CN214029199U - Aircraft fuel system filter blocks up simulation experiment device that freezes - Google Patents
Aircraft fuel system filter blocks up simulation experiment device that freezes Download PDFInfo
- Publication number
- CN214029199U CN214029199U CN202022451729.4U CN202022451729U CN214029199U CN 214029199 U CN214029199 U CN 214029199U CN 202022451729 U CN202022451729 U CN 202022451729U CN 214029199 U CN214029199 U CN 214029199U
- Authority
- CN
- China
- Prior art keywords
- oil
- filter
- box
- experimental box
- simulation experiment
- 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
Images
Landscapes
- Filtering Materials (AREA)
Abstract
The utility model discloses an aircraft fuel system filter blocks up simulation experiment device that freezes, including experimental box, oil tank, measuring box and tight structure of clamp, experimental box top department installs and presss from both sides tight structure, press from both sides tight structural joint and install aviation filter the inside oil storage chamber that is provided with of oil tank, oil storage chamber bottom department installs the oil pump, oil pipe is installed to the end that produces oil of oil pump, oil pipe stretches into in the experimental box, two sets of velocity of flow sensors are installed to the symmetry on the oil pipe at the both ends of pressing from both sides tight structure, install fluid moisture sensor and temperature sensor on the oil pipe of measuring box respectively. This aircraft fuel oil system filter blocks up simulation experiment device that freezes, reasonable in design can carry out fine understanding to the filter under the condition of blocking up that freezes under the states such as different temperatures, can carry out quick effectual change to the filter of the same race and different kind, conveniently carries out the effect contrast test of different kind filters, is fit for using widely.
Description
Technical Field
The utility model belongs to the technical field of fuel oil system filter simulation, concretely relates to aircraft fuel oil system filter blocks up simulation experiment device that freezes.
Background
Aviation fuel refers to a fuel variety specifically designed for aircraft, and has a higher quality than fuel used in heating systems and automobiles, and generally contains different additives to reduce the risk of icing and explosion due to high temperature. When the airplane flies at high altitude, water in fuel oil is analyzed and frozen due to the low-temperature environment, so that a fuel oil pipeline is easily blocked, and the normal work of an engine is further influenced.
In order to simulate the process of icing of water in fuel oil when an airplane flies high above the ground and measure the icing and blocking effects of different filters and the same filter in a low-temperature environment, an icing and blocking simulation experiment device for the filters is needed to solve the problems.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft fuel system filter blocks up simulation experiment device that freezes to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme: an icing and blocking simulation experiment device for an aircraft fuel system filter comprises an experiment box, an oil tank, a measuring box and a clamping structure, the experimental box is of a box-shaped structure, the top of the experimental box is provided with a clamping structure, the clamping structure is clamped with an aviation filter, a refrigeration cavity is arranged in the experiment box, a refrigeration system is arranged in the refrigeration cavity, a measuring box is fixed at the top of one side edge of the experiment box, an oil tank is arranged at the bottom of the other side edge of the experimental box, an oil storage cavity is arranged in the oil tank, an oil pump is arranged at the bottom of the oil storage cavity, an oil pipe is arranged at the oil outlet end of the oil pump, the oil pipe extends into the experimental box, and the oil pipe of the measuring box is respectively provided with an oil liquid moisture sensor and a temperature sensor.
Preferably, press from both sides tight structure and include base, curb plate, accommodate motor and locating plate, the base is fixed in experimental box top department, base top symmetry is fixed with two sets of curb plates, and is two sets of base top department between the curb plate has seted up a set of regulation chamber, and it is provided with the regulation pole to adjust the intracavity rotation, the base is stretched out to the one end of adjusting the pole, and stretches out the end and install accommodate motor, and is two sets of be provided with two sets of locating plates between the curb plate, locating plate bottom department is fixed with the slider, the slider cover is established and is installed on adjusting the pole.
Preferably, two sets of threads with opposite spiral directions are symmetrically arranged on the adjusting rod, the adjusting rod is in threaded fit with the sliding block, and positioning columns matched with the aviation filter are arranged at four corners of the positioning plate.
Preferably, the positioning column is horizontally fixed on the positioning plate, an oil inlet and an oil outlet are respectively formed in two sides of the bottom of the aviation filter, positioning holes matched with the positioning column are drilled in the oil inlet and the oil outlet, and sealing gaskets are fixedly bonded on one sides of the oil inlet and the oil outlet and one side of the positioning plate far away from the side plate.
