WO2012124467A1 - ガスタービン燃焼器およびガスタービン - Google Patents
ガスタービン燃焼器およびガスタービン Download PDFInfo
- Publication number
- WO2012124467A1 WO2012124467A1 PCT/JP2012/054913 JP2012054913W WO2012124467A1 WO 2012124467 A1 WO2012124467 A1 WO 2012124467A1 JP 2012054913 W JP2012054913 W JP 2012054913W WO 2012124467 A1 WO2012124467 A1 WO 2012124467A1
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- Prior art keywords
- combustor
- gas turbine
- top hat
- fuel injection
- nozzle
- Prior art date
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/54—Reverse-flow combustion chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
Definitions
- the present invention relates to a premixed combustion type gas turbine combustor and a gas turbine to which the combustor is applied.
- the gas turbine combustor of the premixed combustion method burns after mixing fuel and compressed air in advance. According to this premixed combustion type gas turbine combustor, it is effective to make the fuel concentration uniform or to reduce NOx.
- Such a premixed combustion type gas turbine combustor is conventionally known (see, for example, Patent Document 1, Patent Document 2, Patent Document 3, and Patent Document 4).
- Uniform fuel concentration is effective in reducing NOx (nitrogen oxide), but since the mixed state of the premixed gas in each main nozzle is substantially equal, the combustion state of each main burner becomes equal, and the combustor The heat distribution in the central axis direction in the combustor is equal throughout the entire circumference. For this reason, a certain area
- the gas turbine combustor (combustor) described in Patent Document 5 aims to prevent the occurrence of combustion vibration.
- This gas turbine combustor introduces airflow into the premixing cylinder by changing the direction of the airflow flowing through the air inflow portion, a cylindrical premixing cylinder provided inside the casing, a combustion cylinder communicating with the premixing cylinder Air flow introduction portion, a pilot nozzle provided on the central axis of the premixing cylinder, and a main premixing nozzle extending substantially parallel to the pilot nozzle and provided at equal central angular intervals in the premixing cylinder
- the main premixing nozzle has a fuel rod for flowing fuel on the central axis, and a downstream fuel injection peg attached to the fuel rod at equal central angular intervals and extending radially outward. Upstream fuel injection pegs arranged in a plurality of stages along the airflow direction are provided on the upstream side of the mixing cylinder.
- the present invention solves the above-described problems, and an object thereof is to provide a gas turbine combustor and a gas turbine that can suppress the generation of combustion vibrations in a wide range of frequencies while maintaining low NOx. .
- a gas turbine combustor includes an outer cylinder, an inner cylinder that is provided inside the outer cylinder and forms an air passage between the outer cylinder, and the inner cylinder.
- a pilot nozzle provided along the combustor axial direction at the center of the inner cylinder, and a plurality of main nozzles provided on the inner peripheral surface of the inner cylinder so as to surround the pilot nozzle along the circumferential direction,
- the gas turbine combustor is provided in a circumferential direction inside the air passage.
- a top hat nozzle that mixes fuel with the combustion air before reaching the main nozzle, and changes the fuel injection position of the top hat nozzle in the combustor axial direction.
- this gas turbine combustor by changing the fuel injection position in the combustor axial direction, there are many combustion vibrations of different frequencies, and instantaneously the phase difference of the frequency of combustion vibrations is increased. Arise. For this reason, the mixing state of the premixed gas is instantaneously different, the combustion state on the downstream side of each main nozzle is instantaneously different, and the heat distribution in the combustor axial direction is instantaneously distributed over the entire circumference of the combustor. Different. For this reason, concentrated heat generation in the combustor is suppressed, and combustion vibration can be suppressed. Moreover, since the mixed state of the premixed gas is equal in a predetermined time unit, the fuel concentration is made uniform. As a result, it is possible to suppress the occurrence of combustion vibrations in a wide range of frequencies while maintaining low NOx.
- a plurality of the top hat nozzles are provided in the circumferential direction, and the positions in the axial direction of the combustor are regularly changed.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies can be obtained while maintaining low NOx by the top hat nozzle, and manufacturing is easy due to regular arrangement. Therefore, the manufacturing cost of the gas turbine combustor can be reduced.
- a plurality of the top hat nozzles are provided in the circumferential direction, and the positions in the combustor axial direction are irregularly changed.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies can be obtained while maintaining low NOx by the top hat nozzle, and there are more combustion vibrations at different frequencies.
- the phase difference of the frequency of combustion vibration is more finely generated, so that combustion vibration in a wider range of frequencies including the specified combustion vibration can be suppressed, so that the effect of suppressing the generation of combustion vibrations in a wide range of frequencies is suppressed.
- Remarkably can be obtained.
- the top hat nozzle includes a plurality of top hat nozzles arranged in a circumferential direction and arranged by changing the position of the combustor axial direction, and the top hat nozzle group Are arranged in the axial direction of the combustor.
- low NOx by the top hat nozzle is maintained by one top hat nozzle group in which a plurality of top hat nozzles are provided in the circumferential direction and arranged by changing the position in the combustor axial direction.
- the effect of suppressing the occurrence of combustion vibrations in a wide range of frequencies can be obtained.
- the effect of suppressing the occurrence of combustion vibrations in a wide range of frequencies can be obtained synergistically.
- the top hat nozzle is formed with a fuel injection port for injecting fuel in the middle of extending in the combustor axial direction, and a plurality of the top hat nozzles are provided in the circumferential direction.
- the position of the fuel injection port in the combustor axial direction is regularly changed and arranged.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies can be obtained while maintaining low NOx by the top hat nozzle, and manufacturing is easy due to regular arrangement. Therefore, the manufacturing cost of the gas turbine combustor can be reduced. Moreover, since the top hat nozzle extends in the combustor axial direction, the position of the fuel injection port in the combustor axial direction can also be changed by changing the axial arrangement, so parts can be shared. Therefore, it is possible to achieve commonality and prevent an increase in the manufacturing cost of the gas turbine combustor.
- the top hat nozzle is formed with a fuel injection port for injecting fuel in the middle of extending in the combustor axial direction, and a plurality of the top hat nozzles are provided in the circumferential direction.
- the position of the fuel injection port in the combustor axial direction is irregularly changed and arranged.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies can be obtained while maintaining low NOx by the top hat nozzle, and there are more combustion vibrations at different frequencies.
- the phase difference of the frequency of combustion vibration is more finely generated, so that combustion vibration in a wider range of frequencies including the specified combustion vibration can be suppressed, so that the effect of suppressing the generation of combustion vibrations in a wide range of frequencies is suppressed.
- the top hat nozzle extends in the combustor axial direction, the position of the fuel injection port in the combustor axial direction can also be changed by changing the axial arrangement, so parts can be shared. Therefore, it is possible to achieve commonality and prevent an increase in the manufacturing cost of the gas turbine combustor.
- gas turbine combustor according to the present invention is characterized in that a plurality of the fuel injection ports are arranged in the axial direction of the combustor.
- the top hat nozzle is formed in an annular shape along the circumferential direction, and a plurality of fuel injection ports for injecting fuel are provided in the circumferential direction. It is characterized by being arranged by changing the position in the axial direction regularly.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies can be obtained while maintaining low NOx by the top hat nozzle, and manufacturing is easy due to regular arrangement. Therefore, it becomes possible to reduce the manufacturing cost of the gas turbine combustor.
- the top hat nozzle is annular, the degree of freedom in designing the arrangement of the fuel injection ports in the circumferential direction is increased.
- a plurality of the top hat nozzles are arranged in the combustor axial direction.
- the top hat nozzle is formed in an annular shape along the circumferential direction, and a plurality of fuel injection ports for injecting fuel are provided in the circumferential direction.
- the fuel injection ports are arranged in such a manner that the positions of the fuel injection ports in the combustor axial direction are changed, and the positions of the fuel injection ports in the circumferential direction are different from each other.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies can be obtained while maintaining low NOx by the top hat nozzle, and manufacturing is easy due to regular arrangement. Therefore, it becomes possible to reduce the manufacturing cost of the gas turbine combustor.
- the top hat nozzle is annular, the degree of freedom in designing the arrangement of the fuel injection ports in the circumferential direction is increased.
- the top hat nozzle is formed in an airfoil shape so as to rectify combustion air introduced into the air passage, and has a fuel injection port for injecting fuel.
- a plurality of the fuel injection ports are provided in the circumferential direction, and the positions of the fuel injection ports in the combustor axial direction are regularly changed.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies can be obtained while maintaining low NOx by the top hat nozzle, and manufacturing is easy due to regular arrangement. Therefore, the manufacturing cost of the gas turbine combustor can be reduced.
- the top hat nozzle is formed in an airfoil shape so as to rectify combustion air introduced into the air passage, and has a fuel injection port for injecting fuel.
- a plurality of the fuel injection ports are provided in the circumferential direction, and the positions of the fuel injection ports in the combustor axial direction are irregularly changed.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies can be obtained while maintaining low NOx by the top hat nozzle, and there are more combustion vibrations at different frequencies.
- the phase difference of the frequency of combustion vibration is more finely generated, so that combustion vibration in a wider range of frequencies including the specified combustion vibration can be suppressed, so that the effect of suppressing the generation of combustion vibrations in a wide range of frequencies is suppressed.
- Remarkably can be obtained.
- gas turbine combustor according to the present invention is characterized in that a plurality of the fuel injection ports are arranged in the axial direction of the combustor.
- the gas turbine of the present invention includes any one of the above gas turbine combustors.
- this gas turbine it is possible to suppress the occurrence of combustion vibrations in a wide range of frequencies while maintaining low NOx. As a result, operation with low NOx and less combustion vibration can be performed.
- FIG. 1 is a schematic configuration diagram of a gas turbine.
- FIG. 2 is a cross-sectional view of the gas turbine combustor according to the first embodiment of the present invention.
- FIG. 3 is an AA arrow view of FIG. 4 is a developed schematic view of C-break D1-D2 of FIG. 3 in the range of B1-B2 of FIG.
- FIG. 5 is a cross-sectional view of the gas turbine combustor according to the second embodiment of the present invention.
- FIG. 6 is an AA cross-sectional enlarged view of FIG.
- FIG. 7 is a developed schematic view of C-break D1-D2 of FIG. 6 in the range of B1-B2 of FIG.
- FIG. 8 is a developed schematic view of C-break D1-D2 of FIG.
- FIG. 9 is a sectional view of a gas turbine combustor according to Embodiment 3 of the present invention.
- FIG. 10 is an AA cross-sectional enlarged view of FIG.
- FIG. 11 is a developed schematic view of C break D1-D2 of FIG. 10 in the range of B1-B2 of FIG.
- FIG. 12 is a sectional view of a gas turbine combustor according to Embodiment 4 of the present invention.
- FIG. 13 is an AA cross-sectional enlarged view of FIG. 14 is a developed schematic view of C-break D1-D2 of FIG. 13 in the range of B1-B2 of FIG.
- FIG. 1 is a schematic configuration diagram of a gas turbine.
- the gas turbine includes a compressor 11, a gas turbine combustor (hereinafter referred to as a combustor) 12, a turbine 13, and an exhaust chamber 14, and a generator (not shown) is connected to the turbine 13. Yes.
- the compressor 11 has an air intake 15 for taking in air, and a plurality of stationary blades 17 and moving blades 18 are alternately arranged in a compressor casing 16.
- the combustor 12 is combustible by supplying fuel to the compressed air (combustion air) compressed by the compressor 11 and igniting it with a burner.
- a plurality of stationary blades 21 and moving blades 22 are alternately arranged in a turbine casing 20.
- the exhaust chamber 14 has an exhaust diffuser 23 that is continuous with the turbine 13.
- a rotor (turbine shaft) 24 is positioned so as to pass through the center of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 14, and an end portion on the compressor 11 side is freely rotatable by a bearing portion 25.
- the end portion on the exhaust chamber 14 side is rotatably supported by the bearing portion 26.
- a plurality of disk plates are fixed to the rotor 24, the rotor blades 18 and 22 are connected, and a drive shaft of a generator (not shown) is connected to the end on the exhaust chamber 14 side.
- the air taken in from the air intake port 15 of the compressor 11 passes through the plurality of stationary blades 21 and the moving blades 22 and is compressed to become high-temperature and high-pressure compressed air.
- Combustion occurs when a predetermined fuel is supplied to the compressed air.
- the high-temperature and high-pressure combustion gas that is the working fluid generated in the combustor 12 passes through the plurality of stationary blades 21 and the moving blades 22 constituting the turbine 13 to drive and rotate the rotor 24. While the generator connected to 24 is driven, the exhaust gas is converted into static pressure by the exhaust diffuser 23 in the exhaust chamber 14 and then released to the atmosphere.
- FIG. 1 is a cross-sectional view of the gas turbine combustor according to the first embodiment
- FIG. 3 is a view taken along the line AA in FIG.
- the inner cylinder 32 is supported so as to form an air passage 30 with a predetermined interval inside the outer cylinder 31, and the tip of the inner cylinder 32 is supported.
- the combustor casing is configured by connecting the tail cylinder 33.
- the pilot tube 35 is disposed in the inner cylinder 32 along the combustor axial direction that is the central portion of the inner cylinder 32 and that is the extending direction of the combustor shaft S.
- the pilot nozzle 35 is provided with a combustion cylinder 35a that is formed in a cylindrical shape with a wide angle at the tip side around the tip part. Further, the pilot nozzle 35 is provided with a pilot swirler 35b between its outer peripheral surface and the inner peripheral surface of the combustion cylinder 35a.
- the inner cylinder 32 includes a plurality of (eight in this embodiment) main nozzles (also referred to as premixing nozzles) 36 so as to surround the pilot nozzle 35 along the circumferential direction on the inner peripheral surface of the inner cylinder 32. It is arranged in parallel with the axis S.
- the main nozzle 36 is provided with an extension cylinder 36a formed in a cylindrical shape around the tip thereof. Further, the main nozzle 36 is provided with a main swirler 36b between its outer peripheral surface and the inner peripheral surface of the extension cylinder 36a.
- the outer cylinder 31 is provided with a top hat portion 34 at its proximal end.
- the top hat portion 34 is disposed along the inner peripheral surface of the base end portion of the outer cylinder 31, and forms a part of the air passage 30 together with the outer cylinder 31, and a base of the cylindrical member 34a. It is comprised with the cover member 34b which obstruct
- the lid member 34b supports the above-described pilot nozzle 35, and a fuel port 35c of the pilot nozzle 35 is disposed outside.
- the fuel port 35c is connected to a pilot nozzle fuel line (not shown) to supply fuel to the pilot nozzle 35.
- the lid member 34b supports the main nozzle 36 described above, and a fuel port 36c of the main nozzle 36 is disposed outside.
- the fuel port 36c is connected to a main nozzle fuel line (not shown) to supply fuel to the main nozzle 36.
- the top hat nozzle 41 is provided in the tubular member 34a of the top hat portion 34 inside the air passage 30 described above. Although not shown in the drawing, the top hat nozzle 41 is provided with a fuel port outside the top hat portion 34, and a fuel is supplied by connecting the top hat nozzle fuel line to the fuel port. Details of the top hat nozzle 41 will be described later.
- a partition wall (not shown) is provided in the cylindrical member 34a of the top hat portion 34 on the base end side of the outer cylinder 31, and the air passage 30 is communicated with the inner cylinder 32 by this partition wall. .
- a rectifying plate 38 is provided between the outer cylinder 31 (cylindrical member 34 a of the top hat portion 34) and the inner cylinder 32 and at the inlet of the air passage 30.
- the rectifying plate 38 is a perforated plate that is provided so as to cover the air passage 30 and in which a large number of holes that connect the upstream side and the downstream side of the air passage 30 are formed.
- a turning portion 39 is provided at a base end portion that forms the air passage 30.
- the turning part 39 substantially reverses the flow path direction of the air passage 30 in cooperation with the partition wall.
- the turning portion 39 is formed with an increased thickness so that the inner surface facing the outer cylinder 31 side approaches the outer cylinder 31 side so as to form a part of the air passage 30.
- a turning vane 39 a is provided inside the inner cylinder 32 and inside the turning portion 39.
- the turning vane 39a extends from the outer side in the radial direction of the main nozzle 36 toward the combustor shaft S, and is curved in a circular arc shape so as to face the front end side of the main nozzle 36 near the position of the main nozzle 36. Has been.
- the fuel injected from the main nozzle 36 and the fuel mixture are mixed by the extension cylinder 36a and flow into the tail cylinder 33 as a swirling flow of the premixed gas by the main swirler 36b. Further, the fuel mixture is mixed with the fuel injected from the pilot nozzle 35, ignited and burned by a not-shown type fire, and is burned into the tail cylinder 33 as combustion gas. At this time, a part of the combustion gas is ejected so as to diffuse into the tail cylinder 33 with a flame, so that the premixed gas flowing into the tail cylinder 33 from each main nozzle 36 is ignited and burned. .
- the flame holding for stable combustion of the lean premixed fuel from the main nozzle 36 can be performed by the diffusion flame by the pilot fuel injected from the pilot nozzle 35. Further, by premixing the fuel by the main nozzle 36, the fuel concentration can be made uniform, thereby reducing NOx.
- a fuel mixture is formed by mixing fuel with compressed air by the top hat nozzle 41 in the air passage 30 to form a low-concentration air-fuel mixture, and then a downstream main nozzle 36 is used as a high-concentration air-fuel mixture.
- the fuel in the air-fuel mixture and the combustion air are mixed more uniformly. Therefore, the generation of the high temperature portion of the combustion gas due to the air-fuel ratio separation can be prevented, and the NOx can be further reduced. be able to.
- top hat nozzle 41 of the present embodiment will be described.
- a plurality of top hat nozzles 41 are provided in the circumferential direction in the air passage 30.
- the top hat nozzle 41 has a columnar shape (for example, a cylindrical shape) extending in a radial direction around the combustor axis S.
- the top hat nozzle 41 is formed with a flow path (not shown) through which fuel is supplied to the inside of the columnar shape, and a fuel injection for injecting fuel to the outside of the columnar shape communicating with the flow path.
- a mouth 41a is formed.
- top hat nozzle 41 is arrange
- several top hat nozzles 41 are arranged together at the position of each main nozzle 36 so that two top hat nozzles 41 are arranged close to each of the eight main nozzles 36 in FIG. May be.
- a plurality of fuel injection ports 41a are provided in the columnar extending direction (indicated by three in FIGS. 2 and 3), and downstream of the compressed air in the air passage 30.
- the number and direction thereof are not limited, and it may be designed so that the fuel is appropriately mixed with the compressed air flowing through the air passage 30.
- top hat nozzle 41 is arrange
- FIG. 4 explains the arrangement of the top hat nozzle 41, and is a developed schematic view taken along line C1-D2 in FIG. 3 in the range B1-B2 in FIG.
- the top hat nozzle 41 shown in FIG. 4 has a circumferential direction D1-D2 in such a manner that the position of B1-B2, which is the extending direction of the combustor axis S, is inclined with respect to the combustor axis S except for orthogonality. In order to line up in a straight line, it is regularly arranged.
- the top hat nozzle 41 is regularly arranged so that the position of B1-B2 that is the extending direction of the combustor shaft S is aligned on the quadratic curve at D1-D2 that is the circumferential direction. It may be changed and arranged.
- the top hat nozzle 41 regularly changes in the extending direction of the combustor axis S.
- the top hat nozzles 41 arranged in the circumferential direction have regularity in the positional relationship changed in the extending direction of the combustor axis S. Means there is. Therefore, as long as the positional relationship changed in the extending direction of the combustor shaft S has regularity, the arrangement may not be arranged on a regular line as shown in FIG.
- top hat nozzle 41 may be arranged in such a manner that the position of B1-B2, which is the extending direction of the combustor shaft S, is irregularly changed from D1-D2 which is the circumferential direction. Good.
- the position of the top hat nozzle 41 that injects the fuel is changed in the extending direction of the combustor shaft S (combustor shaft direction).
- a plurality of top hat nozzles 41 are provided in the circumferential direction, and the position of the combustor shaft S in the extending direction (combustor shaft direction) is regularly changed. Are arranged.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies while maintaining low NOx by the top hat nozzle 41 is obtained, and the manufacturing is easy by regular arrangement. Therefore, the manufacturing cost of the gas turbine combustor 12 can be reduced.
- the generation of combustion vibration is suppressed by the configuration of the top hat nozzle 41 itself that reduces NOx, there is no need to provide a new configuration for generating combustion vibration, and the manufacturing cost of the gas turbine combustor 12 is reduced. There is no problem of increasing the volume or increasing the weight of the gas turbine combustor 12.
- a plurality of top hat nozzles 41 are provided in the circumferential direction, and the position of the combustor shaft S in the extending direction (combustor shaft direction) changes irregularly. Are arranged.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies while maintaining low NOx by the top hat nozzle 41 is obtained, and more combustion vibrations at different frequencies are obtained. Because the phase difference of the frequency of combustion vibration occurs more finely, the combustion vibration in a wider range of frequencies including the specified combustion vibration can be suppressed, so the occurrence of combustion vibrations in a wide range of frequencies is suppressed. The effect can be obtained remarkably. In addition, since the generation of combustion vibration is suppressed by the configuration of the top hat nozzle 41 itself that reduces NOx, there is no need to provide a new configuration for generating combustion vibration, and the manufacturing cost of the gas turbine combustor 12 is reduced. There is no problem of increasing the volume or increasing the weight of the gas turbine combustor 12.
- a configuration in which a plurality of circumferentially arranged and changed positions in the combustor axial direction constitutes one top hat nozzle group, and the top hat nozzle group corresponds to the combustor axis S.
- a plurality of them may be arranged in the extending direction (combustor axial direction).
- a plurality of top hat nozzle groups of the same form among the forms of the first embodiment described above may be arranged in the extending direction of the combustor shaft S, and the top hat nozzle groups of different forms are A plurality of the combustor shafts S may be arranged in the extending direction.
- a low NOx produced by the top hat nozzle 41 is provided by a single top hat nozzle group in which a plurality of top hat nozzles 41 are provided in the circumferential direction and are arranged by changing the position in the combustor axial direction. While maintaining the above, the effect of suppressing the occurrence of combustion vibrations in a wide range of frequencies can be obtained.
- By arranging a plurality of the top hat nozzle groups in the combustor axial direction it becomes possible to obtain synergistically and effectively obtain the effect of suppressing the occurrence of combustion vibrations in a wide range of frequencies.
- top hat nozzles 41 in the top hat nozzle group are provided in the circumferential direction, and the positions of the combustor shaft S in the extending direction (combustor shaft direction) are regularly changed, Since the manufacturing is easy due to the regular arrangement, the manufacturing cost of the gas turbine combustor 12 can be reduced.
- FIG. 5 is a cross-sectional view of the gas turbine combustor according to the second embodiment
- FIG. 6 is an enlarged cross-sectional view taken along the line AA in FIG.
- the gas turbine combustor 12 of the present embodiment employs a top hat nozzle 42 that is different from the top hat nozzle 41 of the gas turbine combustor 12 of the first embodiment described above. Therefore, in the present embodiment, the top hat nozzle 42 will be described, and the same parts as those in the above-described first embodiment will be denoted by the same reference numerals and the description thereof will be omitted.
- a top hat nozzle 42 is provided inside the air passage 30.
- the top hat nozzle 42 is provided with a fuel port outside the top hat portion 34, and a fuel is supplied by connecting a top hat nozzle fuel line to the fuel port.
- top hat nozzles 42 are provided in the circumferential direction in the air passage 30 (indicated by 16 in FIG. 6).
- the top hat nozzle 42 has a columnar shape (for example, a cylindrical shape) extending to the combustor shaft S.
- the top hat nozzle 42 is formed with a flow path (not shown) for supplying fuel to the inside of the columnar shape, and communicates with the flow channel in the extending direction in the middle of the columnar fuel outside.
- a fuel injection port 42a for injection is formed.
- the top hat nozzles 42 are arranged at equal intervals in the circumferential direction as shown in FIG. 6, but may not be equal intervals. For example, several top hat nozzles 42 are arranged at the position of each main nozzle 36 so that two top hat nozzles 42 are arranged close to each of the eight main nozzles 36 in FIG. May be. Further, as shown in FIG. 5, a plurality of fuel injection ports 42 a are provided in the columnar extending direction (indicated by four in FIG. 5), and in the air passage 30, the outer cylinder 31 side, the inner cylinder 32 side, However, the number and direction thereof are not limited, and it may be designed so that fuel is appropriately mixed with the compressed air flowing through the air passage 30.
- FIGS. 7 and 8 illustrate the arrangement of the fuel injection ports 42a of the top hat nozzle 42, and are schematic C1-D2 development views of FIG. 6 in the range B1-B2 of FIG.
- the top hat nozzle 42 shown in FIG. 7 itself is similarly arranged at D1-D2 where the position of B1-B2 which is the extending direction of the combustor shaft S is the circumferential direction.
- the top hat nozzle 42 has a circumferential direction D1 so that the position of B1-B2, which is the extending direction of the combustor shaft S of the fuel injection port 42a, is inclined with respect to the combustor shaft S except for the right angle.
- -D2 is regularly arranged so as to be aligned on a straight line at D2.
- the top hat nozzle 42 has a position of B1-B2 in the extending direction of the combustor shaft S of the fuel injection port 42a on the quadratic curve at D1-D2 in the circumferential direction. You may arrange
- the fuel injection port 42a regularly changes in the extending direction of the combustor shaft S.
- the fuel injection ports 42a of the top hat nozzles 42 arranged in the circumferential direction are changed in the extending direction of the combustor shaft S. This means that the positional relationship is regular. Therefore, as long as the positional relationship changed in the extending direction of the combustor shaft S has regularity, the arrangement may not be arranged on a regular line as shown in FIG.
- the (four) fuel injection ports 42a in the top hat nozzles 42 arranged in the circumferential direction D1-D2 have positions B1-B2 in the extending direction of the combustor shaft S.
- it is regularly changed so as to be aligned on a straight line in the circumferential direction D1-D2 so as to incline except for orthogonality with respect to the extending direction of the combustor axis S, it is not limited to this.
- the position of the fuel injection port 42a in this arrangement and B1-B2, which is the extending direction of the combustor shaft S regularly changes so as to be aligned on a quadratic curve at D1-D2 which is the circumferential direction.
- the arranged fuel injection ports 42a and other regularly arranged fuel injection ports 42a may be mixed.
- top hat nozzle 42 shown in FIG. 8 itself is similarly arranged at D1-D2 in which the position of B1-B2, which is the extending direction of the combustor shaft S, is the circumferential direction.
- the top hat nozzle 42 is arranged such that the position of B1-B2 that is the extending direction of the combustor shaft S of the fuel injection port 42a is irregularly changed in D1-D2 that is the circumferential direction.
- the (four) fuel injection ports 42a in the top hat nozzles 42 arranged in the circumferential direction D1-D2 are combusted in the circumferential direction D1-D2 in each top hat nozzle 42.
- the positions of B1-B2 in the extending direction of the combustor shaft S are irregular, but are arranged at equal intervals in the extending direction of the combustor shaft S.
- the present invention is not limited to this, and although not shown in the drawing, it may be arranged irregularly in the extending direction of the combustor shaft S.
- each (four) fuel injection ports 42a in each top hat nozzle 42 arranged in the circumferential direction D1-D2 has B1-B2 extending direction of the combustor shaft S.
- An arrangement in which the position regularly changes in the circumferential direction D1-D2 with respect to the extending direction of the combustor axis S, and a position of B1-B2 that is the extending direction of the combustor axis S is the circumferential direction D1.
- An arrangement that changes irregularly at -D2 may be mixed.
- the position of the top hat nozzle 42 where the fuel is injected is changed in the extending direction of the combustor shaft S (combustor shaft direction).
- the top hat nozzle 42 has a fuel injection port 42a for injecting fuel in the middle of extending in the extending direction of the combustor shaft S (combustor shaft direction).
- a plurality of the fuel injection ports 42a are provided in the circumferential direction, and the positions of the fuel injection ports 42a in the combustor axial direction are regularly changed.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies while maintaining low NOx by the top hat nozzle 42 is obtained, and manufacture is easy due to regular arrangement. Therefore, the manufacturing cost of the gas turbine combustor 12 can be reduced.
- the generation of combustion vibration is suppressed by the configuration of the top hat nozzle 42 itself for reducing NOx, there is no need to provide a new configuration for generating combustion vibration, and the manufacturing cost of the gas turbine combustor 12 is reduced. There is no problem of increasing the volume or increasing the weight of the gas turbine combustor 12.
- the top hat nozzle 42 extends in the extending direction of the combustor shaft S, fuel injection can be performed even by changing the arrangement in the extending direction. Since the position of the port 42a in the combustor axial direction can be changed, parts can be shared and shared, and a situation in which the manufacturing cost of the gas turbine combustor 12 increases can be prevented.
- the top hat nozzle 42 has a fuel injection port 42a for injecting fuel in the middle of extending in the extending direction of the combustor shaft S (combustor shaft direction).
- a plurality of the fuel injection ports 42a are provided in the circumferential direction, and the positions of the fuel injection ports 42a in the combustor axial direction are irregularly changed.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies while maintaining low NOx by the top hat nozzle 42 is obtained, and more combustion vibrations at different frequencies are obtained. Because the phase difference of the frequency of combustion vibration occurs more finely, the combustion vibration in a wider range of frequencies including the specified combustion vibration can be suppressed, so the occurrence of combustion vibrations in a wide range of frequencies is suppressed. The effect can be obtained remarkably. In addition, since the generation of combustion vibration is suppressed by the configuration of the top hat nozzle 42 itself that reduces MOx, it is not necessary to provide a new configuration for generating combustion vibration, and the manufacturing cost of the gas turbine combustor 12 is reduced. There is no problem of increasing the volume or increasing the weight of the gas turbine combustor 12.
- a plurality of fuel injection ports 42a are arranged in the extending direction of the combustor shaft S (combustor shaft direction).
- FIG. 9 is a cross-sectional view of the gas turbine combustor of the third embodiment
- FIG. 10 is an AA cross-sectional enlarged view of FIG.
- the gas turbine combustor 12 of the present embodiment employs a top hat nozzle 43 that is different from the top hat nozzle 41 of the gas turbine combustor 12 of the first embodiment described above. Therefore, in the present embodiment, the top hat nozzle 43 will be described, and the same parts as those in the above-described first embodiment will be denoted by the same reference numerals and the description thereof will be omitted.
- a top hat nozzle 43 is provided inside the air passage 30.
- a fuel port is provided outside the top hat portion 34, and a fuel is supplied by connecting a top hat nozzle fuel line to the fuel port.
- the top hat nozzle 43 is formed in an annular shape along the circumferential direction in the air passage 30.
- the top hat nozzle 43 has an annular flow path (not shown) for supplying fuel to the inside of the annular shape, and injects fuel to the outside of the annular shape in communication with the flow path.
- a fuel injection port 43a is formed.
- a plurality of fuel injection ports 43a are provided in the circumferential direction (indicated by 16 in FIG. 10), and are directed toward the outer cylinder 31 side and the inner cylinder 32 side in the air passage 30.
- the number and direction thereof are not limited, and it may be designed so that the fuel is appropriately mixed with the compressed air flowing through the air passage 30.
- the fuel injection ports 43a are arrange
- several fuel injection ports 43a are collectively arranged at the position of each main nozzle 36 so that two fuel injection ports 43a are arranged close to each of the eight main nozzles 36 provided in FIG. May be.
- FIG. 11 is a developed schematic view of C break D1-D2 of FIG. 10 in the range of B1-B2 of FIG.
- the top hat nozzle 43 shown in FIG. 11 is provided with an annular central axis inclined with respect to the combustor axis S, and thereby, the B1-B2 extending direction of the combustor axis S of the fuel injection port 43a is set.
- the positions are regularly changed so as to be arranged on a quadratic curve in the circumferential direction D1-D2.
- the annular center axis is provided so as to coincide with the combustor axis S, and the position of B1-B2 that is the extending direction of the combustor axis S of the plurality of fuel injection ports 43a is It may be arranged irregularly changing in the circumferential direction D1-D2.
- the fuel injection position of the top hat nozzle 43 is changed in the extending direction of the combustor shaft S (combustor shaft direction).
- the top hat nozzle 43 is formed in an annular shape along the circumferential direction, and a plurality of fuel injection ports 43a for injecting fuel are provided in the circumferential direction.
- the positions of the ports 43a in the extending direction of the combustor shaft S (combustor shaft direction) are regularly changed.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies while maintaining the low NOx by the top hat nozzle 43 is obtained, and the manufacturing is easy by regular arrangement. Therefore, the manufacturing cost of the gas turbine combustor 12 can be reduced.
- the top hat nozzle 43 is annular, the degree of freedom in designing the arrangement of the fuel injection ports 43a in the circumferential direction is increased.
- the generation of combustion vibration is suppressed by the configuration of the top hat nozzle 43 itself for reducing MOx, it is not necessary to provide a new configuration for generating combustion vibration, and the manufacturing cost of the gas turbine combustor 12 is reduced. There is no problem of increasing the volume or increasing the weight of the gas turbine combustor 12.
- a plurality of top hat nozzles 43 formed in an annular shape along the circumferential direction may be arranged in the extending direction of the combustor shaft S (combustor shaft direction).
- a plurality of top hat nozzle groups of the same form among the forms of the third embodiment described above may be arranged in the extending direction of the combustor shaft S, and top hat nozzle groups of different forms are A plurality of the combustor shafts S may be arranged in the extending direction.
- a plurality of top hat nozzles 43 formed in an annular shape are arranged in the extending direction of the combustor shaft S with the central axis thereof aligned with the combustor shaft S, and the combustors of the mutual fuel injection ports 43a.
- the positions of the fuel injection ports 43a in the circumferential direction may be different from each other so as to change the position in the axial direction.
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies while maintaining the low NOx by the top hat nozzle 43 is obtained, and the manufacturing is easy by regular arrangement. Therefore, the manufacturing cost of the gas turbine combustor 12 can be reduced. Moreover, since the top hat nozzle 43 is annular, the degree of freedom in designing the arrangement of the fuel injection ports 43a in the circumferential direction is increased.
- FIG. 12 is a cross-sectional view of the gas turbine combustor according to the fourth embodiment
- FIG. 13 is an enlarged cross-sectional view taken along the line AA in FIG. 12
- FIG. 14 is a cross-sectional view of FIG.
- FIG. 3 is a developed schematic view of C-break D1-D2.
- the gas turbine combustor 12 of the present embodiment employs a top hat nozzle 44 that is different from the top hat nozzle 41 of the gas turbine combustor 12 of the first embodiment described above. Therefore, in the present embodiment, the top hat nozzle 44 will be described, and the same parts as those in the first embodiment described above will be denoted by the same reference numerals and the description thereof will be omitted.
- a top hat nozzle 44 is provided inside the air passage 30.
- the top hat nozzle 44 is provided with a fuel port outside the top hat portion 34, and a fuel is supplied by connecting the top hat nozzle fuel line to the fuel port.
- a plurality are provided in the circumferential direction in the air passage 30.
- the top hat nozzle 44 has an airfoil shape so as to rectify the compressed air introduced into the air passage 30.
- the top hat nozzle 44 is formed with a flow path (not shown) for supplying fuel to the inside of the airfoil, and communicates with the flow path in the middle of the extending direction of the combustor shaft S.
- a fuel injection port 44a for injecting fuel to the outside of the airfoil is formed.
- top hat nozzles 44 are arranged at equal intervals in the circumferential direction as shown in FIG. Further, as shown in FIG. 13, a plurality of fuel injection ports 44 a are provided in the extending direction of the combustor shaft S (indicated by two in FIG. 12), and toward the both sides in the circumferential direction in the air passage 30. Although provided, there is no limitation on the number and direction thereof, and it may be designed so that the fuel is appropriately mixed with the compressed air flowing through the air passage 30.
- top hat nozzle 44 is arranged by changing the position of injecting the fuel in the extending direction of the combustor shaft S (combustor shaft direction).
- the top hat nozzle 44 shown in FIG. 13 itself is similarly arranged at D1-D2 in which the position of B1-B2, which is the extending direction of the combustor shaft S, is the circumferential direction.
- the top hat nozzle 44 has a circumferential direction D1 such that the position of B1-B2, which is the extending direction of the combustor axis S of the fuel injection port 44a, is inclined with respect to the combustor axis S except for orthogonality.
- -D2 is regularly arranged so as to be aligned on a straight line at D2.
- the top hat nozzle 44 has a position of B1-B2 in the extending direction of the combustor shaft S of the fuel injection port 44a on the quadratic curve at D1-D2 which is the circumferential direction. You may arrange
- the fuel injection port 44a regularly changes in the extending direction of the combustor shaft S.
- the fuel injection port 44a of the top hat nozzle 44 arranged in the circumferential direction is changed in the extending direction of the combustor shaft S. This means that the positional relationship is regular. Therefore, as long as the positional relationship changed in the extending direction of the combustor shaft S has regularity, the arrangement may not be arranged on a regular line as shown in FIG.
- the (two) fuel injection ports 44a provided in the extending direction of the combustor shaft S in the top hat nozzles 44 arranged in the circumferential direction D1-D2 are connected to the combustor shaft S.
- the position of B1-B2 that is the extending direction of the cylinder changes regularly so as to be aligned on a straight line at D1-D2 that is the circumferential direction so as to be inclined with respect to the extending direction of the combustor axis S except for the orthogonal direction. However, this is not the case.
- the positions of the fuel injection ports 44a in this arrangement and the B1-B2 that is the extending direction of the combustor shaft S are regularly changed so as to be aligned on the quadratic curve in the circumferential direction D1-D2.
- the arranged fuel injection ports 44a and other regularly arranged fuel injection ports 44a may be mixed.
- the top hat nozzle 44 itself is similarly arranged at D1-D2 in which the position of B1-B2 that is the extending direction of the combustor shaft S is the circumferential direction, and the fuel injection
- the position of B1-B2 which is the extending direction of the combustor axis S of the port 44a, may be irregularly changed in the circumferential direction D1-D2.
- the present invention is not limited to this, and although not shown in the drawing, it may be arranged irregularly in the extending direction of the combustor shaft S.
- each (two) fuel injection ports 44a provided in the extending direction of the combustor shaft S in each top hat nozzle 44 arranged in the circumferential direction D1-D2 is provided with a combustor.
- the position of B1-B2 which is the extending direction of the axis S changes regularly in the circumferential direction D1-D2 with respect to the extending direction of the combustor axis S, and in the extending direction of the combustor axis S
- An arrangement in which the position of a certain B1-B2 changes irregularly in the circumferential direction D1-D2 may be mixed.
- the fuel injection position of the top hat nozzle 44 is changed in the extending direction of the combustor shaft S (combustor shaft direction).
- the top hat nozzle 44 has a blade shape in such a manner that the compressed air (combustion air) introduced into the air passage 30 is rectified, and fuel injection that injects fuel.
- a plurality of openings 44a are provided in the circumferential direction, and the positions of the fuel injection openings 44a in the extending direction of the combustor shaft S (combustor shaft direction) are regularly changed. .
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies while maintaining low NOx by the top hat nozzle 44 can be obtained, and manufacture is easy by regular arrangement. Therefore, the manufacturing cost of the gas turbine combustor 12 can be reduced.
- the generation of combustion vibration is suppressed by the configuration of the top hat nozzle 44 itself for reducing MOx, it is not necessary to provide a new configuration for generating combustion vibration, and the manufacturing cost of the gas turbine combustor 12 is reduced. There is no problem of increasing the volume or increasing the weight of the gas turbine combustor 12.
- the top hat nozzle 44 has a blade shape in such a manner that the compressed air (combustion air) introduced into the air passage 30 is rectified, and fuel injection that injects fuel.
- a plurality of openings 44a are provided in the circumferential direction, and the positions of the fuel injection openings 44a in the extending direction of the combustor shaft S (combustor shaft direction) are irregularly changed. .
- the above-described effect of suppressing the generation of combustion vibrations in a wide range of frequencies while maintaining low NOx by the top hat nozzle 44 is obtained, and more combustion vibrations at different frequencies are obtained. Because the phase difference of the frequency of combustion vibration occurs more finely, the combustion vibration in a wider range of frequencies including the specified combustion vibration can be suppressed, so the occurrence of combustion vibrations in a wide range of frequencies is suppressed. The effect can be obtained remarkably. In addition, since the generation of combustion vibration is suppressed by the configuration of the top hat nozzle 44 itself for reducing MOx, it is not necessary to provide a new configuration for generating combustion vibration, and the manufacturing cost of the gas turbine combustor 12 is reduced. There is no problem of increasing the volume or increasing the weight of the gas turbine combustor 12.
- a plurality of fuel injection ports 42a are arranged in the extending direction of the combustor shaft S (combustor shaft direction).
- the gas turbine combustor 12 maintains a low NOx while maintaining a wide range. Since generation of combustion vibration at a frequency is suppressed, an operation with low NOx and less combustion vibration can be performed.
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Abstract
Description
図2は、実施の形態1のガスタービン燃焼器の断面図であり、図3は、図2のA-A矢視図である。図2および図3に示すように、上述した燃焼器12は、外筒31の内部に所定間隔をあけて空気通路30を形成するように内筒32が支持され、内筒32の先端部に尾筒33が連結されて燃焼器ケーシングが構成されている。
図5は、実施の形態2のガスタービン燃焼器の断面図であり、図6は、図5のA-A断面拡大図である。
図9は、実施の形態3のガスタービン燃焼器の断面図であり、図10は、図9のA-A断面拡大図である。
図12は、実施の形態4のガスタービン燃焼器の断面図であり、図13は、図12のA-A断面拡大図であり、図14は、図12のB1-B2範囲における図13のC破断D1-D2展開概略図である。
30 空気通路
31 外筒
32 内筒
33 尾筒
34 トップハット部
35 パイロットノズル
36 メインノズル
41 トップハットノズル
41G トップハットノズル群
41a 燃料噴射口
42 トップハットノズル
42a 燃料噴射口
43 トップハットノズル
43a 燃料噴射口
44 トップハットノズル
44a 燃料噴射口
S 燃焼器軸
Claims (14)
- 外筒と、当該外筒の内側に設けられて前記外筒との間に空気通路を形成する内筒と、前記内筒の中心部において燃焼器軸方向に沿って設けられたパイロットノズルと、前記内筒の内周面に周方向に沿って前記パイロットノズルを取り囲むように複数設けられたメインノズルと、を備え、前記空気通路に導入された燃焼用空気に対して前記メインノズルによって燃料を予め混合して前記内筒の内部に噴出させるガスタービン燃焼器において、
前記空気通路の内部にて周方向に亘って設けられて、前記メインノズルに至る以前の前記燃焼用空気に燃料を混合させるトップハットノズルをさらに備え、当該トップハットノズルの燃料を噴射する位置を燃焼器軸方向で変化させることを特徴とするガスタービン燃焼器。 - 前記トップハットノズルは、周方向に複数設けられており、燃焼器軸方向の位置を規則的に変化させて配置されていることを特徴とする請求項1に記載のガスタービン燃焼器。
- 前記トップハットノズルは、周方向に複数設けられており、燃焼器軸方向の位置を不規則に変化させて配置されていることを特徴とする請求項1に記載のガスタービン燃焼器。
- 前記トップハットノズルは、周方向に複数設けられて燃焼器軸方向位置を変化させて配置された1つのトップハットノズル群をなし、前記トップハットノズル群が燃焼器軸方向に複数配置されていることを特徴とする請求項2または3に記載のガスタービン燃焼器。
- 前記トップハットノズルは、燃焼器軸方向に延在した途中に燃料を噴射する燃料噴射口を有して形成され、周方向に複数設けられており、前記燃料噴射口の燃焼器軸方向の位置を規則的に変化させて配置されていることを特徴とする請求項1に記載のガスタービン燃焼器。
- 前記トップハットノズルは、燃焼器軸方向に延在する途中に燃料を噴射する燃料噴射口を有して形成され、周方向に複数設けられており、前記燃料噴射口の燃焼器軸方向の位置を不規則に変化させて配置されていることを特徴とする請求項1に記載のガスタービン燃焼器。
- 前記燃料噴射口が、燃焼器軸方向に複数配置されていることを特徴とする請求項5または6に記載のガスタービン燃焼器。
- 前記トップハットノズルは、周方向に沿って環状に形成され、燃料を噴射する燃料噴射口が周方向に複数設けられており、前記燃料噴射口の燃焼器軸方向の位置を規則的に変化させて配置されていることを特徴とする請求項1に記載のガスタービン燃焼器。
- 前記トップハットノズルは、燃焼器軸方向に複数配置されていることを特徴とする請求項8に記載のガスタービン燃焼器。
- 前記トップハットノズルは、周方向に沿って環状に形成され、燃料を噴射する燃料噴射口が周方向に複数設けられており、燃焼器軸方向に複数配置されているとともに、相互の前記燃料噴射口の燃焼器軸方向の位置を変化させる態様で、相互の燃料噴射口の周方向の位置を異ならせて配置されていることを特徴とする請求項1に記載のガスタービン燃焼器。
- 前記トップハットノズルは、前記空気通路に導入された燃焼用空気を整流する態様で翼型をなし、燃料を噴射する燃料噴射口を有して形成され、周方向に複数設けられており、前記燃料噴射口の燃焼器軸方向の位置を規則的に変化させて配置されていることを特徴とする請求項1に記載のガスタービン燃焼器。
- 前記トップハットノズルは、前記空気通路に導入された燃焼用空気を整流する態様で翼型をなし、燃料を噴射する燃料噴射口を有して形成され、周方向に複数設けられており、前記燃料噴射口の燃焼器軸方向の位置を不規則に変化させて配置されていることを特徴とする請求項1に記載のガスタービン燃焼器。
- 前記燃料噴射口が、燃焼器軸方向に複数配置されていることを特徴とする請求項11または12に記載のガスタービン燃焼器。
- 請求項1~13のいずれか一つに記載のガスタービン燃焼器を備えることを特徴とするガスタービン。
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
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EP12757130.5A EP2698582B1 (en) | 2011-03-16 | 2012-02-28 | Gas turbine combustor and gas turbine |
US13/817,384 US9719419B2 (en) | 2011-03-16 | 2012-02-28 | Gas turbine combustor with top hat nozzle arrangements |
KR1020137003744A KR101471311B1 (ko) | 2011-03-16 | 2012-02-28 | 가스 터빈 연소기 및 가스 터빈 |
JP2013504639A JP5524407B2 (ja) | 2011-03-16 | 2012-02-28 | ガスタービン燃焼器およびガスタービン |
CN201280002443.3A CN103080653B (zh) | 2011-03-16 | 2012-02-28 | 燃气涡轮燃烧器及燃气涡轮 |
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JP2011058588 | 2011-03-16 | ||
JP2011-058588 | 2011-03-16 |
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WO2012124467A1 true WO2012124467A1 (ja) | 2012-09-20 |
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EP (1) | EP2698582B1 (ja) |
JP (1) | JP5524407B2 (ja) |
KR (1) | KR101471311B1 (ja) |
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JP2014159942A (ja) * | 2013-01-22 | 2014-09-04 | Mitsubishi Heavy Ind Ltd | 燃焼器、及び回転機械 |
JP2014163664A (ja) * | 2013-02-27 | 2014-09-08 | General Electric Co <Ge> | 燃焼ダイナミクスのモードカップリングを低減させる燃料ノズル |
JP2015224867A (ja) * | 2014-05-28 | 2015-12-14 | ゼネラル・エレクトリック・カンパニイ | 燃焼システムにおけるコヒーレンス低減のためのシステム及び方法 |
WO2018168747A1 (ja) * | 2017-03-13 | 2018-09-20 | 三菱日立パワーシステムズ株式会社 | 燃焼器用ノズル、燃焼器、及びガスタービン |
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Publication number | Publication date |
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EP2698582A1 (en) | 2014-02-19 |
KR20130041207A (ko) | 2013-04-24 |
EP2698582A4 (en) | 2014-10-08 |
JP5524407B2 (ja) | 2014-06-18 |
CN103080653A (zh) | 2013-05-01 |
US20130139511A1 (en) | 2013-06-06 |
EP2698582B1 (en) | 2017-11-22 |
JPWO2012124467A1 (ja) | 2014-07-17 |
US9719419B2 (en) | 2017-08-01 |
CN103080653B (zh) | 2015-03-25 |
KR101471311B1 (ko) | 2014-12-09 |
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