WO2005075887A1 - 燃焼装置 - Google Patents
燃焼装置 Download PDFInfo
- Publication number
- WO2005075887A1 WO2005075887A1 PCT/JP2005/002371 JP2005002371W WO2005075887A1 WO 2005075887 A1 WO2005075887 A1 WO 2005075887A1 JP 2005002371 W JP2005002371 W JP 2005002371W WO 2005075887 A1 WO2005075887 A1 WO 2005075887A1
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- Prior art keywords
- annular container
- combustion
- fuel
- annular
- air
- Prior art date
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Classifications
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- 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
- F23C3/006—Combustion apparatus characterised by the shape of the combustion chamber the chamber being arranged for cyclonic combustion
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- 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
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/02—Disposition of air supply not passing through burner
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- 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
- F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
- F23C9/006—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber the recirculation taking place in the combustion chamber
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- 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
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
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- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
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- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
Definitions
- the present invention relates to a combustion apparatus, and more particularly, to a combustion apparatus that flows combustion air and fuel into a combustion chamber and mixes and burns combustion air and fuel.
- N O x nitrogen oxides
- Nitrogen oxides are roughly classified into thermal N O x, prompt N O, and fuel N O x, depending on the formation mechanism.
- Thermal NOx is generated by the reaction of nitrogen in the air with oxygen at high temperatures and is strongly dependent on temperature.
- the prompt N O x is generated especially in the overfueled flame zone.
- Fuel N Ox is generated by the involvement of nitrogen compounds contained in the fuel.
- the fuel concentration distribution is made uniform by premixed combustion in which the fuel is well mixed with air before ignition and combustion, and the combustion temperature can be reduced particularly in the premixed combustion of lean combustion.
- premixed combustion has a problem that the stable combustion range is narrow, and backfire and blowout are likely to occur.
- Another disadvantage of liquid fuels is that they cannot be premixed without first evaporating (pre-evaporating) the fuel.
- the fuel is atomized and injected when it passes through a nozzle with a small channel cross-sectional area, but normally the fuel droplets remain at the time of ignition, and the droplets burn and evaporate. There is always a place where the theoretical air ratio is reached, and the temperature is locally high. Mil. Therefore, there is a limit to reducing thermal NOx.
- Pre-evaporation is a technology in which a pre-evaporation section is provided inside or outside the combustor, and the fuel sprayed there is evaporated by heating from the other and then burned.
- pre-evaporation can be expected to reduce thermal NOx equivalent to that of gaseous fuel, it has the disadvantage of increasing the size of the combustor by the pre-evaporation part.
- fuel or air is divided into several stages and supplied into the combustion apparatus to control the air ratio for each region in the combustion chamber.
- a portion with a higher fuel concentration and a portion with a lower fuel concentration than the theoretical air ratio are intentionally created, and thermal NOx is reduced by avoiding the mixed state region where the theoretical air ratio is reached.
- this technology has many achievements in large-scale combustion furnaces, but it cannot be applied to small-sized combustion devices because the fuel or air supply system becomes complicated. It is also difficult to find the optimal values for fuel and air supply positions and division ratios and to control them according to the load.
- burnt gas recirculation slow and uniform combustion is achieved by mixing the pre-burned gas with high temperature and low oxygen concentration with the air before combustion. This lowers the combustion temperature, increases the inert gas, increases the heat capacity, lowers the average flame temperature, and thus reduces the thermal NOx.
- Combustion gas recirculation is mainly applied to boilers, industrial furnace combustion equipment and engines.
- Combustion gas recirculation techniques include flame holders, external recirculation, and internal recirculation. There are also combustion methods called flue gas recirculation (FGR) and exhaust gas recirculation (EGR), but these are basically the same technologies as combustion gas recirculation. .
- FGR flue gas recirculation
- EGR exhaust gas recirculation
- Japanese Patent Laid-Open No. 2 0 0 2-3 6 4 8 1 2 discloses an example in which combustion gas recirculation is used for gaseous fuel.
- the publication discloses an example in which combustion gas recirculation is used for premixed combustion of gaseous fuel.
- the combustion gas is recirculated in a recirculation region formed at the downstream center of the flame holding plate and a space between the combustion device projecting in the combustion chamber and the combustion chamber wall.
- the combustion gas recirculation flow at the downstream center of the flame holding plate does not reach the part where the fuel and air are mixed before ignition, and its action is merely to stabilize the ignition.
- combustion gas recirculation flow from the space between the combustion device and the combustion chamber wall actually stops only in the vicinity of the combustion device, so it burns sufficiently and becomes high temperature and low oxygen concentration.
- the combustion gas does not recirculate and the amount of circulation is small, so the effect of reducing thermal NOX is small.
- the combustion chamber needs to be sufficiently larger than the combustion device diameter so that the combustion gas recirculation flow is sucked from the outside of the combustion device toward the center axis direction. It is not suitable for applications where the size of the combustion chamber needs to be made as small as possible, such as a combustion device for a gas bottle. It is also difficult to apply to liquid fuel.
- the combustion gas is recirculated from the rear center of the flame holding plate by the flame holding plate, and the flame is divided and lifted as a flame, and the combustion gas is also supplied from the flame side.
- Techniques relating to gaseous fuel to be recycled are disclosed. According to this technology, the amount of combustion gas recirculation can be increased, but the structure of the burner is complicated to make a split flame, and there is a portion where there is no flame in the cross section of the burner. Will become large (combustion load per volume is low). It is also difficult to apply this technology to liquid fuel.
- a plurality of premixed gas injection holes are provided in a combustion chamber wall.
- One premixed gas becomes combustion gas and is injected toward the adjacent premixed gas injection hole.
- the air involved in combustion at the time of ignition is fresh air, and since it is mixed for the first time with combustion gas after the start of combustion, there is a problem that the effect of slowing down the combustion is small.
- a low pressure part is created mainly by liquid energy of the combustion air flowing around the fuel nozzle for liquid fuel, and combustion in the furnace The gas is sucked and the combustion gas is mixed with the combustion air.
- the combustion gas is mixed outside the combustion air, it hardly mixes inside the combustion air, and the fuel is first mixed with the combustion air and then gradually mixed with the combustion gas. Therefore, the combustion phenomenon dominates the combustion air with the same oxygen concentration as usual, and in fact, the aim of slow ignition and combustion under a low oxygen concentration cannot be fully realized.
- the structure for sucking combustion gas is complicated.
- the use of split flames complicates the structure of the burner, and the size of the burner increases because there are no flames in the burner cross-sectional area. There is a problem that the combustion load per product is low.
- a swirl flow is induced in a cylindrical combustion device, and the static pressure is reduced at the center of the swirl flow.
- a technique for sucking another gas from the normal direction to the center of rotation is disclosed, and this technique is applied to the combustion gas recirculation in the secondary combustion region in the cylindrical combustion device.
- the primary and secondary air for combustion, and the fuel supply in addition, have the action of inducing the swirl flow; ⁇ , the effect of recirculation of the combustion gas introduced by the swirl is secondary combustion Combustion control of the area is not limited, and the area with high fuel concentration near the base of the flame is not the target area for combustion gas recirculation. Therefore, the effect of reducing ⁇ ⁇ ⁇ is limited only by temperature control at the end of the flame.
- FIG. 1 An example of a conventional general-purpose combustion apparatus is shown in FIG.
- the combustion apparatus shown in FIG. 1 is a cylindrical combustion apparatus, which is a cylindrical container 2 0 0 1, an inflow casing 2 0 0 2, a partition cylinder 2 0 0 4, a fuel nozzle 2 0 0 5, A flame holding plate 2 06 6 arranged coaxially with the fuel nozzle 2 0 0 5 is provided downstream of the fuel nozzle 2 0 5.
- An inflow channel is formed by the cylindrical container 20 0 1, the inflow casing 2 0 0 2, and the partition tube 2 0 4.
- Combustion air 2 0 1 0 flows into inflow casing 2 0 0 2 by a blower or a compressor (not shown), and a space 2 0 0 2 between partition cylinder 2 0 0 4 and fuel nozzle 2 0 0 5 After passing through, it flows through the flame holding plate 2 0 0 6 and flows into the cylindrical container 2 0 1.
- the fuel 20 14 is injected into the cylindrical container 200 1 through the fuel nozzle 2 0 5 by a fuel pump, blower, or compressor (not shown). Fuel 2 0 1 4 and combustion air 2 0 1 0 are mixed and burned to generate combustion gas 2 0 1 6.
- the generated combustion gas 2 0 1 6 flows out from the open end 2 0 0 7 of the cylindrical container 2 0 0 1.
- the flame holding plate 2 0 0 6 is for bringing about stable ignition.
- the flame holding plate 20 06 has a conical shape in which the diameter of the opening end 20 07 is increased, and a space between the partition tube 20 00 and the fuel nozzle 20 05 Blocks the flow of air flowing through 2 0 1 2 to reduce the flow velocity of combustion air 2 0 1 0 at the tip of the fuel nozzle 2 0 0 5 and downstream of the flame holding plate 2 0 0 6 Then, a flow region 2 0 1 8 that flows backward from the downstream is formed.
- the reverse flow 2 0 18 returns the high-temperature combustion gas 2 0 1 6 to the ignition region immediately downstream of the tip of the fuel nozzle 2 0 5.
- FIG. 2A and 2B An example of an annular combustion apparatus in which the combustion apparatus shown in FIG. 1 is applied as it is will be described with reference to FIGS. 2A and 2B.
- the flame holding plate 20 06 is conical, but in the case of the annular combustion apparatus shown in FIGS. 2A and 2B, As shown in FIG. 2B, the flame holding plate is also an annular flame holding plate.