Preferably, the oil pipes are spirally arranged in the refrigerating cavity, and the refrigerating pipe coil on the refrigerating system is arranged at the outer edge of the oil pipe.
The utility model discloses a technological effect and advantage: the icing blockage simulation experiment device for the aircraft fuel system filter can simulate a low-temperature environment at work according to needs through the matching among an experiment box, an oil tank, an oil pump, an oil pipe, an oil liquid moisture sensor, a temperature sensor, a flow velocity sensor, a refrigerating system in a refrigerating cavity and an aviation filter, can well know the icing blockage of the same filter at different temperatures, can measure the influence of additives such as an anti-icing agent on the icing of oil liquid, can conveniently and effectively replace different aviation filters in a comparison experiment through the matching among a base, a side plate, an adjusting motor, an adjusting rod, a positioning plate, a sliding block, a positioning column and a positioning hole on the aviation filter, and avoids the need of disassembling a plurality of groups of bolts when the aviation filter is replaced every time, the working efficiency of the multi-group contrast test can be improved. This aircraft fuel oil system filter blocks up simulation experiment device that freezes, reasonable in design can carry out fine understanding to the filter under the condition of blocking up that freezes under the states such as different temperatures, can carry out quick effectual change to the filter of the same race and different kind, conveniently carries out the effect contrast test of different kind filters, is fit for using widely.
Drawings
Fig. 1 is a schematic structural view of the present invention;
fig. 2 is a cross-sectional view of the present invention;
figure 3 is the utility model discloses press from both sides tight structure and aviation filter's split picture.
In the figure: the device comprises an experiment box 1, an oil tank 2, an oil pump 3, an oil pipe 4, a refrigeration cavity 5, a measurement box 6, an oil water sensor 7, a temperature sensor 8, a flow velocity sensor 9, an aviation filter 10, a clamping structure 11, a base 12, a side plate 13, an adjusting motor 14, an adjusting rod 15, a positioning plate 16, a sliding block 161 and a positioning column 17.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
The utility model provides an aircraft fuel system filter icing blockage simulation experiment device as shown in figures 1-3, which comprises an experiment box 1, an oil tank 2, a measuring box 6 and a clamping structure 11, wherein the experiment box 1 is in a box-shaped structure, the clamping structure 11 is arranged at the top of the experiment box 1, an aviation filter 10 is clamped and arranged on the clamping structure 11, a refrigeration cavity 5 is arranged in the experiment box 1, a refrigeration system is arranged in the refrigeration cavity 5 (the refrigeration system at least comprises a compressor, a condenser, an expansion valve, an evaporator and the like, the specific refrigeration process of the refrigeration system is not specifically explained in the prior art of the refrigeration field), the measuring box 6 is fixed at the top of one side edge of the experiment box 1, the oil tank 2 is arranged at the bottom of the other side edge of the experiment box 1, an oil storage cavity is arranged in the oil tank 2, and an oil pump 3 is arranged at the bottom of the oil storage cavity, oil pipe 4 is installed to the oil outlet end of oil pump 3, oil pipe 4 stretches into experimental box 1 in, and passes refrigeration chamber 5, measuring box 6 in proper order, presss from both sides tight structure 11 and stretches into in the oil tank 2, two sets of velocity of flow sensor 9 are installed to the symmetry on the oil pipe 4 at the both ends of pressing from both sides tight structure 11, and velocity of flow sensor 9's model is GLOBALWATER, can use but not be limited to this model, install fluid moisture sensor 7 and temperature sensor 8 on measuring box 6's oil pipe 4 respectively, fluid moisture sensor 7's model is WIO100, can use but not be limited to this model, temperature sensor 8 can be pt-100, can use but not be limited to this model.
Specifically, the clamping structure 11 comprises a base 12, a side plate 13, an adjusting motor 14 and a positioning plate 16, wherein the clamping structure 11, can conveniently and effectively replace different aviation filters 10 during comparison experiments, avoids the need of disassembling a plurality of groups of bolts when replacing the aviation filters 10 each time, can improve the working efficiency during a plurality of groups of comparison experiments, the base 12 is fixed at the top of the experimental box 1, two groups of side plates 13 are symmetrically fixed at the top of the base 12, a group of adjusting cavities are arranged at the top of the base 12 between the two groups of side plates 13, adjusting rods 15 are rotatably arranged in the adjusting cavities, one ends of the adjusting rods 15 extend out of the base 12, and the extending end is provided with an adjusting motor 14, two groups of positioning plates 16 are arranged between the two groups of side plates 13, the bottom of the positioning plate 16 is fixed with a slide block 161, and the slide block 161 is sleeved on the adjusting rod 15.
