EP0478305A2 - Chambre de combustion et appareil à combustion - Google Patents

Chambre de combustion et appareil à combustion Download PDF

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Publication number
EP0478305A2
EP0478305A2 EP91308745A EP91308745A EP0478305A2 EP 0478305 A2 EP0478305 A2 EP 0478305A2 EP 91308745 A EP91308745 A EP 91308745A EP 91308745 A EP91308745 A EP 91308745A EP 0478305 A2 EP0478305 A2 EP 0478305A2
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EP
European Patent Office
Prior art keywords
combustion
liquid fuel
combustor
air
burner
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.)
Granted
Application number
EP91308745A
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German (de)
English (en)
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EP0478305B1 (fr
EP0478305A3 (en
Inventor
Hironobu Kobayashi
Shigeru Azuhata
Masayuki Taniguchi
Tadayoshi Murakami
Kiyoshi Narato
Michio Kuroda
Satoshi Tsukahara
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Hitachi Ltd
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Hitachi Ltd
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Publication of EP0478305A3 publication Critical patent/EP0478305A3/en
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Classifications

    • 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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/005—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space with combinations of different spraying or vaporising means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23J—REMOVAL OR TREATMENT OF COMBUSTION PRODUCTS OR COMBUSTION RESIDUES; FLUES 
    • F23J15/00—Arrangements of devices for treating smoke or fumes
    • F23J15/02—Arrangements of devices for treating smoke or fumes of purifiers, e.g. for removing noxious material
    • F23J15/04—Arrangements of devices for treating smoke or fumes of purifiers, e.g. for removing noxious material using washing fluids
    • 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
    • F23K5/02—Liquid fuel
    • F23K5/14—Details thereof
    • F23K5/20—Preheating devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • the present invention relates to a combustor in which a liquid fuel is preevaporated, premixed with a combustion air and burned, and to a combustion apparatus comprising the combustor and a combusting process.
  • preevaporated/premixed type combustion wherein a liquid fuel is vaporized (preevaporated) and premixed with air, and the resulting premixture (premixed gas) is ejected from the same nozzle.
  • the use of such preevaporated/premixed combustion is advantageous in the following two respects.
  • One is that the use of the pre-evaporating and pre-mixing type combustion enables the reaction region for combustion to be reduced in size. In other words, the flame can be shortened to enable a high load combustion.
  • the other advantage is that the amount of NOx discharged can be reduced by employing a dilute fuel mixture in the combustion process.
  • a combustion different from the premixing type combustion includes a diffusion combustion wherein air and a fuel are ejected from different nozzles.
  • a region in which the ratio of a theoretical air amount to an actual air amount in a fuel-air mixture (which will be referred to as an air ratio) is of about 1 : 1 is always present in the course of the premixing of a fuel with air in a combustion chamber, even if combustion is conducted under a dilutefuel condition.
  • the temperature of a flame is higher in the vicinity of the region of an air ratio of about 1 : 1 and for this reason, a reduction in the amount of NOx is generally difficult.
  • a premixing type combustion burner which includes an atomizer for atomizing the liquid fuel, and an evaporation chamber in which the atomized liquid fuel is evaporated (see Gas Turbine Academic Society Journal, Vol 16, No.64, PP 47 to 55).
  • a premixing type burner which is at least capable of the formation of finely-divided atomized particles among the requirements included for a premixing type burner, is shown in Fig.10 (see Prog. Energy Combust. Sci., No.6, pp 233 to 261).
  • This premixing type burner comprises an inner cylinder 2 to an inner peripheral surface to which a liquid fuel is supplied, and a pintle 5 mounted within the inner cylinder 2 and increased in diameter in a downstream direction.
  • a prefilming surface 3 is formed around an inner periphery of the inner cylinder at its downstream side and gradually increased in diameter in the downstream direction.
  • Air running straightly through the inner cylinder 2 serves to form the liquid fuel into a film-like configuration to guide it to an atomizing lip 4.
  • the film-like liquid fuel which has reached the atomizing lip 4 is ejected from the atomizing lip 4 toward an outer periphery by the air passed through the inner cylinder 2, and is sheared and finely divided by the air running straightly along the outside of the inner cylinder 2.
  • the finely dividing capability and the spray dispersing property are dependent upon the shape of the pintle 5. This is because the angle of ejection of the liquid fuel with respect to the air running straightly along the outside of the inner cylinder 2 is determined by the shape of the pintle 5.
  • the air is adiabatically compressed by a compressor and heated to a temperature of about 270 to 350°C.
  • the finely divided atomized particles are heated by a combustion air and evaporated.
  • the residence time for the atomized particles in the evaporation chamber is equal to or less than the self-ignition time, and generally, it is preferably that the residence time in the evaporation chamber under a practical condition is equal to or less than about 4 m sec.
  • the residence time for the atomized particles is merely within the self-ignition time, the atomized particles are supplied without being evaporated, resulting in a failure to provide a reduction in the amount of NOx.
  • the preheating of the liquid fuel is commonly used in a heavy oil-fired boiler. In this boiler, however, a lower grade heavy oil solidified at ambient temperature is heated to about 80°C for fluidification, thereby enabling transportation by piping. Consequently, the preheating of the liquid fuel in the heavy oil fired boiler would not promote the evaporation of the atomized particles.
  • the preheating for promoting the evaporation of the atomized particles is described, for example, in Japanese Patent Publication No.14325/80.
  • This method is to preheat the liquid fuel to a temperature equal to or more than the boiling point in an ejection atmosphere and then eject the preheated liquid fuel from a small hole into the evaporation chamber.
  • the fuel ejected from the small hole produces a so-called vacuum boiling phenomenon in the ejection atmosphere, and is finely divided and evaporated due to a volume expansion at this time.
  • NOx and CO are subjects of control as enviromental pollution materials, and a combustor and a denitration device suitable for satisfying the emission standards for NOx and CO should be provided.
  • a combustion intermediate product such as aldehyde is not subject to control, and the present situation is that the aldehyde is scarcely treated.
  • An atomizer as described above is utilized for a combustor for a gas turbine in which combustion is conducted using a large amount of air, because the atomizer finely divides liquid fuel with a small loss in pressure.
  • the evaporation of the liquid fuel requires an increased time, because the evaporation time for the atomized particles in the evaporation chamber is proportional to the square of the particle size of the atomized particles, so that the liquid fuel is supplied to the combustion space without reaching a preevaporated and premixed state. Unless a preevapoared and premixed combustion can be achieved, a low NOx combustion cannot be necessarily achieved.
  • the atomized particles may be adhered to an inner wall of the evaporation chamber.
  • the particles adhered to the inner wall of the evaporation chamber are difficult to vaporize and hence, the evaporation of the liquid fuel may be impeded. For this reason, it is impossible to achieve a preevaporated and premixed combustion suitable for a low NOx combustion process.
  • the prior art is accompanied by a problem that it is difficult to finely divide the liquid fuel and further to uniformly diffuse the finely-divided liquid fuel in the evaporation chamber, and it is impossible to provide a sufficient reduction in the amount of NOx.
  • the prior art fuel preheating method suffers from a problem that the liquid fuel is preheated to a temperature equal to or more than the boiling point in an ejection atmosphere and therefore, the liquid fuel may be boiled in the pipeline for the liquid fuel, resulting in a failure to realize a stable premixed combustion.
  • the pressure in the pipeline for the liquid fuel may be varied whenever the amount of fuel supplied is changed, resulting in a high possibility of the fuel boiling in the pipeline.
  • the boiling point of a liquid fuel comprising a single component can be distinctly defined, but the boiling point of a liquid fuel commonly used cannot be distinctly defined, because it is a mixture of components. For example, if the average value of boiling points of the components is defined as the boiling point of the liquid fuel, then there is a high possibility that the component having a lower boiling point than the average value may be boiled in the pipeline.
  • the atomized particles have increased particle sizes, and there is a large difference between the temperature of the liquid fuel and the boiling point, so that the fuel may be supplied in its unevaporated state to the combustion chamber.
  • the fuel supplied to the combustor may often be varied in type.
  • the fuel is supplied from a tank. If a different type of fuel is added to the tank, the fuel is replaced by the new fuel only after several hours or several days. During this time, the properties of the fuel and particularly the boiling point may be varied, which is accompanied by a danger that the fuel may be boiled in the pipeline, when the combustor is operated at a given temperature.
  • the combustor is capable of burning a variety of types of fuel for reasons of cost and practicality.
  • the prior art combustion apparatus suffers from a problem that a variety of types of fuel cannot be burned, because the fuel can be heated only to a signal predetermined temperature.
  • NOx and CO are subject to control as being enviromental pollution materials, and various provisions therefor have been made.
  • unreacted intermediate materials other than NOx and CO are produced in the course of oxidation of the fuel which are not subject to control because there are only trace products and hence, the present situation is that any provisions therefor have not been made hithereto.
  • the combustion intermediate products become a problem in the combustion of an alcohol based fuel such as a methanol.
  • the fuel is converted via intermediate products into carbon oxides and water.
  • the intermediate product such as aldehyde may be discharged outside the combustor, conjointly with the fact that such an intermediate product itself can be stably present.
  • Another problem is that such an intermediate product cannot be treated satisfactorily in an existing device such as a denitration device which is placed rearwardly of the combustor.
  • a combustor including a premixing type combustion burner which has an atomizer for ejecting a liquid fuel together with a combustion air to atomize the liquid fuel, wherein the atomizer is comprised of an inner shell to an inner peripheral surface of which the liquid fuel is supplied, an outer shell defining a passage for the combustion air running substantially straightly between the outer shell itself and an outer peripheral surface of the inner shell, and a swirling-flow guide plate for swirling the combustion air passed into the inner shell, while directing it in a downstream direction, and the combustor further includes a resistor abruptly decreased in sectional area downstream and provided substantially downstream of the center of the swirling flow and in the vicinity of an outlet of the premixing type combustion burner for providing a resistance to a premixture ejected from the premixing type combustion burner.
  • the inner periphery of the inner shell of the atomizer is increased in diameter toward its downstream side. Further, in the combustor, it is preferred that the inner and outer peripheral surfaces of the inner shell of the atomizer are connected at an acute angle at a downstream end of the inner shell, and the area of an opening in the inner shell is equal to the area of an opening between the inner and outer shells, and that the downstream end of the outer shell is located further downstream than the downstream end of the inner shell.
  • a combustor including a premixing type combustion burner having a space in which a liquid fuel is mixed with combustion air, the combustor comprising a means for forming a swirling flow of the combustion air in the space, a means for forming a straightly running flow of the combustion air, flowing in a downstream direction, around the swirling flow, a means for supplying the liquid fuel to a boundary between the swirling flow and the straightly running flow, and a means provided substantially downstream of the center of the swirling flow and in the vicinity of an outlet of the premixing type combustion burner for forming a circulating flow of a combustion gas produced from the combustion of a premixture ejected from the premixing type combustion burner.
  • the swirling-flow forming means may be comprised of an impeller or a nozzle disposed for swirling the combustion air.
  • the circulating-flow forming means may be comprised of a resistor which is abruptly reduced in sectional area downstream.
  • a combustion apparatus including a combustor designed so that combustion air and an atomized liquid fuel are premixed with each other in a premixing type combustion burner and the resulting mixture is burned in a combustion chamber, the apparatus comprising a means for heating the liquid fuel to a range of temperatures not exceeding T°C, before the liquid fuel is supplied to the premixing type combustion burner, wherein T°C represents a boiling point, in an atomized atmosphere, of one of the components of die liquid fuel, which has the lowest boiling point.
  • the heating means heats the liquid fuel to a temperature equal to or more than T x 0.8°C.
  • a combustion apparatus comprising a means for discriminating the type of liquid fuel, a means for calculating the boiling point of one of the components of the liquid fuel discriminated in type, which has the lowest boiling point, a means for determining a heating temperature for the liquid fuel on the basis of the calculated boiling point, and means for heating the liquid fuel to the determined temperature.
  • the discriminating means may be designed to discriminate the type of the liquid fuel on the basis of physical property values provided before and after the liquid fuel is heated.
