81 results about "Engine knocking" patented technology

The application discloses an ammonia-hydrogen internal combustion engine knock suppression system and a knock suppression method, and belongs to the technical field of internal combustion engine combustion control. The suppression system comprises an ammonia gas supply unit, a hydrogen gas supply unit, a cylinder pressure sensor, a pressure sensor and an electronic control unit. The ammonia gas supply unit realizes ammonia gas supply in a cylinder. The hydrogen gas supply unit realizes hydrogen gas supply in the cylinder. The cylinder pressure sensor is used for monitoring the pressure in the cylinder in real time and calculating CA50. The pressure sensor is used for monitoring the knock intensity of the cylinder. The electronic control unit is electrically connected with the ammonia gas supply unit, the hydrogen gas supply unit, the cylinder pressure sensor and the pressure sensor respectively, is used for receiving sensor signals, calculating ammonia energy (AER) and knock intensity (KI), controlling the ignition time and dynamically adjusting the ammonia mixing ratio, realizing the collaborative optimization of knock suppression and thermal efficiency, and achieving the win-win effect of "knock suppression" and "efficiency increase".

This application provides an engine combustion control method and apparatus, relating to the field of automotive engine technology. The method includes: responding to an engine start command issued by a hybrid vehicle, setting the engine control mode to a high-efficiency combustion control mode; calculating the intake air volume in the engine cylinders based on the vehicle's required torque; calculating the final boost pressure based on the intake air volume; controlling the speed of the electric supercharger based on the final boost pressure; determining the optimal injection frequency and fuel injection parameters for each engine operating condition based on the engine's full-map operating conditions and the intake air volume; and performing fuel injection and engine knock linkage control based on the optimal injection frequency and fuel injection parameters for each operating condition. The engine combustion control method and apparatus provided in this application can achieve efficient combustion of the hybrid engine in the vehicle, achieve optimal thermal efficiency, and enable smooth charging and driving of the vehicle.

This invention discloses a device and control method for maintaining uniform pressure and temperature in the engine intake chamber. The device includes a circulation pipe, with its two ends fixedly connected to the flywheel end and free end of the intake chamber, respectively. The intake passages of the first and last cylinders are connected to the intake chamber. Temperature and pressure detection devices are installed on both the first and last cylinder intake passages. A regulating valve is installed on the circulation pipe to adjust the flow rate of the boosted intercooled air in the circulation pipe. The detection devices are connected to the ECU, and the regulating valve is controlled by the ECU. The regulating valve is configured as an electronic throttle. The ECU monitors the intake pressure and temperature signals of each cylinder in real time, obtains a preset electronic throttle opening angle based on the temperature and pressure differences, and controls the opening angle of the electronic throttle according to the preset angle. This precisely controls and adjusts the flow rate of the boosted intercooled air in the circulation pipe, ensuring uniform intake pressure and temperature in each cylinder, improving engine knock pressure uniformity, exhaust temperature uniformity, and reducing vibration.

The present invention provides a vehicle control device that can suppress vibrations of the vehicle body when the internal combustion engine restarts, even if a restart request occurs before the engine speed of the internal combustion engine reaches "0". [Solution] The control device is applied to a vehicle that transmits torque output from an internal combustion engine to the drive wheels. The control device includes a processing circuit that controls the internal combustion engine. The processing circuit performs ignition timing control, automatic stop control, and automatic start control. Ignition timing control is a control that starts from the initial ignition timing when the engine starts and repeatedly adjusts the ignition timing according to the knock detection result. The processing circuit terminates the ignition timing control (step S13) when the engine rotational speed NE becomes less than or equal to a first rotational speed NE1 which is greater than "0" (step S12: YES).

Method for a power machine (10), comprising: to deactivate individual cylinder valve mechanisms according to a cylinder pattern chosen based on a knock value of each cylinder (14) of the power engine (10), wherein the selection involves selecting a first cylinder (14) which has a knock value above a threshold for deactivation, while a second cylinder (14) with a knock value below a threshold remains active during deactivation, characterized by the fact that the first cylinder (14) remains deactivated for a number of power engine cycles, the number being based on the temperature of the first cylinder (14), the number of power engine cycles being increased if the temperature of the first cylinder (14) rises above a threshold, the temperature of the cylinder (14) including a measured or derived cylinder internal temperature.

The application relates to the technical field of engines and discloses a turbine-based combined cycle engine operation method and a turbine-based combined cycle engine. The turbine-based combined cycle engine operation method comprises the following steps: adopting a pulse detonation combustion mode in a pure turbine mode; adopting a rotating detonation combustion mode in a pure ram mode; and adopting the pulse detonation combustion mode and the rotating detonation combustion mode simultaneously in a transition mode. The application utilizes the advantages of the pulse detonation combustion, such as self-pressurization and high unit thrust, to improve high-speed performance and widen the upper limit of the working Mach number of the pure turbine mode; the advantages of the rotating detonation combustion, such as fast combustion speed, high combustion efficiency, simple structure and short length, are utilized to widen the lower limit of the working Mach number of the pure ram mode. In the transition mode, the turbine-based combined cycle engine simultaneously has the characteristics of the pure turbine mode and the pure ram mode, so that sufficient thrust can be provided for an aircraft.

Combustion system comprising: an injection device (40) configured to inject fuel into a combustion chamber (38) of an engine (91, 92); a spark plug (50) configured to perform ignition (I) of the fuel in the combustion chamber; and a normal control unit (65) configured to perform normal control (α) to cause the injection device to perform a predetermined normal injection (F), and subsequently to cause the spark plug to perform ignition, wherein in a predetermined delay range (D) in the combustion chamber the propagation of the flame (P) is further delayed than in any other range when normal control is performed, and in a knocking condition auto-ignition occurs in the fuel in the delay range when normal control is performed, the combustion system further comprising: an adjustment control unit (66),which is configured to perform a predetermined adjustment control (β) when the knock condition is established in order to suppress auto-ignition, wherein the adjustment control does the following: cause the injector to perform a predetermined main injection (Fm) and subsequently perform a predetermined partial injection (Fs) in a second half of a compression stroke to adjust fuel distribution in the combustion chamber to facilitate flame propagation (P) into the retardation region further than with normal injection, and subsequently cause the spark plug to perform ignition.

A method for controlling an internal combustion engine, said internal combustion engine comprising a cylinder designed to be able to undergo stratified combustion, said method comprising, for each combustion cycle, the steps of: a. determining (31) the number of injection and ignition patterns to be implemented, b. determining (32) the amount of fuel to be injected at each injection by dividing the amount of fuel to be injected in the combustion cycle by the number of patterns to be implemented, c. determining (33) the time of each pattern as a function of the crank angle, said time of each pattern being between the intake bottom dead center and the combustion top dead center of the combustion cycle, d. controlling (34) the fuel injection circuit and the ignition device to produce the patterns as a function of the crank angle, the amount of fuel to be injected for each pattern and the timing of each pattern.

The present disclosure relates to a rotary detonation combustor including a front wall, a radially inner wall, and a radially outer wall. The front wall is disposed at an inlet end of the rotary detonation combustor. The radially inner wall surrounds a longitudinal axis and extends downstream from the front wall to an outlet end of the rotary detonation combustor. The radially outer wall extends downstream from the front wall to the outlet end and surrounds the radially inner wall to define at least one annular cell between the radially inner wall and the radially outer wall. At least one partition is proximate the inlet end and defines at least two mixing zones. A plurality of oxidizer inlets and a plurality of fuel inlets are disposed at the inlet end in fluid communication with the at least two mixing zones.

The application discloses an engine with a built-in sodium-filled heat superconducting element cylinder cover and a structure thereof, and relates to the technical field of vehicle engines.The engine cylinder cover is characterized in that the bottom surface of the engine cylinder cover is shaped into a cylinder cover combustion chamber, the inside of the engine cylinder cover is provided with a cylinder cover water jacket, and at least one closed sodium-filled heat superconducting element is embedded in the solid inside between the cylinder cover combustion chamber and the cylinder cover water jacket of the engine cylinder cover; the inside of the sodium-filled heat superconducting element is provided with a vacuumized sodium-filled cavity, the sodium-filled cavity is filled with a heat transfer medium, one end of the sodium-filled heat superconducting element close to the cylinder cover combustion chamber is provided with a heat absorbing end, and the other end of the sodium-filled heat superconducting element close to the cylinder cover water jacket is provided with a heat dissipating end.The application reduces the physical peak temperature of a local area, reduces structural thermal stress, and eliminates a local high-temperature surface that can cause engine knock.

