[go: up one dir, main page]

WO2011070580A1 - Système de brûleur et procédé permettant d'augmenter l'efficacité d'un échangeur de chaleur - Google Patents

Système de brûleur et procédé permettant d'augmenter l'efficacité d'un échangeur de chaleur Download PDF

Info

Publication number
WO2011070580A1
WO2011070580A1 PCT/IL2010/001043 IL2010001043W WO2011070580A1 WO 2011070580 A1 WO2011070580 A1 WO 2011070580A1 IL 2010001043 W IL2010001043 W IL 2010001043W WO 2011070580 A1 WO2011070580 A1 WO 2011070580A1
Authority
WO
WIPO (PCT)
Prior art keywords
reaction chamber
compounds
reaction
friction
channel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/IL2010/001043
Other languages
English (en)
Other versions
WO2011070580A8 (fr
Inventor
Michael Zettner
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority to EP10835611.4A priority Critical patent/EP2510282B1/fr
Application filed by Individual filed Critical Individual
Priority to JP2012542687A priority patent/JP5633909B2/ja
Priority to BR112012014005A priority patent/BR112012014005A2/pt
Priority to AU2010329441A priority patent/AU2010329441B2/en
Priority to KR1020127017908A priority patent/KR101490784B1/ko
Priority to US13/514,144 priority patent/US9512997B2/en
Priority to CN201080063653.4A priority patent/CN102918325B/zh
Priority to CA2783769A priority patent/CA2783769C/fr
Publication of WO2011070580A1 publication Critical patent/WO2011070580A1/fr
Publication of WO2011070580A8 publication Critical patent/WO2011070580A8/fr
Priority to IL220266A priority patent/IL220266A/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C15/00—Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • F23C3/002—Combustion apparatus characterised by the shape of the combustion chamber the chamber having an elongated tubular form, e.g. for a radiant tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/12—Radiant burners
    • F23D14/126—Radiant burners cooperating with refractory wall surfaces
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/12—Radiant burners
    • F23D14/18—Radiant burners using catalysis for flameless combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23K—FEEDING FUEL TO COMBUSTION APPARATUS
    • F23K5/00—Feeding or distributing other fuel to combustion apparatus
    • F23K5/002—Gaseous fuel
    • F23K5/007—Details
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R7/00—Intermittent or explosive combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2200/00—Combustion techniques for fluent fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2205/00—Pulsating combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone

Definitions

  • the present invention is related to the field of burner systems and heat exchangers. Specifically the invention is related to a new design of burner that allows improved transfer of the heat energy produced in exothermic reactions to heat exchangers that are used for steam production and other systems that use heat exchangers to exchange heat energy from one medium into another.
  • burner-efficiency and/or heat exchanger efficiency or boiler efficiency would lead to an increase of the total efficiency or so called "system efficiency" of such a power station, would save costs, and would decrease the amount of carbon dioxide and excess heat that is created.
  • An increase of burner-efficiency, heat exchanger efficiency and/or boiler efficiency would also allow the use of fuels or compounds with - compared to usual fuel - low energetic value (often incorrectly referred to as low calorific value') and result in the same efficiency as high energy content fuels; thus allowing the use of otherwise waste products as fuels.
  • the reaction of two compounds takes - as an example— the time of 0.1 seconds, then the energy is released within this time and accordingly the volume of the compounds or gases created increases in a certain specific time that is related to the specific pressure and compounds.
  • the time that is needed to expand is also specific for each mixture and pressure and will remain the same as often as the reaction takes place with the same parameters of pressure and amount or masses of the reacting compounds.
  • the same compounds will always - under the same pressure and with the same amounts - react within the same time. In the example taken above: 0.1 sec. (Exceptions to this rule are mixtures with high amounts of non-reacting compounds.)
  • the gases will expand in a much shorter time when the pressure of the compounds in the reaction is increased.
  • the speed with which the resulting gases - that are formed in a reaction of the compounds - expands during and after the reaction is indirectly proportional to the reaction time and thus also directly proportional to the pressure of the compounds during the reaction.
  • the other compounds are actually hindering the chemical reaction because they are physically in the way between oxygen molecules and methane molecules, preventing them from reaching each other and reacting.
  • This effect increases and the flame propagation speed decreases.
  • the density of the buffer material increases and thus becomes less permeable to the compounds that can react chemically.
  • This effect can be compared to fire-protection doors in big buildings that slow down the propagation of a fire, or even hinder it to spread further.
  • Such fire- protection-doors are usually classified according to the amount of time they can delay the spreading of a fire.
  • expansion, deflagration, explosion and detonation all relate to the behaviour of reacting and thus expanding gases that are usually formed by a chemical or physical reaction of compounds, relative to the speed with which they are expanding. With increasing reaction and expansion speed, the way in which gases expand changes. At relative low subsonic speeds gases expand evenly.
  • the pressure of a wave-front from an explosion or detonation on a wall (when the spherical or partially spherical wave front hits the wall and the mass of the wave front goes through a negative acceleration) is much higher than the average pressure of these compounds at the point of time when the reaction starts.
  • the amount of energy that is in the spherically or partially spherically expanding gases is not evenly distributed throughout these gases but is highest at the outside, at the "shock-wave-front".
  • Friction also called 'fluid resistance'
  • This gas friction or fluid resistance increases with pressure and with speed.
  • the gas friction is directly proportional to the pressure of the flowing gases.
  • the gas friction increases exponentially over the pressure. This can best be understood as the mechanical collision of molecules or atoms of the gas or fluid passing through the pipe with molecules or atoms of the pipe.
  • the colliding molecules or atoms are thrown back into the stream and create a flow pattern as a result of being thrown back by the collision that disturbs the free flow until they create a blockage.
  • boundary layers can and will form. For example if a stream of gas flows over a solid surface than the molecules of the gas that are closest to the solid surface will change their path of flow - due to the surface structure of the solid material. Also if a hot gas is streaming over a relatively colder solid surface - no matter whether turbulent or laminar - the gas will transfer a part of its thermal energy to the solid surface and therefore change its properties, primarily its temperature and secondarily its density and therefore volume, thus creating a layer with different flow properties - also referred to as a "boundary layer" between the solid surface and the main part of the gas flow. If gases have to transfer heat energy into solids in heat exchangers, these boundary layers create - mostly unwanted - buffers between the solid wall and the main part of the gas stream, thus significantly decrease the efficiency of heat transfer.
  • a stream of hot gases with a nominal temperature measured in the middle of the hot gas stream has a certain temperature difference to the solid surface.
  • the higher this temperature difference the higher is the possible heat exchange rate.
  • the boundary layer however creates layers of gases that have already exchanged heat with the solid surface and thus react as buffers of lower temperatures - like insulation - between the hot area of the gas stream and the colder solid surface.
  • the temperature difference between the hot gas stream and the colder solid surface cannot be used for the heat exchange, just the much lower temperature difference between the molecules of the boundary layer - that have a lower temperature than the main gas stream - and the solid surface.
  • turbulent streaming of the hot gases is used - instead of laminar streaming.
  • the hot gases are streaming turbulently and can therefore exchange and replace layers that are forming at the boundaries to the solid surfaces.
  • using turbulent streaming instead of laminar streaming of hot gases leads to the effect that more time is necessary to perform the heat transfer.
  • the surface that is covered by turbulent streaming is bigger than the surface that is covered in the same time by a laminar streaming. Therefore the active surface where the heat exchange takes place has to be bigger than would be necessary if there were no effects like the boundary layer, and thus the heat is spread over a bigger surface. Therefore, as a direct consequence, the available temperature also decreases and the same amount of energy has to heat up a bigger surface.
  • Even though the net heat transfer is more efficient with turbulent streaming than with laminar streaming, in both cases only a part heat can be transferred.
  • the publication of Philip Panicker shows on slide 15/27 the "3-way Rotary Valve" for feeding and also on the same page above the rotary valve spring operated back-flow valves.
  • the Shchelkin Spiral disintegrates after a very short time due to the fact that it has to stand within the backflow of the wave front of the explosion or detonation and therefore receives extreme negative acceleration and heat from the wave front of the explosion or detonation. These extreme forces destroy the spiral after a few seconds of operation according to the findings of Philip Panicker and the photos he has published in the aforementioned publication.
  • the Shchelkin Spiral sits between the point of ignition and the outlet and thus results in the blocking of a wave front of an explosion or detonation.
  • the task of the Shchelkin Spiral is in no case to create a pulsing effect or to prevent backflow of wave fronts from explosions or detonations.
  • the invention is a burner system for reacting at least two fluid compounds at very high temperatures to produce controlled continuous pulsing explosions or detonations. After pulsing explosions or detonations are initiated, they are maintained by use of directed and controlled infrared radiation.
  • the burner system of the invention comprises:
  • each inlet chamber connected to each of the inlets, each inlet chamber adapted to prevent the compound that enters it from mixing with another compound;
  • reaction chamber adapted at an inlet end to be connected to a second end of the friction channel in order to receive the compounds that flow through the friction channel;
  • an ignition system adapted to initiate the operation of the burner system.
  • the pressure of the compressed compounds and the internal cross-sectional area and the surface characteristics of the inner surface of the friction channel are adapted to allow fast, free forward flow under pressure of the compounds through the friction channel into the reaction chamber and to create high gas friction for the much faster wave front of an explosion or detonation that takes place in the reaction chamber to prevent the wave front from passing backwards through the friction channel into the inlet chambers. In this way the friction channel is sufficiently blocked against the wave front of the explosion or detonation.
  • This causes the continuous repeated interruption of the flow of the compressed compounds forward into the reaction chamber and allows the build-up of continuous repeating pulses of the compounds under pressure in the reaction chamber. This allows continuous repeating pulsing explosions or detonations to take place in the reaction chamber.
  • the internal shape of the reaction chamber is configured to reflect and focus heat radiation in a form, determined and thus controlled by the shape of the inner surfaces of the reaction chamber into the path of the compounds streaming into the reaction chamber. This creates specific fields of overlapping infrared radiation having sufficiently high temperature to ignite the compounds at a specific point inside the reaction chamber and thus initiates an explosion or detonation after a specific amount of compounds have entered the reaction chamber.