  • a combustion apparatus including a combustor from which a burnable combustion intermediate product is discharged, the apparatus comprising an absorbing device in which an absorbing solution for absorbing the combustion intermediate product is reacted with the combustion intermediate product, and an absorbing solution ejecting device for ejecting the absorbing solution containing the combustion intermediate product absorbed therein into a combustion chamber in the combustor.
  • combustor embraces all combustors, for example, a combustor for a gas turbine, a boiler, a reactor in a chemical plant or the like, and an incinerator, if they are adapted to burn a fuel-air mixture after mixing a liquid fuel with a combustion air.
  • the combustion air flowing into the inner shell is formed into a swirling flow in the inner shell by the swirling-flow guide impeller.
  • the swirling combustion air allows the liquid fuel supplied to the inner peripheral surface of the inner shell to be forced against the inner peripheral surface, thereby forming a liquid fuel film.
  • the inner peripheral surface of the inner shell is increased in diameter in a downstream direction, the liquid fuel in the film form is gradually reduced in thickness, as it flows downstream. This ensures that the liquid fuel can be finely divided.
  • the liquid fuel which has reached the downstream end of the inner shell is ejected to a boundary between the swirling flow formed in the inner shell and the straightly running flow formed between the inner and outer shells, where the liquid fuel is finely divided by reception of a shearing force under actions of the swirling flow and the straightly running flow which act in different directions.
  • the preheating of the liquid fuel is very effective for the fine division of the fuel, and the heating of the fuel to near its boiling point ensures that the surface tension of the fuel can be considerably reduced, and the size of the atomized particles can be of about 40 ⁇ m which is substantially the limit for fine division.
  • the straightly running flow prevents the liquid fuel ejected from the inner shell from being adhered to the inner wall of the evaporation chamber. Also, the swirling flow attracts the atomized particles toward the center of swirling to prevent the liquid fuel from being adhered to the inner wall of the evaporation chamber. If the liquid fuel is adhered to the inner wall of the evaporation chamber, it is difficult to evaporate the adhered liquid fuel and it may be fed in a non-vaporized state to the combustion chamber, so that a dilute premixed combustion cannot be effected. This is the reason why the adhesion of the liquid fuel to the inner wall of the evaporation chamber is prevented.
  • downstream end of the outer shell is located more downstream than the downstream end of the inner shell. The reason is that with such a construction, a straightly running flow can be reliably ensured in the vicinity of the inner wall of the evaporation chamber.
  • the atomized particles of the liquid fuel are attracted toward the center of swirling under the influence of the swirling flow.
  • the area of passage for the straightly running flow i.e., the area of the opening of the inner shell is equal to the area of passage for the swirling flow, i.e., the area of the opening between the inner and outer shells, a substantially uniform distribution of air velocity in the downstream direction within the evaporation chamber can be achieved.
  • the amount of fuel per unit volume is larger at the center of the swirling flow and hence, the amount of fuel per unit amount of air is also larger. If this is considered from the viewpoint of the air ratio, the air ratio is lower at the center of swirling and increasingly higher towards the periphery of the swirling, i.e., towards the vicinity of the evaporation chamber.
  • This flame is propagated from the center of the jet flow to the outside of the jet flow.
  • a mixture of the premixture and the combustion gas or the combustion air is formed around the outer periphery of the jet flow, and hence, the density of the fuel therein is lower, so that the thermal production of NOx is inhibited.
  • One means for realizing such a combustion process is a flame holder.
  • One of the flame holders having the simplest structure is a resistor abruptly reduced in sectional area downstream. If a jet flow collides against the resistor, a circulating flow is formed downstream of the resistor, and the high temperature combustion gas flows into the circulating flow, thereby providing an effect as described above.
  • One approach for promoting the mixing of the combustion gas or the combustion air from the periphery of the premixture jet flow is to provide a combustor structure in which a premixture can be ejected as a straightly running flow, and the combustion gas can be circulated around the premixture jet flow, or a combustor structure in which a premixture jet flow is ejected as a straightly running flow, and the combustion air can be circulated around the premixture jet flow.
  • the premixture and the combustion gas or the combustion air may be ejected with a difference in velocity between the premixture jet flow and the combustion gas or the combustion air.
  • a combustion air passage or a combustion air nozzle is provided in close proximity to the premixing combustion burner, so that the velocity of combustion gas or combustion air ejected may be smaller than the velocity of premixture ejected.
  • the resistor is provided downstream of the swirling flow formed in the evaporation chamber, so that the air ratio of the fuel-air mixture is lower in the vicinity of the resistor and is increasingly higher in a direction away from the resistor.
  • the air ratio at the center of the swirling flow i.e., in the vicinity of the resistor may be of a level enabling firing with the aid of the high-temperature combustion gas. Even if the average air ratio of the premixture ejected from the premixing combustion burner is high, a stable flame can be formed.
  • the residence time in the evaporation chamber is preferred to be constant from the viewpoint of the evaporation of the fuel, but from the operational characteristic of the gas turbine, the amount of combustion air may be increased in some cases, resulting in a shortened residence time in the evaporation chamber. In such a case, the atomized particles flow into the combustion chamber without being completely evaporated, and for this reason, a dilute premixed combustion cannot be achieved to provide a reduction in the amount of NOx.
  • the amount of combustion air may be reduced in some cases, resulting in a prolonged residence time of the atomized particles. If the residence time is too long, however, the atomized particles may be ignited in the evaporation chamber, with the result that the combustor cannot be operated in safety.
  • the liquid fuel is preheated before atomization thereof.
  • the heating temperature range may be as follows: X °C ⁇ temperature°C of liquid fuel ⁇ X x 0.8°C wherein X represents the boiling point, in an atomized atmosphere, of that one of the components of the liquid fuel, which has the lowest boiling point.
  • the determination of an upper limit of the heating temperature at X°C ensures that even if the pressure in the liquid fuel piping is varied in order to vary the amount of liquid fuel supplied, the component having the lowest boiling point is scarcely boiled in the piping, so that the combustor can be operated stably.
  • the atomized particles are evaporated after being ejected from the atomizer into the evaporation chamber, it takes a time corresponding to the sum of the heating time required for the atomized particles to be heated up to a boiling point and the evaporating time required for the atomized particles to be evaporated after reaching the boiling point.
  • the determination of a lower limit of the heating temperature at X x 0.8°C ensures that little heating time is required.
  • the surface tension of the liquid fuel can be reduced down to a very small value and hence, the particle size of the atomized particles can be reduced to substantially near a limit.
  • the evaporating time can be also very shortened, because the square of the particle size is proportional to the evaporating time. Therefore, if the liquid fuel is preheated in this manner, the atomized particles are evaporated in a very short time, ensuring that the residence time of the atomized particles in the evaporation chamber can be set to less than the self-ignition time, and the atomized particles can be evaporated within the residence time. If the atomized particles can be reliably evaporated in the evaporation chamber, the fuel cannot be burned in an atomized droplet state and hence, a reduction in the amount of NOx can be provided.
  • the combustor such as a combustor for a gas turbine, a boiler and an incinerator is capable of burning any of a variety of types of fuel, as described above, but the operation control is difficult and cannot be realized, because the flow characteristic or the like of the fuel may be varied depending upon the type of the fuel.
  • the means for discriminating the type of the liquid fuel is provided, and the heating means for heating the fuel in accordance with the discriminated type is provided.
  • the heating of the fuel in accordance with the type thereof ensures that even with a different type of liquid fuel, the flow characteristic thereof and the like can be kept constant, and a stable operation can be always carried out.
  • the type of the liquid fuel can be discriminated by previously determining a relationship between the temperature and the density, the partial pressure of vapor, the surface tension, the light-refractive index and the like for every liquid fuel and actually measuring values of such parameters of a fuel to be discriminated, and comparing the measured values with the predetermined values.
  • the measurement may be carried out at two places upstream and downstream of the preheater, and the type may be discriminated in the light of resulting values.
  • different physical properties such as the density and the surface tension may be measured at two places.
  • the liquid fuel generally consists of a plurality of components and hence, the boiling point of the liquid fuel cannot be distinctly determined.
  • the heating temperature may be determined on the basis of the boiling point of one of the components which has the lowest boiling point. This is because it is possible to prevent a boiling in a place where the boiling therein is not preferred, such as in the pipeline.
  • an absorbing-solution spraying device for spraying an absorbing solution for absorbing the product in an exhaust gas line ensures that the combustion intermediate product can be removed from an exhaust gas.
  • the combustion intermediate product is ejected into the combustion chamber together with the absorbing solution by the absorbing-solution spraying device.
  • the combustion intermediate product is brought into contact with the high-temperature combustion gas in the combustion chamber and thermally decomposed, for example, into H2O and CO2.
  • a flame is cooled by the absorbing solution, leading to a reduced amount of thermal NOx .
  • sprayed particles of the absorbing solution have a particle size as small as possible, and the flow rate of the absorbing solution is limited to such a level that all the solution can be evaporated in the combustor. This is because unless the evaporation in the combustion chamber is totally completed, not only can the temperature in the combustion chamber due to the evaporation not be expected to be satisfactorily reduced, but also unevaporated droplets collide against the turbine blade to cause an erosion.
  • Figs.1 to 7 illustrate a first embodiment of the present invention, wherein
  • a combustor according to the first embodiment is used for a gas turbine and comprises a combustion cylinder 10, a pilot burner 20 placed upstream of the combustion cylinder 10 in an extension of the center of the combustion cylinder 10, a plurality of premixing type combustion burners 30, 30 --- disposed radially around the pilot burners 20, a preheater 70 for a liquid fuel, and a casing 15 which contains the preheater 70 therein.
  • the interior of the combustion cylinder 10 is a combustion chamber 11, and an annular passage defined between the combustion cylinder 10 and the casing is a wind box 16.
  • the premixing type combustion burner 30 is comprised of an atomizer 40 for atomizing the liquid fuel, and an evaporation chamber 31 in which the atomized liquid fuel is evaporated and premixed with combustion air.
  • the atomizer 40 is disposed upstream of the evaporation chamber 31 and comprises an outer cylindrical shell 41, an inner cylindrical shell 45 concentrically mounted in the outer cylindrical shell 41, and a swirler 50 provided to form a swirling flow of the combustion air in the inner shell 45.
  • the inner cylindrical shell 45 has an inner downstream peripheral surface which is gradually enlarged in diameter in a downstream direction, as shown in Fig.3, and a downstream end 49 in contact with an outer peripheral surface of the inner shell 45, which end is formed to have a knife-edge like section, so that the inner and outer peripheral surfaces of the inner shell 45 are connected with each other at an acute angle.
  • a fuel reservoir 46 is provided in an inner surface of the inner cylindrical shell 45 at a downstream portion thereof.
  • a fuel supply pipe 47 is connected to a fuel distributer 76 and also to the fuel reservoir 46.
  • the inner cylindrical shell 45 has an air inlet hole 48 provided at its upstream portion for permitting the combustion air in the wind box 16 to be passed therethrough into the inner shell 45.
  • the swirler 50 provided within the inner cylindrical shell 45 is comprised of a columnarly formed support 51 provided centrally of the inner cylindrical shell 45, and a plurality of swirl guide impellers 52 radially provided on the support 51.
  • an air inlet hole 42 for permitting the combustion air in the wind box 16 to be passed therethrough into an air passage defined between the inner and outer cylindrical shells 45 and 41.
  • the air inlet hole 42 is formed into a bell shaped mouth to reduce the resistance of air flowing thereinto.
  • a downstream end 43 of the outer cylindrical shell 41 is located further downstream than the downstream end 49 of the inner cylindrical shell 45.
  • the area of the air passage in the inner cylindrical shell 45 is substantially equal to that of the air passage defined between the inner and outer cylindrical shells 45 and 41, so that the flow rates of the combustion air flowing through these air passages are equal to each other.
  • a conical resistor 35 having an apex directed in an upstream direction is provided at a downstream end of the evaporation chamber 31, i.e., substantially centrally in the vicinity of an outlet in each of the premixing type combustion burners 30.
  • the resistor 35 is supported by a resistor support 36 mounted on an inner peripheral surface of the evaporation chamber 31.
  • An air nozzle 60 is provided around a periphery of each of the premixing type combustion burners 30 for ejecting the combustion air.
  • the air nozzle 60 communicates with the wind box 16, and an air flow rate control valve 61 is mounted at such a communication place for controlling the flow rate of the combustion air.
  • the pilot burner 20 is provided at its central portion with a pilot fuel nozzle 21 for ejecting a pilot fuel 26 in a conical film form.
  • a finely-dividing air nozzle 22 is mounted around the pilot fuel nozzle 21 for ejecting air for finely dividing a film-like pilot fuel 26 into finely-divided fuel droplets.
  • an air nozzle 23 is mounted around the finely-dividing air nozzle 22 for ejecting air for combustion of the pilot fuel.
  • a swirler 24 is provided within the air nozzle 23 for swirling the combustion air ejected from the air nozzle 23.
  • the preheater 70 is mounted within the wind box to heat the liquid fuel by utilizing the heat of the heated combustion air.
  • the preheater 70 is connected at its upsteam portion to a fuel tank which is not shown.
  • a measuring means 71 for measuring the density and temperature of the liquid fuel
  • a fuel flow rate control valve 72 for controlling the flow rate of the liquid fuel supplied to the preheater 70.
  • the downstream end of the preheater 70 is connected to the fuel distributer 76 for supplying the liquid fuel in equal amounts to the premixing type combustion burners 30, 30, ---.
  • a measuring means 73 is provided between the fuel distributer 76 and the preheater 70 for measuring the density and temperature of the liquid fuel.
  • the fuel distributer 76 is provided with a fuel return valve 75 for returning the fuel back to the fuel tank.
  • a control system 74 is connected to the fuel flow rate control valve 72 and the return valve 75 for controlling these valves 72 and 75 in response to signals from the measuring means 71 and 73.
  • the control system 74 has a function for discriminating the type of the liquid fuel on the basis of the results of measurement in the measuring means 71 and 73, a function for calculating the boiling point, in a fuel-ejected atmosphere, of that one of the components of the discriminated liquid fuel, which has the lowest boiling point, and a function for determining a temperature for heating the fuel on the basis of the calculated boiling point to control the opening degree of each of the valves 72 and 75.
  • the pilot fuel 26 is ejected in a conical film-like form from the pilot fuel nozzle 21 into the combustion chamber 11.
  • the finely-dividing air 27 is ejected at a rate in the range of about 100 to 200 m/sec from the finely-dividing air nozzle 22 toward the pilot fuel 26 ejected in the conical film-like form.
  • the finely-dividing air 27 causes a strong shearing force to act on the liquid film of the pilot fuel 26 to finely divide the pilot fuel 26.
  • the finely-divided pilot fuel 26 is burned with the aid of the combustion air ejected from the air nozzle 23.
  • the combustion air is formed into a swirling flow by the swirler 24 provided within the air nozzle 23, so that an upstream-directed flow is formed downstream of the pilot fuel nozzle 21 which is around the swirling flow. Therefore, a combustion gas at a high temperature flows thereinto, so that the finely-divided pilot fuel is heated and ignited.
  • a flame produced from the pilot burner 20 is a so-called diffusion flame formed by the combustion air ejected from the separate nozzles 21 and 23 and the pilot fuel 26. For this reason, the pilot flame is formed stably, even if the amount of fuel supplied is varied. However, a higher temperature region in which a fuel-air mixture is burned at a theoretical air ratio is necessarily formed in the diffusion flame and hence, a large amount of NOx may be produced. To prevent this, the pilot burner 20 may be primarily utilized in the event of a smaller loading such as during start up of the combustor, and the premixing type burner 30 may be primarily utilized in the event of increased loading.
  • the density and temperature of the liquid fuel are measured by the measuring means 71 and 73.
  • a relationship between the density and the temperature of the liquid fuel of each type has been determined by a test, and the control system 74 discriminates the type of the liquid fuel from such a relationship and the results of measurement and calculates a boiling point, in the fuel-ejected atmosphere, of the one of the components of the liquid fuel having a lowest biling point.
  • the heating temperature for the liquid fuel is determined on the basis of the calculated boiling point.
  • the type of the liquid fuel is discriminated to determine the heating temperature in this manner and therefore, even with a different type of liquid fuel, a heating temperature suitable for such a liquid fuel can be determined.
  • the measuring means 71 and 73 are provided upstream and downstream of the preheater 70, respectively. This is for the purpose of accurately determining the physical properties of the liquid fuel and discriminating the type of the liquid fuel.
  • the type of the liquid fuel has been discriminated on the basis of the density in this embodiment, it is to be understood that the type of the liquid fuel may be discriminated on the basis of various physical property values such as surface tension, partial pressure of vapor and light-refractive index.
  • the heating temperature is set in a temperature range defined in the following manner: X °C ⁇ heating temperature ⁇ X x 0.8°C wherein X represents the calculated boiling point.
  • the lower limit of the heating temperature has been determined by a test to be a value at which the liquid fuel can be finely divided efficiently.
  • the preheated liquid fuel is supplied to the premixing type combustion burner 30.
  • the liquid fuel is atomized by the atomizer 40; evaporated and premixed in the combustion chamber 31 and burned at the burner outlet.
  • the preheated liquid fuel is supplied via the fuel distributer 76, the fuel supply piping 47 and the fuel reservoir 46 to the inner peripheral surface of the inner cylindrical shell at its upstream portion.
  • the combustion air flowing into the inner cylindrical shell 45 is formed into a swirling flow in the inner cylindrical shell by the swirler 50.
  • the swirling combustion air causes the liquid fuel supplied to the inner peripheral surface of the inner cylindrical shell 45 to be forced onto the inner peripheral surface to provide a film form. Because the inner peripheral surface is gradually increased in diameter in the downstream direction, the liquid fuel in the film form is gradually reduced in thickness, as it flows downwardly.
  • the liquid fuel which has reached the downstream end of the inner cylindrical shell 45 is ejected to an interface between the swirling flow formed in the inner cylindrical shell 45 and a straightly-running flow formed between the inner and outer cylindrical shells 45 and 41, where it is finely divided by being acted upon by a shearing force caused by the actions of the swirling flow and the straightly running flow.
  • the preheating of the liquid fuel is very effective for finely dividing the fuel, wherein the surface tension of the fuel is considerably reduced by heating the fuel up to near its boiling point, and particles having a diameter of about 40 ⁇ m are formed substantially at a limit of fine-division.
  • the flow rates of air suitable for forming the swirling flow and the straightly-running flow are substantially equal to each other, because the areas of the air passages therefor are equal to each other. For this reason, the downstream flow velocities are also equal to each other, thereby ensuring that the straightly running flow and the swirling flow are less disturbed and can be relatively maintained to a downstream side.
  • the straightly running flow inhibits the liquid fuel ejected from the atomizer 40 from being adhered to an inner wall of the evaporation chamber 31. If the liquid fuel is adhered to the inner wall of the evaporation chamber 31, it is difficult to fully evaporate the adhered liquid fuel, and the liquid fuel in its unvaporized state is passed into the combustion chamber 11. If the unvaporized liquid fuel is burned, a large amount of NOx is produced as in the diffusion combustion. Also to prevent this, it is of great significance to form the straightly running flow along the inner wall of the evaporation chamber 31.
  • the swirling flow attracts the atomized particles of the liquid fuel to the center of swirling.
  • the concentration of the atomized particles in the evaporating chamber 31 is higher in the vicinity of a central axis of the atomizer 40 and reduced toward the inner wall of the evaporating chamber 31. Because the air velocity distribution in the evaporating chamber 31 is substantially even, as described above, the proportion of the atomized particle flow rate per a unit air flow rate is reduced from the central axis of the atomizer toward the outer periphery of the atomizer. If the concentration of the atomized particles is considered from the viewpoint of the air ratio, the air ratio is increased from the central portion of the evaporating chamber 31 toward the inner peripheral wall of the evaporating chamber 31.
  • the swirling flow also contributes to a prevention of adhesion of the atomized particles to the inner wall of the evaporating chamber 31 by attracting the atomized particles toward the center of swirling.
  • the atomized particles are heated and evaporated by the combustion air heated to about 350°C, and then mixed with the combustion air to form a premixture (premixed gas) in the course of flowing downward from the evaporating chamber 31.
  • heating time After being ejected from the atomizer 40, it takes an amount of time for the atomized particles to be heated to boiling point (heating time) and a further time for them is be fully evaporated (evaporating time).
  • the heating time required is small, because the liquid fuel has been heated to near the boiling point by the preheater 70.
  • the evaporating time required for the atomized particles reduced in particle size down to near a limit is also very short, because it is proportional to the square of the particle size.
  • the atomized particles are evaporated in a very short time and hence, it is possible to set the residence time for the atomized particles in the evaporation chamber to be within the self-ignition time and to evaporate the atomized particles within the residence time.
  • the testing conditions are as follows: The diameter of an inner periphery of the evaporating chamber : 80 mm, the velocity of air flowing through the evaporating chamber : 70 m/sec., the length of the evaporating chamber : 0.3 m, the velocity of air ejected for the downstream swirling and straightly-running flows at the outlet of the atomizier : 140m/sec., the angle of the swirling-flow guide impeller with respect to a central axis : 30°C.
  • the air ratio was 1.2 in the vicinity of the center of the evaporating chamber and 1.6 in the vicinity of the inner wall of the evaporation chamber, and the average air ratio was of 1.4.
  • the air ratio in the vicinity of the inner wall of the evaporation chamber was about 30 % higher than that in the vicinity of the center of the evaporation chamber.
  • the premixture having such an air ratio distribution is ejected from the premixing type combustion burner 30 and burned.
  • the premixture 90 ejected from the premixing type burner 30 collides against the resistor 35 to form a circulating flow region 91 downstream of the resistor 35.
  • the premixture flows in an upstream direction in the central area of the resistor 35 and in a downstream direction in the peripheral area of resistor 35.
  • a region 93 of dilute premixing of the premixture 90 and the combustion air 92 is defined in a boundary between the premixing type burner 30 and the air nozzle 60.
  • the combustion gas 94 produced from the combustion of the premixture 90 flows into the circulating region 91, so that the circulating region 91 is thereby heated to a high temperature.
  • the high-temperature combustion gas 94 in the circulating region 91 ensures that the premixture 90 reaches an ignition temperature and is ignited to form a burning region 95 downstream of the periphery of the resistor 35.
  • the air ratio distribution in the combustion chamber 11 is now considered, the air ratio is increasingly higher in a direction away from the resistor 35. This is because a premixture 90 of a lower air ratio is ejected from the premixing type burner 30 to the vicinity of the resistor 35, and the combustion air 92 is ejected from the air nozzle 60 provided around the premixing type burner 30.
  • the premixture 90 is first brought into contact with the high-temperature combustion gas 94 downstream of the resistor 35 and burned to form a stabilized premixed flame. Then, the flame is propagated to an outer peripheral area which has a higher air ratio whereby it is difficult to provide a stable combustion, thereby providing a stabilized combustion of a dilute premixture. It should be noted that NOX produced is reduced with an increase in air ratio and hence, the concentration of NOX produced by combustion of the premixture of a higher air ratio around the outer periphery is very low.
  • the air ratio distribution of the premixture is made uniform, but in the present embodiment, the air ratio at the center of the premixing type burner 30 is intentionally lowered, and a premixture 90 having a lower air ratio is passed close to the resistor 35, thereby providing a stabilization of combustion.
  • the combustion air is supplied from the middle of the evaporation chamber 31 to provide an increased intensity of a turbulent flow and an increased uniformity of a primary mixed gas, there is an increased variation in velocity at the outlet of the premixing type burner 30, with the result that the combustion is unstable, and a back flow of the flame to the evaporating chamber is apt to be produced.
  • a combustor used in this test comprises a premixing type combustion burner 81 having an inside diameter of 50 mm and mounted at a central location upstream of a combustion chamber 80 having an inside diameter of 200 mm, a disk-like resistor 82 having an outside diameter of 36 mm and mounted downstream of the burner 81, and an annular air nozzle 83 having an inside diameter of 68 mm and an outside diameter 78 mm and provided around the burner 81, as shown in Fig.6.
  • the test was conducted to measure the concentration of NOx at a combustor outlet in a case where a premixture was ejected from the premixing type burner 81 and a combustion air was ejected from the air nozzle 83, and in a case where the premixture was ejected from only the premixing type burner 81 and no combustion air was ejected from the air nozzle 83.
  • Fig.7 wherein the axis of the ordinate indicates the concentration of NOx at the combustor outlet and is corrected in such a manner that the concentration of oxygen at the combustor outlet is of 0 %, and the axis of abscissas indicates the air ratio in the premixing type burner 81.
  • the black circle corresponds to the case where the premixture was ejected from the premixing type burner 81 and the combustion air was ejected from the air nozzle 83
  • the white circle corresponds to the case where the premixture was ejected from only the premixing type burner 81 and no combustion air was ejected from the air nozzle 83.
  • a gas turbine-combined electric power apparatus of the present embodiment is comprised of a combustor 100, a gas turbine 111 connected to the combustor 100, and a denitration device (not shown), a waste-heat recovery boiler 112, an absorption tower 113 and a smokestack 115, which are disposed in sequence downstream of the gas turbine 100.
  • a spray nozzle 114 is mounted in an upper portion of the absorption tower 113 for spraying water downwardly.
  • a circulating pipe 116 for supplying the water accumulated in the bottom of the tower back to the spray nozzle 114, and a supply pipe 117 for supplying the water accumulated in the bottom of the tower back into the combustor 100.
  • a supply pump 118 is mounted in the supply pipe 117.
  • the combustor 100 is comprised of a combustion cylinder 102 defining a combustion chamber 101, a pilot burner 103 and premixed type combustion burners 104. 104. --- provided upstream of the combustion cylinder 102, and a transducer 105 provided downstream of the combustion cylinder 102.
  • the orifice 106 is designed so that water can be sprayed therethrough by utilizing a water supply pressure.
  • the orifice 106 has an opening diameter which is set in such a manner that the flow rate of water ejected from the orifice 106 can be restrained at a level suitable for such water to be evaporated before reaching a central portion of the combustion cylinder 102.
  • the restraint of the flow rate of the sprayed water by the orifice 106 is for the purpose of preventing the water from being supplied in its unevaporated form to the gas turbine 111.
  • an alcohol is used as a fuel for the combustor 100.
  • an aldehyde which is an intermediate combustion product is produced and supplied together with an exhaust gas to the gas turbine 111.
  • the exhaust gas containing the aldehyde drives the gas turbine 111 and is then passed through the denitration device (not shown) and the waste-heat recovery boiler 112 to a lower portion of the absorption tower 113.
  • the absorption tower 113 water is sprayed downwardly from the spray nozzle 114 to come into contact with the exhaust gas flowing upwardly, so that the aldehyde in the exhaust gas is absorbed into the water.
  • the aldehyde-absorbed water is accumulated in the bottom of the tower 113, and a portion thereof is supplied through the circulating pipe 116 back to the spray nozzle 114.
  • Another portion of such water is passed through the supply pipe 117, compressed by the supply pump 118 and sprayed into the combustion chamber 101 through the orifices 106, 106.
  • the sprayed water is brought into contact with a gas at an increased temperature equal to or more than 1400°C in the combustion chamber 101.
  • the sprayed water reduces the temperature of the increased-temperature gas by a latent heat of vaporization. Such a reduction in temperature ensures that nitrogen in the air is difficult to oxidize, and the amount of NOx produced is reduced.
  • the aldehyde absorbed in the water is thermally decomposed into H2O and CO2 by the increased-temperature gas and discharged from the combustor 100 together with the exhaust gas.
  • the orifices 106 have been provided at the location corresponding to two thirds of the length of the combustion cylinder 102 from its upstream side to its downstream side in the present invention, this being for the purpose of spraying the aldehyde-containing water into the vicinity of a leading end of a flame, it will be understood that if the position of a leading end of a flame is different structurally within the combustor, it is preferable to provide orifices at a different location in correspondence to the position of the leading end

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Spray-Type Burners (AREA)
EP91308745A 1990-09-26 1991-09-25 Chambre de combustion et appareil à combustion Expired - Lifetime EP0478305B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2256404A JP2942336B2 (ja) 1990-09-26 1990-09-26 燃焼器および燃焼設備
JP256404/90 1990-09-26

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EP0478305A2 true EP0478305A2 (fr) 1992-04-01
EP0478305A3 EP0478305A3 (en) 1993-11-24
EP0478305B1 EP0478305B1 (fr) 1997-12-03

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JP (1) JP2942336B2 (fr)
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Cited By (19)

* Cited by examiner, † Cited by third party
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EP0660038A2 (fr) * 1993-12-23 1995-06-28 ROLLS-ROYCE plc Dispositif d'injection de carburant
EP0675322A2 (fr) * 1994-04-02 1995-10-04 ABB Management AG Brûleur à prémélange
EP0692674A3 (fr) * 1994-07-13 1997-07-23 Abb Research Ltd Procédé et dispositif pour la répartition du combustible dans un brûleur adapté aux combustibles liquides ainsi que gazeux
WO1997039284A1 (fr) * 1996-04-17 1997-10-23 Velke William H Procede et dispositif de combustion pour combustibles hydrocarbones liquides
WO1998030841A1 (fr) * 1997-01-10 1998-07-16 Velke William H Procede et dispositif de combustion de combustibles hydrocarbures liquides
FR2765952A1 (fr) * 1997-07-09 1999-01-15 Deutsch Zentr Luft & Raumfahrt Buse de pulverisateur pour la pulverisation du carburant dans des bruleurs
EP0913631A2 (fr) * 1997-11-03 1999-05-06 Max Weishaupt GmbH Installation chauffée par l'huile aux émissions réduites d'oxyde d'azote (NOx)
DE102007009922A1 (de) 2007-02-27 2008-08-28 Ulrich Dreizler Hohlflamme
CN101196293B (zh) * 2006-12-08 2010-09-29 上海齐耀动力技术有限公司 一种热气机用预混旋流平焰式燃烧器
US9366442B2 (en) 2011-06-03 2016-06-14 Kawasaki Jukogyo Kabushiki Kaisha Pilot fuel injector with swirler
US9429324B2 (en) 2011-06-03 2016-08-30 Kawasaki Jukogyo Kabushiki Kaisha Fuel injector with radial and axial air inflow
US10359213B2 (en) 2013-02-14 2019-07-23 Clearsign Combustion Corporation Method for low NOx fire tube boiler
US10386062B2 (en) 2013-02-14 2019-08-20 Clearsign Combustion Corporation Method for operating a combustion system including a perforated flame holder
CN111473365A (zh) * 2020-04-08 2020-07-31 浙江惠文美炉具有限公司 一种用于风机炉的增压隔热式风力助燃装置
US10808927B2 (en) 2013-10-07 2020-10-20 Clearsign Technologies Corporation Pre-mixed fuel burner with perforated flame holder
US10823401B2 (en) 2013-02-14 2020-11-03 Clearsign Technologies Corporation Burner system including a non-planar perforated flame holder
US11415316B2 (en) 2017-03-02 2022-08-16 ClearSign Technologies Cosporation Combustion system with perforated flame holder and swirl stabilized preheating flame
US11460188B2 (en) 2013-02-14 2022-10-04 Clearsign Technologies Corporation Ultra low emissions firetube boiler burner
US11906160B2 (en) 2017-05-08 2024-02-20 Clearsign Technologies Corporation Combustion system including a mixing tube and a flame holder

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JPH05203146A (ja) * 1992-01-29 1993-08-10 Hitachi Ltd ガスタービン燃焼器及びガスタービン発電装置
US8387394B2 (en) 2007-07-09 2013-03-05 Siemens Aktiengesellschaft Gas-turbine burner
CN106122981A (zh) * 2016-07-15 2016-11-16 南通纺都置业有限公司 含盐有机混合废液的焚烧方法
US10953475B2 (en) 2016-11-15 2021-03-23 Synthe Tech Inc. Chip/dust prevention cover, chip/dust prevention cover set, chuck mechanism, and machine tool
CN117948610A (zh) * 2024-03-21 2024-04-30 大同知了科技有限公司 一种激波器、激波气化燃烧机及燃烧方法

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GB2172099A (en) * 1985-03-05 1986-09-10 Steinmueller Gmbh L & C Atomization of fuel in a burner
EP0233971A1 (fr) * 1986-02-24 1987-09-02 NTG Neue Technologien GmbH & Co. KG Procédé pour l'épuration des fumées des installations de chauffage domestiques à mazout
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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0660038A2 (fr) * 1993-12-23 1995-06-28 ROLLS-ROYCE plc Dispositif d'injection de carburant
EP0660038A3 (fr) * 1993-12-23 1996-06-05 Rolls Royce Plc Dispositif d'injection de carburant.
US5647538A (en) * 1993-12-23 1997-07-15 Rolls Royce Plc Gas turbine engine fuel injection apparatus
EP0675322A2 (fr) * 1994-04-02 1995-10-04 ABB Management AG Brûleur à prémélange
EP0675322A3 (fr) * 1994-04-02 1996-05-15 Abb Management Ag Brûleur à prémélange.
EP0692674A3 (fr) * 1994-07-13 1997-07-23 Abb Research Ltd Procédé et dispositif pour la répartition du combustible dans un brûleur adapté aux combustibles liquides ainsi que gazeux
WO1997039284A1 (fr) * 1996-04-17 1997-10-23 Velke William H Procede et dispositif de combustion pour combustibles hydrocarbones liquides
WO1998030841A1 (fr) * 1997-01-10 1998-07-16 Velke William H Procede et dispositif de combustion de combustibles hydrocarbures liquides
FR2765952A1 (fr) * 1997-07-09 1999-01-15 Deutsch Zentr Luft & Raumfahrt Buse de pulverisateur pour la pulverisation du carburant dans des bruleurs
EP0913631A2 (fr) * 1997-11-03 1999-05-06 Max Weishaupt GmbH Installation chauffée par l'huile aux émissions réduites d'oxyde d'azote (NOx)
EP0913631A3 (fr) * 1997-11-03 1999-07-07 Max Weishaupt GmbH Installation chauffée par l'huile aux émissions réduites d'oxyde d'azote (NOx)
CN101196293B (zh) * 2006-12-08 2010-09-29 上海齐耀动力技术有限公司 一种热气机用预混旋流平焰式燃烧器
DE102007009922A1 (de) 2007-02-27 2008-08-28 Ulrich Dreizler Hohlflamme
US9366442B2 (en) 2011-06-03 2016-06-14 Kawasaki Jukogyo Kabushiki Kaisha Pilot fuel injector with swirler
US9429324B2 (en) 2011-06-03 2016-08-30 Kawasaki Jukogyo Kabushiki Kaisha Fuel injector with radial and axial air inflow
US10359213B2 (en) 2013-02-14 2019-07-23 Clearsign Combustion Corporation Method for low NOx fire tube boiler
US10386062B2 (en) 2013-02-14 2019-08-20 Clearsign Combustion Corporation Method for operating a combustion system including a perforated flame holder
US10823401B2 (en) 2013-02-14 2020-11-03 Clearsign Technologies Corporation Burner system including a non-planar perforated flame holder
US11460188B2 (en) 2013-02-14 2022-10-04 Clearsign Technologies Corporation Ultra low emissions firetube boiler burner
US10808927B2 (en) 2013-10-07 2020-10-20 Clearsign Technologies Corporation Pre-mixed fuel burner with perforated flame holder
US11415316B2 (en) 2017-03-02 2022-08-16 ClearSign Technologies Cosporation Combustion system with perforated flame holder and swirl stabilized preheating flame
US11906160B2 (en) 2017-05-08 2024-02-20 Clearsign Technologies Corporation Combustion system including a mixing tube and a flame holder
CN111473365A (zh) * 2020-04-08 2020-07-31 浙江惠文美炉具有限公司 一种用于风机炉的增压隔热式风力助燃装置
CN111473365B (zh) * 2020-04-08 2022-06-03 浙江惠文美炉具有限公司 一种用于风机炉的增压隔热式风力助燃装置

Also Published As

Publication number Publication date
DE69128333T2 (de) 1998-07-09
EP0478305B1 (fr) 1997-12-03
JP2942336B2 (ja) 1999-08-30
DE69128333D1 (de) 1998-01-15
EP0478305A3 (en) 1993-11-24
JPH04136603A (ja) 1992-05-11

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