35 results about "Deflagration to detonation transition" patented technology

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.

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.

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.

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.

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.

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.

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.

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.