  • the internal shape of the reaction chamber at the entrance side is conical, in the middle essentially cylindrical, and at the outlet side hemispherical.
  • Embodiments of the burner system comprise a secondary reaction chamber fitted over the outlet end of a first reaction chamber.
  • the secondary reaction chamber is supplied with at least two preheated and compressed fluid compounds through inlets and friction channels.
  • the first reaction chamber and the secondary reaction chamber are connected together such that the compounds that enter the secondary reaction chamber are ignited by the wave fronts of the hot gases that were formed in a first reaction inside the first reaction chamber and then explode or detonate.
  • At least the part of the external wall of the system that is over the reaction chambers and outlet channels is adapted as a heat exchanger that is surrounded by a medium to be heated by the energy of the pulsing pressure waves created by the explosions or detonations that take place inside the reaction chamber. This energy is transferred on impact of the waves with the internal walls of the reaction chamber through the heat exchanger to the medium.
  • the burner systems of the invention can be adapted to function as a linear engine by fitting a partially cone shaped expansion chamber at the outlet end of the last reaction chamber.
  • the expansion chamber is provided with inlets adapted to feed a fluid through channels into it and the system adapted such that the energy of explosions or detonations that take place in the reaction chamber or reaction chambers is used to heat the walls of the evaporation chamber thereby to rapidly evaporate the fluid.
  • the invention is a heat exchanger comprising walls that define at least the reaction chambers of at least one burner system according to the first aspect of the invention.
  • the invention is a method of increasing the efficiency of a heat exchanger comprising walls defining a reaction chamber for a combustion reaction.
  • the method comprises the steps of initiating and maintaining controlled continuous pulsing explosions or detonations of at least two pressurized fluid compounds at very high temperatures.
  • the explosions or detonations are maintained by use of infrared radiation.
  • the frequency of the explosions or detonations is controlled by adjusting the pressure of the fluid compounds.
  • a build-up of continuous repeating pulses of the compounds under pressure in the reaction chamber is allowed by adapting the pressure of the compounds and the internal cross-sectional area and the surface characteristics of the inner surface of a channel through which the compounds enter the reaction chamber to allow fast, free forward flow under pressure of the compounds through the channel into the reaction chamber and to create high gas friction for the much faster wave front of an explosion or detonation that takes place in the reaction chamber to prevent the wave front from passing through the channel.
  • This causes continuous repeating interruption of the flow of the compressed compounds forward into the reaction chamber, which sufficiently blocks the channel against the wave front of the explosion or detonation thus allowing continuous repeating pulsing explosions or detonations to take place in the reaction chamber.
  • the reaction chamber is a component of a burner system according to the first aspect of the invention.
  • the reaction chamber is a component of a burner system according to the first aspect of the invention including a secondary reaction chamber.
  • Fig. 1 schematically shows a basic embodiment of a prior art reaction chamber designed to carry out the method of the invention
  • Fig. 2 schematically shows a basic embodiment of the reaction chamber of the invention
  • Fig. 3 schematically shows an embodiment similar to that shown in Fig. 2 comprising an additional chamber housing a sparkplug;
  • Fig. 4 schematically shows a an embodiment of a reaction chamber comprising a plurality of inlets, inlet chambers, and friction channels;
  • Fig. 5 schematically shows a similar embodiment to that shown in Fig. 4 demonstrating how the distance that a shock wave from a detonation or explosion can travel backwards through the friction channels is limited;
  • Fig. 6 symbolically shows the effect caused by the special shapes given to the ends of the reaction chamber
  • Fig. 7 schematically shows an embodiment of the reaction chamber in which the reaction chamber comprises several small outlet channels
  • Fig. 8 schematically is an end view of the reaction chamber that shows the outlet channels of the embodiment shown in Fig. 7;
  • Fig. 9 schematically shows an embodiment of the invention in which a reaction chamber is built into a heat exchanger
  • Fig. 10 schematically shows an embodiment of the invention comprising a first or primary reaction chamber which is followed by a secondary reaction chamber;
  • Fig. 11 and Fig. 12 schematically show an embodiment of the invention in which the embodiment shown in Fig. 10 is adapted to be used as an engine.
  • This invention deals with a method to burn, combust or otherwise react compounds in order to reach higher temperature of a reaction between two or more compounds, for example fuel and air.
  • the invention relates to a method of increasing the efficiency of heat-exchangers or systems that are connected to burners or other devices in order to heat water, steam, or other materials from the release of thermal energy.
  • This invention is for the improvement mainly of heat exchangers that are used for steam production but also other systems that use heat exchangers in connection with exothermic reactions to exchange heat energy from one medium into another.
  • the present invention provides a burner system that allows 'quasi continuous burning' of fluids at very high temperatures by using controlled continuous pulsing explosions or detonations instead of continuous flow and thus creating pulsing pressure waves that can be easily utilised for increasing heat exchanger efficiency.
  • the pulsation of combustion or incineration is not related to pulsed detonations or explosions. Natural pulsation of combustion or incineration is the result of the manner in which the flames propagate one molecule after the other or one gas batch after the other.
  • the burner system of the invention is also different from so-called pulse-detonation-engines in that the system of the invention does not comprise any moving parts and or valves.
  • Fig. 1 shows the basic embodiment for the burner system previously described in US 5,131,840 and US 6,555,727. A quarter of the burner has been cut away along the length to reveal the inner structure.
  • an inlet (1) for one of the compounds under pressure, for example a fuel gas.
  • inlet (2) for a second compound under pressure, for example air as an oxidizer.
  • Both compounds under pressure are introduced into separate inlet chambers (3) and (4)).
  • An injector needle (4') connected to the front of inlet chamber (4) leads the compound directly into channel (5') and insures that no mixing of the compounds takes place outside of the channel.
  • Fig. 2 shows the basic embodiment of the burner system of the invention.
  • friction channel (5) is longer and has a smaller diameter than channel (5')
  • reaction chamber (7) is now a closed structure that has been given a very specific shape.
  • reaction chamber (7) where it connects to friction-channel (5) the interior walls of the reaction chamber are intentionally given a conical inside shape and at the outlet side (11), where the reaction chamber (7) connects to the outlet channel (9), the inner surface of reaction chamber (7) is given a hemispherical shape.
  • the outlet channel (9) is a thin channel having a diameter similar to that of friction channel (5).
  • Fig. 3 shows a similar embodiment to that shown in Fig. 2. However it has an additional chamber (12) where a sparkplug (13) is mounted in order to ignite the compounds under pressure during the start-up period of the burner's operation.
  • the ignition chamber (12) is connected to the reaction chamber (7) by channels (14) and (15) so that compounds under pressure can also stream into chamber (12) and the ignited compounds back into reaction chamber (7).
  • This or an equivalent arrangement is necessary in all embodiments of the invention in order to initiate the operation of the burner; however it will not be shown in the other figures for clarity.
  • Fig. 4 shows an embodiment of a burner that has the basic features of that shown in Fig. 2. However, this embodiment of the burner has a plurality of inlets, inlet chambers, and friction channels. In Fig. 4 two of sets of inlets (1,2), inlet chambers (3,4), and friction channels are visible. All friction channels end in the same reaction chamber (7).
  • Fig. 5 shows a similar embodiment to that shown in Fig. 4. This figure shows how the angle between the axes of the inlet chambers (3,4) and friction channels (5) limits the distance that a shock wave from a detonation or explosion can travel backwards through the friction channels (5) to the relatively small region (18) in which the ends of the two friction channels overlap at the entrance to the single reaction chamber (7). The reason for this is that a shock-wave front can only travel straight. It cannot bend and cannot travel around any curves.
  • Fig. 6 symbolically shows the effect caused by the special shapes given to the ends of the reaction chamber.
  • the dark wavy arrows represent infrared radiation reflected from the interior walls of reaction chamber (7).
  • the conical surface causes a forward reflection of the radiation.
  • the cylindrical circumferential wall (20) of the reaction chamber reflects the heat as infrared radiation perpendicular to and in the direction of the longitudinal symmetry axis of the reaction chamber (7).
  • the heat is reflected by the hemispherical surface to a focal point inside reaction chamber (7) on its longitudinal axis.
