CN115595183A - Sustainable aviation fuel-based nanofluid fuel and implementation method thereof - Google Patents
Sustainable aviation fuel-based nanofluid fuel and implementation method thereof Download PDFInfo
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- CN115595183A CN115595183A CN202211245083.1A CN202211245083A CN115595183A CN 115595183 A CN115595183 A CN 115595183A CN 202211245083 A CN202211245083 A CN 202211245083A CN 115595183 A CN115595183 A CN 115595183A
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Abstract
A sustainable aviation fuel-based nano fluid fuel and a realization method thereof are characterized in that matrix fuel and carbon-based high-energy nano particles used as combustion enhancers are mixed according to a proportion and then are uniformly dispersed under magnetic stirring and ultrasonic dispersion, and diversified hydrogen bond acceptor elements are introduced into a nano structure, so that the hydrogen bond stabilizing effect of the nano particles in a fuel system is enhanced. The invention adopts a new inorganic carbon synthesis method, starts from an inorganic nano structure, introduces diversified hydrogen bond acceptor elements such as N, O, S and the like into the nano structure, strengthens the hydrogen bond stabilizing effect of nano particles in a fuel system by a bionic hydrogen bond strategy, and realizes the stable dispersion of the sustainable aviation fuel-based nano fluid fuel for a super long time.
Description
Technical Field
The invention relates to a technology in the field of aviation fuel, in particular to a sustainable aviation fuel-based nano fluid fuel capable of keeping stable dispersion for more than 90 days and an implementation method thereof.
Background
When biomass alternative fuel is mixed in the existing aviation kerosene, the combustion heat value of the existing aviation kerosene is greatly reduced (the heat value of the biomass alternative fuel is about 26.0MJ/kg, and the heat value of pure kerosene is about 45.0 MJ/kg), and the flying distance is obviously shortened. In order to improve the sustainability of Sustainable Aviation Fuel (SAF) and the volumetric energy density of liquid fuel, high Energy Density Material (HEDM) is mixed into liquid hydrocarbon fuel to form high energy nanofluid fuel, but because the density of the HEDM is much higher than that of the liquid hydrocarbon fuel, when the HEDM is added into the liquid fuel, precipitation and aggregation phenomena occur. Therefore, the biggest challenge in adding HEDM to liquid fuels is how to ensure the stability of the suspension.
Disclosure of Invention
The invention provides a sustainable aviation fuel-based nano fluid fuel and a realization method thereof aiming at the defect that the long-term stable dispersion of the nano fluid fuel cannot be effectively realized in the prior art, a novel inorganic carbon synthesis method is adopted, diversified hydrogen bond acceptor elements such as N, O, S and the like are introduced into a nano structure from an inorganic nano structure, the hydrogen bond stabilizing effect of nano particles in a fuel system is enhanced through a bionic hydrogen bond strategy, and the stable dispersion of the sustainable aviation fuel-based nano fluid fuel for a super long time is realized.
The invention is realized by the following technical scheme:
the invention relates to a method for realizing sustainable aviation fuel-based nano fluid fuel, which is characterized in that matrix fuel and carbon-based high-energy nano particles used as combustion enhancers are mixed in proportion and then are uniformly dispersed under magnetic stirring and ultrasonic dispersion, and diversified hydrogen bond acceptor elements are introduced into a nano structure, so that the hydrogen bond stabilizing effect of the nano particles in a fuel system is enhanced.
The carbon-based high-energy nano particles are preferably carbonized polyphosphazene, and the carbonization temperature is more preferably 500-900 ℃.
The mass ratio of the carbonized polyphosphazene to the matrix mixed fuel is 0.1-0.5%.
The matrix blended fuel preferably consists of RP-3 kerosene and ethanol, and more preferably the proportion of the RP-3 kerosene to the ethanol is 1:1.
The magnetic stirring is preferably carried out for 30min under the setting of 1600 r/min.
The ultrasonic dispersion is preferably carried out for 2h at the setting of 192W and 50 ℃.
The invention relates to a nano fluid fuel prepared by the method, which consists of matrix mixed fuel and carbonized polyphosphazene, wherein: the mass ratio E50/K50 of RP-3 kerosene and ethanol in the matrix mixed fuel is 50:50, the carbonization temperature CPZS of the Carbonized Polyphosphazene (CPZS) is respectively 500 ℃,700 ℃ and 900 ℃; the mass proportion of the carbonized polyphosphazene in the matrix mixed fuel is 0.1-0.5%.
Drawings
FIG. 1 is a graph of the micro-topography of CPZS at different carbonization temperatures;
FIG. 2 is a graph of the probability of ignition, the ignition temperature, and the ignition delay time for E50/K50 (a and b) and 0.1% -0.5% CPZS-700/(E50/K50) fuels (including 0.5% CPZS-500 and 0.5% CPZS-900) (c and d);
FIG. 3 is a graph of E50/K50 and 0.5% CPZS-700/(E50/K50) evaporation at 785 ℃;
FIG. 4 is a graph of the dispersion sedimentation of a nanofluid fuel suspension as a function of time, 0.1% -0.5% CPZS-700/(E50/K50).
Detailed Description
Example 1
The present embodiment configures the nanofluid fuel in the following proportions:
step one, adding E50/K50 with the mass of 1g into a beaker;
step two, adding CPZS-500 into the beaker, wherein the mass percentage content is 0.5%;
step three, uniformly dispersing the nano fluid fuel by magnetic stirring for 30min (1600 r/min) and ultrasonic dispersion for 2 hours (192W, 50 ℃).
This example measured the ignition and combustion characteristics of 0.5% CPZS-500/(E50/K50) nanofluid fuel, respectively, using a hanging drop ignition test apparatus and a high speed camera, listing the ignition and combustion events containing 0.5% CPZS-500/(E50/K50). Wherein the micro-morphology of the CPZS-500 at the carbonization temperature of 500 ℃ is shown in figure 1.
As shown in FIG. 2, the ignition probability of the E50/K50-based nanofluid fuel, added with 0.5% CPZS-500, according to the present example, as a function of the ambient temperature was tested to be substantially identical to 0.1% CPZS-700/(E50/K50), the ambient temperature to 100% probability of ignition is 825 deg.C; the ignition temperature was 391 ℃ (ambient temperature 900 ℃); 975 deg.C, ignition delay time 812ms.
Example 2
The present embodiment configures the nanofluid fuel in the following proportions:
step one, adding E50/K50 with the mass of 1g into a beaker;
step two, adding CPZS-700 into the beaker, wherein the mass percentage content is 0.1%;
step three, uniformly dispersing the nano fluid fuel by magnetic stirring for 30min (1600 r/min) and ultrasonic dispersion for 2 hours (192W, 50 ℃).
This example measured the ignition and combustion characteristics of 0.1% CPZS-700/(E50/K50) nanofluid fuel, respectively, using a suspended droplet ignition test apparatus and a high speed camera, listing the ignition and combustion conditions containing 0.1% CPZS-700/(E50/K50). Wherein the micro-morphology of the CPZS-700 at the carbonization temperature of 700 ℃ is shown in figure 1.
As shown in FIGS. 2 and 4, the ambient temperature of the present example, to achieve 100% probability of ignition, was tested to 825 deg.C, with the addition of 0.1% CPZS-700 of the E50/K50-based nanofluid fuel; the ignition temperature was 395 ℃ (ambient temperature 900 ℃); 975 ℃, ignition delay time 736ms; and no sedimentation occurred for 90 days.
Example 3
The nanofluid fuel was formulated in the present example in the following proportions:
step one, adding E50/K50 with the mass of 1g into a beaker;
step two, adding CPZS-700 into the beaker, wherein the mass percentage of the CPZS-700 is 0.2%;
step three, uniformly dispersing the nano fluid fuel by magnetic stirring for 30min (1600 r/min) and ultrasonic dispersion for 2 hours (192W, 50 ℃).
This example measured the ignition and combustion characteristics of 0.2% CPZS-700/(E50/K50) nanofluid fuel, respectively, using a hanging drop ignition test apparatus and a high speed camera. Ignition and combustion events containing 0.2% CPZS-700/(E50/K50) are enumerated.
