CN211348019U - Automatic jet fuel freezing point tester - Google Patents
Automatic jet fuel freezing point tester Download PDFInfo
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- CN211348019U CN211348019U CN201922213891.XU CN201922213891U CN211348019U CN 211348019 U CN211348019 U CN 211348019U CN 201922213891 U CN201922213891 U CN 201922213891U CN 211348019 U CN211348019 U CN 211348019U
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- cold bath
- bath temperature
- laser
- freezing point
- jet fuel
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Abstract
The utility model discloses an automatic jet fuel ice point apparatus, including survey quick-witted case, switch, microcomputer, survey chamber, double glazing test tube, cold bath dewar bottle, low temperature medium, cold bath rabbling mechanism, sample temperature measurement sensor, sample rabbling mechanism, operating system and refrigeration coil pipe, the inside of double glazing test tube is equipped with laser detection mechanism. The utility model discloses in, one side of survey quick-witted case is equipped with overlapping compressor refrigerating system, overlapping compressor refrigerating system refrigerates survey quick-witted case through coupling hose, make the cold bath temperature can reach below-70 ℃, through the setting of constant temperature cold bath heating pipe, cold bath temperature measurement sensor and cold bath temperature controller, can make the cold bath temperature stable, help the test of fuel, replace the mode of phototube through laser emission receiver tube and the special reflector panel of laser, can satisfy in the test below-70 ℃, stability is higher, can accurately judge the crystallization degree of oil appearance.
Description
Technical Field
The utility model relates to a fuel measurement technical field sprays paint especially relates to automatic jet fuel freezing point tester.
Background
At present, most of domestic aviation fuel tests are manual test equipment, results of a small amount of automatic test equipment are not stable, manual tests need to look at a test tube and a thermometer, the temperature is recorded immediately when an oil sample is found to be turbid, then the temperature is raised until the turbid oil sample becomes clear, the temperature is recorded immediately, the labor intensity is high, a small amount of automatic test equipment adopts photoelectric detection, because the freezing point test tube is very thin, the temperature sensor, the stirring rod and the photoelectric detection part are required to be arranged in the test tube, the photoelectric tube can rarely work normally at the low temperature of 70 ℃ below zero, once the photoelectric tube works abnormally, the detection result is deviated, laser is adopted to detect the freezing point, because the laser brightness is high, the irradiation distance is long, and the digital dynamic acquisition and identification technology is adopted, the freezing point of the aviation fuel can be easily and accurately detected.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a: the automatic jet fuel freezing point tester aims to solve the problem that a photoelectric tube can rarely work normally at a low temperature of-70 ℃, and once the photoelectric tube works abnormally, the detection result is deviated.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the automatic jet fuel freezing point tester comprises a testing case, a power switch, a microcomputer, a testing cavity, a double-layer glass test tube, a cold bath Dewar flask, a low-temperature medium, a cold bath stirring mechanism, a sample temperature measuring sensor, a sample stirring mechanism, a lifting system and a refrigerating coil, wherein a laser detection mechanism is arranged inside the double-layer glass test tube, the laser detection mechanism consists of a laser emission receiving tube and a special laser reflection plate, and a refrigerating mechanism is arranged on one side of the testing case.
As a further description of the above technical solution:
the laser emission receiving tube is arranged at the top inner surface wall of the double-layer glass test tube, and the special laser reflection plate is arranged at the bottom inner surface wall of the double-layer glass test tube.
As a further description of the above technical solution:
the refrigerating mechanism comprises a cascade compressor refrigerating system, and the cascade compressor refrigerating system is communicated with the measuring case through a connecting hose.
As a further description of the above technical solution:
the inside of survey chamber is equipped with cold bath temperature sensor and constant temperature cold bath heating pipe, install cold bath temperature controller on the survey quick-witted case.
As a further description of the above technical solution:
the output end of the cold bath temperature measuring sensor is electrically connected with the input end of the cold bath temperature controller, and the output end of the cold bath temperature controller is electrically connected with the input end of the cold bath temperature measuring sensor.