  • the compounds under pressure stream through the friction channel (5) into the reaction chamber along this line of concentrated reflected infrared radiation until the focal point at the middle of the spherical shape of the outlet.
  • the compounds are ignited at the focus to start the next detonation or explosion.
  • Fig. 7 shows an embodiment of the burner system wherein the single outlet to reaction chamber and outlet channel (9) of the embodiment of Fig. 2 is replaced with several smaller outlets (22) that are each connected to a separate outlet channel (23);
  • Fig. 8 is an end view of the embodiment shown in Fig. 7 showing the ends of the several outlet channels (23);
  • Fig. 9 shows an embodiment of the invention, where the outside of the reaction chamber (7) (note that the reaction chamber in this figure is an embodiment that will be described with respect to Fig. 10) and the outlet channels are formed as a heat exchanger to heat, for example, water.
  • a thread light structure (24) allows the water, which would be contained in a casing that is hermetically sealed to the end (31) of the block of material (30) from which the burner assembly and heat exchanger are formed, to run into the gaps (25) between the "threads" enabling the water to come in contact with the outer walls of the reaction chamber (7) and outlet channels.
  • Fig. 9 makes it obvious how easy it is to incorporate the burner system of the invention into a heat exchanger in which the whole reaction area where the heat is generated is covered with a heat exchanger.
  • Figure 10 shows an embodiment of the invention with a secondary reaction chamber.
  • Inlets (1,2) feed friction channel 5 which leads into primary reaction chamber 7.
  • Reaction chamber 7 is designed as for the previously described embodiments and functions in the same way. Fitted over the outlet end of primary reaction chamber 7 is secondary reaction chamber 7', into which reactant compounds are fed through inlets ( ⁇ ,2') and friction channels (5') ⁇
  • Fig. 11 and Fig. 12 schematically show an embodiment of the invention in which the embodiment shown in Fig. 10 is adapted to be used as an engine.
  • An additional partially cone shaped chamber (28) is fitted over the outlet end of the secondary partial reaction chamber (7').
  • Inlets (30) are adapted to feed a fluid, for example water, through channels (31) into chamber (28).
  • Friction channel (5) is a hollow pipe or channel having a cross- section of any shape or geometry. Depending on the manufacturing method of the burner system, it can be formed as a round and straight tube or as a round and straight bore through a block of metal. In the friction channel (5), both compounds mix but don't react.
  • the speed with which the compounds pass through the friction channel (5) has to be high enough to prevent a possible premature reaction. Usually a flow-rate of more then 60 metres per second is easily sufficient because a flame front can travel no faster so that at no point could a flame front travel backwards through the friction channel (5).
  • the pressure of the compressed compounds, the geometry, and especially the cross-sectional area of the friction channel (5) and the characteristics of its inner surface have to be chosen in the right way to optimise these effects of fast free flow under pressure into the reaction chamber (7) without allowing flame fronts to be able to travel backwards by using the high gas friction of the much faster advancing wave-front to prevent compounds from passing backwards into the inlet chamber (3).
  • the reaction chamber (7) At the outlet side of the friction channel (5) is the reaction chamber (7) whose interior has a wider diameter and relatively shorter length than the friction channel.
  • the mixture In the reaction chamber (7), the mixture is ignited and reacts.
  • the ignition is initiated by means of infrared radiation.
  • a more complicated ignition system is used as described with reference.
  • the compounds are preheated and under pressure and accordingly react with each other so quickly that they explode or detonate in the reaction chamber with their speed of detonation depending on the pressure of the compounds in the reaction chamber (7). Starting from the centre point of the reaction the explosion - or detonation - wave spreads outwards.
  • the speed of the explosion - or - detonation front is much higher than that of the compounds flowing towards the reaction chamber and causes so much fluid friction that the explosion - or detonation - front cannot reach the other side of the friction channel (5) but is stopped on its way.
  • this effect can be increased. Due to its extremely high speed, the wave front of the explosion or detonation can only move straight. By moving extremely fast backwards from the reaction chamber (7) into the friction channel (5) the explosion or detonation wave interrupts the flow of the compressed compounds in the friction channel (5) that are advancing towards the reaction chamber (7).
  • the explosion or detonation also functions as a micro-heat-pump that concentrates energy at the wave front and increases the temperature there. This effect creates an artificially high difference of temperature between the circumferential walls (20) of the reaction chamber (7) and the surface of the wave front. Therefore, because of the temperature difference between the wave front and the wall (20), a large part of the heat energy is transferred very rapidly into the circumferential wall (20) of the reaction chamber (7).
  • a pump (or pulse) mechanism is created.
  • the compounds are continuously fed under pressure into the inlet chambers (3,4) before the friction channel (5).
  • the gas volume in the inlet chamber acts as a gas-spring and is constantly compressed by detonations and expanded by the following low pressure.
  • outlet channel (9) of the reaction chamber (7) At the side of the reaction chamber (7) that is opposite to the outlet of the friction channel (5), there is the outlet channel (9) of the reaction chamber (7).
  • the gases that had been created by the reaction inside the reaction chamber have this outlet channel (9) as their only exit to leave the reaction chamber (7).
  • the geometry of outlet channel (9) is basically designed similarly to the friction channel (5). It is long and narrow to create sufficient gas friction or drag in the outlet channel (9) to slow down the gases. In accordance with the same physical effects of gas friction, this design will also ensure that the high speed of the wave front of the explosion or detonation will create so much gas friction that the gases cannot flow through the outlet channel (9) during the explosion or detonation.
  • the shock wave When the shock wave travels into the friction channel (5), it has a very high speed due to the explosion or detonation.
  • the specific value of the speed depends on the pressure under which the compounds react and the material properties of the compounds, as well the precise geometry and size of the reaction chamber (7).
  • a speed of between 2,000 metres per second to 6,000 meters per second is possible and can be reached without difficulty.
  • the Shockwave front starts to move spherically in all directions also including into the friction channel (5). The time until the shock wave front is stopped is extremely short.
  • the friction channel (5) has, for example in order to make understanding easier, a length of 100 mm, the reaction chamber (7) a length of 30 mm, and the speed of the explosion is a relative low 1,900 metres per second, than it takes the wave front around 0.000,052,6 seconds to reach the stop-point inside the friction channel (5), where it has lost so much energy due to the built-up of gas friction that it cannot go further. Beside the drag or gas or fluid friction also the loss of energy due to heat-exchange with the walls of the friction channel (5) slows the wave front down significantly.
  • the wave front contains high density mass, high pressure, and high temperature.
  • the compressed compounds are again forced through the friction channel (5) and reach the reaction chamber (7).
  • the compounds are ignited each time at the same speed, i.e. after the incoming compounds reach the end of the reaction chamber. Because they are under pressure, their ignition temperature is higher than for the same compounds at lower pressure.
  • the compressed compounds have to be ignited when they reach about the middle of the reaction chamber (7), not at the entrance (6), where the friction channel opens into the reaction chamber, otherwise there would be only a small amount of mass of compounds that could react. Therefore, the timing of the ignition has to be precise.
  • reaction chamber (7) The beginning of reaction chamber (7) is at the end of the friction channel (5).
  • the friction channel (5) the compressed preheated compounds are flowing rapidly towards the reaction chamber (7).
  • the cross section of the reaction chamber (7) is larger than the cross section of the friction channel (5) and also than the cross section of the outlet (9).
  • the reaction chamber begins (6) At the inlet side (10) of the reaction chamber (7) where the friction channel (5) ends the reaction chamber begins (6) and the cross section has to change from a small diameter to a larger diameter. The enlargement of the diameter is best realised with a conical shape. After the first few reactions, the walls (20) of the reaction chamber (7) will become warm and then hot.
  • the conical shape of the entrance area (6) causes a forward reflection of infrared radiation away from the entrance of the reaction chamber (7) towards the middle or centre of the reaction chamber (7) depending on the angle of the conical sides relative to the axis. There the infrared radiation will naturally create an area of focused infrared radiation.
  • the physical laws of optics apply and the infrared waves behave exactly the same as visible light waves when they are reflected from shaped mirrors. What is different however and of great importance is that the infrared radiation continues for some time after the production of heat ceases. While the reflection of visible light from a mirror will stop nearly immediately (due to the time the light needs to travel it is not exactly at the same instant) when the light source for the reflection is switched off. The infrared radiation will continue to radiate even when the reaction is interrupted or ended.
