CN115105862A - Permeable membrane, application of permeable membrane in dehydration method of cyclopropane aerospace fuel, dehydration method, dehydration system and fuel - Google Patents
Permeable membrane, application of permeable membrane in dehydration method of cyclopropane aerospace fuel, dehydration method, dehydration system and fuel Download PDFInfo
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- CN115105862A CN115105862A CN202210656271.7A CN202210656271A CN115105862A CN 115105862 A CN115105862 A CN 115105862A CN 202210656271 A CN202210656271 A CN 202210656271A CN 115105862 A CN115105862 A CN 115105862A
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- 239000000446 fuel Substances 0.000 title claims abstract description 250
- 230000018044 dehydration Effects 0.000 title claims abstract description 136
- 238000006297 dehydration reaction Methods 0.000 title claims abstract description 136
- 239000012528 membrane Substances 0.000 title claims abstract description 125
- LVZWSLJZHVFIQJ-UHFFFAOYSA-N Cyclopropane Chemical compound C1CC1 LVZWSLJZHVFIQJ-UHFFFAOYSA-N 0.000 title claims abstract description 117
- 238000000034 method Methods 0.000 title claims abstract description 54
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 141
- 230000003204 osmotic effect Effects 0.000 claims abstract description 28
- 125000001559 cyclopropyl group Chemical group [H]C1([H])C([H])([H])C1([H])* 0.000 claims abstract description 10
- 150000001942 cyclopropanes Chemical class 0.000 claims abstract description 9
- 239000004372 Polyvinyl alcohol Substances 0.000 claims description 34
- 229920002451 polyvinyl alcohol Polymers 0.000 claims description 34
- 239000002033 PVDF binder Substances 0.000 claims description 31
- 229920002981 polyvinylidene fluoride Polymers 0.000 claims description 31
- ZMXDDKWLCZADIW-UHFFFAOYSA-N N,N-Dimethylformamide Chemical compound CN(C)C=O ZMXDDKWLCZADIW-UHFFFAOYSA-N 0.000 claims description 30
- 239000011259 mixed solution Substances 0.000 claims description 20
- 238000001816 cooling Methods 0.000 claims description 19
- 239000002904 solvent Substances 0.000 claims description 18
- -1 cyclopropanyl Chemical group 0.000 claims description 14
- 238000007790 scraping Methods 0.000 claims description 10
- 238000013329 compounding Methods 0.000 claims description 9
- 238000002156 mixing Methods 0.000 claims description 8
- 125000002496 methyl group Chemical group [H]C([H])([H])* 0.000 claims description 3
- 239000000498 cooling water Substances 0.000 claims description 2
- 125000001495 ethyl group Chemical group [H]C([H])([H])C([H])([H])* 0.000 claims description 2
- 239000000203 mixture Substances 0.000 claims description 2
- 239000007788 liquid Substances 0.000 abstract description 60
- 238000000926 separation method Methods 0.000 abstract description 4
- 239000000047 product Substances 0.000 description 31
- 230000000694 effects Effects 0.000 description 11
- LPAHHILSHMILJD-UHFFFAOYSA-N 1,2-diethyl-1-methylcyclopropane Chemical compound CCC1CC1(C)CC LPAHHILSHMILJD-UHFFFAOYSA-N 0.000 description 9
- 230000000052 comparative effect Effects 0.000 description 9
- 238000004581 coalescence Methods 0.000 description 8
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- 239000002250 absorbent Substances 0.000 description 5
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- 238000001179 sorption measurement Methods 0.000 description 5
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- 238000002360 preparation method Methods 0.000 description 4
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 3
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- BGNXCDPZJCUKKN-UHFFFAOYSA-N CCCC1CC1(C)CCC Chemical compound CCCC1CC1(C)CCC BGNXCDPZJCUKKN-UHFFFAOYSA-N 0.000 description 1
- CSNNHWWHGAXBCP-UHFFFAOYSA-L Magnesium sulfate Chemical compound [Mg+2].[O-][S+2]([O-])([O-])[O-] CSNNHWWHGAXBCP-UHFFFAOYSA-L 0.000 description 1
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- JTJMJGYZQZDUJJ-UHFFFAOYSA-N phencyclidine Chemical compound C1CCCCN1C1(C=2C=CC=CC=2)CCCCC1 JTJMJGYZQZDUJJ-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D17/00—Separation of liquids, not provided for elsewhere, e.g. by thermal diffusion
- B01D17/02—Separation of non-miscible liquids
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D17/00—Separation of liquids, not provided for elsewhere, e.g. by thermal diffusion
- B01D17/02—Separation of non-miscible liquids
- B01D17/04—Breaking emulsions
- B01D17/042—Breaking emulsions by changing the temperature
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D17/00—Separation of liquids, not provided for elsewhere, e.g. by thermal diffusion
- B01D17/08—Thickening liquid suspensions by filtration
- B01D17/085—Thickening liquid suspensions by filtration with membranes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
- B01D—SEPARATION
- B01D71/00—Semi-permeable membranes for separation processes or apparatus characterised by the material; Manufacturing processes specially adapted therefor
- B01D71/06—Organic material
- B01D71/38—Polyalkenylalcohols; Polyalkenylesters; Polyalkenylethers; Polyalkenylaldehydes; Polyalkenylketones; Polyalkenylacetals; Polyalkenylketals
-
- C—CHEMISTRY; METALLURGY
- C10—PETROLEUM, GAS OR COKE INDUSTRIES; TECHNICAL GASES CONTAINING CARBON MONOXIDE; FUELS; LUBRICANTS; PEAT
- C10L—FUELS NOT OTHERWISE PROVIDED FOR; NATURAL GAS; SYNTHETIC NATURAL GAS OBTAINED BY PROCESSES NOT COVERED BY SUBCLASSES C10G, C10K; LIQUEFIED PETROLEUM GAS; ADDING MATERIALS TO FUELS OR FIRES TO REDUCE SMOKE OR UNDESIRABLE DEPOSITS OR TO FACILITATE SOOT REMOVAL; FIRELIGHTERS
- C10L1/00—Liquid carbonaceous fuels
- C10L1/04—Liquid carbonaceous fuels essentially based on blends of hydrocarbons
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- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Oil, Petroleum & Natural Gas (AREA)
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- General Chemical & Material Sciences (AREA)
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- Separation Using Semi-Permeable Membranes (AREA)
Abstract
The invention discloses a permeable membrane and application thereof in a dehydration method of a cyclopropane aerospace fuel, the dehydration method, a dehydration system and the fuel, wherein the dehydration method comprises the following steps: 1) dehydrating the cyclopropane aerospace fuel at low temperature within the temperature range of 4-15 ℃; 2) carrying out high-temperature treatment on the low-temperature dehydrated cyclopropane-based aerospace fuel at the temperature of 50-90 ℃; 3) and (3) performing osmotic dehydration on the cyclopropane based aerospace fuel subjected to high-temperature treatment by adopting a negative pressure permeable membrane to obtain the dehydrated cyclopropane based aerospace fuel. After the cyclopropane group aerospace fuel is treated at low temperature, the solubility of the dissolved water in the fuel is reduced, so that free water is separated out and generated, and the free water is gathered into larger water drops to be settled, so that the water and the cyclopropane group aerospace fuel are separated; water molecules in the high-temperature cyclopropane-based aerospace fuel can be vaporized into water vapor through the permeable membrane under the action of pressure difference and under negative pressure, and the water vapor is cooled to form liquid water, so that the separation from the fuel is realized, and the dehydration is completed.
