CN201320458Y - Automatic testing device for aviation fuel water reaction - Google Patents
Automatic testing device for aviation fuel water reaction Download PDFInfo
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- CN201320458Y CN201320458Y CNU2008202159671U CN200820215967U CN201320458Y CN 201320458 Y CN201320458 Y CN 201320458Y CN U2008202159671 U CNU2008202159671 U CN U2008202159671U CN 200820215967 U CN200820215967 U CN 200820215967U CN 201320458 Y CN201320458 Y CN 201320458Y
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Abstract
The utility model relates to an automatic testing device for aviation fuel water reaction, which is characterized in that a front support (2) and a rear support (3) are installed on a base (1); a guide rail (4) is installed on the front support (3); the guide rail (4) is matched with a sliding block or a roller (5); the sliding block or the roller (5) is installed on a sliding plate (6); the lower part of the sliding plate (6) is connected with a bracket (7); one end of a connecting pin (8) is fixed on the sliding plate (6); the other end of the connecting pin (8) is installed on a swinging arm (14); a connecting rod bearing (9) is inserted into the other end of the swinging arm (14); the other end of the connecting rod bearing is connected with one end of a drive rod (10); a counterbalance (11) is installed on the other end of the drive rod (10); the drive rod (10) is installed on a rotating shaft (12) which drives the drive rod (10) to rotate; the rotating shaft (12) is supported on the rear support (3); a rotating wheel (13) is installed on the rotating shaft (12) and drives the rotating shaft (12) to rotate; and the rotating wheel (13) is connected with a motor (16). The utility model has the advantages of simple structure, convenient manufacturing, accurate testing and favorable repeatability.
Description
Technical field
The utility model relates to a kind of detection test apparatus, especially a kind of be used for that the Aviation Fuel water reaction test uses be used for experimental rig that test tube is shaken, specifically a kind of aviation fuel water reaction automatic tester.
Background technology
In relevant national standard, stipulated corresponding aviation fuel water reaction test method, as the method for inspection of water miscibility component existence in aviation gasoline and the aviation turbine fuel, and these components are to the assay method of Volume Changes and oil-water interfaces influence.When being used for aviation gasoline, the water reaction volume of mensuration changes, and shows the existence of water-soluble component such as alcohols.When being used for aviation turbine fuel, the grading of the water reaction interface of mensuration shows the existence that more soluble contaminants (as surfactant) arranged.The pollutant that influences the interface makes filter separator very fast ineffective easily, and allows free water and particle pass through, and finally influences the oily safety of using of aircraft equipment.
Therefore, the aviation fuel water reaction test is an important method checking the cleanliness index of water miscibility component existence in jet fuel and the aviation gasoline.Carry out water reaction test, significant to the quality control that adapts to the jet fuel production control, improves the quality of products and strengthen in oil product transportation, the storage process.In recent years, often dispute is appearred in the jet fuel water reaction test because of the result is different between oil Petrochemical Enterprises, oil depot, the station.Find that through investigation the main cause that causes the objection of water reaction result is experimental condition wider range of standard method regulation, is being easy to generate difference aspect the actual control and then is influencing result of the test.State Standard of the People's Republic of China " aviation fuel water reaction test method GB/T1793-2000 " regulation test procedure is: at room temperature get the 20ml PBS and pour in the graduated cylinder, read volume and be accurate to 0.5ml.Add the 80ml sample again, beyond the Great Wall glass stopper; Shake graduated cylinder 2min ± 5s, per second 2～3 times, the amplitude of shaking is 12～25cm (and requiring carefully to shake graduated cylinder to avoid producing vortex, because it can destroy the emulsification that may form); Immediately graduated cylinder is placed on the platform that does not have vibrations, leaves standstill 5min; Do not pick up graduated cylinder, under natural light irradiation, the observed and recorded result.This regulation is difficult to agree by artificial the grasp owing to there is not supporting apparatus to realize, therefore causes the test deviation easily.
The purpose of jet fuel water reaction test mainly is to check and has or not water-soluble filler in the jet fuel, the cleannes of evaluating the fuels, the separating property of evaluation oil (comprising additive), water simultaneously.
