2018-03-14 | 2019-10-29 | 江苏科技大学 | A kind of suspension drop protective cover automatic separating apparatus and method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4351789A (en) * | 1981-07-27 | 1982-09-28 | The B. F. Goodrich Company | Mold and process for molding |
| CN101283214A (en) * | 2005-10-06 | 2008-10-08 | 卡-博投资有限公司 | Pipe testing tool with magnetic clamps |
| CN201969373U (en) * | 2011-01-05 | 2011-09-14 | 上海海事大学 | Novel experimental apparatus for liquid flash vaporization |
-
2013
- 2013-07-29 CN CN201310321719.0A patent/CN103487255B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4351789A (en) * | 1981-07-27 | 1982-09-28 | The B. F. Goodrich Company | Mold and process for molding |
| CN101283214A (en) * | 2005-10-06 | 2008-10-08 | 卡-博投资有限公司 | Pipe testing tool with magnetic clamps |
| CN201969373U (en) * | 2011-01-05 | 2011-09-14 | 上海海事大学 | Novel experimental apparatus for liquid flash vaporization |
Non-Patent Citations (3)
| Title |
|---|
| "凝胶燃料单滴燃烧的建模、实验及应用";张蒙正;《火箭推进》;20100630;第36卷(第3期);第1-9页 * |
| "环境模拟设备在人-机-环境系统工程研究中的作用";刘慧敏;《第五届全国人-机-环境系统工程学术会议》;20040326;第142页 * |
| 苏凌宇."负压环境下燃料液滴蒸发过程的试验和理论研究".《中国优秀博硕士学位论文全文数据库(硕士) 工程科技Ⅱ辑》.2006,(第03期), * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103487255A (en) | 2014-01-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103529078B (en) | Drop evaporation ignition experiment device and using method thereof under a kind of high temperature and high pressure environment | |
| CN106525687B (en) | Supercritical carbon dioxide soaks shale experimental apparatus | |
| CN103487255B (en) | A kind of experimental cabin with temperature and pressure separating mechanism | |
| CN102062020B (en) | Transparent combustion chamber with square interior passage | |
| CN202256064U (en) | Pressure tester for air pressure explosion proof of capacitor shell | |
| CN104330519B (en) | A kind of particle pneumatic floating laser ignition experimental provision | |
| CN102175404B (en) | Waterproofness tester | |
| CN103759926B (en) | Cylinder sleeve fatigue test device | |
| CN102269674A (en) | Temperature control and explosion-proof integrated device for high-pressure hydrogen storage cylinder test | |
| RU2014150873A (en) | VALVE OF THE FUEL SUPPLY SYSTEM FOR THE INTERNAL COMBUSTION ENGINE AND METHOD FOR CONTROL OF THE FUEL SUPPLY SYSTEM FOR THE INTERNAL COMBUSTION ENGINE | |
| CN205449393U (en) | LED lamps and lanterns gas tightness detection device | |
| CN104912678B (en) | Gas or dual fuel engine | |
| BRPI0800386A (en) | method of starting a gas turbine helicopter engine powered by a fuel circuit, fuel supply circuit to a combustion chamber of a gas turbine helicopter engine, and, gas turbine helicopter engine | |
| GB2519018A (en) | Temperature-controlled combustion system and method | |
| CN112504567A (en) | Method for detecting leakage of lithium battery | |
| CN102788692A (en) | Thermal state seal test device of superhigh temperature hot valve | |
| JP2009180582A (en) | Device for detecting high-temperature leakage in sofc battery pack | |
| CN101968430B (en) | Device and method for measuring maximum aperture of filter element by dry method | |
| CN214500052U (en) | Straight-through type adjustable one-way valve | |
| CN109916568A (en) | Electric machine controller sealing propertytest system, device and method | |
| CN202221373U (en) | Test tool used for safety valve of battery case | |
| CN109488488B (en) | Test section suitable for longitudinal combustion unstable optical measurement under high-temperature and high-pressure environment | |
| CN110660496B (en) | Real-time monitoring system for rupture and failure of cladding for high-temperature mandrel test | |
| CN103107299A (en) | Protection structure of lithium battery | |
| CN102230907B (en) | Calorimeter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |