7results about How to "Guaranteed combustion stability" patented technology

The present application belongs to the technical field of internal combustion engine, and particularly relates to a kind of alcohol hydrogen fusion engine precombustion chamber system and its control method.Alcohol hydrogen fusion engine precombustion chamber system includes the engine main body with the main combustion chamber and precombustion chamber being communicated with each other, and also includes methanol supply unit, hydrogen production unit, hydrogen delivery control unit, exhaust gas recirculation unit and main control unit;Main control unit collects engine operating parameters and judges current working condition, and adjusts methanol supply path, hydrogen supply path, precombustion chamber working mode, hydrogen production unit heating mode and on-off state of exhaust gas recirculation unit according to working condition.The present application can realize engine full-condition combustion performance optimization without complex auxiliary device, and also considers cold start reliability, high and low load combustion stability and operation energy efficiency, to improve the whole machine operation reliability and transient response capability.

The application discloses a combined propulsion device mode conversion scheme design method, comprising the following steps: obtaining a Mach number interval of a combined propulsion device when the combined propulsion device is converted from a first mode to a second mode, and selecting a plurality of representative flight state points; for each representative flight state point, respectively performing discrete scanning on a primary propulsion unit mass flow range and a secondary fuel fuel-air ratio range, to form a plurality of candidate working condition combinations; for each candidate working condition combination, calculating flow and combustion characteristics in a thrust chamber, and screening a target working condition combination which can stably combust and meet a thrust demand; obtaining an optimal target working condition combination under each representative flight state point based on enumeration search, and generating a continuous and implementable mode conversion scheduling path. The application is applied to the combined propulsion field, and can effectively realize efficient, stable and safe operation of a mode conversion process.

The invention discloses a self-adaptive control method for a low-carbon multi-fuel internal combustion engine based on fuel activity online identification, which comprises the following steps of: acquiring a pressure signal in a cylinder and a crank angle signal, calculating an instantaneous apparent heat release rate, and extracting waveform topological characteristics of the heat release rate; inputting the extracted heat release rate waveform topological features into the trained fuel activity mapping model to obtain an equivalent reaction activity index of the current mixed fuel; based on the equivalent reaction activity index, dynamically interpolating in a map database or switching to a corresponding reference control strategy, determining a basic value of a control parameter under the current working condition, and performing closed-loop increment correction on the control parameter based on the deviation between the current combustion parameter and a target parameter to obtain a correction value, and performing one-cycle control by taking the sum of the basic value and the correction value as a final value of the control parameter. The invention further discloses a corresponding control system. The combustion stability of the internal combustion engine under the multi-fuel variable working condition can be ensured without knowing the specific fuel type.

The warmer with the heat conduction structure comprises a gas cylinder, an ignition container and a fire grate, the gas cylinder is used for storing combustible gas, the ignition container is communicated with a gas cylinder gas path and used for igniting the combustible gas in the gas cylinder, a radiation panel is arranged on the side, away from the gas cylinder, of the fire grate, and the fire grate is arranged at the tail end of the ignition container and the tail end of the gas cylinder gas path. A heat conduction piece is arranged between the gas cylinder and the fire grate, and a heat conduction path from the fire grate to the gas cylinder is formed through the heat conduction piece. The gas cylinder has the effects of improving the gasification efficiency of liquefied gas in the gas cylinder, ensuring the combustion stability and the heating effect and saving energy.

The application discloses a kind of premixing combustion stabilization method and device of tank furnace, belongs to calcined coke production technical field, using preheated air and cold air mix, participate in volatile combustion, make first layer fireway negative pressure-50~‑20Pa;The eighth layer fireway negative pressure is-180~‑120Pa;Gate negative pressure is-250~‑150Pa;First layer fireway temperature is 1260~1320 ℃;Second layer fireway temperature is 1260~1320 ℃;The eighth layer fireway temperature is 1060~1120 ℃;Exhaust fume temperature is 1040~1100 ℃.The application is by using the method of preheated air and cold air mixing combustion-supporting, maintains the stability of flame distribution in fireway.

The application belongs to the technical field of aero-engines, and discloses an aero-engine combustion chamber main combustion stage fuel nozzle and a fuel control method. The aero-engine combustion chamber main combustion stage fuel nozzle comprises a same center axis, a duty class fuel nozzle, a swirler and a main combustion stage fuel nozzle which are sequentially sleeved from inside to outside, and the outlet of the main combustion stage fuel nozzle is sleeved with a sleeve. The fuel control method ensures that the fuel jet flow of the duty class fuel nozzle is unchanged, the swirler rotates around the duty class fuel nozzle, the fuel jet flow of the main combustion stage fuel nozzle is adjusted, and then the total fuel jet flow of the aero-engine combustion chamber main combustion stage fuel nozzle is changed. The fuel control method of the aero-engine combustion chamber main combustion stage fuel nozzle realizes efficient fuel injection under different working conditions, guarantees the combustion efficiency and stability of the combustion chamber, controls the combustion temperature distribution of the main combustion zone, and reduces the pollutant emission of the combustion chamber.

The application discloses a kind of ignition angle control method, device, vehicle and storage medium, the method comprises: determining the target EGR rate and target EGR flow of engine in steady state condition;Based on the speed and load parameters of engine and target EGR rate, determine the modified ignition angle of engine under target EGR rate, and based on the speed and load parameters of engine, determine the basic ignition angle of engine under no EGR rate;Current EGR state of engine is obtained, and according to current EGR state, target EGR flow, modified ignition angle and basic ignition angle, determine the target ignition angle of engine.So, ignition angle can be matched with EGR rate, reach the best control state of engine, improve the combustion efficiency of engine.