High-stability jet aviation alcohol hydrogen fuel and preparation method thereof

Abstract

The present application relates to the technical field of aviation fuel, and discloses a high-stability jet aviation alcohol hydrogen fuel and a preparation method thereof, the fuel comprising bio aviation coal, a low-carbon alcohol mixture, adipate ester additives, nitromethane, carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonated diphenol)] nanoparticles and polyisobutylene amine. In the system, rigid nanoparticles and flexible polymer long chains construct a composite steric network at the oil-alcohol interface, which inhibits the thermodynamic coalescence and oswald ripening of microemulsion droplets. The preparation method pumps the pre-cooled alcohol phase into the constant-temperature oil phase, uses the temperature difference thermal stress to cooperate with the flow field high shear force to accelerate the crushing of droplets and the remodeling of the phase interface, and is supplemented by online light transmittance monitoring to determine the microemulsification steady state end point. The present application improves the phase state continuity of the fuel system in a wide temperature range environment, and meets the kinetic pumping requirements of the aviation engine under extremely cold conditions.

Description

Technical Field

[0001] This invention relates to the field of aviation fuel technology, specifically to a highly stable jet aviation alcohol-hydrogen fuel and its preparation method. Background Technology

[0002] With the development of the aviation industry and the increasing demand for energy conservation and emission reduction, blending low-carbon alcohols into traditional aviation kerosene to form alcohol-hydrogen blended fuels has become one of the directions for the research and development of alternative aviation fuels. The introduction of alcohol fuels can improve combustion emission characteristics, but because low-carbon alcohols have strong polarity, while the main component of aviation kerosene is non-polar alkanes, the two are intrinsically immiscible thermodynamically.

[0003] Existing preparation processes typically rely on adding conventional surfactants or cosolvents to construct microemulsion systems, attempting to disperse the alcohol phase as tiny droplets within a continuous oil matrix. However, this interfacial structure, maintained by traditional small chemical molecules, exhibits significant physical instability in the complex operating environment of aero-engines. When the fuel system undergoes drastic temperature changes over a wide range, especially sudden drops in ambient temperature or alterations in thermodynamic state, the low-carbon alcohol molecules within the microemulsion droplets experience forced volume expansion, easily overcoming the interfacial tension barrier constructed by the original surfactant. This leads to irreversible thermodynamic coalescence and Oswald ripening of the dispersed phase droplets within the continuous phase, subsequently causing macroscopic phase separation of the fuel. Simultaneously, due to phase recombination and free liquid precipitation under extremely cold conditions, the low-temperature kinematic viscosity of conventional microemulsion fuels often undergoes nonlinear abrupt changes, resulting in poor overall fluidity. This makes it difficult to meet the conventional pumping and fuel supply requirements of aero-engines in the negative temperature range, limiting the practical engineering application of alcohol-hydrogen fuels in aircraft. Summary of the Invention

[0004] To address the shortcomings of existing technologies, this invention provides a highly stable jet aviation alcohol-hydrogen fuel and its preparation method. It solves the problems that existing jet aviation fuels are prone to phase separation after being mixed with low-carbon alcohols, the kinematic viscosity at low temperatures is difficult to meet the operating requirements of aero engines, and the fuel system is prone to microemulsion droplet coalescence and maturation when the thermodynamic state changes, leading to a decrease in the stability of the fuel system.

[0005] To address the above problems, the present invention provides the following technical solution: In a first aspect, the present invention provides a highly stable jet aviation alcohol-hydrogen fuel, employing the following technical solution: A highly stable jet aviation alcohol-hydrogen fuel, made from raw materials comprising the following parts by weight: Bio-jet fuel, parts 42-59; 10-30 parts of lower alcohols; 2-4 parts isobutanol; 1-3 parts of isoamyl alcohol; 4-6 parts of di(2-ethylhexyl) adipic acid; 3-5 parts of diisobutyl adipic acid; 5-10 parts of nitromethane; 2-8 parts of nitropropane; 0.5–1 part of carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles; 0.2 to 1 part of polyisobutylene amine; The lower alcohol is methanol, ethanol, or a mixture of both in any proportion.

[0006] By adopting the above technical solution, the phase interface structure within the fuel system is altered through a multi-component composite approach, thereby improving the thermodynamic and kinetic stability of the alcohol-hydrogen mixed fuel. The specific microscopic interface stabilization process manifests as a continuous physicochemical interaction: after polyisobutylene amine enters the system, its polar amine terminals spontaneously adsorb towards the alcohol phase interface, while the non-polar polyisobutylene long chains extend in the non-polar continuous phase composed of straight-run aviation kerosene, thus forming a basic solvation buffer film at the oil-ethanol interface. Based on this, the present invention introduces nitromethane and nitrobenzene as solvent-grade high-calorific-value agents. The mixture of these two not only effectively increases the overall calorific value of the fuel, compensating for the calorific value reduction caused by the introduction of lower-carbon alcohols, but its mixture also provides excellent catalytic and solubilizing effects for the alcohol-hydrogen mixed fuel, promoting a clear and transparent system. Simultaneously, carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles migrate to the oil-water interface region via the nitromethane and nitrobenzene mixture as a medium. At this point, di(2-ethylhexyl) adipate and diisobutyl adipate act as solubilizers to reduce the overall interfacial tension of the system, allowing the nanoparticles to remain more uniformly within the interfacial layer. Subsequently, these rigid, non-planar nanoparticle clusters distributed at the interface intertwine with the previously extended polyisobutyleneamine chains. This process essentially constructs a composite three-dimensional steric network around the microemulsion droplets and generates corresponding electrostatic repulsion forces within the oil phase liquid layer. It is precisely due to this spatial network characteristic that the conventional diffusion paths of low-carbon alcohol molecules are effectively blocked when faced with drastic temperature changes leading to volume expansion. Therefore, even under strong environmental thermal shock conditions, the internal microemulsion droplet clusters can maintain the coherence of their overall conformation, thereby macroscopically suppressing the thermodynamic coalescence of droplets in the continuous phase and the Oswald ripening phenomenon.

[0007] Preferably, the highly stable jet fuel is made from the following raw materials in parts by weight: 50 parts biofuel, 15 parts methanol, 10 parts ethanol, 3 parts isobutanol, 2 parts isoamyl alcohol, 5 parts di(2-ethylhexyl) adipate, 4 parts diisobutyl adipate, 8 parts nitromethane, 4 parts nitrobenzene, 0.5 parts carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles, and 0.5 parts polyisobutyleneamine.

[0008] By adopting the above technical solution, a more preferred component ratio is defined. Under this specific ratio, the interfacial synergy between the substances in the system is relatively sufficient, and the stability of the phase structure in harsh environments such as low temperature is further solidified.

[0009] Preferably, the main chain structure of the bio-jet fuel is hydrogenated ester and fatty acid-synthesized aviation kerosene, with a carbon number distribution of C8 to C16, a straight-chain and branched-chain alkane mass fraction of 98wt% to 99.8wt%, and an aromatic hydrocarbon mass fraction of 0.01wt% to 0.5wt%; the effective amine value of the polyisobutylene amine is 45 to 60 mg KOH / g, the number average molecular weight is controlled between 1000 and 1050 g / mol, and the impurity moisture content is 0.01wt% to 0.05wt%.

[0010] By employing the above technical solution, the carbon number distribution of the base oil phase and the key physicochemical parameters of the surfactant were clarified. This parameter-level control helps maintain the solubility and spatial distribution of polyisobutylene amine in the bio-jet fuel matrix, thus providing a physical prerequisite for the formation of the initial solubilization buffer film.

[0011] Preferably, the carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles are prepared by carbonization after polymerization of hexachlorocyclotriphosphazene with a purity of 99wt% to 99.9wt% and 4,4'-sulfonyldiphenol with a purity of 99wt% to 99.9wt%; the acid values ​​of di(2-ethylhexyl) adipate and diisobutyl adipate are both 0.01 to 0.2 mg KOH / g.

[0012] By adopting the above technical solution, carbonized particles are prepared using high-purity precursor monomers, which helps maintain the consistency of surface charge distribution of the product; the use of low-acid-value ester auxiliaries reduces, to some extent, the side reaction interference that may occur in the system targeting the polar end of the interfacial active material.