- a plurality of cylindrical fuel nozzles 205 may be attached to the flame holding plate 206, or an annular fuel nozzle (not shown) may be used.
- the action of the fuel nozzle 205 is the same as that of the cylindrical combustion apparatus shown in FIG.
- the combustion apparatus shown in FIG. 3 is a cylindrical combustion apparatus applied to boilers and industrial furnaces.
- combustion air 2 0 1 0 flows through.
- a first swirler 2 0 0 3, a second swirler 2 0 3 0 disposed outside the annular container 2 0 0 1, and an outer cylinder 2 0 3 1 are provided.
- the swirler 2 0 0 3 swirls the flow of the combustion air 2 0 1 0 to form a negative pressure region at the center of the swirl flow and a flow region 2 0 1 9 that flows backward from the downstream.
- the reverse flow 20 1 9 returns the high-temperature combustion gas 2. 0 1 6 to the ignition region immediately downstream of the tip of the fuel nozzle 2 0 0 5, and stabilizes the ignition in the same manner as the flame holding plate 2 0 0 6.
- the second swirler 2 0 3 0 When the second swirler 2 0 3 0 is away from the combustion chamber wall 2 0 3 2, the second swirler 2 0 3 0 is The combustion gas 20 1 6 in the combustion chamber is sucked through and mixed with the combustion air 2 0 1 0 to cause combustion.
- combustion gas 2 0 1 6 is introduced from outside the swirling flow of combustion air 2 0 1 0, combustion air 2 0 1 Almost no mixing inside 0, / Fuel 2 0 1 4 is first mixed with combustion air 2 0 10 and then gradually mixed with combustion gas 2 0 1 6. Therefore, the combustion phenomenon dominates the combustion air 20 10 with the same oxygen concentration as usual, and in fact, ignition and combustion under a low oxygen concentration cannot be realized.
- the combustion gas In the combustion apparatus shown in FIG. 3, the combustion gas must be sufficiently larger than the diameter of the outer cylinder 20 3 1 because the combustion gas recirculation flow is sucked from the outside of the outer cylinder 20 3 1. There is. Therefore, this combustion device is the size of a combustion chamber such as a gas turbine combustion device. The law needs to be as small as possible; it is not suitable for certain applications. In addition, the combustion apparatus shown in Fig. 3 is not suitable for application to an annular combustion apparatus.
- the configuration, operation, and problems of the conventional annular gas turbine combustion system will be described with reference to FIG.
- the conventional gas turbine combustion system has a very low total air ratio because the target temperature is much lower than the theoretical air volume, that is, the flame temperature in the combustion with the air volume just including the oxygen volume necessary for fuel combustion. It is difficult to burn in a single stage when using low and normal hydrocarbon fuels.
- the supply of combustion air is divided into several stages, fuel is mixed with only a part (primary air 2 0 40 0) and burned, and then the remaining air is added to obtain the desired air Complete combustion is achieved with respect to the outlet temperature.
- the primary combustion region 2 0 4 From the position where the first-stage combustion air is mixed with fuel in the container 2 0 0 1 a to the second-stage air inlet is referred to as the primary combustion region 2 0 4 2.
- Technical in order to add air downstream of the primary combustion zone 2 0 4 2 so that combustion efficiency is not reduced and unburned components are not emitted or NO x generation is increased in gas turbine combustion Many ideas are known.
- reference numeral 2 0 4 4 denotes an air hole formed in the container 2 0 0 1 a
- reference numeral 2 0 4 6 denotes an air bottle 2 0 4 4 that flows into the container 2 0 0 1 a
- combustion under low oxygen concentration by combustion gas recirculation is effective in reducing thermal NOx.
- the conventional combustion device that focuses on combustion under low oxygen concentration by combustion gas recirculation has sufficient combustion gas recirculation amount and NOx reduction effect, and realizes pre-evaporation combustion even with liquid fuel. There is no one that can achieve premixed combustion like gaseous fuel. Disclosure of the invention
- the present invention has been proposed in view of the above-mentioned problems of the prior art, has a relatively simple structure, maximizes the effect of combustion gas recirculation, pre-vaporization of liquid fuel, and gaseous fuel /
- the aim is to provide a combustion device that realizes premixed combustion of liquid fuel and slow combustion at low oxygen concentration, and realizes combustion that suppresses the generation of NOx.
- the present invention is suitable for realizing ceramicization aiming at high temperature resistance at a low cost, and the structure can be simplified particularly when applied to a combustion apparatus for a gas evening bottle, thereby reducing the cost.
- the purpose is to provide a combustion device that can be downed.
- a combustion apparatus that can control and generate combustion gas recirculation with a simple structure.
- the combustion apparatus includes an inner cylinder part constituting an inner peripheral side surface, an outer cylinder part constituting an outer peripheral side face, an open end part, and an annular container having a closed end part, and the open end part of the annular container.
- An air supply unit that supplies combustion air into the annular container so as to have a velocity component in the central axis direction of the annular container toward the closed end, and the release from the closed end of the annular container
- a fuel supply section for supplying fuel into the annular container so as to have a velocity component in the central axis direction of the annular container toward the end.
- the combustion chamber has an annular cross section, in which the flow of air supplied in a region separated from the fuel supply means first intersects the wake of the supplied fuel, and the fuel supply Since it is configured to intersect again with the wake of the fuel supplied in the area near the means, combustion gas recirculation can be actively generated with a simple structure. Therefore, when the present invention is applied to a general-purpose combustion apparatus, the stability is high and the action of combustion gas recirculation can be maximized.
- combustion gas recirculation action can be maximized with high stability, combustion can be performed with combustion gas having a high temperature and a low oxygen concentration. For this reason, even in the case of liquid fuels, where it has been difficult to reduce NOX with conventional technologies, pre-evaporation combustion with stable evaporation behavior, premixed combustion regardless of gaseous fuel or liquid fuel, slow combustion Thus, it is possible to achieve uniform combustion with a low maximum flame temperature and combustion with a low average flame temperature due to the heat capacity of the inert gas in the combustion gas. Therefore, it is possible to achieve thermal N O X suppression, which was difficult with the prior art.
- the air flow track and the fuel flow track intersect twice without making the air flow track and the fuel flow track the same.
- the fuel flow wake first intersects the area near the tip of the fuel wake, and the air flow wake intersects the fuel flow wake the second time from the root of the fuel flow wake to the vicinity of the tip.
- the air flow and the fuel flow are opposed to each other, the air flows in the opposite direction from the outlet direction, the fuel flows in the outlet direction, and the fuel moves away from the spraying side. It is only necessary to spread outward in the direction perpendicular to the center axis of the combustion chamber (in the radial direction in the case of a cylindrical container).
- combustion gas recirculation is actively controlled with a simple structure.
- a combustion apparatus that can be controlled.
- the combustion apparatus includes: an inner cylinder portion that forms an inner peripheral side surface; an outer cylinder portion that forms an outer peripheral side surface; an open end portion; a closed end portion; An inflow passage that is formed through the outer peripheral side surface of the annular container at a position separated from the closed end, and is provided inside the closed end of the annular container; And a fuel nozzle for supplying fuel into the annular container.
- the inflow channel forms an air flow having a velocity component in the central axis direction of the annular container and a velocity component swirling in the circumferential direction of the annular container from the open end to the closed end.
- the fuel nozzle injects fuel toward the inflow channel so as to have a velocity component in the central axis direction of the annular container and a velocity component in the radial direction from the closed end toward the open end. Is configured to do.
- a combustion apparatus that can control and generate combustion gas recirculation with a simple structure.
- the combustion apparatus includes an inner cylinder part that forms an inner peripheral side surface, an outer cylinder part that forms an outer peripheral side surface, an open end part, and a closed end part, and combustion air in the annular container.
- the outer cylinder portion has a smaller diameter at a position away from the closed end portion by a predetermined distance along the central axis of the annular container.
- the inflow channel is formed in a portion where the diameter of the outer cylinder portion is reduced, and the velocity component in the central axis direction of the annular container from the open end toward the closed end and the annular container An air flow having a velocity component swirling in the circumferential direction is formed.
- the fuel nozzle injects fuel toward the inflow channel so as to have a velocity component in the central axis direction of the annular container and a velocity component in the radial direction from the closed end toward the open end. Is configured to do.
- a combustion apparatus that can control and generate combustion gas recirculation with a simple structure.
- the combustion apparatus includes an inner cylinder portion that forms an inner peripheral side surface, an outer cylinder portion that forms an outer peripheral side surface, an open end portion, a closed end portion, and a substantially coaxial axis with the central axis of the annular vessel.
- a cylindrical member which is disposed on the open end side of the outer cylinder part and has a small diameter of the outer cylinder part, and an end part of the outer cylinder part and an outer peripheral surface of the cylindrical member.
- An annular connecting member to be connected; an inflow passage formed in the connecting member for supplying combustion air into the annular container; and provided inside a closed end of the annular container; And a fuel nozzle for supplying fuel.
- the inflow channel extends from the open end to the closed end.
- An air flow having a velocity component in the central axis direction of the annular container and a velocity component rotating in the circumferential direction of the annular container is formed.
- the fuel nozzle directs the fuel toward the inflow channel so as to have a velocity component in the central axis direction of the annular container and a velocity component in the radial direction from the closed end toward the open end. It is comprised so that it may inject.
- a combustion apparatus that can control combustion gas recirculation positively with a simple structure.
- the combustion apparatus includes: an inner cylinder portion that forms an inner peripheral side surface; an outer cylinder portion that forms an outer peripheral JJ surface; an open end portion; a closed end portion; and a central axis of the annular vessel.
- An annular member that is coaxially disposed on the open end side, includes an inner cylindrical portion that forms an inner peripheral side surface, an outer peripheral side surface, and a diameter of the outer cylindrical portion of the annular container is also small.