Description
Technical Field
The invention belongs to the technical field of liquid propellants, and particularly relates to a permeable membrane, application thereof in a dehydration method of a cyclopropane-based aerospace fuel, the dehydration method, a dehydration system and the fuel.
Background
In the cyclopropane structure, three carbon atoms are in the same plane, forming an equilateral triangle with an angle of 60 degrees. The C-C bond of the cyclopropane structure is shorter than the C-C bond of the straight-chain alkane, the bond energy is high, and the cyclopropane compound has a cyclopropane ternary strained ring structure, so that the cyclopropane compound has high tensile energy. Therefore, the cyclopropane compound can be used as a fuel component of an aerospace propellant, and contributes to improving the specific impulse performance of the propellant.
In the 19 th century or around the 60 th century, the Su Union developed a cyclopropane-based high-performance liquid aerospace fuel, the compound name of which was 1-methyl-1, 2-dipropylcyclopropane, and the name of which was Syntin. The compound is a high-tension ring compound containing 3 cyclopropane structures, can be used for a liquid oxygen kerosene rocket engine by combining with liquid oxygen, is improved by more than 7s compared with the conventional petroleum-based rocket kerosene, is the only cyclopropyl rocket fuel realizing model application at present, and is also the focus of research of experts and scholars in the field of space fuel.
Because the cyclopropane structure has certain polarity, the overall polarity of the cyclopropane-based fuel is slightly greater than that of the conventional petroleum-based rocket kerosene. The solubility of water molecules in cyclopropane-based fuels is relatively high, typically above 200 ppm. However, rocket fuel applications have extremely stringent requirements for water content.
For example, the water content of petroleum-based rocket kerosene is typically below 150ppm, sometimes even below 50 ppm. Due to the influence of the low temperature of the liquid oxygen pipeline, the excessive water content in the kerosene is easy to cause water crystallization and precipitation, block an engine and cause serious accidents. Therefore, it is important to reduce the water content of rocket fuels.
Conventional dehydration methods include distillation dehydration, desiccant adsorption dehydration, filtration dehydration, microfiltration or nanofiltration membrane dehydration, and the like. Most of these methods are suitable for removing free water from fuel, and the removal effect is not ideal, and is generally used for removing water with a water content of 1000 ppm.
The water content in the cyclopropane fuel is more than 200ppm, so the conventional dehydration method can not effectively remove free water and dissolved water in the cyclopropane fuel. In addition, at present, no dehydration method is suitable for removing dissolved water and free water in fuels with higher polarity represented by cyclopropane aerospace liquid fuels, so that the large-scale application of aerospace liquid fuels is hindered.
Therefore, in order to realize the industrial application of the cyclopropane aerospace liquid fuel, a fuel dehydration method which has simple process and high treatment efficiency and is suitable for industrial amplification is urgently needed to be found.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a dehydration method of cyclopropane-based space fuel, which effectively reduces the water content in the cyclopropane-based space fuel by combining a low-temperature dehydration process and a high-temperature negative pressure membrane permeation process.
The basic concept of the technical scheme adopted by the invention is as follows:
a dehydration method of cyclopropane-based aerospace fuel comprises the following steps:
1) dehydrating the cyclopropanyl aerospace fuel at low temperature within the temperature range of 4-15 ℃;
2) carrying out high-temperature treatment on the low-temperature dehydrated cyclopropane-based aerospace fuel at the temperature of 50-90 ℃;
3) and (3) performing osmotic dehydration on the cyclopropane based aerospace fuel subjected to high-temperature treatment by adopting a negative pressure permeable membrane to obtain the dehydrated cyclopropane based aerospace fuel.
The solubility of water in the cyclopropane-based aerospace fuel changes with temperature, and the lower the temperature, the lower the solubility of water in the cyclopropane-based aerospace fuel. After the cyclopropane aerospace fuel is processed at low temperature, the solubility of the water dissolved in the cyclopropane aerospace fuel liquid is reduced, and then the free water is separated out and generated, and the free water is gathered into larger water drops to be settled, so that the water and the cyclopropane aerospace fuel liquid can be well separated.
The water content in the cyclopropanyl aerospace fuel dehydrated at low temperature is greatly reduced, but part of water still exists in the form of dissolved water and is not easy to separate out. Therefore, the cyclopropanyl aerospace fuel is subjected to high-temperature treatment; water molecules in the high-temperature cyclopropane based aerospace fuel can permeate through the permeable membrane under the action of pressure difference, and are vaporized into water vapor under the negative pressure condition, and then the water vapor is cooled to form liquid water which is separated from the cyclopropane based aerospace fuel, so that the dehydrated cyclopropane based aerospace fuel is obtained.
Further, the step 1) comprises: precooling the cyclopropane-based space fuel to 10-15 ℃, and then dehydrating the precooled cyclopropane-based space fuel at a low temperature in a temperature range of 4-10 ℃;
preferably, the dehydration is carried out at a low temperature within the temperature range of 4-10 ℃ for 30min-1 h.
When the cyclopropane based space fuel is precooled to 7-15 ℃, the cyclopropane based space fuel is in a low-temperature state, and then the cyclopropane based space fuel is kept in a low-temperature state of 4-10 ℃, the solubility of the water dissolved in the cyclopropane based space fuel is reduced, the water is separated out to generate free water, and the free water is gathered into larger water beads to be settled, so that the water and the cyclopropane based space fuel are well separated.
