WO2019187559A1 - 燃焼器及びそれを備えるガスタービン - Google Patents

燃焼器及びそれを備えるガスタービン Download PDF

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Publication number
WO2019187559A1
WO2019187559A1 PCT/JP2019/002217 JP2019002217W WO2019187559A1 WO 2019187559 A1 WO2019187559 A1 WO 2019187559A1 JP 2019002217 W JP2019002217 W JP 2019002217W WO 2019187559 A1 WO2019187559 A1 WO 2019187559A1
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WO
WIPO (PCT)
Prior art keywords
fuel
combustor
mixing
air
fuel nozzle
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2019/002217
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
勝義 多田
斉藤　圭司郎
谷村　聡
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Power Ltd
Original Assignee
Mitsubishi Hitachi Power Systems Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mitsubishi Hitachi Power Systems Ltd filed Critical Mitsubishi Hitachi Power Systems Ltd
Priority to US16/980,998 priority Critical patent/US11371707B2/en
Priority to DE112019000871.4T priority patent/DE112019000871B4/de
Priority to CN201980019938.9A priority patent/CN111936790B/zh
Priority to KR1020207026866A priority patent/KR102396908B1/ko
Publication of WO2019187559A1 publication Critical patent/WO2019187559A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/22—Fuel supply systems
    • F02C7/232—Fuel valves; Draining valves or systems
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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
    • F23R3/10—Air inlet arrangements for primary air

Definitions

  • the present invention relates to a combustor and a gas turbine including the combustor.
  • a combustor for a gas turbine a combustor including a disk member in which a plurality of fuel injection holes for injecting fuel are formed is known.
  • the fuel injection hole is formed by opening in the central axis direction of the disk member, and the fuel injected through the fuel injection hole burns, so that the flame in the central axis direction of the disk member Is supposed to occur.
  • a combustor described in Patent Document 1 As such a combustor, a combustor described in Patent Document 1 is known.
  • a mixing pipe that communicates with the air chamber is connected to the fuel injection hole (see, in particular, FIG. 4).
  • the air supplied from the air chamber and the fuel supplied from the fuel inlet formed in the tube wall of the mixing tube merge (particularly, refer to paragraph 0021). Further, the mixed gas of air and fuel inside the mixing tube is injected from the fuel injection hole and burned in the combustion chamber (see particularly paragraph 0021).
  • the present invention has been made in view of such problems, at least one embodiment of the present invention, while achieving low NO X reduction, a gas turbine with possible sufficiently suppressed combustor and it flashback
  • the purpose is to provide.
  • a combustor includes a casing having an air chamber filled with air, and at least one mixing channel in which an inlet side is connected to the air chamber and an outlet side is connected to the combustion chamber.
  • At least one mixing channel forming member having an inflow port communicating with the air chamber formed on the inlet side of the mixing channel, and the inside of the air chamber
  • At least one fuel nozzle having a fuel injection hole that is located upstream of the inflow port of the mixing flow path forming member and injects fuel toward the downstream side. It is characterized by providing.
  • fuel and air can be sufficiently mixed in the mixing channel. That is, when the air in the air chamber, which is a relatively large space, passes through a relatively narrow inlet, a contracted flow is generated in the mixing channel. Further, fuel is injected from a fuel injection hole located on the upstream side of the inlet, and the injected fuel flows together with air from the inlet. Then, the inflowing fuel and air are sufficiently mixed in the mixing channel by the contraction action generated in the mixing channel. Consequently, to suppress the deviation of the fuel concentration in the mixing channel, it is possible to reduce the NO X reduction. In addition, the air flows upstream from the inlet of the mixing channel and downstream from the fuel injection hole, so that flashback (backfire) due to high fuel concentration in the vicinity of the channel wall can be suppressed.
  • flashback backfire
  • the fuel injection hole is directed toward the inflow port when viewed from the upstream side to the downstream side along the axial direction of the casing. It is comprised so that it may do.
  • the fuel can be easily flowed to the inlet. Thereby, the amount of fuel scattered into the air chamber can be suppressed, and flame control by fuel amount control can be easily performed.
  • the at least one fuel nozzle includes a first fuel nozzle and a second fuel nozzle disposed adjacent to the first fuel nozzle.
  • Each of the fuel injection holes included in the first fuel nozzle and the fuel injection holes included in the second fuel nozzle are arranged in the axial direction of the casing from the upstream side to the downstream side. When viewed from the side, it is configured to be directed to the common inlet.