The present application relates to a kind of active cooling method applied to engine, comprising: one, establish the active thermal protection theory analysis model suitable for oblique knock engine;Two, preliminary determination active thermal protection theory analysis model parameter;Three, load heat flow condition, active thermal protection theory analysis model is carried out active cooling simulation analysis, obtains coolant temperature distribution;Four, confirm whether coolant temperature distribution satisfies the upper limit requirement of coolant temperature and the use requirement of solid wall material temperature, if satisfy, enter step six, if not satisfy, enter step five;Five, change active thermal protection theory analysis model parameter, repeat step three-four;Six, the rectangular cooling channel of local high heat flow area is modified to cooling channel configuration with different bending structure, until meet the demand;Seven, according to the active thermal protection theory analysis model and parameter of final processing active thermal protection structure.The present application solves the heat protection problem of oblique knock engine structure.

This application belongs to the field of aero-engine simulation technology, and relates to a method and apparatus for simulating the overall pulsation characteristics of a rotating detonation turbine engine. The method includes: obtaining the given total pressure pulsation characteristics of the rotating detonation combustor; calculating the total outlet pressure of the rotating detonation combustor at the current simulation moment; inputting the total outlet pressure of the rotating detonation combustor into a pre-constructed overall performance model of the turbojet engine in transition state. The overall performance model is formed by coupling various engine components through aerodynamic parameter interfaces in the order of airflow, considering rotor dynamics and volume effects during coupling; solving for independent engine variables and the characteristics of each component under the constraints of overall engine matching conditions of flow balance and power balance until the residuals converge; extracting the total inlet pressure of the rotating detonation combustor and calculating the characteristics of each engine component at the next simulation moment. This application realizes the simulation of the unsteady coupling characteristics of the rotating detonation combustor and the turbojet engine.

This invention discloses an anti-knock control method, control device, and vehicle applied to an engine in a hybrid power system. The control method includes: adjusting the engine's initial demand torque change rate limit, initial torque limit, and initial speed limit to a first demand torque change rate limit, a first torque limit, and a first speed limit, respectively; acquiring the engine's knock intensity signal and knock thrust angle under normal operating conditions; determining the engine's knock risk based on the knock intensity signal and knock thrust angle; and correcting the first demand torque change rate limit, the first torque limit, and the first speed limit based on the knock risk. The anti-knock control method provided by this invention can adjust the engine's parameter usage limits in real time, using the engine to operate to the maximum extent possible and to prevent the risk of engine knock, thereby improving engine efficiency and economy.

The application discloses a multiple ignition device for a hydrogen peroxide kerosene rotating detonation rocket combustion chamber and relates to the technical field of aerospace. The device comprises a combustion chamber and a propellant delivery device. The combustion chamber is a double-layer shell structure. A kerosene cooling channel is arranged between the shells. An annular kerosene collecting cavity is arranged around the tail of the shell and is connected with the inlet of the cooling channel. The hydrogen peroxide kerosene propellant ignition device enables the rotating detonation rocket engine to have multiple starting capabilities. The ignition and detonation can be realized by controlling the valve, and the reusable engineering application potential of the rotating detonation rocket engine is significantly improved. The kerosene is ignited by using hydrogen peroxide catalysis, the ignition process is realized, and no additional device such as a spark plug is needed, so that the structure is simple. The device can realize multiple ignitions by controlling the on-off of the propellant valve, and multiple ignition devices are not needed, so that the reliability of the system is significantly improved.

This control unit is suitable for vehicles that transmit torque from an internal combustion engine to the drive wheels. The control unit includes a processing circuit for controlling the internal combustion engine. This processing circuit performs ignition timing control, automatic stop control, and automatic start control. Ignition timing control involves repeatedly adjusting the ignition timing based on knock detection results from the initial ignition timing during engine startup. The processing circuit terminates ignition timing control when the engine speed falls below the first speed greater than 0.

The application provides a rotating detonation afterburner of an aero-engine, and relates to the technical field of gas turbine engines, and specifically comprises a rotating detonation afterburner connected to an exhaust end of a casing of the engine, an air inlet of the rotating detonation afterburner is connected to an exhaust port of the casing, and an airflow injection channel is arranged on the exhaust end of the casing and / or the air inlet of the rotating detonation afterburner, the airflow injection channel is connected to an internal space and an external space of the air inlet of the rotating detonation afterburner, and when exhaust gas of the exhaust end of the engine passes through the air inlet of the rotating detonation afterburner, the air in the external space of the connection part between the rotating detonation afterburner and the casing is introduced into the rotating detonation afterburner through the airflow injection channel. Through the processing scheme, the stability of the detonation wave is stabilized, and the stability of the rotating detonation afterburner is improved.