  • the infrared radiation has to bridge a time gap of 0.001,692 seconds at a low speed and less than 0.000, 846 seconds with higher speed of the gases in the friction channel (5). That is less than one millisecond.
  • the reaction chamber (7) is connected to an outlet (9) channel that has a smaller cross-section area than the reaction chamber (7). Therefore, at the outlet end (11) of the reaction chamber (7) there is a decrease in the cross sectional area. If this decrease of cross sectional area at the outlet (9) were shaped in a hemispherical shape, it would create a focal point or area for the infrared radiation reflected off of it.
  • the reaction chamber (7) With first a conical inlet side (10) and a hemispherical outlet side (11), there is a longitudinal field of focused infrared radiation along the centre line of the reaction chamber (7) that ends in a focus point where the concentration of the reflected infrared radiation is highest.
  • the focal point is the ignition point. Because the ignition takes place in the centre of the reaction chamber (7) the reaction front moves evenly outwards and also the explosion or detonation wave has its starting or central point on the line of focused reflected infrared radiation.
  • the compressed compounds ignite and thus react at a chosen point within the reaction chamber (7).
  • the design with hemispherical outlet side (11) and conical inlet side (10) to reflect the infrared radiation inside the combustion chamber is just one possible realisation of the idea of using infrared reflection to ignite the explosion or detonation.
  • the precise timing of the ignition by infrared radiation can easily be adjusted by varying the speed of the compounds that are forced through the friction channel, the geometry of the friction channel (5) and its length.
  • a higher pressure of the compounds would lead to a higher flow rate in the friction channel (5) and also to a shorter reaction time inside the reaction chamber (7).
  • the exact frequency can be adjusted. It is also possible to shape the reaction chamber (7) in such a way that the focal point of the infrared radiation is at a point that allows higher filling volumes — for example with different angles of the conical shaped entrance and end (10).
  • the focused infrared radiation reflection cannot be used for the ignition, because the walls of the reaction chamber (7) are not yet sufficiently heated up to create enough infrared radiation for ignition that is radiated backwards into the reaction chamber (7).
  • An ordinary spark plug (13) that is mounted in the circumferential wall (20) of the reaction chamber (7) would be sufficient to ignite the preheated compressed compounds at the beginning, before the infrared radiation is able to reignite the pulsing mixture.
  • a spark plug (13) were situated in the circumferential wall (20) of the reaction chamber (7), this part of the surface could not be used for heat exchange and also cannot be used for the infrared radiation reflection.
  • the spark plug (13) or similar device located in the wall of the reaction chamber (7) could easily be damaged or destroyed. Therefore, a better design is to create a small ignition chamber (12) with one or more small channels (14,15) leading from chamber (12) into the reaction chamber (7). Thus, the ignition can be outside the reaction chamber (7) and all of the heat produced could be realised and used.
  • the burner system of the invention is used in connection with a heat exchanger then it is a great advantage to use one single piece of heat conducting material, for example metal, to create the inlet chambers (3,4), the friction channel (5), the reaction chamber (7), and the outlet channel (9) in the interior of the piece of material and to use the outside of this material as walls for the heat exchanger (24).
  • the reaction chamber (7) would then constitute the interior of the heat exchanger and the outer surfaces would be surrounded with the medium that is to be heated.
  • the friction channel (5) and the reaction chamber (7) are relatively small. To increase the capacity of the burner it is better to add more friction channels (17) and reaction chambers of the same size than to increase the the friction channel (5) the effects of the combination of flow-speed, pressure and gas-friction are changed, and the effects achieved in this invention could be lost. Also the ratio between surface area to content would shift and decrease exponentially with linear increase of the cross sectional areas of the friction channels or the reaction chamber.
  • FIG. 10 schematically illustrates such an embodiment.
  • Inlets (1,2) feed friction channel 5 which leads into primary reaction chamber 7.
  • Reaction chamber 7 is designed as for the previously described embodiments and functions in the same way.
  • Fitted over the outlet end of primary reaction chamber 7 is secondary reaction chamber 7', into which reactant compounds are fed through inlets ( ⁇ ,2') and friction channels (5').
  • the preheated and compressed compounds that enter secondary reaction chamber (7') are ignited by the wave fronts of the hot gases that were formed in the primary reaction inside the primary reaction chamber (7) and then explode or detonate after the primary explosion or detonation.
  • the secondary reaction chamber (7') is different in several ways from the primary reaction chamber (7).
  • the reaction in the primary reaction chamber (7) depends on the infrared radiation for ignition at the exact time and at an exact location. Therefore, the friction channel (5) for the primary reaction in the primary reaction chamber (7) has to be located and oriented such that the preheated compressed compounds flow through the reflected infrared radiation in order to ignite. Practically this is easiest to achieve with gas flow along the symmetry axis in the middle of the reaction chamber. Because the friction channel (5) is lined up with this axis in order to let the preheated compressed compounds into the field of reflected infrared radiation for ignition, the following explosion or detonation of the primary reaction is able to cause the wave front go backwards into the friction channel (5).
  • the secondary reaction in the secondary reaction chamber (7') is then ignited by the expanding wave front of the primary reaction that moves out of the primary reaction chamber (7) into the secondary reaction chamber (7').
  • the primary reaction chamber (7) has a diameter of 20 mm and a length of 30 mm
  • the wave front from the example discussed herein above with relative low speed of 1,900 meters per second would ignite and start the secondary reaction after 0.000,01 seconds or 0.01 milliseconds after the primary reaction.
  • the chosen speeds are very low. These speeds can easily be much higher. In such a case, the time difference between the primary and secondary reaction would be much shorter than 0.01 milliseconds.
  • the friction channels (5') leading to the secondary partial reaction chamber (7') step can be positioned away from the centre of the explosion or detonation of the secondary reaction. In this way, the preheated and compressed compounds for the secondary reaction would enter the secondary reaction chamber (7') at an angle to the point of their ignition. Thus, the wave front created by the secondary reaction cannot enter deeply into the friction channel (5') or channels. Therefore the friction channels (5') leading to the secondary reaction chamber (7') can be kept shorter and have larger diameters than the friction channel (5) leading to the primary reaction chamber (7). Therefore larger amounts of compounds can be brought through the friction channels (5') of the secondary reaction chamber (7') than through the central friction channel (5) of the primary reaction chamber (7).
  • the primary reaction which takes place using, for example, a well a defined and 'standard' fuel in the primary reaction burner (7) can be used as "pilot flame” to ignite a secondary reaction between compounds with varying properties or compositions in the secondary reaction chamber (7').
  • Other embodiments of the invention comprise more than two stages or combine several multi-stage reaction chambers in rows, circular, or other configurations. The choice of design of the burner device depends upon the application.
  • Fig. 11 and Fig. 12 schematically show an embodiment of the invention in which the embodiment shown in Fig. 10 is adapted to be used as a linear engine.
  • an additional partially cone shaped expansion chamber (28) is fitted over the outlet end of the secondary partial reaction chamber (7').
  • Inlets (30) are adapted to feed a fluid, for example water, through channels (29) into chamber (28).
  • Propulsion is the main purpose for this embodiment and not a stationary heat exchanger, as in previously described embodiments.
  • the energy of primary and secondary reactions that take place in reaction chamber (7) and reaction chamber (7') is used to heat the walls of chamber (28) and thereby to rapidly evaporate water or similar compounds or mixtures of fluid that enter chamber (28).
  • the volume of the outlet stream is increased— in the case of the example of water by a factor of over 1,600.
  • the outlet channel (or outlet channels) has to be sufficiently large to allow the combined volumes of the reaction products from the primary and secondary reaction chambers and the gas or vapour produced in the expansion chamber (28) to escape.
  • more than two inlets (1,2) and inlet chambers (3,4) can be provided to allow three or more compounds to be introduced into the reaction chambers (7,7') and more than one type of compound can be introduced into expansion chamber 28 through inlets (31).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Physical Or Chemical Processes And Apparatus (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Gas Burners (AREA)