Because China Petroleum constantly develops, oil recovery and oil Refining Technologies improve constantly, and are applied to demulsifier, corrosion inhibiter in crude Treatment and process.For improving the performance of jet fuel, often also be added with such as antifreeze additive, antisatic additive, anticorrosive additive, thermostability additive ... Deng; In acid, alkali refining process, if the soda acid slag separates totally, the washing sedimentation is insufficient; And in fuel storage, keeping, transportation, sneak into some surface reactive material, cleannes and and the separating property of water that these all might make fuel infiltrate water-soluble filler and influence fuel.Therefore, carry out water reaction test, the quality monitoring of strengthening the jet fuel production control, improve the quality of products and strengthening in oil product transportation, the storage process is had its important practical sense.
China's existing aviation fuel water reaction test method is GB/T1793-2000, is that adopting by reference U.S. test material association criterion ASTM D1094-85 " aviation fuel water reaction normal test method " works out.
The basic principle of the method is: with the cushioning liquid and the fuel mix that can keep PH=7, if having water-soluble filler in the fuel, then enter water, thereby cause the Volume Changes of water layer under condition determination.If trace demulsifier, corrosion inhibiter, additive, metallic salt or other surface reactive material (can reduce the general name of solution surface tension material) that have residual acid, alkaline residue in the fuel and carry into from raw material or process equipment, just can be adsorbed on the interface (interface that refers to liquid-liquid) between fuel and water two liquid, form intermediate layers such as fiber bar, fragment, foam or scum silica frost, or near immiscible fuel and moisture absciss layer, present emulsion.
This test has three kinds of evaluation criteria:
(1) the water Volume Changes is accurate to 0.5ml.
(2) state of interface: from the observed phenomenon of interface state be chosen as 1, totally three grades of 1b, 2.With 1 grade is best.
(3) separation degree: being divided into 1,2,3 grade by two liquid phase separation states, is best with 1 grade.
More than three kinds of evaluation results, all do not carry out quantitatively only illustrating to have or not in the fuel to have analyte, and the light and heavy degree that has analyte.And the result is that the physical-chemical phenomenon of appearance is evaluated after based on fuel and the neutral water mixing, so this assay method is called " water reaction ".
Tool plug glass cylinder: 100ml has only been stipulated in water reaction at present, and scale division value is 1ml, and the distance between the top of 100ml mark and graduated cylinder should be 50～60mm, and other has only stipulated the method for shaking, but does not have supporting with it instrument.As preceding described, same sample can different results occur because of the difference of the dynamics of experimenter's operation, amplitude, frequency, especially qualifiedly be easy to different result of the tests occur during with defective edge when oil product is in, cause producing dispute between supplier and the user.
Summary of the invention
The purpose of this utility model is mainly to rely on manually to shake test tube and different experimenters is often taken place during at existing aviation fuel water reaction test the different tests result to occur, the problem that error is bigger designs a kind of aviation fuel water reaction automatic tester that can shake the water reaction solution according to test specification.
The technical solution of the utility model is:
A kind of aviation fuel water reaction automatic tester, comprise base 1, it is characterized in that on described base 1, being equipped with fore-stock 2 and after-poppet 3, guide rail 4 is installed on the fore-stock 3, guide rail 4 matches with slide block or pulley 5, slide block or pulley 5 are installed on the slide plate 6, the bottom of slide plate 6 is connected with the carriage 7 that test tube is installed, one end of the connecting pin 8 that drive slide plate 6 moves up and down is fixed on the slide plate 6, the other end of connecting pin 8 is inserted in the bearing on rocking arm 14 1 ends; be fitted with an end of pitman shaft 9 in the bearing of rocking arm 14 other ends; the other end of pitman shaft 9 links to each other with an end of drive rod 10; other end of drive rod 10 is equipped with balance weight 11, and drive rod 10 is installed in the rotating shaft 12 that drives its rotation, and rotating shaft 12 is bearing on the after-poppet 3 by bearing; the runner 13 that drives its rotation is installed on it; runner 13 and drive rod 10 lay respectively at the both sides of after-poppet 3, and runner 13 links to each other with the output shaft of motor 16 by driving-belt 15, and motor 16 is installed on the base 1.
