WO2022255334A1 - ガスタービン燃焼器 - Google Patents
ガスタービン燃焼器 Download PDFInfo
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- WO2022255334A1 WO2022255334A1 PCT/JP2022/022050 JP2022022050W WO2022255334A1 WO 2022255334 A1 WO2022255334 A1 WO 2022255334A1 JP 2022022050 W JP2022022050 W JP 2022022050W WO 2022255334 A1 WO2022255334 A1 WO 2022255334A1
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- resonator
- region
- gas turbine
- cylinder
- axial direction
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 82
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 77
- 230000008859 change Effects 0.000 claims abstract description 37
- 230000002093 peripheral effect Effects 0.000 claims description 45
- 238000005192 partition Methods 0.000 claims description 14
- 239000000446 fuel Substances 0.000 description 45
- 239000007789 gas Substances 0.000 description 32
- 230000004048 modification Effects 0.000 description 18
- 238000012986 modification Methods 0.000 description 18
- 238000010586 diagram Methods 0.000 description 7
- 238000001816 cooling Methods 0.000 description 6
- 239000000203 mixture Substances 0.000 description 6
- 239000000567 combustion gas Substances 0.000 description 5
- 230000002238 attenuated effect Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
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- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 2
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910000531 Co alloy Inorganic materials 0.000 description 1
- 229910000990 Ni alloy Inorganic materials 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000007792 addition Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 239000011796 hollow space material Substances 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000010363 phase shift Effects 0.000 description 1
- 230000000644 propagated effect Effects 0.000 description 1
- 239000001294 propane Substances 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
Images
Classifications
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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
- F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
- F02C5/10—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid forming a resonating or oscillating gas column, i.e. the combustion chambers having no positively actuated valves, e.g. using Helmholtz effect
-
- 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
- F23R3/005—Combined with pressure or heat exchangers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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 disclosure relates to combustors for gas turbine engines.
- a gas turbine combustor equipped with a resonator to reduce vibration caused by combustion is known.
- a resonator is attached to a combustion cylinder that defines a combustion chamber, and a resonance chamber of the resonator opens into the combustion chamber.
- a resonator is attached to a flow sleeve arranged radially outside a combustion cylinder that defines a combustion chamber, and a resonance chamber of the resonator opens into an air flow path defined by the flow sleeve.
- Patent Document 1 the heat of the combustion chamber is directly transmitted to the resonance chamber, and the resonator becomes hot. Extra cooling of the resonator to increase the combustion temperature to compensate for the cooling can increase NOx.
- Patent Document 2 the heat transferred from the combustion chamber to the resonator is reduced, but there is room for improvement in terms of vibration reduction.
- a gas turbine combustor is a tubular body that defines a combustion chamber, extends from a first side in an axial direction toward a second side, and has an exhaust port on the second side in the axial direction.
- an air channel for supplying air to the combustion chamber; and at least one resonator including at least one opening opening into the air channel.
- the air flow path is arranged along an upstream region along the outer peripheral surface of the cylindrical body and along the inner peripheral surface of the cylindrical body on the first side in the axial direction with respect to the combustion chamber, a downstream region communicating with the combustion chamber; and a direction change region connecting the upstream region to the downstream region in a radial direction of the cylindrical body, wherein a turning region adjacent said upstream region with a change in orthogonal cross-sectional area.
- the opening opens into a space downstream of the upstream area in the air flow path.
- a gas turbine combustor is a tubular body that defines a combustion chamber, extends from a first side in an axial direction toward a second side, and has an exhaust port on the second side in the axial direction. and an air flow path for supplying air to the combustion chamber.
- the air flow path is arranged along an upstream region along the outer peripheral surface of the cylindrical body and along the inner peripheral surface of the cylindrical body on the first side in the axial direction with respect to the combustion chamber, a downstream region communicating with the combustion chamber; and a direction change region connecting the upstream region to the downstream region in the radial direction of the cylindrical body.
- the tubular body has a leak hole that bypasses the turning region and communicates the downstream region with the upstream region.
- FIG. 1 is a schematic diagram of a gas turbine engine.
- FIG. 2 is a cross-sectional perspective view of the combustor of the first embodiment.
- 3 is a cross-sectional view of the combustor of FIG. 2;
- FIG. FIG. 4 is a diagram illustrating low frequency pressure wave propagation in the combustor of FIG. 5 is a diagram illustrating high-frequency pressure wave propagation in the combustor of FIG. 3.
- FIG. FIG. 6 is a drawing for explaining the path difference of pressure wave propagation in the direction change region of FIG.
- FIG. 7A is a perspective view showing a modification of the resonator of FIG. 3.
- FIG. 7(B) is a cross-sectional view along the line VIIB-VIIB of FIG. 7(A).
- FIG. 7(C) is a sectional view taken along line VIIC-VIIC of FIG. 7(A).
- FIG. 8A is a cross-sectional view of a main part showing a first modification of the combustor of FIG. 3.
