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35 results about "Deflagration to detonation transition" patented technology
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Deflagration to detonation transition (DDT) refers to a phenomenon in ignitable mixtures of a flammable gas and air (or oxygen) when a sudden transition takes place from a deflagration type of combustion to a detonation type of explosion.
Shaped walls for enhancement of deflagration-to-detonation transition
ActiveUS20070144179A1Increased turbulenceIncrease turbulent kinetic energyTurbine/propulsion fuel supply systemsTurbine/propulsion engine ignitionCombustorCombustion chamber
A detonation chamber for a pulse detonation combustor including: a plurality of dimples disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of dimples enhance a turbulence of a fluid flow through the detonation chamber
Owner:GENERAL ELECTRIC CO
Geometric configuration and confinement for deflagration to detonation transition enhancement
InactiveUS20070137172A1Increase elasticityWell mixedContinuous combustion chamberEfficient propulsion technologiesCombustorDeflagration to detonation transition
A pulse detonation combustor is provided with a fuel-air mixer located upstream from a detonation chamber. A fuel-air mixture exits the fuel-air mixer and enters the detonation chamber, where it is ignited by an ignition source. The flow from the fuel-air mixer passes over the surface of a center body, which extends downstream from the fuel-air mixer. The surface of the center body contains at least one turbulence generator, which imparts additional turbulence in the fuel-air mixture passing through the chamber. The turbulence generator aids in the mixing of the fuel and air of the fuel-air mixture to enhance the deflagration to detonation transition within the pulse detonation combustor.
Owner:GENERAL ELECTRIC CO
Detonative cleaning apparatus
InactiveUS7011047B2Pulsating combustionHollow article cleaningCombustionDeflagration to detonation transition
Methods and apparatus are provided for cleaning a surface within a vessel. A fuel / oxidizer charge is provided within a combustion conduit. An initial deflagration commenced in a first portion of the charge produces a final detonation at least in another portion of the charge to expel a shockwave from the conduit which impinges upon the surface. The deflagration-to-detonation transition may be encouraged by mechanical enhancements and / or by making the first charge portion more detonable than the second.
Owner:SHOCKSYST
Testing device and method for deflagration to detonation transition
InactiveCN103675194ASimple and fast operationReliable dataChemical analysis using combustionCombustionHigh energy
The invention relates to a testing device and method for deflagration to detonation transition. The device comprises a sample tube, a verification plate and a plug, wherein the sample tube is used for containing a sample to be tested, the verification plate is fixedly installed at one end of the sample tube and used for packaging the sample and detecting whether a perforation is formed in the verification plate or not during combustion of the sample, and the plug is fixedly installed at the other end of the sample tube. The method comprises the steps that the sample is ignited for testing when the sample is packaged in the sample tube, and meanwhile, detonation velocities of the sample between adjacent test holes are tested to obtain at least two groups of detonation velocities; if the perforation is formed in the verification plate, it proves that the sample has the deflagration to detonation transition, or if the detonation velocity of the sample is stable, it proves that the sample has the deflagration to detonation transition, wherein the stability of the detonation velocity of the sample refers to that the standard deviation of at least two groups of detonation velocity values is not more than 35. The device is particularly applicable to deflagration to detonation transition tests of high-energy propellants. Compared with traditional testing methods and devices for the deflagration to detonation transition, the testing device and method have the advantages that two evaluation indicators, namely, the perforation and the stable detonation velocity are adopted, so that the testing efficiency and the data credibility are improved.
Owner:XIAN MODERN CHEM RES INST
Shaped walls for enhancement of deflagration-to-detonation transition
ActiveUS7669405B2Increased turbulenceIncrease turbulent kinetic energyTurbine/propulsion fuel supply systemsTurbine/propulsion engine ignitionCombustorDeflagration to detonation transition
A detonation chamber for a pulse detonation combustor including: a plurality of dimples disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of dimples enhance a turbulence of a fluid flow through the detonation chamber.