Further, the step 2) comprises: firstly, preheating the cyclopropanyl aerospace fuel dehydrated at low temperature to 50-70 ℃, and then carrying out high-temperature treatment on the preheated cyclopropanyl aerospace fuel at the temperature of 85-90 ℃.
When the cyclopropane-based aerospace fuel is preheated to 50-70 ℃, the cyclopropane-based aerospace fuel is in a high-temperature state, then high-temperature treatment is carried out within the temperature range of 85-90 ℃, water in the cyclopropane-based aerospace fuel after high-temperature treatment is vaporized into water vapor under the negative pressure condition, and the water vapor is cooled and condensed into liquid water which is separated from the cyclopropane-based aerospace fuel.
Further, the pressure difference between two sides of the permeable membrane in the step 3) is 28-40 kpa;
preferably, the pressure difference is 35-40 kpa;
preferably, the time period of osmotic dehydration in the step 3) is 20-40 min.
Preferably, the permeable membrane in the step 3) is formed by compounding polyvinyl alcohol and polyvinylidene fluoride;
preferably, in the step 3), at least two times of osmotic dehydration of the negative pressure permeable membrane are carried out.
Water in the high-temperature treated cyclopropane-based aerospace fuel can permeate through a permeable membrane compounded by polyvinyl alcohol and polyvinylidene fluoride under the action of pressure difference and is vaporized into water vapor under the negative pressure condition.
Further, the method also comprises the following steps after the step 3): step 4), cooling and condensing the water vapor generated in the osmotic dehydration process;
preferably, in the step 4), the temperature is reduced to a temperature range of 20-30 ℃.
The invention also provides a permeable membrane, which is compounded by polyvinyl alcohol and polyvinylidene fluoride.
The permeable membrane is compounded by polyvinyl alcohol and polyvinylidene fluoride, and hydroxyl active groups are used as permeable groups, so that water molecules can be effectively adsorbed and permeated. The content of hydroxyl active groups in the polyvinyl alcohol is high, the adsorption and permeation effects on water molecules are good, and the efficiency is high; moreover, the permeable membrane has the function of resisting the hydrophilic wetting of an organic solvent, has higher toughness, can effectively prevent the permeation of fuel molecules, and can effectively reduce the loss rate of the fuel. In addition, the polyvinyl alcohol and the polyvinylidene fluoride can not be dissolved in the cyclopropane aerospace fuel, so that the high purity of the cyclopropane aerospace fuel is ensured, and the pollution of the osmotic membrane to the cyclopropane aerospace fuel is avoided.
Further, the step of preparing the permeable membrane by compounding the polyvinyl alcohol and the polyvinylidene fluoride comprises the following steps:
31) mixing polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water according to a mass ratio of 100: 5-20: 150-200: preparing a mixed solution according to the proportion of 1000-1300;
32) scraping the mixed solution into a film structure;
33) standing and compacting the membrane structure to form the permeable membrane;
preferably, in the step 32), the film structure is scraped at the temperature of 40-50 ℃, and the thickness of the film structure is 0.5-1.3 mm;
preferably, in the step 33), the permeable membrane is formed by standing at normal temperature until the solvent is volatilized and compacting; preferably, the mixture is kept still for 48 hours.
The invention also provides the use of a permeable membrane as described above in a process for the dehydration of a cyclopropane-based aerospace fuel;
preferably, the permeable membrane is used in a process for the dehydration of a cyclopropane-based aerospace fuel as described above.
The invention also discloses a cyclopropane aerospace fuel, which is dehydrated by adopting any one of the dehydration methods in the technical scheme, and the water content of the cyclopropane aerospace fuel is not higher than 100 ppm;
preferably, the structural formula of the cyclopropane-based aerospace fuel is shown as the following formula I:
wherein R is 1 Selected from methyl, ethyl, cyclopropyl.
The invention also discloses a dehydration system of the cyclopropane-based space fuel, which is controlled by adopting any dehydration method in the technical scheme;
preferably, the dewatering system comprises:
the low-temperature dehydration device is used for dehydrating the cyclopropane-based space fuel at low temperature;
the high-temperature treatment device is communicated with the low-temperature dehydration device and is used for carrying out high-temperature treatment on the cyclopropane-based aerospace fuel dehydrated by the low-temperature dehydration device at low temperature;
the negative pressure permeation membrane component is communicated with the high-temperature treatment device and is used for permeating and dehydrating the high-temperature treated cyclopropane-based space fuel;
preferably, the device also comprises a cooling device which is communicated with the negative pressure osmotic membrane component and is used for cooling and condensing water vapor generated in the osmotic dehydration process;
preferably, the negative pressure permeable membrane module comprises:
a housing having a cavity therein;
the permeable membrane is arranged in the shell and divides the cavity into a first cavity and a second cavity, the first cavity is communicated with the high-temperature treatment device and used for containing the cyclopropane aerospace fuel, and the cooling device is communicated with the second cavity and used for cooling water vapor in the second cavity;
preferably, the dewatering system comprises at least two groups of the negative pressure osmosis membrane modules.
After adopting the technical scheme, compared with the prior art, the invention has the following beneficial effects:
in the invention, after the cyclopropane-based aerospace fuel is treated at low temperature, the solubility of the dissolved water in the cyclopropane-based aerospace fuel liquid is reduced, and then the dissolved water is separated out to generate free water, and the free water is gathered into larger water drops to be settled, so that the water and the cyclopropane-based aerospace fuel liquid can be well separated.
The water content in the cyclopropanyl aerospace fuel dehydrated at low temperature is greatly reduced, but part of water still exists in the form of dissolved water and is not easy to separate out. Therefore, the cyclopropanyl aerospace fuel is subjected to high-temperature treatment; water molecules in the high-temperature cyclopropane based aerospace fuel can permeate through the permeable membrane under the action of pressure difference, and are vaporized into water vapor under the condition of negative pressure, and then the water vapor is cooled to form liquid water which is separated from the cyclopropane based aerospace fuel, so that the dehydrated cyclopropane based aerospace fuel is obtained.