As shown in FIGS. 2 and 4, the E50/K50-based nanofluid fuel, added with 0.2% CPZS-700, of the present example was tested to achieve an ambient temperature of 815 ℃ at 100% probability of ignition; the ignition temperature is 385 ℃ (ambient temperature 900 ℃); 975 ℃, ignition delay time 637ms; and no sedimentation occurred for 70 days.
Example 4
The present embodiment configures the nanofluid fuel in the following proportions:
step one, adding E50/K50 with the mass of 1g into a beaker;
step two, adding CPZS-700 into the beaker, wherein the mass percentage content is 0.3%;
step three, uniformly dispersing the nano fluid fuel by magnetic stirring for 30min (1600 r/min) and ultrasonic dispersion for 2 hours (192W, 50 ℃).
This example measured the ignition and combustion characteristics of 0.3% CPZS-700/(E50/K50) nanofluid fuel, respectively, using a hanging drop ignition test apparatus and a high speed camera. The ignition and combustion conditions containing 0.3% CPZS-700/(E50/K50) are enumerated.
As shown in FIGS. 2 and 4, the E50/K50-based nanofluid fuel, added with 0.3% CPZS-700, of the present example was tested to reach an ambient temperature of 810 ℃ at 100% probability of ignition; the ignition temperature is 383 ℃ (the ambient temperature is 900 ℃); 975 ℃, ignition delay time of 589ms; and no sedimentation occurred for 90 days.
Example 5
The nanofluid fuel was formulated in the present example in the following proportions:
step one, adding E50/K50 with the mass of 1g into a beaker;
step two, adding CPZS-700 into the beaker, wherein the mass percentage content is 0.4%;
step three, uniformly dispersing the nano fluid fuel by magnetic stirring for 30min (1600 r/min) and ultrasonic dispersion for 2 hours (192W, 50 ℃).
This example measured the ignition and combustion characteristics of 0.4% CPZS-700/(E50/K50) nanofluid fuel, respectively, using a hanging drop ignition test apparatus and a high speed camera. The ignition and combustion conditions containing 0.4% CPZS-700/(E50/K50) are enumerated.
As shown in FIGS. 2 and 4, the E50/K50-based nanofluid fuel, added with 0.4% CPZS-700, of the present example was tested to reach an ambient temperature of 795% probability of ignition; the ignition temperature was 375 ℃ (ambient temperature 900 ℃); 975 ℃, ignition delay time of 479ms; and no sedimentation occurred for 90 days.
Example 6
The present embodiment configures the nanofluid fuel in the following proportions:
step one, adding E50/K50 with the mass of 1g into a beaker;
step two, adding CPZS-700 into the beaker, wherein the mass percentage content is 0.5%;
step three, uniformly dispersing the nano fluid fuel by magnetic stirring for 30min (1600 r/min) and ultrasonic dispersion for 2 hours (192W, 50 ℃).
This example measured the ignition and combustion characteristics of 0.5% CPZS-700/(E50/K50) nanofluid fuel, respectively, using a hanging drop ignition test apparatus and a high speed camera. The ignition and combustion conditions containing 0.5% CPZS-700/(E50/K50) are enumerated.
As shown in FIGS. 2, 3 and 4, the ambient temperature of the present example tested to achieve 100% probability of ignition by adding 0.5% of the E50/K50-based nanofluid fuel CPZS-700; the ignition temperature is 360 ℃ (the ambient temperature is 900 ℃); at 975 ℃, the ignition delay time is 243ms;0.5% CPZS-700/(E50/K50) that micro-explosion phenomenon did not occur in the evaporation of nanofluid fuel; and no sedimentation occurred for 90 days.
Example 7
The present embodiment configures the nanofluid fuel in the following proportions:
step one, adding E50/K50 with the mass of 1g into a beaker;
step two, adding CPZS-900 into the beaker, wherein the mass percentage content is 0.5%;
step three, uniformly dispersing the nano fluid fuel by magnetic stirring for 30min (1600 r/min) and ultrasonic dispersion for 2 hours (192W, 50 ℃).
This example measured the ignition and combustion characteristics of 0.5% CPZS-900/(E50/K50) nanofluid fuel, respectively, using a hanging drop ignition test apparatus and a high speed camera, listing the ignition and combustion events containing 0.5% CPZS-900/(E50/K50). Wherein the micro-morphology of the CPZS-900 at the carbonization temperature of 900 ℃ is shown in figure 1.
