44 results about "Equivalence ratio" patented technology

The embodiment of the invention provides a prediction method and device for the outlet temperature of an aero-engine combustion chamber, computer equipment and a medium, and relates to the technical field of performance evaluation and prediction.The method comprises the following steps that input parameters related to combustion chamber operation and combustion chamber structure are collected in batches, an optimal parameter set is generated, and the optimal parameter set is stored; working condition vectors are constructed through combustion chamber working conditions; constructing a stable parameter set through the optimized parameter set and the working condition vector, screening all parameters in the stable parameter set, and adjusting weights corresponding to the parameters in the working condition vector through an adaptive weight model; and constructing a physical constraint coupling prediction model, training the physical constraint coupling prediction model based on the physical constraint, generating a trained physical constraint coupling prediction model, and outputting the unevenness of the temperature distribution of the outlet of the combustion chamber through the model. According to the scheme, high-precision prediction of the temperature distribution unevenness of the outlet of the combustion chamber can be realized under the conditions of different pressures, temperatures, equivalence ratios and the like.

The invention belongs to the technical field of hypersonic flight vehicle control, and particularly relates to an INDI-based flight and thrust integrated control method for a hypersonic flight vehicle. The method comprises the following specific steps: designing a vertical-direction-controlled flight-thrust integrated longitudinal dynamic model of the hypersonic aircraft, designing a trajectory guiding outer ring to realize height and speed tracking control, designing an attitude stabilizing outer ring to realize attack angle tracking control, constructing an attitude control inner ring to realize flight-thrust control of an acceleration level, and designing a flight-thrust model of the hypersonic aircraft. And designing an engine compensation layer to process dynamic delay of an actuator. Through the MIMO-INDI mechanism, the pneumatic / propulsion coupling effect is actively utilized, collaborative distribution of the fuel equivalence ratio of the elevator and the engine is achieved, and the comprehensive control performance of the aircraft is improved. The method is a flight / propulsion integrated control method and has a wide application prospect.

The present disclosure is directed to a supersonic oblique rotating detonation wave engine (SORDE) and systems and methods for generating a supersonic oblique rotating detonation wave. The SORDE is configured to produce and sustain a supersonic oblique rotating detonation wave through the injection of fuel at supersonic speeds into an inlet air flow between Mach 1 and Mach 7. The SORDE and method include injecting fuel into the inlet air in an amount to generate an equivalence ratio of 0.2 to 2.5. Some embodiments include a plurality of fuel injector ports each having a diameter of about 0.010 inches to about 0.040 inches; an annular wedge disposed in or upstream of the detonation chamber with an angle of about 5 degrees to about 40 degrees relative to a longitudinal axis of the engine; and / or a cylindrical center body disposed in or upstream of the detonation chamber.

The invention discloses a two-stage supporting plate injector applied to a wide-working-condition scramjet engine combustion chamber, belongs to the technical field of scramjet engines, solves the problem that an existing alternating supporting plate is low in fuel and air mixing efficiency under the conditions of a high Mach number and a high equivalence ratio, and comprises a supporting plate body. One end of the supporting plate body is a wedge-shaped tail edge formed by arranging a plurality of wedge-shaped slopes in a staggered mode, and first-stage fuel oil spraying holes are formed in the staggered points of the wedge-shaped slopes in the wedge-shaped tail edge. The two side faces of the supporting plate body are symmetrically provided with a plurality of second-stage fuel oil spraying holes inclined in the wedge-shaped tail edge direction. The first-stage fuel injection hole and the second-stage fuel injection hole form a two-stage fuel injection system, the fuel input mode is changed fundamentally, and the fuel flow ratio of the two-stage fuel injection system is dynamically adjusted according to different inlet Mach numbers and equivalence ratios, so that the two-stage support plate injector can be used in various working conditions, and the service life of the two-stage support plate injector is prolonged. And the optimal mixing efficiency can be realized through the optimal fuel distribution strategy.

