219results about How to "Stable ignition" patented technology

The invention discloses a testing device of gunpowder combustion characteristics in vacuum, which mainly comprises a combustion chamber, a vacuum pump, an electric heater, a thermoelectric couple, a high speed camera and a data acquisition and processing system; wherein, the vacuum pump provides vacuum environment for the combustion chamber; by controlling the heating current and the heating time of the electric heater, different ignition isoperibols can be provided for tested gunpowder samples in the combustion chamber; and the data acquisition and processing system collects the test data generated by the thermoelectric couple and the gunpowder combustion images shot by the high speed camera when the tested gunpowder samples combust, and finally obtains the combustion characteristics of the tested gunpowder samples through corresponding processing and calculation. The invention not only can be used for testing the parameters such as combustion speed, combustion surface temperature and combustion heat and the like of the gunpowder in vacuum, but also can be used for the generation and collection of the combustion products of the gunpowder under different vacuum conditions. The invention has the overriding advantages of high integration level, obtaining various parameters by one testing and low testing expenses.

Device for depositing a coating on an internal surface of a container (10), of the type in which the deposition is carried out by means of a low-pressure plasma created inside the container (10) by excitation of a precursor gas by microwave-type electromagnetic waves. An injection tube (13) is provided that dips into the container (10) to a length of between one quarter and one half of the total height of the container (10) in question, between the top (18) and the bottom (17) of the container (10), said length of the injection tube (13) constituting a longitudinal antenna (16) capable of picking up a UHF electromagnetic wave generated by said generator (3) and of propagating the HT ignition signal, a UHF short-circuit (19) in the form of a plate (21, 23, 25) being provided on the injection tube (13) in such a way that the face of said plate (21, 23, 25) on the cavity side defines a point of zero amplitude of the electromagnetic wave propagating along said injection tube (13), the length between said short-circuit (19) and the free end (13a) of said injection tube (13) corresponding to an odd number of quarter-wavelengths so as to obtain a maximum amplitude, that is to say an antinode, at the free end (13a) of the injection tube (13).

A compression ignition gasoline engine uses low-cetane number fuel, such as gasoline. The engine includes a combustion control device having an injector directly injecting fuel into a combustion chamber, intake and exhaust valves, and a variable valve device changing a valve timing, in which the compression ignition gasoline engine includes: at least two intake valves and two exhaust valves; a spark plug positioned at the center portion of the combustion chamber; and an injector positioned adjacent to the spark plug toward the center portion of the combustion chamber, in which the exhaust valve is a symmetric valve lift in which the lift and the opening section of the tow exhaust valves are the same in low lift, and the intake valve is an asymmetric valve lift in which the lift and the opening of the two intake valves are different in the low lift.

The invention relates to a low-flow, high-mixing ratio and stepless regulation gas-liquid mixing gas generator, which comprises a round mixing channel, a spray head, an igniter and a body part. The spray head is arranged between the round mixing channel and the body part, and the opening of the spray head faces the body part; the igniter is arranged in the body part; and the round mixing channel comprises a fuel channel communicated with a fuel joint, a main air channel communicated with a main air joint, and an auxiliary air channel communicated with an auxiliary air joint. The technical problem that defects exist in the prior art is solved. The gas-liquid mixing gas generator can be reliably operated and realizes large-scale stable and high-efficiency combustion and stepless regulation.

A pilot combustor particularly for use in a burner of a gas turbine engine is provided. A method for burning a fuel in a pilot combustor zone of a pilot combustor is also provided. The pilot combustor includes rotationally symmetric walls defining a combustion room with an exit having a rich concentration of fuel in air for burning the fuel for the creation of a flow of an non equilibrium unquenched concentration of radicals elevated to a temperature above 2000 K in the combustion room and directed along a centre line of the pilot combustor through a throat at the exit of the pilot combustor, wherein a quarl is located downstream of the throat of the pilot combustor. According to the method the pilot combustor is arranged upstream of a burner for providing a main lean partially premixed combustion process.

An ignition device at least equipped with a DC power source, an ignition coil unit, a spark plug, an ignition switch, and an auxiliary power source, wherein the auxiliary power source is at least equipped with a discharge energy accumulating means, a discharge switch, and a discharge driver. The ignition device is further equipped with a secondary-current feedback controlling means comprising a secondary current detecting means for detecting a secondary current flowing during the ignition coil unit discharge period, and a secondary current feedback control circuit-for determining an upper limit and a lower limit for the secondary current from binary threshold values, and driving so as to open and close the discharge switch on the basis of the determination results. Furthermore, energy is introduced from the auxiliary power source without switching the polarity of the secondary current.

