711 results about "Engine knocking" patented technology

The invention discloses an optimization control method for a target EGR rate, which comprises the following steps: entering EGR closed-loop enabling under the condition of meeting the closed-loop enabling of an EGR system, determining a filtering time coefficient of the target EGR rate according to the response time of a supercharger and the time of exhaust gas flowing from an EGR valve to an EGR exhaust gas convergence point, and calculating the change rate of the filtering time coefficient of the target EGR rate; obtaining filtering time according to a filtering time learning coefficient and the change rate of the filtering time coefficient of the target EGR rate; according to the filtering time and the target EGR rate, the filtered target EGR rate is obtained; and an EGR valve is controlled according to the filtered target EGR rate. According to the method provided by the invention, the target EGR rate can be optimized, the influence on engine knock deterioration when EGR enters is improved, and meanwhile, the supercharging control stability and the emission performance of the engine are improved.

The invention discloses a wide-range rotary detonation combustion chamber runner structure and an operation method thereof, and belongs to the technical field of rotary detonation ramjet engines. Comprising an equipment throat, an expansion section and an outer ring switching section, the end, away from the equipment throat, of the expansion section is connected with an outer ring switching device, the outer ring switching device is connected with an equal direct oil injection section, the equal direct oil injection section is connected with an expansion concave cavity section, and the expansion concave cavity section is connected with an exhaust nozzle shell; an inner column is arranged in the outer ring switching device and the equal-straight oil injection section and movably connected with a plug type spray pipe. According to the flow channel structure of the wide-range rotary detonation combustion chamber, a plurality of static and dynamic pressure measuring points are arranged on the surface of the outer ring switching section, so that the combustion state is monitored in real time; the plug type spray pipe moves back and forth in the inner column guide rail through the lead screw, and the throat area is flexibly adjusted so as to adapt to the working range from the low Mach number to the high Mach number. The equal direct oil injection section ensures different combustion requirements through a multi-group annular injection design; the expansion concave cavity section is provided with a pre-explosion pipe connector and a plasma igniter installation panel, and the multi-work ignition requirement is met.

The embodiment of the invention is suitable for the technical field of automobiles, and provides an ignition angle correction method and device, an engine and a vehicle, and the method comprises the steps that if a knock retreat angle is larger than a first retreat angle threshold value, a basic ignition angle corresponding to basic fuel oil is obtained according to current engine state information; the mark corresponding to the basic fuel oil is smaller than the mark corresponding to target fuel oil of the engine; controlling the engine to execute ignition operation based on the basic ignition angle; and if the first number of times that the knock retreat angle of the engine within the preset duration is larger than the second retreat angle threshold value meets the first preset condition, the basic ignition angle is periodically corrected according to the target stride on the basis of a preset correction period till the difference value between the corrected basic ignition angle and the target ignition angle meets the second preset condition. The method provided by the embodiment of the invention can reduce the probability of phenomena such as knocking and abnormal combustion of the engine, so that the fault probability of the engine is reduced.

The invention discloses a high-horsepower fuel oil dune buggy gas supply assembly, and belongs to the technical field of internal combustion engine gas inlet systems, the high-horsepower fuel oil dune buggy gas supply assembly comprises an outer cover, a sealed space is limited in the outer cover, and the outer cover is provided with a gas inlet head and a gas exhaust head; the inner container is arranged in the sealed space of the outer cover, and the inner container comprises a first inner shell and a second inner shell; and the pumping piece is arranged in the first inner shell and used for pressurizing air and pumping the air to the second inner shell. Through optimization of the overall structure, high-pressure airflow is generated through the pumping piece, air is physically separated into cold air and hot air in the vortex chamber, and cold air far lower than the environment temperature can be actively provided for an engine without any refrigerant and a complex compressor; the problems that the fuel oil dune buggy is low in inflation efficiency and high in detonation risk in a high-temperature environment are solved, strong, stable and continuous power is output, and power attenuation of the high-horsepower fuel oil dune buggy caused by high-temperature protection of an engine is relieved.

The invention discloses a rocket-based rotary detonation engine combustion chamber structure and application thereof, and belongs to the technical field of rocket engine research. The combustion chamber structure comprises an isolation section, an equal-direction oil injection section and an expansion-concave cavity section which are connected in sequence. A central rocket is arranged in the isolation section and the equal direct oil injection section; and four groups of first ring-jet injection points are arranged on the equal straight oil injection section, two groups of second ring-jet injection points are arranged on the central rocket, and two groups of third ring-jet injection points are arranged on the expansion-concave cavity section. Oil is injected into the expansion-concave cavity section firstly, a pre-detonation pipe is adopted for igniting an oil-gas mixture, rotating detonation waves are formed, the built-in center rocket can provide thrust for the aircraft at the ground zero speed and form an injection effect for air suction, extra thrust is provided when the cruising thrust of the aircraft is insufficient, and when the rotating detonation combustion flameout boundary exists, the detonation effect is achieved. A flame stabilizing mechanism is provided for rotary detonation combustion, and stable work of wide-speed-range and wide-height-range rotary detonation combustion is achieved.

The present invention relates to the field of engine control technology, and specifically provides an engine electronic main water pump control method, device and storage medium. In the method: S1, obtains a first parameter group and a knock compensation parameter, and determines whether the electronic main water pump can start closed-loop control based on a target water temperature based on the first parameter group and the knock compensation parameter. If the determination is yes, enters S2; S2, determines whether the conditions for starting the knock compensation function are met based on the current engine state; if the determination result is yes, enters S3, and if the determination result is no, enters S5; S3, determines whether knock compensation is performed based on the current electronic main water pump output offset. If the electronic main water pump output offset is greater than a preset value, knock compensation is performed and enters S4; otherwise, enters S5; S4, switches the closed-loop control based on the target water temperature to the open-loop control based on the target water temperature; S5, starts the open-loop control strategy based on the target water temperature; in this way, the purpose of increasing the engine cooling intensity and thermal efficiency is achieved.

A mixture of a fuel and an oxidant is flowed into a rotating detonation engine defining a longitudinal axis and having an outer body and an inner body spaced from the outer body to thereby define an annular combustion chamber. The fuel is combusted in the presence of the oxidant in the annular combustion chamber so as to generate a detonation wave that rotates in the combustion chamber around the longitudinal axis and produces one or more combustion products that flow out of the rotating detonation engine. The one or more combustion products are mixed with a feedstock so as to decompose the feedstock.

The embodiment of the invention provides an engine control method and device, a vehicle and a storage medium, and the method comprises the steps that the running state of the vehicle is monitored, a state monitoring result is obtained, and the state monitoring result is used for representing whether the knocking phenomenon occurs in the current running state of the vehicle or not; in response to the state monitoring result that the knocking phenomenon occurs in the current running state of the vehicle, the fuel quality of fuel currently used by the vehicle, the current running parameters and running state parameters of an engine and a first control parameter are obtained, the fuel quality is used for reflecting the combustion capacity of the fuel in multiple dimensions, and the fuel quality is used for reflecting the combustion capacity of the fuel in multiple dimensions; the running state parameters are used for reflecting running conditions of the engine; adjusting a first control parameter currently used by the engine based on the fuel oil quality and the operation parameter operation state parameter to obtain a target control parameter; and controlling the engine to operate based on the target control parameter. The technical problem that in the related technology, the stability of controlling operation of the engine is poor is solved.

The invention relates to the technical field of engines, in particular to a piston combustion chamber for a diesel and natural gas engine and the engine, and the piston combustion chamber for the diesel and natural gas engine comprises an omega-shaped pit. The straight opening type omega-shaped pit structure is adopted, compared with a traditional ignition type combustion chamber, the ineffective conical volume in the center of the combustion chamber is removed, the top dead center injection diffusion combustion mode is better met, the air utilization rate is higher, the compression ratio is higher, and higher heat efficiency can be better achieved; compared with a traditional necking omega-shaped diesel engine combustion chamber, a plurality of necking structures are removed, the first annular concave face and the second annular concave face are designed, the characteristic of natural gas injection is better met, the front end space of flames is fully released, the air utilization rate is increased, the heat transfer loss is reduced, and the combustion efficiency and the heat efficiency are improved; due to the design of the large-curvature concave surface, the problems of heat load concentration and particle friction caused by a sharp structure can be avoided, and the problems of out-of-control combustion, knocking and engine damage are reduced.

The invention discloses a pulse detonation attitude control engine system which comprises an ignition detonation straight pipe and at least one S-shaped attitude control pipe. The ignition detonating straight pipe comprises an ignition section and an obstacle detonating section which are sequentially arranged in the axial direction; wherein an explosion promotion barrier is arranged in the barrier explosion initiation section; each S-shaped attitude control tube comprises a branch tube and two bent push tubes; the center of the branch pipe is vertically arranged at the tail end of the obstacle detonating section and is communicated with the obstacle detonating section through a valve; the two bent push pipes are symmetrically arranged relative to the center of the branch pipe to form an S shape; each bent push pipe comprises a bent pipe section and an exhaust nozzle section, and the two ends of each bent pipe section are connected with the corresponding branch pipe and the corresponding exhaust nozzle section respectively. According to the invention, the advantages of high-efficiency combustion and high-precision adjustable pulse thrust of the pulse detonation engine can be played as far as possible while the microminiaturization of the attitude control engine is met, the thermodynamic cycle theory can be improved by more than 20% compared with common chemical propulsion, and the on-orbit life of a spacecraft is effectively prolonged.

The invention provides a methanol-diesel dual-fuel engine knock control method, relates to the technical field of engine control, and aims to implement multi-cylinder independent control, realize differentiated control of each cylinder, independently collect and filter knock sensor signals of each cylinder, and improve the reliability of the engine knock control. Extracting the detonation characteristic intensity of each cylinder by using a fast Fourier transform and time domain integral analysis method; judging which level of response strategy threshold range the knock characteristic intensity is located in, and executing a response strategy of a matching level; and establishing an adaptive learning mechanism, and optimizing the threshold value of each level of response strategy. The method has the advantages that the knocking detection accuracy is remarkably improved, the optimal control boundary under different methanol mixing proportions is achieved through a self-adaptive learning mechanism, the problem of inconsistency of cylinders under the dual-fuel working condition is solved by adopting a differentiated cylinder control strategy, the engine safety is guaranteed, and the reliability of the engine is improved. Torque output under the full-load working condition is improved, the failure rate of knock-related parts is reduced, the service life of an engine is prolonged, and pollutant emission is reduced.

The invention relates to the technical field of vehicle supercharging control, in particular to a supercharger performance control method and device of a hybrid power system and a vehicle. The method comprises the steps that a plateau ignition angle MAP table and a plateau air inlet VVT angle MAP table of the vehicle in a high altitude mode are obtained; a plateau air inlet VVT angle MAP table is corrected, meanwhile, the knocking thrust angle condition of the hybrid power system is checked, and the maximum performance of a current supercharger is determined so as to correct the exhaust gas recirculation rate; calibration limits are generated based on at least part of detonation, preignition, the highest rotating speed of turbine hardware, the combustion center of gravity, the combustion boundary and the HCU series-parallel economic line, and comprehensive test check is conducted based on the calibration limits so that performance optimization can be conducted on the engine. Therefore, the problems that in the related technology, due to the fact that the performance and the response speed of the supercharger in the plateau area are reduced, the actual torque of an engine cannot meet the requirement of a hybrid power system, and then the series-parallel connection switching and electricity protection capacity of the vehicle is affected are solved.

The invention provides a conventional and detonation dual-mode spontaneous combustion propellant space engine, and belongs to the technical field of spacecraft propulsion systems. The conventional and detonation dual-mode spontaneous combustion propellant space engine comprises a propellant control valve, an engine head, an engine body and an external excitation device. The propellant control valve, the engine head part and the engine body part are connected in sequence, and the external excitation device is embedded into the outer wall of the engine body part; according to the invention, by adopting an external excitation mode, the space engine in a detonation mode is realized; by means of a selective excitation mode, the space engine capable of selecting a conventional mode and a detonation mode is achieved. The detonation combustion is applied to the spontaneous combustion propellant space engine, the upper limit of the combustion efficiency of the space engine of a constant-pressure thermodynamic cycle is broken through, and the combustion efficiency is further improved on the original basis.

The invention discloses a combustion heating type ground test wind tunnel for premixing detonation combustion research, which comprises a combustion heating chamber and a mixing spray pipe, and the combustion heating chamber comprises an injector and a combustion chamber. Wherein the injector is used for spraying out alcohol, oxygen and air and mixing the alcohol, the oxygen and the air to form mixed gas, high-heat gas enters the combustion chamber to be fully combusted after ignition, and finally the mixed gas is sprayed out from the combustion chamber to the mixing spray pipe. Alcohol is sprayed in a scattering mode through the alcohol spraying opening, so that the alcohol collides with oxygen sprayed out of the oxygen spraying straight groove and is fully mixed with the oxygen, meanwhile, air is sprayed out of the air spraying piece, gas mixing is promoted, and heat generated by alcohol combustion is prevented from being conducted to a combustion chamber. The combustion chamber absorbs heat through cooling liquid in the outer side cooling groove, and damage of the heat of the combustion chamber to the wind tunnel structure is avoided.

The invention discloses a natural gas engine in-cylinder combustion cycle compensation control method and system, and the method comprises the steps: carrying out the calibration of a rack and a whole vehicle, and recording the preset signals of misfire and knocking; detecting an engine knock signal and an engine misfire signal, comparing the engine knock signal and the engine misfire signal with a misfire and knock preset signal, judging whether knock or misfire exists at present or not, and correcting the EGR rate and the ignition advance angle according to the knock signal and the misfire signal if knock or / and misfire are / is judged; and measuring an air humidity value through an atmospheric environment sensor, comparing the air humidity value with an air humidity preset value, judging whether the current humidity is abnormal or not, if the humidity is abnormal, correcting the EGR rate and the ignition advance angle, and then returning to the previous step. Through monitoring knock, misfire and humidity signals, interactive processing is carried out, a compensation correction strategy is executed, the combustion cycle fluctuation ratio in an engine cylinder is effectively reduced, and the operation stability of an engine is improved.

The invention relates to the technical field of pulse detonation engine oil supply, in particular to a pulse detonation combustion chamber oil supply system which comprises a fuel oil filter, a flow regulating valve, a fuel oil flow meter, a fuel oil electric heater, an electromagnetic valve, a high-pressure direct-drive electronic fuel injector, a detonation chamber wall surface regeneration cooling mechanism and a fuel oil control system. Fuel oil is electrically heated in the starting process, an electric heater and the high-temperature wall face of the detonation chamber are used for heating the fuel oil within the full working condition range, the initial temperature of the fuel oil entering the pulse detonation combustion chamber is increased, the atomization mixing effect of the fuel oil in the pulse detonation combustion chamber is improved, and the combustion heat efficiency in the pulse detonation combustion chamber is improved; the regenerative cooling structure plays a role in heat exchange and detonation wave formation acceleration on the outer wall and the inner wall of the pulse detonation combustion chamber, the overall structure is simplified while the function is guaranteed, and the reliability of system operation is improved. And the requirements of the pulse detonation combustion chamber on stable oil supply flow under different working conditions and special conditions are met.

The invention relates to the technical field of aero-engines, and discloses an efficient thermal protection hybrid thermodynamic cycle combined engine and a control method thereof.The combined engine composed of an external rotary detonation engine and an internal turbine engine is adopted, and modal switching of the combined engine is achieved through an inlet adjusting valve and an adjustable exhaust nozzle; the working upper limit of a turbine engine can be effectively joined, power relay can be completed, so that a thrust gap is spanned, the structural design complexity is relatively low, the system stability is relatively high, and in a stress application rotating detonation mode, the reliability is high. Combustible mixtures sprayed by the rotary detonation engine are guided into the afterburner of the turbine engine through the afterburner diverter valve for detonation combustion, an original cooling device of the afterburner is used for thermal protection, and an outer casing is prevented from being damaged due to high temperature.

The invention relates to the technical field of engines, in particular to an anti-knock ignition system of a hydrogen internal combustion engine, a control method and device of the anti-knock ignition system, a storage medium and electronic equipment. The system comprises an ignition coil, an external resistor and a spark plug, wherein the external resistor is connected to the secondary end of the ignition coil in parallel and close to the side where the spark plug is located; the control method comprises the steps of obtaining a current ignition advance angle; calculating a current knock index; whether the knock index is smaller than a current knock index threshold value or not is judged, if not, the ignition advance angle is adjusted according to a preset updating path, and the preset updating path is jointly determined according to the ignition advance angle, the knock index, the knock index threshold value and the adjusting coefficient; and if yes, the current ignition advance angle is kept, and an ignition control signal is sent according to the current ignition advance angle. Compared with the prior art, the method has the advantages that the risk of secondary discharge of the ignition coil is reduced, and engine knock suppression under all working conditions is achieved.

The invention belongs to the technical field of engines, and discloses a rotary detonation combustion chamber which comprises a combustion chamber body, the combustion chamber body comprises a combustion chamber shell composed of an inner sleeve structure and an outer sleeve structure, a fluid channel is formed in the combustion chamber shell, and the inlet end of the fluid channel is a combustion chamber air inlet; the fluid channel comprises a combustion chamber throat section, a first expansion section, a U-shaped groove section, a second expansion section and a combustion chamber downstream straight section which are sequentially arranged. One end of the combustion chamber throat section communicates with the combustion chamber air inlet. And the U-shaped groove section comprises a U-shaped groove fillet section and a U-shaped groove straightway section which are arranged in sequence. The whole U-shaped groove fillet section is of a topological fluid diode structure, and one end, close to the first expansion section, of the topological fluid diode structure is of an arc-shaped structure. The topological fluid diode structure provides a new view angle and a new solution for optimization of the combustion chamber, and design and development of the more efficient and more stable combustion chamber are promoted.

This application relates to the technical field of detonation engines and discloses an inlet device for a low-loss adjustable rotary detonation combustion chamber, which includes a throat section for mixing hot air and fuel. An air inlet for inputting hot air and a fuel inlet for inputting fuel are provided in the throat section. The throat section includes a throat inner cylinder and a throat outer cylinder located outside the throat inner cylinder. A ring slot channel is provided between the throat inner cylinder and the throat outer cylinder. The ring slot channel communicates with the air inlet and the fuel inlet. An adjusting mechanism for regulating the size of the ring slot channel is provided on the throat outer cylinder. This application does not require repeated disassembly and replacement of the throat section when calculating the optimal mixing ratio of hot air and fuel, and has the effect of simple operation.

The invention relates to the technical field of engines, and discloses a turbine-based combined cycle engine operation method and a turbine-based combined cycle engine, and the turbine-based combined cycle engine operation method comprises the steps that a pulse detonation combustion mode is adopted in a pure turbine mode; a rotary detonation combustion mode is adopted in a pure stamping mode; a pulse detonation combustion mode is adopted in the transition mode, and meanwhile, a rotary detonation combustion mode is adopted. By utilizing the advantages of self-pressurization and high unit thrust of pulse detonation combustion, the high-speed performance is improved, and the working Mach number upper limit of a pure turbine mode is widened; by utilizing the advantages of high combustion speed, high combustion efficiency, simple structure and short length of rotary detonation combustion, the lower limit of the working Mach number of a pure stamping mode is widened. And in the transition mode, the characteristics of a pure turbine mode and a pure stamping mode are achieved at the same time, and enough thrust is provided for the aircraft.