- An annular member having an outer cylindrical part, an annular first connecting member that connects an end surface of the outer cylindrical part of the annular container on the open end side and an outer peripheral surface of the outer cylindrical part of the annular member, and A second connecting member for connecting the open end side end surface of the inner cylindrical portion of the annular container and the closed end side end surface of the inner cylindrical portion of the annular member; and formed on the first connecting member
- An inflow passage for supplying combustion air into the annular container, and an inner side of the closed end of the annular container.
- a fuel nozzle for supplying fuel to Jo vessel.
- the inflow channel is configured to form an air flow having a velocity component in the central axis direction of the annular container and a velocity component swirling in the circumferential direction of the annular container from the open end toward the closed end.
- the fuel nozzle injects fuel toward the inflow channel so as to have a velocity component in the central axis direction of the annular container and a velocity component in the radial direction from the closed end toward the open end. Is configured to do.
- An additional inflow channel for allowing air to flow into the annular container may be provided in the inner cylindrical portion of the annular container.
- An additional inflow channel (auxiliary air inlet) is provided near the inner cylindrical portion of the closed end of the annular container and radially inward of the fuel nozzle, and air flows toward the central axis of the annular container. You may comprise so that it may flow.
- An additional inflow channel for allowing air to flow inward in the radial direction of the annular container may be provided in the outer cylindrical portion of the annular container.
- the combustion apparatus further includes a rectifying structure that suppresses a swirling flow of air in the vicinity of the closed end of the annular container and / or in the vicinity of the closed end of the outer cylinder of the annular container. May be.
- the combustion apparatus has a speed in a central axis direction of the annular container from the open end to the closed end in the vicinity of the closed end of the annular container and ⁇ or the closed end of the outer cylinder of the annular container.
- a flow of air having a component and swirling in the circumferential direction of the annular container A rectifying structure (guide vane) may be further provided that converts this into a flow inward in the radial direction in the vicinity of the closed end.
- An additional fuel nozzle may be provided at a position closer to the closed end than the inflow channel in the central axis direction of the outer cylindrical portion of the annular container.
- the fuel flow has a velocity component in the direction of the combustion chamber central axis and a velocity component in the direction from the combustion chamber central axis to the combustion chamber wall surface, that is, radially outward, and the air flow is
- the combustion chamber is configured to have a speed component facing in the direction opposite to the fuel flow in the axial direction and a speed component swirling in the circumferential direction, and the fuel flow is directed toward the outlet of the combustion device. Since the combustion air flow has a velocity component in the direction opposite to the outlet direction, the above-described flow can be realized.
- a part of the flow of air supplied from the air supply means (inflow passage) into the combustion chamber flows along the wall surface of the combustion chamber as an air flow that does not become low-temperature combustion gas or combustion gas. .
- the inner wall of the combustor is protected from the heat inside the combustor by a low-temperature combustion gas or an air flow that does not become a combustion gas.
- the generation of thermal NOx can be suppressed even in the co-firing of gaseous fuel Z and liquid fuel, and in the combustion of low heat generation fuel and waste liquid.
- combustion gas recirculation can be actively generated with a simple structure.
- the primary combustion region of the combustion device it has high stability and can maximize the effect of combustion gas recirculation. Due to the high stability, in the gas evening bin combustion apparatus to which the present invention is applied, the primary combustion region can be designed to be leaner, so that the average combustion temperature is kept low, and the thermal NOX is reduced. This has the effect of further suppressing the generation of the.
- the effect of combustion gas recirculation can be maximized with high stability.
- thermal NO X generation can be suppressed.
- the combustion apparatus of the present invention since the inner wall is suitably cooled by the low-temperature air flow, a highly durable gas turbine combustion apparatus can be provided. Furthermore, the combustion apparatus of the present invention has a simple structure, so that heat-resistant materials such as ceramics can be easily used and can be easily disassembled and replaced. Provision of a single-bottle combustion apparatus is realized.
- a gas turbine is constituted by a combustion device provided with an auxiliary fuel nozzle, the generation of thermal NOx can be suppressed even in the combustion of gaseous fuel / liquid fuel or in the combustion of low calorific fuel or waste liquid.
- FIG. 1 is a cross-sectional view showing a conventional cylindrical combustion apparatus.
- FIG. 2A is a cross-sectional view showing a conventional annular combustion apparatus.
- FIG. 2B is a front view of FIG. 2A.
- FIG. 3 is a cross-sectional view showing another example of a conventional cylindrical combustion apparatus.
- FIG. 4 is a cross-sectional view showing a conventional annular fuel burner for a gas turbine.
- FIG. 5 is a perspective view showing the combustion apparatus in the first embodiment of the present invention.
- FIG. 6 is a cross-sectional view of FIG.
- FIG. 7 is a perspective view showing a combustion apparatus in the second embodiment of the present invention.
- FIG. 8 is a cross-sectional view of FIG.
- FIG. 9 is a perspective view showing a combustion apparatus in the third embodiment of the present invention.
- FIG. 10 is a cross-sectional view of FIG.
- FIG. 11 is a perspective view showing a combustion apparatus according to a fourth embodiment of the present invention.
- FIG. 12 is a cross-sectional view of FIG.
- FIG. 13 is a perspective view showing an example of a swirler in the embodiment of the present invention.
- FIG. 14 is a perspective view showing another example of the swirler in the embodiment of the present invention.
- FIG. 15 is a perspective view showing another example of the swirler in the embodiment of the present invention.
- FIG. 16 is a sectional view showing another example of the inflow casing in the embodiment of the present invention. 2.
- FIG. 17 is a perspective view showing another example of the inflow casing in the embodiment of the present invention.
- FIG. 18 is a cross-sectional view of FIG.
- FIG. 19 is a perspective view showing another example of the fuel nozzle in the embodiment of the present invention.
- FIG. 20 is a cross-sectional view of FIG.
- FIG. 21 is a perspective perspective view showing the operation in the embodiment of the present invention.
- FIG. 22A is a partially enlarged sectional view of FIG.
- Figure 22B is an enlarged view of Figure 22A.
- FIG. 23 is a cross-sectional view showing the combustion apparatus in the fifth embodiment of the present invention.
- FIG. 24 is a cross-sectional view showing the combustion apparatus in the sixth embodiment of the present invention.
- FIG. 25 is a perspective perspective view showing the combustion apparatus in the seventh embodiment of the present invention.
- FIG. 26 is a perspective perspective view showing the combustion apparatus in the eighth embodiment of the present invention.
- FIG. 27 is a perspective perspective view showing the combustion apparatus according to the ninth embodiment of the present invention.
- FIG. 28 is a perspective perspective view showing the combustion apparatus in the 10th embodiment of the present invention.
- FIG. 29 is a perspective perspective view showing the combustion apparatus according to the first embodiment of the present invention.
- FIG. 30 is a perspective perspective view showing the combustion apparatus in the first and second embodiments of the present invention.
- FIG. 31 is a cross-sectional view showing a combustion apparatus according to the first embodiment of the present invention.
- FIG. 32 is a perspective view showing the combustion apparatus in the 14th embodiment of the present invention.
- FIG. 33 is a cross-sectional view of FIG.
- FIG. 34 is a cross-sectional view showing the combustion apparatus in the 15th embodiment of the present invention.
- FIG. 35 is a cross-sectional view showing the combustion apparatus in the 16th embodiment of the present invention.
- FIG. 36 is a perspective view showing a case where a swirler is not used in the combustion apparatus according to the second embodiment of the present invention.
- FIG. 37 is a cross-sectional view of FIG.
- FIG. 38 is a block diagram showing an example in which the combustion apparatus of the present invention is applied to a gas turbine generator.
- the combustion apparatus shown in FIG. 5 includes an annular container 12 with one end (closed end) 10 closed, an inflow casing 14, a swirler 16, and an upper end (closed end) of the annular container 1 2.
- a fuel nozzle 18 provided on the back surface of 10 is provided.
- a plurality of air inflow portions 20 are formed at a common pitch on the side surface of the outer periphery of the annular container 12 (the outer cylinder portion 13 described later), and the combustion air 2 2 is passed through the air inflow portion 20.
- the inflow passage is formed by the air inflow section 20, the inflow casing 14, and the swirler 16.
- the annular container 12 has an inner tube portion 15 and an outer tube portion 13, and the inner tube portion 15 and the outer tube portion 13 are closed. It is configured to be closed by the end 10.
- the lower end of the annular vessel 12 is an open combustion gas outlet 26.
- a plurality of inner air inflow portions 30 are formed at positions above the air inflow portion 20 formed in the outer cylindrical portion 13.
- the number of the swirlers 16 is the same as the plurality of air inflow portions 20 having the common pitch, and is not twisted in the normal direction with respect to the central axis.
- it has a guide vane that is disposed obliquely upward and whose inner end is connected to the vicinity of the air inflow portion 20. Other details of the swirler 16 will be described later.
- the inflow casing 14 includes an inner cylinder 3 4 disposed so that a predetermined gap portion 3 2 is formed inside an inner cylinder portion 15 of the annular container 12, and an outer cylinder portion 1 of the annular container 12.
- An outer cylinder 3 8 arranged so that a predetermined gap portion 3 6 is formed on the outside of 3, and an inner bottom portion connecting the lower end of the inner cylinder 3 4 and the lower end of the inner cylinder portion 15 of the annular container 12
- a member 40 and an outer bottom member 42 connecting the lower end of the outer cylinder 38 and the lower end of the outer cylinder part 13 of the annular container 12.
- a plurality of holes are formed in a single ring made of a hollow material, or a plurality of nozzle tips. It can be realized by attaching. .
