787 results about "Aviation fuel" patented technology

The invention provides a flexible preparation system and method for sustainable aviation fuel, and the system comprises a green power supply module which is used for outputting fluctuating green electric energy; the process execution device is connected with the green power supply module and comprises five process modules, namely an air carbon capture module, a co-electrolysis module, a Fischer-Tropsch synthesis module, a hydrogen production module and a hydrogenation refining module; the data acquisition module is used for acquiring the temperature, the pressure, the liquid level, the raw material input flow and / or the product output flow of each process module in the process execution device; and the decision control module is used for predicting the future power supply condition of the green electricity based on the historical weather data of the green electricity location, adjusting the distribution of the power in each process module according to the future power supply condition, and adjusting the temperature, pressure and / or raw material input flow in each process module. According to the invention, the cost, the reliability, the operation and maintenance performance, the product quality and the green power utilization rate can be substantially improved at the same time, and the flexible and stable operation of the system under the green power condition is realized.

An aircraft gas turbine engine includes a combustor, with a combustion chamber and fuel spray nozzles to inject fuel into the chamber. The nozzles include first and second subsets. The first subset of nozzles is supplied with fuel at a greater rate than each of the second subset. A ratio of nozzles in the first subset to the second subset is 1:3 to 1:6. A lean cruise nvPM emissions index ratio isEIcruise⁡(lean),SAFEIcruise⁡(lean),FF,where EIcruise(lean),SAF isEImaxTO,SAF+EIclimb,SAF2and EIcruise(lean),FF isEImaxTO,FF+EIclimb,FF2.EImaxTO,SAF is nvPM emissions index operating at 100% available thrust and EIclimb,SAF is the nvPM emissions index operating at 85% available thrust if fuel includes sustainable aviation fuel. EImaxTO,FF is the nvPM emissions index operating at 100% available thrust and EIclimb,FF is the nvPM emissions index at 85% available thrust if fuel is a fossil-based hydrocarbon. The lean cruise nvPM emissions index ratio is less than 1.

A gas turbine engine for an aircraft is disclosed. The gas turbine engine comprises: a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. A thrust nvPM emissions index ratio is defined as:EImaxTO / FmaxTOEIidle / Fidlewhere: EIidle is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 7% available thrust for given operating conditions; EImaxTO is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 100% available thrust for the given operating conditions; FmaxTO is the thrust of the gas turbine engine at around 100% available thrust in kN for the given operating conditions; and Fidle is the thrust of the gas turbine engine at around 7% available thrust in kN for the given operating conditions. The thrust nvPM emissions index ratio is greater than 0.001. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the plurality of fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

A gas turbine engine for an aircraft is disclosed. The gas turbine engine comprises: a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:3 to 1:6. A MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles. Also disclosed are methods of operating the gas turbine engine.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:2 to 1:5. An MTO nvPM emissions index ratio-modified fuel flow is defined as:EImaxTO,SAFEImaxTO,FF×Wf,maxTOwhere: EImaxTO,SAF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); EImaxTO,FF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel; and Wf,maxTO is the mass flow rate of fuel provided to the plurality of fuel spray nozzles in kg / s when the gas turbine engine is operating at around 100% available thrust for the given operating conditions. The MTO nvPM emissions index ratio-modified fuel flow of the gas turbine engine in kg / s is less than 2. The gas turbine engine is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

A gas turbine engine includes: a rich burn, quick quench, lean burn combustor having a number of fuel spray nozzles in the range 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An nvPM emissions index ratio is defined as:EIidle×Wf,idleEImaxTO×Wf,maxTOwhere: EIidle and EImaxTO are respectively the nvPM emissions index in mg / kg of gas turbine engine if operating at around 7% or 100% available thrust for given operating conditions; Wf,idle and Wf,maxTO are respectively the rate of fuel flow to fuel spray nozzles in kg / s at around 7% or 100% available thrust for given operating conditions. The fuel-flow nvPM emissions index ratio is less than 0.08. The gas turbine engine is configured to provide fuel including sustainable aviation fuel to fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. An MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel comprising a SAF to the fuel spray nozzles. Also disclosed is a method of operating a gas turbine engine.

A gas turbine engine for an aircraft is disclosed. The gas turbine engine comprises: a combustor, comprising a combustion chamber and a plurality of fuel spray nozzles configured to inject fuel into the combustion chamber, wherein the plurality of fuel spray nozzles comprises a first subset of fuel spray nozzles and a second subset of fuel spray nozzles, wherein the combustor is operable in a condition in which each of the fuel spray nozzles of the first subset of fuel spray nozzles is supplied with fuel at a greater fuel flow rate than each of the fuel spray nozzles of the second subset of fuel spray nozzles, wherein a ratio of the number of fuel spray nozzles in the first subset of fuel spray nozzles to the number of fuel spray nozzles in the second subset of fuel spray nozzles is in the range of 1:3 to 1:6. A MTO nvPM emissions index ratio is defined as:EImaxTO,SAFEImaxTO,FFwhere: EImaxTO,SAF is the nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for given operating conditions if a fuel provided to the plurality of fuel spray nozzles comprises a sustainable aviation fuel (SAF); and EImaxTO,FF is the nvPM emissions index in mg / kg of the gas turbine engine when operating at around 100% available thrust for the given operating conditions if a fuel provided to the plurality of fuel spray nozzles is a fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio of the gas turbine engine is less than 1. The gas turbine engine is configured to provide fuel comprising a SAF to the plurality of fuel spray nozzles. Also disclosed are methods of operating the gas turbine engine.

A gas turbine engine includes: a rich burn, quick quench, lean burn combustor having a number of fuel spray nozzles in range of 14-22 or a number of fuel spray nozzles per unit engine core size in range 2 to 6. An MTO nvPM emissions index ratio is:EImaxTO,SAFEImaxTO,FF×Wf,maxTOwhere: EImaxTO,SAF and EImaxTO,FF are respectively the nvPM emissions index in mg / kg when operating around 100% available thrust for given operating conditions if fuel provided to fuel spray nozzles includes either sustainable aviation fuel (SAF) or fossil-based hydrocarbon fuel; Wf,maxTO is mass flow rate of fuel provided to fuel spray nozzles in kg / s when gas turbine engine is operating at around 100% available thrust for given operating conditions. MTO nvPM emissions index is less than 2. The gas turbine engine is configured to provide fuel including SAF to fuel spray nozzles. Also disclosed is method of operating gas turbine engine.

The invention relates to the technical field of digital pump operation control, in particular to a digital pump operation method and system, and provides the following scheme that winding temperature gradient distribution, axial strain and cooling liquid dielectric property parameters are collected and input into a preset finite element thermal model, boundary conditions are corrected by adopting an adjoint matrix method, and the temperature gradient distribution, the axial strain and the cooling liquid dielectric property parameters are obtained. And reconstructing a three-dimensional transient heat flux density field to realize precise positioning of a local overheating area. Contribution of a heat source item to a temperature field is calculated based on sensitivity analysis, a heat flow density field is optimized in combination with the Fourier law, and calculation precision is improved. The device is suitable for the fields of urban water supply, petrochemical engineering, aviation fuel pumps and the like, the heat management precision of equipment can be improved, the service life is prolonged, and the operation efficiency is improved.

The invention discloses a production method and a production device of an energy-saving sustainable aviation fuel, and the production method comprises the following steps: S1, adsorbing carbon dioxide in air by using an adsorbent, desorbing through high-temperature carrier gas, and cooling and compressing the desorbed carbon dioxide; s2, carbon dioxide and deionized water are preheated and then electrolyzed, and synthesis gas and oxygen are generated; s3, after the synthesis gas is compressed, performing Fischer-Tropsch reaction to generate a mixture of Fischer-Tropsch oil wax, light hydrocarbon and water, cooling and separating, and returning the Fischer-Tropsch reaction heat to preheat the synthesis gas; s4, pressurizing the Fischer-Tropsch oil wax, mixing the Fischer-Tropsch oil wax with hydrogen, carrying out hydrofining reaction to generate a gas-liquid isomerous oil-gas mixture, cooling and separating, and recycling heat energy of a product to And S5, after gas-liquid separation, preheating a liquid phase, carrying out rectification operation, separating and cooling to obtain a sustainable aviation fuel product. By recovering the heat in each link, the heat is efficiently utilized, and the energy-saving performance of production is improved.

The invention relates to the technical field of hydrogen energy aviation, and discloses a hydrogen energy aviation fuel storage-supply system and method based on solid hydrogen storage, and the hydrogen energy aviation fuel storage-supply system and method based on solid hydrogen storage are characterized in that the hydrogen release amount adjusting range of a hydrogen storage material is matched with the hydrogen fuel demand adjusting range of a power device by adjusting the hydrogen release catalytic reaction environment temperature of the solid hydrogen storage material; by adopting the pressure stabilizing device, the problem of flow and pressure fluctuation caused by hysteresis of hydrogen release adjustment is solved, and hydrogen release flow adjustment and engine throttling control can be carried out through the thrust rod.

The invention discloses a reaction condition optimization control method and system for biological aviation kerosene production, and particularly relates to the field of biological aviation kerosene production. The method comprises the following steps: firstly, acquiring parameters such as temperature, pressure, flow, catalyst activity and raw material components of biological aviation kerosene in real time through a sensor module consisting of a temperature sensor, a pressure sensor, a flow sensor and the like, and then carrying out pretreatment operations such as median filtering and wavelet denoising on acquired data; constructing an LSTM-Transformer hybrid model based on the preprocessed data to predict the second-by-second value of each parameter in the future 10 minutes, correcting the predicted value according to a catalyst activity index formula, further optimizing the prediction model by using a shadow model, comparing the predicted value with a preset interval and a threshold value, judging the state of the predicted value, and determining the second-by-second value of each parameter in the future 10 minutes. And finally, generating a fixed fine-tuning, strengthening or emergency control strategy according to a judgment result. According to the method, the biological aviation kerosene production reaction conditions can be accurately predicted, regulated and controlled, and the production stability, safety and product quality are improved.

A propulsion system including: a fuel cell assembly having a fuel cell defining an outlet positioned to remove output products from the fuel cell and a fuel cell assembly operating condition; a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the combustion section configured to receive a flow of aviation fuel from an aircraft fuel supply and further configured to receive the output products from the fuel cell; and a controller comprising memory and one or more processors, the memory storing instructions that when executed by the one or more processors cause the propulsion system to perform operations including receiving data indicative of a mid-flight flameout within the combustion section; modifying the fuel cell assembly operating condition in response to receiving data indicative of the mid-flight flameout within the combustion section; and initiating a relight of the combustion section.

The invention relates to a manufacturing method of high-density aviation fuel, in particular to an aviation fuel mixture based on monoterpenoids and a preparation method of the aviation fuel mixture. Comprising monoterpenoids, polyhydric alcohols and a catalyst which serve as raw materials, and the mass ratio of the raw materials to the polyhydric alcohols is 1: 1. The conversion rate is high, the treatment steps are reduced, the thermal stability and combustion gravimetric heat of the product are improved, and the method is suitable for preparing aviation fuel with high density, low viscosity and low-temperature performance; cyclization and hydrogenation are carried out through a one-pot method, a reaction container does not need to be transferred, and the operation is simple; according to the polyol solvent system, cyclization of the monoterpenoids becomes easier due to participation of polyol, and the conversion rate is increased; according to the dual-catalyst system, a combination of an acidic catalyst and a heterogeneous hydrogenation catalyst is used in a reaction container, so that efficient dehydration and hydrogenation reactions are ensured; the aromatic compound content in the fuel can be controlled by adjusting hydrogenation conditions.

The invention provides a low-pressure hydroisomerization / cracking process for preparing bio-based aviation fuel, and relates to the technical field of biomass energy. A three-stage hydrogenation process is adopted, a low-temperature and low-pressure homogeneous hydrogenation method combining an oil soluble catalyst with a suspended bed reactor A and a suspended bed reactor B is adopted in the front stage of step (1) and step (2), low-cost hydrogenation upgrading pretreatment is conducted on high-silicon and high-metal biomass inferior grease, deep fixed bed hydrofining is conducted in the middle stage of step (1) and step (2), and high-silicon and high-metal biomass inferior grease is obtained. In order to improve the yield of light oil products, a rear-section fixed bed hydroisomerization reactor is additionally arranged to carry out isomerization / cracking processing on heavy components.

Provided herein are systems and methods for converting CO2 and a reduction gas, such as H2 or a hydrocarbon, using a reduction catalyst and an aromatic catalyst into mixtures of paraffins, and aromatics for use as aviation fuel. The reduction catalyst and aromatic catalyst, and systems and methods incorporating the same, provide advantages over other methods in the art related to increased yield, catalyst stability and longevity.

The invention discloses an intelligent aviation fuel optimization method and related equipment, and the method comprises the steps: constructing an aviation fuel consumption prediction model which is used for predicting the fuel consumption of each leg, and providing basic data for the subsequent refueling optimization calculation; a mathematical optimization method is adopted, the minimum fuel cost and the minimum fuel consumption serve as optimization objectives, and the optimal refueling amount of each leg is calculated; iterative optimization is carried out through a gradient descent algorithm, and an optimal refueling scheme is solved on the premise that preset constraint conditions are met. According to the method, a feasible fuel optimization scheme can be provided with higher precision and lower calculation cost by combining data-driven intelligent prediction and a mathematical optimization algorithm. Compared with a traditional method, the method can adapt to changes of different air routes, weather and market environments, and an airline company can make an aviation oil filling plan more flexibly and efficiently. The method can be widely applied to the aviation oil management field.

The invention discloses an aviation fuel gear pump performance prediction method based on lumped parameters. The method comprises the following steps: 1, dividing internal control volumes of the gear pump and analyzing communication relations of the control volumes; 2, establishing a gear pump dynamic mathematical model by combining the internal pressure and flow characteristics of the gear pump and the geometric structure characteristics of the gear pump; step 3, establishing a gear pump 3D model based on UG and measuring related data, storing the data in a 1D table as the input of a gear pump Amesim lumped parameter model, and simulating the change relation of the gear cavity volume and the area of each throttling channel along with the rotation of the gear pump; and 4, establishing a gear pump lumped parameter performance model based on Amesim, inputting data according to oil liquid characteristics and the gear pump 3D model, setting corresponding parameters, performing gear pump multi-working-condition performance simulation, and analyzing and predicting pressure characteristics and flow characteristics of the gear pump under different working conditions. According to the method, a gear pump lumped parameter performance model is built based on Amesim modeling software and UG geometric modeling software, so that the internal flow pressure characteristic and the output pressure flow characteristic of the gear pump are predicted.

The invention relates to the technical field of filtering devices, and particularly discloses a sustainable aviation fuel raw material treatment device and method.The sustainable aviation fuel raw material treatment device comprises a barrel, a filtering mechanism and a cleaning mechanism, the filtering mechanism comprises a plurality of filtering assemblies and a first driving structure, and each filtering assembly comprises two filtering plates and a hinge shaft; the two filter plates are hinged to the hinge shafts through first torsional springs correspondingly, every two adjacent filter assemblies can abut against each other, the interior of the barrel is divided into a pre-filter cavity and a post-filter cavity, the cleaning mechanism comprises a back-flushing assembly and a collecting assembly, and the back-flushing assembly comprises an adjusting rod and a second driving structure. The adjusting rod is used for driving the two filter plates in the same group to reversely rotate around a hinged shaft and are arranged in a V shape, the collecting assembly comprises a scraping plate and a third driving structure, filter holes are densely distributed in the scraping plate, and an impurity collecting groove is formed in the lower end of the scraping plate; when the filter plate is blocked, the filter plate can be subjected to back-flushing cleaning through the back-flushing assembly, washed impurities are collected through the collecting assembly, and the separation effect is guaranteed.

The anti-leakage airplane oil pumping connector structure comprises a positioning base, the positioning base is movably embedded into an airplane oil well mouth, the positioning base is integrally formed by a cambered surface concave part and a positioning ring part, a positioning oil return mechanism is fixedly installed above the positioning ring part, and the positioning oil return mechanism and an oil well oil pipe are movably installed. An installation top ring face is arranged at the top end of the arc-face concave portion, an organ protective cover is fixedly installed on the installation top ring face, and a protective buckle plate is installed on the top of the organ protective cover in a hinged mode. Then, a positioning oil return mechanism and an organ protective cover are matched to perform protective covering on the connecting part of the oil pumping pipe and the wellhead of the oil well, aircraft fuel oil leaked from the oil pumping connecting part can flow back into the oil well through matching of an arc-surface concave part of the positioning base, a first backflow through hole and a second backflow through hole, and aviation fuel oil resources are saved; meanwhile, aviation is prevented from polluting the periphery of the wellhead.

A gas turbine engine for an aircraft. The gas turbine engine comprising: a rich burn, quick quench, lean burn (RQL) combustor having a number of fuel spray nozzles in the range of 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. A first idle-MTO nvPM emissions index ratio is defined as:EIidle / EImaxTO where: EIidle is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 7% available thrust for given operating conditions; and EImaxTO is the system loss corrected nvPM emissions index in mg / kg of the gas turbine engine if operating at around 100% available thrust for the given operating conditions. The first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 0.8. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the fuel spray nozzles. A method of operating the gas turbine engine is also disclosed.

The invention relates to the technical field of sustainable aviation fuel preparation processes, and discloses a process for producing sustainable aviation fuel by capturing carbon dioxide of an industrial boiler with an industrial byproduct hydrogen, which comprises the following steps: S1, raw material pretreatment; s2, converting hydrogen and carbon dioxide in the raw materials into Fischer-Tropsch synthesis gas by using a catalyst; s3, converting the Fischer-Tropsch synthesis gas obtained in S2 into liquid alkane; s4, the liquid alkane obtained in S3 is subjected to hydroisomerization to generate sustainable aviation fuel, industrial by-products of hydrogen and carbon dioxide can be converted into the sustainable aviation fuel through the steps of Fischer-Tropsch synthesis, hydroisomerization and the like, the fuel can serve as a substitute of petroleum fuel, dependence on traditional petroleum resources is reduced, and the sustainable aviation fuel is obtained. According to the invention, not only can sustainable aviation fuel be produced, but also light products (C5-C8 alkanes) and heavy products (C16-C24 alkanes) can be generated, and the light products and the heavy products can be respectively used for further Fischer-Tropsch synthesis reaction and can be sold as automotive second-generation biodiesel.

A gas turbine engine has a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. A combustor is operable with the first subset of fuel spray nozzles supplied with fuel at a greater fuel flow rate than each the second subset of fuel spray nozzles. A a ratio of the first subset of fuel spray nozzles to the second subset of fuel spray nozzles is 1:2 to 1:5. A first idle-MTO nvPM emissions index ratio is:EIidleEImaxTOwhere: EIidle is the system loss corrected nvPM emissions index in mg / kg operating at around 7% available thrust; and EImaxTO is the system loss corrected nvPM emissions index in mg / kg operating at around 100% available thrust; and the first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 60. A sustainable aviation fuel (SAF) can be provided to the fuel spray nozzles.

The invention relates to the technical field of aero-engine turbine blade cooling, and discloses an aero-engine turbine blade cooling structure and a pre-cooling method.The aero-engine turbine blade cooling structure comprises an inner wall and an outer wall which are of a double-layer structure, the inner wall is arranged in the outer wall, the inner wall comprises a wall face, and a plurality of impact holes are formed in the wall face in parallel in a penetrating mode; a plurality of cooling channels are arranged in the wall surface in parallel; the cooling channels are arranged among the impact holes; each cooling channel comprises an inlet end and an outlet end; the inlet end is connected with a fuel oil system and is used for feeding fuel oil into the cooling channel; the outlet end is connected with a fuel oil system and used for discharging fuel oil in the channel to the fuel oil system. The diameter of the cooling channel is within 1mm; and a plurality of air film holes are formed in the outer wall. Cooling gas in the turbine is pre-cooled through aviation fuel, so that the cooling effect of the turbine is further improved.

A gas turbine engine has a first subset of fuel spray nozzles and a second subset of fuel spray nozzles. A combustor is operable with the first subset of fuel spray nozzles supplied with fuel at a greater flow rate than each of the second subset of fuel spray nozzles. A ratio of the first subset of fuel spray nozzles to the second subset of fuel spray nozzles is 1:2 to 1:5. A first idle-MTO nvPM emissions index ratio is:EIidleEImaxTO,where: Elidle is the nvPM emissions index in mg / kg operating at around 7% available thrust; ElmaxTO is the nvPM emissions index in mg / kg of the gas turbine engine operating at around 100% available thrust; and the first idle-MTO nvPM emissions index ratio of the gas turbine engine is less than 60. A sustainable aviation fuel (SAF) can be provided to the fuel spray nozzles.

The present invention provides a method for producing synthetic fuel from water and carbon dioxide. The method includes the steps of (a) preparing water-derived hydrogen, (b) preparing carbon dioxide, (c) introducing the hydrogen and carbon dioxide into a first reaction to produce a first product comprising synthesis gas, (d) introducing the synthesis gas into a second reaction to produce a second product comprising syncrude, (e) dividing the syncrude oil into a plurality of fractions comprising a first fraction, (f) introducing at least one fraction of the plurality of fractions into a hydrogenation reaction to produce a third product, and (g) recovering a fraction corresponding to a boiling point range of the first fraction from the third product. The present invention also provides an aviation fuel produced by the method.

The invention relates to the technical field of mixing, and specifically discloses a mixing device for sustainable aviation fuel, comprising an axle rotatably arranged in a container, wherein a plurality of mixing components are arranged in sequence from top to bottom in the container, wherein the mixing component comprises an inner ring, an outer ring, and a mixing piece fixedly arranged between the outer side of the inner ring and the inner side of the outer ring, wherein a material cavity for loading a catalyst is arranged in the mixing piece, two shielding plates are slidably arranged on the mixing piece, a rack matched with the shielding plates on the mixing piece is slidably arranged on the inner ring, a driving rod is coaxially slidably arranged on the axle, and a driving assembly corresponding to the mixing assembly one by one is arranged on the driving rod, when the driving rod rotates and the driving rod moves upward at equal intervals intermittently, a plurality of inner rings can rotate in sequence from bottom to top, a plurality of annular cavities can be connected with a filling ring in sequence, and then a plurality of inner rings can rotate together and the filling ring is blocked by the driving rod, and the invention is conducive to uniformly mixing waste grease and glycerin, and improving the mixing efficiency with the catalyst.

The invention discloses a sustainability evaluation method and system for continuous aviation fuel, and relates to the technical field of high-efficiency energy-saving engineering evaluation service. The method comprises the following steps: acquiring carbon footprint data of a sustainable aviation fuel SAF in raw material acquisition, product production, transportation and use stages, and constructing a full-life-cycle carbon footprint dynamic model and a distributed carbon footprint database in combination with an LCA industry database; updating the carbon emission factor in real time, and calculating the carbon emission result of the SAF in combination with the process parameters of each manufacturing process; determining environmental income deduction of waste regeneration, landfill treatment and energy recovery by adopting a regeneration cycle carbon emission allocation algorithm; and generating a sustainability evaluation report including a fossil source, a biological source, land utilization change, resource consumption intensity and a waste treatment environmental effect according to the environmental income deduction and carbon emission result. According to the method and the device, the integrity and the accuracy of the sustainability evaluation of the SAF are improved.

Embodiments of systems and methods to produce aviation fuel are disclosed. An example of a method to produce aviation fuel includes fractionating a renewable diesel feedstock in a fractionator to produce a C8− fraction, a C8-18 fraction, and a C18+ fraction. Additionally, the method includes providing the C8-18 fraction to an isomerization reactor to produce an aviation fuel product. The method includes supplying at least a portion of the C18+ fraction to a hydrocracking reactor to produce a hydrocracked product. The method further includes recycling at least a portion of the hydrocracked product to the fractionator for fractionating along with the renewable diesel feedstock.