WO2020203268A1 - Chambre de combustion et turbine à gaz - Google Patents

Chambre de combustion et turbine à gaz Download PDF

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Publication number
WO2020203268A1
WO2020203268A1 PCT/JP2020/011786 JP2020011786W WO2020203268A1 WO 2020203268 A1 WO2020203268 A1 WO 2020203268A1 JP 2020011786 W JP2020011786 W JP 2020011786W WO 2020203268 A1 WO2020203268 A1 WO 2020203268A1
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WO
WIPO (PCT)
Prior art keywords
inner cylinder
nozzle
fuel
air
flow path
Prior art date
Application number
PCT/JP2020/011786
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English (en)
Japanese (ja)
Inventor
虹造 青木
敏彦 齋藤
公宣 戸貝
Original Assignee
三菱重工業株式会社
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 三菱重工業株式会社 filed Critical 三菱重工業株式会社
Publication of WO2020203268A1 publication Critical patent/WO2020203268A1/fr

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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
    • 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
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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

Definitions

  • the present invention relates to combustors and gas turbines.
  • the present application claims priority with respect to Japanese Patent Application No. 2019-072827 filed in Japan on April 5, 2019, the contents of which are incorporated herein by reference.
  • a dual-fired combustor capable of burning gas fuel and oil fuel is known.
  • oil fuel is burned by such a dual-fired combustor, a technique of injecting water together with oil fuel into a combustion cylinder is known.
  • Patent Document 1 discloses a configuration in which a water supply unit is provided in an air flow path formed between an inner peripheral surface of an outer cylinder and an outer peripheral surface of an inner cylinder.
  • the air flow path formed in the combustor of Patent Document 1 includes an inversion portion in which the flow direction is reversed at the rear end of the inner cylinder.
  • the air that has passed through the reversing portion is supplied to the fuel nozzle that injects fuel into the inner cylinder.
  • the water supply unit is provided before the reversing unit in the air flow path and supplies water or steam to the air flowing through the air flow path.
  • the flame temperature in the combustor is reduced by supplying water or steam to the air in the water supply unit, and NOx (nitrogen oxide), soot, etc. are reduced.
  • the water supply unit is supplied to the air flow path between the outer cylinder and the inner cylinder. Therefore, the water supplied from the water supply unit to the air flow path tends to adhere to the inner peripheral surface on the radial outer side of the reversing portion due to the centrifugal force acting on the water at the reversing portion. When water adheres to the inner peripheral surface of the reversing portion, it becomes difficult for the water to reach the flame. As a result, there is room for improvement in the effect of reducing the flame temperature in the combustor and reducing NOx and soot.
  • the present invention has been made in view of the above circumstances, and an object of the present invention is to provide a combustor and a gas turbine capable of further reducing NOx, soot, and the like.
  • the combustor includes an outer cylinder, an inner cylinder, a plurality of fuel nozzles, an air flow path portion, a swirl, and a water injection portion.
  • the outer cylinder has a tubular shape extending in the axial direction.
  • the inner cylinder is provided inside the outer cylinder in the radial direction.
  • the inner cylinder has a tubular shape extending in the axial direction.
  • the plurality of fuel nozzles are provided in the inner cylinder.
  • the fuel nozzle has a fuel injection portion for injecting fuel at the tip portion.
  • the air flow path portion allows air introduced from the outside between the inner peripheral surface of the outer cylinder and the outer peripheral surface of the inner cylinder to flow to the first side in the axial direction, and the first side in the axial direction of the inner cylinder.
  • the air flow direction is reversed at the end of the air and the air is sent into the inner cylinder.
  • the swirl is provided on the upstream side of the inner cylinder in the air flow direction with respect to the fuel injection portion of the fuel nozzle.
  • the swirl swirls the air flow around the central axis of the fuel nozzle.
  • the water injection portion is provided on the upstream side of the swirl and on the downstream side of the end portion of the inner cylinder in the air flow direction in the inner cylinder.
  • the water injection unit injects water into the inner cylinder from the outer peripheral surface of the fuel nozzle.
  • the combustor according to the first aspect may further include a pilot nozzle and a guide vane.
  • the pilot nozzles are provided inside the inner cylinder in the radial direction of the plurality of fuel nozzles.
  • the guide vane is provided inside the end of the inner cylinder in the radial direction.
  • the guide vane guides the air sent into the inner cylinder by reversing the flow direction of the air in the air flow path portion toward the second side in the axial direction.
  • the water injection unit may be provided on the downstream side of the inner cylinder in the air flow direction with respect to the guide vane. With this configuration, the flow direction of the air that has passed through the guide vanes in the inner cylinder is along the axial direction.
  • the fuel nozzle according to the first or second aspect may include a tapered portion.
  • the tapered portion is provided between the nozzle body portion on the first side in the axial direction and the tip portion on the second side in the axial direction.
  • the outer diameter of the tapered portion gradually decreases toward the second side in the axial direction.
  • the water injection portion may be provided on the tapered portion.
  • the water injection unit according to any one of the first to third aspects has a plurality of nozzle holes provided at intervals in the circumferential direction of the fuel nozzle. You may do so. With this configuration, by injecting water from a plurality of nozzle holes in the circumferential direction, more droplets can be supplied to the portion where the fuel is injected from the fuel nozzle.
  • the plurality of nozzle holes according to the fourth aspect may be provided at unequal intervals in the circumferential direction of the fuel nozzle.
  • the fuel nozzle according to any one of the first to fifth aspects may include a fuel supply flow path portion and a water supply flow path portion.
  • a plurality of fuel supply flow paths are provided around the central axis, and the fuel is supplied toward the fuel injection section.
  • the water supply flow path portion supplies water to the water injection portion.
  • the water supply flow path portion is provided between the outer peripheral surface of the fuel nozzle and the fuel supply flow path portion, and is provided at intervals in the circumferential direction about the central axis.
  • the water supply flow path portion of the sixth aspect is provided at a distance between the outer peripheral surface of the fuel nozzle and the gas supply flow path portion.
  • the heat from the high-temperature air flowing in the inner cylinder is electrically conducted to the portion radially inside the water supply flow path portion through between the water supply flow path portions. Therefore, the temperature difference generated inside the fuel nozzle can be suppressed, and the thermal stress inside the fuel nozzle can be suppressed.
  • the gas turbine includes a combustor according to any one of the first to sixth aspects. By doing so, the commercial value of the gas turbine can be improved.
  • FIG. 1 is a cross-sectional view showing the internal configuration of the combustor of this embodiment.
  • the combustor 10 of this embodiment is provided in the passenger compartment 2 of the gas turbine 1.
  • the combustor 10 is of a dual type capable of gas-fired and oil-fired. Compressed air generated by the compressor of the gas turbine 1 (not shown) is introduced into the combustor 10.
  • the combustor 10 injects fuel into the introduced compressed air to generate high-temperature and high-pressure combustion gas.
  • the combustor 10 includes an outer cylinder 11, an inner cylinder 12, a tail cylinder 13, a back wall 14, a pilot nozzle 21, a main nozzle (fuel nozzle) 22, an air flow path portion R, a main swirl 29, and the like. It mainly includes a water injection unit 30.
  • the outer cylinder 11 is supported by the passenger compartment 2 of the gas turbine 1.
  • the outer cylinder 11 is formed in a tubular shape extending in the axial direction Da where the central axis O1 extends.
  • the inner cylinder 12 is provided inside the radial Dr centering on the central axis O1 with respect to the outer cylinder 11.
  • the inner cylinder 12 has a tubular shape extending in the axial direction Da.
  • the end portion 12a of the first side Da1 of the inner cylinder 12 in the axial direction Da is located inside the radial direction Dr of the end portion 11a of the first side Da1 of the outer cylinder 11 in the axial direction Da1.
  • the end portion 12b of the second side Da2 of the inner cylinder 12 in the axial direction Da is arranged on the second side Da2 of the end portion 11b of the second side Da2 of the outer cylinder 11 in the axial direction Da.
  • the inner cylinder 12 in this embodiment illustrates a case where the inner cylinder 12 has a cylindrical portion 51 (described later) at the end portion 12a of the first side Da1 in the axial direction Da1.
  • the tail cylinder 13 is provided on the outer side of the radial Dr of the end portion 12b of the second side Da2 of the inner cylinder 12.
  • the tail cover 13 has a tubular shape extending in the axial direction Da.
  • the back wall 14 closes the end portion 11a of the first side Da1 of the outer cylinder 11 in the axial direction Da1.
  • the back wall 14 has a guide surface 15 continuous with the circumferential direction Dc around the central axis O1.
  • the guide surface 15 is a curved surface that is concave on the first side Da1 in the axial direction Da when viewed from a direction orthogonal to the central axis O1.
  • the guide surface 15 is arranged at intervals with respect to the end portion 12a of the first side Da1 of the inner cylinder 12.
  • the pilot nozzle 21 is provided along the central axis O1 of the inner cylinder 12.
  • the pilot nozzle 21 injects fuel supplied from the outside from the tip portion 21a. A flame is generated by igniting the fuel injected from the pilot nozzle 21.
  • the pilot nozzle 21 includes a pilot cone 24.
  • the pilot cone 24 is formed in a tubular shape that surrounds the tip portion 21a of the pilot nozzle 21 from the outer peripheral side.
  • the pilot cone 24 has a tapered cone portion 24c.
  • the inner diameter of the tapered cone portion 24c gradually increases from the vicinity of the tip portion 21a of the pilot nozzle 21 toward the generation direction of the flame.
  • the tapered cone portion 24c regulates the diffusion range and direction of the flame and enhances the flame retention property.
  • pilot swirl 28 is provided between the outer peripheral surface of the pilot nozzle 21 and the inner peripheral surface of the pilot cone 24.
  • the pilot swala 28 rectifies the air supplied into the pilot cone 24.
  • a plurality of main nozzles 22 are provided in the inner cylinder 12.
  • the plurality of main nozzles 22 are arranged outside the pilot nozzle 21 in the radial direction Dr and at intervals in the circumferential direction Dc.
  • Each main nozzle 22 extends in the axial direction Da of the inner cylinder 12.
  • FIG. 2 is an enlarged cross-sectional view showing a main part of the combustor.
  • a fuel injection portion 22f for injecting fuel gas, oil
  • Fuel is supplied to the fuel injection unit 22f through a supply pipe 22x provided in the main nozzle 22.
  • the fuel injection unit 22f has a plurality of nozzle holes (not shown) for injecting the supplied fuel.
  • a main burner 25 is provided on the outer peripheral side of the tip portion 22a of the main nozzle 22.
  • the main burner 25 has a tubular shape, and the side 25a close to the pilot cone 24 on the center side of the inner cylinder 12 is formed so as to gradually incline toward the outer peripheral side in the direction of flame generation.
  • a main swirl 29 is provided between the outer peripheral surface of the tip portion 22a of the main nozzle 22 and the inner peripheral surface of the main burner 25.
  • the main swirl 29 swirls the air supplied into the main burner 25 around the central axis O2 of the main nozzle 22.
  • the air flow path portion R includes an introduction flow path portion R1, an inversion flow path portion R2, and an internal flow path portion R3.
  • the introduction flow path portion R1 is formed between the inner peripheral surface 11f of the outer cylinder 11 and the outer peripheral surface 12g of the inner cylinder 12. Air is introduced into the introduction flow path portion R1 from the opening 16 formed in the gap between the end portion 11b of the second side Da2 in the axial direction Da of the outer cylinder 11 and the outer peripheral surface 12g of the inner cylinder 12.
  • a punch metal 27 is provided in the opening 16.
  • the punch metal 27 is a perforated plate in which a large number of holes are formed.
  • the punch metal 27 rectifies the high-temperature and high-pressure air flowing from the compressor (not shown) of the gas turbine 1.
  • the air introduced into the introduction flow path portion R1 flows toward the first side Da1 in the axial direction Da in the introduction flow path portion R1.
  • the reversing flow path portion R2 reverses the flow direction of the air introduced into the introduction flow path portion R1 to the second side Da2 in the axial direction Da.
  • the reversing flow path portion R2 is provided with a cylindrical portion 51 and a guide vane 52.
  • the cylindrical portion 51 forms an end portion 12a of the first side Da1 of the inner cylinder 12.
  • the cylindrical portion 51 has a bell mouth structure that bulges outward from Dr in the radial direction.
  • the guide vanes 52 are provided between the main nozzles 22 adjacent to each other in the circumferential direction Dc.
  • the guide vane 52 is provided inside the radial Dr of the end portion 12a of the inner cylinder 12.
  • the guide vane 52 extends from the vicinity of the tip 51a (the end portion 12a of the inner cylinder 12) of the first side Da1 of the cylindrical portion 51 toward the second side Da2 in the axial direction Da, curved inward in the radial direction Dr. There is.
  • the inner peripheral end portion 52a of the guide vane 52 is arranged on the second side Da2 in the axial direction Da from the end portion 12a of the inner cylinder 12.
  • the reversing flow path portion R2 allows the air introduced into the introduction flow path portion R1 to flow from the inside of the radial direction Dr to the second side Da2 in the axial direction Da by the guide surface 15 of the back wall 14 and the guide vane 52. Invert.
  • the air whose flow direction has been changed by the reversing flow path portion R2 is sent from the inside of the end portion 12a of the inner cylinder 12 to the inner flow path portion R3 in the inner cylinder 12.
  • the guide vane 52 guides the air sent into the inner cylinder 12 with the air flow direction reversed toward the second side Da2 in parallel with the axial direction Da.
  • the internal flow path portion R3 is formed inside Dr in the radial direction of the inner cylinder 12.
  • the air whose flow direction is reversed in the inverted flow path portion R2 is directed from the end portion 12a side of the first side Da1 in the axial direction Da of the inner cylinder 12 to the end portion 12b of the second side Da2 in the internal flow path portion R3. Then, it flows in the distribution direction Df parallel to the central axis O2.
  • the water injection unit 30 is provided on the upstream side (first side in the axial direction Da) of the main swirl 29 in the air flow direction Df in the inner cylinder 12.
  • the main swirl 29 is provided on the upstream side of the flow direction Df with respect to the fuel injection portion 22f of the main nozzle 22.
  • the water injection portion 30 is provided on the downstream side (second side in the axial direction Da) of the end portion 12a of the inner cylinder 12.
  • the water injection unit 30 is provided on the downstream side of the guide vane 52 in the air flow direction Df in the inner cylinder 12.
  • the water injection portion 30 illustrated in this embodiment is provided in the tapered portion 22c of the main nozzle 22.
  • the tapered portion 22c is provided between the nozzle main body portion 22b of the first side Da1 in the axial direction Da and the tip portion 22a of the second side Da2 in the axial direction Da of the main nozzle 22.
  • the outer diameter of the tapered portion 22c gradually decreases toward the second side Da2 in the axial direction Da.
  • FIG. 3 is a cross-sectional view taken along the line AA of FIG.
  • the water injection unit 30 has a plurality of nozzle holes 31.
  • the plurality of nozzle holes 31 are provided in the tapered portion 22c of the main nozzle 22 at equal intervals in the circumferential direction around the central axis O2.
  • Each nozzle hole 31 is formed so as to penetrate the inside and outside of the main nozzle 22. Water is supplied to each nozzle hole 31 from the outside through a water supply flow path portion (not shown) provided in the main nozzle 22.
  • Each nozzle hole 31 ejects water supplied from the water supply flow path portion radially outward from the outer peripheral surface of the main nozzle 22.
  • the direction of water ejection from each nozzle hole 31 may be inclined to the downstream side of the distribution direction Df with respect to the plane orthogonal to the central axis O2.
  • the angle at which water is ejected from each nozzle hole 31, in other words, the inclination angle of the central axis of the nozzle hole 31, is set so that all the water droplets ejected from each nozzle hole 31 pass through the main swirl 29. Is preferable.
  • the cross-sectional shape of the nozzle hole 31 illustrated in the first embodiment has a circular outer diameter.
  • the water ejected from the plurality of nozzle holes 31 is sequentially formed into droplets, and in the internal flow path portion R3 in the inner cylinder 12, together with the air flowing along the flow direction Df, the water on the downstream side of the flow direction Df (axial direction Da). It flows toward the second side Da2).
  • the water droplets flow into the main burner 25 of the main nozzle 22 together with the air, and the swirling force is applied by the main swirl 29.
  • the fuel injected from the fuel injection portion 22f provided at the tip portion 22a of the main nozzle 22 is diffused into the air swirling around the central axis O2 in the main burner 25.
  • the diffused fuel is ignited by the flame generated in the pilot cone 24.
  • the water droplets injected by the water injection unit 30 evaporate in the flame.
  • the water droplets ejected into the air in the inner cylinder 12 from the water injection unit 30 provided on the upstream side of the main swirl 29 are the main swirl 29. It swirls with the air. As a result, the dispersibility of the droplets is improved, and the droplets are atomized and easily evaporated. Therefore, it is possible to further reduce NOx and soot. Further, the droplets evaporate to generate steam, which increases the volume of air containing steam and improves the output of the gas turbine 1.
  • the water injection unit 30 of the first embodiment is provided on the downstream side of the air flow direction Df in the inner cylinder 12 with respect to the guide vane 52.
  • the distribution direction Df of the air passing through the guide vane 52 in the inner cylinder 12 is the axial direction Da. Therefore, it is possible to prevent the water injected from the water injection unit 30 from diffusing toward the pilot nozzle 21 side. Therefore, it is possible to prevent the droplets of water from reaching the flame generated by the pilot nozzle 21, and to prevent the flame of the pilot nozzle 21 from being affected by misfire.
  • the water injection portion 30 of the first embodiment is provided in the tapered portion 22c.
  • the water droplets ejected from the water injection portion 30 provided on the tapered portion 22c efficiently flow toward the main swirl 29 on the downstream side thereof.
  • the water injection unit 30 of the first embodiment has a plurality of nozzle holes 31 provided at intervals in the circumferential direction of the main nozzle 22. By injecting water from a plurality of nozzle holes 31 in the circumferential direction, more droplets can be supplied to the portion where the fuel is injected from the main nozzle 22.
  • the water injection unit 30 is provided in the tapered portion 22c of the main nozzle 22, but the present invention is not limited to this.
  • the water injection portion 30 (plurality of nozzle holes 31) may be provided on the outer peripheral surface of the nozzle body portion 22b of the main nozzle 22.
  • FIG. 4 is a view showing a modified example of the water injection portion of the first embodiment, and is a cross-sectional view of a main nozzle in a portion where a nozzle hole is provided.
  • the injection method of the water injection unit 30 of the first embodiment described above was a method of injecting from a hole (liquid column spray method (LJICF)), but for example, as shown in FIG. 4, the main nozzle 22 is provided.
  • Each nozzle hole 31A may have a slit shape that is continuous in the circumferential direction around the central axis O2 (liquid film spraying method). The water ejected from the slit-shaped nozzle hole 31A becomes a film.
  • the combustor 10B includes an outer cylinder 11, an inner cylinder 12, a tail cylinder 13, a back wall 14, a pilot nozzle 21, a main nozzle (fuel nozzle) 22, and an air flow path portion. It mainly includes R, a main swirl 29, and a water injection unit 30B.
  • FIG. 5 is a cross-sectional view showing the arrangement of nozzle holes of the water injection portion in the second embodiment.
  • the water injection unit 30B has a plurality of nozzle holes 31B.
  • the plurality of nozzle holes 31B are provided in the tapered portion 22c of the main nozzle 22 at unequal intervals in the circumferential direction about the central axis O2 of the main nozzle 22.
  • the nozzle holes 31B are sparsely arranged on the side of the inner cylinder 12 near the inner peripheral surface 12f (upper side of the paper surface in FIG. 5).
  • the nozzle holes 31 are densely arranged on the side close to the pilot nozzle 21 inside Dr in the radial direction. More specifically, in the main nozzle 22, inside the inner cylinder 12 in the radial direction, the nozzle is located at a predetermined angle ⁇ 1 (for example, 15 °) on both sides in the circumferential direction with the position P1 facing the pilot nozzle 21 side as the center. Holes 31B1 are formed respectively. Further, in the main nozzle 22, the nozzle holes 31B are not arranged in a range of less than a predetermined angle ⁇ 2 (for example, 60 °) on both sides in the circumferential direction around the position P2 facing the radial direction Dr outside of the inner cylinder 12. In the main nozzle 22, two nozzle holes 31B2 and 31B3 are arranged in a range of a predetermined angle ⁇ 2 or more centered on the position P2, for example, at a sandwiching angle ⁇ 3 (for example, 30 °).
  • water droplets ejected from the plurality of nozzle holes 31B are collected by the secondary flow G1 of air generated between the inner peripheral surface 12f in the inner cylinder 12 and the main nozzle 22. , It is possible to suppress the aggregation. Further, on the side close to the pilot nozzle 21 inside Dr in the radial direction, water droplets ejected from the plurality of nozzle holes 31B1 are diffused by the secondary flow G2 from the pilot nozzle 21 side. As a result, the distribution of water droplets injected from the water injection unit 30B can be made uniform while suppressing the influence of the secondary flows G1 and G2.
  • the water droplets injected into the air in the inner cylinder 12 from the water injection unit 30B provided on the upstream side of the main swirl 29 swirl together with the air in the main swirl 29.
  • the dispersibility of the droplets is improved, and the droplets are atomized and easily evaporated.
  • the droplets evaporate to generate steam, which increases the volume of air containing steam and improves the output of the gas turbine 1.
  • FIG. 6 is a cross-sectional view showing a flow path layout in the main nozzle according to the third embodiment.
  • the combustor 10C includes an outer cylinder 11, an inner cylinder 12, a tail cylinder 13, a back wall 14, a pilot nozzle 21, a main nozzle (fuel nozzle) 22C, and an air flow path portion. It mainly includes R, a main swirl 29, and a water injection unit 30.
  • each main nozzle 22C includes an oil supply flow path portion 41, a gas supply flow path portion (fuel supply flow path portion) 42, and a water supply flow path portion 43.
  • the oil supply flow path portion 41, the gas supply flow path portion 42, and the water supply flow path portion 43 are formed in the main nozzle 22C.
  • the oil supply flow path portion 41 is provided along the central axis O2 of the main nozzle 22C.
  • the oil supply flow path portion 41 supplies fuel oil for oil burning to the fuel injection portion 22f from the outside.
  • the gas supply flow path portion 42 is provided on the outer side in the radial direction of the oil supply flow path portion 41.
  • a plurality of gas supply flow path portions 42 are provided around the central axis O2 at intervals. Each gas supply flow path portion 42 extends in parallel with the central axis O2.
  • the gas supply flow path portion 42 supplies fuel gas for gas cooking to the fuel injection portion 22f from the outside.
  • the water supply flow path portion 43 is provided on the outer side in the radial direction with respect to the gas supply flow path portion 42.
  • the water supply flow path portion 43 is provided radially inside the outer peripheral surface of the main nozzle 22C.
  • a plurality of water supply flow path portions 43 are provided at intervals in the circumferential direction about the central axis O2.
  • Each water supply flow path portion 43 extends in parallel with the central axis O2. That is, each water supply flow path portion 43 is arranged between the outer peripheral surface of the main nozzle 22C and the gas supply flow path portion 42, and is provided at intervals in the circumferential direction.
  • the water supply flow path portion 43 supplies water supplied from the outside to each nozzle hole 31 of the water injection portion 30.
  • the water supply flow path portion 43 of the combustor 10C of the third embodiment is provided with a gap between the outer peripheral surface of the main nozzle 22C and the gas supply flow path portion 42.
  • the heat from the high-temperature air flowing in the inner cylinder 12 is thermally conducted to the portion radially inside the water supply flow path portion 43 through the water supply flow path portion 43. Therefore, it is possible to suppress the occurrence of a temperature distribution inside the main nozzle 22C and suppress the thermal stress inside the main nozzle 22C.
  • the water droplets ejected into the air inside the inner cylinder 12 from the water injection unit 30 provided on the upstream side of the main swirl 29 are the main swirl 29. Turns with the air. As a result, the dispersibility of the droplets is improved, and the droplets are atomized and easily evaporated. Therefore, it is possible to further reduce NOx and soot. Further, the droplets evaporate to generate steam, which increases the volume of air containing steam and improves the output of the gas turbine 1.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Abstract

Une chambre de combustion (10) est pourvue d'un cylindre externe (11), d'un cylindre interne (12), d'une pluralité de buses principales (22), de parties de canal d'écoulement d'air (R), d'éléments de turbulence principaux (29) et de parties de projection d'eau (30). Chacune des buses principales (22) comporte, au niveau d'une pointe (22a), une partie de projection de carburant (22f) permettant de projeter un carburant. Chacun des éléments de turbulence principaux (29) est disposé sur le côté amont de la partie de projection de carburant (22f) de la buse principale correspondante (22), dans la direction de circulation d'air (Df) dans le cylindre interne (12). L'élément de turbulence principal (29) amène l'écoulement d'air à tourner autour de l'axe central (O2) (axe) de la buse principale (22). La partie de projection d'eau correspondante (30) est agencée sur le côté amont de l'élément de turbulence principal (29) dans le cylindre interne (12) et le côté aval d'une partie d'extrémité (12a) du cylindre interne (12) dans la direction de circulation d'air (Df). La partie de projection d'eau (30) projette l'eau dans le cylindre interne (12) depuis la surface circonférentielle externe (12g) de la buse principale (22).
PCT/JP2020/011786 2019-04-05 2020-03-17 Chambre de combustion et turbine à gaz WO2020203268A1 (fr)

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JP2019072827A JP7171496B2 (ja) 2019-04-05 2019-04-05 燃焼器及びガスタービン
JP2019-072827 2019-04-05

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WO2020203268A1 true WO2020203268A1 (fr) 2020-10-08

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004077076A (ja) * 2002-08-21 2004-03-11 Mitsubishi Heavy Ind Ltd 燃料供給機構
JP2005195284A (ja) * 2004-01-08 2005-07-21 Mitsubishi Heavy Ind Ltd ガスタービン用燃料ノズル、ガスタービン用燃焼器、ガスタービン用燃焼器の燃焼方法
JP2015129490A (ja) * 2014-01-08 2015-07-16 三菱日立パワーシステムズ株式会社 燃焼器およびガスタービン

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2004077076A (ja) * 2002-08-21 2004-03-11 Mitsubishi Heavy Ind Ltd 燃料供給機構
JP2005195284A (ja) * 2004-01-08 2005-07-21 Mitsubishi Heavy Ind Ltd ガスタービン用燃料ノズル、ガスタービン用燃焼器、ガスタービン用燃焼器の燃焼方法
JP2015129490A (ja) * 2014-01-08 2015-07-16 三菱日立パワーシステムズ株式会社 燃焼器およびガスタービン

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