Owner:GENERAL ELECTRIC CO
Jet ignition device of pulse detonation engine
InactiveCN102619643AIncrease working frequencyImprove convenienceIntermittent jet plantsRocket engine plantsDraining tubeDeflagration to detonation transition
The invention relates to a jet ignition device of a pulse detonation engine, which is characterized in that a jet tube is fixedly connected with a mixing chamber through a sealing clamp nut, an adjusting plug is mounted at the top end of the jet tube through a sealing nut and a clamping nut; a drain tube is arranged in a jet chamber inside the jet tube and is connected with the jet tube through a fixing rib, and the lower end of the drain tube extends into the mixing chamber; and an ignition seat is arranged on one side of the jet tube and is located at one end of an outlet of the drain tube. Compared with the time and the distance for generating detonation waves by normal ignition devices, the time and the distance for generating the detonation waves by the jet ignition device are shorter, accordingly the DDT (deflagration to detonation transition) time and distance is shortened. In this case, length of a detonation chamber can be further shortened so as to improve working frequency of the pulse detonation engine. After the detonation chamber is shortened, exhausting burden in the pulse detonation engine is reduced, so that expansion wave-beams generated from the outlet of the pulse detonation engine can catch up with pressure waves transmitted before, pressure disturbance in an air-inlet passage is reduced, and working stability of the pulse detonation engine is enhanced while better propulsive performance is achieved.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Detonative cleaning apparatus
InactiveUS20050112516A1Pulsating combustionHollow article cleaningCombustionDeflagration to detonation transition
Methods and apparatus are provided for cleaning a surface within a vessel. A fuel / oxidizer charge is provided within a combustion conduit. An initial deflagration commenced in a first portion of the charge produces a final detonation at least in another portion of the charge to expel a shockwave from the conduit which impinges upon the surface. The deflagration-to-detonation transition may be encouraged by mechanical enhancements and / or by making the first charge portion more detonable than the second.
Owner:SHOCKSYST
Duplex tab obstacles for enhancement of deflagration-to-detonation transition
ActiveUS20120047873A1Increased fluid turbulenceIncreased turbulenceContinuous combustion chamberPulsating combustionCombustorDeflagration to detonation transition
A detonation chamber for a pulse detonation combustor including: a plurality of duplex tab obstacles disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of duplex tab obstacles enhance a turbulence of a fluid flow through the detonation chamber.
Owner:GENERAL ELECTRIC CO
Detonation tube structure of multi-tube pulse detonation engine
InactiveCN102042121AReduce distanceReduce intensityIntermittent jet plantsDeflagration to detonation transitionDiameter ratio
The invention provides a detonation tube structure of a multi-tube pulse detonation engine, which is characterized by comprising at least two detonation tubes, wherein the central axes of all detonation tubes are uniformly distributed along the circumferential direction; two adjacent detonation tubes along the circumferential direction are communicated through a circular arc flame crossover tube; the internal diameter ratio of the flame crossover tube to the detonation tubes is 1 / 3:1; the distance between the central axis of the flame crossover tube and the fuel nozzle of each detonation tube is 2 to 4 times the internal diameter of the detonation tube; and an igniter is arranged at the middle position of the wall of each flame crossover tube. By the detonation tube structure, the ignition energy of a single tube in the multi-tube pulse detonation engine can be improved on the premise of small energy ignition, the deflagration to detonation transition (DDT) distance of the single tube under the same ignition condition is shortened, the adverse effect of fuel gas back transmission on the air-breathing multi-tube pulse detonation engine can be reduced, and the synchronism of multi-tube work is improved.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Thermally initiated venting system and method of using same
ActiveUS20070240600A1Ammunition storageAmmunition loadingShaped chargeDeflagration to detonation transition
An apparatus includes a thermally-activated, deflagration initiation device, a deflagration-to-detonation transition manifold, a first transfer line connecting the deflagration initiation device and the deflagration-to-detonation transition manifold, and a linear shaped charge coupled with the first transfer line. An apparatus includes a heat-to-detonation transition manifold, a heat pipe connected to the transition manifold, a linear shaped charge, and a transfer line connecting the heat-to-detonation transition manifold and the linear shaped charge. An apparatus includes a thermally-activated pyrotechnic train and a linear shaped charge coupled with the pyrotechnic train. A method includes initiating a deflagrating material at a predetermined temperature or within a predetermined range of temperatures, initiating a detonating material with the deflagrating material, and initiating a linear shaped charge with the detonated material.
Owner:LOCKHEED MARTIN CORP
Deflagration-to-detonation transition energy gathering explosive device
InactiveCN108627058ASolve the problem that it cannot be ignited directly with high-voltage electric sparkImprove reliabilityBlastingPressure riseDeflagration to detonation transition
The invention discloses a deflagration-to-detonation transition energy gathering explosive device, and belongs to the technical field of explosive devices. The deflagration-to-detonation transition energy gathering explosive device comprises a high-pressure electric spark ignition device and an energy gathering explosive device, wherein the energy gathering explosive device comprises an explosivecharging container and a shaped charge cover; the explosive charging container comprises a barrel-shaped explosive charging container body and a top cover; an ignition electrode mounting hole is formed in the top cover; the shaped charge cover is arranged in the barrel-shaped explosive charging container body; a detonating explosive charging layer, a booster explosive layer and a high explosive layer are arranged above the shaped charge cover inside the barrel-shaped explosive charging container body from top to bottom in sequence; the detonating explosive charging layer comprises a mixed explosive charging layer, a bulk hexogen layer and a hexogen grain from top to bottom in sequence; the mixed explosive charging layer is a mixture of black powder, active metal powder and perchlorate; thehigh-pressure electric spark ignition device comprises a power source, a pressure rising device and two ignition electrodes; and the two ignition electrodes are arranged on one insulation plug whichis arranged in the ignition electrode mounting hole. The deflagration-to-detonation transition energy gathering explosive device can realize safe and stable detonation, generates effective shaped charge jet and is suitable for silenced detonation.
Owner:南京君缘科爆工程技术有限公司 +1
Safe and environment-friendly initiating explosive substituent and preparation method thereof
The invention discloses a safe and environment-friendly initiating explosive substituent and a preparation method thereof. In a microstructure, the initiating explosive substituent takes fine particle high explosive as a core, takes an additive which burns at a high speed as a housing; and the initiating explosive substituent is quick in combustion and deflagration to detonation transition capability due to the special microstructure. The explosive substituent disclosed by the invention can be taken as a safe and environment-friendly initiating explosive, to replace the existing conventional explosives which are poor in safety, contains heavy metal or generates a mass of wastewater in the process of preparation, such as GTG, lead azide, DDNP (dinitrodiazophenol), lead trinitroresorcinate and BNCP. According to the invention, the problems of security risk and environment occur when the exciting initiating explosive for a detonating cap is prepared can be solved, and the normal size and the low cost of the detonating cap can be kept simultaneously.
Owner:INST OF CHEM MATERIAL CHINA ACADEMY OF ENG PHYSICS
Testing device for testing deflagration to detonation transition performance of propellant powder
The invention discloses a testing device for testing the deflagration to detonation transition performance of propellant powder. The testing device comprises an electric igniter, an end cover, ignition powder, a pressure sensor, a deflagration to detonation transition pipe and charged propellant powder, and further comprises a sleeve, a simulated bullet and a simulated launching pipe. The end cover is a cylinder with a center step through hole in the axial direction, and is connected with the sleeve through threads, the igniter and the ignition powder are arranged in the center through hole of the end cover, the sleeve is a cylinder with an observation slot along a generatrix of the cylinder, the deflagration to detonation transition pipe is arranged in the sleeve, and is compactly filled with the charged propellant powder, and the charged propellant powder is in close contact with the ignition powder. The simulated launching pipe is a cylinder with external threads at one end, and is connected with the sleeve through the threads, and the simulated bullet is arranged in the simulated launching pipe. The error of testing the wave surface-time relation of explosive and powder deflagration and detonation can be reduced, and the simulated launching pipe is closer to a real launching pipe, and can be equivalent to the actual launching environment.
Owner:XIAN MODERN CHEM RES INST
Spiral multi-channel pulse detonation engine
InactiveCN103899436AEffective use of space sizeShort filling timeIntermittent jet plantsRocket engine plantsInlet channelDeflagration to detonation transition
The invention discloses a spiral multi-channel pulse detonation engine which comprises an engine shell, spiral partition plates, gas inlet slots, a plurality of spark plugs and a gas inlet rotor. The engine shell is circular, the spiral partition plates are fixed onto an inner ring wall of an annular cavity to form spiral channels, and the gas inlet slots are formed in the inner ring wall and are positioned among the spiral partition plates; two spiral slots which are in identical shapes are formed in the gas inlet rotor and are used as common gas inlet channels. The gas inlet rotor is in close fit with an inner ring of the engine shell and can freely rotate. The multiple spark plugs are mounted at the ends of the engine, are correspondingly matched with the spiral channels on the inner ring wall and are controlled by a computer, an automatic ignition effect can be realized according to the rotational speed of the gas inlet rotor and phase of the gas inlet channels, and accordingly a multi-tube time-sharing initiation effect can be realized. The spiral multi-channel pulse detonation engine has the advantages that a low-energy ignition mode is adopted by the engine, so that axial DDT (deflagration to detonation transition) distances can be shortened, and the spatial size of the engine can be effectively utilized; the gas inlet slots are formed in positions along a detonation chamber, and gas can flow into the spiral multi-channel pulse detonation engine via the gas inlet slots, so that the spiral multi-channel pulse detonation engine is short in filling time and high in gas inlet filling speed, and the detonation frequency can be increased.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Duplex tab obstacles for enhancement of deflagration-to-detonation transition
ActiveUS8881500B2Increased fluid turbulenceIncreased turbulenceContinuous combustion chamberPulsating combustionCombustorDeflagration to detonation transition
A detonation chamber for a pulse detonation combustor including: a plurality of duplex tab obstacles disposed on at least a portion of an inner surface of the detonation chamber wherein the plurality of duplex tab obstacles enhance a turbulence of a fluid flow through the detonation chamber.
Owner:GENERAL ELECTRIC CO
Experimental device and experimental method for influence of convective combustion on deflagration to detonation transition
ActiveCN108088949AAvoid cloggingReduce in quantityChemical analysis using combustionCombustionExperimental methods
The invention relates to an experimental device and an experimental method for influence of convective combustion on deflagration to detonation transition. The experimental device comprises an ignition head, ignition powder, an initial end cover, a deflagration to detonation transition tube, a phenolic resin casing pipe, an experimental sample of an energetic material, a punching net pipe, a speedmeasurement probe, a pressure sensor, a strain gauge and a tail end cover, wherein the initial end and the tail end of the deflagration to detonation transition tube are respectively connected with the initial end cover and the tail end cover; the phenolic resin casing pipe is positioned in the deflagration to detonation transition tube and is in clearance fit with the deflagration to detonationtransition tube; the punching net pipe is arranged on the tail end cover by a stepped hole in the tail end cover and is used for forming convective combustion and controlling the intensity of the convective combustion; an experimental sample is putted into the phenolic resin casing pipe and the punching net pipe can be putted into the experimental sample; the pressure sensor and the speed measurement probe are inserted into the experimental sample through pressure measurement holes in the deflagration to detonation transition tube and speed measurement holes in the phenolic resin casing pipe;the strain gauge is arranged between two adjacent pressure measurement holes of the deflagration to detonation transition tube.