To sum up, owing to adopted above-mentioned technical scheme, the beneficial effects of the utility model are that:
the utility model discloses in, one side of survey quick-witted case is equipped with overlapping compressor refrigerating system, overlapping compressor refrigerating system refrigerates survey quick-witted case through coupling hose, make the cold bath temperature can reach below-70 ℃, through the setting of constant temperature cold bath heating pipe, cold bath temperature measurement sensor and cold bath temperature controller, can make the cold bath temperature stable, help the test of fuel, replace the mode of phototube through laser emission receiver tube and the special reflector panel of laser, can satisfy in the test below-70 ℃, stability is higher, can accurately judge the crystallization degree of oil appearance.
Drawings
FIG. 1 is a schematic diagram of an assay system according to an embodiment of the present invention;
fig. 2 is a schematic diagram illustrating an internal structure of a double-layer glass test tube according to an embodiment of the present invention;
illustration of the drawings:
1. a cascade compressor refrigeration system; 2. a connecting hose; 3. a power switch; 4. a microcomputer; 5. a special laser reflector; 6. measuring a case; 7. a sample temperature measuring sensor; 8. a constant-temperature cold bath heating pipe; 9. double-layer glass test tubes; 10. a low temperature medium; 11. a cold bath temperature controller; 12. a laser emission receiving tube; 13. a cold bath stirring mechanism; 14. a measurement chamber; 15. a sample stirring mechanism; 16. a lifting system; 17. a cold bath dewar flask; 18. a cold bath temperature measurement sensor; 19. a refrigeration coil.
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 of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.
The cooling bath temperature controller 11 related in the utility model is a PI D controller;
referring to fig. 1-2, the present invention provides a technical solution: an automatic jet fuel freezing point tester comprises a testing case 6, a power switch 3, a microcomputer 4, a testing cavity 14, a double-layer glass test tube 9 and a cold bath Dewar flask 17, wherein a low-temperature medium 10 and a low-temperature medium 10 are arranged inside the testing cavity 14, a cold bath stirring mechanism 13, a sample temperature measuring sensor 7 and a cold bath stirring mechanism 13 are used for stirring the low-temperature medium 10, a sample stirring mechanism 15, a lifting system 16 and a refrigerating coil pipe 19 are arranged, the refrigerating coil pipe 19 is arranged in a spiral shape, the contact area of the cold bath stirring mechanism and the low-temperature medium 10 is increased, a laser detection mechanism is arranged inside the double-layer glass test tube 9 and consists of a laser transmitting and receiving tube 12 and a special laser reflection plate 5, the refrigerating mechanism is arranged on one side of the testing case 6, the laser transmitting and receiving tube 12 is arranged on the top inner surface wall of the double-layer glass test tube 9, the special laser reflection plate 5 is, the laser transmitting and receiving tube 12 and the special laser reflecting plate 5 replace a photoelectric tube, detection is carried out in a laser mode, the testing at the temperature below 70 ℃ below zero can be met, the stability is higher, and the crystallization degree of the oil sample can be accurately judged.
Specifically, as shown in fig. 1, the refrigeration mechanism includes a cascade compressor refrigeration system 1, the cascade compressor refrigeration system 1 is communicated with the measurement enclosure 6 through a connection hose 2, and the cascade compressor refrigeration system 1 can refrigerate the measurement cavity 14 of the measurement enclosure 6 through the connection hose 2, so that the measurement cavity 14 is stabilized below-70 ℃.
