35results about How to "Shorten ignition delay" patented technology

A geometric compression ratio in an engine main body 1 is set to 15 or less. Injection control means (ECU 40) performs a main injection of injecting fuel near a compression top dead center, and a preceding injection prior to the main injection at a specific region of predetermined load within an operating region on a relatively low-speed side. The injection control means performs, as the preceding injection, a pilot injection of performing injection at a timing such that at least part of a fuel spray reaches outside a cavity 31 on a top face of a piston, and a pre-injection of injecting fuel at a predetermined timing after the pilot injection, to suppress thereby ignition of the fuel injected by the pilot injection and shorten an ignition delay of the fuel injected by the main injection.

Composite combustion catalyst particles are described and disclosed. A metal core of a combustible metal can be coated with a metal oxide coating. Additionally, a catalyst coating can at least partially surround the metal oxide coating to form a composite catalyst particle. The composite catalyst particles can be dispersed in a variety of fuels such as propulsion fuels and the like to form an enhanced fuel. During initial stages of combustion, the catalyst coating acts to increase combustion of the fuel. As combustion proceeds, the metal core heats sufficiently to disturb the metal oxide coating. The metal core then combusts in highly exothermic reactions with an oxidizer and the catalyst coating to provide improved energy densities to the enhanced fuel. Enhanced fuels using these composite combustion catalyst particles can exhibit decreased ignition delay times and increased energy densities sufficient for use in high performance propulsion applications such as pulse detonation engines, scramjets, and ramjets.

The invention relates to a diesel engine and a method of controlling the diesel engine. The diesel engine includes an engine body to be supplied with fuel containing diesel fuel as its main component, a geometric compression ratio being set to 15:1 or below, a fuel injection valve arranged in the engine body so as to be oriented toward a cylinder of the engine body and for directly injecting the fuel into the cylinder, and a control module for controlling a mode of injecting the fuel into the cylinder through the fuel injection valve. The control module performs a main injection where the fuel is injected to cause a main combustion mainly including a diffusion combustion and performs a plurality of pre-stage injections where the fuel is injected prior to the main injection to cause a pre-stage combustion prior to the main combustion. The control module controls the injection mode of the injections to adjust a heat release rate.

The invention relates to the technology of a propeller, which aims to provide a boron-based solid fuel propeller igniting through a plasma generator. The boron-based solid fuel propeller igniting by using the plasma generator comprises an air inlet, a gas generator, a secondary combustion chamber and a tail sprayer nozzle. The gas generator is internally provided with the boron-based solid fuel, the plasma generator is arranged at the tail end of the gas generator, and the plasma injection opening is aligned with solid fuel. The propeller further comprises an electric control and adjustment system for adjusting the power of the plasma generator and a cooling water system for cooling. The plasma generation process is stable, and high density heat can be provided within a certain time. Compared with conventional igniting powder applied to ignition of the boron-based solid fuel propeller, the ignition is not limited by operation time. Compared with the conventional igniting powder, the temperature is greatly enhanced, and ignition of the boron-based solid fuel can be realized. The ignition power of the plasma can be precisely adjusted through the power adjusting system, so that the invention provides the boron-based solid fuel propeller suitable for different dosages.

A diesel fuel composition comprising an organic nitrate is described. The organic nitrate may be a terpene nitrate. Methods of using an organic nitrate for achieving a desired cetane number, and uses of organic nitrates for the purpose of reducing the ignition delay of the fuel and/or for increasing its cetane number to a defined level are also described, as are methods of operating a compression ignition engine.

A piston for an internal combustion engine and method of construction thereof are provided. The piston includes an upper crown formed at least in part by a first metal material and a thermally insulating insert. The upper crown has an upper wall forming an upper combustion surface and a ring belt region. The upper combustion surface is formed at least in part by the thermally insulating insert. The thermally insulating insert has a base surface with pores extending upwardly therein. The first metal material is infused and solidified in the pores, with the first metal material forming a first bonding surface. The piston further includes a body portion formed from a second metal material. The body portion provides pin bosses having coaxially aligned pin bores and diametrically opposite skirt portions. The body portion has a second bonding surface bonded to the first bonding surface of the first metal material.

Disclosed is a biodiesel fuel additive composition which accelerates combustion phenomenon, reduces ignition delay, and improves Cetane number, thereby lowering particulate emissions, and improving fuel economy in diesel engines.

The present invention relates to an injection nozzle for an internal combustion engine in a motor vehicle. A nozzle body has at least one spray hole, a nozzle needle mounted in the nozzle body with adjustable stroke for controlling an injection of fuel through the at least one spray hole. A booster piston is drive-coupled to an actuator and has a booster face which delimits a booster chamber. According to the invention, the nozzle needle has a control face which delimits a control chamber. In order to dampen the movement of the nozzle needle into its needle seat as the nozzle needle closes, a damping piston is arranged in the nozzle body with an adjustable stroke. The damping piston separates the control chamber from the booster chamber. A damping path is provided in the damping piston to hydraulically connect the control chamber to the booster chamber in a throttled manner.