A combustion-powered, fastener-driving tool includes a cylinder and a combustion chamber disposed on top of the cylinder that accommodates a gaseous mixture of existing air in the combustion chamber and fuel injected therein. A spark plug generates a spark to combust the gaseous mixture in the combustion chamber. A trigger produces the spark in the spark plug when operated. A piston is movably supported in the cylinder and driven by combustion in the combustion chamber. A driving blade is coupled to the piston for driving a fastener. A spark controller is provided for generating a plurality of sparks in succession with the spark plug.

A control system for an internal combustion engine having at least one fuel injection valve for injecting fuel into a combustion chamber of the engine. A compression end temperature in the combustion chamber is estimated. A target compression end temperature is calculated according to an operating condition of the engine. A main injection and a plurality of pilot injections before the main injection are performed by at least one fuel injection valve. A fuel injection amount in a first-performed pilot injection of the plurality of pilot injections is controlled so that the estimated compression end temperature coincides with the target compression end temperature.

The invention discloses an air inlet of an air-breathing pulse detonation engine. The housing of the engine constitutes the circular air inlet, wherein an inlet cone is arranged on the medial axis at the rear end of the air inlet; a cylindrical structure at the rear part of the inlet cone and the housing of the engine constitute a ring-shaped channel; the air flow is fed into a special-shaped channel having a special-shaped structure via the ring-shaped channel; the special-shaped channel is evenly distributed on the circumference of the air inlet with the distance between the central symmetrical curve of the special-shaped channel and the medial axis of the engine remaining unchanged but deviating along the circumference; a fuel channel is arranged on the medial axis of the inlet cone, and the two ends of the fuel channel are connected with the fuel inlet and a fuel injection lever located on the medial axis outside the rear end of the cylindrical structure; the fuel injection lever is particularly a hollow oil tube with one end thereof being closed; a plurality of fuel injection holes are formed on the lateral surface of the fuel injection lever; the housing of the engine and the rear end surface of the cylindrical structure constitute a mixing chamber; and an igniter is located on the lateral wall of the mixing chamber. The invention can improve the atomization and evaporation of the fuel and reduce the impact of reversed fuel on the air inlet.

An auxiliary injection is carried out at an in-cylinder temperature at which a premixed combustion by the auxiliary injection is separatable into a low-temperature oxidation reaction and a high-temperature oxidation reaction, in a compression self-igniting internal combustion engine in which fuel injected into a cylinder from a fuel injection valve combusts in the cylinder, and that is configured to carry out an operation of fuel injection from the fuel injection valve. The operation of fuel injection includes at least a main injection and the auxiliary injection. The main injection causes a combustion mainly including a diffusion combustion in the cylinder. The auxiliary injection is carried out prior to the main injection and causes a combustion mainly including the premixed combustion in the cylinder. Specifically, an in-cylinder gas temperature (750K) is used as a reference, and the auxiliary injection is carried out before the in-cylinder gas temperature reaches 750K, so as to separate the low-temperature oxidation reaction and the high-temperature oxidation reaction from one another. This control makes the premixed combustion slow before a compression top dead center is reached, and ensures control of the premixed combustion in a temperature controlled manner in accordance with the transition of the in-cylinder gas temperature. This ensures unambiguous determination of the injection time of the auxiliary injection based on the in-cylinder temperature, and facilitates the attempt to simplify the fuel injection control.

A combustion type power tool having a combustion chamber in which a fan is rotatably provided and an ignition plug is exposed. A combustible gas and air are mixed together by the fan, and the mixture is ignited by a spark generated at the ignition plug. As a result of combustion, gas expansion occurs to permit a piston and a driver blade to move for driving a fastener into a workpiece. A spark energy is set in a range of from 0.04 J to 0.08 J.

The invention belongs to the field of aeroengines and mainly relates to a partial pre-mixing and pre-evaporation burning chamber with a prefilm type nozzle. The head of the burning chamber consists of an auxiliary burning level and a main burning level, wherein the auxiliary burning level comprises a primary axial swirler, a contraction section, a throat, an expansion section and an auxiliary oilway nozzle; and the main burning level comprises a primary axial swirler, a primary radial swirler, a pre-mixing section, a contraction throat and the prefilm type nozzle. The burning chamber at the head in the above structure adopts a DIPME (direct injection pre-mixing and pre-evaporation) mixed burning mode with central classification, when in small fire state, the auxiliary burning level adopts a rich oil direct injection burning mode, and when in large fire state, the auxiliary burning level adopts a lean oil direct injection burning mode, and the main burning level adopts a lean oil partial pre-mixing and pre-evaporation burning mode. In order to guaranteeing fuel oil atomization, the main burning level adopts the prefilm type nozzle. The head of the burning chamber can guarantee performance of the burning chamber, and pollutant discharge is greatly reduced.

