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.

The invention relates to a diesel engine and a method of controlling the same. The diesel engine of the present invention includes an engine body supplied with fuel containing diesel fuel as its main component, and the geometric compression ratio is set below 15:1; it is arranged in the engine body toward the cylinder of the engine body and directly injected a fuel injection valve for fuel into the cylinder; and a control module for controlling a pattern of injecting the fuel into the cylinder through the fuel injection valve. The control module performs a main injection such that the injected fuel produces a main combustion mainly comprising diffusion combustion, and performs a plurality of pre-stage injections prior to the main injection such that the injected fuel produces a pre-stage prior to the main combustion combustion. The control module controls an injection pattern of the injection to adjust a heat release rate.

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.

The invention relates to a micro gas-liquid dual-purpose high energy igniter, and relates to the technical field of engines. The micro gas-liquid dual-purpose high energy igniter has the advantages that 1) the success rate is increased, and the ignition lag time is shortened under the condition of relatively low ignition energy of a single igniter plug; 2) an efficient circumferential rotational flow structure can be formed in the igniter, the flue gas and flue oil retention time is prolonged, and mixing is enhanced, so that the formation of a stable flame structure is facilitated; 3) a circumferential vortex system structure is formed in a flow field, wherein the vortex system structure comprises a vortex system structure body clinging to the inside wall surface of an inner wall and a circumferential vortex system flow structure formed by entraining inner fluid by the vortex system structure body; 4) the ignition lag is reduced, the ignition success rate is increased, and the flue gasand flue oil retention time is prolonged on the premise of the smallest size of the igniter; and 5) the atomization effect can be ensured, and the fogdrop collision with a stone wall can be avoided.

The invention discloses a method for efficiently catalytically decomposing ammonium perchlorate based on energetic complex [Mn(BTO)(H2O)2]n. The method comprises mixing an energetic complex [Mn(BTO)(H2O)2]n and ammonium perchlorate according to a certain ratio and grinding; and putting the ground mixture in a nitrogen environment and reacting at 270-305 DEG C for 5-10 min. The employed catalyst [Mn(BTO)(H2O)2]n has extremely good catalytic decomposition effect on ammonium perchlorate, and is capable of greatly reducing the decomposition temperature, and control on decomposition temperature of ammonium perchlorate is realized by changing the addition amount of the catalyst. The method is simple and reliable, hopefully, the burning rate of spaceflight propellants can be improved, and the firing delay can be shortened.

The invention provides a fuel gas generating device. The fuel gas generating device comprises an injector (1), an oxidizing agent collector (2), a fuel collector (3) and a body (4), wherein the oxidizing agent collector (2) and the fuel collector (3) are arranged on the injector (1) which is connected to the body (4); an oxidizing agent and fuel enter the injector (1) respectively through the circular ring-shaped oxidizing agent collector (2) and the fuel collector (3), then are atomized by double coaxial nozzles (5) and coaxial direct-flow type nozzles (6) in the injector (1) and finally are burned; and products generated after burning enter the body (4). The fuel gas generating device solves the problems of long ignition delay time, low ignition reliability and uneven fuel gas outlet temperature, shortens ignition delay and improves ignition reliability and evenness of fuel gas outlet temperature from structural design.