Abstract

La présente invention concerne un système de brûleur qui permet de brûler de manière quasiment continue des fluides à des températures très élevées en utilisant des explosions ou des détonations d'impulsion continue contrôlée au lieu d'un écoulement continu, créant ainsi des ondes de pression d'impulsion qui peuvent être utilisées facilement pour augmenter l'efficacité de l'échangeur de chaleur. Après l'amorçage, les explosions ou détonations sont maintenues par l'utilisation de rayonnement infrarouge. Les explosions ou détonations impulsées transmettent leurs ondes de choc directement aux parois de l'échangeur de chaleur, l'introduction d'une part d'énergie supérieure dans l'échangeur de chaleur serait alors possible avec tout autre procédé d'échange de chaleur. De plus, l'énergie cinétique de l'accélération négative de la masse dans l'onde de l'explosion ou de détonation est ajoutée en tant que chaleur supplémentaire introduite dans les parois de l'échangeur de chaleur.
PCT/IL2010/001043 2009-12-10 2010-12-09 Système de brûleur et procédé permettant d'augmenter l'efficacité d'un échangeur de chaleur Ceased WO2011070580A1 (fr)

Priority Applications (9)

Application Number Priority Date Filing Date Title
CA2783769A CA2783769C (fr) 2009-12-10 2010-12-09 Systeme de bruleur et procede permettant d'augmenter l'efficacite d'un echangeur de chaleur
JP2012542687A JP5633909B2 (ja) 2009-12-10 2010-12-09 バーナシステム、および熱交換器の効率を高めるための方法
BR112012014005A BR112012014005A2 (pt) 2009-12-10 2010-12-09 sistemas de queimador e um método para aumentar a eficiência de um trocador de calor
AU2010329441A AU2010329441B2 (en) 2009-12-10 2010-12-09 A burner system and a method for increasing the efficiency of a heat exchanger
KR1020127017908A KR101490784B1 (ko) 2009-12-10 2010-12-09 열교환기의 효율을 증가시키기 위한 버너 시스템 및 열교환기의 효율을 증가시키는 방법
EP10835611.4A EP2510282B1 (fr) 2009-12-10 2010-12-09 Système de brûleur et procédé permettant d'augmenter l'efficacité d'un échangeur de chaleur
CN201080063653.4A CN102918325B (zh) 2009-12-10 2010-12-09 燃烧器系统和用于提高热交换器效率的方法
US13/514,144 US9512997B2 (en) 2009-12-10 2010-12-09 Burner system and a method for increasing the efficiency of a heat exchanger
IL220266A IL220266A (en) 2009-12-10 2012-06-07 Burner and method for increasing the efficiency of a heat converter

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB0921660.7A GB0921660D0 (en) 2009-12-10 2009-12-10 Method for increasing the efficiency of a heat exchanger
GB0921660.7 2009-12-10

Publications (2)

Publication Number Publication Date
WO2011070580A1 true WO2011070580A1 (fr) 2011-06-16
WO2011070580A8 WO2011070580A8 (fr) 2011-08-25

Family

ID=41666918

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IL2010/001043 Ceased WO2011070580A1 (fr) 2009-12-10 2010-12-09 Système de brûleur et procédé permettant d'augmenter l'efficacité d'un échangeur de chaleur

Country Status (11)

Country Link
US (1) US9512997B2 (fr)
EP (1) EP2510282B1 (fr)
JP (1) JP5633909B2 (fr)
KR (1) KR101490784B1 (fr)
CN (1) CN102918325B (fr)
AU (1) AU2010329441B2 (fr)
BR (1) BR112012014005A2 (fr)
CA (1) CA2783769C (fr)
GB (1) GB0921660D0 (fr)
IL (1) IL220266A (fr)
WO (1) WO2011070580A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2558509C1 (ru) * 2014-02-18 2015-08-10 Объединенный Институт Ядерных Исследований Способ ускорения тела
US9206775B2 (en) 2012-02-01 2015-12-08 United Technologies Corporation Fuel preheating using electric pump
US9316157B2 (en) 2012-02-01 2016-04-19 Hamilton Sundstrand Corporation Fuel system for starting an APU using a hybrid pump arrangement
RU2686138C1 (ru) * 2018-02-26 2019-04-24 Общество с ограниченной ответственностью "Новые физические принципы" Способ получения сильно перегретого пара и устройство детонационного парогенератора (варианты)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU2011323198B2 (en) 2010-11-05 2015-06-18 Thermochem Recovery International, Inc. Solids circulation system and method for capture and conversion of reactive solids
AU2012315914B2 (en) 2011-09-27 2015-07-09 Thermochem Recovery International, Inc. System and method for syngas clean-up
GB2516267B (en) * 2013-07-17 2016-08-17 Edwards Ltd Head assembly
CN105940265A (zh) * 2013-12-04 2016-09-14 阿卜杜拉国王科技大学 用于燃烧和材料合成的设备和方法
JP6542223B2 (ja) * 2013-12-04 2019-07-10 キング アブドゥーラ ユニバーシティ オブ サイエンス アンド テクノロジー 燃焼のための装置および方法
CA3014874C (fr) 2016-02-16 2019-03-19 Thermochem Recovery International, Inc. Systeme et procede de generation de produit gazeux integre en energie a deux etages
MX2018011589A (es) 2016-03-25 2019-09-18 Thermochem Recovery Int Inc Sistema y metodo de generacion de gas producto de energia ntegrada de tres etapas.
US10364398B2 (en) 2016-08-30 2019-07-30 Thermochem Recovery International, Inc. Method of producing product gas from multiple carbonaceous feedstock streams mixed with a reduced-pressure mixing gas
US9920926B1 (en) 2017-07-10 2018-03-20 Thermochem Recovery International, Inc. Pulse combustion heat exchanger system and method
US10099200B1 (en) 2017-10-24 2018-10-16 Thermochem Recovery International, Inc. Liquid fuel production system having parallel product gas generation
WO2019185736A1 (fr) * 2018-03-29 2019-10-03 Explo Engineering Ag Dispositif et procédé pour la génération d'ondes de pression de haute amplitude
US11555157B2 (en) 2020-03-10 2023-01-17 Thermochem Recovery International, Inc. System and method for liquid fuel production from carbonaceous materials using recycled conditioned syngas
US11466223B2 (en) 2020-09-04 2022-10-11 Thermochem Recovery International, Inc. Two-stage syngas production with separate char and product gas inputs into the second stage
EP4650664A1 (fr) * 2024-05-14 2025-11-19 Technische Universität Berlin Système de chauffage pour produire et appliquer de la chaleur et procédé de production et d'application de chaleur dans un système de chauffage