- FIG. 8B is a cross-sectional view of a main part showing a second modification of the combustor of FIG.
- FIG. 8(C) is a cross-sectional view of a main part showing a third modification of the combustor of FIG.
- FIG. 9 is a cross-sectional view of the essential parts of the combustor of the second embodiment.
- FIG. 10A is a perspective view showing a modification of the resonator of FIG. 9.
- FIG. FIG. 10A is a perspective view showing a modification of the resonator of FIG. 9.
- FIG. 10(B) is a cross-sectional view along line XB-XB of FIG. 10(A).
- FIG. 11(A) is a cross-sectional view of a main part showing a first modification of the combustor of FIG. 9.
- FIG. 11(B) is a cross-sectional view of a main part showing a second modification of the combustor of FIG. 9 .
- FIG. 12 is a cross-sectional view of the essential parts of the combustor of the third embodiment.
- 13A to 13C are schematic diagrams showing variations of the air flow path of the combustor.
- FIG. 14 is a cross-sectional view of the essential parts of the combustor of the fourth embodiment.
- FIG. 15 is a cross-sectional view of the essential parts of the combustor of the fifth embodiment.
- FIG. 1 is a schematic diagram of a gas turbine engine 1.
- a gas turbine engine 1 (hereinafter referred to as gas turbine) includes a rotating shaft 2 , a compressor 3 , a combustor 4 and a turbine 5 .
- the compressed air supplied from the compressor 3 is guided to the combustor 4, and the mixture of the fuel supplied from the fuel supply line and the compressed air supplied from the compressor 3 is combusted in the combustor 4.
- the high-temperature, high-pressure combustion gas discharged from the combustor 4 drives the turbine 5 .
- Turbine 5 is mechanically coupled to load 6 (eg, a generator) and compressor 3 via rotating shaft 2 .
- FIG. 2 is a cross-sectional perspective view of the combustor 4 of the first embodiment.
- FIG. 3 is a cross-sectional view of combustor 4 of FIG.
- axial direction X the direction in which the axis C of the casing 11 and the cylindrical body 12 extends.
- first side the side opposite to the discharge port 32 of the tubular body 12
- second side the discharge port 32 side
- a direction perpendicular to the axial direction X is referred to as a "radial direction Y”.
- a direction extending circumferentially around the axis C is referred to as a “circumferential direction Z”.
- the combustor 4 (also referred to as a gas turbine combustor) is, for example, one of a plurality of can-shaped combustors arranged annularly around the rotation axis 2 of the gas turbine 1 (see FIG. 2). Note that the combustor 4 is not limited to this, and may be applied to a gas turbine having only one combustor, for example. As shown in FIGS. 2 and 3, the combustor 4 includes a casing 11, a tubular body 12, a fuel injector 13, an igniter 14, a fuel supply structure 15, an air flow path 16, a current plate 17 and a resonator 18.
- the casing 11 includes a tubular casing 21 and end plates 22 .
- the tubular casing 21 has a tubular shape and extends from the first side (left side in FIG. 3) in the axial direction X toward the second side (right side in FIG. 3).
- the tubular casing 21 has an air inlet 30 open to the second side to receive air A from the compressor 3 (see FIG. 1).
- the end plate 22 is arranged on the first side in the axial direction X with respect to the cylindrical body 12 and has an inner surface facing an air flow path 16 which will be described later.
- the end plate 22 closes the first side opening of the cylindrical casing 21 and is fixed to the first side end of the cylindrical casing 21 with a fastener.
- the tubular body 12 is housed in the casing 11 .
- the axis C of the cylinder 12 coincides with the axis of the casing 11 .
- the cylinder 12 includes a combustion cylinder 23 that is a first cylinder and a support cylinder 24 that is a second cylinder.
- the combustion cylinder 23 defines a combustion chamber 31 inside thereof.
- a discharge port 32 of the combustion cylinder 23 opens to the second side.
- the support cylinder 24 is adjacent to the first side of the combustion cylinder 23 and arranged coaxially with the combustion cylinder 23 .
- the support tube 24 defines an air chamber 33 inside in the radial direction Y thereof.
- the material of the combustion tube 23 eg, cobalt alloy or nickel alloy
- the cylindrical body 12 may have only the combustion cylinder 23 and the support cylinder 24 may be omitted.
- the fuel injector 13 is housed in the cylinder 12 .
- the fuel injector 13 has a fuel injection port 13 a opening into the combustion chamber 31 .
- the fuel injection port 13 a is configured to inject fuel F supplied from a fuel supply structure 15 (described later) into the combustion chamber 31 together with air A supplied from the air chamber 33 .
- the fuel injector 13 is arranged on the first side in the axial direction X with respect to the combustion chamber 31 . In this embodiment, as an example, the fuel injector 13 is arranged corresponding to the boundary between the combustion cylinder 23 and the support cylinder 24 to separate the combustion chamber 31 and the air chamber 33 .