The permeable membrane is compounded by polyvinyl alcohol and polyvinylidene fluoride, and the hydroxyl active groups are used as the permeable groups, so that water molecules can be effectively adsorbed and permeated. The content of hydroxyl active groups in the polyvinyl alcohol is high, the adsorption and permeation effects on water molecules are good, and the efficiency is high; in addition, the permeable membrane has the function of resisting the hydrophilic wetting of the organic solvent, has higher toughness, can effectively prevent the permeation of fuel molecules, and can effectively reduce the loss rate of the fuel. In addition, the polyvinyl alcohol and the polyvinylidene fluoride can not be dissolved in the cyclopropane aerospace fuel, so that the high purity of the cyclopropane aerospace fuel is ensured, and the pollution of the osmotic membrane to the cyclopropane aerospace fuel is avoided.
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention, are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention without limiting the invention to the right. It is obvious that the drawings in the following description are only some embodiments and that for a person skilled in the art, other drawings can also be derived from them without inventive effort. In the drawings:
FIG. 1 is a schematic diagram of the assembly structure of the dehydration system of the cyclopropane-based aerospace fuel of the invention.
In the figure:
1. a precooler; 2. a low temperature dehydration tank; 3. a preheater; 4. a heater; 5. a housing; 6. a permeable membrane; 7. a first product tank; 8. a second product tank; 9. a condenser; 10. a vacuum pump.
It should be noted that the drawings and the description are not intended to limit the scope of the inventive concept in any way, but to illustrate it by a person skilled in the art with reference to specific embodiments.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and the following embodiments are used for illustrating the present invention and are not intended to limit the scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.
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; may be directly connected or indirectly connected through an intermediate. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1
As shown in fig. 1, the present embodiment discloses a dehydration system for a cyclopropane-based aerospace fuel, which includes:
the low-temperature dehydration device is used for dehydrating the cyclopropane-based space fuel at low temperature;
the high-temperature treatment device is communicated with the low-temperature dehydration device and is used for carrying out high-temperature treatment on the cyclopropane-based aerospace fuel dehydrated by the low-temperature dehydration device at low temperature;
the negative pressure permeation membrane component is communicated with the high-temperature treatment device and is used for permeating and dehydrating the high-temperature treated cyclopropane-based space fuel;
and the cooling device is communicated with the negative pressure permeation membrane component and is used for cooling and storing the permeated and dehydrated cyclopropane-based aerospace fuel.
Specifically, the low-temperature dehydration device comprises a precooler 1 and a low-temperature dehydration tank 2 communicated with the precooler 1, wherein the cyclopropane-based space fuel flows into the precooler 1 for precooling and then flows into the low-temperature dehydration tank 2 for low-temperature dehydration;
the high-temperature treatment apparatus includes a preheater 3 and a heater 4. The preheater 3 is communicated with the low-temperature dehydration tank 2, and the cyclopropane-based space fuel flowing out of the low-temperature dehydration tank 2 firstly flows into the preheater 3 to be preheated; the preheater 3 is communicated with the heater 4, and the cyclopropane-based aerospace fuel flowing out of the preheater 3 flows into the heater 4 for high-temperature treatment.
The negative pressure permeable membrane assembly comprises a shell 5 with a cavity inside and a permeable membrane 6 arranged inside the shell 5 and dividing the cavity into a first chamber and a second chamber, wherein the first chamber is communicated with a heater 4 and is used for containing high-temperature cyclopropane-based space fuel, the first chamber and the second chamber have pressure difference, and moisture of the cyclopropane-based space fuel in the first chamber is changed into water vapor under a negative pressure environment; water vapour enters the second chamber from the first chamber through the permeable membrane 6 under the influence of a pressure differential.
The second chamber is communicated with a condenser 9 of the temperature reducing device, and water vapor in the second chamber is condensed to form liquid water under the action of the condenser 9 and is separated from the cyclopropane aerospace fuel.
The first chamber is communicated with a first product tank 7, and the cyclopropane-based space fuel in the first chamber flows into the first product tank 7; further, the liquid flowing out of the first product tank 7 flows into the other shell of the negative pressure osmosis membrane component, the osmotic dehydration is carried out again, and the cyclopropyl group aerospace fuel after the osmotic dehydration is stored in the second product tank 8.
The dewatering system of the present invention further comprises a vacuum pump 10 in communication with the condenser 9 and the housing 5 for creating a negative pressure within the housing 5.
The dehydration system of the cyclopropane-based aerospace fuel can realize continuous and efficient dehydration of the cyclopropane-based aerospace fuel, does not need any water absorbent in the dehydration process, does not produce solid waste, can realize continuous operation, and is a dehydration system suitable for industrial amplification.
Example 2
The fuel in this example was 1kg of 1-methyl-1, 2-diethylcyclopropane (initial water content 230ppm), and the dehydration was carried out using the dehydration system for a cyclopropane-based aerospace fuel shown in fig. 1, and the dehydration step included:
1) conveying the fuel at the speed of 20mL/min by using a feed pump, pre-cooling the fuel to 10 ℃ by using a pre-cooler 1, conveying the fuel into a 2L low-temperature dehydration tank 2, controlling the temperature of a cooling medium in a tank body jacket of the low-temperature dehydration tank 2 to be 2 ℃, keeping the temperature of fuel liquid in a tank body of the low-temperature dehydration tank 2 to be 4-5 ℃, and keeping the residence time of the fuel liquid to be 1 h;
2) then the fuel was delivered into the preheater 3 at a rate of 20mL/min using a feed pump, heated to 50 ℃, and then the feed pump delivered the fuel to the heater 4 at the same rate, the fuel being heated to 85 ℃;
3) the heated fuel liquid enters a first chamber of a negative pressure permeable membrane assembly shell 5, the pressure difference between two sides of a permeable membrane 6 is controlled to be 38kPa, the residence time of the fuel liquid in the shell 5 is 30min, and then the fuel liquid flows into a first product tank 7 at the flow rate of 20mL/min through a pump;
the preparation method of the permeable membrane 6 comprises the following steps: mixing polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water according to a mass ratio of 100: 5: 150: preparing a mixed solution according to the proportion of 1000; scraping the mixed solution into a film structure with the thickness of 0.5mm at 40 ℃; standing the membrane structure at normal temperature for 48 hours to volatilize the solvent, and compacting after the solvent is volatilized to form the permeable membrane;
4) the fuel liquid in the first product tank 7 is continuously conveyed into the first chamber of the negative pressure permeable membrane assembly shell 5 at the flow rate of 20mL/min for secondary osmotic dehydration, the pressure difference between two sides of the permeable membrane 6 is controlled to be 38kPa, and the residence time of the fuel liquid in the shell 5 is controlled to be 30 min;
5) and (3) cooling the fuel liquid subjected to secondary osmotic dehydration to 23 ℃, and conveying the fuel liquid into a second product tank 8 to obtain a final dehydrated product.