As shown in FIG. 2, the test results show that the ambient temperature of the example, to which 0.5% CPZS-900 of the E50/K50-based nanofluid fuel was added, reached 100% probability of ignition, was 800 ℃; the ignition temperature is 375 ℃ (the ambient temperature is 900 ℃); 975 deg.C, ignition delay time 201ms.
Compared with the prior art, the method adopts a new inorganic carbon synthesis method, starts from an inorganic nano structure based on a bionic hydrogen bond strategy, introduces diversified hydrogen bond acceptor elements such as N, O, S and the like into the nano structure, and utilizes the high-energy sustainable aviation fuel-based nano fluid fuel formed by the carbonized polyphosphazene to keep long-term stable dispersion. The nano fluid fuel prepared by the method realizes stable dispersion for more than 90 days based on a bionic hydrogen bond strategy, and has remarkable enhancing effects on the evaporation, ignition and combustion performances of the fuel. The prepared nano fluid fuel has the advantages of stable physical form, no layering, good dispersion stability in a normal temperature environment and the like, and the preparation process has the characteristics of simplicity in operation, strong practicability and the like.
The foregoing embodiments may be modified in many different ways by one skilled in the art without departing from the spirit and scope of the invention, which is defined by the appended claims and not by the preceding embodiments, and all embodiments within their scope are intended to be limited by the scope of the invention.
Claims (7)
1. A method for realizing sustainable aviation fuel-based nano fluid fuel is characterized in that matrix fuel and carbon-based high-energy nano particles used as combustion enhancers are mixed in proportion and then are uniformly dispersed under magnetic stirring and ultrasonic dispersion, and diversified hydrogen bond acceptor elements are introduced into a nano structure, so that the hydrogen bond stabilizing effect of the nano particles in a fuel system is enhanced;
the carbon-based high-energy nano particles are carbonized polyphosphazenes.
2. A method for realizing sustainable aviation fuel-based nanofluid fuel as claimed in claim 1, wherein said carbonized polyphosphazene has a carbonization temperature of 500-900 ℃.
3. A method for realizing a sustainable aviation fuel-based nanofluid fuel according to claim 1, wherein the mass ratio of the carbonized polyphosphazene to the matrix blended fuel is 0.1% -0.5%.
4. A method for realizing sustainable aviation fuel-based nanofluid fuel according to claim 1, wherein the matrix blend fuel comprises RP-3 kerosene and ethanol.
5. A method for realizing sustainable aviation fuel-based nanofluid fuel according to claim 1, wherein the magnetic stirring is set at 1600 rpm for 30min.
6. A method for realization of sustainable aviation fuel-based nanofluid fuel according to claim 1, wherein said ultrasonic dispersion is 192W at 50 ℃ for 2h.
7. A nanofluid fuel prepared according to the method of any one of claims 1 to 6, consisting of a matrix mixed fuel and a carbonized polyphosphazene, wherein: the mass ratio E50/K50 of RP-3 kerosene to ethanol in the matrix mixed fuel is 50:50, the carbonization temperature CPZS of the Carbonized Polyphosphazene (CPZS) is respectively 500 ℃,700 ℃ and 900 ℃; the mass proportion of the carbonized polyphosphazene in the matrix mixed fuel is 0.1-0.5%.
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| CN106190344A (en) * | 2016-08-04 | 2016-12-07 | 浙江大学 | A kind of method preparing high energy composite carbon hydrogen fuel and fuel thereof |
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| JP2006216503A (en) * | 2005-02-07 | 2006-08-17 | Nissan Motor Co Ltd | Catalyst layer of solid polymer fuel cell |
| AU2006296396A1 (en) * | 2005-09-30 | 2007-04-05 | International Fuel Technology Inc. | Fuel compositions containing fuel additive |
| CN105621390A (en) * | 2015-12-31 | 2016-06-01 | 上海交通大学 | Preparation method of heteroatom-doped carbon hollow microspheres |
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| 李爱元;张慧波;陈亚东;王建中;储昭荣;: "聚磷腈在航空航天高分子材料中的应用", 化学推进剂与高分子材料, no. 06, pages 40 * |
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