35results about How to "Shorter ignition delay time" patented technology

The invention provides a small organic molecule gelling agent and its preparation method and application, belonging to the technical field of gel fuel. The organic small molecule gelling agent provided by the present invention contains a cyclopropane structure, and the cyclopropane structure belongs to a high-tension structure, which endows the gelling agent with excellent gel performance, and the high-tension cyclopropane structure can also greatly improve the combustion performance of the gelling agent. It can shorten the ignition delay of fuel and play a role in promoting combustion. Moreover, the multiple hydroxyl groups contained in the organic small molecule gel provided by the present invention can effectively form a gel through hydrogen bonding, so it has excellent gel performance for high energy density fuels and energetic nanofluid fuels and has shear Thinning properties, the minimum gelling agent is not higher than 1% when forming a stable gel.

The invention discloses a plasma on-duty flame igniter based on an aero-engine afterburner. The plasma on-duty flame igniter comprises a flame stabilizer and an embedded cathode combination. The embedded cathode combination comprises a connecting sleeve, a cathode shell, a transverse insulating pipe, a Y type cathode, a guide rod shell, a longitudinal insulating pipe and a power-on guide rod. Theconnecting sleeve is in threaded connection with the cathode shell, the right end of the connecting sleeve is welded to the flame stabilizer, the left middle portion of the transverse insulating pipeis arranged in the cathode shell, and the closed end of the Y type cathode is arranged in the transverse insulating pipe. The guide rod shell is vertically arranged on the top of the left side of thecathode shell, the upper middle portion of the longitudinal insulating pipe is arranged in the guide rod shell, after the lower end of the longitudinal insulating pipe penetrates through the cathode shell, the end of the longitudinal insulating pipe is located in the right portion of the transverse insulating pipe, and the upper middle portion of the power-on guide rod is arranged in the longitudinal insulating pipe. The problems that an existing aero-engine afterburner is bad in working environment and complex in structure, and stable rapid ignition and continuous organized combustion are notfacilitated.

A non-laminated gas producing agent and its production are disclosed. The non-laminated gas producing agent consists of oxygen-enriched carbamidine nitrate 40-60% with granularity 0.5-6mu, basic copper nitrate 10-28% as oxidant with granularity 0.5-6mu, copperon oxide of catalyst with primary oxidant 15-30% with granularity 0.1-6mu, and clay or paraffin wax 0.1-3% as process assistant with granularity 1-20mu. The production is carried out by: breaking the materials, adding into mixer by proportioning, mixing, sieving by screen, adding water 10-30%, agitating, drying, sieving the dried materials by screen with 20-80 mesh to obtain medicine particles, pressing into tablets, and drying the tablets under 100-120deg.C for 1.5-2.5hrs with water content <0.4%. It achieves wide regulating range, high gas output efficiency, and clean gas composition.

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 ramjet with a function of high-speed pre-atomization of liquid aviation kerosene. The ramjet comprises a shunt cone, a gas inlet channel wall surface, a combustion chamber wall surface, an exhaust nozzle wall surface, an oil storage tank and an oil delivering pipe, wherein the shunt cone is connected with the oil storage tank through the oil delivering pipe; the gas inletchannel wall surface, the combustion chamber wall surface and the exhaust nozzle wall surface are connected in sequence; the shunt cone and the oil storage tank which serve as one part are arranged in a cavity formed by the gas inlet channel wall surface, the combustion chamber wall surface and the exhaust nozzle wall surface; a gas inlet channel is formed between the shunt cone and the gas inletchannel wall surface, a combustion chamber flow channel is formed between the shunt cone and the combustion chamber wall surface, an exhaust nozzle flow channel is formed between the shunt cone and the exhaust nozzle wall surface, and the gas inlet channel, the combustion chamber flow channel and the exhaust nozzle flow channel communicate in sequence; and a gas inlet hole is formed in the top ofthe shunt cone. The economy and safety of the ramjet are improved.

The invention discloses a rail type sliding arc exciter based on plasma. The rail type sliding arc exciter based on the plasma comprises an exciter body and electrodes, wherein the number of the electrodes is at least two, and the electrodes are used for generating electric arcs; the exciter body comprises a first contact, a rotational flow section and a second connect, wherein the shape of the first contact and the shape of the second contact both are cylindrical, the shape of the rotational flow section is in a circular truncated cone shape, the first connect, the second connect and the rotational flow section are of an integrated forming structure, the axes of the first connect, the second connect and the rotational flow section are positioned on the same straight line, the small end ofthe rotational flow section is arranged at one end of the first connect, and the large end of the rotational flow section is arranged at one end of the second connect. According to the rail type sliding arc exciter, the structure is simple, the plasma is used for reinforcing combustion, the ignition boundary of an engine is expanded, the ignition success rate and the combustion efficiency of theengine are improved, and the rail type sliding arc exciter can be popularized and used.

The invention belongs to the field of laser propulsion, and in particular relates to an energy-containing liquid laser-enhanced propulsion device based on microfluidic technology. Including a microfluidic supply system, a microreaction mixed chip system and a laser ablation system; the microfluidic supply system and the microreaction mixed chip system are connected through a microtube, and the propellant is transmitted to the microreaction mixed chip system; the microreaction mixed chip system includes There are two micro-channels and a mixing combustion chamber. There is a nozzle at the outlet of the fluid, and the direction of the axis of the nozzle is the incident direction of the laser pulse; energetic propellants. The propulsion device of the present application can realize fast ignition, controllable thrust and flow, and can provide micro-satellites with high specific impulse and thrust-to-impulse ratio at the same time.