In this example, the final dehydrated product obtained weighed 0.95kg, had a water content of 93ppm and a loss rate of 5%.
Example 3
The fuel in this example was 1kg of 1-methyl-1, 2-diethylcyclopropane (initial water content 210ppm), and the dehydration was carried out using the dehydration system for a cyclopropane-based aerospace fuel shown in fig. 1, and the dehydration step included:
1) conveying the fuel at the speed of 20mL/min by using a feed pump, pre-cooling the fuel to 7 ℃ by using a pre-cooler 1, conveying the fuel into a 2L low-temperature dehydration tank 2, controlling the temperature of a cooling medium in a tank body jacket of the low-temperature dehydration tank 2 to be 2 ℃, keeping the temperature of fuel liquid in a tank body of the low-temperature dehydration tank 2 to be 5 ℃, and keeping the residence time of the fuel liquid to be 1 h;
2) then the fuel is delivered into the preheater 3 at a rate of 20mL/min by means of a feed pump, heated to 60 ℃, and then delivered to the heater 4 at the same rate by the feed pump, the fuel being heated to 90 ℃;
3) the heated fuel liquid enters a first chamber of a negative pressure permeable membrane assembly shell 5, the pressure difference between two sides of a permeable membrane 6 is controlled to be 40kPa, the residence time of the fuel liquid in the shell 5 is 30min, and then the fuel liquid flows into a first product tank 7 at the flow rate of 20mL/min through a pump;
the preparation method of the permeable membrane 6 comprises the following steps: mixing polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water according to a mass ratio of 100: 5: 150: preparing a mixed solution according to the proportion of 1000; scraping the mixed solution into a film structure with the thickness of 0.5mm at 40 ℃; standing the membrane structure at normal temperature for 48 hours to volatilize the solvent, and compacting after the solvent is volatilized to form the permeable membrane;
4) the fuel liquid in the first product tank 7 is continuously conveyed into the first chamber of the negative pressure permeable membrane assembly shell 5 at the flow rate of 20mL/min for secondary osmotic dehydration, the pressure difference between two sides of the permeable membrane 6 is controlled to be 40kPa, and the residence time of the fuel liquid in the shell 5 is controlled to be 30 min;
5) and (3) cooling the fuel liquid subjected to the secondary osmotic dehydration to 30 ℃, and conveying the fuel liquid into a second product tank 8 to obtain a final dehydrated product.
In this example, the final dehydrated product obtained weighed 0.94kg, had a water content of 88ppm and a loss of 6%.
Example 4
The fuel in this example was 1kg of 1-methyl-1, 2-diethylcyclopropane (initial water content 210ppm), and the dehydration was carried out using the dehydration system for a cyclopropane-based aerospace fuel shown in fig. 1, and the dehydration step included:
1) conveying the fuel at the speed of 20mL/min by using a feed pump, pre-cooling the fuel to 15 ℃ by using a pre-cooler 1, conveying the fuel into a 2L low-temperature dehydration tank 2, controlling the temperature of a cooling medium in a tank body jacket of the low-temperature dehydration tank 2 to be 7 ℃, keeping the temperature of fuel liquid in a tank body of the low-temperature dehydration tank 2 to be 10 ℃, and keeping the residence time of the fuel liquid to be 30 min;
2) the fuel was then delivered into the preheater 3 at a rate of 20mL/min using a feed pump, heated to 70 ℃, and then the feed pump delivered the fuel to the heater 4 at the same rate, the fuel being heated to 88 ℃;
3) the heated fuel liquid enters a first chamber of a negative pressure permeable membrane assembly shell 5, the pressure difference between two sides of a permeable membrane 6 is controlled to be 35kPa, the residence time of the fuel liquid in the shell 5 is 40min, and then the fuel liquid flows into a first product tank 7 at the flow rate of 20mL/min through a pump;
the preparation method of the permeable membrane 6 comprises the following steps: polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water are mixed according to the mass ratio of 100: 15: 175: 1200, preparing a mixed solution; scraping the mixed solution into a film structure with the thickness of 0.5mm at 40 ℃; standing the membrane structure at normal temperature for 48 hours to volatilize the solvent, and compacting after the solvent is volatilized to form the permeable membrane;
4) the fuel liquid in the first product tank 7 is continuously conveyed into the first chamber of the negative pressure permeable membrane component shell 5 at the flow rate of 20mL/min for secondary osmotic dehydration, the pressure difference between two sides of the permeable membrane 6 is controlled to be 35kPa, and the retention time of the fuel liquid in the shell 5 is controlled to be 40 min;
5) and (3) cooling the fuel liquid subjected to secondary osmotic dehydration to 20 ℃, and conveying the fuel liquid into a second product tank 8 to obtain a final dehydrated product.
In this example, the final dehydrated product obtained weighed 0.95kg, had a water content of 60ppm, and had a loss rate of 5%.
Example 5
The fuel in this example was 1kg by weight of 1-methyl-1, 2-diethylcyclopropane (initial water content 210ppm), and the dehydration was carried out using the dehydration system for a cyclopropane-based aerospace fuel shown in fig. 1, and the dehydration step included:
1) conveying the fuel at the speed of 20mL/min by using a feed pump, pre-cooling the fuel to 8 ℃ by using a pre-cooler 1, conveying the fuel into a 2L low-temperature dehydration tank 2, controlling the temperature of a cooling medium in a tank body jacket of the low-temperature dehydration tank 2 to be 4 ℃, keeping the temperature of fuel liquid in a tank body of the low-temperature dehydration tank 2 to be 7 ℃, and keeping the residence time of the fuel liquid to be 20 min;
2) the fuel was then delivered into the preheater 3 at a rate of 20mL/min using a feed pump, heated to 65 ℃, and then the feed pump delivered the fuel to the heater 4 at the same rate, the fuel being heated to 87 ℃;
3) the heated fuel liquid enters a first chamber of a negative pressure permeable membrane assembly shell 5, the pressure difference between two sides of a permeable membrane 6 is controlled to be 28kPa, the residence time of the fuel liquid in the shell 5 is 20min, and then the fuel liquid flows into a first product tank 7 at the flow rate of 20mL/min through a pump;
the preparation method of the permeable membrane 6 comprises the following steps: mixing polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water according to a mass ratio of 100: 20: 200: 1300 to prepare a mixed solution; scraping the mixed solution into a film structure with the thickness of 0.5mm at 45 ℃; standing the membrane structure at normal temperature for 48 hours to volatilize the solvent, and compacting after the solvent is volatilized to form the permeable membrane;
4) the fuel liquid in the first product tank 7 is continuously conveyed into the first chamber of the negative pressure permeable membrane assembly shell 5 at the flow rate of 20mL/min for secondary osmotic dehydration, the pressure difference between two sides of the permeable membrane 6 is controlled to be 28kPa, and the residence time of the fuel liquid in the shell 5 is controlled to be 20 min;
5) and (3) cooling the fuel liquid subjected to the secondary osmotic dehydration to 22 ℃, and conveying the fuel liquid into a second product tank 8 to obtain a final dehydrated product.