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY
Multi-tube detonation lateral wave ignition device
InactiveCN101858278AChange relatively independent featuresIgnition continues uninterruptedIntermittent jet plantsRocket engine plantsCombustionHigh energy
The invention relates to a multi-tube detonation lateral wave ignition device comprising a plurality of parallel detonation tubes, lateral flame tubes and flame check valve assemblies, wherein the lateral flame tubes are connected with the adjacent detonation tubes and form lateral flame channels of which the tails and the heads are communicated in a system, and the flame check valve assemblies are arranged in the lateral flame tubes. Not only flames in the upstream detonation tubes move to the exit of a spray tube, the branches of the flames also enter the lateral flame tubes, and lateral combustion waves in the tubes move to the adjacent downstream detonation tubes by the flame check valve assemblies to ignite premixed fuels in the downstream detonation tubes to realize combustion; the process is circulated in cycles among the detonation tubes to realize the deflagration to detonation transition (DDT) process of the ignition self-sustaining of a detonation tube system. The invention has simple structure, can meet the demands of high frequency and high-energy ignition and overcome the difficulties of continuous ignition and deflagration to detonation transition. The invention can be used as the ignition realizing mode of a multi-tube pulse detonation engine.
Owner:SHANGHAI UNIV
Thermally initiated venting system and method of using same
ActiveUS7530314B2Ammunition storageAmmunition loadingShaped chargeDeflagration to detonation transition
An apparatus includes a thermally-activated, deflagration initiation device, a deflagration-to-detonation transition manifold, a first transfer line connecting the deflagration initiation device and the deflagration-to-detonation transition manifold, and a linear shaped charge coupled with the first transfer line. An apparatus includes a heat-to-detonation transition manifold, a heat pipe connected to the transition manifold, a linear shaped charge, and a transfer line connecting the heat-to-detonation transition manifold and the linear shaped charge. An apparatus includes a thermally-activated pyrotechnic train and a linear shaped charge coupled with the pyrotechnic train. A method includes initiating a deflagrating material at a predetermined temperature or within a predetermined range of temperatures, initiating a detonating material with the deflagrating material, and initiating a linear shaped charge with the detonated material.
Owner:LOCKHEED MARTIN CORP
System and Method for Power Production Using a Hybrid Helical Detonation Device
InactiveUS20090322102A1Shorten the lengthFast fillEngine manufactureGas turbine plantsCombustion chamberEngineering
The system and method described herein uses a hybrid pulsed detonation engine (PDE) system to drive a turbine that powers an electric generator. The combustion chamber of the PDE is shaped in a helical form, so that the external length of the section is reduced, while maintaining the distance for acceleration to detonation. This allows the achievement of deflagration to detonation transition without the help of turbulence enhancing obstacles, while keeping the overall size of the detonation tube small. The PDE output can be scaled by: increasing the cross sectional area of the detonation chamber; increasing the number of detonation tubes; and increasing the frequency of operation of the PDE. The replacement of conventional deflagrative internal combustion engines, including gas turbines and reciprocating engines, with pulsed detonation engines for electric power generation, may provide fuel savings and have a lower environmental impact.
Owner:BOARD OF RGT THE UNIV OF TEXAS SYST
Detonative cleaning apparatus
InactiveUS20060185623A1Hollow article cleaningBoiler cleaning apparatusCombustionDeflagration to detonation transition
Methods and apparatus are provided for cleaning a surface within a vessel. A fuel / oxidizer charge is provided within a combustion conduit. An initial deflagration commenced in a first portion of the charge produces a final detonation at least in another portion of the charge to expel a shockwave from the conduit which impinges upon the surface. The deflagration-to-detonation transition may be encouraged by mechanical enhancements and / or by making the first charge portion more detonable than the second.
Owner:AARNIO MICHAEL J +2
True temperature multispectral measurement method for deflagration to detonation transition process
InactiveCN111044565ARealize temperature calibrationMaterial heat developmentSensing radiation from gases/flamesExplosive AgentsSpectrograph
The invention discloses a true temperature multispectral measurement method for a deflagration to detonation transition process, and solves the problem that the true temperature cannot be obtained byusing an existing method. According to the invention, optical signals generated during deflagration or detonation of explosives and charges are transmitted to a DMD spectrograph to form a plurality ofspectrum channels and corresponding radiance information by optical fibers through an optical detection unit before the optical fibers are damaged, and the true temperature and the spectral emissivity of a solid product in the deflagration to detonation transition process of the explosives are obtained through inversion. The method has the characteristics of wide temperature measurement range, high sampling frequency and high measurement precision. The method is suitable for real-time measurement of the true temperature and spectral emissivity of high-temperature solid products in the deflagration to detonation transition process based on a sample tube method, and is also suitable for measurement of the deflagration temperature or detonation temperature of other energetic materials with the temperature ranging from 1400 DEG C to 4000 DEG C.
Owner:XIAN MODERN CHEM RES INST
Internal Detonation Reciprocating Engine
InactiveUS20090126343A1Improve efficiencyHigh densityInternal combustion piston enginesJet propulsion plantsCombustionMaster cylinder
A method of rotating a crank shaft and in internal detonation engine are provided. The internal detonation engine comprises a deflagration to detonation transition section. The deflagration to detonation transition section is connected to a main cylinder, which houses a piston. Inducing a detonation wave from the deflagration wave and passing the detonation wave through a fluid, gives rise to high pressure and temperature in a cylinder and pushes a piston towards bottom dead center. An internal detonation reciprocating engine may be a single cylinder and may be either a two or four stroke engine. A two-stroke internal detonation reciprocating engine is similar to a four-stroke internal detonation reciprocating engine but has different valve placements. Detonations produce a more thorough combustion of the fuel and may, thereby, yield reduced emissions of carbon monoxide as compared to internal combustion engines.
Owner:LU FR K +4
Pulse detonation engine with ejector and method for processing main detonation tube
InactiveCN102174913AReduce the temperatureImprove thermal fatigue lifeRocket engine plantsThermal fatigueDeflagration to detonation transition
The invention provides a pulse detonation engine with an ejector and a method for processing a main detonation tube. The invention is characterized in that one end of an ejector is a horn-shaped expansion section, the wall surface of the expansion section is a 1 / 4 arch wall surface; the relation between the radius R of an arc section and the inner diameter D of a cylindrical section is as follows: 2 / 5is less than or equal to R / Dis less than or equal to 3 / 5; the ejector and a main detonation tube are installed coaxially, the relation between the inner diameter d of the main detonation tubes and D is as follows: 2 / 5is less than or equal to d / Dis less than or equal to 3 / 5; L represents the axial distance the main detonation tube stretches into the ejector, the relation between L and d is as follows: 2is less than or equal to L / dis less than or equal to 6; a spiral channel is arranged in the tube wall of the main detonation tube. In the invention, by designing the entrance structure of the ejector, the structural relationship between the main detonation tube and the ejector and the spiral channel in the tube wall of the main detonation tube, reignited fuel oil can be fully heated inside the tube wall, which is conducive to the reduction of DDT (deflagration to detonation transition) distance, the lowering of the temperature of the main detonation tube and the lengthening of the thermal fatigue life of the main detonation tube.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Safe detonator
The invention discloses an essentially safe detonator for civil use or engineering blasting. According to the safe detonator, a perchlorate carbon hydrazide complex is served as an initiating explosive; and the pressure switching effect exists in the deflagration to detonation transition process of such initiating explosives, so that the deflagration to detonation transition process can be realized reliably in an airtight state of sealing the detonator, thereby outputting detonation waves; and the deflagration to detonation transition process cannot be realized in a pressure relief state of opening the detonator. Therefore, the detonator only utilizing the initiating explosive has special use safety and reliability and can be assembled together with the electric ignition components of an electric heating wire, magnetoelectric ignition components, the ignition control components of an electronic circuit or the ignition components of an explosive-guiding pipe to form a safe electric detonator, a safe magnetoelectric detonator, an essentially safe electronic detonator or a safe explosive-guiding detonator so as to be used for civil blasting equipment. As a result, accidental explosion accidents are controlled effectively as well as terrorist events are prevented.