The position of described balance weight 11 on drive rod 10 is adjustable, and the position of pitman shaft 9 on drive rod 10 is also adjustable.
Counting is installed on fore-stock 3 uses sensor, be equipped with at rocking arm 14 on the end of pitman shaft 9 sensing element that matches is installed.
Described counting sensor is Hall element or optocoupler sensor, and correspondingly described sensing element is magnet or sensor devices.
Described carriage 7 is provided with the elastic card claw of clamping test tube and makes the adjustment screw of test tube clamping and positioning.
Described counting links to each other with the input of sensor measuring circuit D1 with the output of sensor, the output of sensor measuring circuit D1 links to each other with interface and control circuit D2 corresponding input end, the output that the power input of interface and control circuit D2 is corresponding with power circuit D3 links to each other, the output of interface and control circuit D2 links to each other with central processing unit D4 corresponding input end, central processing unit D4 is connected with button and display circuit D5 and time delayer D6 respectively, and the power input of central processing unit D4 links to each other with the power output end of corresponding power circuit D3.
Described central processing unit D4 is made up of single-chip microcomputer U1-1, memory U1-2, U1-4 and button interface circuit L2; Described button and display circuit D5 show that by keyboard integrated circuit U 4, nixie display U3, U2, interface circuit L3 and key circuit U5 form; Described interface and control circuit D2 are made up of single-chip microcomputer U3-3 and peripheral circuit thereof.
The beneficial effects of the utility model:
The utility model provides reliable experimental condition control device for aviation fuel water reaction test method, can improve the implementation effect of existing national standard test method, reduce artificial test error, to the jet fuel production control, improve the quality of products and the quality monitoring etc. strengthened in oil product transportation, the storage process will produce far-reaching positive meaning, have military preferably, economic and social benefit, can be widely used in oil depot, station and oil Petrochemical Enterprises administrative department.
The utility model can make GB test method defined terms with standard criterion require controlled, thereby avoid different personnel, different experiments chamber when carrying out water reaction test, to produce deviation, guarantee the repeatability and the reliability of result of the test, avoid the dispute that result of the test is produced because of human factor.
The utlity model has simple in structure, easily manufactured, can realize Automatic Control by simple circuit design, realize that test period, per minute shake number of times and the distance that fluctuates adjustable, therefore except the water reaction that can check oil product is whether qualified, also can find out best test parameters by the different parameters adjustment.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is the syndeton schematic diagram of slide plate of the present utility model and fore-stock.
Fig. 3 is an electric theory diagram of the present utility model.
Fig. 4 is the electrical schematic diagram of sensor measuring circuit of the present utility model.
Fig. 5 is the electrical schematic diagram of interface of the present utility model and control circuit.
Fig. 6 is the electrical schematic diagram of power circuit of the present utility model.
Fig. 7 is the electrical schematic diagram of central processing unit of the present utility model.
Fig. 8 is button of the present utility model and display circuit electrical schematic diagram.
Fig. 9 is the electrical schematic diagram of motor power supply circuits of the present utility model.
The specific embodiment
Below in conjunction with drawings and Examples the utility model is further described.
Shown in Fig. 1-9.