In this example, the final dehydrated product obtained weighed 0.95kg, had a water content of 45ppm and a loss of 5%.
Example 6
The permeable membrane is compounded by polyvinyl alcohol and polyvinylidene fluoride, and the step of compounding the polyvinyl alcohol and the polyvinylidene fluoride to prepare the permeable membrane comprises the following steps:
31) polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water are mixed according to the mass ratio of 100: 5: 150: preparing a mixed solution according to the proportion of 1000;
32) scraping the mixed solution into a film structure with the thickness of 0.5mm at 40 ℃;
33) and standing the membrane structure at normal temperature for 48 hours to volatilize the solvent, and compacting after the solvent is volatilized to form the permeable membrane.
Example 7
The permeable membrane is compounded by polyvinyl alcohol and polyvinylidene fluoride, and the step of compounding the polyvinyl alcohol and the polyvinylidene fluoride to prepare the permeable membrane comprises the following steps:
31) mixing polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water according to a mass ratio of 100: 5: 150: 1000 to prepare a mixed solution;
32) scraping the mixed solution into a film structure with the thickness of 0.5mm at 40 ℃;
33) and standing the membrane structure at normal temperature for 48 hours to volatilize the solvent, and compacting after the solvent is volatilized to form the permeable membrane.
Example 8
The permeable membrane is compounded by polyvinyl alcohol and polyvinylidene fluoride, and the step of compounding the polyvinyl alcohol and the polyvinylidene fluoride to prepare the permeable membrane comprises the following steps:
31) mixing polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water according to a mass ratio of 100: 20: 200: 1300 to prepare a mixed solution;
32) scraping the mixed solution into a film structure with the thickness of 1.3mm at 50 ℃;
33) and standing the membrane structure at normal temperature for 48 hours to volatilize the solvent, and compacting after the solvent is volatilized to form the permeable membrane.
Example 9
The permeable membrane is compounded by polyvinyl alcohol and polyvinylidene fluoride, and the step of compounding the polyvinyl alcohol and the polyvinylidene fluoride to prepare the permeable membrane comprises the following steps:
31) mixing polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water according to a mass ratio of 100: 15: 175: 1200, preparing a mixed solution;
32) scraping the mixed solution into a film structure with the thickness of 1mm at 45 ℃;
33) and standing the membrane structure at normal temperature for 48 hours to volatilize the solvent, and compacting after the solvent is volatilized to form the permeable membrane.
Comparative example 1
This comparative example, using 1-methyl-1, 2-diethylcyclopropane (initial water content 230ppm), specifically includes the following dehydration step:
1) weighing 200g of 1-methyl-1, 2-diethylcyclopropane, adding the weighed 1-methyl-1, 2-diethylcyclopropane into a 500mL flask, adding 20g of a water absorbent (anhydrous magnesium sulfate) into the flask at room temperature, and stirring the water absorbent at a stirring speed of 200 rpm;
2) stirring for 5 hr, standing for 50min, filtering to remove lower solid phase, collecting upper liquid layer (178 g), and drying to obtain dehydrated 1-methyl-1, 2-diethyl cyclopropane.
Comparative example 2
This comparative example, which used 1-methyl-1, 2-dicyclopropyl cyclopropane (initial water content 210ppm), specifically included the following dehydration step:
1) weighing 200g of 1-methyl-1, 2-dicyclopropyl cyclopropane, adding the 1-methyl-1, 2-dicyclopropyl cyclopropane into a 500mL flask, and conveying the 1-methyl-1, 2-dicyclopropyl cyclopropane into a coalescence filter with a pore size of 3 microns at a flow rate of 20mL/min by using a raw material pump under the condition of room temperature;
2) the filtered 1-methyl-1, 2-dicyclopropyl cyclopropane is collected, 169g in total, and dried to obtain dehydrated 1-methyl-1, 2-diethyl cyclopropane.
Test example 1:
the experimental examples differ from example 3 in that: the test example only used step 1) of example 3 for dehydration.
Test example 2:
the experimental examples differ from example 3 in that: the present test example only used step 2) and step 3) of example 3 for dehydration.
Test example 3:
the experimental examples differ from example 3 only in that: the step 1) does not include a pre-cooling step.
Test example 4:
the experimental examples differ from example 3 only in that: in the step 1), the temperature of the fuel liquid in the tank body of the low-temperature dehydration tank 2 is kept at 2 ℃.
Test example 5:
the experimental examples differ from example 3 only in that: in the step 1), the temperature of the fuel liquid in the tank body of the low-temperature dehydration tank 2 is kept at 15 ℃.
Test example 6:
the experimental examples differ from example 3 only in that: the step of preheating is not included in the step 2).
Test example 7:
the experimental examples differ from example 3 only in that: in step 2) the heater 4 heats the fuel to 70 ℃.
Test example 8:
the experimental examples differ from example 3 only in that: in step 2) the heater 4 heats the fuel to 100 ℃.
Test example 9:
the experimental examples differ from example 3 only in that: the pressure difference across the permeable membrane 6 in step 3) was 10 kPa.
Test example 10:
the experimental examples differ from example 3 only in that: the pressure difference across the permeable membrane 6 in step 3) was 60 kPa. Test example 11:
the experimental examples differ from example 3 only in that: the pressure difference across the permeable membrane 6 in step 2) was 35 kPa. Test example 12:
the experimental examples differ from example 3 only in that: the pressure difference across the permeable membrane 6 in step 2) was 28 kPa.