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4473348A (en) * 1980-08-18 1984-09-25 Nauchno-Proizvodstvennoe Obiedinenie Po Tekhnologii Mashinostroenia "Tsniitmash" Method for pulse-burning fuel gases in industrial furnaces
US5090891A (en) * 1989-06-26 1992-02-25 Indugas, Inc. Hybrid combustion device and system therefor
US5845480A (en) * 1996-03-13 1998-12-08 Unison Industries Limited Partnership Ignition methods and apparatus using microwave and laser energy
US20020185097A1 (en) * 2001-05-24 2002-12-12 Ryan Thomas W. Methods and apparatuses for laser ignited engines
US6555727B2 (en) * 1995-03-20 2003-04-29 Michael L. Zettner Fluid compound thermochemical conversion process and converter
US20070015099A1 (en) * 2005-06-30 2007-01-18 General Electric Company Naturally aspirated fluidic control for diverting strong pressure waves
US20080209884A1 (en) * 2004-04-30 2008-09-04 William Anthony Denne Pulse Jet Engines
US20090136798A1 (en) * 2005-06-10 2009-05-28 Forschungszentrum Juelich Gmbh Autothermic Reformer

Family Cites Families (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2644512A (en) * 1949-06-13 1953-07-07 Heizmotoren Ges Uberlingen Am Burner device having heat exchange and gas flow control means for maintaining pyrophoric ignition therein
US2695053A (en) * 1949-06-13 1954-11-23 Swingfire Bahamas Ltd Intermittent combustion device provided with means for controlling the combustion gas flow therein
US2950592A (en) * 1954-01-06 1960-08-30 Curtis Automotive Devices Inc Resonant pulse jet engine having an engine valve antechamber
US2796734A (en) * 1955-11-14 1957-06-25 Jr Albert G Bodine Sonic burner heat engine with acoustic reflector for augmentation of the second harmonic
US3151454A (en) * 1961-04-24 1964-10-06 Curtis Dyna Prod Corp Starting and fuel system for pulse jet devices
GB1275461A (en) * 1969-02-17 1972-05-24 Shell Int Research Pulsating combustion system
CH569940A5 (en) * 1973-07-16 1975-11-28 Battelle Memorial Institute Sound absorber for pulsatory gas burner - has branch Helmholtz resonator, annular multi-chamber resonator and absorbent jacket each end
US4382771A (en) * 1980-05-12 1983-05-10 Lola Mae Carr Gas and steam generator
JPS59231309A (ja) * 1983-06-11 1984-12-26 Matsushita Electric Ind Co Ltd パルス燃焼装置
JPS60232404A (ja) * 1984-05-02 1985-11-19 Toshiba Corp パルス燃焼装置
US4574745A (en) * 1984-07-23 1986-03-11 American Gas Association Compact pulse combustion burner with enhanced heat transfer
JPH0663650B2 (ja) * 1986-01-10 1994-08-22 株式会社東芝 パルス燃焼装置
DE3737247C1 (de) 1987-11-03 1989-03-02 Zettner Michael L Brenneinrichtung
US4856981A (en) * 1988-05-24 1989-08-15 Gas Research Institute Mixing rate controlled pulse combustion burner
DE3916556A1 (de) * 1989-05-20 1990-11-22 Kornaker Walter Vorrichtung zum reinigen der abgase von verbrennungskraftmaschinen
GB9013154D0 (en) * 1990-06-13 1990-08-01 Chato John D Improvements in pulsating combustors
US5249952A (en) * 1992-04-24 1993-10-05 Cosmos Ventures, Inc. Exhaust fume energy source and waste combustion apparatus
US5285769A (en) * 1992-10-13 1994-02-15 Washington State University Research Foundation Aerosol generating rotary pulse-jet orchard heater
JP3200779B2 (ja) * 1992-11-10 2001-08-20 誠 西村 金属のろう付用パルスバーナー
US5456594A (en) * 1994-03-14 1995-10-10 The Boc Group, Inc. Pulsating combustion method and apparatus
CN1143729C (zh) * 1995-03-20 2004-03-31 迈克尔·L·策特纳 可流动化合物实现热化学转化的方法和实现这种方法的转化器
JP3670020B2 (ja) * 1995-11-29 2005-07-13 パワーテック・インダストリーズ・インコーポレイテッド パルス燃焼器
EP0889756B1 (fr) * 1996-12-28 2002-09-04 Aerostar Coatings, S.L. Appareil de detonation autonome
JPH10288310A (ja) * 1997-04-11 1998-10-27 Aichi Mach Ind Co Ltd パルス燃焼装置
USH1931H1 (en) * 1997-12-01 2001-01-02 The United States Of America As Represented By The Department Of The Navy Apparatus for activity controlled waste incinerator afterburner
US6210149B1 (en) * 1998-05-26 2001-04-03 Zinovy Z. Plavnik Pulse combustion system and method
AU5403599A (en) * 1998-08-31 2000-03-21 Clean Energy Combustion Systems Inc. Circular pulsating combustors
US6016669A (en) * 1998-11-30 2000-01-25 General Electric Company Pulsed fuel-oxygen burner and method for rotatable workpieces
US6312250B1 (en) * 1999-04-19 2001-11-06 North American Manufacturing Company Premix burner with firing rate control
DE19942387A1 (de) * 1999-07-14 2001-01-18 Abb Alstom Power Ch Ag Verfahren zum Verbrennen eines flüssigen Brennstoffes in einem Verbrennungssystem sowie Verbrennungssystem zur Durchführung des Verfahrens
DE19934612A1 (de) * 1999-07-23 2001-01-25 Abb Alstom Power Ch Ag Verfahren zur aktiven Unterdrückung von strömungsmechanischen Instabilitäten in einem Verbrennungssystem sowie Verbrennungssystem zur Durchführung des Verfahrens
US6584774B1 (en) * 2001-10-05 2003-07-01 The United States Of America As Represented By The Secretary Of The Air Force High frequency pulsed fuel injector
US6584765B1 (en) * 2001-12-21 2003-07-01 United Technologies Corporation Pulse detonation engine having an aerodynamic valve
ITTO20020850A1 (it) * 2002-10-01 2004-04-02 Powertech Ind Inc Camera di combustione a impulsi dotata di piastre multiple utilizzabile come caldaia per acqua calda
US7200538B2 (en) * 2003-01-15 2007-04-03 General Electric Company Methods and apparatus for modeling gas turbine engines
US6964171B2 (en) * 2003-09-11 2005-11-15 The United States Of America As Represented By The Secretary Of The Navy Method and apparatus using jets to initiate detonations
EP1735371B1 (fr) * 2004-04-12 2010-07-07 The Yokohama Rubber Co., Ltd. Procede destine a produire une composition contenant un polymere a partir d'un liquide contenant un constituant polymere et appareil de sechage associe
US7637096B2 (en) * 2004-11-25 2009-12-29 Rolls-Royce Plc Pulse jet engine having pressure sensor means for controlling fuel delivery into a combustion chamber
DE102006017355A1 (de) * 2006-04-11 2007-10-18 Spot Spirit Of Technology Ag Verfahren und Vorrichtung zum Erreichen von besseren Wärmeübergängen bei der Verwendung von Impulsbrennern
US20080299504A1 (en) * 2007-06-01 2008-12-04 Mark David Horn Resonance driven glow plug torch igniter and ignition method
US20090165438A1 (en) * 2007-12-26 2009-07-02 Occhipinti Anthony C Pulse detonation engine
US7628606B1 (en) * 2008-05-19 2009-12-08 Browning James A Method and apparatus for combusting fuel employing vortex stabilization
JP4911648B2 (ja) * 2009-02-13 2012-04-04 タマティーエルオー株式会社 爆発溶射装置