  • fuel can be injected from the plurality of fuel injection holes to the inlet. For this reason, in the mixed gas flow in the mixing channel, the fuel concentration unevenness in the radial direction and the circumferential direction can be suppressed. As a result, when the mixed gas is burned in the combustion chamber, the occurrence of flame unevenness can be suppressed.
  • the at least one fuel nozzle includes a plurality of fuel nozzles, and each of the fuel injection holes of the fuel nozzle has an axis of the casing.
  • the common inlet is configured to be directed, and is provided at equal intervals in the circumferential direction of the inlet.
  • the casing is formed between the combustion chamber and the air chamber inside the casing. It has a fuel chamber for storing fuel inside.
  • the fuel flow path can be formed so as to avoid the air chamber, and the internal space of the air chamber can be sufficiently secured.
  • the internal space of the air chamber is sufficiently secured, the inflow of air from the air chamber to the inflow port is easily performed uniformly regardless of the position of the mixing flow path forming member. As a result, the deviation of the air inflow amount for each mixing channel can be particularly sufficiently suppressed.
  • the fuel nozzle further includes a perforated plate including a second opening that communicates the air chamber and the mixing channel, and the fuel nozzle is formed in a bottomed cylindrical shape that is closed at one end and opened at the other end. The opening on the other end side is connected to the first opening of the perforated plate.
  • the fuel in the fuel chamber can be supplied to the inlet of the mixing channel through the first opening of the perforated plate with a simple configuration.
  • the fuel nozzle is connected to a fuel supply source, one end side of which is the fuel supply source, and the inflow port It is formed in the bottomed cylinder shape by which the other end side which faces is obstruct
  • the length of each fuel nozzle can be changed for each fuel nozzle.
  • the length of the mixing channel can be changed corresponding to the length of the fuel nozzle.
  • the at least one mixing channel includes a plurality of mixing channels
  • the mixing channel forming member includes the plurality of mixing channels.
  • a plurality of mixing tubes each forming a plurality of mixing tubes spaced from each other.
  • air can be guided to the inlet of the mixing tube through the gap between the mixing tubes.
  • air can be supplied to the mixing pipe from the downstream side, and the above-described contraction action can be further increased.
  • the fuel and air can be mixed more sufficiently in the mixing channel.
  • the at least one mixing channel includes a plurality of mixing channels
  • the mixing channel forming member includes the plurality of mixing channels. It is characterized by comprising a partition aggregate formed by a set of a plurality of partitions partitioning each of them.
  • the problem when a problem occurs in the mixing flow path, the problem can be solved by replacing the entire partition aggregate, so that maintenance can be easily performed. Further, since the mixing channels are partitioned by the partition walls, there is no wasted space and the combustor can be downsized. Furthermore, since the mixing channels are formed densely, fuel can be supplied to more mixing channels through one fuel nozzle. As a result, the number of fuel nozzles can be reduced. Furthermore, mixing close to a jet subjected to a cross wind can be generated, and particularly sufficient mixing is possible.
  • a gas turbine according to at least one embodiment of the present invention is for compressing the combustor according to any one of (1) to (9) above and the air supplied to the combustor.
  • a compressor and a turbine configured to be driven by combustion gas discharged from the combustion chamber of the combustor.
  • an expression indicating that things such as “identical”, “equal”, and “homogeneous” are in an equal state not only represents an exactly equal state, but also has a tolerance or a difference that can provide the same function. It also represents the existing state.
  • expressions representing shapes such as quadrangular shapes and cylindrical shapes represent not only geometrically strict shapes such as quadrangular shapes and cylindrical shapes, but also irregularities and chamfers as long as the same effects can be obtained. A shape including a part or the like is also expressed.
  • the expressions “comprising”, “comprising”, “comprising”, “including”, or “having” one constituent element are not exclusive expressions for excluding the existence of the other constituent elements.
  • FIG. 1 is a schematic configuration diagram showing a gas turbine 100 according to an embodiment of the present invention.
  • a gas turbine 100 according to an embodiment includes a compressor 2 for compressing air as an oxidant supplied to a combustor 4 (that is, generating compressed air), compressed air, and fuel.
  • a turbine 6 configured to be driven by combustion gas discharged from a combustion chamber 124 (to be described later) of the combustor 4.
  • a power generator (not shown) is connected to the turbine 6, and power is generated by the rotational energy of the turbine 6.
  • the combustion gas is generated by burning a mixed gas of fuel and air.
  • the combustor 4 can sufficiently mix fuel and air. Performing Therefore, the gas turbine 100 provided with such a combustor 4, by burning a well mixed gas mixture as described above, while achieving low NO X reduction, stable operation of the gas turbine 100 be able to.
  • Examples of the combusted fuel combusted in the combustor 4 include hydrogen, methane, light oil, heavy oil, jet fuel, natural gas, gasified coal, and the like, and any combination of one or more of these may be used. Can burn.
  • the compressor 2 is provided on the compressor casing 10, the inlet side of the compressor casing 10, and is provided so as to penetrate both the compressor casing 10 and the turbine casing 22.
  • the rotor 8 and various blades disposed in the compressor casing 10 are provided.
  • the various blades are an inlet guide blade 14 provided on the air intake 12 side, a plurality of stationary blades 16 fixed on the compressor casing 10 side, and a rotor so as to be alternately arranged with respect to the stationary blades 16. 8 and a plurality of blades 18 implanted in 8.
  • the air taken in from the air intake 12 passes through the plurality of stationary blades 16 and the plurality of moving blades 18 and is compressed into high-temperature and high-pressure compressed air.
  • the high-temperature and high-pressure compressed air is sent from the compressor 2 to the subsequent combustor 4.
  • the combustor 4 includes a casing 20. Although only one is shown in FIG. 1, a plurality of combustors 4 are annularly arranged around a rotor 8 inside a gas turbine casing (not shown) (which may be configured as a part or all of the casing 20).
  • the combustor 4 is supplied with fuel and compressed air generated by the compressor 2 and combusts the fuel to generate combustion gas that is a working fluid of the turbine 6. Then, the combustion gas is sent from the combustor 4 to the subsequent turbine 6.
  • the turbine 6 includes a turbine casing 22 and various blades arranged in the turbine casing 22.
  • the various blades include a plurality of stationary blades 24 fixed to the turbine casing 22 side, and a plurality of moving blades 26 implanted in the rotor 8 so as to be alternately arranged with respect to the stationary blades 24. .
  • the combustion gas passes through the plurality of moving blades 26 extending from the plurality of stationary blades 24, so that the rotor 8 is rotationally driven.
  • a generator (not shown) connected to the rotor 8 is driven.
  • an exhaust chamber 30 is connected to the downstream side of the turbine casing 22 via an exhaust casing 28.
  • the combustion gas after driving the turbine 6 is discharged to the outside through the exhaust casing 28 and the exhaust chamber 30.
  • FIG. 2 is a cross-sectional view showing the vicinity of the combustor 4.
  • the alternate long and short dash line indicates the axis L of the casing 20.
  • the number of the mixing flow path forming members 131 (mixing pipes) is smaller than that shown in FIG. 3 for convenience of illustration.
  • the combustor 4 includes the casing 20 as described above.
  • a cylindrical member 105 is disposed inside the casing 20, and the cylindrical member 105 is supported and fixed inside the casing 20 by support members 106 disposed at equal intervals on the outer circumferential wall thereof.
  • the support member 106 is provided with an interval in the circumferential direction.
  • an air chamber 121 is formed on the rear side of the tubular member 105 and is filled with air (compressed air) flowing through the air flow path 110 and flowing from the vehicle compartment 40.
  • a first support plate 111, a second support plate 112, and a third support plate 113 are arranged with a space therebetween.
  • a fuel chamber 122 for storing fuel in the mixed gas injected from the mixed gas injection hole 141 is formed. That is, the casing 20 includes a fuel chamber 122 for storing fuel between a combustion chamber 124 formed inside the combustor liner 46 and an air chamber 121 inside the casing 20. The supply of fuel from the fuel chamber 122 to the mixed gas injection hole 141 will be described later.
  • a fuel flow path (not shown) communicating with the fuel port 52 is connected to the fuel chamber 122. Therefore, fuel is supplied to the fuel chamber 122 through the fuel port 52 and the fuel flow path.
  • a fuel flow path can be formed so as to avoid the air chamber 121, and a sufficient internal space of the air chamber 121 can be secured.
  • the fuel flow path communicating with the fuel port 52 passes through the outside of the air chamber 121 and can be connected to the fuel chamber 122 by traversing the air flow path 110 in the middle of the air flow path 110.
  • the support member 106 may also serve as the fuel flow path.
  • the internal space of the air chamber 121 is sufficiently secured, air can easily flow in from the air chamber 121 to the inlet 142 regardless of the position of the mixing flow path forming member 131. As a result, the deviation of the air inflow amount for each mixing channel 134 can be particularly sufficiently suppressed.
  • a cooling air chamber 123 is formed between the second support plate 112 and the third support plate 113.
  • a combustion chamber 124 is formed on the front side of the third support plate 113. Therefore, the third support plate 113 becomes high temperature due to fuel combustion in the combustion chamber 124. Therefore, cooling air for cooling the third support plate 113 is supplied to a cooling air chamber 123 formed on the side opposite to the combustion chamber 124.
  • the cooling air is supplied to the cooling air chamber 123 through a cooling air supply system (not shown). Further, the used cooling air after cooling the third support plate 113 is exhausted to, for example, the combustion chamber 124 through an exhaust passage (not shown).
  • the first support plate 111, the second support plate 112, and the third support plate 113 are all configured in a disc shape so as to fit into the cylindrical member 105 formed in a cylindrical shape.
  • the first support plate 111, the second support plate 112, and the third support plate 113 are disposed so that the axis L passes through the respective center points (not shown) perpendicular to the axis L of the casing 20.
  • the first support plate 111, the second support plate 112, and the third support plate 113 all have through holes (not shown). Then, the mixed flow path forming member 131 is supported by the first support plate 111, the second support plate 112, and the third support plate 113 by inserting the tubular mixed flow path forming member 131 into the through hole.
  • the mixing channel forming member 131 is made of, for example, metal and is configured as a mixing tube formed in a tubular shape. Therefore, one mixing channel 134 is formed in one mixing channel forming member 131. And the combustor 4 is provided with the some mixing flow path formation member 131 (one may be sufficient), and the some mixing flow path 134 is formed. Therefore, the mixing channel forming member 131 is configured as a plurality of mixing tubes that form each of the plurality of mixing channels 134.
  • the plurality of mixing pipes (mixing flow path forming member 131) are provided in the combustor 4 by being spaced apart from each other.
  • the mixing flow path forming member 131 includes a mixing flow path 134 (see FIG. 5) for mixing the fuel and air that flowed therein.
  • the inlet side (rear side) of the mixing channel 134 is connected to the air chamber 121, and the outlet side (front side) is connected to the combustion chamber 124.
  • At least one mixing channel forming member 131 is provided inside the casing 20 along the axis L of the casing 20.
  • An inlet 142 communicating with the air chamber 121 is formed on the inlet side of the mixing channel 134, and fuel and air flow through the inlet 142.
  • the fuel and air that flowed in are sufficiently mixed in the mixing channel 134 to generate a mixed gas.
  • the mixed gas is injected into the combustion chamber 124 through the mixed gas injection hole 141 formed on the outlet side of the mixing channel 134.
  • FIG. 3 is an enlarged perspective view showing the vicinity of the mixed gas injection hole 141 of the combustor 4.
  • the disc-shaped third support plate 113 is disposed in the front side of the cylindrical member 105.
  • the third support plate 113 supports a mixing flow path forming member 131 configured by a mixing tube.
  • at least one mixed gas injection hole 141 is formed on the outlet side of the mixing flow path 134 inside the mixing flow path forming member 131, and the mixed gas injection hole 141 communicates with the combustion chamber 124 (not shown in FIG. 3). To do.
  • the fuel injected from the mixed gas injection hole 141 is ignited by an ignition source (not shown) and burns inside the combustion chamber 124.
  • an air flow path 110 that connects the vehicle compartment 40 (see FIG. 2) and the air chamber 121 (see FIG. 2) is formed inside the casing 20 and outside the cylindrical member 105.
  • a combustor liner 46 (see FIG. 2) is disposed on the front side of the cylindrical member 105 as shown in FIG. Therefore, the compartment 40 and the air flow path 110 and the combustion chamber 124 communicating with the mixed gas injection hole 141 are partitioned by the combustor liner 46.
  • the first support plate 111 is composed of a porous plate that partitions the air chamber 121 and the fuel chamber 122.
  • the perforated plate constituting the first support plate 111 includes a first opening 111a (not shown in FIG. 2; see FIG. 5) that communicates the air chamber 121 and the fuel chamber 122, and the air chamber 121 and the mixing channel 134.
  • the inflow port 142 (2nd opening) which connects is included.
  • the air chamber 121 and the fuel chamber 122 communicate with each other through a nozzle portion injection hole 133 included in a fuel nozzle 132 described below.
  • a metal fuel nozzle 132 is connected to the rear side of the first support plate 111. Therefore, the fuel nozzle 132 is disposed inside the air chamber 121 disposed on the rear side of the first support plate 111. At least one fuel nozzle 132 is provided. The fuel nozzle 132 is located upstream of the inlet 142 of the mixing flow path forming member 131 and has a nozzle portion injection hole 133 (fuel injection hole) that injects fuel toward the downstream side.
  • the fuel nozzle 132 will be described with reference to FIG.
  • FIG. 4 is an enlarged perspective view showing the vicinity of the fuel nozzle 132 of the combustor 4.
  • a part of the fuel nozzle 132 provided in the combustor 4 is extracted and illustrated.
  • a solid line arrow shown in FIG. 4 indicates the flow of fuel injected from the nozzle portion injection hole 133.
  • At least one fuel nozzle 132 is formed as described above, and is formed in a bottomed cylindrical shape with one end side (rear side) closed and the other end side (front side) opened. And the said opening formed in the other end side of the fuel nozzle 132 is connected to the 1st opening 111a (not shown in FIG. 4, please refer FIG. 5) of the perforated plate which comprises the 1st support plate 111. FIG. Therefore, the inside of the fuel nozzle 132 communicates with the fuel chamber 122 described above. By doing in this way, the fuel inside the fuel chamber 122 can be supplied to the inflow port 142 of the mixing channel 134 through the first opening 111a of the porous plate with a simple configuration.
  • a nozzle part injection hole 133 communicating with the air chamber 121 is formed on the side surface of the fuel nozzle 132.
  • the nozzle part injection hole 133 is for injecting the fuel in the fuel chamber 122 to the inlet 142 of the mixing flow path forming member 131 supported by the first support plate 111.
  • the inflow port 142 communicates with an air chamber 121 (not shown in FIG. 4). Therefore, the air that fills the air chamber 121 also reaches the inflow port 142.
  • both fuel and air flow into the mixing channel forming member 131 through the inlet 142, they are mixed in the mixing channel 134 formed in the mixing channel forming member 131 to generate a mixed gas.
  • the generated mixed gas is injected into the combustion chamber 124 from the mixed gas injection hole 141 formed on the downstream side of the mixing flow path 134 and burned.
  • FIG. 5 is a diagram showing the flow of fuel (solid arrow) and air (broken arrow) flowing from the inlet 142.
  • the flow shown inside the fuel nozzle 132 is the air flow passing around the fuel nozzle 132, but for the sake of convenience of illustration, it passes through the inside of the fuel nozzle 132. Show.
  • the fuel flowing in from the inflow port 142 is injected from the nozzle portion injection hole 133 located on the upstream side (rear side) of the inflow port 142.
  • the air flowing in from the inflow port 142 fills the air chamber 121 that is a space in which the inflow port 142 is formed. Accordingly, the air flows into the inflow port 142 from the inside of the air chamber 121 having a much larger space than the inflow port 142. Therefore, air flows into the inlet 142 from various directions around the inlet 142.
  • an air flow linearly directed from the upstream side (rear side) of the nozzle portion injection hole 133 of the fuel nozzle 132 to the inlet 142 is generated, and nozzle portion injection is performed.
  • an air flow that curves from the vertical direction toward the inflow port 142 is also generated. Therefore, air flows into the mixing channel 134 from various directions.
  • a contracted flow is generated in part A in the vicinity of the inlet 142 of the mixing channel 134.
  • the generated contracted flow sufficiently mixes the fuel that flows in as shown by the solid line arrow in FIG. 5 and the air that flows in as shown by the broken line in FIG.
  • FIG. 6 is a view showing the arrangement of the fuel nozzle 132 and the mixing flow path forming member 131. This figure shows a state when viewed from the upstream side to the downstream side (that is, from the rear side to the front side) along the direction of the axis L (see FIG. 2) of the casing 20. However, in FIG. 6, the illustration of the first support plate 111 is omitted for the sake of illustration.
  • the plurality of nozzle portion injection holes 133 formed on the side surface of the fuel nozzle 132 are all configured to be directed to the inlet port 142.
  • the inlet 142 is formed in the air chamber 121 as described above, and the air from the vehicle compartment 40 flows into the air chamber 121. Then, an air flow from the air chamber 121 toward the inflow port 142 is formed. Therefore, when the above-mentioned visual recognition is performed, fuel can be easily flowed to the inflow port 142 by being injected so as to be directed to the inflow port 142. As a result, the amount of fuel scattered into the air chamber 121 can be suppressed, and flame control based on fuel amount control can be easily performed.
  • a plurality of fuel nozzles 132 are arranged around one mixing flow path forming member 131. That is, the fuel nozzle 132 includes a plurality of fuel nozzles 132 (first fuel nozzles) and a fuel nozzle 132 (second fuel nozzle) disposed adjacent to the fuel nozzle 132 (first fuel nozzle).
  • the fuel nozzle 132 is included.
  • each of the nozzle part injection hole 133 which the said arbitrary fuel nozzle 132 (1st fuel nozzle) has, and the nozzle part injection hole 133 which the said adjacent fuel nozzle 132 (2nd fuel nozzle) has are said visual recognition.
  • the common inlet 142 is directed.
  • each of the nozzle portion injection holes 133 in the plurality of fuel nozzles 132 is configured to be directed to the common inlet 142 when the above-described visual recognition is performed.
  • each nozzle part injection hole 133 is provided in the circumferential direction of the one inflow port 142 at equal intervals.
  • four nozzle portion injection holes 133 are arranged at equal intervals in the circumferential direction of one inflow port 142.
  • FIG. 7 is a view showing the arrangement of the fuel nozzle 132 and the mixing flow path forming member 131, and is a view showing an embodiment different from FIG. Similarly to the case shown in FIG. 6, the state shown in FIG. 7 is also viewed from the upstream side to the downstream side (that is, from the rear side to the front side) along the axis L (see FIG. 2) direction of the casing 20. Is shown.
  • the fuel nozzle 132 and the mixing flow path forming member 131 are arranged in a close-packed grid arrangement. That is, around the fuel nozzle 132, six mixing flow path forming members 131 are arranged at equal intervals.
  • the axis lines of the six mixing flow path forming members 131 are positioned in a close-packed lattice pattern around the axis line of one fuel nozzle 132.
  • fuel can be injected from one fuel nozzle 132 to the six mixing flow path forming members 131.
  • the number of fuel nozzles 132 can be smaller than the number of mixing flow path forming members 131.
  • FIG. 8 is a cross-sectional view showing the vicinity of the combustor 4A according to the second embodiment of the present invention.
  • the fuel chamber 122 is formed between the first support plate 111 and the second support plate 112.
  • a fuel nozzle 132 including a nozzle portion injection hole 133 communicating with the fuel chamber 122 is provided on the rear side of the first support plate 111 that partitions the fuel chamber 122.
  • the fuel chamber 122 is not provided, but the fuel nozzle 132 extending from the rear inner wall 20 a of the casing 20 so as to cross the air chamber 121 is provided.
  • the fuel nozzle 132 is connected via a fuel port 52 to a fuel supply source (not shown) that is a supply source of fuel combusted in the combustion chamber 124.
  • One end of the fuel nozzle 132 is connected to the fuel supply source. On the other hand, the other end faces the inlet 142 of the mixing channel forming member 131.
  • the other end side of the fuel nozzle 132 is formed in a closed bottomed cylindrical shape.
  • a nozzle portion injection hole 133 for injecting fuel flowing in from the inflow port 142 is formed on the side surface on the other end side of the fuel nozzle 132.
  • four nozzle portion injection holes 133 are formed at equal intervals in the circumferential direction.
  • each fuel nozzle 132 can be changed for each fuel nozzle 132.
  • the length of the mixing channel 134 can be changed corresponding to the length of the fuel nozzle 132.
  • resonance can be suppressed and combustion vibration of the combustor 4A can be easily suppressed.
  • the rear inner wall 20a of the casing 20 that constitutes the combustor 4A is configured by a curved surface that curves forward along the axis L of the casing 20, unlike the combustor 4 that is configured by a plane.
  • the rear inner wall 20a is configured by a curved surface that protrudes toward the front side (inside the casing 20) in the central direction.
  • the rear inner wall 20a By configuring the rear inner wall 20a in this way, it is possible to suppress the air flowing into the air chamber 121 from the one air flow path 110 disposed above and below from being released to the other air flow path 110 side. As a result, the same amount of air can be poured into each of the inlets 142 from the inlet 142 closest to the air flow path 110 to the inlet 142 arranged in the center. As a result, mixing unevenness can be suppressed in each mixing channel 134.
  • the mixing flow path forming member 131 protrudes into the air chamber 121.
  • a gap is formed between the mixing flow path forming members 131.
  • FIG. 9 is a diagram showing the flow of fuel and air flowing in from the inlet 142 in the combustor 4A according to the second embodiment of the present invention.
  • the fuel nozzle 132 is disposed on the upstream side of the inflow port 142.
  • the fuel nozzle 132 is arranged in the air chamber 121 such that at least a part (all in the example shown in FIG. 9) of the inflow port 142 of the mixing channel forming member 131 is exposed to the air chamber 121.
  • the fuel injection from the nozzle portion injection hole 133 of the fuel nozzle 132 is performed from the upstream side to the downstream side (that is, from the rear side) along the axis L (see FIG. 2) direction of the casing 20 in the same manner as the combustor 4 described above. This is performed so as to be directed toward the inflow port 142 when viewed from the front side. As a result, fuel and air flow from the inlet 142 in the same manner as described in the combustor 4. As a result, a contracted flow can be generated in the portion A, and the fuel and air can be sufficiently mixed in the mixing channel 134.
  • illustration is omitted for simplification of illustration, but since the first support plate 111 (see FIG. 2) as described above is not provided, the front side of the inflow port 142 is also provided. An air flow toward the inlet 142 is formed. That is, an air flow passing through the gap between the mixing flow path forming members 131 constituted by the mixing pipe is formed. Thereby, air flows from various directions are formed at the inlet 142 as compared with the combustor 4 described above. As a result, the contracted flow action in the part A can be further increased, and the fuel and air can be mixed more sufficiently in the mixing channel 134.
  • a gap is formed between the front end surface of the fuel nozzle 132 and the inlet 142.
  • the front end surface of the fuel nozzle 132 and the inflow port 142 may be brought into contact with each other.
  • a groove is provided on the front end face of the fuel nozzle 132 so that a part of the opening end of the inlet 142 can be fitted, and the part of the opening end of the inlet 142 is fitted in this groove. (So-called inlay fitting).
  • the length of the mixing channel forming member 131 in the front-rear direction may be changed according to the mixing channel forming member 131. That is, the length of the mixing channel forming member 131 in the front-rear direction may be the same or different in all the mixing channel forming members 131.
  • the length of the mixing flow path forming member 131 for each mixing flow path forming member 131 the length of the mixing flow path 134 can be changed for each mixing flow path 134, and the combustion vibration of the combustor 4 is suppressed. Easy to do.
  • FIG. 10 is a view showing the arrangement of the fuel nozzles 132 and the partition wall assemblies 160 provided in the combustor 4B according to the third embodiment of the present invention.
  • the partition aggregate 160 can be used in place of the mixing tube as the mixing channel forming member 131 and includes a plurality of mixing channels 134. Therefore, a plurality of mixing channels 134 are included in one partition aggregate 160 (an example of a mixing channel forming member).
  • the partition aggregate 160 is constituted by a set of a plurality of partition walls 161 that partition each of the plurality of mixing channels 134.
  • the partition wall assembly 160 is formed in the shape of a regular hexagon when viewed from the upstream side to the downstream side (that is, from the rear side to the front side) along the direction of the axis L (see FIG. 2) of the casing 20. Are provided. That is, the partition aggregate 160 is formed in a honeycomb shape.
  • the fuel nozzle 132 is disposed so as to overlap with any one opening 162.
  • six nozzle portion injection holes 133 are formed in the fuel nozzle 132 at equal intervals in the circumferential direction. Therefore, fuel is injected from each of the six nozzle injection holes 133 into the six inlets 142 disposed around the opening 162 where the fuel nozzle 132 overlaps.
  • the partition wall assembly 160 as the mixing channel forming member 131, when a failure occurs in the mixing channel 134, the failure can be solved by replacing the entire partition wall assembly 160, thus facilitating maintenance. It can be carried out. Further, since the mixing channels 134 are partitioned by the partition wall 161, there is no useless space, and the combustor 4B can be downsized. Furthermore, since the mixing channels 134 are formed densely, fuel can be supplied to more mixing channels 134 through one fuel nozzle 132. As a result, the number of fuel nozzles 132 can be reduced. Furthermore, mixing close to a jet subjected to a cross wind can be generated, and particularly sufficient mixing is possible.
  • FIG. 11 is a diagram showing the flow of fuel and air flowing in from the inflow port 142.
  • the fuel injection from the nozzle portion injection hole 133 of the fuel nozzle 132 is performed so as to be directed to the inlet 142 of the partition wall assembly 160 when the above-described visual recognition is performed.
  • the fuel is injected toward six inlets 142 (see also FIG. 10) arranged around the opening 162 that overlaps the fuel nozzle 132.
  • FIG. 12 is a view showing the arrangement of the fuel nozzle 132 and the partition wall assembly 160, and is a view showing an embodiment different from FIG.
  • the partition aggregate 160 shown in FIG. 12 is configured in a staggered pattern unlike the partition aggregate 160 configured in the honeycomb shape. And although illustration is abbreviate
  • FIG. 13 is a cross-sectional view showing the vicinity of the combustor 4C according to the fourth embodiment of the present invention.
  • the longitudinal length of the tubular member 105 is shorter than the length of the tubular member 105 provided in the combustor 4A (see FIG. 8). That is, in the combustor 4 ⁇ / b> C, the rear end of the cylindrical member 105 is substantially the same as the installation position of the support member 106. Therefore, the air chamber 121 in the combustor 4 ⁇ / b> C is larger than the air chamber 121 formed in the combustor 4 ⁇ / b> A because the air flow path 110 formed between the cylindrical member 105 and the inner wall of the casing 20 is shortened. It has become.
  • a baffle plate 170 is installed between the rear end of the tubular member 105 and the rear inner wall 20a of the casing 20.
  • the baffle plate 170 is supported on the inner wall surface of the casing 20 at a position where it collides with the air flow in the air flow path 110 (a position where the air flow is blocked).
  • the air flowing into the air flow path 110 from the vehicle compartment 40 flows through the air flow path 110 along the inner wall surface of the casing 20 and reaches the air chamber 121.
  • the baffle plate 170 is installed in the air chamber 121 at a position where it collides with the air flow in the air flow path 110, the flow of air reaching the air chamber 121 is changed by the baffle plate 170. Specifically, as shown by solid line arrows in FIG. 13, the whole air chamber 121 passes through a gap between the mixing flow path forming members 131 arranged with a space therebetween.
  • the radial direction of the cylindrical tube member 105 depends on the pressure loss until the air flowing out from the air channel 110 passes through the gap of the mixing channel forming member 131 and reaches the inlet 142.
  • the length of the mixing flow path forming member 131 can be easily adjusted.
  • the amount of air flowing in from the inflow port 142 can be easily made comparable.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
PCT/JP2019/002217 2018-03-26 2019-01-24 燃焼器及びそれを備えるガスタービン Ceased WO2019187559A1 (ja)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US16/980,998 US11371707B2 (en) 2018-03-26 2019-01-24 Combustor and gas turbine including the same
DE112019000871.4T DE112019000871B4 (de) 2018-03-26 2019-01-24 Brennkammer und damit ausgestattete gasturbine
CN201980019938.9A CN111936790B (zh) 2018-03-26 2019-01-24 燃烧器以及具备该燃烧器的燃气轮机
KR1020207026866A KR102396908B1 (ko) 2018-03-26 2019-01-24 연소기 및 그것을 구비하는 가스 터빈

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JP2018058233A JP6941576B2 (ja) 2018-03-26 2018-03-26 燃焼器及びそれを備えるガスタービン
JP2018-058233 2018-03-26

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JP7349403B2 (ja) 2020-04-22 2023-09-22 三菱重工業株式会社 バーナー集合体、ガスタービン燃焼器及びガスタービン
JP7339206B2 (ja) * 2020-04-22 2023-09-05 三菱重工業株式会社 バーナー集合体、ガスタービン燃焼器及びガスタービン
JP7379265B2 (ja) * 2020-04-22 2023-11-14 三菱重工業株式会社 バーナー集合体、ガスタービン燃焼器及びガスタービン
KR102460672B1 (ko) * 2021-01-06 2022-10-27 두산에너빌리티 주식회사 연료 노즐, 연료 노즐 모듈 및 이를 포함하는 연소기
KR102667812B1 (ko) 2022-02-07 2024-05-20 두산에너빌리티 주식회사 연소기용 노즐 및 이를 포함하는 가스 터빈
JPWO2024203677A1 (https=) 2023-03-29 2024-10-03
DE112024000980T5 (de) 2023-04-26 2025-12-04 Mitsubishi Heavy Industries, Ltd. Brenneranordnung, gasturbinenbrennkammer und gasturbine

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JP6941576B2 (ja) 2021-09-29
KR20200119875A (ko) 2020-10-20
US11371707B2 (en) 2022-06-28
DE112019000871B4 (de) 2024-11-07
KR102396908B1 (ko) 2022-05-12
JP2019168198A (ja) 2019-10-03
CN111936790B (zh) 2023-03-21
CN111936790A (zh) 2020-11-13
DE112019000871T5 (de) 2020-11-12

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