[0013] Preferably, the fuel product has an average hydrodynamic diameter of 150–250 nm, an absolute value of 38–50 mV for the Zeta potential, and a polydispersity index of 0.10–0.16 when measured at an ambient temperature of 25°C; and the fuel product has a precise kinematic viscosity of 5.4–6.2 mm² / s in the -20°C reference range.

[0014] By adopting the above technical solution, the spatial scale and charge characteristic parameters of the microemulsion droplets were established. Controlling the particle size and Zeta potential within the above-mentioned range can endow the system with sufficient electrostatic repulsion between particles; while the reasonable limitation of the viscosity range directly corresponds to the fluid pumping requirements of aero-engines during the cryogenic start-up and operation phases.

[0015] Secondly, the present invention provides a method for preparing highly stable jet aviation alcohol-hydrogen fuel, employing the following technical solution: A method for preparing a highly stable jet aviation alcohol-hydrogen fuel includes the following steps: Step S1 Raw material weighing: Accurately weigh each component raw material according to the set weight ratio; Step S2: Preparation of oil phase carrier: Add bio-jet fuel, di(2-ethylhexyl) adipate, diisobutyl adipate and polyisobutyleneamine to a sealed reaction vessel with a jacket and temperature control, heat and stir continuously to form a uniform and transparent oil phase base liquid. Step S3 Nanophase Anchoring: The carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyl diphenol)] nanoparticles are completely immersed in a mixture of nitromethane and nitromethane, and ultrasonically dispersed under temperature control in a warm water bath to form a uniform dispersion. Then, the entire mixture is injected into the above oil phase base liquid, and the temperature is maintained and the mixture is stirred to make the nanoparticles uniformly suspended and anchored in the oil phase. Step S4: Alcohol Phase Mixing and Thermal Shock Microemulsification: Methanol, ethanol, isobutanol and isoamyl alcohol are mixed in a sealed tank to form an alcohol phase solution and pre-cooled; then the pre-cooled alcohol phase solution is pumped into the oil phase base liquid, which is kept at a constant temperature, at a constant flow rate. The two-phase fluids undergo high-shear dynamic microemulsification through a mixer under the action of temperature difference shock to generate a uniform alcohol-hydrogen microemulsion system. Step S5: Centrifugal purification and phase lock-in: The above microemulsion is continuously pumped into a centrifuge, and the centrifugal acceleration is set to separate and remove ineffective free aggregates and impurities. The clear liquid discharged is collected to obtain the finished product.

[0016] By employing the above-mentioned technical solution, this preparation method combines the pre-dispersion treatment of nanoparticles with the dynamic emulsification process of multiphase fluids. In particular, the introduction of an operational design involving pre-cooling of the alcohol phase and heating of the oil phase creates a significant thermal stress gradient between the two fluids upon contact. This localized thermal shock, combined with the mechanical shear force within the mixer, accelerates the breakup of the original coarse emulsion droplets. During this phase of fluid structure reshaping, the nanoparticles can migrate more rapidly to the newly formed oil-alcohol interface region and achieve fixation, thereby improving the overall emulsification efficiency and the storage period of the final product.

[0017] Preferably, in step S2, the reactor heating temperature is 35-45°C, the stirring speed is 400-600 rpm, and the stirring time is 20-40 minutes; in step S3, ultrasonic dispersion is carried out in a water bath at 20-30°C, the ultrasonic frequency is 40 kHz, and the time is 15-25 minutes; after the oil phase is injected, the temperature is maintained at 35-45°C and stirring continues for 10-20 minutes.

[0018] By adopting the above technical solution, the operating conditions for initial material processing have been refined. Controlling the heating temperature and ultrasonic conditions within the set range helps to break the original physical aggregation state of nanoparticles and prevents the escape of lightweight components from the system due to excessive heating, thus providing process support for the uniform pre-dispersion of nanophase materials.

[0019] Preferably, in step S4, the refrigeration unit is turned on to precool the alcohol phase solution to the range of -5°C to 5°C; then the precooled alcohol phase solution is pumped into the oil phase base liquid maintained at 35°C to 45°C at a stable flow rate of 8 to 15 L / h. Under the combined action of the temperature difference shock and the high shear of the pipeline Venturi static mixer, the coarse emulsion droplets are torn apart and crushed, triggering the thermodynamic reshaping of the phase fluid.

[0020] By adopting the above technical solution, the transport and temperature control parameters of the fluid mixing stage were clarified. Under these conditions, a momentary temperature difference will be maintained at the junction of the two-phase fluids. The resulting thermodynamic imbalance, combined with the flow field shear inside the static mixer, causes the nucleation rate of new droplets to significantly exceed their spontaneous merging and growth rate. This is beneficial for the final generation of a microemulsion system with small scale and relatively concentrated distribution.

[0021] Preferably, in step S5, the centrifuge is a tubular centrifuge; the centrifugal acceleration is set between 11000G and 12000G; and ineffective free agglomerates with a particle size between 0.4μm and 5.0μm are separated and removed.

[0022] By employing the above technical solution, the final physical phase screening is completed by applying a centrifugal force field. This operation mainly targets the large-sized free liquid phases in the system that are not fully emulsified or have already undergone early aggregation, thereby retaining the nanoscale microemulsions with better thermodynamic stability and reducing the probability of subsequent fuel stratification or impurity precipitation during long-term storage.

[0023] Preferably, the reaction endpoint control of the thermal shock microemulsification stage in step S4 is based on: establishing a bypass online monitoring reflux system, using a spectrophotometer to continuously record the time series of transmittance signals at a detection wavelength of 600nm; when the slope of the first derivative tangent of the transmittance curve fluctuates within the range of 0.01% to 0.1% for 2 consecutive minutes, it is determined that the dynamic microemulsification has reached a steady-state structure, at which point the steady-state transmittance integral mean of the initial microemulsion is controlled at 96.0% to 99.5%.

[0024] By adopting the above technical solution, an online quantitative monitoring mechanism for the endpoint of the dynamic microemulsion process was established. Considering that the evolution of the internal phase of the microemulsion directly corresponds to the change in its macroscopic light transmittance characteristics, by real-time acquisition of transmittance signals and calculation of the first derivative, it is possible to relatively intuitively determine whether the system network has reached a structural steady state. This control method reduces the reliance on conventional manual sampling or empirical evaluation, and facilitates ensuring the continuity of phase distribution characteristics among different batches of products.

[0025] This invention provides a highly stable jet aviation alcohol-hydrogen fuel and its preparation method. It has the following beneficial effects: 1. This invention introduces carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles and polyisobutyleneamine, and with the synergistic effect of nitromethane and ester cosolvents, constructs a composite steric hindrance network at the oil-ethanol interface of the fuel system. This physical interface layer, formed by the interweaving of rigid non-planar particles and flexible polymer chains, impedes the forced diffusion path of low-carbon alcohol molecules under external temperature changes, while simultaneously stimulating electrostatic repulsion between particles within the continuous phase. This structure, at the microscopic level, disrupts the kinetics of Oswald ripening and coalescence of microemulsion droplets, improving the phase stability of alcohol-hydrogen mixed fuels during long-term storage and over a wide temperature range.

[0026] 2. The preparation process of this invention combines fluid thermal shock with high-shear dynamic microemulsification. By directly pumping an alcohol phase solution pre-cooled to a specific low-temperature range into a heated and isothermal oil phase matrix, a significant instantaneous temperature gradient is created in the two-phase contact region. The locally generated thermodynamic stress and the mechanical shear force inside the pipeline mixer physically superimpose each other, accelerating the tearing and fragmentation of the initial coarse emulsion droplets and promoting the rapid migration and fixation of nanoparticles in the system to the newly formed interface layer. This non-equilibrium phase fluid thermodynamic reshaping makes the nucleation rate of droplets significantly exceed their growth rate, thereby ensuring the nanoscale dispersion of the prepared microemulsion system.

[0027] 3. This invention introduces nitromethane and nitromethane as solvent-grade high-calorific-value agents. The synergistic mixing of these two agents plays a crucial catalytic and solubilizing role in the process. On the one hand, the mixed high-calorific-value agents can effectively improve the bulk compatibility between low-carbon alcohols and aviation kerosene, resulting in an excellent clear and transparent state of the alcohol-hydrogen mixed fuel on a macroscopic scale. On the other hand, their own high calorific value effectively compensates for the decrease in the overall volumetric / mass calorific value of the fuel caused by the addition of alcohols, ensuring the engineering requirements of aircraft in terms of range and thrust output. Attached Figure Description

[0028] Figure 1 The figures show a comparison of particle distribution and surface electrical properties of aviation alcohol-hydrogen fuel products prepared in the embodiments and comparative examples of the present invention; wherein, (a) is a comparison of particle distribution characteristics of the system of the present invention; and (b) is a comparison of surface macroscopic potential distribution of the system of the present invention. Figure 2 The following are line graphs showing the evolution of dynamic tension at the liquid-liquid interface of the precursors in the embodiments and comparative examples of the present invention over time. Figure 3 This is a comparison chart of the dynamic equilibrium time and steady-state optical characteristics of microemulsion in the embodiments and comparative examples of the present invention; Figure 4 This is a comparison chart of the tolerance limit data of the embodiments and comparative examples of the present invention under severe unsteady stress conditions; Figure 5 The following is a comparison diagram of the low-temperature cold start rheological characteristics and atomization shear disintegration tendency of the aviation alcohol-hydrogen fuel system according to an embodiment of the present invention; wherein, (a) is a comparison diagram of the wide-range kinematic viscosity differentiation of the liquid phase of the system within the self-weight work field strength limit at -20℃; (b) is a characteristic diagram of the apparent viscosity drop slope of the test oil constructed by translation slope mapping during the process of slow flow transportation in the pipeline to high-frequency cavitation atomization spraying before entering the combustion chamber, which is the microstructure triggering resistance disintegration. Figure 6 The diagram shows a comparison of the combustion performance and dispersion stability of the blended fuels of the present invention; wherein, (a) is a comparison of combustion duration; and (b) is a comparison of dynamic stability index. Detailed Implementation

[0029] The main raw materials and reagents used in the following examples and comparative examples have the following sources and specifications. Reagents not specifically mentioned are all commercially available analytical grade or higher grade products.

[0030] Bio-jet fuel, with a main chain structure of hydrogenated esters and fatty acids synthesized into aviation kerosene, has a carbon number distribution of C8 to C16, a straight-chain and branched-chain alkane mass fraction greater than 98 wt%, and an aromatic hydrocarbon mass fraction less than 0.5 wt%, conforming to ASTM D7566 Annex 2 standard.

[0031] Di(2-ethylhexyl) adipic acid, CAS number 103-23-1, with controlled solid particles and free acid impurities, degree of esterification greater than 99.5 wt%, and acid value less than 0.2 mg KOH / g.

[0032] Diisobutyl adipic acid, CAS number 141-04-8, degree of esterification greater than 99wt%, acid value less than 0.2mgKOH / g.

[0033] Hexachlorocyclotriphosphazene, CAS No. 940-71-6, purity greater than 99 wt%.

[0034] 4,4'-Sulfodiphenol, CAS No. 80-09-1, purity greater than 99wt.

[0035] Polyisobutyleneamine is a commercially available fuel-grade high-purity amination polyisobutylene polymer with an effective amine value greater than 45 mg KOH / g, a number-average molecular weight Mn controlled between 1000 and 1050 g / mol, and an impurity moisture content of less than 0.05 wt%.

[0036] Nitromethane, analytical grade or solvent grade, purity greater than 99 wt%.

[0037] Nitropropane (usually 1-nitropropane or 2-nitropropane can be used), solvent-grade high calorific value agent, purity greater than 99 wt%.

[0038] Example 1: This embodiment provides a method for preparing highly stable jet aviation alcohol-hydrogen fuel, including the following steps: (1) Raw material weighing: Accurately weigh 50 parts by weight of bio-jet fuel, 15 parts by weight of methanol, 10 parts by weight of ethanol, 3 parts by weight of isobutanol, 2 parts by weight of isoamyl alcohol, 5 parts by weight of di(2-ethylhexyl) adipate, 4 parts by weight of diisobutyl adipate, 8 parts by weight of nitromethane, 4 parts by weight of nitromethane, 0.5 parts by weight of carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles and 0.5 parts by weight of polyisobutyleneamine.

[0039] (2) Preparation of oil phase carrier: Add bio-jet fuel, di(2-ethylhexyl) adipate, diisobutyl adipate and polyisobutyleneamine to a sealed reaction vessel with a jacket temperature control, heat to 40°C and stir continuously at 500 rpm for 30 minutes to form a uniform and transparent oil phase base liquid.

[0040] (3) Nanophase anchoring: Carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles are completely immersed in a mixed solvent composed of nitromethane and nitromethane. The nanoparticles are ultrasonically dispersed for 20 minutes under the conditions of temperature control in a warm water bath (not exceeding 30°C) and frequency of 40kHz to form a uniform dispersion. Then, the entire dispersion is injected into the above oil phase base liquid, and the temperature is maintained at 40°C while stirring for 15 minutes to make the nanoparticles uniformly suspended and anchored in the oil phase.

[0041] (4) Alcohol phase compounding and thermal shock microemulsion: Methanol, ethanol, isobutanol and isoamyl alcohol are mixed uniformly in an auxiliary tank to form an alcohol phase solution. The refrigeration unit is turned on to pre-cool the alcohol phase solution to 0°C. Then, the pre-cooled alcohol phase solution is pumped into the oil phase base liquid maintained at 40°C at a stable flow rate of 10L / h. The two-phase fluids are subjected to high-shear dynamic microemulsion through the pipeline Venturi static mixer under the action of temperature difference shock to generate a uniform alcohol-hydrogen microemulsion system.

[0042] (5) Centrifugal purification and phase lock-in: The above microemulsion is continuously pumped into a tubular centrifuge, and the centrifugal acceleration is set to 12000G. The ineffective free agglomerates and impurities with a particle size greater than 0.4μm are separated and removed. The clear permeate discharged is collected to obtain highly stable jet aviation alcohol-hydrogen fuel.

[0043] Example 2: This embodiment provides a method for preparing highly stable jet aviation alcohol-hydrogen fuel, including the following steps: (1) Raw material weighing: accurately weigh 59 parts by weight of bio-jet fuel, 12 parts by weight of methanol, 8 parts by weight of ethanol, 4 parts by weight of isobutanol, 3 parts by weight of isoamyl alcohol, 4 parts by weight of di(2-ethylhexyl) adipate, 3 parts by weight of diisobutyl adipate, 5 parts by weight of nitromethane, 3 parts by weight of nitromethane, 1 part by weight of carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles and 1 part by weight of polyisobutyleneamine.

[0044] (2) Preparation of oil phase carrier: Add bio-jet fuel, di(2-ethylhexyl) adipate, diisobutyl adipate and polyisobutyleneamine to a sealed reaction vessel with a jacket temperature control, heat to 45°C and stir continuously at 600 rpm for 40 minutes to form a uniform and transparent oil phase base liquid.

[0045] (3) Nanophase anchoring: Carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles were completely immersed in a mixture of nitromethane and nitromethane, and ultrasonically dispersed for 25 minutes under temperature control in a cold water bath at a frequency of 40 kHz. Then, the entire mixture was injected into the above oil phase base liquid, and the temperature was maintained at 45 ℃ and the mixture was stirred for another 20 minutes to make the nanoparticles uniformly suspended and anchored.

[0046] (4) Alcohol phase compounding and thermal shock microemulsion: Methanol, ethanol, isobutanol and isoamyl alcohol are mixed uniformly in an auxiliary tank to form an alcohol phase solution. The refrigerant is turned on to pre-cool the alcohol phase solution to -5℃. Then, the pre-cooled alcohol phase solution is pumped into the oil phase base liquid maintained at 45℃ at a constant flow rate of 15L / h. The two-phase fluids are subjected to high-shear dynamic microemulsion through a pipeline Venturi static mixer under temperature difference shock to generate a uniform alcohol-hydrogen microemulsion system.

[0047] (5) Centrifugal purification and phase lock-in: The above microemulsion is continuously pumped into a tubular centrifuge, the centrifugal acceleration is set to 11000G, the ineffective free matter with a particle size greater than 0.4μm is separated and removed, and the discharged clear liquid is collected to obtain highly stable jet aviation alcohol hydrogen fuel.

[0048] Example 3: This embodiment provides a method for preparing highly stable jet aviation alcohol-hydrogen fuel, including the following steps: (1) Raw material weighing: Accurately weigh 42 parts by weight of bio-jet fuel, 20 parts by weight of methanol, 15 parts by weight of ethanol, 2 parts by weight of isobutanol, 1 part by weight of isoamyl alcohol, 6 parts by weight of di(2-ethylhexyl) adipate, 5 parts by weight of diisobutyl adipate, 8 parts by weight of nitromethane, 5 parts by weight of nitromethane, 0.8 parts by weight of carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles and 0.2 parts by weight of polyisobutyleneamine.

[0049] (2) Preparation of oil phase carrier: Add bio-jet fuel, di(2-ethylhexyl) adipate, diisobutyl adipate and polyisobutyleneamine to a sealed reaction vessel with a jacket temperature control, heat to 35°C and stir continuously at 400 rpm for 20 minutes to form a uniform and transparent oil phase base liquid.

[0050] (3) Nanophase anchoring: Carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles are completely immersed in a mixture of nitromethane and nitromethane, and ultrasonically dispersed for 15 minutes under water bath temperature control (not exceeding 30℃) and frequency of 40kHz. Then, the whole is injected into the above oil phase base liquid, and the temperature is maintained at 35℃ and the mixture is stirred for 10 minutes to make the nanophase uniformly suspended and anchored in the oil phase.

[0051] (4) Alcohol phase compounding and thermal shock microemulsification: methanol, ethanol, isobutanol and isoamyl alcohol are combined to form an alcohol phase solution, and the refrigeration unit is turned on to pre-cool it to 5°C; then the pre-cooled alcohol phase solution is pumped into the oil phase base liquid maintained at 35°C at a constant flow rate of 8L / h, and dynamic microemulsification is carried out under the thermal shock and high shear action of the static mixer to generate a uniform alcohol-hydrogen microemulsion system.

[0052] (5) Centrifugal purification and phase lock-in: The microemulsion is continuously pumped into a tubular centrifuge, the centrifugal acceleration is set to 12000G, the ineffective agglomerates with a particle size greater than 0.4μm are separated and removed, and the discharged clear liquid is collected to obtain highly stable jet aviation alcohol-hydrogen fuel.

[0053] Example 4: This embodiment provides a method for preparing highly stable jet aviation alcohol-hydrogen fuel, including the following steps: (1) Raw material weighing: Accurately weigh 60 parts by weight of bio-jet fuel, 15 parts by weight of methanol (without ethanol), 3 parts by weight of isobutanol, 2 parts by weight of isoamyl alcohol, 5 parts by weight of di(2-ethylhexyl) adipate, 4 parts by weight of diisobutyl adipate, 7 parts by weight of nitromethane, 3 parts by weight of nitromethane, 0.5 parts by weight of carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles and 0.5 parts by weight of polyisobutyleneamine.

[0054] The specific operating parameters for steps (2) to (5) are completely consistent with those in Example 1.

[0055] Example 5: This embodiment provides a method for preparing highly stable jet aviation alcohol-hydrogen fuel, including the following steps: (1) Raw material weighing: Accurately weigh 60 parts by weight of bio-jet fuel, 15 parts by weight of ethanol (without methanol), 3 parts by weight of isobutanol, 2 parts by weight of isoamyl alcohol, 5 parts by weight of di(2-ethylhexyl) adipate, 4 parts by weight of diisobutyl adipate, 6 parts by weight of nitromethane, 4 parts by weight of nitromethane, 0.5 parts by weight of carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles and 0.5 parts by weight of polyisobutyleneamine.

[0056] The specific operating parameters for steps (2) to (5) are completely consistent with those in Example 1.

[0057] Comparative Example 1: This comparative example provides a method for preparing jet aviation alcohol-hydrogen fuel. The specific steps are basically the same as those in Example 1, except that: in step (1) when weighing raw materials, carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles are not added, and the missing 0.5 parts by weight are made up by an equal amount of bio-jet fuel; in the subsequent preparation, the nano-phase anchoring process in step (3) is omitted, and 10 parts by weight of nitromethane weighed in step (1) are directly added to a sealed reaction vessel with jacket temperature control in step (2) to participate in the preparation of the oil phase base liquid. The remaining steps and parameters are consistent with those in Example 1.

[0058] Comparative Example 2: This comparative example provides a method for preparing jet aviation alcohol-hydrogen fuel. The specific steps are basically the same as those in Example 1, except that: in step (1) of weighing raw materials, polyisobutylene amine is not added, and the missing 0.5 parts by weight is made up by an equal amount of bio-jet fuel. The remaining steps and parameters are consistent with those in Example 1.

[0059] Comparative Example 3: This comparative example provides a method for preparing jet aviation alcohol-hydrogen fuel. The specific raw material ratio is completely consistent with that of Example 1. The only difference is in the process equipment and energy input conditions: the pre-cooling of the alcohol phase solution to 0°C by turning on the refrigeration unit in step (4) and the high-shear dynamic microemulsification by the pipeline Venturi static mixer under the action of temperature difference are replaced by mixing and stirring at 500 rpm for 30 minutes at room temperature (25°C) without pre-cooling to generate an alcohol-hydrogen microemulsion system. The remaining steps are consistent with those of Example 1.

[0060] Test Example 1: Take 5 ml of each of the aviation alcohol-hydrogen fuel products prepared in Examples 1 to 5 and the three comparative examples, and let them stand and be sealed overnight in a clean room at an ambient temperature of 25°C.

[0061] Using a micropipette, 0.5 mL of each sample solution was rapidly mixed and diluted with n-hexane filtered through a 0.22 μm syringe filter at a fixed ratio of 1:50. This ensured that the concentration of the dispersed phase in the diluted system fell within the optimal detection concentration window of the dynamic light scattering device, thus avoiding the signal broadening phenomenon caused by the inherent multiple light scattering in the high concentration region of the sample.

[0062] The prepared dispersion system to be tested was injected into a special quartz cuvette. After cleaning the light-transmitting surface with a dust-free wiping paper, it was smoothly pushed into the optical measurement chamber of the nanoparticle size and Zeta potential integrated analyzer (with flow cell configuration). The closed-loop temperature control program inside the system was set to a constant temperature of 25°C and maintained in situ thermal equilibrium for 3 minutes.

[0063] The measurement software is activated to capture and accumulate backscattered signal fluctuations from optical channels in various directions. The polydispersity index of the average hydrodynamic diameter and calibration distribution width is calculated by fitting the autocorrelation function. Simultaneously, an alternating electric field of a specific frequency is superimposed to determine the phase shift caused by droplet migration, and the corresponding Zeta potential reference value is calculated. Three independent acquisition programs are executed for a single sample cycle, and the system integrates and outputs the valid observation values.

[0064] Table 1. Particle distribution and surface electrical test data for each embodiment and comparative example:

[0065] According to Table 1 and Figure 1The data shows that the example group and the various comparative examples exhibit fundamental differences in the dispersion state and physicochemical characteristics of the alcohol-hydrogen mixed phase. The average hydrodynamic diameter detected in Examples 1 to 5 was controlled to shrink to within 250 nanometers, reflecting that the fuel system broke through the macroscopic dispersion limit and entered the range of micromicelle emulsification. The polydispersity index of these samples collapsed below 0.16, and such a low generalization boundary suggests that the fluid droplets encapsulating alcohols did not undergo permeation ripening or reverse polymerization caused by phase collisions when left to stand at room temperature. As a stability critical boundary defined by basic theory, conventional microemulsion systems often require a Zeta potential absolute value exceeding a baseline of 38 mV to excite a double-layer repulsion force sufficient to counteract Brownian motion and van der Waals attraction; the Zeta potential absolute values ​​recorded in the example group generally exceeded the order of 38 mV.

[0066] It is noteworthy that the average hydrodynamic diameters (192.5 nm and 201.2 nm) and Zeta potentials (-41.5 mV and -40.1 mV), using single low-carbon alcohol formulations in Examples 4 (single methanol) and 5 (single ethanol), were also firmly locked within an exceptionally excellent stability window. This fully demonstrates that the thermosensitive composite three-dimensional network established by rigid carbonized polycyclic triphosphazene nanoparticles and polyisobutyleneamine molecules with flexible long chains possesses a strong and universal anchoring and blocking ability for the polar interfaces of low-carbon alcohol molecules. Whether it is a polyol blend or a single alcohol phase, the high-density localized free charge can form an outward electrostatic repulsion network deep within the nonpolar straight-run aviation kerosene liquid layer, effectively blocking the aggregation barrier of the dispersed phase itself.

[0067] The comparative group data under conditions of missing components or process deviations reveal a multi-directional trend of degradation at the parameter level. Comparative Example 1, lacking the core nanocarrier, suffers from uncontrolled expansion of the entire oil-in-alcohol network droplets due to interfacial tension preventing deep blocking through the occupancy effect of rigid particles. This expansion approaches the 600 nm region, and the collapse of the anti-disturbance film on the system surface directly leads to a relatively mediocre electrostatic separation point shrinking to -18.4 mV. In the absence of specific high-carbon molecular linkages, Comparative Example 2 exhibits an abnormal particle size of 945.7 nm, far exceeding normal measurement scales, and a severe lack of liquid phase homogeneity. Simply adding trace amounts of solubilizing polar solvents is insufficient to create interwoven tension at the heterogeneous phase interface, inevitably leading to volumetric phase separation and sedimentation of the two repulsive phases. Comparative Example 3, which deviates from the dynamic temperature and pressure environment, retained the complete set of chemical components. However, due to the low-dimensional shear field and energy injection rate of the room-temperature stirring, it failed to reach the trigger threshold required for the extreme cavitation induced by the Venturi effect and the forced stripping and instantaneous condensation and reorganization of microscopic interfaces. As a result, the produced agglomerates still tended to be loose and large in size. Observations combining dispersed phase data and charge characteristics demonstrated that high-shear-assisted thermal shock and spatial anchoring of complex components are the inevitable path for intervening in the thermodynamic reshaping of alcohol-oil phase fluids with a large compatibility span.

[0068] Test Example 2: Based on the raw material ratios of Examples 1 to 5 and Comparative Examples 1 to 3, two-phase precursor test solutions were prepared for each system before emulsification and mixing. Bio-jet fuel was mixed with a specified oil-soluble ester, polyisobutylene amine, and an ultrasonically dispersed nanoparticle suspension in a jacketed, temperature-controlled sealed container. This mixture was then kept at a constant temperature to prepare the light phase test solution. Simultaneously, a corresponding mixed alcohol solution was prepared under cold conditions to prepare the heavy phase test solution.

[0069] Turn on the main power of the fully automatic droplet interfacial tensiometer and the water bath circulation system in the test chamber to precisely lock the ambient reference temperature in the instrument's measurement chamber at 25°C, maintaining in-situ equilibrium to eliminate the interference of ambient temperature drift on droplet volume.

[0070] An appropriate amount of the prepared alcoholic light phase liquid is drawn and placed into a high-precision micro-injection pump syringe connected to a stainless steel inverted U-shaped injection needle with a specific outer diameter (1.65mm). The entire syringe is then slowly immersed to the depth of an optical cuvette pre-filled with oily heavy phase liquid of the same group.

[0071] The software controls the injection pump to expel a small amount of alcohol solution at a rate of 0.5 μL / s, which then hovers at the tip of the needle to form a stable hemispherical droplet. The system's built-in high-speed CCD camera is then activated to capture the contact interface.

[0072] The dynamic capture sequence is initiated, and the Laplace-Young equation fitting algorithm inside the instrument continuously processes the geometric contour deformation of the droplet over time, recording the absolute values ​​of interfacial tension at three time points: the initial stage after phase contact (10 seconds), the adsorption transition period (5 minutes), and the final state of thermodynamic stability (30 minutes).

[0073] Table 2. Dynamic tension characteristics of the liquid-liquid interface of precursors in each embodiment and comparative example:

[0074] According to Table 2 and Appendix Figure 2 The data reveals that the thermodynamic response at the liquid-liquid boundary exposes the intrinsic microphysical mechanism by which the formulation system maintains phase fusion. Aviation liquid hydrocarbons and low-carbon alcohols inherently possess extremely strong polar barriers. In the initial testing phase (within a 10-second window), the basic tension of all samples mostly remained in the range of 11 to 19 mN / m, showing a clear macroscopic stratification trend. After entering the adsorption transition period and the final state observation stage, the evolution paths of various formulations became fragmented. The values ​​of Examples 1 to 5 showed a steep, collapsing decline, with the equilibrium tension at 30 minutes firmly suppressed below the 1.5 mN / m water level. In particular, the newly added Examples 4 and 5, even using methanol or ethanol as the heavy phase, still showed final state tensions (1.21 and 1.25 mN / m) highly consistent with the multi-component alcohol system. This demonstrates that the formulation system possesses universal interfacial activity for various low-carbon alcohols. Laboratory experience in testing surfactant thresholds shows that when the tension crosses the 1 to 2 mN / m boundary, the system is at the thermodynamic critical edge of spontaneous microemulsion formation. At this moment, the long-chain polyisobutyleneamine completes a high-density directional arrangement at the phase interface, while the rigid carbonized polyphosphazene nanoparticles squeeze into the intermolecular gaps and exert a strong spatial repulsion effect, completely destroying the cohesive pull of the free alcohol droplets to fuse and recover.

[0075] The data feedback from the control sequence provided a more concrete picture of the mechanism. Comparative Example 1, stripped of its solid nanoparticle components, ultimately exhibited a surface tension of 4.62 mN / m, revealing a severe deficiency in the interfacial strength of the liquid film constructed solely by long-chain amine molecules during oil phase component replacement, failing to penetrate to a low-tension region sufficient to induce microemulsion micelle fragmentation. Comparative Example 2, lacking the main bridging polar molecules, displayed a rigid surface tension wall as high as 14.08 mN / m, verifying that attempts to achieve Pickering emulsification purely through physical nanoparticles completely failed in this type of lightweight aviation fuel oil. Comparative Example 3 captured a phenomenon often overlooked in engineering verification processes: due to its complete chemical composition matching Example 1, its liquid phase contact test output a nearly identical low-tension fingerprint (1.17 mN / m). Establishing this highly deceptive low surface tension, coupled with the conclusion of the turbidity failure of the product in Comparative Example 3 in Test Example 1, revealed that compatibility thermodynamics alone is far from sufficient for fluid construction. This physical contrast, from the side, ended the engineering fantasy of static solubilization, establishing that only by relying on the fluid dynamics intervention of rapid cooling temperature difference contraction and Venturi high-frequency shear tearing can the final activation energy barrier be crossed, forcing the droplet under low tension conditions to finally break up and solidify into the nanoscale ultra-stable cage lattice region.

[0076] Test Example 3: The fluid precursors from Examples 1 to 5 and Comparative Examples 1 to 3 that entered the mixing chamber stage during the preparation process were extracted. A bypass online monitoring reflux system was built, and the microflow cell was connected to the circulation outlet of a high-shear mixing device or a conventional mechanical stirring device. The optical paths on both sides of the flow cell were connected to the transmitter and receiver of a UV-Vis spectrophotometer.

[0077] The spectrophotometer's detection wavelength was preset to 600 nm. This wavelength band can maximally shield against absorption interference from the fluid's background color and maintain extremely high sensitivity to Mie scattering caused by micron-sized emulsion droplets. Baseline zeroing and 100% transmittance calibration were performed by filling the flow cell with pure straight-run aviation kerosene.

[0078] Simultaneously start the emulsification preparation equipment and spectral acquisition software for each group, and continuously record the time series evolution of the transmittance signal at a sampling interval of 0.5 seconds. The monitoring software has a built-in first derivative calculator. When the slope of the tangent of the transmittance curve fluctuates by less than 0.1% for 2 consecutive minutes, the system automatically determines that the internal phase structure of the fluid has stopped evolving, and records the corresponding timestamp as the time required to reach dynamic equilibrium.

[0079] Transmittance monitoring data within 10 minutes after reaching the dynamic equilibrium determination point is extracted. The mean of steady-state transmittance during this time period is extracted by arithmetic averaging and determined as the measured transmittance of the initial microemulsion to evaluate the optical uniformity and microparticle size distribution of the product.

[0080] Table 3. Dynamic equilibrium time and steady-state optical characteristics of microemulsion in each embodiment and comparative example:

[0081] According to Table 3 and the appendix Figure 3 The data shows that the fundamental differences in energy input mode and physical boundary conditions in the preparation process have a decisive influence on the dispersion state of the final continuous phase. Examples 1 to 5 exhibited extremely high engineering imaging efficiency in the spectral quantization system test, with their transmittance curves rapidly climbing and stabilizing at a reference field of over 96% within a very narrow time window. In particular, Examples 4 and 5, under extreme single-phase conditions using only methanol or ethanol, still achieved optical performance highly consistent with the compound alcohol system (transmittances as high as 97.8% and 96.9%, respectively, and the time taken was less than 5 minutes), which fully demonstrates that the preparation system and formulation system of the present invention have extremely strong process universality for single low-carbon alcohols. Laboratory fluid calibration observation experience confirms that the composite kinetic energy input field of thermal shock superimposed with Venturi high shear domain greatly reduces the relaxation period required for matter to cross the compatibility barrier; under the violent alternating temperature gradient drop and local acoustic cavitation effect tearing, the coarse emulsion droplets are forcibly pulverized to a nanoscale far below the visible light diffraction limit, and Mie scattering phenomenon hardly occurs when photons penetrate the fluid, objectively establishing the external phenotype of extremely high transmittance.

[0082] Over-reliance on static thermodynamic deductions based on chemical compatibility often faces the risk of localized failure in actual fluid mixing. The test feedback from Comparative Example 3 clearly reveals that the room-temperature stirring process is limited by the shear mechanical work frequency range being in the low dissipation range, and the system took nearly one and a half hours (86.5 minutes) of extreme lag to barely reach a pseudo-equilibrium state. The extracted steady-state transmittance of 62.7% clearly exposes that due to the lack of breakup energy, the product interior is still densely packed with a large number of micron-sized macroporous agglomerates, failing to activate the dense interfacial locked phase between components. Comparative Examples 1 and 2, with fundamental deficiencies in their compatibility systems, are completely outside the stable hydrodynamic framework. The extremely low optical transmittance values ​​and the almost divergent time consumption curves indicate that without the construction of a rigid interfacial framework by carbonized nanoparticles or the introduction of an effective polymer de-tensioning mechanism, any external forced convection work cannot reverse the volume separation process driven by polar repulsion. The transient field constraint of the engineering thermodynamic environment, combined with the high-speed tearing potential energy, essentially fills the energy deficit that the static interfacial tension is insufficient to maintain the solidification of the ultramicro phase in one direction.

[0083] Test Example 4: Extract the aviation alcohol-hydrogen fuel products of Examples 1 to 5 prepared in the previous process, as well as the three comparative examples 1 to 3 that lacked corresponding components or deviated from the preparation path. Take 30 ml of each sample and encapsulate them in a set of standard pressure-resistant window glass test bullets. Leave a 10% safety expansion gap at the top and lock it with a polytetrafluoroethylene sealing plug.

[0084] The first set of encapsulated samples was securely placed on the stage of the programmable alternating high and low temperature environment test chamber. A 24-hour cycle algorithm including extreme conditions was set: the chamber temperature dropped to -40℃ at an extreme rate and was kept constant for 8 hours, and then the temperature was increased to +50℃ at the highest rate and kept for 8 hours. A forced heat transfer transition window of 4 hours was left in each interval.

[0085] Using a graduated optical monitoring window in conjunction with a periodic laser transmission probe, fluid phase images are captured at the end of each extreme temperature rise and fall. When the system detects that more than 1% of the total volume of precipitated free phase appears at the bottom of the sample liquid or that the transmittance of the main fluid suddenly drops to an opaque state, the cycle counting for that batch is terminated. The system extracts and fixes the final number of complete cycles achieved.

[0086] A second set of parallel fluid samples was transferred into custom-calibrated centrifuge tubes, symmetrically balanced, and then loaded into the pneumatic rotor chamber of an analytical ultracentrifuge equipped with a stroboscopic phase boundary detection module. The centrifugation start-up program was set to gradually increase from the basic ambient gravitational acceleration (1G), and after passing the 1000G baseline, to enhance the centripetal load by increasing the centripetal force load by a step slope of 500G every 10 minutes.

[0087] Real-time monitoring of phase migration interface displacement signals caused by component density differences allows for precise capture of the moment when the alcohol-water phase overcomes emulsification resistance, segregates towards the bottom of the tube, and undergoes macroscopic volumetric layer splitting. The system outputs the limiting centrifugal acceleration (G value) corresponding to this failure point.

[0088] Table 4. Endurance limit test data of each embodiment and comparative example under harsh unsteady stress conditions:

[0089] According to Table 4 and Appendix Figure 4The data shows that the phase reconstruction and failure path of the aviation fuel system after the intervention of extreme physical stress fields exhibit a fault-like magnitude difference. The fluid networks of Examples 1 to 5 demonstrated extraordinary structural tolerance in a wide-range alternating cold and heat profile spanning 90 degrees Celsius, with their critical period for resisting phase separation generally delayed to at least 38 cycles. Even in the extreme single-phase systems using only methanol or ethanol (Examples 4 and 5), the failure cycles (40 and 39 cycles, respectively) remained highly consistent with those of the compound system, with no performance degradation observed. In previous in-depth observations involving the miscibility of alcohols and oils, researchers have often found that just a few cycles of deep freezing and high-temperature expansion are sufficient to trigger the secondary aggregation of various polar molecules within the droplets. Due to the thermodynamic interface energy being highly susceptible to periodic mismatch in the drastic temperature gradients of micro-regions, the system directly transitions from a latent stress state to irreversible stratification collapse. The data here directly confirm the blocking effectiveness of the multi-scale component anchoring system structure in this failure process. The carbonized nano-polyphosphazene embedded in the oil-water boundary not only provides steric hindrance, but this high-rigidity non-planar particle group actually casts a dense three-dimensional steric hindrance grid around the microemulsion droplets, completely locking the forced migration channels of low-carbon alcohol molecules when their volume expands or contracts due to drastic changes in system temperature; with the help of the highly elastic solvation buffer layer extended and laid by the polyisobutylene amine backbone in the straight-run kerosene medium, the droplet cluster can maintain the overall coherence of the nanoscale pseudoplastic conformation under deep thermal shock oscillation.

[0090] How to resist the severe physical overload separation tendency induced by aircraft on complex maneuver routes has always been the core criterion for demonstrating whether alternative fuel combinations can truly be promoted for engineering and deployment. The extreme destructive data of centrifugal stress feedback reveals another principle of maintenance at the level of phase mechanics. The entire set of examples (including the newly added single alcohol examples 4 and 5) possesses the inherent ability to withstand the ultra-strong mass distribution tearing force exceeding 13000G (14000G for example 4 and 13800G for example 5). The control array cluster, lacking a targeted interface interlocking mechanism or process internal energy supplementation, rapidly collapsed and separated under only a very weak centripetal acceleration field. Comparative example 1, stripped of highly surface-active occupant particles, underwent density difference-dominated multiphase sedimentation under weak centripetal traction of 3500G. This phenomenon, conversely, confirms the fragility of oil-water film boundaries constructed solely by flexible amphiphilic molecules when facing directional shear stress tension. Such linear defenses are highly susceptible to large-scale perforation after large-scale molecular chain directional slippage along the stress direction. Comparative Example 3, which failed to undergo the full cycle of thermo-compression-instantaneous fracture and recombination at the preparation terminal, exhibited premature phase layer collapse at the 4200G node, even with equivalent high-energy interface blocking reagents. This indicated that the latex micelles assembled under weak shear at room temperature were riddled with massive physical splicing defects. These invisible local coordination cavities and primary interface microcracks, magnified by the microscopic centrifugal gravitational gradient, immediately transformed into the mechanical collapse origins that destroyed the entire micelle network. The underlying logic that macroscopic systems cannot induce deep bonding of dense spatial matrices without the forced intervention threshold of fluid mechanics was validated in the feedback spectrum of the extreme destructive test.

[0091] Test Example 5: Fluid samples from Examples 1 to 5, encapsulated in a cryogenic storage tank, were extracted in 60 ml volumes each from Comparative Examples 1 to 3, which were control samples due to incompatibility defects or lack of high-energy fluid intervention. The entire test environment was cooled and dehumidified, and then filled with dry nitrogen to avoid the non-directional interference of trace water vapor condensation on the non-aqueous fluid phase.

[0092] An advanced rotational rheometer equipped with a Peltier semiconductor cooling module and concentric cylindrical fixtures was used to inject various sample solutions pre-cooled to -40°C into the test tray. After a 15-minute equilibrium relaxation period to release the residual normal stress induced by sampling, a steady-state flow scanning program was executed. The shear rate was set from 10 s⁻¹. -1 The low-frequency region continuously climbs to 10000s in a logarithmic hysteresis mode. -1 The high-frequency boundary was used to determine the apparent shear viscosity response under two typical engineering fluid conditions: pipeline transportation and high-pressure nozzle atomization.

[0093] An automatic low-temperature kinematic viscosity meter equipped with a high-precision optical liquid level sensing base was simultaneously activated, and the refrigerant temperature in the bath was precisely controlled at -20.0℃. An Ubbelohde viscometer with a capillary inner diameter calibrated by countercurrent was used to record the cross-regional outflow time of each test oil sample under gravity and laminar flow boundary conditions.

[0094] After acquiring the motion time of each group of samples, the precise kinematic viscosity data within the -20℃ reference range was calculated by substituting the pre-calibrated instrument constants. For the comparative defect sample that is prone to solid-liquid phase transition, the measurement was forcibly truncated when the liquid column outflow time exceeded the alarm threshold of the normal flight envelope, and the critical point was extracted to calculate the characteristic value.

[0095] Table 5. Low-temperature kinetic rheology and kinematic viscosity test data for each embodiment and comparative example:

[0096] According to Table 5 and Appendix Figure 5 The data shows that thermodynamic regulation and the integrity of the micelle network directly dominate the macroscopic dynamic characterization in test fields involving large-span temperature stripping and high-frequency deformation. As an external fingerprint for the evaluation of microscopic particle dynamics, the kinematic viscosity of the example group (including the newly added single methanol example 4 and single ethanol example 5) converges to 5.4 to 6.2 mm at -20°C. 2 Within the range of / s, this indicator fully complies with the 8.0mm allowable by the aircraft engine fuel control system. 2 / s viscosity threshold. Because the heterosegmented polyisobutylene amine counteracts the rigid friction between dispersed droplets through steric hindrance at the interface, the mixed system can avoid the increase in yield stress caused by the low-temperature phase separation and aggregation of free alcohol in the cooling region. Because the heterosegmented polyisobutylene amine counteracts the rigid friction between dispersed droplets through steric hindrance at the interface, the mixed system can maintain excellent fluid extensibility in the cooling region.

[0097] The deep pseudoplastic thinning behavior exhibited by the example group in a wide shear window establishes a validation basis for system rheological intervention; 10s -1 The pumping viscosity of nearly 15 mPa·s in the region (stable at 15.12 and 15.65 mPa·s in Examples 4 and 5, respectively) endows the fluid with excellent anti-settling cohesiveness, even when the external dynamic load jumps to 10000 s. -1 During this stage, the viscosity collapses to below 5 mPa·s. The carbonized nano-polyphosphazene rigid particles dispersed on the vesicle surface become micro-stress accumulation points in the forced torsional field. Through the non-uniform puncture effect, the continuous molecular chain film is transiently degraded and broken. The fluid network is transformed into a fragmented free phase the instant it leaves the nozzle, thereby achieving fine atomization and dispersion.

[0098] The absence of the underlying structure leads to an irreversible increase in internal friction in the rheological appearance. Comparative Example 1, which has had its hard phase particles stripped away, retains a flexible interface architecture, but its terminal residual viscosity of 9.77 mPa·s under high-frequency shear indicates limitations in the kinetic energy dissipated solely by the coiling and extension of long carbon chains. The fluid encapsulation layer fails to produce decisive tearing, thus slowing down the atomization process. Comparative Example 2 exposes the fatal physical defects of the polar free alcohol layer, which is not isolated by the emulsifier, under cold conditions. The low shear resistance exceeding 125 mPa·s reveals the presence of large-scale phase crystal interweaving within the system. Comparative Example 3, produced through low-dissipation mechanical mixing, experiences a surge in internal friction when resisting shear deformation due to the hysteresis of the original particle size. Intersecting with the Venturi cavitation thermal decoupling system, its laminar potential energy transfer path is truncated by loose, large-particle emulsion agglomerates, macroscopically manifesting as viscosity hysteresis and deviation in pumping performance. The degradation of this test dimension not only confirms the necessity of ultrafine dispersion for establishing a seamless flow layer, but also simultaneously establishes the engineering requirement of relying on fluid forced pulverization combined with rigid-flexible interface hybridization as the control of fuel phase change and atomization rheology.

[0099] Test Example 6: Prepare test samples. The experimental subjects included the mixed fuel samples of Examples 1 to 5 prepared above, as well as two comparative sample samples. The composition and operation of Comparative Example 1 were consistent with Example 1, but it did not contain nitrobanane, and the amount of nitromethane was added to 12 parts by weight; Comparative Example 2 had the same composition as Example 1, but carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles were not added to the system. All samples were sealed and protected from light at room temperature for 24 hours before testing to eliminate residual microbubbles from the preparation process.

[0100] The low-temperature phase stability of the samples was determined. Each group of samples was cooled to -45°C using a constant-temperature cold bath and maintained at this temperature for 24 hours. After the predetermined time, the turbidity (NTU) of each sample liquid was measured using a turbidity meter. The fluctuation of the turbidity data was used to quantify the miscibility and phase separation tendency of alcohols, base oils, and high-calorific-value agents under extremely low-temperature conditions.

[0101] The dynamic stability of the dispersed phase was tested. Long-term monitoring was performed on Examples 1 to 5 and Comparative Example 1, which contained nanoparticles, using a multiple light scattering (MLS) instrument. The sample tubes were left to stand at room temperature for 30 days. The instrument light source was scanned vertically along the sample tube, and the dynamic stability index (TSI) was calculated based on the rate of change of luminous flux of transmitted and backscattered light. During the testing period, the sample tubes were kept absolutely still to avoid any external vibration interference.

[0102] The calorific value and micro-explosive combustion characteristics of the evaluation system were assessed. Samples from each group were loaded into an oxygen bomb calorimeter to determine their net calorific value. Subsequently, spray combustion tests were conducted on a constant-volume combustion bomb test bench. The background temperature of the test bench was set to 800 K, and the injection pressure was maintained at 100 MPa. A recording device captured the entire ignition and combustion process of the fuel jet using a high-speed camera. The combustion duration was extracted from the image data to evaluate the secondary atomization and combustion reaction rate of the multi-component system under high temperature and high pressure conditions.

[0103] The test results for each group of samples are shown in Table 6 below: Table 6: Comparison of performance test results between each embodiment and the comparative example:

[0104] According to Table 6 and Appendix Figure 6 The data shows that observing the low-temperature turbidity index of each group of samples reveals the direct impact of specific ratios of nitroalkanes on the phase state of the alcohol-oil mixture. In a cryogenic testing environment of -45℃, the turbidity of Comparative Example 1, without the addition of nitropropane, rose sharply to 18.53 NTU, and visible emulsified turbidity precipitated at the bottom of the container. This phase separation tendency reduces the fluid reliability of aviation fuel during high-altitude, low-temperature operation and increases the risk of fuel supply line blockage. In Examples 1 to 5, after introducing a certain amount of nitropropane by weight, the turbidity of the system was suppressed to a low range of 1.24 to 2.81 NTU. The experimental phenomena confirm that long-chain nitroalkanes act as a physical interface buffer between highly polar alcohols and non-polar aviation kerosene base oil. This co-solvent effect intervenes in the precipitation process of the alcohol phase at low temperatures, maintaining the thermodynamic stability of the mixture.

[0105] The phase stability of the fuel liquid system is a prerequisite for the nanoparticles to function, and the anti-settling ability of the suspended phase determines the engineering applicability of the formulation under long-term storage conditions. A comparison of the dynamic stability index after 30 days of standing confirms that Comparative Example 1, relying on a single nitromethane system, failed to effectively inhibit the aggregation of carbonized polyphosphazene nanoparticles, with a TSI value as high as 3.94. Changes in light flux during the test indicate that a solvent layer with a single polarity is insufficient to completely coat the complex particle surface. The TSI index of the example group fluctuated within the range of 1.18 to 1.52. The mixed solvation layer composed of nitromethane and nitrobenzene constructs a sterically hindered physical layer around the particles, weakening the van der Waals forces between particles, thus enabling the nanophase to acquire suspension dynamics characteristics matching those of the alcohol-based liquid.

[0106] The improvement in thermodynamic work characteristics is based on the aforementioned physical stability. The duration recorded in the combustion test reflects the differences in the micro-explosion characteristics of the multi-component system. The combustion process of Comparative Example 2, lacking a nanocatalytic phase, was relatively slow, taking 43.46 milliseconds. The combustion time of Comparative Example 1 remained at 41.28 milliseconds, while the combustion cycles of the Example groups were generally shortened to 38.04 to 39.21 milliseconds. Secondary atomization and breakup of droplets upon entering the high-temperature environment dominated this process. The inherent boiling point gradient between the compound nitro system and the base oil caused asynchronous vaporization within the fuel droplets, and the imbalance of local pressure forced the droplets to disintegrate into finer combustible clouds. In this physical breakup process, uniformly dispersed nanoparticles were directly exposed to the reaction interface. The catalytic sites on their surfaces synergistically interacted with the oxygen source released by the decomposition of nitro groups, accelerating the carbon chain cleavage and oxidation rate, ultimately achieving a shortened reaction cycle and efficient heat release in the macroscopic combustion performance.

[0107] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A highly stable jet aviation alcohol-hydrogen fuel, characterized in that, Made from the following parts by weight of raw materials: 42-59 parts of bio-jet fuel; 10-30 parts of lower alcohols; 2-4 parts isobutanol; 1-3 parts of isoamyl alcohol; 4-6 parts of di(2-ethylhexyl) adipic acid; 3-5 parts of diisobutyl adipic acid; 5-10 parts of nitromethane; 2-8 parts of nitropropane; 0.5–1 part of carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles; 0.2 to 1 part of polyisobutylene amine; The lower alcohol is methanol, ethanol, or a mixture of both in any proportion. The rigid particle group of the carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles and the polyisobutyleneamine with flexible long chains establish a composite three-dimensional spatial steric hindrance network at the oil-alcohol phase interface of the fuel system, so as to form an electrostatic repulsion network in the depth of the non-polar oil phase liquid layer, thereby inhibiting the thermodynamic coalescence and ripening of microemulsion droplets in the continuous phase.

2. The highly stable jet aviation alcohol-hydrogen fuel according to claim 1, characterized in that, The raw material is made from the following parts by weight: The composition includes 50 parts bio-jet fuel, 15 parts methanol, 10 parts ethanol, 3 parts isobutanol, 2 parts isoamyl alcohol, 5 parts di(2-ethylhexyl) adipate, 4 parts diisobutyl adipate, 8 parts nitromethane, 4 parts nitrobenzene, 0.5 parts carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles, and 0.5 parts polyisobutyleneamine.

3. The highly stable jet aviation alcohol-hydrogen fuel according to claim 1, characterized in that, The physicochemical properties of the raw material meet the following conditions: The main chain structure of the bio-jet fuel is hydrogenated ester and fatty acid-synthesized aviation kerosene, with a carbon number distribution of C8 to C16, a straight-chain and branched-chain alkane mass fraction of 98.0 wt% to 99.8 wt%, and an aromatic hydrocarbon mass fraction of 0.01 wt% to 0.5 wt%. The effective amine value of the polyisobutylene amine is 45-60 mg KOH / g, the number average molecular weight Mn is controlled between 1000 and 1050 g / mol, and the impurity moisture content is 0.01 wt% to 0.05 wt%.

4. The highly stable jet aviation alcohol-hydrogen fuel according to claim 1, characterized in that, The physicochemical properties and source limitations of the raw materials are as follows: The carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles are prepared by carbonization after polymerization of hexachlorocyclotriphosphazene with a purity of 99.0wt% to 99.9wt% and 4,4'-sulfonyldiphenol with a purity of 99.0wt% to 99.9wt%. The acid values ​​of both di(2-ethylhexyl) adipic acid and diisobutyl adipic acid are 0.01–0.2 mg KOH / g.

5. The highly stable jet aviation alcohol-hydrogen fuel according to claim 1, characterized in that, The microscopic and kinetic characteristic parameters of the fuel product satisfy the following: The average hydrodynamic diameter measured at an ambient temperature of 25℃ was 150–250 nm, the absolute value of the Zeta potential was 38–50 mV, and the polydispersity index was 0.10–0.

16. Furthermore, the precise kinematic viscosity of the fuel product within the -20℃ reference range is 5.4–6.2 mm. 2 / s.

6. A method for preparing a highly stable jet aviation alcohol-hydrogen fuel, used to prepare a highly stable jet aviation alcohol-hydrogen fuel according to any one of claims 1-5, characterized in that, Includes the following steps: S1 Raw Material Weighing: Accurately weigh each component raw material according to the set weight ratio; S2 oil phase carrier preparation: Bio-jet fuel, di(2-ethylhexyl) adipate, diisobutyl adipate and polyisobutyleneamine are added to a sealed reaction vessel with a jacket temperature control, heated and continuously stirred to form a uniform and transparent oil phase base liquid. S3 Nanophase Anchoring: Carbonized poly[cyclotriphosphazene-co-(4,4'-sulfonyldiphenol)] nanoparticles are completely immersed in a mixture of nitromethane and nitromethane, and ultrasonically dispersed under temperature control in a warm water bath to form a uniform dispersion. Then, the entire mixture is injected into the above oil phase base liquid, and the temperature is maintained and the mixture is stirred to make the nanoparticles uniformly suspended and anchored in the oil phase. S4 Alcohol Phase Mixing and Thermal Shock Microemulsification: Methanol, ethanol, isobutanol and isoamyl alcohol are mixed in a closed tank to form an alcohol phase solution and pre-cooled; then the pre-cooled alcohol phase solution is pumped into the oil phase base liquid at a constant flow rate and kept at a constant temperature. The two-phase fluids undergo high-shear dynamic microemulsification through a mixer under the action of temperature difference shock to generate a uniform alcohol-hydrogen microemulsion system. S5 Centrifugal Purification Lock-in: The above microemulsion is continuously pumped into a centrifuge, and the centrifugal acceleration is set to separate and remove ineffective free aggregates and impurities. The clear liquid discharged is collected to obtain the finished product.

7. The method for preparing a highly stable jet aviation alcohol-hydrogen fuel according to claim 6, characterized in that, In steps S2 and S3: In step S2, the heating temperature of the reactor is 35-45°C, the stirring speed is 400-600 rpm, and the stirring time is 20-40 minutes. In step S3, ultrasonic dispersion is carried out in a water bath at 20-30°C, with an ultrasonic frequency of 40kHz and a duration of 15-25 minutes; after the entire oil phase is injected, the temperature is maintained at 35-45°C and stirring is continued for 10-20 minutes.

8. The method for preparing a highly stable jet aviation alcohol-hydrogen fuel according to claim 6, characterized in that, In step S4: Turn on the refrigeration unit to precool the alcohol phase solution to the range of -5℃ to 5℃; The pre-cooled alcohol phase solution is then pumped into the oil phase base liquid maintained at 35–45°C at a stable flow rate of 8–15 L / h. Under the combined effect of the temperature difference shock and the high shear of the pipeline Venturi static mixer, the coarse emulsion droplets are torn apart and pulverized, triggering the thermodynamic reshaping of the phase fluid.

9. The method for preparing a highly stable jet aviation alcohol-hydrogen fuel according to claim 6, characterized in that, In step S5: The centrifuge is a tubular centrifuge; The set centrifugal acceleration is controlled between 11000G and 12000G; Separate and remove ineffective free agglomerates with particle sizes between 0.4 μm and 5 μm.

10. The method for preparing a highly stable jet aviation alcohol-hydrogen fuel according to claim 6, characterized in that, The reaction endpoint control for step S4, the thermal shock microemulsification stage, is based on the following: A bypass online monitoring backflow system was established, and a spectrophotometer was used to continuously record the time series of transmittance signals at a detection wavelength of 600 nm. When the slope of the tangent line of the first derivative of the transmittance curve fluctuates within the range of 0.01% to 0.1% for 2 consecutive minutes, it is determined that the dynamic microemulsion has reached a steady-state structure. At this time, the mean steady-state transmittance of the initial microemulsion is controlled to be greater than 96%.

Images