Test example 13:
the experimental examples differ from example 3 only in that: the permeable membrane in step 3) is a Nafion permeable membrane.
Test example 14:
the experimental examples differ from example 3 only in that: the structural formula of the cyclopropane-based aerospace fuel is shown as the following formula I:
R 1 is methyl.
Test example 15:
the experimental examples differ from example 3 only in that: the structural formula of the cyclopropane aerospace fuel is shown as the following formula I:
R 1 is a cyclopropane group.
The water content and loss rate of the target products obtained in examples 2 to 5, comparative example 1, comparative example 2 and test examples 1 to 15 were measured. Wherein the content of the first and second substances,
the detection method of the water content comprises the following steps: detection was performed according to the SH/T0246 standard.
The loss rate detection method comprises the following steps: the weight of the final dehydrated product was taken and the loss rate was [1- (weight of dehydrated product/weight of product before dehydration) ]. 100%. The results are shown in table 1 below:
table 1:
from table 1 above, it can be seen that:
comparing example 2 with comparative example 1, it can be seen that: compared with the scheme of dehydrating by a dehydrating agent, the dehydration method is adopted for dehydration, so that the water content in the cyclopropane-based space fuel is obviously reduced, namely, the dehydration method is adopted for dehydrating the cyclopropane-based space fuel by combining a low-temperature dehydration process and a high-temperature negative pressure membrane permeation process, the dehydration efficiency is high, no water absorbent is needed, no solid waste is generated, and continuous operation can be realized.
The dewatering method employed in comparative example 2 was coalescence filtration dewatering. The coalescence filtering water removal mainly utilizes the difference of water-oil surface tension, when the fuel oil flows into the coalescence separator, the fuel oil firstly flows through the coalescence filter element, and the coalescence filter element coalesces tiny water drops into larger water drops. Most of the water drops after coalescence can be separated and removed from the oil by self-weight, then the oil product flows through the separation filter element, and the separation filter element has good oleophylic and hydrophobic properties, so that the water content is further separated. But the coalescing filtration method is not suitable for the removal of the dissolved water in the fuel.
Comparing example 3 with comparative example 2, it can be seen that: compared with the scheme of dewatering in a coalescence filtering mode, the dewatering method is adopted for dewatering, so that the water content in the cyclopropane-based aerospace fuel is obviously reduced, namely the method combining the low-temperature dewatering process and the high-temperature negative pressure membrane permeation process is adopted for dewatering the cyclopropane-based aerospace fuel, the dewatering efficiency is high, any water absorbent is not needed, solid waste is not generated, and continuous operation can be realized.
Comparing example 3 with test example 1, it can be seen that: the cyclopropane-based aerospace fuel is dehydrated only by a low-temperature dehydration process, so that the dissolved water in the cyclopropane-based aerospace fuel cannot be effectively removed, and the dehydration effect is poor because a large amount of water is still dissolved in the fuel under the action of polarity; and the low-temperature dehydration process and the high-temperature negative pressure membrane permeation process are combined, so that the dehydration efficiency of the fuel is higher, and the water content of the fuel is lower.
Comparing example 3 with test example 2, it can be seen that: because the solubility of the dissolved water in the cyclopropane aerospace fuel liquid is relatively high, the cyclopropane aerospace fuel is dehydrated only by a high-temperature negative-pressure membrane permeation process, the solubility of the dissolved water cannot be reduced, the dehydration effect is poor, and a large amount of water is difficult to remove thoroughly; and the low-temperature dehydration process and the high-temperature negative pressure membrane permeation process are combined, so that the dehydration efficiency of the fuel is higher, and the water content of the fuel is lower.
Comparing example 3 with test example 3, it can be seen that: the precooling step can effectively assist in reducing the solubility of the dissolved water in the cyclopropane-based space fuel liquid, and the precooling and subsequent low-temperature dehydration in the precooling step are favorable for improving the dehydration effect on the cyclopropane-based space fuel.
Comparing example 3 with test examples 4 to 5, it can be seen that: the low-temperature dehydration temperature is too low or too high, which is not favorable for removing the dissolved water in the cyclopropane aerospace fuel, and the solubility of water is larger at the too high temperature, which is not favorable for separating out the water in the fuel; at the excessively low temperature, the energy consumption can be further improved, the subsequent high-temperature membrane permeation dehydration link is influenced, and the loss rate of the fuel is increased. Only when the temperature of low-temperature dehydration is kept between 4 ℃ and 10 ℃, the solubility of the water dissolved in the cyclopropane-based aerospace fuel liquid can be fully reduced, so that the water dissolved in the fuel can be effectively removed, and the over-high loss rate of the fuel can not be caused.
Comparing example 3 with test example 6, it can be seen that: the preheating step can effectively assist in heating the cyclopropane aerospace fuel, so that the subsequent high-temperature treatment effect on the fuel is better, water in the fuel after high-temperature treatment is favorably gasified into steam under the negative pressure condition, the water in the fuel is further removed, and the loss rate of the fuel is favorably reduced.
Comparing example 3 with test examples 7 and 8, it can be seen that: the too low or too high temperature of the high-temperature dehydration is not favorable for removing the dissolved water in the cyclopropane aerospace fuel; when the temperature is too high, fuel molecules can enter the other side of the permeable membrane, so that the fuel loss rate is too high; when the temperature is too low, the water cannot be fully gasified and permeated, and the dehydration effect is poor. Only when the temperature of high-temperature dehydration is kept between 85 ℃ and 90 ℃, the dissolved water in the cyclopropane aerospace fuel liquid can be fully heated, the water in the cyclopropane aerospace fuel after high-temperature treatment is vaporized into steam under the negative pressure condition, the steam is cooled and condensed into liquid water, the liquid water is separated from the cyclopropane aerospace fuel and then the dissolved water in the fuel is effectively removed, and fuel molecules cannot enter the other side of the permeable membrane, so that the lower loss rate of the fuel is ensured.
Comparing example 3 with test examples 9 to 12, it can be seen that: the excessive high and low pressure difference at the two sides of the permeable membrane is not beneficial to separating out the water vapor, and the excessive high osmotic pressure is easy to bring fuel molecules into the other side of the permeable membrane, so that the loss rate of the fuel is too high; when the osmotic pressure is too low, the water cannot be fully permeated and gasified, and the dehydration effect is poor. The water content in the fuel can be effectively reduced only when the pressure difference is in the range of 28-40kpa, and the loss rate of the fuel is low.