The application provides a series type double combustion chamber rotating detonation ramjet engine and a working method, which comprises a combustion chamber outer shell, an air inlet channel, a separation section, a first stage combustion chamber, a first stage contraction section, a second stage combustion chamber, a second stage contraction section, an outlet nozzle, a combustion chamber center body, a first stage fuel injection cavity, a second stage fuel injection cavity, a first stage fuel injection hole, a second stage fuel injection hole, a center body front support and a center body rear support. The application is aimed at the rotating detonation combustion organization flow characteristics under high or low Mach number working conditions, realizes the compatibility of high or low Mach number rotating detonation combustion working conditions in the same flow channel, and thus widens the working Mach number range of the rotating detonation ramjet engine. Considering the large difference in the combustion back pressure transmission distance under the high / low incoming flow Mach number working conditions, the two combustion chambers are arranged in series, and the combustion organization working mode is reasonably arranged, so that the combustion back pressure transmission problem under the wide incoming flow Mach number condition can be solved.

The application provides a rotary detonation vector propulsion device based on inner column swing, which comprises a driving rod, a movable combustion chamber inner column, a combustion chamber head and a tail nozzle. The movable combustion chamber inner column comprises a movable combustion chamber inner column front end spherical surface and a movable combustion chamber inner column rear end cylinder; the combustion chamber head comprises an injection structure, a combustion chamber head straight ring plate, a combustion chamber head curved ring plate, a high-temperature-resistant sealing ring and a cooling channel; the tail nozzle is a plug nozzle, which comprises a plug nozzle outer ring and a plug nozzle center cone. The case or the parts fixed on the case are connected with the driving rod front end through a rotary pair, the driving rod rear end is connected with the inside of the movable combustion chamber inner column front end spherical surface through a rotary pair, and the movable combustion chamber inner column front end spherical surface outer wall is matched with the inner wall of the combustion chamber head curved ring plate through a spherical pair. When the device works, the two rotary pairs are respectively driven to rotate by the motor at a certain angular velocity, so that the movable combustion chamber inner column swings and deflects, the rotary detonation wave intensity in the combustion chamber and the gas flow are uneven, and thus the rotary detonation engine generates a vector thrust. The application can be used in the fields of rotary detonation vector propulsion and the like.

The application relates to the field of aerospace propulsion technology, and discloses a multi-mode cluster shock-absorbing pulse detonation engine with intelligent gap control; the engine comprises multiple explosion tube bodies in a concentric circle layout, a hydraulic sealing system, a fuel supply system, an electric arc igniter, an integrated thermal management system and an intelligent control system. The core lies in: the sealing reliability is ensured through intelligent dynamic gap control; a wide-range flight is adapted through multi-mode gas supply; precise ignition control is realized through multi-sensor fusion; waste heat is recycled and thrust gain is generated through integrated thermal management; and vibration and noise are inhibited through cluster detonation interference with a specific layout. The application has the dual-mode intelligent switching capability of high-frequency large thrust and low-frequency high efficiency, integrates health monitoring, and forms an advanced propulsion system solution scheme with high reliability, wide-range self-adaptation and low vibration.

The application provides a kind of calibration method and calibration system of engine, it is related to engine technical field, the calibration method includes: when engine is in knock state, control engine reduces ignition advance angle and obtains the vibration data in time domain within single cycle, wherein vibration data includes vibration intensity and corresponding time;In the whole time domain of vibration data, multiple sub-time regions are divided, and the vibration data in each sub-time region is time-frequency converted to obtain the vibration spectrum corresponding to each sub-time region, wherein the vibration spectrum includes the vibration power corresponding to different frequencies;In high frequency region, each vibration spectrum is integrated to obtain signal intensity and the sub-time region and frequency band corresponding to signal intensity;When signal intensity is greater than a predetermined threshold, the sub-time region and frequency band corresponding to signal intensity are calibrated as high frequency background noise region.The method effectively identifies high frequency background noise band, reduces the interference to real knock calibration, and shortens the time of knock calibration.

This invention discloses a turbine power generation device based on pulse detonation, comprising a compressor, a pulse detonation combustion chamber, a gas turbine, a coupling, a generator, and a controller. During operation, air enters from the compressor and is split into inner and outer bypass air. The inner bypass air passes through a cyclone separator and enters the mixing chamber. Fuel, controlled by a solenoid valve, enters the mixing chamber through a nozzle at the center of the cyclone separator, mixing with the air to form a premixed gas. After passing through a central conical blunt body, the premixed gas is ignited by a high-energy electric nozzle in a concave cavity and enters the detonation section. The flame accelerates in this section, ultimately forming a detonation wave. This detonation wave ejects the outer bypass air and enters the tailpipe together, further increasing the pressure. The ejected airflow enters the gas turbine and drives the generator to generate electricity. Compared to traditional slow-burning power generation devices, this invention has higher power generation efficiency, a wider range of power output variation, and can achieve rapid changes in power output.

If the intake valve closing timing during cranking is constant, it can easily lead to starting problems under low-temperature conditions, and conversely, knocking under high-temperature conditions. [Solution] The internal combustion engine is equipped with an electrically operated variable valve timing mechanism that changes the phase of the camshaft and the crankshaft that open and close the intake valves within a predetermined angular range. In its default state, the variable valve timing mechanism is set to a late closing setting where the intake valve closing timing IVC is relatively far behind bottom dead center BDC. During cranking, the target conversion angle of the variable valve timing mechanism is controlled according to the coolant temperature, such that the lower the coolant temperature, the closer the intake valve closing timing IVC is to bottom dead center BDC, increasing the amount of intake air in the cylinder.

An assembly for a gas turbine engine includes a primary combustor disposed within a core flow path of the gas turbine engine; a high-pressure turbine positioned downstream of the primary combustor; a low-pressure turbine positioned downstream of the high-pressure turbine; and a supplemental combustor positioned within the core flow path, downstream of the high-pressure turbine and upstream of the low-pressure turbine.

A diesel engine system (101) for an agricultural machine (100) includes a diesel internal combustion engine (ICE) (201) configured to combust fossil diesel fuel and alternative diesel fuel, a knock sensor (213) integrated in the diesel internal combustion engine (201), a NOx sensor (209) and an electronic control unit (210). The electronic control unit (210) is configured to receive a knocking signal from the knock sensor (213), receive a NOx concentration signal from the NOx sensor (209), determine a fuel specific characteristic value based on the knocking signal and the NOx concentration signal, determine a fuel specific reference value, compare the fuel specific characteristic value with the fuel specific reference value, and determine whether the combusted diesel fuel is fossil diesel fuel or alternative diesel fuel.

This invention discloses a subsonic ramjet engine based on counter-rotating rotary detonation flame stabilization ignition, belonging to the field of subsonic ramjet engine flame stabilization ignition technology. It includes an intake cooling channel, an integrated fuel supply device, and a symmetrical rotary detonation flame stabilization device. The intake cooling channel cools the engine wall temperature; the integrated fuel supply device achieves high system integration, low flow resistance loss, and lightweight and convenient design; the symmetrical rotary detonation flame stabilization device uses a counter-rotating jet to assist in creating a stable low-speed recirculation zone in the main combustion chamber, thereby achieving flame stabilization. Furthermore, the continuously operating rotary detonation generator acts as a pre-combustion tube, providing forced ignition to the main combustion chamber. This highly integrated invention effectively cools the combustion chamber wall temperature of the subsonic ramjet engine, improves combustion stability, and significantly increases the ignition success rate of the main combustion chamber, thus providing an effective technical approach for subsonic ramjet engines to operate within a wide range of conditions.

The present application relates to aerospace propulsion technology field, disclose supersonic detonation combustor, including natural gas fuel interface and oxygen-rich oxidant interface, fuel delivery assembly, for conveying natural gas fuel and oxygen-rich oxidant to combustor;Premixing component, for premixing fuel, oxidant and combustion air and completing detonation reaction;Injection assembly, for ejecting the detonation gas stream in the form of supersonic speed;The fuel delivery assembly includes upper connecting pipe, and the upper connecting pipe top is fixedly connected with natural gas fuel interface.The present application, through the synergistic optimization effect of multistage premixing technology and detonation reaction process, significantly improves the thermal efficiency, compared with the traditional combustor, the combustion performance is greatly enhanced, this efficient synergistic mechanism can more fully release fuel energy, realize the maximum utilization of energy, thereby fundamentally reduce the operating cost caused by energy consumption.

An ignition timing correction method, an engine, and a vehicle. The method comprises: if knock retard is greater than a first retard threshold, acquiring, on the basis of current engine state information, a base ignition timing corresponding to a base fuel, wherein the grade corresponding to the base fuel is lower than the grade corresponding to a target fuel of an engine; controlling the engine to perform an ignition operation on the basis of the base ignition timing; and if the first number of times that the knock retard of the engine within a preset duration is greater than a second retard threshold satisfies a first preset condition, on the basis of a preset correction period, periodically correcting the base ignition timing according to a target step until the difference between the corrected base ignition timing and a target ignition timing satisfies a second preset condition.