Specifically, two sets of threads with opposite spiral directions are symmetrically formed in the adjusting rod 15, the adjusting rod 15 is in threaded fit with the sliding block 161, positioning columns 17 matched with the aviation filter 10 are arranged at four corners of the positioning plate 16, and the positioning columns 17 can play a role in auxiliary positioning.
Specifically, the positioning column 17 is horizontally fixed on the positioning plate 16, an oil inlet and an oil outlet are respectively arranged on two sides of the bottom of the aviation filter 10, positioning holes matched with the positioning column 17 are drilled in the oil inlet and the oil outlet, a sealing gasket is fixedly bonded on one side of the oil inlet and the oil outlet and one side of the positioning plate 16 far away from the side plate 13, and the sealing gasket can play a role in auxiliary sealing during working.
Specifically, the oil pipes 4 are arranged in the refrigeration cavity 5 in a spiral shape, and the refrigeration pipe coil on the refrigeration system is arranged at the outer edge of the oil pipes 4.
Specifically, the aircraft fuel system filter icing and blocking simulation experiment device comprises a base, a sliding block 161, a regulating motor 14, a refrigerating system, an oil pump 3, a temperature sensor 8, a water level sensor 7, a water level sensor 3, a water level sensor 6, a water level sensor 3, a water level sensor 6, a water level sensor 3, a water level sensor and a water level sensor 3, can measure the flow of fluid before through aviation filter 10 and the flow of fluid after aviation filter 10 through two sets of velocity of flow sensor 9 that set up on oil pipe 4, and then freeze the jam situation to the filter and carry out fine understanding, the cooperation between temperature sensor 8 and the velocity of flow sensor 9 can freeze the jam situation and carry out fine understanding under the different temperatures, still can be through adding like anti-icing agent etc. to observing the jam effect that freezes of filter under the same temperature at the during operation. This aircraft fuel oil system filter blocks up simulation experiment device that freezes, reasonable in design can carry out fine understanding to the filter under the condition of blocking up that freezes under the states such as different temperatures, can carry out quick effectual change to the filter of the same race and different kind, conveniently carries out the effect contrast test of different kind filters, is fit for using widely.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications and variations can be made in the embodiments or in part of the technical features of the embodiments without departing from the spirit and the scope of the invention.
Claims (5)
1. The utility model provides an aircraft fuel system filter blocks up simulation experiment device that freezes, includes experimental box (1), oil tank (2), measures case (6) and presss from both sides tight structure (11), its characterized in that: the experimental box (1) is a box-shaped structure, the top of the experimental box (1) is provided with a clamping structure (11), the clamping structure (11) is connected with an aviation filter (10), the experimental box (1) is internally provided with a refrigeration cavity (5), the refrigeration cavity (5) is internally provided with a refrigeration system, the top of one side edge of the experimental box (1) is fixed with a measuring box (6), the bottom of the other side edge of the experimental box (1) is provided with an oil tank (2), the inside of the oil tank (2) is provided with an oil storage cavity, the bottom of the oil storage cavity is provided with an oil pump (3), the oil outlet end of the oil pump (3) is provided with an oil pipe (4), the oil pipe (4) stretches into the experimental box (1) and sequentially passes through the refrigeration cavity (5), the measuring box (6) and the clamping structure (11) to stretch into the oil tank (2), two sets of flow rate sensors (9) are symmetrically installed on the oil pipe (4) at the two ends of the clamping structure (11), an oil liquid moisture sensor (7) and a temperature sensor (8) are respectively arranged on an oil pipe (4) of the measuring box (6).
2. The aircraft fuel system filter icing blockage simulation experiment device as recited in claim 1, wherein: press from both sides tight structure (11) and include base (12), curb plate (13), accommodate motor (14) and locating plate (16), base (12) are fixed in experimental box (1) top department, base (12) top symmetry is fixed with two sets of curb plate (13), and is two sets of base (12) top department between curb plate (13) has seted up a set of regulation chamber, and the regulation intracavity is rotated and is provided with regulation pole (15), the one end of adjusting pole (15) stretches out base (12), and stretches out the end and install accommodate motor (14), and is two sets of be provided with two sets of locating plate (16) between curb plate (13), locating plate (16) bottom department is fixed with slider (161), slider (161) cover is established and is installed on adjusting pole (15).