A gas turbine engine includes a compressor section, a combustion section, and a turbine section in a serial flow arrangement wherein the combustion section includes: a combustor liner at least partially defining a combustion chamber; and a gaseous fuel nozzle assembly fluidly coupled with the combustion chamber and including: a rich fuel supply configured to provide a rich mixture of gaseous fuel and air; a lean fuel supply configured to provide a lean mixture of gaseous fuel and air, the lean mixture having a lower equivalence ratio than the rich mixture; a rich fluid passage fluidly coupled to the rich fuel supply to discharge the rich mixture into the combustion chamber; and a lean fluid passage fluidly coupled to the lean fuel supply to discharge the lean mixture into the combustion chamber.

The present invention relates to a method for controlling combustion speed through equivalence ratio stratification of an internal combustion engine using hydrogen fuel. By controlling the combustion speed, thermal efficiency can be improved by reducing heat transfer losses, heat transfer losses can be reduced and effective power can be generated by improving the initial combustion speed including the flame development period, and nitrogen oxide emissions can be reduced by lowering the overall average temperature of the combustion chamber.

A non-transitory, processor readable medium stores instructions that, when executed by a processor, causes the processor to receive (1) an indication of a feed gas flow rate measured between a feed gas source and an internal combustion engine (ICE) and (2) an indication of an oxygen enriched air flow rate measured between an air separation unit (ASU) and the ICE. A measured equivalence ratio is determined based on a feed gas composition, the feed gas flow rate, and the oxygen enriched air flow rate. The instructions further cause the processor to generate at least one of a first signal to cause a change in revolution speed of the ICE, a second signal to cause a first flow control device to modify the feed gas flow rate, or a third signal to cause a second flow control device to modify the oxygen enriched air flow rate.

The invention provides a method and a system for verifying oxygen sensor connection. Systems and methods for detecting and compensating for erroneous wiring of an oxygen sensor of a cylinder bank of an engine are disclosed. In one example, a fuel control parameter is monitored to determine whether the fuel control parameter diverges to a fuel control threshold. If so, the controller may switch to adjust which cylinder's equivalence ratio in response to the output of the particular oxygen sensor.

Systems and methods for detecting and compensating for incorrect wiring of lambda sensors on a cylinder bank of an internal combustion engine are disclosed. In one example, fuel control parameters are monitored to determine whether they diverge from fuel control thresholds. If so, a control unit can switch the cylinder equivalence ratios set in response to an output from a specific lambda sensor.

The application discloses a simulation method for energy storage container explosion relief safety verification, an electronic device and a storage medium. The simulation method comprises the following steps: performing geometric simplification processing on a simplified model to obtain the simplified model and a gas domain model of the simplified model; obtaining a fuel equivalence ratio of the simplified model according to the gas domain model of the simplified model, and performing explosion simulation processing on the simplified model according to simulation parameters and the fuel equivalence ratio to obtain a pressure characteristic parameter of the simplified model; and performing structure simulation processing on the simplified model according to the pressure characteristic parameter to obtain a structure damage degree of the energy storage container. In the simulation method, the structure damage degree of the energy storage container can be evaluated in a simulated manner, the evaluation accuracy of the explosion relief safety of the energy storage container is improved to a certain extent, potential safety hazards and environmental pollution can be avoided, and the cost can be reduced.

The invention discloses a diesel gasification device and a cyclic quantitative control method. The controller firstly preheats the heating piece and then controls the air inlet valve to be opened, so that air enters the mixing cavity through the air inlet pipe and the heating net, and the pressure in the cavity is adjusted to a preset pressure threshold upper limit Ptar1; the controller calculates the target fuel injection quantity of the liquid fuel injector according to the air state in the mixing cavity and the target equivalence ratio and controls the liquid fuel injector to complete fuel injection; the controller controls an oil and gas injection valve to be opened, an oil and gas mixture is injected till the lower limit Ptar2 of a preset pressure threshold value is reached, and after injection is finished, the controller calculates the residual air amount and the residual fuel oil amount in a mixing cavity based on the pressure, temperature and oxygen concentration detection signals after injection; and the controller opens the air inlet valve to supplement air to the mixing cavity until the pressure in the cavity reaches the pressure threshold upper limit Ptar1, then the air inlet valve is closed, the air supplement amount is determined according to the pressure difference before and after air supplement, and the needed oil supplement amount is calculated in combination with the target equivalence ratio. According to the invention, spray crushing and atomization are realized no longer depending on ultrahigh injection pressure.

The application discloses a material high-temperature hydrogen permeation simulation experiment device and experiment method based on a counter diffusion flame burner. Fuel enters a fuel cavity with horizontal initial momentum, is discharged after the initial momentum is weakened, and oxidant is vertically discharged with an initial speed and is distributed above the fuel gas flow, so that the fuel and the oxidant form a speed difference, the oxidant can form an entrainment effect on the fuel, the mixing of the oxidant and the fuel is promoted, the stability and heat release efficiency of the counter diffusion flame are improved, sufficient combustion and uniformity of flame temperature distribution are ensured, efficient and uniform mixing can be realized without a swirl generator, the structure of the counter diffusion flame burner is simplified, the equivalence ratio of the oxidant and the fuel can be adjusted by a data acquisition and control system to adjust the combustion state of the flame, so that the flame height, the temperature and the active free radical concentration are accurately controlled, the application scene of a sample is effectively simulated, various flame environments can be provided for performance experiments of the sample, and the experimental reliability is improved.

The application provides a working method of a low total temperature state of a hot jet experiment device of a shock wave wind tunnel, which utilizes the principles of stable combustion limit, ignition limit and high temperature ablation limit in a combustion process to determine the optimal ignition area of the equivalence ratio of hydrogen and air combustion; in combination with the operation time sequence of the hot jet experiment device, the equivalence ratio of hydrogen and air combustion is ignited under the working condition of the optimal ignition area, and the combustion chamber stably combusts under a high total temperature state; by reducing the equivalence ratio of hydrogen and air combustion within the lean oil ignition area range, the combustion chamber continues to stably combust under a low total temperature state. The hydrogen and air in the combustion chamber are ignited under the working condition of a large equivalence ratio and stably combust under a high total temperature state, then the flow of hydrogen and air is accurately adjusted to the working condition of a small equivalence ratio by an electronic pressure reducing valve, and the stable combustion under a low total temperature state is maintained, thereby solving the problem that the hot jet experiment device cannot work under a low total temperature state.

The invention discloses a hydrogen internal combustion engine injection control method based on pre-combustion chamber ignition, which comprises the following steps of: when a piston is positioned in a range of a crankshaft angle of 50-70 degrees before a compression top dead center, starting to inject hydrogen into a pre-combustion chamber; the hydrogen injection duration of the pre-combustion chamber is controlled to be smaller than a 5-degree crankshaft angle, and the equivalence ratio of the pre-combustion chamber during ignition is 0.8-1.2; when the piston is close to an upper dead center, a pre-combustion chamber spark plug is triggered to ignite, so that a pre-combustion chamber flame kernel is formed within a crankshaft angle of 1-5 degrees after ignition; flame of the pre-combustion chamber is sprayed into the main combustion chamber through the jet flow channel, multi-point ignition flame cores are formed in the main combustion chamber, and combustion of mixed gas formed by mixing hydrogen and air is promoted. And when the compression stroke is finished, hydrogen injection of the pre-combustion chamber is stopped, and the total injection duration angle does not exceed the 100-degree crankshaft angle before the lower dead center of the piston. According to the hydrogen internal combustion engine injection control method based on pre-combustion chamber ignition, by optimizing the time, duration and control strategy of pre-combustion chamber fuel injection and cooperating with a corresponding sensing and feedback adjusting mechanism, stable and rapid ignition and flame propagation of hydrogen lean combustion are achieved, and the combustion efficiency is improved. The lean burn limit is widened, NOx emission is reduced, and the heat efficiency of the engine is remarkably improved. The invention further discloses an engine system.

A combustion appliance 100 using a gaseous fuel, such as hydrogen, has a combustion unit 120 for burning a combustible air-gas mixture 131. An air-gas mixing unit 110 is arranged upstream of the combu

On the basis of a relationship between the rate of non-burning of fuel and an equivalence ratio, the present invention: determines a limit equivalence ratio that serves as a target of the equivalence ratio and is derived from an upper limit value of the rate of non-burning in accordance with the oxygen content actually detected from fuel used in an internal combustion engine; establishes a target value for the oxygen concentration of an intake manifold so as to achieve the limit equivalence ratio; and controls an EGR rate so as to achieve the target value.

The present application relates to the technical field of low pollution combustion of ammonia-doped fuel, in particular to a low pollution stable combustion regulation method of ammonia-doped fuel based on carbon-nitrogen separation combustion organization, which comprises fuel grading supply, wherein carbon-hydrogen fuel such as CH4, coal powder and NH3 are injected into a combustion zone in layers through independent channels, wherein NH3 can be injected from the center of a burner, and carbon-hydrogen fuel is distributed in the outer layer of NH3, and mixing is realized through the action of swirl shear; air grading combustion, wherein a main air path and a secondary air path are set, the main air path adopts rich premixing, and the secondary air path supplements air to realize grading combustion; NH3 pre-decomposition treatment, wherein part of NH3 is pre-decomposed during combustion, and the pre-decomposition rate is controlled at 20%-40%; carbon-nitrogen path separation is realized through fuel layer injection, and reduction intermediates are generated by combining NH3 pre-decomposition, thereby synergistically inhibiting NO x generation and CO emission, and equivalence ratio is dynamically regulated based on a Damkohler number cross-scale model, so that industrial application is realized.

The invention discloses a medium-calorific-value synthesis gas nozzle for a light gas turbine, a swirler, a nozzle-swirler assembly, a combustion chamber and the gas turbine. The nozzle comprises a nozzle main body and a nozzle head; the nozzle head comprises a cylindrical part and a circular truncated cone part which are connected in sequence; a plurality of rows of fuel spray holes are formed in the conical surface of the circular truncated cone part, a V-shaped end part arranged inwards is arranged on the upper bottom surface, and a central spray hole is formed in the middle of the circular truncated cone part. The swirler comprises a sleeve and swirling vanes, an inner cavity at the front end of the sleeve is a slow expansion section, an inner cavity at the rear end of the sleeve is a sudden expansion section, and the slow expansion section and the sudden expansion section jointly form a trumpet-shaped inner cavity. The swirl nozzle head with multiple densely distributed spraying holes is combined with the trumpet-shaped swirler sleeve, a high equivalence ratio area near the nozzle and a high flow speed area at the downstream of the nozzle can be built, and therefore nozzle ablation, synchronous swirling of fuel and air and sudden expansion flow guiding of the sleeve are avoided, and interference of the large flow characteristic of medium-heat-value fuel on swirling can be reduced; and the backflow intensity and the fuel-air mixing uniformity are obviously improved, so that the combustion is stable.

The present application belongs to the technical field of hypersonic vehicle control, and particularly relates to a hypersonic vehicle flight-propulsion integrated control method based on INDI. The specific steps include: establishing a hypersonic vehicle flight-propulsion integrated longitudinal dynamics model in the form of a wall, designing a trajectory guide outer loop to realize height and speed tracking control, designing an attitude stabilization outer loop to realize angle of attack tracking control, constructing an attitude control inner loop to realize flight-propulsion control at the acceleration level, and designing an engine compensation layer to handle actuator dynamic delay. The present application actively utilizes the aerodynamic / propulsion coupling effect through the MIMO-INDI mechanism to realize collaborative distribution of elevators and engine fuel equivalence ratio, thereby improving the comprehensive control performance of the vehicle. The method is a flight / propulsion integrated control method, and has a wide application prospect.

The invention provides an externally-attached multifunctional plasma flame stabilizer, and relates to the technical field of plasma ignition combustion supporting. Comprising an evaporative flame stabilizer and an externally-attached exciter. The evaporative flame stabilizer is provided with a combustion area defined by apron boards, and the apron boards are provided with notches penetrating through the inside and the outside. And the externally attached exciter is embedded into the notch. According to the design, on the premise that the aerodynamic shape and the internal flow field of the flame stabilizer are not changed, high integration of the ignition function and the flame stabilizing function is achieved, occupation of the combustion area space and interference of main airflow are avoided, and the device compactness and the engineering applicability are improved. A gliding arc discharge plasma exciter is adopted, non-equilibrium plasmas can be generated under the atmospheric pressure and act on a backflow area, ignition reliability is enhanced, fuel atomization and evaporation are promoted, the ignition boundary is expanded, flame quenching is restrained, the device is suitable for poor working conditions such as low equivalence ratio, low temperature, low pressure or high flow speed, and jump from passive flame stabilization to active intensified combustion is achieved.

The application discloses a method for identifying SDPF damage, and relates to the technical field of engine aftertreatment systems, and solves the technical problem that the existing installation of differential pressure sensors before and after the SDPF is prone to false positives or false negatives. The method comprises the following steps: acquiring a theoretical NOx conversion efficiency value, a measured NOx conversion efficiency value and a urea / NOx equivalent ratio value, and calculating an efficiency deviation value of the theoretical NOx conversion efficiency value and the measured NOx conversion efficiency value; comparing the urea / NOx equivalent ratio value with a set equivalent ratio limit value, and comparing the efficiency deviation value with a preset efficiency limit value; and when the urea / NOx equivalent ratio value is greater than or equal to the equivalent ratio limit value and the efficiency deviation value is greater than or equal to the efficiency limit value, an SDPF damage fault alarm is performed. The application reduces the influence of the damage position and shape of the SDPF on a single sensor, and reduces the risk of sensor identification errors through comparison of multiple related parameters.

This application relates to an ammonia internal combustion engine system and its control method, belonging to the field of internal combustion engines. The ammonia internal combustion engine system includes an ammonia supply device, an ammonia decomposition device, an engine block, and an ignition device. The ammonia supply device includes an ammonia injector for supplying ammonia. The ammonia decomposition device includes a catalyst for decomposing ammonia into nitrogen and hydrogen. The engine block includes a main combustion chamber. The ignition device is partially located within the main combustion chamber. The control method for the ammonia internal combustion engine includes controlling the total ammonia flow rate to 20–23 L / min, simultaneously controlling the ammonia decomposition rate in the ammonia decomposition device to 50–60%, and controlling the equivalence ratio to 1.05–1.23. This control process prioritizes power characteristics while also considering good burnout and emission characteristics. It not only provides a reference for the design and application of ammonia internal combustion engines but also represents a practical control method for ammonia internal combustion engines.

The present application relates to a kind of sliding arc plasma supported oil and gas cascade ignition combustion exciter, belong to plasma ignition combustion field.The exciter includes primary component, gas inlet component and secondary component;Primary component includes shell cathode, inner cathode located in shell cathode, anode spaced in inner cathode and insulator located between anode and inner cathode, shell cathode is equipped with gas guide pipe, gas guide pipe is communicated between shell cathode and inner cathode, anode and inner cathode are equipped with and spaced gap communication, gas inlet component includes sliding arc precombustion cavity, its outside is equipped with fuel atomization cavity, and the fuel atomization cavity is formed between the two, shell cathode extends into sliding arc precombustion cavity, and sliding arc precombustion cavity and gap are communicated;Secondary component includes secondary cavity, and fuel atomization cavity is located in one end of secondary cavity.In the present application, the flow of fuel in oil and gas is adjusted to realize the switching of exciter between different working modes, so that the exciter can work normally in a wider equivalence ratio range.

This application provides a fuel supply device belonging to the field of aero-engine technology. It includes an ignition nozzle, a general nozzle, a main fuel line manifold, and an auxiliary fuel line manifold. The auxiliary fuel line manifold has a semi-annular structure and connects to multiple auxiliary fuel line branches. The main fuel line manifold has a full-annular structure and connects to multiple main fuel line branches. The ignition nozzle is connected to both the auxiliary and main fuel line branches, and the general nozzle is connected to the main fuel line branches. The ignition nozzle has an internal ignition structure. Both the ignition nozzle and the general nozzle have main and auxiliary fuel lines. When the engine speed increases from the start-up state to low operating conditions, only the auxiliary fuel line manifold supplies fuel. As the engine speed increases, the auxiliary and main fuel line manifolds supply fuel simultaneously. The main fuel line equivalence ratio of the ignition nozzle and the general nozzle is equivalent, and the auxiliary fuel line equivalence ratio of the ignition nozzle and the general nozzle is equivalent. This application's solution improves fuel atomization quality under low operating conditions and widens the ignition and shutdown boundaries.

The invention discloses a material high-temperature hydrogen permeation simulation experiment device and method based on a reverse diffusion flame burner, fuel enters a fuel cavity with horizontal initial momentum and is discharged after the initial momentum is weakened, and an oxidant is vertically discharged at an initial speed and is distributed above fuel airflow, so that a speed difference is formed between the fuel and the oxidant; the oxidant can form an entrainment effect on fuel so as to promote mixing of the oxidant and the fuel, improve stability and heat release efficiency of reverse diffusion flames and ensure sufficient combustion and flame temperature distribution uniformity, meanwhile, efficient and uniform mixing can be achieved without a rotational flow generator, the structure of the reverse diffusion flame burner is simplified, and the cost is reduced. The data acquisition and control system can adjust the equivalence ratio of the oxidant to the fuel so as to adjust the combustion state of the flame, so that the flame height, the temperature and the active free radical concentration are accurately controlled, the application scene of the sample is effectively simulated, various flame environments can be provided for the performance experiment of the sample, and the experiment reliability is improved.

This invention discloses a comprehensive and detailed reaction mechanism for natural gas / air and its development method. The comprehensive and detailed reaction mechanism includes 290 gas-phase components and 3339 gas-phase elementary reactions, 1 bulk component and 2 surface sites, and 56 soot particle surface reactions. This invention is based on the IDT of chain alkane oxidation, the concentration distribution of small-molecule gas-phase components and large-molecule PAHs of soot nucleation precursors in fuel-rich BSF ethylene flames, the distribution characteristics of soot SVF and PND in fuel-rich BSF and CDF ethylene flames, and the NO content of BSF methane flames under different equivalence ratios. x NO concentration distribution and the reaction of syngas / ammonia in different lean combustion atmospheres x A multidimensional validation study of PK_CNS was conducted, comparing various aspects such as concentration change characteristics. Based on the high consistency between predicted and experimental values, the excellent predictive performance of PK_CNS was verified, and it can be extended to describe the combustion process of natural gas in flame-heated furnaces.

The application discloses a combustion chamber nonlinear stability prediction method based on multi-input thermoacoustic disturbance modeling, which is used for evaluating the thermoacoustic stability of combustion chambers of aeroengines, gas turbines and the like. The method is characterized in that: geometric, operation and analysis parameters are input first, and then the cooling flow distribution is calculated; the effective equivalence ratio, the heat release rate and the temperature field are calculated, and the acoustic modal frequency is calculated; the MISO transfer function of the equivalence ratio and the inlet flow double disturbance is constructed, and the FTF curve is generated; the oscillation is determined through a limit cycle detection algorithm, the saturated heat release rate is calculated by calling the Tanh / PowerLaw model, and finally the results are visualized. The application realizes multi-factor coupling precise modeling, can be involved in the early stage of design, and only needs several minutes for calculation, so that the prediction accuracy and efficiency are improved, the research and development cost is reduced, and the safety of the combustion chamber is ensured.

A method for controlling a two-stroke engine assembly having a two-stroke internal combustion engine (ICE) having first and second cylinders; and an exhaust system fluidly. The exhaust system has a tuned pipe and a catalytic converter. The method having the steps of: sensing in the exhaust system, with a lambda sensor, a first combustion air-fuel equivalence ratio (λ) and a second combustion λ, the first and second combustion λ's being subsequent combustion λ's of different ones of the first and second cylinders; determining, by an engine control unit (ECU), a difference between the first and second combustion λ's; and in response to the difference between the first and second combustion λ's being greater than a predetermined λ, modifying an air-fuel ratio in at least one of the first and second cylinders to reduce the difference between the first and second combustion λ's below the predetermined λ.

A gas turbine engine, comprising a compressor section, combustion section, and turbine section in serial flow arrangement, with the combustion section comprising: a combustor liner that at least partially defines a combustion chamber; and a gaseous fuel nozzle assembly fluidly coupled with the combustion chamber and comprising: a rich fuel supply configured to provide a rich mixture of gaseous fuel and air; a lean fuel supply configured to provide a lean mixture of gaseous fuel and air, the lean mixture having a lower equivalence ratio than the rich mixture; a rich fluid passage fluidly coupled to the rich fuel supply to emit the rich mixture into the combustion chamber; and a lean fluid passage fluidly coupled to the lean fuel supply to emit the lean mixture into the combustion chamber.