WO2024203677A1 - バーナー集合体、ガスタービン燃焼器及びガスタービン - Google Patents

バーナー集合体、ガスタービン燃焼器及びガスタービン Download PDF

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Publication number
WO2024203677A1
WO2024203677A1 PCT/JP2024/010904 JP2024010904W WO2024203677A1 WO 2024203677 A1 WO2024203677 A1 WO 2024203677A1 JP 2024010904 W JP2024010904 W JP 2024010904W WO 2024203677 A1 WO2024203677 A1 WO 2024203677A1
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WO
WIPO (PCT)
Prior art keywords
region
cross
extension direction
burner assembly
inlet
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/JP2024/010904
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English (en)
French (fr)
Japanese (ja)
Inventor
志 張
信一 福場
圭祐 三浦
拓 江川
喜敏 藤本
健太 谷口
朋 川上
竜平 加野島
宗幸 楯
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 Heavy Industries Ltd
Mitsubishi Power Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Mitsubishi Power 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 Heavy Industries Ltd, Mitsubishi Power Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to DE112024000649.3T priority Critical patent/DE112024000649T5/de
Priority to CN202480015290.9A priority patent/CN120693484A/zh
Priority to JP2025510617A priority patent/JPWO2024203677A1/ja
Priority to KR1020257027065A priority patent/KR20250133784A/ko
Publication of WO2024203677A1 publication Critical patent/WO2024203677A1/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
    • F23R3/02—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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/82—Preventing flashback or blowback
    • 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
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • 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
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/10—Flame flashback
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the present disclosure relates to burner assemblies, gas turbine combustors, and gas turbines.
  • This application claims priority based on Japanese Patent Application No. 2023-053155, filed with the Japan Patent Office on March 29, 2023, the contents of which are incorporated herein by reference.
  • one technique for achieving low NOx emissions while maintaining flashback resistance is to form a large number of independent short flames using a burner assembly (cluster burner).
  • a burner assembly cluster burner
  • multiple mixing passages that mix fuel and air are arranged, and the scale of fuel mixing is reduced, making it possible to obtain high mixing performance without actively utilizing swirling flow to mix fuel and air.
  • Patent Document 1 discloses a burner assembly for suppressing flashback while achieving low NOx emissions.
  • Each burner in this burner assembly is equipped with a fuel nozzle and a mixing passage into which fuel and air flow, and the fuel nozzle includes a protrusion that protrudes upstream in the air flow direction from the inlet of the mixing passage.
  • a fuel injection hole is formed on the side of the protrusion, and fuel injected from the fuel injection hole flows into the inlet of the mixing passage together with air, where the fuel and air are mixed.
  • the burner assembly described in Patent Document 1 has room for further improvement in terms of suppressing flashback.
  • At least one embodiment of the present disclosure aims to provide a burner assembly, a gas turbine combustor, and a gas turbine that can suppress flashback.
  • a burner assembly comprising a plurality of burners for mixing fuel and air, the burner assembly comprising: Each of the plurality of burners has a flow path through which the air can flow, The flow path is a first region in which the fuel injection hole is formed, the first region being an upstream region of the air flow; a second region that is a region downstream of the first region and in which the fuel injected from the injection hole and the air are mixed, The first region is The flow path extends from an upstream end to a connection position with the second region, the injection hole is formed at a position closer to the connection position than the upstream end portion, At least one protrusion protruding radially inward from the flow path and in which the injection hole is formed; At least one peripheral wall portion adjacent to the at least one protrusion in a circumferential direction of the flow passage and not provided with the protrusion; having When viewed from the extending direction of the flow path, a second cross-sectional area in the second region
  • a gas turbine combustor according to at least one embodiment of the present disclosure, A burner assembly having the configuration of (1) above; a combustion liner forming a space in which a flame is formed downstream of the burner assembly; Equipped with.
  • a gas turbine according to at least one embodiment of the present disclosure, A compressor; a gas turbine combustor configured to receive the air compressed by the compressor and fuel and to combust the fuel to generate combustion gas; a turbine driven by the combustion gas generated in the gas turbine combustor; Equipped with The gas turbine combustor is a gas turbine combustor having the configuration described above in (2).
  • At least one embodiment of the present disclosure provides a burner assembly, a gas turbine combustor, and a gas turbine that can suppress flashback.
  • FIG. 1 is a schematic configuration diagram of a gas turbine according to an embodiment.
  • FIG. 2 is a cross-sectional view showing the vicinity of a combustor.
  • FIG. 2 is a perspective view for explaining a structure of a combustor.
  • FIG. 2 is a partial schematic perspective view of a portion of a burner assembly according to one embodiment.
  • 5 is a cross-sectional view of a portion of a burner assembly according to one embodiment, taken along the line VV in FIG. 4.
  • 6 is a schematic diagram showing a part of a cross section taken along the line VI-VI in FIG. 5.
  • FIG. 2 is a partial schematic perspective view of a portion of a burner assembly according to one embodiment, with an inlet channel wall removed for illustration purposes.
  • FIG. 1 is a schematic configuration diagram of a gas turbine according to an embodiment.
  • FIG. 2 is a cross-sectional view showing the vicinity of a combustor.
  • FIG. 2 is a perspective view for explaining a structure of
  • FIG. 2 is a schematic diagram showing a part of a burner assembly with an inlet flow passage wall removed for the purpose of explanation, viewed from the upstream side in the air flow direction along the central axis.
  • 9 is a schematic diagram showing a part of a cross section taken along the line IX-IX in FIG. 8.
  • 9 is a schematic diagram showing a part of a cross section taken along the line XX in FIG. 8 .
  • 5 is a cross-sectional view of a portion of a burner assembly according to another embodiment, taken along line VV in FIG. 4.
  • 12 is a schematic diagram showing a part of a cross section taken along the line XII-XII in FIG. 11.
  • FIG. 7 is a cross-sectional view of a portion XIII enclosed by a dashed line in FIG. 6 as viewed from the upstream side in the air flow direction.
  • FIG. 7 is a cross-sectional view of a portion XIII enclosed by a dashed line in FIG. 6 as viewed from the upstream side in the air flow direction, and shows another example of the protrusion.
  • FIG. 2 is a diagram for explaining dimensions of each part of a burner assembly according to some embodiments.
  • FIG. 2 is a diagram for explaining dimensions of each part of a burner assembly according to some embodiments.
  • 11A to 11C are diagrams for explaining variations in the shape of a protrusion.
  • FIG. 18 is a cross-sectional view of a portion XVIII enclosed by a dashed line in FIG. 17 as viewed from the upstream side in the air flow direction.
  • FIG. 18 is a cross-sectional view of a portion XVIII enclosed by a dashed line in FIG. 17 as viewed from the upstream side in the air flow direction, showing another example.
  • 11A to 11C are diagrams for explaining variations in the shape of a protrusion.
  • 21 is a cross-sectional view of a portion XXI surrounded by a dashed line in FIG. 20 as viewed from the upstream side in the air flow direction.
  • 13A and 13B are diagrams for explaining modified examples of the introduction channel wall and the channel wall.
  • FIG. 2 is a schematic diagram for explaining the extending direction of a fuel injection hole, showing a cross section perpendicular to the central axis.
  • FIG. 2 is a schematic diagram for explaining the extending direction of a fuel injection hole, showing a cross section perpendicular to the central axis.
  • 7 is a diagram showing another example of a protrusion of a fuel nozzle, and corresponds to a cross-sectional view taken along the line XXV-XXV in FIG. 5 .
  • 1 is a schematic diagram showing a portion of a burner assembly according to a modified example of the first region, viewed from the upstream side in the air flow direction along the central axis L.
  • FIG. 4 is a schematic cross-sectional view of a first region appearing in a cross section including a central axis of a flow channel.
  • FIG. 4 is a schematic cross-sectional view of a first region appearing in a cross section including a central axis of a flow channel.
  • FIG. 4 is a schematic cross-sectional view of a first region appearing in a cross section including a central axis of a flow channel.
  • FIG. 27 is a schematic cross-sectional view showing the AA cross section in FIG. 26.
  • 27 is a schematic cross-sectional view showing the cross section taken along line BB in FIG. 26.
  • 27 is a schematic cross-sectional view showing the AA cross section in FIG. 26.
  • 27 is a schematic cross-sectional view showing the cross section taken along line BB in FIG. 26.
  • 27 is a schematic cross-sectional view showing the AA cross section in FIG. 26.