Comparing example 3 with test example 13, it can be seen that: the permeable membrane is compounded by polyvinyl alcohol and polyvinylidene fluoride, and the hydroxyl active groups are used as the permeable groups, so that water molecules can be effectively adsorbed and permeated. The content of hydroxyl active groups in the polyvinyl alcohol is high, the adsorption and permeation effects on water molecules are good, and the efficiency is high; in addition, the permeable membrane has the function of resisting the hydrophilic wetting of the organic solvent, has higher toughness, can effectively prevent the permeation of fuel molecules, and can effectively reduce the loss rate of the fuel. In addition, the polyvinyl alcohol and the polyvinylidene fluoride can not be dissolved in the cyclopropane aerospace fuel, so that the high purity of the cyclopropane aerospace fuel is ensured, and the pollution of the osmotic membrane to the cyclopropane aerospace fuel is avoided.
And other commercially available permeable membranes such as: the Nafion permeable membrane adopts sulfo permeable groups, has weaker adsorption capacity on moisture than hydroxyl, has poorer separation and dehydration effects, and can not effectively prevent the permeation of fuel molecules, so that the fuel loss rate is higher; in addition, the Nafion permeable membrane can be partially dissolved in the cyclopropane aerospace fuel, so that the fuel is polluted.
Although the present invention has been described with reference to a preferred embodiment, it should be understood that various changes, substitutions and alterations can be made herein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. A dehydration method of cyclopropane aerospace fuel is characterized in that: the method comprises the following steps:
1) dehydrating the cyclopropanyl aerospace fuel at low temperature within the temperature range of 4-15 ℃;
2) carrying out high-temperature treatment on the low-temperature dehydrated cyclopropane-based aerospace fuel at the temperature of 50-90 ℃;
3) and (3) carrying out osmotic dehydration on the high-temperature treated cyclopropane-based space fuel by adopting a negative pressure permeable membrane to obtain the dehydrated cyclopropane-based space fuel.
2. The method for dehydrating a cyclopropane-based aerospace fuel according to claim 1, wherein step 1) comprises: precooling the cyclopropane-based space fuel to 7-15 ℃, and then dehydrating the precooled cyclopropane-based space fuel at a low temperature in a temperature range of 4-10 ℃;
preferably, the dehydration is carried out at a low temperature within the temperature range of 4-10 ℃ for 30min-1 h.
3. A method for dehydrating a cyclopropane-based aerospace fuel according to claim 1 or 2, wherein step 2) comprises: firstly, preheating the cyclopropanyl aerospace fuel dehydrated at low temperature to 50-70 ℃, and then carrying out high-temperature treatment on the preheated cyclopropanyl aerospace fuel at the temperature of 85-90 ℃.
4. A process for the dehydration of cyclopropane-based aerospace fuel according to any of claims 1-3, wherein the pressure differential across the membrane in step 3) is from 28 to 40 kpa;
preferably, the pressure difference is 35-40 kpa;
preferably, the time length of osmotic dehydration in the step 3) is 20-40 min;
preferably, the permeable membrane in the step 3) is formed by compounding polyvinyl alcohol and polyvinylidene fluoride;
preferably, in the step 3), at least two times of osmotic dehydration of the negative pressure permeable membrane are carried out.
5. The method for dehydrating a cyclopropane-based aerospace fuel according to any of claims 1-4, further comprising, after step 3): step 4), cooling and condensing the water vapor generated in the osmotic dehydration process;
preferably, in the step 4), the temperature is reduced to a temperature range of 20-30 ℃.
6. The permeable membrane is characterized by being formed by compounding polyvinyl alcohol and polyvinylidene fluoride.
7. The permeable membrane according to claim 6, wherein the step of preparing the permeable membrane by compounding the polyvinyl alcohol and the polyvinylidene fluoride comprises:
31) mixing polyvinyl alcohol, polyvinylidene fluoride, dimethylformamide and water according to a mass ratio of 100: 5-20: 150-200: preparing a mixed solution according to the proportion of 1000-1300;
32) scraping the mixed solution into a film structure;
33) standing and compacting the membrane structure to form the permeable membrane;
preferably, in the step 32), the film structure is scraped at the temperature of 40-50 ℃, and the thickness of the film structure is 0.5-1.3 mm;
preferably, in the step 33), the permeable membrane is formed by standing at normal temperature until the solvent is volatilized and compacting; preferably, the mixture is kept still for 48 hours.
8. Use of a permeable membrane according to claim 6 or 7 in a process for the dehydration of a cyclopropane-based aerospace fuel;
preferably, the permeable membrane is used in a process for the dehydration of a cyclopropane-based aerospace fuel as claimed in any of claims 1-5.
9. A cyclopropane-based aerospace fuel, comprising: dehydrating by the dehydration method according to any one of the above claims 1 to 5, wherein the water content is not higher than 100 ppm;
preferably, the structural formula of the cyclopropane-based aerospace fuel is shown as the following formula I:
wherein R is 1 Selected from methyl, ethyl, cyclopropyl.
10. A dehydration system for a cyclopropane-based aerospace fuel, which is characterized in that: controlled by the dewatering method of any one of claims 1 to 5;
preferably, the dewatering system comprises:
the low-temperature dehydration device is used for dehydrating the cyclopropane-based space fuel at low temperature;
the high-temperature treatment device is communicated with the low-temperature dehydration device and is used for carrying out high-temperature treatment on the cyclopropane-based aerospace fuel dehydrated by the low-temperature dehydration device at low temperature;
the negative pressure permeation membrane assembly is communicated with the high-temperature treatment device and is used for performing permeation dehydration on the cyclopropane-based space fuel subjected to high-temperature treatment;
preferably, the device also comprises a cooling device which is communicated with the negative pressure osmotic membrane component and is used for cooling and condensing water vapor generated in the osmotic dehydration process;
preferably, the negative pressure permeable membrane module comprises:
a housing having a cavity therein;
the permeable membrane is arranged in the shell and divides the cavity into a first cavity and a second cavity, the first cavity is communicated with the high-temperature treatment device and used for containing the cyclopropane aerospace fuel, and the cooling device is communicated with the second cavity and used for cooling water vapor in the second cavity;
preferably, the dehydration system at least comprises two groups of the negative pressure permeable membrane modules.
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