The invention belongs to the technical field of aviation aircrafts, and particularly relates to a hybrid power engine and an aviation aircraft. The invention provides a hybrid power engine which comprises a detonation combustion chamber, a center shaft and a power generation assembly, the power generation assembly comprises a stator, an outer rotor and fourth permanent magnets, the stator is hinged to the center shaft, the outer rotor is of an annular structure, a plurality of first grooves are formed in the annular outer wall of the outer rotor, and the fourth permanent magnets are embedded in the first grooves; the fourth permanent magnet is matched with the stator for power generation; the detonation combustion chamber is arranged in the outer rotor and drives the outer rotor to rotate; the center shaft is provided with an energy storage part, and the power generation assembly is electrically connected with the energy storage part. The invention further provides an aviation aircraft comprising the hybrid power engine. According to the engine, the detonation combustion chamber combusts to drive the outer rotor to rotate to generate electricity, redundant power of the detonation combustion chamber generates electricity through the power generation assembly and then is stored in the energy storage part, waste of redundant energy is avoided, and the energy storage part can also be used for providing driving power.

The invention relates to the technical field of rocket engines, in particular to a rocket support plate and concave cavity combined oblique detonation engine which comprises a mixing section, a combustion chamber and an exhaust nozzle which are sequentially connected, the mixing section is of a hollow structure, a fuel-rocket support plate assembly is arranged in the mixing section, and a detonation slope-concave cavity combined support plate assembly is arranged in the combustion chamber; a middle flow channel for constant-pressure combustion is formed in the middle of the detonation slope-concave cavity combined supporting plate assembly, and an upper flow channel and a lower flow channel for constant-volume combustion are formed by the upper surface and the lower surface of the detonation slope-concave cavity combined supporting plate assembly and the inner wall of the combustion chamber. According to the device, an oblique detonation combustion mode, a rocket mode, a subsonic combustion ramjet mode and a scramjet mode are integrated into the same engine, a split flow channel structure is formed, full-speed domain coverage from low Mach to ultrahigh Mach (more than 8 Mach) is achieved, and combustion organizations in different flight stages are optimized through a mode switching mechanism.

The invention relates to a control method based on low-temperature cold start of a heuristic integrated heavy oil engine, and relates to the field of heuristic integrated heavy oil engines. According to the technical scheme, the preheating plug in the cylinder is combined with the air inlet heating grid, synchronous control is achieved through the same relay, the electric energy requirements of synchronous work and dragging and preheating are met by means of sufficient battery capacity, and the device can be adapted to the ultra-low temperature of-40 DEG C or below and the plateau environment of 4700 m or above; three starting attempts are supported by single-time power-on through intelligent preheating control logic, the pre-preheating and heating-while-dragging processes are executed each time, fault information is automatically uploaded after starting fails, frequent power-off is not needed, and the starting efficiency is improved. And moreover, through an intermittent post-preheating and intake synchronous heating strategy, the combustion stability in the cylinder is effectively improved, the rotating speed fluctuation time is shortened, and mechanical damage caused by flameout and unstable idling after starting is avoided. In addition, the dragging rotating speed control based on the torque can prevent the problem of engine damage caused by accidental detonation after multiple starting failures.

A rotating detonation combustion system includes a detonation channel including an inner wall and an outer wall and extend in a longitudinal direction from an inlet of the detonation channel to an outlet of the detonation channel. A first mixing element and a second mixing element are disposed in the rotating detonation combustion system. The first mixing element forming a ring on the inner wall and the second mixing element forming a ring on the outer wall of the detonation channel adjacent the inlet. Each of the first mixing element and the second mixing element comprise a plurality of protrusions disposed circumferentially along the inner wall and the outer wall and extend into the detonation channel such that the plurality of protrusions affects vectors of at least a portion of the fuel and at least a portion of the fluid passing through recesses between the plurality of protrusions.

The invention discloses a rotating detonation afterburner based on centrifugal nozzle discrete injection, and belongs to the technical field of detonation propulsion. The combustion chamber comprises a gas collecting cavity, an injection unit, a centrifugal nozzle, an outer ring and an inner column, wherein an annular detonation combustion chamber is formed between the inner wall surface of the outer ring and the outer wall surface of the inner column. The centrifugal nozzles are uniformly arranged at the intersection of the gas collection cavity and the injection unit in the circumferential direction to realize primary atomization of the fuel oil; the air is accelerated by the injection unit from the air collection cavity and then is mixed with the atomized fuel oil, secondary atomization is achieved, the particle size of liquid drops is remarkably reduced, and the fuel activity and mixing uniformity are improved. The injection unit adopts a Laval nozzle profile, air is accelerated to supersonic speed in the injection unit, and pressure of a combustion chamber is prevented from being transmitted forwards. The rotary detonation engine is suitable for the high-temperature low-oxygen environment, supports the annular combustion chamber configuration and the empty cylinder combustion chamber configuration, can achieve stable rotary detonation detonation and propagation of liquid fuel and air, and provides technical support for engineering application of the rotary detonation engine.

A fuel control system for a turbine engine includes a mixer for mixing first and second fuels to obtain a fuel blend, a fuel blend analyzer, a combustor operable with the fuel blend, and a knock sensor coupled to the combustor. The system also includes a controller configured to: receive a measurement indicative of a composition of the fuel blend; compare the fuel blend measurement to an operational model of the combustor; determine, based on the comparison, a predicted combustion condition in the combustor associated with the fuel blend measurement; control, based on the predicted combustion condition, flow of the first fuel or the second fuel; receive a combustion signal indicative of combustion behavior in the combustor; compare the predicted combustion condition to the combustion signal; and update the operational model if the predicted combustion condition does not match the indicated combustion behavior.

Disclosed in the present application are a control method, apparatus and device for a cooling system in an engine, and a storage medium, wherein the cooling system in the engine comprises a water-cooled intercooler and an electronic water pump. The control method comprises: acquiring an actual air-output temperature of a water-cooled intercooler; determining whether the actual air-output temperature is within a preset temperature range; and controlling a low-pressure EGR system and / or an electronic water pump on the basis of a determination result. By means of the technical solution provided in the present application, abnormal problems of overtemperature, knocking, etc., occurring in an engine can be reduced, thereby improving the reliability of the engine.

The invention discloses a cooperative control method for the air-fuel ratio, the injection opportunity and the cooling liquid temperature of a hydrogen fuel engine. The cooperative control method comprises the steps that S1, operation condition parameters and combustion state parameters of the hydrogen fuel engine are monitored; s2, based on the operation condition parameters, adaptively determining a target air-fuel ratio, a fuel injection opportunity and a cooling liquid temperature through a preset control strategy; s3, the combustion state and the engine operation condition are evaluated in real time through a closed-loop feedback control system, and the following cooperative adjustment is executed: the hydrogen supply amount is adjusted to maintain the target air-fuel ratio; the hydrogen injection time is adjusted, and the combustion phase is optimized. According to the cooperative control method for the air-fuel ratio, the injection opportunity and the cooling liquid temperature in the hydrogen fuel engine, the target air-fuel ratio, the hydrogen fuel injection opportunity and the engine cooling liquid temperature are comprehensively adjusted under a closed-loop feedback control framework, optimal control over the combustion process under different working conditions is achieved, and therefore the braking heat efficiency of the engine is improved, and the service life of the engine is prolonged. And pollutant emission is reduced, knocking is restrained, and the application requirement for efficient cleaning of the engine is met.

The invention relates to the technical field of aero-engine combustion chamber design, in particular to a multi-layer mixing section structure of a pulse detonation combustion chamber. The multi-layer mixing structure is characterized in that the multi-layer mixing structure comprises a multi-layer mixing section arranged in a detonation pipe, an oil supply pipe is arranged on the detonation pipe, the multi-layer mixing section comprises an inner mixing ring and an outer mixing ring, and the inner mixing ring and the outer mixing ring form three Venturi type circulation channels through connecting structures; and a fuel nozzle connected with an oil supply pipe is arranged at the axis of the inner mixing ring. By means of the multi-layer mixing section, incoming flow air is divided into multiple jet flows, the mixing efficiency of fuel oil and air is improved, the mixing uniformity of the fuel oil and air is remarkably improved, and the mixing distance is shortened. Meanwhile, according to the regenerative cooling structure, a fuel oil channel is designed in a multi-layer mixing section, recycling of the wall face of the pulse detonation combustion chamber is achieved, meanwhile, the oil injection temperature is increased, the fuel oil and air mixing effect is improved, and the combustion efficiency is improved.