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4473348A (en) * 1980-08-18 1984-09-25 Nauchno-Proizvodstvennoe Obiedinenie Po Tekhnologii Mashinostroenia "Tsniitmash" Method for pulse-burning fuel gases in industrial furnaces
US5090891A (en) * 1989-06-26 1992-02-25 Indugas, Inc. Hybrid combustion device and system therefor
US6555727B2 (en) * 1995-03-20 2003-04-29 Michael L. Zettner Fluid compound thermochemical conversion process and converter
US5845480A (en) * 1996-03-13 1998-12-08 Unison Industries Limited Partnership Ignition methods and apparatus using microwave and laser energy
US20020185097A1 (en) * 2001-05-24 2002-12-12 Ryan Thomas W. Methods and apparatuses for laser ignited engines
US20080209884A1 (en) * 2004-04-30 2008-09-04 William Anthony Denne Pulse Jet Engines
US20090136798A1 (en) * 2005-06-10 2009-05-28 Forschungszentrum Juelich Gmbh Autothermic Reformer
US20070015099A1 (en) * 2005-06-30 2007-01-18 General Electric Company Naturally aspirated fluidic control for diverting strong pressure waves

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP2510282A4 *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9206775B2 (en) 2012-02-01 2015-12-08 United Technologies Corporation Fuel preheating using electric pump
US9316157B2 (en) 2012-02-01 2016-04-19 Hamilton Sundstrand Corporation Fuel system for starting an APU using a hybrid pump arrangement
RU2558509C1 (ru) * 2014-02-18 2015-08-10 Объединенный Институт Ядерных Исследований Способ ускорения тела
RU2686138C1 (ru) * 2018-02-26 2019-04-24 Общество с ограниченной ответственностью "Новые физические принципы" Способ получения сильно перегретого пара и устройство детонационного парогенератора (варианты)

Also Published As

Publication number Publication date
JP2013513778A (ja) 2013-04-22
AU2010329441B2 (en) 2016-05-12
US9512997B2 (en) 2016-12-06
EP2510282A4 (fr) 2017-12-20
WO2011070580A8 (fr) 2011-08-25
JP5633909B2 (ja) 2014-12-03
CN102918325A (zh) 2013-02-06
GB0921660D0 (en) 2010-01-27
EP2510282B1 (fr) 2019-05-08
US20120264070A1 (en) 2012-10-18
AU2010329441A1 (en) 2012-07-26
CN102918325B (zh) 2015-09-30
BR112012014005A2 (pt) 2018-06-05
IL220266A (en) 2015-10-29
CA2783769C (fr) 2017-11-07
CA2783769A1 (fr) 2011-06-16
IL220266A0 (en) 2012-07-31
KR101490784B1 (ko) 2015-02-09
KR20130004248A (ko) 2013-01-09
EP2510282A1 (fr) 2012-10-17

Similar Documents

Publication Publication Date Title
CA2783769C (fr) Systeme de bruleur et procede permettant d'augmenter l'efficacite d'un echangeur de chaleur
CN104919249B (zh) 增压燃烧装置及方法
CN104154567B (zh) 一种旋转爆震燃烧室
US5168123A (en) Chemical initiation of detonation in fuel-air explosive clouds
RU2435060C2 (ru) Двигатель с импульсной детонацией, работающий на воздушно-топливной смеси
CN110131071B (zh) 一种脉冲爆震发动机燃烧室及其起爆方法
CN101881238A (zh) 一种吸气式脉冲爆震发动机及其起爆方法
JP3692127B2 (ja) 爆轟波発生装置
US20050279083A1 (en) Folded detonation initiator for constant volume combustion device
RU2333423C2 (ru) Способ инициирования детонации в горючих смесях и устройство для его осуществления
RU2378525C1 (ru) Ракетный двигатель твердого топлива
RU2429409C1 (ru) Способ инициирования детонации в трубе с горючей смесью и устройство для его осуществления
Ciccarelli et al. Flame acceleration enhancement by distributed ignition points
KR101362671B1 (ko) 연소부피를 줄이는 매트릭스수단을 갖춘 증기발생 보일러
RU2487256C2 (ru) Способ детонационного сжигания водорода в стационарном сверхзвуковом потоке
RU192351U1 (ru) Горелка
Ciccarelli et al. Investigation of flame acceleration enhancement for a pulse detonation engine initiation system
NO177162B (no) Fremgangsmåte og apparat til tenning av gasser i flammetårn
RU2613351C1 (ru) Ракетный двигатель твёрдого топлива управляемого снаряда
CN115219214A (zh) 一种气液两相激波聚焦起爆实验装置
WO2015016733A1 (fr) Moteur à détonation par impulsion et à réaction (variantes)

Legal Events

Date Code Title Description
WWE Wipo information: entry into national phase

Ref document number: 201080063653.4

Country of ref document: CN

121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 10835611

Country of ref document: EP

Kind code of ref document: A1

WWE Wipo information: entry into national phase

Ref document number: 220266

Country of ref document: IL

ENP Entry into the national phase

Ref document number: 2783769

Country of ref document: CA

WWE Wipo information: entry into national phase

Ref document number: 2012542687

Country of ref document: JP

NENP Non-entry into the national phase

Ref country code: DE

WWE Wipo information: entry into national phase

Ref document number: 13514144

Country of ref document: US

WWE Wipo information: entry into national phase

Ref document number: 2010329441

Country of ref document: AU

ENP Entry into the national phase

Ref document number: 20127017908

Country of ref document: KR

Kind code of ref document: A

WWE Wipo information: entry into national phase

Ref document number: 6108/DELNP/2012

Country of ref document: IN

Ref document number: 2010835611

Country of ref document: EP

ENP Entry into the national phase

Ref document number: 2010329441

Country of ref document: AU

Date of ref document: 20101209

Kind code of ref document: A

DPE1 Request for preliminary examination filed after expiration of 19th month from priority date (pct application filed from 20040101)
REG Reference to national code

Ref country code: BR

Ref legal event code: B01A

Ref document number: 112012014005

Country of ref document: BR

ENP Entry into the national phase

Ref document number: 112012014005

Country of ref document: BR

Kind code of ref document: A2

Effective date: 20120611