Specifically, as shown in fig. 1, a cold bath temperature sensor 18 and a constant temperature cold bath heating pipe 8 are arranged inside the measurement cavity 14, the cold bath temperature sensor 18 and the constant temperature cold bath heating pipe 8 are fixed on the two side cavity walls of the measurement cavity 14, a cold bath temperature controller 11 is installed on the measurement case 6, the cold bath temperature controller 11 is fixed on the front surface wall of the measurement case 6, the output end of the cold bath temperature sensor 18 is electrically connected with the input end of the cold bath temperature controller 11, the output end of the cold bath temperature controller 11 is electrically connected with the input end of the cold bath temperature sensor 18, the cold bath temperature sensor 18 measures the temperature of the low-temperature medium 10, the cold bath temperature sensor 18 transmits a measurement signal to the cold bath temperature controller 11, and the cold bath temperature controller 11 transmits the signal to the constant temperature cold bath heating pipe 8, so that the temperature of the low-temperature medium 10 is in a stable state.
The working principle is as follows: when the device is used, the cascade compressor refrigeration system 1 refrigerates the measuring case 6 through the connecting hose 2, so that the measuring cavity 14 of the measuring case 6 is stabilized below minus 70 ℃, the cold bath temperature measuring sensor 18 measures the temperature of the low-temperature medium 10, the cold bath temperature measuring sensor 18 transmits a measuring signal to the cold bath temperature controller 11, the cold bath temperature controller 11 transmits the signal to the constant-temperature cold bath heating pipe 8, so that the temperature of the low-temperature medium 10 is in a stable state, and the device is favorable for testing fuel.
The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (5)
1. The automatic jet fuel freezing point tester comprises a testing machine case (6), a power switch (3), a microcomputer (4), a testing cavity (14), a double-layer glass test tube (9), a cold bath Dewar flask (17), a low-temperature medium (10), a cold bath stirring mechanism (13), a sample temperature measuring sensor (7), a sample stirring mechanism (15), a lifting system (16) and a refrigerating coil pipe (19), and is characterized in that a laser detection mechanism is arranged inside the double-layer glass test tube (9), the laser detection mechanism is composed of a laser emission receiving tube (12) and a special laser reflection plate (5), and a refrigerating mechanism is arranged on one side of the testing machine case (6).
2. The automatic jet fuel freezing point tester according to claim 1, wherein the laser emission receiving tube (12) is disposed at the top inner surface wall of the double-layer glass test tube (9), and the laser special reflection plate (5) is disposed at the bottom inner surface wall of the double-layer glass test tube (9).
3. The automatic jet fuel freezing point tester of claim 1, wherein the refrigeration mechanism comprises a cascade compressor refrigeration system (1), and the cascade compressor refrigeration system (1) is communicated with the tester case (6) through a connecting hose (2).
4. The automatic jet fuel freezing point tester of claim 1, wherein a cold bath temperature measuring sensor (18) and a constant temperature cold bath heating pipe (8) are arranged inside the testing cavity (14), and a cold bath temperature controller (11) is installed on the testing cabinet (6).
5. The automatic jet fuel freezing point tester of claim 4, wherein the output end of the cold bath temperature sensor (18) is electrically connected with the input end of the cold bath temperature controller (11), and the output end of the cold bath temperature controller (11) is electrically connected with the input end of the cold bath temperature sensor (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922213891.XU CN211348019U (en) | 2019-12-11 | 2019-12-11 | Automatic jet fuel freezing point tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922213891.XU CN211348019U (en) | 2019-12-11 | 2019-12-11 | Automatic jet fuel freezing point tester |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211348019U true CN211348019U (en) | 2020-08-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922213891.XU Active CN211348019U (en) | 2019-12-11 | 2019-12-11 | Automatic jet fuel freezing point tester |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113125493A (en) * | 2021-04-15 | 2021-07-16 | 濮阳市盛源能源科技股份有限公司 | Instrument for analyzing crystallization point of maleic anhydride |
-
2019
- 2019-12-11 CN CN201922213891.XU patent/CN211348019U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113125493A (en) * | 2021-04-15 | 2021-07-16 | 濮阳市盛源能源科技股份有限公司 | Instrument for analyzing crystallization point of maleic anhydride |
| CN113125493B (en) * | 2021-04-15 | 2023-09-12 | 濮阳市盛源能源科技股份有限公司 | Instrument for analyzing maleic anhydride crystallization point |
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