  • 27 is a schematic cross-sectional view showing the cross section taken along line BB in FIG. 26.
  • 27 is a schematic cross-sectional view showing the AA cross section in FIG. 26.
  • 27 is a schematic cross-sectional view showing the AA cross section in FIG. 26.
  • 27 is a schematic cross-sectional view showing the AA cross section in FIG. 26.
  • 27 is a schematic cross-sectional view showing the cross section taken along line BB in FIG. 26.
  • 27 is a schematic cross-sectional view showing the AA cross section in FIG. 26.
  • 27 is a schematic cross-sectional view showing the cross section taken along line BB in FIG. 26.
  • expressions indicating that things are in an equal state such as “identical,””equal,” and “homogeneous,” not only indicate a state of strict equality, but also indicate a state in which there is a tolerance or a difference to the extent that the same function is obtained.
  • expressions describing shapes such as a rectangular shape or a cylindrical shape do not only represent rectangular shapes or cylindrical shapes in the strict geometric sense, but also represent shapes that include uneven portions, chamfered portions, etc., to the extent that the same effect can be obtained.
  • the expressions “comprise,””include,””have,””includes,” or “have” of one element are not exclusive expressions excluding the presence of other elements.
  • FIG. 1 is a schematic diagram of a gas turbine according to one embodiment.
  • the gas turbine 1 includes a compressor 2 for generating compressed air, a combustor 4 for generating combustion gas using the compressed air and fuel, and a turbine 6 configured to be rotationally driven by the combustion gas.
  • a generator (not shown) is connected to the turbine 6.
  • the compressor 2 includes a plurality of stator vanes 16 fixed to the compressor casing 10 side, and a plurality of rotor blades 18 implanted in the rotor 8 so as to be arranged alternately with respect to the stator vanes 16 .
  • Air is taken in through an air intake 12 and sent to the compressor 2. This air passes through a plurality of stator vanes 16 and a plurality of rotor blades 18 and is compressed to become high-temperature, high-pressure compressed air.
  • the combustor 4 is supplied with fuel and compressed air generated by the compressor 2, and the fuel is combusted in the combustor 4 to generate combustion gas, which is the working fluid of the turbine 6.
  • the gas turbine 1 has multiple combustors 4 arranged circumferentially around the rotor 8 inside the casing 20.
  • the turbine 6 includes a plurality of stator vanes 24 and rotor blades 26 that are provided in a combustion gas passage defined by a turbine casing 22.
  • the stator vanes 24 and rotor blades 26 of the turbine 6 are provided downstream of the combustor 4 with respect to the flow of combustion gas.
  • the stator vanes 24 are fixed to the turbine casing 22 side, and a plurality of the stator vanes 24 arranged along the circumferential direction of the rotor 8 constitute a stator vane row.
  • the moving blades 26 are implanted in the rotor 8, and a plurality of the moving blades 26 arranged along the circumferential direction of the rotor 8 constitute a moving blade row.
  • stator vane rows and moving blade rows are arranged alternately in the axial direction of the rotor 8.
  • the combustion gas from the combustor 4 that has flowed into the combustion gas passage passes through a plurality of stator vanes 24 and a plurality of rotor blades 26 to rotate the rotor 8, which drives a generator connected to the rotor 8 to generate electricity.
  • the combustion gas that has driven the turbine 6 is exhausted to the outside via an exhaust chamber 30.
  • FIG. 2 is a cross-sectional view showing the vicinity of the combustor 4.
  • FIG. 3 is a perspective view for explaining the structure of the combustor 4.
  • the combustor 4 includes a burner assembly 32, a cylindrical casing 20 with a bottom that houses the burner assembly 32, and a combustion tube 25 that forms a space downstream of the burner assembly 32 in which a flame is formed.
  • the dashed line indicates a central axis L common to each of the casing 20, the burner assembly 32, and the combustion tube 25.
  • the burner assembly 32 is disposed inside the casing 20 of the combustor 4.
  • the burner assembly 32 is held inside a cylindrical member 34 disposed inside the casing 20, and the cylindrical member 34 is supported by the casing 20 via a plurality of supports 35 disposed at intervals around the central axis L.
  • an air flow passage 36 is formed through which the compressed air flowing in from the casing 40 flows.
  • the compressed air that flows into the air flow passage 36 from the casing 40 passes through the axial gap 23 between the burner assembly 32 and the bottom surface 21 of the casing 20, and flows together with fuel into a plurality of mixing passages 46 (described below) provided in the burner assembly 32.
  • the fuel and air mixed in the burner assembly 32 are ignited by an ignition device (not shown), forming a flame in the combustion tube 25 and generating combustion gas.
  • the burner assembly 32 includes a plurality of burners 42 for mixing fuel and air as described below.
  • Each burner 42 includes a flow passage 100, described below, through which the fuel and air flow.
  • the burner assembly 32 when viewed from the downstream side along the central axis L, includes a plurality of flow passages 100 arranged in a pentagonal region drawn by a two-dot chain line centered on the central axis L, and in five regions arranged in the circumferential direction outside the pentagon so as to correspond to each side of the pentagon.
  • the layout pattern of the flow channels 100 shown in FIG. 3 is merely an example, and the layout pattern of the flow channels 100 is not necessarily as shown in FIG.
  • FIG. 4 is a partial schematic perspective view showing a part of a burner assembly 32 according to one embodiment.
  • FIG. 5 is a view equivalent to the V-V cross section of FIG. 4 of a part of a burner assembly 32 according to one embodiment.
  • FIG. 6 is a schematic view showing a part of the VI-VI cross section in FIG. 5.
  • FIG. 7 is a partial schematic perspective view showing a part of a burner assembly 32 according to one embodiment, with the introduction channel wall 115 described below removed for the sake of explanation.
  • FIG. 8 is a schematic view of a part of the burner assembly 32 with the introduction channel wall 115 removed for the sake of explanation, viewed from the upstream side in the air flow direction along the central axis L.
  • FIG. 9 is a schematic view showing a part of the IX-IX cross section of FIG. 8.
  • FIG. 10 is a schematic view showing a part of the X-X cross section of FIG. 8.
  • FIG. 11 is a cross-sectional view equivalent to the V-V cross-sectional view of FIG. 4 for a portion of a burner assembly 32 according to another embodiment.
  • FIG. 12 is a schematic diagram showing a portion of the XII-XII cross-sectional view of FIG. 11.
  • FIG. 13 is a cross-sectional view of part XIII surrounded by a dashed line in FIG. 6 as viewed from the upstream side in the air flow direction.
  • FIG. 14 is a cross-sectional view equivalent to the XIII cross-sectional view of part XIII surrounded by a dashed line in FIG. 6 as viewed from the upstream side in the air flow direction, and shows another example of a protrusion 51, which will be described later.
  • the burner assembly 32 includes multiple burners 42 for mixing fuel and air.
  • Each of the burners 42 includes an inlet passage 110 for introducing compressed air for combustion from the casing 40 (see FIG. 1 and FIG. 2) to each of the burners 42, a plurality of fuel nozzles 43 for injecting fuel, and a mixing passage 46 into which the fuel injected from the plurality of fuel nozzles 43 and the compressed air supplied from the inlet passage 110 flow.
  • each of the burners 42 includes one inlet passage 110, one mixing passage 46, and four fuel nozzles 43 arranged around one mixing passage 46, as in the first burner 42a (see FIG. 8) described later, and fuel is injected from the four surrounding fuel nozzles 43 into one mixing passage 46.
  • four mixing passages 46 are arranged around one fuel nozzle 43, and one fuel nozzle 43 injects fuel into the four mixing passages 46.
  • a flow path 100 through which fuel and air flow includes an introduction flow path 110 and a mixing flow path 46 that is continuous with the downstream side of the introduction flow path 110.
  • the introduction flow path 110 and the mixing flow path 46 are connected at an inlet 48 (see, for example, FIGS. 6 and 12 ) of the mixing flow path 46, which will be described later, which is a connection position between the introduction flow path 110 and the mixing flow path 46.
  • the introduction channel 110 is a first region 101 of the channel 100
  • the mixing channel 46 is a second region 102 of the channel 100 .
  • the flow paths 100 are configured as through holes extending parallel to each other, and the central axis O of each of the flow paths 100 extends in a direction along the central axis L of the casing 20.
  • the central axis O of each of the flow paths 100 and the central axis L of the casing 20 are parallel to each other.
  • the radial direction and the circumferential direction about the central axis O may be simply referred to as the radial direction and the circumferential direction in the description of each part of the flow passage 100. Note that the extension direction of the flow passage 100 coincides with the extension direction of the central axis O.
  • the inlet flow passage wall 115 forming the inlet flow passage 110 shown in Figures 4 to 6 is configured in a cylindrical shape so as to define the inlet flow passage 110, which has a circular cross-section, on the inside, and functions as a straightening section for straightening the air flowing into the mixing flow passage 46.
  • the inlet flow path wall 115 forming the inlet flow path 110 shown in Figures 11 and 12 is configured in a rectangular tubular shape so as to define the inlet flow path 110, which has a rectangular cross-section, on the inside, and functions as a straightening section for straightening the air flowing into the mixing flow path 46.
  • any two burners 42 whose mixing flow paths 46 are closest to each other among the plurality of burners 42 will be referred to as the first burner 42a and the second burner 42b for convenience.
  • the flow path 100 of the first burner 42a may be referred to as the first flow path 100a
  • the flow path 100 of the second burner 42b may be referred to as the second flow path 100b.
  • the second flow path 100b is the flow path 100 closest to the first flow path 100a.
  • the introduction flow passage wall 115 forming the introduction flow passage 110 (110a) of the first burner 42a and the introduction flow passage wall 115 forming the introduction flow passage 110 (110b) of the second burner 42b share a partition portion 118 (118ab) that separates the introduction flow passage 110a of the first burner 42a from the introduction flow passage 110b of the second burner 42b.
  • the introduction flow passage wall 115 of the introduction flow passage 110 shares the partition portion 118 with each of the introduction flow passage walls 115 of the multiple introduction flow passages 110 (four introduction flow passages 110 in the illustrated embodiment) around the introduction flow passage 110.
  • the thickness t1 of the partition wall portion 118 (118ab) in the VI-VI cross section and the XII-XII cross section of the burner assembly 32 is constant in the direction along the central axis O of the first burner 42a.
  • each of the fuel nozzles 43 includes a protruding portion 50 that protrudes from a downstream region in the introduction flow passage 110, i.e., from the inlet 48 of the mixing flow passage 46 (see FIG. 6, for example), upstream in the air flow direction.
  • Each of the fuel nozzles 43 also includes a plurality of fuel injection holes 53 formed in a side surface 44 of the protruding portion 50. In the exemplary embodiment shown in FIG. 8, four fuel injection holes 53 are formed in the side surface 44 of the protruding portion 50 at positions corresponding to the four flow passages 100 (mixing flow passages 46) around the protruding portion 50.
  • Each of the fuel injection holes 53 may extend in a direction perpendicular to the central axis O so as to inject fuel toward the central axis O of the flow passage 100, as will be described later, or may extend in a direction oblique to the direction perpendicular to the central axis O.
  • each fuel nozzle 43 includes a base end 431 having the above-mentioned side surface 44 formed parallel to the central axis O, and a tip end 432 formed from the base end 431 toward the upstream side in the air flow direction.
  • each of the protrusions 50 has a base end 431 and a portion of a tip end 432 that protrudes radially inward into the introduction flow path 110 in a downstream region of the introduction flow path 110.
  • Each of the protrusions 50 shown in Figures 4 to 6, 11 and 12 has the same shape as a body of revolution about an axis parallel to the central axis O.
  • a portion of the base end 431 and the tip end 432 of each of the four protrusions 50 arranged to surround one introduction flow passage 110 protrudes radially inward from circumferential positions every 90 degrees around the central axis O. Focusing on each of the protrusions 50, in the examples shown in Figures 4 to 6, 11 and 12, each of the protrusions 50 protrudes inwardly of each of the four introduction flow paths 110 arranged to surround one of the protrusions 50.
  • the protrusions 51 that are protruding inward of the introduction flow passage 110 of two protrusions 50 adjacent in the circumferential direction centered on the central axis O are spaced apart in the circumferential direction.
  • a peripheral wall portion 116 is provided between two protrusions 51 adjacent in the circumferential direction where no protrusion 51 is provided. That is, in the example shown in Figures 4 to 6, 11 and 12, the protrusions 51 and the peripheral wall portion 116 are arranged alternately in the circumferential direction at the axial positions where the protrusions 51 are provided.
  • the top surface 54 of the protrusion 50 (the end surface of the protrusion 50 in the direction of the axis O, i.e., the tip of the protrusion 50) includes a convex curved surface 56.
  • the entire top surface 54 of the protrusion 50 is formed by the smoothly curved convex curved surface 56.
  • the top surface 54 of the protrusion 50 may be formed, for example, in a streamlined shape. Variations in the shape of the protrusion 50 will be described later.
  • the protrusion 51 in a cross section along the extension direction of the central axis O, includes a base end 431 that extends linearly along the extension direction of the central axis O, and a tip end 432 that is formed so that the amount of protrusion radially inward gradually increases upstream of the base end 431 toward the base end 431.
  • This makes it possible to suppress separation of the air flow from the tip end 432 toward the base end 431. Therefore, a region with a low flow velocity and high fuel concentration is unlikely to be formed in the vicinity of the fuel injection hole 53 (in the vicinity of the fuel jet). As a result, the risk of flashback, which is backfire from the outlet 47 of the mixing channel 46, can be suppressed.
  • the flow passage wall 55 forming the mixing flow passage 46 is configured in a tubular shape so as to define the mixing flow passage 46 having a circular cross section inside, and functions as a mixing tube for mixing fuel and air.
  • the flow passage wall 55 forming the mixing flow passage 46 (46a) of the first burner 42a and the flow passage wall 55 forming the mixing flow passage 46 (46b) of the second burner 42b share a partition wall portion 58 (58ab) that separates the mixing flow passage 46a of the first burner 42a from the mixing flow passage 46b of the second burner 42b.
  • the flow passage wall 55 of the mixing flow passage 46 shares the partition wall portion 58 with each of the flow passage walls 55 of the multiple mixing flow passages 46 (four mixing flow passages 46 in the illustrated embodiment) surrounding the mixing flow passage 46.
  • the thickness t2 of the partition wall portion 58ab in the VI-VI cross section and the XII-XII cross section of the burner assembly 32 is constant in the direction along the central axis O of the first burner 42a downstream of the upstream end 61 of the partition wall portion 58ab in the air flow direction. Also, as shown in FIGS. 8 and 11, the thickness t2 of the partition wall portion 58ab increases with distance from the VI-IV cross section in FIG. 5, the C-C cross section in FIG. 8, and the XII-XII cross section in FIG. 11. Note that, as shown in FIG.
  • the C-C cross section is a cross section that passes through the center C1 of the inlet 48 of the mixing flow passage 46a of the first burner 42a and the center C2 of the inlet 48 of the mixing flow passage 46b of the second burner 42b, and is along the central axis O of the mixing flow passage 46 of the first burner 42a.
  • the VI-IV section in Figure 5 and the XII-XII section in Figure 11 are cross sections at the same position as the CC section.
  • an end face 59 (the upstream end face in the air flow direction) of a partition portion 58 separating the two adjacent mixing passages 46 has a saddle shape.
  • the inlet 48 of the mixing flow channel 46 (see, for example, FIGS. 6 and 12), which is the connection position between the introduction flow channel 110 and the mixing flow channel 46, is defined as the boundary position between the introduction flow channel wall 115 and the upstream end 61 of the partition section 58ab in the air flow direction.
  • the position of the inlet 48 of the mixing flow channel 46 in the direction of the central axis O is defined as the most downstream position of the boundary positions as shown in FIGS.
  • the thickness t2 of the partition portion 58ab in the VI-VI cross section and the XII-XII cross section of the burner assembly 32 decreases toward the upstream side in the air flow direction at the upstream end 61 of the partition portion 58ab in the air flow direction.
  • the upstream end face 59 of the partition portion 58ab in the air flow direction includes a convex curve 60.
  • the entire end face 59 of the partition portion 58ab is formed by a smoothly curved convex curve 60.
  • the end surface 59 of the partition wall portion 58ab may be formed, for example, in a streamlined shape.
  • the protrusion 50 of the second fuel nozzle 43b is located on the opposite side to the protrusion 50 of the first fuel nozzle 43a across the plane V (see Figure 10) that includes the above-mentioned C-C cross section.
  • the height H of the partition wall 58ab increases as it approaches the protruding portion 50 of the first fuel nozzle 43a from the position of the plane V (the position of the above-mentioned C-C cross section), and increases as it approaches the protruding portion 50 of the second fuel nozzle 43b from the position of the plane V.
  • the upstream end surface 59 of the partition wall 58ab in the air flow direction includes a concave curve 62 that connects the side surface 44 of the protruding portion 50 of the first fuel nozzle 43a and the side surface 44 of the protruding portion 50 of the second fuel nozzle 43b. Note that, as shown in FIG.
  • the above-mentioned X-X cross section is a cross section perpendicular to the straight line U (see FIG. 8) that connects the center C1 of the inlet 48 of the mixing passage 46a of the first burner 42a (see FIG. 6) and the center C2 of the inlet 48 of the mixing passage 46b of the second burner 42b.
  • the first cross-sectional area S1 of the inlet flow passage 110 when viewed in the extension direction of the flow passage 100, i.e., along the central axis O, is larger than the second cross-sectional area S2 of the mixing flow passage 46 when viewed along the central axis O.
  • the inner diameter Du of the inlet flow passage 110 is larger than the inner diameter Dm of the mixing flow passage 46a in the upstream region in the air flow direction from the position where the protrusion 51 appears in the inlet flow passage 110.
  • the inner diameter of the inlet flow passage 110 at the peripheral wall portion 116 is equal to the inner diameter Du of the inlet flow passage 110 in the upstream region in the air flow direction from the position where the protrusion 51 appears in the inlet flow passage 110.
  • the first cross-sectional area S1 of the inlet passage 110 when viewed along the central axis O is larger than the second cross-sectional area S2 of the mixing passage 46 when viewed along the central axis O.
  • the equivalent diameter Due of the inlet passage 110 is larger than the inner diameter Dm of the mixing passage 46a.
  • the equivalent diameter Due of the inlet passage 110 is the diameter of a circle having a cross-sectional area equal to the cross-sectional area of the inlet passage 110 when viewed along the central axis O.
  • the equivalent diameter of a certain cross section is the diameter of a circle having a cross-sectional area equal to the cross-sectional area of the cross section.
  • the diameter Dic (see Figures 5 and 13) of a virtual inscribed circle inscribed in the base ends 431 of the multiple protrusions 51 protruding into one introduction flow path 110 when viewed along the central axis O, i.e., the distance between two base ends 431 facing each other across the central axis O in the burner assembly 32 shown in Figures 4 to 6, 11 and 12, when viewed along the central axis O, is preferably greater than or equal to the inner diameter Dm of the mixing flow path 46a, as shown in Figures 13, 14 and Figure 25 described later.
  • the protrusion 50 may be attached to the flow path wall 55 by inserting the protrusion 50, which is made of a separate member from the member constituting the flow path wall 55, into a fuel plenum 55PL, which is a space formed within the flow path wall 55 and capable of storing fuel, and fixing the protrusion 50 to the flow path wall 55.
  • the diameter Dic of the inscribed circle may be larger than the inner diameter Dm of the mixing flow path 46a, or may be made equal to the inner diameter Dm of the mixing flow path 46a by increasing the diameter of the protrusion 50 upstream of the portion inserted into the flow path wall 55.
  • the diameter D of the inscribed circle may be equal to the inner diameter D of the mixing flow path 46a, or may be larger than the inner diameter D of the mixing flow path 46a, as shown in FIGS. 5 and 13.
  • the upstream end 61 of the partition wall 58 that separates adjacent mixing channels 46 is located downstream in the air flow direction from the peripheral wall 116 located between two circumferentially adjacent protrusions 51.
  • the compressed air flowing from the chamber 40 into the air flow path 36 passes through the axial gap 23 between the burner assembly 32 and the bottom surface 21 of the casing 20, and flows into each of the inlet flow paths 110 provided in each of the multiple burners 42 of the burner assembly 32.
  • the compressed air that flows into each inlet flow path 110 is straightened as it flows from the upstream end 111 (see Figure 4), which is the upstream end of the inlet flow path 110 (the upstream end of the flow path 100), toward the downstream side in the air flow direction.
  • the second cross-sectional area S2 of the mixing flow passage 46 is smaller than the first cross-sectional area S1 of the introduction flow passage 110, when air flows through the radially outer region of the introduction flow passage 110 into the mixing flow passage 46, it flows downstream while moving radially inward along the upstream end 61 of the partition section 58.
  • Fuel is injected into the flow passage 100 from a fuel injection hole 53 formed in a side surface 44 of a protruding portion 50 that protrudes radially inward. 6 and 12, the air flowing along the upstream end 61 of the partition portion 58 flows into the mixing flow passage 46 so as to get between the fuel injected from the fuel injection hole 53 and the wall surface 55s of the flow passage wall 55 of the mixing flow passage 46. Therefore, a region with high fuel concentration is unlikely to be formed near the wall surface 55s of the flow passage wall 55. As a result, the risk of flashback, which is a backfire from the outlet 47 of the mixing flow passage 46, can be reduced.
  • the fuel injection hole 53 is formed in the inlet passage 110 at a position closer to the inlet 48 than the upstream end 111.
  • the air is rectified in the inlet passage 110 as it reaches the vicinity of the fuel injection hole 53 (the vicinity of the fuel jet).
  • This suppresses the effects of turbulence in the air flow before it flows into the inlet passage 110, making it difficult for a region with low flow velocity and high fuel concentration to form in the vicinity of the fuel injection hole 53 (the vicinity of the fuel jet).
  • the risk of flashback can be suppressed.
  • the combustor 4 includes the burner assembly 32 described above, which reduces the risk of flashback. Therefore, the combustor 4 can be used stably.
  • the gas turbine 1 is equipped with the combustor 4, which reduces the risk of flashback and enables stable operation of the gas turbine.
  • FIG. 15 is a diagram for explaining the dimensions of each part of the burner assembly 32 according to some embodiments.
  • FIG. 16 is a diagram for explaining the dimensions of each part of the burner assembly 32 according to some embodiments.
  • FIG. 17 is a diagram for explaining variations in the shape of the protrusion 50.
  • FIG. 18 is a cross-sectional view of part XVIII surrounded by a dashed line in FIG. 17 as viewed from the upstream side in the air flow direction.
  • FIG. 19 is a diagram equivalent to the cross-sectional view of part XVIII surrounded by a dashed line in FIG. 17 as viewed from the upstream side in the air flow direction, and shows another example.
  • FIG. 20 is a diagram for explaining variations in the shape of the protrusion 50.
  • FIG. 21 is a cross-sectional view of part XXI surrounded by a dashed line in FIG. 20 as viewed from the upstream side in the air flow direction.
  • FIG. 22 is a diagram for explaining modified examples of the inlet flow passage wall 115 and the flow passage wall 55.
  • FIG. 23 is a schematic diagram for explaining the extension direction of the fuel injection hole 53, showing a cross section perpendicular to the central axis O.
  • FIG. 24 is a schematic diagram for explaining the extension direction of the fuel injection hole 53, showing a cross section perpendicular to the central axis O.
  • FIG. 25 is a diagram showing another example of the protrusion 50 of the fuel nozzle 43, and is a diagram equivalent to the cross section viewed from the arrows XXV-XXV in FIG. 5.
  • a first distance L1 in the extension direction of the central axis O between the upstream end 111 of the flow passage 100 and the center position of the opening 53ap in the protrusion 51 of the fuel injection hole 53 is preferably 1 time or more, and preferably 5 times or more, of the inner diameter Dm of the mixing flow passage 46 when viewed from the extension direction of the central axis O. This allows the air flow to be effectively rectified in the inlet flow passage 110, effectively reducing the risk of flashback.
  • the cross-sectional shape of the mixing flow channel 46 when viewed from the extending direction of the central axis O is other than a circle, the above-mentioned inner diameter Dm is the equivalent diameter of the mixing flow channel 46.
  • the second distance L2 in the extension direction between the inlet 48 of the mixing channel 46 and the upstream end 44u on the side 44 of the protrusion 50 may be less than or equal to 1 time the inner diameter Dm of the mixing channel 46 when viewed from the extension direction of the central axis O. This makes it possible to prevent the length of the protrusion 51 along the extension direction of the central axis O from increasing, thereby preventing a low-velocity area from occurring near the wall surface of the flow passage 100.
  • the cross-sectional shape of the mixing flow channel 46 when viewed from the extending direction of the central axis O is other than a circle, the above-mentioned inner diameter Dm is the equivalent diameter of the mixing flow channel 46.
  • the third distance L3 in the extension direction of the central axis O between the inlet 48 of the mixing passage 46 and the center position of the opening 53ap in the protrusion 51 of the fuel injection hole 53 is preferably greater than the opening diameter dap of the opening 53ap and less than the second distance L2.
  • the cross-sectional area of the passage 100 becomes smaller when viewed from the extension direction of the passage 100, and therefore, a flow toward the radially inward direction occurs in the air flowing from the introduction passage 110 into the mixing passage 46 near the inlet 48 of the mixing passage 46.
  • This makes it difficult for a region of high fuel concentration to be formed near the wall surface 55s of the mixing passage 46 in the fuel ejected from the fuel injection hole 53. As a result, the risk of flashback can be suppressed.
  • the fuel injection hole 53 will be too close to the mixing flow passage 46, making it difficult for air to enter between the fuel injected from the fuel injection hole 53 and the wall surface 55s of the flow passage wall 55 of the mixing flow passage 46, which may reduce the effect of the present disclosure in that it becomes difficult to form a region of high fuel concentration near the wall surface 55s of the mixing flow passage 46.
  • the fuel injection hole 53 will be located too far upstream from the vicinity of the inlet 48 of the mixing passage 46, where air flows radially inward, and there is a risk that a region of high fuel concentration will be easily formed near the inner wall of the introduction passage 110.
  • the fuel ejected from the fuel injection holes 53 is less likely to form areas of high fuel concentration near the inner walls of the inlet passage 110 or the mixing passage 46, thereby reducing the risk of flashback.
  • a fourth distance L4 in the extension direction of the central axis O from the upstream end 111 of the inlet passage 110 to the upstream end 51t of the protrusion 51 may be 0 or greater. This makes it possible to ensure the air straightening effect in the inlet flow passage 110 while reducing the risk of flashback.
  • the top surface 54 of the tip portion 432 may have an arc shape in a cross section along the extension direction of the central axis O, as shown in Fig. 7 for example. That is, in the burner assembly 32 according to some embodiments, the convex curved surface 56 may be a spherical surface. This makes it possible to reduce the distance from the upstream end 111 of the inlet passage 110 to the base end 431 while making it difficult to disturb the flow of air from the tip end 432 to the base end 431, making it easier to ensure the effect of the present disclosure that an area of high fuel concentration is less likely to be formed near the wall surface 55s of the mixing passage 46.
  • the convex surface 56 may be a conical or pyramidal surface instead of a spherical surface.
  • the convex surface 56 is a conical or pyramidal surface, it is preferable that the surface shape gradually changes from the base end 431 to the conical or pyramidal surface.
  • the convex curved surface 56 may be an ogive, such as the nose cone at the tip of a rocket, or may be a surface of revolution that is a quadratic curve, such as a parabola.
  • the top surface 54 of the tip portion 432 may have an elliptical arc shape in a cross section taken along the extension direction of the central axis O, as shown in FIG. 17, for example.
  • the major axis of the elliptical arc is aligned along the extension direction of the central axis O as shown in FIG. 17 , the air flow from the tip end 432 to the base end 431 can be made less likely to be disturbed compared to when the top surface 54 of the tip end 432 has a circular arc shape in a cross section along the extension direction as shown in FIG. 7 .
  • the shape of the protrusion 51 protruding into the introduction flow path 110 of the tip portion 432 may be, for example, as shown in FIG. 18 , a shape in which the cross section appearing in a plane perpendicular to the central axis O is circular, or, for example, as shown in FIG. 19 , a shape in which the cross section appearing in a plane perpendicular to the central axis O is elliptical.
  • the apex located on the major axis of the ellipse protrudes into the introduction flow path 110
  • the apex located on the minor axis of the ellipse may also protrude into the introduction flow path 110 .
  • the protrusion 51 may have a shape other than a circle or an ellipse in a cross section of the base end 431 in a plane (FIG. 21) perpendicular to the central axis O, as shown in FIG. 20 and FIG. 21, and may have, for example, a rectangular shape with rounded corners.
  • the protrusion 50 may be hollow having a space 50a therein in which fuel can be stored, as shown, for example, in Figures 20, 21, and 23 to 25. Although omitted in Figures 9 and 10, as shown in Figure 25, a fuel plenum 55PL that is a space that communicates with the above-mentioned space 50a and is capable of storing fuel may be formed in the flow path wall 55 downstream of the protrusion 50 in the air flow direction.
  • a gap may be provided between the introduction flow passage wall 115 forming the introduction flow passage 110 (110a) of the first burner 42a and the introduction flow passage wall 115 forming the introduction flow passage 110 (110b) of the second burner 42b, and this gap may be used as a flow passage 119 for compressed air.
  • a flow passage 55fp may be provided to connect an opening 55ap opening in a wall surface 55s of the flow passage wall 55 forming the mixing flow passage 46 and the flow passage 119, so that the compressed air from the flow passage 119 can be ejected from the opening 55ap to perform film cooling on the wall surface 55s of the flow passage wall 55.
  • the position of the opening 55ap in the direction of the central axis O may be near the outlet 47 (see Fig. 4) of the mixing flow passage 46.
  • Each of the fuel injection holes 53 may extend in a direction perpendicular to the central axis O of the flow passage 100 so as to inject fuel toward the central axis O as shown in FIG. 23, for example. Furthermore, each of the fuel injection holes 53 may extend in a direction oblique to a direction perpendicular to the central axis O, as shown in FIG. In the example shown in Figures 23 and 24, each of the fuel injection holes 53 may extend along a plane perpendicular to the central axis O, or may be inclined toward the downstream side in the air flow direction as shown in Figure 25.
  • the inlet flow passage wall 115 forming the inlet flow passage 110 has a flat surface extending in a direction perpendicular to the central axis O of the flow passage 100. If such a flat surface exists, there is a risk that air flowing from the outside along the extension direction of the central axis O will collide with the flat surface, causing disturbance in the flow, and the air will separate and flow from the inner circumferential surface near the inlet of the introduction passage 110. Even if such disturbance in the air flow occurs to some extent, in the burner assembly 32 according to some of the above-mentioned embodiments, the air is rectified as it flows through the introduction passage 110, reducing the risk of flashback.
  • FIG. 26 is a schematic diagram of a part of a burner assembly 32 according to a modified example of the first region 101, viewed from the upstream side in the air flow direction along the central axis L.
  • FIG. 27 is a schematic cross-sectional view of the first region 101 (inlet flow channel 110) appearing in a cross section including the central axis O of the flow channel 100, and shows the AA cross section or the BB cross section of FIG. FIG.
  • FIG. 28 is a schematic cross-sectional view of the first region 101 (inlet flow channel 110) appearing in a cross section including the central axis O of the flow channel 100, and shows the AA cross section or the BB cross section of FIG.
  • FIG. 29 is a schematic cross-sectional view of the first region 101 (inlet flow channel 110) appearing in a cross section including the central axis O of the flow channel 100, and shows the AA cross section or the BB cross section of FIG. It should be noted that the magnitude of the radius of curvature R, which will be described later, differs between FIG. 27, FIG. 28, and FIG.
  • the inlet passages 110 are arranged at equal intervals, for example, along a first direction Dr1 perpendicular to the extension direction of the passage 100 (the extension direction of the central axis O) and a second direction Dr2 perpendicular to the extension direction of the central axis O and the first direction Dr1.
  • the inlet passage 110 has inner surfaces (inner wall surfaces 115Is) of adjacent inlet areas 113 described later in the first direction Dr1 separated by a distance La.
  • the introduction passage 110 is such that the inner wall surfaces 115Is of adjacent introduction regions 113 in the second direction Dr2 are spaced apart by a distance La or more.
  • a direction that extends in a direction different from the first direction and the second direction and is perpendicular to the extension direction of the central axis O is defined as a third direction Dr3.
  • the introduction passage 110 has inner wall surfaces 115Is of adjacent introduction regions 113 in the third direction Dr3 spaced apart by a distance Lb.
  • the angular difference between the first direction Dr1 and the third direction Dr3 is greater than or equal to 45 degrees and less than 90 degrees, because the inner wall surfaces 115Is of adjacent introduction areas 113 in the second direction Dr2 are separated by a distance La or more.
  • the introduction flow passage 110 includes an inlet region 112 including an upstream end portion 111, and an introduction region 113 connected to the inlet region 112 downstream of the inlet region 112.
  • the inlet region 112 is defined by an inner wall surface 112Is formed in a curved shape that is convex toward the inside of the first region 101 in a cross section along the extension direction of the flow passage 100 (extension direction of the central axis O), as shown in Figures 27 to 29 and the various figures described below, and is formed so that the cross-sectional area of the flow passage 100 gradually decreases toward the downstream side.
  • the position of the center (center of curvature) Ca of the radius of curvature R of the inner wall surface 112Is is set so that the inner wall surface 112Is is convex toward the inside of the first region 101, for example, in a cross section along the extension direction of the central axis O.
  • the introduction region 113 is defined by an inner wall surface formed in a straight line parallel to the extension direction of the central axis O, i.e., an inner wall surface 115Is of the introduction flow path wall 115, in a cross section along the extension direction of the central axis O (axis O direction). That is, the inner peripheral surface of the introduction region 113 becomes the inner wall surface 115Is of the introduction flow path wall 115.
  • the introduction region 113 has a configuration similar to that of the introduction flow channel 110 in some of the above-mentioned embodiments.
  • the downstream side of the introduction region 113 is connected to the mixing flow channel 46 at the inlet 48 of the mixing flow channel 46 (see, for example, FIGS.
  • the introduction flow channel 110 has a configuration in which an inlet region 112 is added to the upstream side of the introduction flow channel 110 in some of the above-mentioned embodiments.
  • the inlet region 112 and the introduction region 113 are connected at a connection position 114 between the two.
  • the inner wall surface 112Is that defines the inlet region 112 and the inner wall surface 115Is that defines the introduction region 113 are smoothly connected without any steps around the entire periphery of the connection position 114.
  • the position of the center of curvature Ca in the axis O direction for at least the inner wall surface 112Is in the vicinity of the connection position 114 among the inner wall surfaces 112Is defining the inlet region 112 is set to coincide with the position of the connection position 114 in the axis O direction.
  • inner wall surface 112Is defining inlet region 112 has a semicircular arc shape and is smoothly connected at connection position 114 to each of inner wall surfaces 115Is of two adjacent introduction regions 113 in the cross section.
  • FIG. 28 shows a case where the radius of curvature R in the cross section shown in FIG. 28 is less than 0.5 times the distance L between inner wall surfaces 115Is of adjacent introduction regions 113 in the cross section (R ⁇ 0.5 ⁇ L).
  • the inner wall surface 115Is of two adjacent introduction regions 113 in the cross section for example the inner wall surface 115Is of the introduction region 113 on the left side in the figure is smoothly connected to the inner wall surface 115Is at a connection position 114.
  • the inner wall surface 115Is of the introduction region 113 on the right side in the figure is smoothly connected to the inner wall surface 112Is of the entrance region 112 continuing from the inner wall surface 115Is at a connection position 114.
  • the connection portion will have a shape that slopes downstream. Therefore, when the radius of curvature R is less than 0.5 times the distance L (R ⁇ 0.5 ⁇ L), the upstream end 111 is configured with a flat surface 112p, and the inner wall surface 112Is of the inlet region 112 on the left side in the figure and the inner wall surface 112Is of the inlet region 112 on the right side in the figure are smoothly connected to the flat surface 112p. In this case, the distance in the axis O direction between the flat surface 112p and the connection position 114 is equal to the radius of curvature R.
  • FIG. 29 shows a case where the radius of curvature R in the cross section shown in FIG. 29 exceeds 0.5 times the distance L between inner wall surfaces 115Is of adjacent introduction regions 113 in the cross section (R>0.5 ⁇ L).
  • the inner wall surface 115Is of two adjacent introduction regions 113 in the cross section for example the inner wall surface 115Is of the introduction region 113 on the left side in the figure is smoothly connected to the inner wall surface 115Is at a connection position 114.
  • the inner wall surface 115Is of the introduction region 113 on the right side in the figure is smoothly connected to the inner wall surface 112Is of the entrance region 112 continuing from the inner wall surface 115Is at a connection position 114. Then, the inner wall surface 112Is of the inlet area 112 on the left side in the figure and the inner wall surface 112Is of the inlet area 112 on the right side in the figure are connected.
  • connection portion 112c between the inner wall surface 112Is of the inlet region 112 on the left side in the figure and the inner wall surface 112Is of the inlet region 112 on the right side in the figure has a pointed shape in the cross section shown in FIG.
  • the dashed arc extending from the connection portion 112c is an imaginary line obtained by extending the inner wall surface 112Is of the inlet region 112 on the left side of the figure to the right side of the figure, and an imaginary line obtained by extending the inner wall surface 112Is of the inlet region 112 on the right side of the figure to the left side of the figure, both of which are arcs with a radius of curvature R.
  • FIG. 30A is a schematic cross-sectional view showing the cross section AA in FIG. 26 in the case where the radius of curvature R is less than 0.5 times the distance La (R ⁇ 0.5 ⁇ La).
  • FIG. 30B is a schematic cross-sectional view showing the cross section BB in FIG. 26 in the case where the radius of curvature R is less than 0.5 times the distance La (R ⁇ 0.5 ⁇ La).
  • the shape of the inlet region 112 in both the A-A cross section in FIG. 26 and the B-B cross section in FIG. 26 will be the same as the shape shown in FIG. 28. That is, when the radius of curvature R is less than 0.5 times the distance La (R ⁇ 0.5 ⁇ La), the upstream end 111 in both the A-A cross section in FIG. 26 and the B-B cross section in FIG. 26 will be composed of a flat surface 112p. That is, when the radius of curvature R is less than 0.5 times the distance La (R ⁇ 0.5 ⁇ La), the inlet region 112 will be surrounded by a flat surface 112p all around.
  • the inlet region 112 is formed of an inner wall surface 112Is having a curve with a radius of curvature R in a cross section along the axis O direction, except for the flat surface 112p. Therefore, when air flows into the inlet region 112, the air is easily guided into the inlet region 112, so that air is less likely to separate from the inner circumferential surfaces (inner wall surface 112Is, inner wall surface 115Is) of the inlet region 112 and the introduction region 113. This reduces pressure loss in the first region 101 (introduction flow path 110) and reduces flow path deviation in the first region 101 (introduction flow path 110). This makes it possible to more effectively suppress the risk of flashback.
  • the inner circumferential surface (inner wall surface 112Is) of the inlet region 112 appearing in a cross section of the inlet region 112 along the axial direction O may be formed in a curved shape having a radius of curvature R that is 0.5 times the distance La between the inner circumferential surfaces (inner wall surfaces 115Is) of adjacent introduction regions 113 in the first direction Dr1.
  • the shape of the inlet region 112 in the cross section B-B in Figure 26 will be the same as the shape shown in Figure 28.
  • the upstream end 111 in the cross section B-B in Figure 26 will be composed of a flat surface 112p.
  • the shape of the inlet region 112 in the A-A cross section in FIG. 26 is the same as the shape shown in FIG. 27, and other than the flat surface 112p, the inlet region 112 is formed by the inner wall surface 112Is having a curve with a radius of curvature R in the cross section along the axis O direction. Therefore, when air flows into the inlet region 112, the air is easily guided into the inlet region 112, so that air is less likely to separate from the inner circumferential surfaces (inner wall surface 112Is, inner wall surface 115Is) of the inlet region 112 and the introduction region 113. This reduces the pressure loss in the first region 101 (introduction flow path 110) and reduces the flow path deviation in the first region 101 (introduction flow path 110). This makes it possible to more effectively suppress the risk of flashback.
  • the inner circumferential surface (inner wall surface 112Is) of the inlet region 112 appearing in a cross section of the inlet region 112 along the axial O direction may extend in a direction different from the first direction Dr1 and the second direction Dr2, and may be formed in a curved shape having a radius of curvature R that is 0.5 times the distance Lb between the inner circumferential surfaces (inner wall surfaces 115Is) of adjacent introduction regions 113 in a third direction Dr3 perpendicular to the axial O direction.
  • the shape of the inlet region 112 in the A-A cross section in Figure 26 will be the same as the shape shown in Figure 29.
  • the connection portion 112c in the A-A cross section in Figure 26 will have a pointed shape.
  • the shape of the inlet region 112 is similar to the shape shown in Fig. 27, so that when air flows into the inlet region 112, the air is more easily guided into the inlet region 112. This can reduce pressure loss in the first region 101 (inlet flow path 110) and can reduce flow path deviation in the first region 101 (inlet flow path 110). This can further effectively suppress the risk of flashback.
  • FIG. 33A is a schematic cross-sectional view showing the cross section AA in FIG. 26 in the case where the radius of curvature R exceeds 0.5 times the distance Lb (R>0.5 ⁇ Lb).
  • FIG. 33B is a schematic cross-sectional view showing the cross section BB in FIG. 26 in the case where the radius of curvature R exceeds 0.5 times the distance Lb (R>0.5 ⁇ Lb).
  • the inner circumferential surface (inner wall surface 112Is) of the inlet region 112 appearing in a cross section of the inlet region 112 along the axial O direction may extend in a direction different from the first direction Dr1 and the second direction Dr2, and may be formed in a curved shape having a radius of curvature R that exceeds 0.5 times the distance Lb between the inner circumferential surfaces (inner wall surfaces 115Is) of adjacent introduction regions 113 in a third direction Dr3 perpendicular to the axial O direction.
  • the shape of the entrance region 112 in both the A-A section in FIG. 26 and the B-B section in FIG. 26 will be the same as the shape shown in FIG. 29. That is, when the radius of curvature R is more than 0.5 times the distance Lb (R>0.5 ⁇ Lb), the connection portion 112c has a pointed shape in both the A-A section in FIG. 26 and the B-B section in FIG. 26. In other words, when the radius of curvature R is more than 0.5 times the distance Lb (R>0.5 ⁇ Lb), the entrance region 112 is surrounded by the connection portion 112c having a pointed shape over its entire circumference. Therefore, when the radius of curvature R is more than 0.5 times the distance Lb (R>0.5 ⁇ Lb), the flat surface 112p is not formed.
  • FIG. 35B is a schematic cross-sectional view showing the cross section BB in FIG. 26 in the case where the formation of flat surface 112p and connecting portion 112c having a pointed shape is avoided over the entire periphery of inlet region 112.
  • the inner wall surface 112Is of the inlet region 112 that appears in a cross section including the central axis O has a constant radius of curvature R from the connection position 141 to the upstream end 111, but the radius of curvature R may be varied from the connection position 141 to the upstream end 111.
  • Figure 35A is a schematic cross-sectional view showing the A-A section in Figure 26 when the shape of the inner wall surface 112Is of the inlet region 112, as seen in a cross section including the central axis O over the entire circumference of the inlet region 112, is an ellipse having a major axis parallel to the direction of the axis O.
  • Figure 35B is a schematic cross-sectional view showing the B-B section in Figure 26 when the shape of the inner wall surface 112Is of the inlet region 112, as seen in a cross section including the central axis O over the entire circumference of the inlet region 112, is an ellipse having a major axis parallel to the direction of the axis O.
  • the shape of the inner wall surface 112Is of the inlet region 112, as seen in a cross section including the central axis O over the entire circumference of the inlet region 112, may be, for example, an elliptical shape having a major axis parallel to the axis O.
  • the major axis radius be three times or more the distance L.
  • first direction Dr1 and the second direction are perpendicular to each other, but they do not necessarily have to be perpendicular to each other.
  • each of the burners 42 includes one inlet passage 110, one mixing passage 46, and four fuel nozzles 43 arranged around one mixing passage 46, and is configured so that fuel is injected into one mixing passage 46 from the four surrounding fuel nozzles 43, but each of the burners 42 may have only one fuel nozzle 43, or it is sufficient that each of the burners 42 has at least one fuel nozzle 43.
  • a burner assembly 32 is a burner assembly 32 including a plurality of burners 42 for mixing fuel and air.
  • Each of the plurality of burners 42 includes a flow path 100 through which air can flow.
  • the flow path 100 includes a first region 101 (inlet flow path 110) in which a fuel injection hole (fuel injection hole 53) is formed, which is an upstream region of the air flow, and a second region 102 (mixing flow path 46) in which the fuel injected from the injection hole (fuel injection hole 53) and the air are mixed, which is an upstream region of the first region 101 (inlet flow path 110).
  • the first region 101 extends from an upstream end 111 of the flow path 100 to a connection position (inlet 48) with the second region 102 (mixing flow path 46).
  • an injection hole fuel injection hole 53
  • the first region 101 (inlet flow passage 110) has at least one protrusion 51 that protrudes radially inward of the flow passage 100 and in which an injection hole (fuel injection hole 53) is formed, and at least one peripheral wall portion 116 that is adjacent to the at least one protrusion 51 in the circumferential direction of the flow passage 100 and does not have the protrusion 51.
  • the second cross-sectional area S2 in the second region 102 (mixing flow passage 46) is smaller than the first cross-sectional area S1 in the first region 101 (inlet flow passage 110).
  • the fuel injection hole (fuel injection hole 53) is formed in the first region 101 (inlet flow passage 110) at a position closer to the connection position (inlet 48) than the upstream end 111.
  • the air is rectified in the process of reaching the vicinity of the injection hole (fuel injection hole 53) (the vicinity of the fuel jet) in the first region 101 (inlet flow passage 110). Therefore, the influence of the turbulence of the air flow before flowing into the first region 101 (inlet flow passage 110) is suppressed, and a region with a low flow rate and high fuel concentration is unlikely to be formed in the vicinity of the injection hole (fuel injection hole 53) (the vicinity of the fuel jet). As a result, the risk of flashback can be suppressed.
  • the first distance L1 in the extension direction between the upstream end 111 of the flow passage 100 and the center position of the opening 53ap in the protrusion 51 of the injection hole (fuel injection hole 53) may be at least 1 time the equivalent diameter (inner diameter Dm) of the second region 102 (mixing flow passage 46) when viewed from the extension direction.
  • the configuration (2) above allows the air to be effectively rectified in the first region 101 (inlet flow passage 110), effectively reducing the risk of flashback.
  • the first distance L1 may be 5 times or more the equivalent diameter (inner diameter Dm).
  • the above configuration (3) allows the air to be more effectively rectified in the first region 101 (inlet flow passage 110), thereby more effectively reducing the risk of flashback.
  • the tip portion 432 is formed so that the amount of radial inward protrusion gradually increases as it approaches the straight portion (base end 431) upstream of the straight portion (base end 431), making it possible to suppress separation of the air flow from the tip portion 432 toward the straight portion (base end 431). Therefore, an area with low flow velocity and high fuel concentration is less likely to form near the injection hole (fuel injection hole 53) (near the fuel jet). As a result, the risk of flashback can be suppressed.
  • the second distance L2 in the extension direction between the connection position (inlet 48) and the upstream end 44u of the straight section (base end 431) may be less than or equal to 1 time the equivalent diameter (inner diameter Dm) of the second region 102 (mixing flow channel 46) when viewed from the extension direction.
  • the above configuration (5) prevents the length of the protrusion 51 along the extension direction from increasing, thereby preventing a low-velocity area from occurring near the wall surface of the flow path 100.
  • the third distance L3 in the extension direction between the connection position (inlet 48) and the center position of the opening 53ap in the protrusion 51 of the injection hole (fuel injection hole 53) is greater than the opening diameter dap of the opening 53ap and is smaller than the second distance L2 in the extension direction between the connection position (inlet 48) and the upstream end 44u in the straight portion (base end 431).
  • the above configuration (6) reduces the risk of flashback because the fuel ejected from the injection hole (fuel injection hole 53) is less likely to form a region of high fuel concentration near the inner wall of the first region 101 (inlet flow passage 110) or the second region 102 (mixing flow passage 46).
  • the surface (top surface 54) of the tip portion 432 may have an arc shape in a cross section along the extension direction.
  • the above configuration (7) reduces the distance from the upstream end 111 of the flow passage 100 to the straight section (base end 431) while making it difficult to disturb the air flow from the tip end 432 to the straight section (base end 431), making it easier to ensure the effect of the present disclosure that a region with high fuel concentration is unlikely to form near the inner wall (wall surface 55s) of the second region 102 (mixing flow passage 46).
  • the surface (top surface 54) of the tip portion 432 may have an elliptical arc shape in a cross section along the extension direction.
  • the air flow from the tip portion 432 to the straight portion (base end portion 431) can be made less likely to be disturbed compared to when the surface (top surface 54) of the tip portion 432 has an arc shape in a cross section along the extension direction.
  • This makes it easier to ensure the effect of the present disclosure, that is, the formation of a region with high fuel concentration is less likely to occur near the inner wall (wall surface 55s) of the second region 102 (mixing flow path 46).
  • the distance from the upstream end 111 of the flow path 100 to the straight portion (base end 431) can be reduced compared to when the surface (top surface 54) of the tip portion 432 has an arc shape in a cross section along the extension direction, and the overall length of the flow path 100 can be prevented from becoming longer.
  • the fourth distance L4 in the extension direction from the upstream end 111 of the flow path 100 to the upstream end 51t of the protrusion 51 may be 0 or greater.
  • the above configuration (9) can reduce the risk of flashback while ensuring the air straightening effect in the first region 101 (inlet flow passage 110).
  • the first region 101 may include an inlet region 112 including an upstream end 111, and an introduction region 113 connected to the inlet region 112 downstream of the inlet region 112.
  • the inlet region 112 may be defined by an inner wall surface (inner wall surface 112Is) formed in a curved shape that is convex toward the inside of the first region 101 (introduction flow passage 110) in a cross section along the extension direction (axis O direction), and may be formed so that the cross-sectional area of the flow passage 100 gradually decreases toward the downstream side.
  • the introduction region 113 may be defined by an inner wall surface (inner wall surface 115Is) formed in a straight line parallel to the extension direction (axis O direction) in a cross section along the extension direction (axis O direction).
  • the above configuration (10) makes it easier for air to be guided into the inlet region 112 when it flows into the inlet region 112, making it harder for air to separate from the inner circumferential surfaces (inner wall surface 112Is, inner wall surface 115Is) of the inlet region 112 and the introduction region 113. This reduces pressure loss in the first region 101 (introduction flow path 110) and reduces flow path deviation in the first region 101 (introduction flow path 110). This makes it possible to more effectively suppress the risk of flashback.
  • the flow paths 100 may be arranged at equal intervals along a first direction Dr1 perpendicular to the extension direction (axis O direction) and a second direction Dr2 perpendicular to the extension direction (axis O direction) and the first direction Dr1.
  • the inner circumferential surface (inner wall surface 112Is) of the inlet region 112 appearing in a cross section of the inlet region 112 along the extension direction (axis O direction) may be formed in a curved shape having a radius of curvature R of 0.5 times the distance La between the inner circumferential surfaces (inner wall surfaces 115Is) of the introduction regions 113 adjacent to each other in the first direction Dr1.
  • the above configuration (11) makes it easier for air to be guided into the inlet region 112 when it flows into the inlet region 112, making it harder for air to separate from the inner circumferential surfaces (inner wall surface 112Is, inner wall surface 115Is) of the inlet region 112 and the introduction region 113. This reduces pressure loss in the first region 101 (introduction flow path 110) and reduces flow path deviation in the first region 101 (introduction flow path 110). This makes it possible to more effectively suppress the risk of flashback.
  • the flow paths 100 may be arranged at equal intervals along a first direction Dr1 perpendicular to the extension direction (axis O direction) and a second direction Dr2 perpendicular to the extension direction (axis O direction) and the first direction Dr1.
  • the inner circumferential surface (inner wall surface 112Is) of the inlet region 112 appearing in a cross section of the inlet region 112 along the extension direction (axis O direction) may extend in a direction different from the first direction Dr1 and the second direction Dr2, and may be formed in a curved shape having a radius of curvature R that is 0.5 times the distance Lb between the inner circumferential surfaces (inner wall surfaces 115Is) of adjacent introduction regions 113 in a third direction Dr3 perpendicular to the extension direction (axis O direction).
  • the above configuration (12) makes it easier for air to be guided into the inlet region 112 when it flows into the inlet region 112, making it harder for air to separate from the inner circumferential surfaces (inner wall surface 112Is, inner wall surface 115Is) of the inlet region 112 and the introduction region 113. This reduces pressure loss in the first region 101 (introduction flow path 110) and reduces flow path deviation in the first region 101 (introduction flow path 110). This makes it possible to more effectively suppress the risk of flashback.
  • the flow paths 100 may be arranged at equal intervals along a first direction Dr1 perpendicular to the extension direction (axis O direction) and a second direction Dr2 perpendicular to the extension direction (axis O direction) and the first direction Dr1.
  • the inner circumferential surface (inner wall surface 112Is) of the inlet region 112 appearing in a cross section of the inlet region 112 along the extension direction (axis O direction) may extend in a direction different from the first direction Dr1 and the second direction Dr2, and may be formed in a curved shape having a radius of curvature R that exceeds 0.5 times the distance Lb between the inner circumferential surfaces (inner wall surfaces 115Is) of adjacent introduction regions 113 in a third direction Dr3 perpendicular to the extension direction (axis O direction).
  • the above configuration (13) makes it easier for air to be guided into the inlet region 112 when it flows into the inlet region 112, making it harder for air to separate from the inner circumferential surfaces (inner wall surface 112Is, inner wall surface 115Is) of the inlet region 112 and the introduction region 113. This reduces pressure loss in the first region 101 (introduction flow path 110) and reduces flow path deviation in the first region 101 (introduction flow path 110). This makes it possible to more effectively suppress the risk of flashback.
  • the flow path 100 may include a first flow path 100a and a second flow path 100b closest to the first flow path 100a.
  • the upstream end 51t of the protrusion 51 may be located downstream of the upstream end 111 of the flow path 100.
  • the inner diameter Du of the introduction flow path 110 can be adjusted by appropriately adjusting the thickness t1 of the partition (partition portion 118 (118ab)) that separates the introduction flow path 110 (110a) in the first flow path 100a from the introduction flow path 110 (110b) in the second flow path 100b.
  • a gas turbine combustor (combustor 4) includes a burner assembly 32 having any of the configurations (1) to (14) above, and a combustion liner 25 that forms a space downstream of the burner assembly 32 in which a flame is formed.
  • the configuration (15) above includes a burner assembly 32 having any of the configurations (1) to (14) above, which reduces the risk of flashback. Therefore, the gas turbine combustor (combustor 4) can be used stably.
  • a gas turbine 1 includes a compressor 2, a gas turbine combustor (combustor 4) configured to receive air compressed by the compressor 2 and fuel and to burn the fuel to generate combustion gas, and a turbine 6 driven by the combustion gas generated in the gas turbine combustor (combustor 4).
  • the gas turbine combustor (combustor 4) is the gas turbine combustor (combustor 4) having the configuration described in (15) above.
  • the configuration of (16) above includes a gas turbine combustor (combustor 4) configured as in (15) above, which reduces the risk of flashback and enables the gas turbine 1 to be operated stably.

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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/JP2024/010904 2023-03-29 2024-03-21 バーナー集合体、ガスタービン燃焼器及びガスタービン Ceased WO2024203677A1 (ja)

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DE112024000649.3T DE112024000649T5 (de) 2023-03-29 2024-03-21 Brenneranordnung, gasturbinenbrennkammer und gasturbine
CN202480015290.9A CN120693484A (zh) 2023-03-29 2024-03-21 喷燃器集合体、燃气轮机燃烧器及燃气轮机
JP2025510617A JPWO2024203677A1 (https=) 2023-03-29 2024-03-21
KR1020257027065A KR20250133784A (ko) 2023-03-29 2024-03-21 버너 집합체, 가스 터빈 연소기 및 가스 터빈

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2014115072A (ja) * 2012-12-05 2014-06-26 General Electric Co <Ge> ガス・タービン・エンジンの燃焼器用燃料ノズル
JP2015001371A (ja) * 2013-06-13 2015-01-05 ゼネラル・エレクトリック・カンパニイ 燃料噴射ノズルおよびその製造方法
JP2018189285A (ja) * 2017-04-28 2018-11-29 三菱日立パワーシステムズ株式会社 燃料噴射器及びガスタービン
JP2021173191A (ja) * 2020-04-22 2021-11-01 三菱パワー株式会社 バーナー集合体、ガスタービン燃焼器及びガスタービン

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6941576B2 (ja) 2018-03-26 2021-09-29 三菱パワー株式会社 燃焼器及びそれを備えるガスタービン

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2014115072A (ja) * 2012-12-05 2014-06-26 General Electric Co <Ge> ガス・タービン・エンジンの燃焼器用燃料ノズル
JP2015001371A (ja) * 2013-06-13 2015-01-05 ゼネラル・エレクトリック・カンパニイ 燃料噴射ノズルおよびその製造方法
JP2018189285A (ja) * 2017-04-28 2018-11-29 三菱日立パワーシステムズ株式会社 燃料噴射器及びガスタービン
JP2021173191A (ja) * 2020-04-22 2021-11-01 三菱パワー株式会社 バーナー集合体、ガスタービン燃焼器及びガスタービン

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DE112024000649T5 (de) 2025-11-13

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