A self-adaptive regulation and control supercritical hydrothermal combustion type multi-element thermal fluid generation system comprises a reactor, a material pretreatment module, an oxidizing agent supply module, a cooling module, a temperature and pressure regulating module and the like, and the reactor, the material pretreatment module, the oxidizing agent supply module and the supercritical hydrothermal combustion reaction module are used for generating multi-element thermal fluid; the pressure and the temperature of the multi-element thermal fluid are adjusted through the temperature and pressure adjusting module, the wall face of the reactor is protected through the cooling module, the multi-element thermal fluid meeting the exploitation requirement is safely and stably produced, and a feasible scheme is provided for efficient exploitation of thickened oil.

The invention discloses a carborane plasticized boron-containing fuel-rich propellant, the propellant takes a carborane derivative with weak polarity as a plasticizer and boron powder as a fuel, and the carborane plasticizer has a rigid boron cage structure with high calorific value characteristic, a flexible alkane chain structure and a fluoride structure containing boron powder combustion efficiency. The propellant has good compatibility with components of the propellant, does not sublimate or migrate, improves the processing property of the propellant, improves the energy performance and combustion performance of the propellant, reduces the generation of condensed phases, and improves the service life of the propellant. The technical requirements of the solid ramjet engine for high calorific value, excellent ignition performance, high combustion efficiency, low condensed phase, clean fuel gas and low residue of the propellant are met, and a solid foundation is laid for solving the power source requirement problem of the solid ramjet engine.

The invention relates to the technical field of commercial kitchen ware and in particular discloses an ejector matched with a high-depth combustion chamber and a combustor of an ignition structure, wherein an air ejection hose is arranged at the bottom of a distributor, an air flow ejected by the air ejection hose can dredge gas in the combustion chamber to flow out of the combustion chamber to reduce the probability of occurrence that the gas vibrates to induce squeal, and air ejected by the air ejection hose supplements air secondarily for combustion reaction of primary fire and mixed gas, so that the air flow of the fixed gas in the main fire can be reduced. A kindling material fire ejecting port is arranged in the inner side surface of an oil-water sundry reserving basin, so that the main fire and the mixed gas can be ignited quickly and stably to reduce the ignition time delay and avoid detonation generated by accumulation of the mixed gas. The ejector has independent tissue air and gas supplying and mixing and combusting functions and an independent kindling material mixed gas distribution chamber. An ignition needle function is not affected by a combustion flame in the distributor fully, so that the ejector has fully independent self-combustion and self-regulation function.

The invention discloses an artillery microwave ignition device, and belongs to the technical field of artillery ignition. According to the artillery microwave ignition device, a coaxial resonant cavity is adopted as a microwave ignition cavity, the coaxial resonant cavity is filled with the gunpowder medium, through holes are evenly distributed in the outer conductor of the coaxial resonant cavity and used for enabling flames after gunpowder ignition to be evenly sprayed out from the through holes, and the purpose that propellant powder is ignited at multiple points at the same time is achieved. The structure is simple, the structure of an ignition emission part of a conventional artillery is slightly changed, and the structure can be conveniently applied to an artillery system. Compared with the prior art, the artillery microwave ignition device can be conveniently and rapidly assembled and debugged, the test efficiency is greatly improved, the trajectory performance of an artillery is effectively improved, and engineering and modularization of artillery microwave ignition are achieved.

The invention relates to a micro-combustor based on a liquid fuel, and relates to the technical field of engines. According to the micro-combustor based on the liquid fuel provided by the invention, firstly, the species of fuel oil have no any limitation, so that various liquid-state fuels and even gas-state fuels can be adopted; secondly, the fuel oil is preheated so as to be ensured to be high-efficiently evaporated and combusted; thirdly, the ignition delay is shortened, the success rate of ignition is improved, and the fuel oil and fuel gas residence time can be prolonged with a smaller size, so that the geometric dimension required for an ignitor is reduced; and fourthly, the heat load formed in the inner wall during the combustion process can be effectively absorbed, so that the surface temperature is reduced, and the service life of the combustor is prolonged.

Regulated pneumatic gas is supplied through a gas supply tube (14) which is welded to a pilot valve housing (18) which accommodates a solenoid valve (16). When the solenoid valve is electrically activated and opened, the pneumatic gas flows through a bifurcated channel (22) which is welded to the pilot valve housing and to a fuel valve mechanism (24A) and to an oxidizer valve mechanism (24B). The force of the pneumatic gas causes pistons (38A, 38B) to actuate respective poppets (36A, 36B). Movement of the poppets results in the dispensing of fuel propellant from a fuel outlet chamber (44A) and the dispensing of oxidizer from an oxidizer outlet chamber (44B). The fuel valve mechanism and oxidizer valve mechanism are positioned and oriented such that the exiting fuel and oxidizer are mixed in a vortex rocket engine.

Ignition of a gas discharge lamp 10, which has a gas containing main space and two inner electrodes, of a lighting unit 4 of a lighting system is achieved by the use of a high frequency resonance circuit. The resonance circuit is connected to the inner electrodes and to a supply device 2, which supplies an alternating supply voltage. An outer electrode 22 is arranged near one the inner electrodes and to a node of the resonance circuit. Upon supplying the supply voltage a high voltage alternating burst will be generated at the outer electrode. This will result into a discharge of the gas in the main space. In turn, this will induce a discharge of the remaining gas. Then the frequency of the supply voltage will increase and a small reactive current only will remain to flow through the resonance circuit.