- the combustion air 2 2 can be blower or pressure. It flows into the gap 3 6 formed by the outer cylinder 3 8 of the inflow casing 1 4 and the outer cylinder part 1 3 of the annular container 1 2 by a compressor (not shown), and passes through the swirler 1 6 It flows into the annular container 12 from the air inflow portion 20 obliquely upward.
- the fuel 21 is injected into the annular container 12 via the fuel nozzle 18 by a fuel pump, blower, or compressor (not shown).
- the fuel 21 and the combustion air 2 2 are mixed and burned, and the combustion gas 24 is discharged from the open end 26 of the annular vessel 12.
- the first embodiment as shown in FIG.
- the combustion container 22 is located at a position away from the closed end 10 of the annular container 12 by a predetermined distance in the axial direction of the annular container 12.
- 1 2 Closed end 10 With a velocity component opposite to the direction from the 0 toward the open end 2 6 (outlet direction) (from the air inlet 20 toward diagonally upward) It flows into 2 and turns. That is, the air 22 flowing into the annular container 12 from the air inflow portion 20 is the velocity component and the annular container in the central axis J direction of the annular container 12 from the open end portion 26 toward the closed end portion 10. 1 A flow 28 having a velocity component swirling in the circumferential direction of 2 is formed.
- the fuel 2 3 spreads in the radial direction with respect to the central axis of the annular vessel 1 2 from the closed end 10 of the annular vessel 1 2 to the outlet 2 6 method, and combustion air It is injected toward the inflow portion 20 of the 2 2. That is, the fuel 23 has a velocity component directed from the closed end 10 toward the open end 26 and a velocity component directed radially outward toward the inflow portion 20 (inflow passage). It is injected. Further, since the air 22a flows obliquely downward in the annular container 12 from the inner air inflow part 30, the inner wall of the inner cylindrical part 15 of the annular container 12 is suitably cooled. .
- the opening ratio, shape, and pitch of the air inflow portion 20 with respect to the side surface of the annular container 12 can be arbitrarily set.
- a structure in which the flow of the combustion air 22 flowing in the inflow portion 20 of the combustion air 22 into the annular container 12 is deflected as long as it has a velocity component opposite to that of the outlet 26. May be provided.
- reference numeral 28 is composed of combustion air 22 flowing in from the air inflow section 20 and combustion gas generated by mixing and burning the fuel, in the direction opposite to the outlet 26.
- a swirling flow having a large velocity component is obtained:
- the annular container 1 2 in the first embodiment of FIGS. 5 and 6 is an annular container 1 1 2 having a structure (stepped structure) in which the outer cylindrical portion 1 1 3 is narrowed. It is the embodiment replaced with.
- An air inflow portion 20 is formed at a portion where the outer diameter of the outer cylindrical portion 1 1 3 changes discontinuously.
- the swirler 16 and the inflow casing 14 are substantially the same as those in the fourth embodiment shown in FIGS. 11 and 12 to be described later, and a detailed description of the swirler 16 and the inflow casing 14 will be given in the fourth embodiment. This is done when explaining.
- the combustion air 22 flowing into the annular vessel 1 1 2 from the air inflow portion 20 turns with a larger velocity component in the opposite direction to the outlet 26. It flows into the annular container 1 1 2 so as to form a stream 2 8.
- the air 22 flowing into the annular container 1 1 2 has a velocity component in the direction of the central axis J of the annular container 1 1 2 from the open end 26 to the closed end 110, and It forms a stream 28 with a velocity component that turns in the direction.
- the fuel 23 is directed toward the air inflow portion 20 (inflow passage), in the direction of the central axis J in the direction of the velocity component from the closed end 110 to the open end 26 and radially outward. Injected with velocity component.
- the cross-section changing portion 1 0 0 of the outer cylindrical portion 1 1 3 of the annular container 1 1 2 is drawn perpendicular to the axial direction of the annular container 1 1 2, but the angle is arbitrary. .
- the opening ratio, shape and pitch of the air inflow portion 20 can be arbitrarily set.
- a structure for deflecting the flow of the combustion air 22 flowing in at the air inflow portion 20 may be provided.
- reference numeral 1 15 indicates the inner cylinder of the annular container 1 12
- reference numeral 1 1 0 indicates the closed end of the annular container 1 12.
- annular container 1 1 2 in the second embodiment of FIGS. 7 and 8 is changed into the following annular container 2 1 2 according to the manufacturing requirements.
- the annular vessel 2 1 2 is a cross-sectional change portion (stepped portion), and extends the inner peripheral side surface (inner cylinder portion) 2 1 5 of the annular vessel 2 1 2 to the downstream side, and the secondary cylinder 2 0 0 A (tubular member) is provided separately.
- the secondary cylinder 20 0 is small enough to be completely received by the outer cylinder 2 1 3 of the annular container 2 1 2. That is, the cross-sectional area of the secondary tube 2100 is smaller than the cross-sectional area of the outer tube portion 2 1 3 of the annular container 2 1 2, and the secondary tube is placed in a virtual cylinder shape that extends the outer tube portion 2 1 3. 2 0 0 is completely included.
- the outer cylindrical portion of the annular container 2 1 2 2 1 3 the open end 2 6 the end 2 1 3 a and the outer peripheral surface of the secondary tube 2 0 0 close to the 2 1 0 side are annular Connected with 2 7 0
- the connection member 2 70 is formed with an air inflow portion 20 (inflow passage).
- the inner cylindrical part 2 15 of the annular container 2 1 2 has a shape extending substantially coaxially with the secondary cylinder 2 200 and toward the open end 2 6 side of the annular container 2 1 2.
- the annular chamber 2 1 2, the secondary cylinder 2 0 0, and the connecting member 2 7 0 constitute a combustion chamber. Easy preparation.
- the air that has flowed into the annular container 2 1 2 from the inflow part 20 travels in the central axis J direction of the annular container 2 1 2 from the open end 26 to the closed end 2 10.
- a flow 28 having a velocity component and swirling in the circumferential direction of the annular vessel 2 1 2 is formed.
- the fuel is directed toward the inflow portion 20 (inflow passage) toward the velocity component and the radial direction outward in the central axis J direction from the closed end portion 2 10 to the open end portion 26. Injected with velocity component.
- auxiliary air inlet 2 7 1 is provided inwardly, and is configured to allow air to flow in the direction of the central axis J of the annular vessel 2 1 2 (indicated by arrow 2 7 2). Yes.
- the air 2 72 flows on the inner wall surface 2 15 a of the inner cylinder portion 2 15, and the inner wall surface 2 15 a of the inner tube portion 2 15 is efficiently cooled.
- the auxiliary air inlet 2 7 1 is indicated by an arrow in FIG.
- This auxiliary air inlet 2 71 can be applied not only to the third embodiment of FIGS. 9 and 10, but also to the first and second embodiments of FIGS. Similarly, in the other embodiments described later in FIG. 11 and later, the configuration in which the air flow 2 71 is injected from the auxiliary air flow inlet 2 71 to cool the inner wall surface 2 15 a is applied. Is possible.
- FIG. 11 and 12 a combustion apparatus according to the fourth embodiment will be described with reference to FIGS. 11 and 12.
- FIG. 11 and 12 the annular container 1 1 2 in the second embodiment shown in FIGS. 7 and 8 is changed to the following annular container 3 1 2 according to the manufacturing requirements.
- the annular container 3 1 2 has a cross-sectional change part (stepped part) 4 0 0, a secondary annular container (annular member) 4 0 2, a first connecting member 2 70, and a second connecting member 4 7
- reference numeral 4 0 4 indicates the inner cylindrical portion of the secondary annular container 4 0
- reference numeral 4 06 indicates the outer cylindrical portion of the secondary annular container 4 0 2
- the outer cylindrical portion 4 06 of the secondary annular container 4 0 2 is completely received by the outer cylindrical portion 2 1 3 of the annular container 3 1 2. Small enough to be accepted.
- the cross-sectional area of the outer cylindrical portion 4 06 of the secondary annular container 40 2 is smaller than the cross-sectional area of the outer cylindrical portion 2 1 3 of the annular container 3 1 2, and the virtual portion obtained by extending the outer cylindrical portion 2 1 3
- the outer cylindrical portion 4 06 of the secondary annular container 40 2 is completely contained in the cylindrical shape.
- the open end 2 of the outer cylinder 2 1 3 of the annular container 3 1 2 2 6 end 2 1 3 a and the closed end 2 1 of the outer cylinder 4 0 6 of the secondary annular container 4 0 2 The outer peripheral surface near the 0 side is connected by an annular first connection member 2 70, and an air inflow portion 20 (inflow channel) is formed in the connection member 2 70.
- the inner cylindrical portion 4 0 4 of the secondary annular container 4 0 2 is located on the extension of the inner cylindrical portion 2 1 5 of the annular container 3 1 2, and the inner cylindrical portion of the secondary annular container 4 0 2 4 0 4 and the inner cylindrical part 2 15 of the annular container 3 1 2 are connected by a second connecting member 4 70.
- the inner cylindrical portion 2 15 of the annular container 3 1 2 and the inner cylindrical portion 4 0 4 of the secondary annular container 4 0 2 are shown to have the same inner diameter.
- the inner diameter dimension of the inner cylindrical portion 2 15 of the annular container 3 12 may be different from the inner diameter dimension of the inner cylindrical portion 40 4 of the secondary annular container 40 2.
- the swirler 16 generally has an air introduction path 56 formed by arranging swirl vanes 54 that deflect the flow between the inner cylinder 50 and the outer cylinder 52. Constitute.
- an air introduction path 56 a that deflects the flow may be opened in the annular member 58 as shown in FIG.
- the shape of the air introduction path 5 6 a at that time is arbitrary.
- the air introduction path 5 6 b divided for each air inflow portion 20 of the connection member 2 70. May be attached to the connection member 2 70.
- the swirler 16 may also serve as a connection member. That is, in the example of FIG. 13, the inner cylinder 50 and the outer cylinder 52 are eliminated, and the secondary cylinder 2 0 0 of the third embodiment (see FIGS. 9 and 10) and the container 2 1 2 ( 9 and FIG. 10) are connected by swirl vanes 5 4, and the secondary annular container 4 0 2 (see FIGS. 11 and 12) of the fourth embodiment and the annular container 3 1 2 And swirl blades 5 4 are connected to each other so that swirl blades 5 4 also serve as connecting members 2 7 0. Yes.
- the annular member 58 can also serve as the connecting member 2 70 (FIGS. 9 to 12).
- the first connecting member 2 70 is drawn perpendicular to the axial direction of the annular container 3 1 2 and the secondary annular container 4 0 2.
- the angle is arbitrary.
- the opening ratio, shape, and pitch of the air inflow portion 20 can be arbitrarily set.
- the swirler 16 is drawn in an axial flow shape, it may be a mixed flow shape in which the combustion air 22 flows from the outer periphery of the swirler 16.
- a structure for deflecting the flow of the air 22 flowing in the air inflow portion 20 in the radial direction may be provided.
- the inflow casing 14 may be a so-called reverse flow type inflow casing 14 b suitable for a centrifugal, a compressor, or a turbine.
- the inflow casing 14 c may be integrated with the annular container 3 12 as shown in FIGS. 17 and 18.
- the inflow casing 14c is a double structure in which the closed end 210 side of the air inflow part 20 of the annular container 3 1 2 or the entire annular container 3 1 2 is surrounded by the inflow casing 14c. Therefore, the fuel nozzle 18 and the ignition device (not shown) can be attached without penetrating the inflow casing 14 c. That is, the structure becomes simple and the cost can be reduced (in that case, it is desirable to insulate the exposed annular container 3 1 2 with a heat insulating material).
- an extension pipe is connected to the air introduction path 5 6 b, for example.
- an inflow pipe in which the extension pipes are joined may be provided to change to the inflow casing 14. The same applies when there are other air introduction paths.
- a plurality of nozzles 18 a are abbreviated as shown in FIGS. 19 and 20. They may be arranged concentrically. Also in this case, the fuel is jetted from the closed end 2 1 0 of the annular container 3 1 2 toward the outlet 2 6 and at an angle radially outward with respect to the central axis of the annular container 3 1 2.
- the same action as that of a single nozzle can be realized as long as it is injected in a conical shape having a relatively small spread angle, or in a fan shape, and toward the inflow portion 20 of the combustion air.
- Multiple nozzles 18 a are effective especially when a single nozzle is difficult to apply in a large combustion device.
- the same structure regarding the swirler, casing, and fuel nozzle described above can be applied to the first to fourth embodiments and all the following embodiments.
- the fuel 2 1 is injected from the fuel nozzle 18 with a grab angle radially outward with respect to the central axis J of the annular vessel 3 1 2 (see Fig. 2 2 A). . That is, the fuel is injected toward the air inflow portion 20 with a velocity component in the central axis J direction from the closed end portion 2 10 to the open end portion 26 and a radially outward component.
- Combustion air 22 in FIG. 2 2 A is the gap formed by the outer cylinder 3 8 of the inflow casing 14 and the outer cylinder 2 1 3 of the annular container 3 1 2 by a blower or a compressor (not shown). 3 6 and flows into the annular container 3 1 2 from an air inflow portion (not shown) formed in the connecting member 2 70 via the swirler 16.
- the fuel air 2 2 b flowing into the annular vessel 3 1 2 goes back in the annular vessel 3 1 2 while turning in the opposite direction to the outlet 2 6 and intersects with one wake 2 3 a at the position 2 5 (Fig.
- the air 2 2 b flowing into the annular container 3 1 2 from the air inflow portion is a velocity component in the direction of the central axis J of the annular container 3 1 2 from the open end portion 2 6 toward the closed end portion 2 10.
- a flow 28 that swirls in the circumferential direction of the annular container 3 1 2 is formed.
- the fuel 2 1 that has passed through the fuel track 2 3 a at position 2 5 has evaporated somewhat, and the particle diameter has been reduced, and has progressed through the air stream.
- the speed of the fuel 21 and the fuel air 2 2 are opposite to each other, so that the fuel 2 1 flows into the combustion air 2 2 b. Get on and ignite to form a flame and burn.
- Combustion air 2 2 b turns into a combustion gas 2 4 b having a high temperature and a low oxygen concentration while further going up while rotating the annular vessel 3 1 2 in the direction opposite to the outlet. Then, as it approaches the closed end 2 1 0 of the annular container 3 1 2, it changes its direction toward the central axis of the annular container 3 1 2, and toward the outlet 2 6 toward the inner cylinder 2 1 5 of the annular container 3 1 2. Change direction and cross fuel track 2 3 b at position 2 7. That is, combustion gas recirculation occurs.
- the fuel wake 2 3 b traversed by the combustion gas 2 4 a may be the same as the fuel wake 2 3 a ⁇ At position 2 7 (see Fig.
- the combustion gas 2 at high temperature and low oxygen concentration 2 4 b pre-evaporates without igniting the fuel.
- the evaporated fuel wakes up with the combustion gas 2 4 b and burns Although the burnt gas 2 4 b is hot, the evaporated fuel is not immediately ignited and premixed to suppress the combustion rate because it has a low oxygen concentration. Then, after a predetermined time has elapsed, it ignites and burns, and the combustion gas 2 4 b becomes a combustion gas 24 having a higher temperature and a lower oxygen concentration and is discharged from the outlet 26.
- the fourth embodiment most of the fuel does not first contact the combustion air 2 2 but first contacts the combustion gas 2 4 b. It is important to be able to achieve ignition and combustion.
- the fuel In the case of gaseous fuel as well, the fuel must be jetted in such a way that it penetrates the air flow and the surrounding part is partially mixed with the air (before the fuel jet loses its momentum) so that it reaches the position 25.
- the combustion air 2 2 b crosses the fuel wake 2 3 a and mixes with the fuel 2 1 while going up the annular vessel 3 1 2 while turning in the opposite direction to the outlet 2 6. However, it becomes a high temperature, low oxygen concentration fuel gas 2 4 b.
- Combustion gas 2 4 b has high temperature but low oxygen concentration, so it suppresses the combustion rate. Therefore, it does not ignite immediately and becomes premixed. After a predetermined time, it ignites and burns.
- FIGS. 2 1, 2 2 A and 2 2 B The flow in the combustion apparatus in the embodiment of the present invention is as shown in FIG. 2 2 B in the cross section passing through the central axis of the annular vessel 3 1 2. Shown in It is supposed to be.
- the combustion air 2 2 flowing into the annular vessel 3 1 2 is schematically divided into 2 2 a, 2 2 b, 2 2 c, 2 2 d, and 2 2 e according to the position. Most of the combustion air 2 2 flowing into the annular vessel 3 1 2 2 2 b, 2 2 c, 2 2 d collides with the fuel wake and becomes combustion gas 2 4 b, 2 4 c, 2 4 d, respectively, Go up deep inside vessel 3 1 2 and cross fuel track 2 3 again.
- FIGS. 21, 22 A and 22 B Another essential action in the embodiment of the present invention illustrated in FIGS. 21, 22 A and 22 B is that the combustion gas crosses evenly along the fuel wake.
- the combustion apparatus according to the embodiment of the present invention as shown in FIG. 2 2 A, the second annular flame 60 from the inner cylindrical portion 2 15 of the annular container 3 1 2 and the outer Two first annular flames 6 2, which are close to the cylindrical part 2 1 3 but are separated from the inner wall of the outer cylinder 2 1 3 of the annular container 3 1 2, are formed.
- the residence time in the annular container 3 1 2 is long, and it is well mixed and uniform in the circumferential direction.
- 2 2 and fuel 2 1 are facing each other, and high-temperature combustion gas is disturbed from the second annular flame 60 to the combustion air before it meets the fuel.
- the increase in the temperature of combustion air and the decrease in oxygen concentration due to the supply by flow diffusion promotes evaporation while suppressing the ignition of fuel, thus increasing the stability of the flame.
- the second annular flame 60 is converted into the first annular flame 62 by the combustion gas 2 4 a, 2 4 b, 2 4 c, 2 4 d of the first annular flame 6 2 crossing the fuel wake 2 3.
- the fuel air 2 2 a flowing in from the position closest to the inner peripheral surface of the outer cylinder 2 1 3 of the annular vessel 3 1 2 is (fuel 2 1 or) the fuel wake 2 3 and It goes up deepest in the annular vessel 3 1 2 without colliding, and as it goes up, it mixes with the combustion gas 2 4 b to become combustion gas 2 4 a. Since the combustion gas 2 4 a has a relatively low temperature, the inner surface of the annular vessel 3 1 2 is protected from overheating.
- the combustion air 2 2 e that has flowed into the annular container 3 1 2 at the position farthest from the inner surface of the outer cylindrical part 2 1 3 of the annular container 3 1 2 is on the outlet 2 6 side from the arrival point of the fuel 21 Inverted and flows in the direction of outlet 26, so it does not become combustion gas, but gradually becomes the main flame from the part far from the inner peripheral surface 4 0 6 a of the outer cylinder 4 0 6 of the secondary annular container 4 0 2 (second (Annular flame) Mix with 60 combustion gases.
- the portion closest to the inner peripheral surface 4 0 6 a of the outer cylinder 4 0 6 of the secondary annular vessel 4 0 2 is relatively low temperature, and the main flame 6 0
- the inner peripheral surface 4 0 6 a of the outer cylinder 4 0 6 of the secondary annular container 4 0 2 is protected from the high temperature of On the inner peripheral side 2 15 of the annular container 3 1 2 and the inner peripheral side (inner cylinder 40 4) of the secondary annular container 40 2, high-temperature combustion gas passes in the vicinity.
- air holes 30 are provided on the inner circumferential surface of the annular container 3 1 2 and the inner circumferential surface 4 0 4 a of the inner cylinder 4 0 4 of the secondary annular container 4 0 2 for cooling. Air may be jetted out or cooled along a wall surface.
- the inner circumference of the annular container 3 1 2 and the inner circumference 4 0 4 of the inner ring 4 0 4 of the secondary annular container 4 0 4 When a is made of a heat-resistant material, the inner circumference of the annular container 3 1 2
- the air inflow hole 30 may not be provided on the inner peripheral surface 40 04 a of the side and secondary annular container 40 2.
- the combustion chamber is divided into an annular vessel 3 1 2 and a downstream structure (secondary annular vessel), so that the annular vessel 3 1 2 can be easily taken out.
- the disassembly, replacement, and maintenance of the combustion device is easier and the maintainability is improved.
- the closed end 5 1 0 of the annular container is formed of a free circular arc having a curvature that does not have a cross-sectional curve L r unlike the first to fourth embodiments described above.
- This is an embodiment having an annular container 51 2 formed of a curved surface.
- the annular container 5 12 is mainly composed of a curved closed end 5 10, and the extremely short inner cylinder 5 1 5 of the annular container 5 1 2
- a secondary annular container 40 2 is connected to the outer cylindrical portion 5 1 3 via the connection member 2 70 and the outer cylindrical portion 5 13 3 via the connection member 2 70.
- the same operation as described in the fourth embodiment can be realized.
- the annular container 5 1 2 is made of a heat-resistant material such as ceramics, especially in applications where the combustion temperature is high due to the closed end portion 5 10 of the annular container 5 1 2 being curved, Manufacture is easier and costs can be reduced.
- the combustion chamber is divided into an annular vessel 5 1 2 and a downstream structure (secondary annular vessel 4 0 2), the annular vessel 5 1 2 can be easily removed, and compared with the conventional combustion chamber Equipment is easy to disassemble, replace, and maintain, improving maintenance.
- the annular container 5 12 configured by a partially curved surface of the fifth embodiment may be applied to the first to third embodiments.
- the combustion apparatus shown in Fig. 24 has an auxiliary air hole formed in the outer cylindrical portion of the annular container in comparison with the applied type of the fourth embodiment of Figs. 11 and 12, i.e., the fourth embodiment. It is an embodiment. That is, in FIG. 24, the combustion device of the sixth embodiment is configured such that a plurality of auxiliary air is supplied to the outer cylindrical portion 6 13 near the closed end portion 6 10 of the annular vessel 61 2. This is an embodiment in which 6 1 9 is formed.
- the combustion air 2 2 d flowing in from the plurality of auxiliary air holes 6 1 9 formed in the outer cylinder portion 6 1 3 near the closed end portion 6 1 0 in this manner is an annular container 6 1 in the centripetal direction. 2 Since it flows into the inside, the surrounding combustion gas 2 4 b is attracted and the outer periphery of the annular container 6 1 2 as a whole near the closed end 6 1 0 of the container 6 1 2 (outer cylinder part) 6 1 3 Inner circumference (inner cylinder) 6 1 5 To promote flow in the direction toward 5.
- auxiliary air holes 6 19 of the sixth embodiment may be applied to the first embodiment, the second embodiment, and the third embodiment.
- FIG. 25 is different from the fourth embodiment (see FIGS. 11 and 12) in that a guide vane 11 having a rectifying structure is provided inside the closed end 2 10 of the annular container 3 1 2.
- This is an embodiment provided with a plurality.
- a guide vane 1 1 ⁇ By providing such a guide vane 1 1 ⁇ , the same effect as that of the auxiliary air hole 6 1 9 in the sixth embodiment (see Fig. 24) can be obtained.
- the This is substantially the same as the fourth embodiment except that a plurality of guide vanes 1 1 having a rectifying structure are provided inside the closed end 2 10 of the annular container 3 1 2.
- the guide vane 11 can also be applied to the first to third embodiments and the sixth embodiment described above.
- the outer cylinder 2 1 3 This is an embodiment realized by providing a plurality of guide vanes 1 1 a which are rectifying structures in a region near the closed end 2 10 on the inner wall of the 2. Substantially the same as the fourth embodiment except that a plurality of guide vanes 1 1 a having a rectifying structure are provided on the inner wall of the outer cylindrical portion 2 1 3 on the side close to the closed end 2 1 0 of the annular container 3 1 2 The same as above.
- the guide van 11a can also be applied to the first to third embodiments and the sixth embodiment described above.
- the rectifying structure shown in the seventh embodiment and the eighth embodiment can be provided.
- the combustion apparatus shown in FIG. 27 is obtained by applying the same guide vane as that in the seventh embodiment and the eighth embodiment to the fifth embodiment shown in FIG. That is, the guide vane 1 lb is formed along the inside of the curved surface of the closed end portion 5 10 consisting of the curved surface of the annular container 5 1 2 to the top of the substantially closed end portion 5 1 0 in the illustrated embodiment. ing.
- the guide vanes 1 1, lla, 1 lb shown in the seventh to ninth embodiments described above are swiveled in the vicinity of the closed ends 2 1 0, 5 1 0 of the annular containers 2 1 2, 5 1 2
- the flow is suppressed and the flow is arranged in the radial direction.
- the combustion gas 2 4 a (not shown) swirling in the same manner as in the fifth embodiment is converted into an annular vessel 2 1 2, 5 1 2 closed end 2 1 0, 5 1 0 can be guided toward the inner periphery, and smoothly recirculated toward the fuel wake 2 3.
- the 10th embodiment in FIG. 28 is an embodiment in which the guide vane 11 that is the rectifying structure in the seventh embodiment in FIG. 25 is optimized. That is, in the guide vane 11 1 c of the 10th embodiment, the shape of the guide vane 11 of the seventh embodiment in FIG. 25 is the same as that of the inner cylinder 2 1 of the annular vessel 3 1 2. It is wound in a spiral shape on the 5th side and curved in an arc shape so that it can easily flow to the center.
- the guide vane 1 1 c can also be applied to the first to third embodiments and the sixth embodiment. In addition It can also be used with the guide vanes 1 1 a of the eight embodiments.
- the first embodiment in FIG. 29 is an embodiment in which the guide vane 11a which is the rectifying structure in the eighth embodiment in FIG. 26 is optimized. That is, in the guide vane 11 1 d of the first embodiment, the shape of the guide vane 1 1 a in the eighth embodiment of FIG. 26 is formed on the inner wall of the outer cylindrical portion 3 1 2 of the annular container 2 1 2. The upper end of the guide vane 11 1 d is deformed so as to rise in the vertical direction in the illustrated example.
- the guide vane 1 I d can also be applied to the first to third embodiments and the sixth embodiment. Further, it may be used together with the guide vane 11 of the seventh embodiment, or may be used with the guide vane 11c shown in the 10th embodiment.
- the first 2nd embodiment of FIG. 30 is an embodiment in which the guide vane 1 1 b which is the rectifying structure in the ninth embodiment of FIG. 27 is optimized. That is, in the guide vane 11 1 e of the 12th embodiment, the shape of the guide vane 11 1 b of the 9th embodiment of FIG. The upper end of the guide vane 11 1 e is deformed so as to rise in the vertical direction in the illustrated example.
- the rectifying structure (guide vane) 1 1 c, 1 1 d, 1 1 e is a flow of the swirling combustion gas 2 4 a (not shown). It acts to actively and more smoothly deflect the flow in the centripetal direction, and this makes the combustion gas 2 4 a swirling and flowing more smoothly into the annular vessel 2 1 2, 5 1 2 Close the closed end 2 1 0, 5 1 0 near the inner circumference (inner cylinder) 2 1 5, 5 1 2 of the annular container 2 1 5, 5 1 5 lead to the fuel wake 2 3 recirculate be able to.
- the rectifying structure may be configured by adding an object such as a plate shape or a trapezoidal shape to the annular containers 2 1 2 and 5 12, or a groove shape on the inner surface of the annular containers 2 1 2 and 5 12 You may comprise the shape of.
- the combustion apparatus has a slightly closed end of the inflow portion 20 of the combustion air 2 2 on the inner surface of the outer tube portion 7 1 3 of the annular container 7 1 2 having the inner tube portion 7 15 and the outer tube portion 7 13.
- Fuel injected from auxiliary fuel nozzle 7 0 2 is injected from main fuel nozzle 1 8
- the fuel may be the same or different. Even if the combustion device is large or the injection pressure is limited by gaseous fuel, it is difficult to make the fuel 2 1 reach the inflow portion 2 0 (not shown) of the combustion air 2 2.
- combustion with reduced generation of thermal NOX can be realized by combustion gas recirculation as in the second embodiment.
- liquid fuel from the fuel nozzle 18 and gaseous fuel from the auxiliary fuel nozzle 702 liquid / gas mixed combustion can be realized with a simple configuration. Further, the turndown performance can be further improved by the auxiliary fuel nozzle 70 2.
- the fuel nozzle 18 will produce a low calorific value.
- the auxiliary fuel nozzle 70 2 is provided with a plurality of nozzles on the inner surface of the outer cylindrical portion 7 1 3 of the annular container 7 1 2.
- a single ring with a large number of injection holes may be arranged on the inner surface of the outer flange portion 7 1 3 of the annular container 7 1 2.
- the auxiliary fuel nozzle 70 2 of the first 3rd embodiment is also applicable to the first to third embodiments and the fifth to 12th embodiments.
- the above-described embodiment (first embodiment to first to third embodiment) is regarded as a primary combustion region, and further downstream of the outlet 26. What is necessary is just to provide an air inflow part.
- technical measures to add air downstream of the primary combustion region so that the combustion efficiency is not reduced and unburned components are not discharged or NO x generation is not increased. Is well known. Therefore, when the present invention is applied to a gas turbine, it can be realized by applying a known technique to the embodiments described so far, so that many application embodiments can be made while maintaining the essence of the present invention. It becomes. Although not all of them can be described, some examples are described below.
- FIGS. 32 and 33 A gas turbine combustion apparatus according to the first embodiment will be described with reference to FIGS.
- the first embodiment of FIGS. 32 and 33 is an embodiment in which the combustion apparatus of the fourth embodiment is applied to a gas evening bin combustion apparatus.
- the gas evening bin combustion apparatus is the fourth embodiment.
- the secondary annular container is extended to the outlet side and replaced with a secondary annular container 8 0 2 in which air holes 8 1 4 and 8 1 4 b are opened at appropriate positions of the secondary annular container 8 0 2 It has been.
- the secondary annular container 80 2 has a downstream expanded section (8 0 8) force. This can be arbitrarily set.
- the secondary annular container 80 2 is integrally formed up to the outlet 26, but may be divided according to manufacturing requirements.
- Secondary and dilution air 8 1 8 flows into the secondary annular vessel 8 0 2 through air holes 8 1 4 and 8 1 4 b formed in a plurality of stages.
- the combustion gas recirculation occurs evenly along the fuel wake 2 3, so that it is burned with the combustion gas of high temperature and low oxygen concentration.
- both gaseous and liquid fuels (with the theoretical mixing ratio locally as in normal diffusion combustion) (This is not a combustion where there are locally high temperatures.)
- the combustion has a uniform, low maximum flame temperature, and a low average flame temperature due to the heat capacity of the inert gas in the combustion gas. It is suppressed.
- the inner wall surface of the outer cylinder 8 0 6 up to the secondary air hole 8 1 4 on the most upstream side of the secondary annular vessel 8 0 2 is cooled by a part of the primary air 8 1 7 as in the fourth embodiment. .
- a cooling air hole 8 14 b may be arbitrarily formed in the wall surface of the outer cylinder 8 06 of the secondary annular container 80 2.
- High-temperature gas passes through the inner surfaces of the inner peripheral side 2 1 5 of the annular container 3 1 2 and the inner cylinder 8 0 4 of the secondary annular container 8 0 2. Therefore, if necessary, air holes are provided in the inner peripheral side 2 1 5 of the annular container 3 1 2 and the inner cylinder 8 0 4 of the secondary annular container 80 2, and cooling air is jetted. Or you may cool by ejecting along a wall surface.
- the inner cylinder 8 0 4 of the annular container 3 1 2 is made of a heat-resistant material, the inner circumference side 3 1 2 and 2 of the annular container 2 1 2 The inner cylinder 8 04 of the next annular container 8 0 2 does not have to be provided with an air inflow hole.
- the stability of the primary combustion region 8 1 6 is high, the flow rate of the primary air 8 1 7 relative to the total air flow rate can be increased to lower the combustion temperature as a leaner primary combustion, Furthermore, the generation of thermal NOX can be suppressed.
- the combustion chamber is divided into an annular vessel 3 1 2 and a downstream structure (secondary annular vessel 8 0 2), the annular vessel 3 1 2 can be easily taken out, and combustion is performed in comparison with the prior art. Equipment is easy to disassemble, replace, and maintain, improving maintainability.
- the first embodiment to the third embodiment, and the sixth embodiment to the first embodiment are applied to the gas evening bin combustion apparatus. Actions and effects can be realized in the same way.
- the first embodiment to the third embodiment The functions and effects of the embodiment, and the sixth embodiment to the first to third embodiments are exhibited as they are.
- the 15th embodiment of FIG. 34 is an embodiment in which the combustion apparatus of the fifth embodiment described above is applied to a gas turbine combustion apparatus.
- the gas evening bottle combustion apparatus has a secondary annular vessel extended to the outlet 26 side, and an air hole 8 at an appropriate position of the secondary annular vessel 8 0 2. 1 4 and 8 1 4 b are replaced by the opened secondary annular container 8 0 2.
- the secondary annular container 80 2 has an expanded cross section downstream, but this can be arbitrarily set.
- the secondary annular container 80 2 is integrally formed up to the outlet 26, but may be divided according to manufacturing requirements. Secondary and dilution air 8 1 8 flows into the secondary annular vessel 8 0 2 through air holes 8 1 4 and 8 1 4 b formed in a plurality of stages.
- combustion gas recirculation occurs evenly along the fuel wake 2 3, so that combustion is performed with combustion gas of high temperature and low oxygen concentration.
- gas combustion and liquid fuel and the theoretical mixing ratio locally (like normal diffusion combustion) (This is not a combustion where there are locally high temperatures.) Uniform, low maximum flame temperature, and low average flame temperature due to the heat capacity of inert gas in the combustion gas. Is suppressed.
- the F3 ⁇ 4 wall of the outer cylinder 8 0 6 up to the secondary air hole 8 1 4 on the most upstream side of the secondary annular vessel 8 0 2 is cooled by a part of the primary air 8 1 7 as in the fifth embodiment. .
- a cooling air hole 8 14 b may be arbitrarily formed in the wall surface of the outer cylinder 8 06 of the secondary annular container 80 2.
- High-temperature combustion gas passes in the vicinity of the inner peripheral side of the annular vessel 5 1 2 and the inner surface 8 0 4 of the secondary annular vessel 8 0 2. Therefore, if necessary, air holes 8 14 are provided on the inner peripheral surface of the annular vessel 51 2 and the inner cylinder 80 4 inner surface of the secondary annular vessel 80 2 so that the cooling air is jetted. Alternatively, it may be cooled by spraying on the wall surface.
- the inner cylinder 8 0 4 of the annular container 5 1 2 and the secondary annular container 8 0 2 is made of a heat-resistant material, the inner cylinder 8 0 4 of the annular container 5 1 2 and the secondary annular container 8 0 2
- the air inflow hole may not be provided.
- the combustion chamber is configured such that the closed end portion 5 10 of the annular vessel 5 1 2 is formed in a dome shape with a curved surface.
- the annular container 5 12 is formed of a heat resistant material such as ceramic in an application where the temperature is high, the manufacturing becomes easier and the cost can be reduced.
- annular vessel 5 1 2 can be easily taken out, compared with the prior art.
- Combustion equipment can be easily disassembled, replaced, and maintained, improving maintainability.
- FIG. 35 is an application example of the 14th embodiment described above. That is, in the combustion apparatus of the 14th embodiment of FIG. 31, the secondary air swirler 8 15 is used instead of the air hole in the mixing portion of the secondary air 8 18. However, an air hole 8 1 4 force is provided in the inner cylinder 80 4 of the secondary annular container 80 2, and an air hole 8 14 b is provided in the outer cylinder 8 0 6.
- air is swirled and supplied to the combustion chamber. Examples of supplying air without swirling are shown in FIGS. 36 and 37.
- air is supplied so as to have a velocity component in the direction opposite to the fuel flow in the direction of the combustion chamber central axis at the air inflow portion 20.
- This is a configuration that uses only one introduction path 17.
- the airflow wake and the fuel flow wake intersect twice without making the airflow wake and fuel wake the same, and the airflow wake is the first fuel flow wake. Intersects with the area near the tip of the fuel wake, and the airflow wake intersects with the wake of the fuel flow for the second time in the state of the flow from the root of the fuel flow wake to the vicinity of the tip. It is possible to form.
- FIGS. 36 and 37 show the configuration without the swirler in the second actual embodiment
- the configurations without the swirler are similarly applied to the first and third to 16th embodiments described above.
- the configuration shown in the first to first sixteenth embodiments using the swirler the air flow becomes a swirl flow swirling along the inner wall surface of the combustion apparatus, and the centrifugal force acts, so the air flow is Before changing the direction of the flow toward the outlet of the combustor, it is possible to move up along the inner surface of the outer peripheral surface of the combustor more smoothly and over a long distance.
- the configuration shown in the first to first sixteenth embodiments is as shown in FIG. Compared to the configuration representatively shown in Fig. 6 and Fig. 37, the above flow state can be formed more efficiently.
- the gas evening bin generator shown in FIG. 38 includes a gas evening bin device 90 and a generator 90.
- the gas evening bottle device 900 has a turbine 90 4 that rotates with combustion gas, a combustor 90 6 that burns a mixture of fuel and air, and a fuel supply amount to the combustor 9 0 6.
- the combustion apparatus of the above-described embodiment is used as a fuel burner 9 06 in FIG.
- the turbine 9 0 4 has a plurality of rotating blades (not shown) that rotate in response to the combustion gas 9 2 6, and is connected to the air compressor 9 1 0 via the rotating shaft 9 1 4, and It is rotatably supported in a casing (not shown).
- the air compressor 9 10 is driven by a turbine 90 4 through a rotating shaft 9 14, and is configured to compress air 9 16 supplied into the air compressor 9 10.
- This pneumatic compressor 9 1 0 is connected to the combustor 9 0 6 via the pipe 9 1 8, and the air 9 2 0 compressed by the air compressor 9 1 0 is connected via the pipe 9 1 8 It is configured to be supplied to the combustor 90 6.
- the fuel control valve 9 0 8 is arranged on the upstream side of the combustor 9 0 6, and the fuel 9 2 2 supplied from a fuel supply source (not shown) passes through the fuel control valve 9 0 8 and then combustor 9 0. Supplied to 6.
- the fuel control valve 90 8 is configured so that the opening of the valve is variable, and this opening is operated by the control device 9 1 2 via the control signal line 9 2 4, so that the combustor 9 0 6 The supply amount of fuel 9 2 2 is adjusted.
- the fuel 9 2 2 and the compressed air 9 2 0 supplied to the combustor 90 6 form an air-fuel mixture in the combustor 9 0 6, and the air-fuel mixture burns in the combustor 9 0 6, thereby High-pressure combustion gas 9 2 6 is generated. Then, the generated high-temperature / high-pressure combustion gas 9 2 6 is supplied to the turpin 90 4, so that the turbine 90 4 rotates at a high speed.
- the turbine 9 0 4 is directly connected to the generator 9 0 2 through the rotating shaft 9 1 4, and the generator 9 0 2 is rotationally driven by the rotation of the turbine 9 0 4 to generate power.
- a rotating speed detector 9 2 8 for detecting the rotating speed of the evening bottle 9 0 4 is installed in the vicinity of the generator 90 2 in FIG. 3 8. . 'Rotation speed Information on the rotational speed detected by the detector 9 2 8 is transmitted to the control device 9 1 2 via the signal line 9 30.
- the configuration and operational effects of the combustor 90 6 are the same as the configuration and operational effects of the combustion apparatus in each of the above-described embodiments.
- the combustion gas recirculation is actively controlled and generated with a simple structure, thereby providing high stability and combustion.
- the effect of gas recirculation can be maximized.
- combustion gas recirculation action can be maximized with high stability, it can be burned with combustion gas of high temperature and low oxygen concentration to have stable evaporation behavior in the case of liquid fuel.
- Evaporative combustion, premixed combustion regardless of gaseous fuel and liquid fuel, slow combustion, uniform and low maximum flame temperature combustion, low average flame temperature combustion due to heat capacity of inert gas in combustion gas Therefore, it is possible to provide a combustion apparatus that can suppress the generation of thermal NOX, which was difficult with the conventional technology.
- the inner wall of the combustion apparatus is suitably cooled by a low-temperature air flow, it is possible to provide a highly durable combustion apparatus.
- auxiliary fuel nozzle When an auxiliary fuel nozzle is provided, it is possible to provide a combustion device that can suppress the generation of thermal NOx even in the combustion of gaseous fuel / liquid fuel, combustion of low heat generation fuel, and waste liquid.
- combustion gas recirculation Because it is possible to maximize the effect of combustion gas recirculation with high stability, it can be burned with combustion gas at high temperature and low oxygen concentration.
- gas fuel Pre-evaporation combustion with stable evaporation behavior, gas fuel ⁇ Premixed combustion regardless of liquid fuel, slow combustion, uniform, low maximum flame temperature combustion, inert gas in the combustion gas Combustion with low average flame temperature due to heat capacity, and the ability to further reduce the combustion temperature by being able to design the primary combustion region to be leaner, which can suppress the generation of thermal NOX Can be provided.
- the inner wall of the combustion device is preferably cooled by a low-temperature air flow, A highly reliable gas turbine combustion apparatus can be provided.
- the cross-sectional shape of the containers 12, 112, 212, and 312 is an annular shape (annular), but can be changed to any shape. Further, as long as a swirl flow is formed as a whole in the container, it may be an annular shape constituted by two polygons completely including one) ⁇ the other. Alternatively, the cross-sectional shapes of the containers 12, 1 1 2, 2 1 2, 3 1 2 may be changed in the axial direction other than the position where the air inflow portion 20 is formed (axial direction).
- an arbitrary air inlet may be provided on the inner peripheral side of the annular containers 12, 1 1 2, 212, 312 and the secondary annular container 402. This is mainly for cooling the walls of the annular containers 12, 1 1 2, 212, 31 2 and the secondary annular container 402.
- the air inflow hole may not be provided. Further, downstream of the air inflow portion 20, combustion air necessary for combustion may be supplied from these air holes.
- the shape of the inflow casing 14 in the first to fourth embodiments can be arbitrarily deflected.
- the inflow casing that is structured to flow in from the axially closed end portions 10, 1 10, and 2 10 has a scroll shape that flows in from the circumferential direction, It is good also as a shape which flows into the reverse direction from the circumference
- a so-called reverse flow inflow casing 14a suitable for a centrifugal compressor and a turbine may be used.
- the present invention can be suitably used for a combustion apparatus that flows combustion air and fuel into a combustion chamber and mixes and burns the combustion air and fuel.
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Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/588,212 US20080193886A1 (en) | 2004-02-10 | 2005-02-09 | Combustion Apparatus |
EP05710271A EP1731833A1 (en) | 2004-02-10 | 2005-02-09 | Combustion apparatus |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2004032941 | 2004-02-10 | ||
JP2004-032941 | 2004-02-10 |
Publications (1)
Publication Number | Publication Date |
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WO2005075887A1 true WO2005075887A1 (ja) | 2005-08-18 |
Family
ID=34836111
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2005/002371 WO2005075887A1 (ja) | 2004-02-10 | 2005-02-09 | 燃焼装置 |
Country Status (4)
Country | Link |
---|---|
US (1) | US20080193886A1 (ja) |
EP (1) | EP1731833A1 (ja) |
CN (1) | CN1918432A (ja) |
WO (1) | WO2005075887A1 (ja) |
Families Citing this family (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1985920B1 (en) * | 2007-04-26 | 2019-04-10 | Mitsubishi Hitachi Power Systems, Ltd. | Combustor and a fuel suppy method for the combustor |
CN103334833B (zh) | 2007-11-12 | 2019-04-05 | 格塔斯热力学驱动系统有限责任公司 | 轴向活塞发动机以及用于操作轴向活塞发动机的方法 |
JP2010230257A (ja) * | 2009-03-27 | 2010-10-14 | Dainichi Co Ltd | 燃焼装置 |
US8453461B2 (en) | 2011-08-25 | 2013-06-04 | General Electric Company | Power plant and method of operation |
US8266913B2 (en) | 2011-08-25 | 2012-09-18 | General Electric Company | Power plant and method of use |
US8453462B2 (en) | 2011-08-25 | 2013-06-04 | General Electric Company | Method of operating a stoichiometric exhaust gas recirculation power plant |
US8205455B2 (en) | 2011-08-25 | 2012-06-26 | General Electric Company | Power plant and method of operation |
US8245492B2 (en) | 2011-08-25 | 2012-08-21 | General Electric Company | Power plant and method of operation |
US9127598B2 (en) | 2011-08-25 | 2015-09-08 | General Electric Company | Control method for stoichiometric exhaust gas recirculation power plant |
US8713947B2 (en) | 2011-08-25 | 2014-05-06 | General Electric Company | Power plant with gas separation system |
US8347600B2 (en) | 2011-08-25 | 2013-01-08 | General Electric Company | Power plant and method of operation |
US8245493B2 (en) | 2011-08-25 | 2012-08-21 | General Electric Company | Power plant and control method |
US8266883B2 (en) | 2011-08-25 | 2012-09-18 | General Electric Company | Power plant start-up method and method of venting the power plant |
JP5584260B2 (ja) * | 2012-08-08 | 2014-09-03 | 日野自動車株式会社 | 排気浄化装置用バーナー |
DE102012217263B4 (de) * | 2012-09-25 | 2023-02-02 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Drallbrenner und Verfahren zum Betrieb eines Drallbrenners |
WO2016046074A1 (en) | 2014-09-26 | 2016-03-31 | Innecs B.V. | Burner |
CN104764043B (zh) * | 2015-03-31 | 2022-10-21 | 中国联合重型燃气轮机技术有限公司 | 一种燃气轮机燃烧室冷却气稳焰装置 |
CN104764042B (zh) * | 2015-03-31 | 2022-10-21 | 中国联合重型燃气轮机技术有限公司 | 一种燃烧室冷却气稳焰装置 |
CN106287706A (zh) * | 2016-08-31 | 2017-01-04 | 林宇震 | 气态燃料掺混器 |
WO2018075854A1 (en) * | 2016-10-21 | 2018-04-26 | Fgc Plasma Solutions | Apparatus and method for using plasma to assist with the combustion of fuel |
US11506384B2 (en) * | 2019-02-22 | 2022-11-22 | Dyc Turbines | Free-vortex combustor |
RU2749472C1 (ru) * | 2020-07-14 | 2021-06-11 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева - КАИ" (КНИТУ-КАИ) | Регулируемая кольцевая камера сгорания |
CN114636152A (zh) * | 2020-12-15 | 2022-06-17 | 杭州鸿和能源环境科技有限公司 | 一种多级内燃式低氮燃烧器 |
CN112902227A (zh) * | 2021-03-04 | 2021-06-04 | 西北工业大学 | 微型发动机燃烧室多通道式蒸发管 |
CN115143490B (zh) * | 2022-06-15 | 2023-08-01 | 南京航空航天大学 | 一种周向交错对冲射流与全环大尺度旋流耦合的燃烧室 |
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- 2005-02-09 EP EP05710271A patent/EP1731833A1/en not_active Withdrawn
- 2005-02-09 US US10/588,212 patent/US20080193886A1/en not_active Abandoned
- 2005-02-09 WO PCT/JP2005/002371 patent/WO2005075887A1/ja active Application Filing
- 2005-02-09 CN CNA2005800045641A patent/CN1918432A/zh active Pending
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Also Published As
Publication number | Publication date |
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CN1918432A (zh) | 2007-02-21 |
US20080193886A1 (en) | 2008-08-14 |
EP1731833A1 (en) | 2006-12-13 |
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