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY
Backflow type detonation tube structure for pulse detonation engine
InactiveCN109209681AShorten the axial distanceShorten the axial lengthRocket engine plantsCombustion chamberDeflagration to detonation transition
The invention provides a backflow type detonation tube structure for a pulse detonation engine. With a bent pipeline structure adopted, the axial distance of the detonation tube can be greatly reduced, the axial length of the pulse detonation engine can be decreased, the weight of the pulse detonation engine can be reduced, the structure of a detonation combustion chamber is more compact, the heatcapacity intensity of the combustion chamber can be increased, and the engine can obtain greater thrust / power; and with a fan-shaped pipeline structure adopted, the detonation tube in the combustionchamber is distributed more reasonably, and the capacity of the detonation tube is larger, and therefore, the thrust of the pulse detonation engine can be improved; a fan-shaped obstacle in the detonation tube has a semi-circular cross section, and the fan-shaped obstacle enables a better DDT (deflagration to detonation transition) shortening effect compared with an ordinary rectangular-section obstacle.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
a safety detonator
ActiveCN103148745BSimple methodLow input costAmmunition fuzesDetonatorDeflagration to detonation transition
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY
Internal Detonation Reciprocating Engine
InactiveUS20090320812A1High densityImprove pressure resistanceReciprocating combination enginesInternal combustion piston enginesCombustionMaster cylinder
A method of rotating a crank shaft and in internal detonation engine are provided. The internal detonation engine comprises a deflagration to detonation transition section. The deflagration to detonation transition section is connected to a main cylinder, which houses a piston. Inducing a detonation wave from the deflagration wave and passing the detonation wave through a fluid, gives rise to high pressure and temperature in a cylinder and pushes a piston towards bottom dead center. An internal detonation reciprocating engine may be a single cylinder and may be either a two or four stroke engine. A two-stroke internal detonation reciprocating engine is similar to a four-stroke internal detonation reciprocating engine but has different valve placements. Detonations produce a more thorough combustion of the fuel and may, thereby, yield reduced emissions of carbon monoxide as compared to internal combustion engines.
Owner:BOARD OF RGT THE UNIV OF TEXAS SYST
An experimental device and method for the effect of convective combustion on combustion transition to detonation
ActiveCN108088949BAvoid cloggingReduce in quantityChemical analysis using combustionExperimental methodsCombustion
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY
A test device for measuring the combustion-to-detonation performance of propellants
InactiveCN104634192BReduce mistakesAmmunition testingDeflagration to detonation transitionDeflagration
Owner:XIAN MODERN CHEM RES INST
A combustion-to-detonation test device and method
InactiveCN103675194BSimple and fast operationReliable dataChemical analysis using combustionCombustionHigh energy
The invention relates to a testing device and method for deflagration to detonation transition. The device comprises a sample tube, a verification plate and a plug, wherein the sample tube is used for containing a sample to be tested, the verification plate is fixedly installed at one end of the sample tube and used for packaging the sample and detecting whether a perforation is formed in the verification plate or not during combustion of the sample, and the plug is fixedly installed at the other end of the sample tube. The method comprises the steps that the sample is ignited for testing when the sample is packaged in the sample tube, and meanwhile, detonation velocities of the sample between adjacent test holes are tested to obtain at least two groups of detonation velocities; if the perforation is formed in the verification plate, it proves that the sample has the deflagration to detonation transition, or if the detonation velocity of the sample is stable, it proves that the sample has the deflagration to detonation transition, wherein the stability of the detonation velocity of the sample refers to that the standard deviation of at least two groups of detonation velocity values is not more than 35. The device is particularly applicable to deflagration to detonation transition tests of high-energy propellants. Compared with traditional testing methods and devices for the deflagration to detonation transition, the testing device and method have the advantages that two evaluation indicators, namely, the perforation and the stable detonation velocity are adopted, so that the testing efficiency and the data credibility are improved.
Owner:XIAN MODERN CHEM RES INST
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