A swirler for premixing a flow of fuel and a flow of air provided to a burner for a gas turbine engine is provided. The burner is provided with a swirler for mixing the air and the fuel and wherein the swirler is provided with swirler wings, wherein a channel formed between two adjacent swirler wings defines a passage. The swirler includes one fuel tube for gaseous fuel positioned in parallel on each side of a mixing rod in the passage, wherein the fuel tubes are provided with a plurality of diffuser holes distributed along the tube acting as gas injectors for efficiently distributing fuel in a flow of air passing through the swirler passage.

The invention relates to a three-stage stratified combustion high temperature rise combustion chamber structure which is applied to an aircraft engine high in thrust-weight ratio. An oil-gas mixing device at the head of a combustion chamber is divided into a precombustion stage and a main combustion stage. Precombustion stage fuel oil enters a precombustion area through a center direct jet nozzle and a precombustion stage pre-film nozzle to form a solid atomizer cone, and the stability of precombustion stage flame is improved. The main combustion stage injects fuel oil through two rows of fuel oil injection holes, the inner-layer fuel oil injection hole injects the fuel oil into a swirler air channel inside the main combustion stage, the outer-layer fuel oil injection hole injects the fuel oil into a swirler air channel outside the main combustion stage, and thus two combustion areas, that is, the inner-layer main combustion area and the outer-layer main combustion area are formed in the main combustion stage. The oil-gas ratio of the inner-layer main combustion area is larger than that of the outer-layer main combustion area, so that the inner-layer main combustion area is ignited by the precombustion stage flame more easily, and a stabilizing effect is further achieved on the outer-layer main combustion area by the inner-layer main combustion area. Step-by-step stable combustion is achieved among the three combustion areas, and hence the combustion stability of the head of the high temperature rise combustion chamber is jointly improved.

The invention relates to a fuel gas injection method for natural gas engines, in particular to a multiple-injection control method for a fuel supply device of a natural gas engine. The method includes that the natural gas engine is a four-stroke engine, and each working cycle of the natural gas engine includes four stages; the fuel supply device of the natural gas engine is arranged on the lateral side of a gas inlet, and natural gas and air are mixed for combustion in a cylinder; multiple-injection control of the fuel supply device is realized by adjusting injection times and quantity of natural gas supplied by the fuel supply device in a crank angle range from 2400 before top dead center of compression stroke of an engine piston to 2400 after top dead center of compression stroke of the engine piston. Aiming at different engine load conditions, stability in ignition of engines is guaranteed by means of partial stratification, flame propagation velocity is increased, and firing stability is improved.

This invention relates to coal tar pitch slurry and its preparation, and it belongs to waste residue disposal technology field and energy and environmental protection field. It mainly solves the problem of hard to burn directly of coal tar pitch. Its feature is that this coal tar pitch slurry is a fluid liquid fuel, and its components and their weight percentage is that coal tar pitch powder 50%-60%, water 38%-49.5%, dispersant 0.5%-2%. The preparation is that middle temperature coal tar pitch whose softening point is 85-95deg.C or high temperature coal tar pitch whose softening point is 100-110deg.C is freezed 20-28h with brittle temperature -30-15 deg.C, then shattered after adding surfactant, and then screening to get coal tar pitch powder with particle size 200-320 meshes, and then adding this coal tar pitch powder into water solution of dispersant, at last, coal tar pitch slurry fuel with good fluidity, good atomization performance, high combustion efficiency and low pollutants emission is produced by stirred homogeneously.

The invention discloses a microwave-assisted spark plug ignition method, comprising the steps of issuing a pulse signal to a spark plug system to trigger the same to generate a pulse high voltage; issuing a pulse signal to a microwave system to trigger the same to generate a microwave pulse of specific frequency and power; loading the pulse high voltage to a spark plug, breaking down thin gas via arc discharging to generate a plasma cluster; the plasma cluster can be expanded via microwave pulse irradiation to achieve ignition via thin combustion in an internal combustion engine. The invention also discloses a microwave-assisted spark plug ignition integrated set. The method of the invention combines the advantages of spark plug high-voltage discharge breakdown and those of microwave-to-plasma-cluster coupling energy; the integrated set of the invention includes a spark plug system and a microwave system, and achieves stable ignition via thin combustion in high-pressure environment of a combustor of the internal combustion engine.