3. The aircraft fuel system filter icing blockage simulation experiment device as recited in claim 2, wherein: two sets of screw threads with opposite spiral directions are symmetrically arranged on the adjusting rod (15), the adjusting rod (15) is in threaded fit with the sliding block (161), and positioning columns (17) matched with the aviation filter (10) are arranged at four corners of the positioning plate (16).
4. The aircraft fuel system filter icing blockage simulation experiment device as recited in claim 3, wherein: the positioning column (17) is horizontally fixed on the positioning plate (16), an oil inlet and an oil outlet are respectively formed in two sides of the bottom of the aviation filter (10), positioning holes matched with the positioning column (17) are drilled in the outer portions of the oil inlet and the oil outlet, and sealing gaskets are fixedly bonded on one side of the oil inlet and the oil outlet and one side of the positioning plate (16) far away from the side plate (13).
5. The aircraft fuel system filter icing blockage simulation experiment device as recited in claim 1, wherein: the oil pipe (4) is arranged in the refrigeration cavity (5) in a spiral shape, and a refrigeration pipe coil on the refrigeration system is arranged at the outer edge of the oil pipe (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022451729.4U CN214029199U (en) | 2020-10-29 | 2020-10-29 | Aircraft fuel system filter blocks up simulation experiment device that freezes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022451729.4U CN214029199U (en) | 2020-10-29 | 2020-10-29 | Aircraft fuel system filter blocks up simulation experiment device that freezes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214029199U true CN214029199U (en) | 2021-08-24 |
Family
ID=77355127
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022451729.4U Active CN214029199U (en) | 2020-10-29 | 2020-10-29 | Aircraft fuel system filter blocks up simulation experiment device that freezes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214029199U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114354534A (en) * | 2021-12-30 | 2022-04-15 | 中国航空油料有限责任公司 | Method for establishing aviation kerosene property prediction model by utilizing binary linear classifier |
-
2020
- 2020-10-29 CN CN202022451729.4U patent/CN214029199U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114354534A (en) * | 2021-12-30 | 2022-04-15 | 中国航空油料有限责任公司 | Method for establishing aviation kerosene property prediction model by utilizing binary linear classifier |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102359859B (en) | Clean vacuum system used for engine plume test research and vacuumizing and repressing method thereof | |
| CN214029199U (en) | Aircraft fuel system filter blocks up simulation experiment device that freezes | |
| CN208672312U (en) | The low-temp low-pressure experimental cabin of simulated altitude | |
| CN103015997A (en) | Filtration plugging testing apparatus and simulation method for process of fracture temporary plugging by ice crystals | |
| CN107202675A (en) | The anti-freeze method of continous way transonic wind tunnel hydrojet nitrogen cooling system cooler | |
| CN108343600A (en) | A kind of performance test bed and application method for compressor | |
| CN205203423U (en) | Refrigerating system suitable for aircraft fuel oil system icing tests | |
| CN110879159A (en) | High-temperature high-humidity aerosol sampling device and sampling method | |
| CN103105482A (en) | Method for testing compression characteristics of gelled crude oil | |
| CN102359860B (en) | Clean vacuum system for engine plume test study and vacuum pumping repressing method thereof | |
| CN212133038U (en) | Process cooling water system for battery workshop | |
| CN220081627U (en) | Air compressor machine heat exchange tube bank with filter bypass subassembly | |
| CN209043534U (en) | A kind of inner hexagon device free of demolition of plate heat exchanger | |
| CN108195720A (en) | A kind of hydraulic air oil viscosity adjustable attenuation index testing device and test method | |
| CN2275240Y (en) | Quick freeze-thawing test device for concrete | |
| CN218847662U (en) | Refrigerator refrigerating system testing arrangement | |
| US1808087A (en) | Apparatus for treating gas | |
| RU146825U1 (en) | DEVICE FOR TESTING SEPARATION EQUIPMENT | |
| CN210892216U (en) | High-low temperature impact test box refrigerating system | |
| CN203881642U (en) | Device for determining specific fluidity of foam liquid | |
| CN105972001A (en) | Industrial refrigeration device for hydraulic bypass with adjustable pressure relief valve | |
| CN207513839U (en) | Dry screw air compressor grade postcooling structure | |
| CN201819487U (en) | Prepressing setting device for expansion valve | |
| CN220891084U (en) | Novel double-needle type pressure reducing valve | |
| CN221570875U (en) | Cooling circulation device for condensation point pour point tester |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |