498 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 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 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.

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.

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.

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 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.

A gas turbine engine for aircraft includes a combustor with a combustion chamber and fuel spray nozzles to inject fuel into the combustion chamber. The fuel spray nozzles include a first subset and a second subset of nozzles. Each of the first subset is supplied with fuel at a greater rate than each of the second subset. A ratio of the first subset to the second subset is 1:2 to 1:5. A MTO nvPM emissions index ratio isEImaxTO,SAFEImaxTO,FF.EImaxTO,SAF is nvPM emissions index in mg / kg of the engine when operating at around 100% available thrust if fuel provided to the fuel spray nozzles includes sustainable aviation fuel. EImaxTO,FF IS nvPM emissions index in mg / kg of the engine when operating at around 100% available thrust if fuel provided to the fuel spray nozzles is fossil-based hydrocarbon fuel. The MTO nvPM emissions index ratio is less than 1.

The invention relates to a heterogeneous catalysis technology, and aims to provide a method for improving the yield of components of aviation kerosene prepared by ethylene oligomerization through combination of a fixed bed and a slurry bed. Comprising a fixed bed reactor and a slurry bed reactor which are sequentially connected in series, the fixed bed reactor is filled with a metal modified mesoporous zeolite molecular sieve catalyst, and the slurry bed reactor is filled with a mesoporous zeolite molecular sieve catalyst. The method comprises the following steps: firstly, carrying out ethylene oligomerization reaction in a fixed bed reactor to generate a product containing C4-C8 olefin; the reaction product is directly introduced into the fixed bed reactors connected in series for secondary reaction, and the final product comprises C5-C16 + liquid phase olefin as an aviation fuel component. By adopting a fixed bed-slurry bed reactor combined method, the ethylene conversion rate can be greatly improved; secondary oligomerization is carried out by using an acidic mesoporous zeolite molecular sieve catalyst, so that the selectivity of aviation kerosene components is improved; the mesoporous catalyst prepared by an alkali treatment method has a good diffusion effect and keeps high activity for a long time.

The invention discloses an aviation fuel gear pump confidence degree evaluation method based on the Bayesian theory. The method comprises the following steps: step 1, firstly, determining Weibull distribution as a theoretical basis of reliability modeling according to the life characteristics of the aviation fuel gear pump, and providing probability model support for subsequent analysis; 2, on the basis of Weibull distribution, adopting a Bayesian method to fuse historical data and field test data, and achieving point estimation and interval estimation of shape parameters and scale parameters of the aviation fuel gear pump; and step 3, based on the point estimation and the interval estimation, constructing an MTBF confidence interval and verifying by adopting a Bootstrap method, and finally completing quantitative evaluation of the reliability confidence of the aviation fuel gear pump. According to the method, the specific problems of low evaluation precision, poor confidence interval reliability and insufficient historical data utilization rate of a traditional method under the small sample condition are solved.

The invention discloses an aviation fuel gear pump service life estimation method based on gear failure, and relates to the technical field of gear pump service life estimation. Combining the smoke scattering spectrum, the gear material parameters and the Hertz contact theory to calculate the dynamic contact stress of the gear surface, and constructing a multi-physical field data set; extracting a polarization degree, a polarization angle, a stress change rate and a smoke concentration variable quantity from the multi-physical field data set to generate a node feature vector sequence; and fusing the dynamic graph embedded vector with the corrected Hertz contact item and Archard wear item to construct a physical constraint neural differential equation. According to the method, a corrected Hertz contact item and an Archard wear item are rigidly embedded into a neural differential equation, and a state evolution trajectory is iteratively generated by using a Dorman-Prince solver, so that the model is ensured to conform to a data driving rule and a physical conservation constraint at the same time.

The invention discloses a preparation method of a catalyst for hydrogenation of CO2 to sustainable aviation fuel (SAF). The catalyst stabilizes FeCx active sites through carbon species, and comprises the following steps: (a) carbon nanotubes, activated carbon, glucose or polyol are used as a carbon source, (b) FeMn, FeZn or FeGa are used as active sites, and (c) alkali metal Li, Na or K is used as an auxiliary agent to promote adsorption of CO2. According to the catalyst, active metal is deposited on carbon species through a coprecipitation method, and the catalyst prepared through the synthesis method not only can weaken oxidation of H2O on FeCx active sites, but also is beneficial to increase of carbon chains to promote CO2 hydrogenation to generate aviation fuel with high selectivity. The invention discloses a preparation method of a high-stability Fe-based catalyst for hydrogenation of CO2 to SAF.

The invention relates to the technical field of biological aviation kerosene, and discloses a process for preparing biological aviation kerosene from waste grease. The method comprises the following steps: introducing waste oil into a hydrofining reactor, introducing hydrogen, carrying out a hydrodeoxygenation reaction under the catalysis of a hydrogenation catalyst, carrying out a reaction on the obtained hydrodeoxygenated oil in an isomerization pour point depressing reactor, and finally carrying out isomerization hot high-pressure separation treatment, isomerization cold high-pressure separation treatment and rectification tower segmentation to obtain the biological aviation kerosene. The specific surface area of a carbon matrix of the hydrogenation catalyst is large, the void structure is rich, a large number of Ni-Mo-P active catalytic centers can be exposed, precious metals such as platinum and ruthenium do not need to be added, the hydrodeoxygenation reaction efficiency of waste oil and fat is remarkably improved, the mass fraction of branched paraffin and cycloparaffin in biological aviation fuel is high, and the combustion performance is better.

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 fuel-flow nvPM emissions index ratio is defined as:E⁢Iidle×Wf,idleE⁢ImaxTO×Wf,maxTOwhere: EIidle is the 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 nvPM emissions index in mg / kg of the gas turbine engine if operating at around 100% available thrust for the given operating conditions; Wf,idle is the rate of fuel flow to the fuel spray nozzles in kg / s at around 7% available thrust for the given operating conditions; and Wf,maxTO is the rate of fuel flow to the fuel spray nozzles in kg / s at around 100% available thrust for the given operating conditions. The fuel-flow nvPM emissions index ratio of the gas turbine engine is less than 0.3. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the plurality of fuel spray nozzles. Also disclosed are methods of operating a gas turbine engine.

The invention provides a self-adaptive planning aviation fuel cell extended range power system evaluation method and system, and belongs to the technical field of power system evaluation, and the method comprises the steps: constructing a state space model of an aviation fuel cell extended range power system, building a multi-stage decision model, solving a control strategy of each stage through a self-adaptive dynamic planning algorithm, and calculating the state space model of the aviation fuel cell extended range power system. Performing difference mining on each state difference matrix, and determining an incidence relation graph of state variables and control variables in the corresponding flight stage; acquiring current state data of the aviation fuel cell extended range power system in real time, adjusting optimization parameters of a control strategy in a corresponding stage to obtain an optimal strategy in combination with a state space model and an incidence relation graph, and dynamically adjusting output power of a fuel cell and a super capacitor in combination with a power distribution strategy; and when the power output margin is lower than a safety preset threshold value, an alarm signal is triggered. And the requirements of efficient and safe operation of the aviation fuel cell range extending system are met.

The invention discloses an aviation fuel gear pump performance prediction method based on lumped parameters, which relates to the technical field of aviation hydraulic simulation, and comprises the following steps: dividing fluid working cavities according to the geometric structure of a fuel gear pump, defining the flow exchange relation and the pressure change relation among the fluid working cavities, and establishing a coupling calculation path; forming a basic prediction model; the method comprises the following steps: extracting a biofuel blending ratio and a water content parameter according to a fuel component parameter input in real time, comparing the biofuel blending ratio and the water content parameter with a preset blending ratio threshold to trigger a corresponding correction rule, generating a compensation coefficient, and generating an elastic modulus parameter in combination with the water content parameter and the compensation coefficient; and inputting a preset working condition parameter and an elastic modulus parameter into the basic prediction model, calculating mass flow exchange data through the flow exchange relationship, driving the pressure change relationship to solve, and outputting an initial pressure distribution vector. Through the elastic modulus parameter dynamic generation step, the problem of physical property parameter static correction distortion under the variable component working condition is solved.

Embodiments of the present disclosure are directed to providing fuel emissions monitoring and / or management for an aerial vehicle. In an example, fuel consumption data and carbon emissions data for an aerial vehicle is determined. The fuel consumption data provides a comparison between (i) first fuel consumption data associated with a first type of aviation fuel being utilized by the aerial vehicle and (ii) second fuel consumption data associated with a second type of aviation fuel that is not being utilized by the aerial vehicle. The carbon emissions data is based on (i) volume data indicative of a real-time volume of the first type of aviation fuel, (ii) a first carbon emissions factor for the first type of aviation fuel, and (iii) a second carbon emissions factor for the second type of aviation fuel. In another example, a rendering of the fuel consumption data is caused via a display.

Processes for making aviation fuels include a step of forming a C16− olefin stream by oligomerizing a mixture of decenes with a C6− alpha-olefin or by subjecting the mixture of decenes and a C8− alpha-olefin to metathesis. The C16− olefin stream is then hydrogenated to form C16− paraffins, and these C16− paraffins can be used to form an aviation fuel. Particular C11-C16 olefin compositions and paraffin compositions prepared by these processes also are described.

A process for the production of sustainable aviation fuel (SAF) with low carbon intensity. The jet fuel is produced from the reaction of hydrogen from the electrolysis of water with captured carbon dioxide. The hydrogen and carbon dioxide are reacted to product a stream comprising carbon monoxide. Hydrogen and carbon monoxide are reacted to produce n-alkanes. Alkanes are hydroisomerized to produce sustainable aviation fuel with low carbon intensity.

The invention discloses an aircraft fuel centrifugal pump impeller parameterization design method, and relates to the technical field of aircraft fuel centrifugal pump impeller parameterization design, and the aircraft fuel centrifugal pump impeller parameterization design method comprises the steps that a point cloud conversion terminal carries out Poisson sampling on the surface of each impeller model, and a point cloud data set containing coordinates, normal vectors and curvatures is generated; in a physical constraint neural network architecture construction stage, a neural network terminal inputs working condition vectors and performance requirements into a PointNet + + encoder to extract global features, then geometric point cloud coordinates are generated by using Transform in combination with MLP, and eddy dynamics physical constraints including a vorticity intensity suppression item and a vorticity gradient constraint item are applied in training. According to the method, the multi-objective loss function combination is designed through the training optimization terminal, the point cloud geometric error, the fluid equation residual error and the performance index deviation are fused, multi-dimensional collaborative optimization of the geometric accuracy, the fluid mechanics compliance, the performance standard degree and the structural reliability of the impeller is achieved, and finally the aviation fuel centrifugal pump impeller with better comprehensive performance is obtained.

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 14-22 or a number of fuel spray nozzles per unit engine core size in the range 2 to 6. A fuel-flow nvPM emissions index ratio is defined as:EIidle×Wf,idleEImax⁢TO×Wf,maxTOwhere: 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; Wf,idle is the rate of fuel flow to the fuel spray nozzles in kg / s at around 7% available thrust for the given operating conditions; and Wf,maxTO is the rate of fuel flow to the fuel spray nozzles in kg / s at around 100% available thrust for the given operating conditions. The fuel-flow nvPM emissions index ratio of the gas turbine engine is less than 0.08. The gas turbine engine is configured to provide fuel comprising a sustainable aviation fuel (SAF) to the fuel spray nozzles. Also disclosed is a method of operating the gas turbine engine.