A kind of aviation fuel water reaction automatic tester, comprise that base 1 and cover are contained in the housing 19 on the base 1, fore-stock 2 and after-poppet 3 are installed on described base 1, guide rail 4 is installed on the fore-stock 3, guide rail 4 matches with slide block or pulley 5, slide block or pulley 5 are installed on the slide plate 6, guide rail 4 can adopt cylindrical structure shown in Figure 2, the pulley 5 that matches with cylinder guide rail 4 can adopt the pulley that has arc groove on the periphery, during concrete enforcement, guide rail 4 also can adopt I-shaped or V font guide rail commonly used on the lathe, and corresponding slide block 5 also should adopt the I-shaped or V font slide block that matches, it is simple in structure that pulley and cylinder match, cost is low, but precision and wearability are slightly poor, the good precision height of the wearability of machine tool guideway and slide block, certainly cost is also high, can be determined according to user's needs when specifically implementing.When the bottom of slide plate 6 is connected with the carriage 7 that test tube is installed, carriage 7 is provided with the elastic card claw 20 of clamping test tube and makes the adjustment screw 21 of test tube clamping and positioning.One end of the connecting pin 8 that drive slide plate 6 moves up and down is fixed on the slide plate 6, the other end of connecting pin 8 is inserted in the bearing on rocking arm 14 1 ends; be fitted with an end of pitman shaft 9 in the bearing of rocking arm 14 other ends; the other end of pitman shaft 9 links to each other with an end of drive rod 10; other end of drive rod 10 is equipped with balance weight 11; drive rod 10 is installed in the rotating shaft 12 that drives its rotation; rotating shaft 12 is bearing on the after-poppet 3 by bearing; the runner 13 that drives its rotation is installed on it; runner 13 and drive rod 10 lay respectively at the both sides of after-poppet 3; runner 13 links to each other with the output shaft of motor 16 by driving-belt 15, and motor 16 is installed on the base 1.As shown in Figure 1.
During concrete enforcement, the position of balance weight 11 on drive rod 10 also can be designed to adjustable structure, the position of pitman shaft 9 on drive rod 10 also can be designed to adjustable structure, and adjustable structure both can adopt the guiding mechanism of electromechanical structure, also can adopt the helicitic texture of pure machinery.
Counting is installed with sensor 17 on fore-stock 3, is equipped with at rocking arm 14 on the end of pitman shaft 9 sensing element 18 that matches is installed.Counting can adopt Hall element or optocoupler sensor with sensor, and correspondingly described sensing element can adopt magnet or sensor devices.
Fig. 3 is an electric theory diagram of realizing electric control system of the present utility model.It is mainly by sensor measuring circuit D1 (Fig. 4), interface and control circuit D2 (Fig. 5), power circuit D3 (Fig. 6), central processing unit D4 (Fig. 7), button and display circuit D5 (Fig. 8), time delays device D6 (model can be JSA100), power supply and firing switch, form for the motor power supply circuits (Fig. 9) of direct current generator power supply, and wherein power circuit D3 provides the low-voltage direct working power for corresponding interface and control circuit D2, button and display circuit D5, central processing unit D4 etc.
Counting links to each other with the input of sensor measuring circuit D1 with the output of sensor, the output of sensor measuring circuit D1 links to each other with interface and control circuit D2 corresponding input end, the output that the power input of interface and control circuit D2 is corresponding with power circuit D3 links to each other, the output of interface and control circuit D2 links to each other with central processing unit D4 corresponding input end, central processing unit D4 is connected with button and display circuit D5 and time delayer D6 respectively, and the power input of central processing unit D4 links to each other with the power output end of corresponding power circuit D3.
Central processing unit D4 is made up of single-chip microcomputer U1-1, memory U1-2, U1-4 and button interface circuit L2, as shown in Figure 7; Button and display circuit D5 show that by keyboard integrated circuit U 4, nixie display U3, U2, interface circuit L3 and key circuit U5 and peripheral circuit thereof form, as shown in Figure 8; Interface and control circuit D2 are made up of single-chip microcomputer U3-3 and peripheral circuit thereof, as shown in Figure 5.
The utility model does not relate to the part prior art that maybe can adopt all same as the prior art to be realized.
Claims (7)
1, a kind of aviation fuel water reaction automatic tester, comprise base (1), it is characterized in that on described base (1), being equipped with fore-stock (2) and after-poppet (3), guide rail (4) is installed on the fore-stock (3), guide rail (4) matches with slide block or pulley (5), slide block or pulley (5) are installed on the slide plate (6), the bottom of slide plate (6) is connected with the carriage (7) that test tube is installed, one end of the connecting pin (8) that drive slide plate (6) moves up and down is fixed on the slide plate (6), the other end of connecting pin (8) is inserted in the bearing on rocking arm (14) one ends; be fitted with an end of pitman shaft (9) in the bearing of rocking arm (14) other end; the other end of pitman shaft (9) links to each other with an end of drive rod (10); the other end of drive rod (10) is equipped with balance weight (11); drive rod (10) is installed in the rotating shaft (12) that drives its rotation; rotating shaft (12) is bearing on the after-poppet (3) by bearing; the runner (13) that drives its rotation is installed on it; runner (13) and drive rod (10) lay respectively at the both sides of after-poppet (3); runner (13) passes through driving-belt (15) and links to each other with the output shaft of motor (16), and motor (16) is installed on the base (1).
2, aviation fuel water reaction automatic tester according to claim 1 is characterized in that the position of described balance weight (11) on drive rod (10) is adjustable, and the position of pitman shaft (9) on drive rod (10) is also adjustable.
3, aviation fuel water reaction automatic tester according to claim 1 is characterized in that being equipped with counting and uses sensor on fore-stock (3), be equipped with at rocking arm (14) on the end of pitman shaft (9) sensing element that matches is installed.
4, aviation fuel water reaction automatic tester according to claim 3 is characterized in that described counting sensor is Hall element or optocoupler sensor, and correspondingly described sensing element is magnet or sensor devices.
5, aviation fuel water reaction automatic tester according to claim 1 is characterized in that described carriage (7) is provided with the elastic card claw and the adjustment screw that makes the test tube clamping and positioning of clamping test tube.
6, aviation fuel water reaction automatic tester according to claim 3, it is characterized in that described counting links to each other with the input of sensor measuring circuit (D1) with the output of sensor, the output of sensor measuring circuit (D1) links to each other with interface and control circuit (D2) corresponding input end, the output that the power input of interface and control circuit (D2) is corresponding with power circuit (D3) links to each other, the output of interface and control circuit (D2) links to each other with central processing unit (D4) corresponding input end, central processing unit (D4) is connected with button and display circuit (D5) and time delayer (D6) respectively, and the power input of central processing unit (D4) links to each other with the power output end of corresponding power circuit (D3).
7, aviation fuel water reaction automatic tester according to claim 6 is characterized in that described central processing unit (D4) is made up of single-chip microcomputer (U1-1), memory (U1-2, U1-4) and button interface circuit (L2); Described button and display circuit (D5) are made up of keyboard demonstration integrated circuit (U4), nixie display (U3, U2), interface circuit (L3) and key circuit (U5); Described interface and control circuit (D2) are made up of single-chip microcomputer (U3-3) and peripheral circuit thereof.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008202159671U CN201320458Y (en) | 2008-11-26 | 2008-11-26 | Automatic testing device for aviation fuel water reaction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008202159671U CN201320458Y (en) | 2008-11-26 | 2008-11-26 | Automatic testing device for aviation fuel water reaction |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201320458Y true CN201320458Y (en) | 2009-10-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2008202159671U Expired - Lifetime CN201320458Y (en) | 2008-11-26 | 2008-11-26 | Automatic testing device for aviation fuel water reaction |
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| Country | Link |
|---|---|
| CN (1) | CN201320458Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101430314B (en) * | 2008-11-26 | 2011-12-14 | 中国人民解放军南京军区联勤部油料监督处 | Aviation fuel water reaction automatic tester |
| CN114452868A (en) * | 2022-02-08 | 2022-05-10 | 睿科集团(厦门)股份有限公司 | High-frequency vertical oscillation device for extraction pretreatment |
-
2008
- 2008-11-26 CN CNU2008202159671U patent/CN201320458Y/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101430314B (en) * | 2008-11-26 | 2011-12-14 | 中国人民解放军南京军区联勤部油料监督处 | Aviation fuel water reaction automatic tester |
| CN114452868A (en) * | 2022-02-08 | 2022-05-10 | 睿科集团(厦门)股份有限公司 | High-frequency vertical oscillation device for extraction pretreatment |
| CN114452868B (en) * | 2022-02-08 | 2023-04-25 | 睿科集团(厦门)股份有限公司 | High-frequency vertical oscillation device for extraction pretreatment |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20091007 Effective date of abandoning: 20081126 |