- the fuel F is gaseous fuel such as carbon-containing gas (natural gas, propane gas) or hydrogen-containing gas (hydrogen gas), but liquid fuel may also be used. Further, the fuel F and the air A may be premixed and injected into the combustion chamber 31 as an air-fuel mixture, or may be mixed in the combustion chamber 31 .
- the igniter 14 penetrates the cylinder casing 21 and the combustion cylinder 23 in the radial direction Y, and the ignition part 14 a of the igniter 14 is exposed to the combustion chamber 31 .
- the air-fuel mixture injected from the fuel injector 13 into the combustion chamber 31 is ignited by the igniter 14 to generate flame in the combustion chamber 31 .
- the high-temperature, high-pressure combustion gas G generated in the combustion chamber 31 is discharged from the discharge port 32 .
- the fuel supply structure 15 is not particularly limited as long as it can supply the fuel F supplied from the fuel supply line outside the casing 11 to the fuel injector 13 .
- the fuel supply structure 15 includes a header pipe 25 and a plurality of branch pipes 26 and 27 branched from the header pipe 25 .
- the mother pipe 25 penetrates the end plate 22 on the axis C of the cylindrical body 12 and extends in the axial direction X.
- One end of the mother pipe 25 is arranged in the air chamber 33 and the other end of the mother pipe 25 is arranged outside the casing 11 .
- the mother pipe 25 has a multi-tube structure in which a plurality of cylindrical pipes are concentrically arranged, and a plurality of circular tubular fuel supply passages 25a and 25b are concentrically provided therein.
- Branch pipes 26 , 27 connect header pipe 25 to fuel injector 13 .
- the inside of the branch pipe 26 communicates with the fuel supply path 25a, and the inside of the branch pipe 27 communicates with the fuel supply path 25b.
- the branch pipes 26 and 27 have a portion that protrudes outward in the radial direction Y from the mother pipe 25 and a portion that extends in the axial direction X toward the fuel injector 13 .
- the positions in the radial direction Y where the branch pipes 26 and 27 are connected to the fuel injector 13 are different.
- the flow rate of the fuel F supplied to each part of the fuel injector 13 can be independently controlled by adjusting the opening degree of the flow control valve capable of adjusting the flow rate of each fuel supply passage 25a, 25b. .
- the air flow path 16 is configured to supply the air A supplied from the compressor 3 (see FIG. 1) to the combustion chamber 31 .
- the air flow path 16 has a reverse flow shape extending from the air inlet 30 toward the first side in the axial direction X and turning back toward the second side in the axial direction X. As shown in FIG.
- the air flow path 16 has an air introduction path 34 that is a gap between the inner peripheral surface of the casing 11 and the outer peripheral surface of the cylinder 12 .
- the air introduction passage 34 introduces the air A compressed by the compressor 3 (see FIG. 1) from the air inlet 30 and guides it in the direction opposite to the flow direction of the combustion gas G in the combustion chamber 31 .
- An axial flow type in which the air A and the combustion gas G flow in the same direction may be used.
- the support cylinder 24 has a plurality of air introduction ports 35 arranged in the circumferential direction Z at its first side portion.
- the air inlet of the support tube 24 may be a large opening that includes a plurality of air inlets 35 .
- the air introduction port 35 communicates the air introduction path 34 with the air chamber 33 .
- the air A that has flowed through the air introduction path 34 passes through the air introduction port 35 and is led to the air chamber 33 inside the support tube 24 in the radial direction Y. As shown in FIG.
- the air A guided to the air chamber 33 flows toward the fuel injector 13 and mixes with the fuel F in the fuel injector 13 .
- the straightening plate 17 is arranged perpendicular to the axis C in the support cylinder 24 .
- the current plate 17 is arranged on the second side in the axial direction X with respect to the air inlet 35 .
- the rectifying plate 17 has its outer peripheral portion fixed to the support tube 24 and its inner peripheral portion fixed to the end plate 22 via a tubular bracket fitted on the mother pipe 25 .
- the straightening plate 17 has a plurality of straightening holes 17a.
- the current plate 17 divides the air chamber 33 into two spaces aligned in the axial direction X. As shown in FIG. That is, the straightening plate 17 divides the air chamber 33 into a pre-straightening space 33a and a post-straightening space 33b.
- the pre-rectification space 33a is a space on the first side of the air chamber 33 and is adjacent to the air inlet 35.
- the post straightening space 33b is the space on the second side of the air chamber 33 and is adjacent to the fuel injector 13. As shown in FIG.
- the current plate 17 is located on the second side in the axial direction X with respect to the air inlet 35 .
- the straightening plate 17 straightens the air A introduced into the air chamber 33 from the air inlet 35 into a uniform flow toward the combustion chamber 31 . Note that the straightening plate 17 may be omitted.
- the air flow path 16 is configured by the air introduction path 34, the air introduction port 35, and the air chamber 33.
- the air flow path 16 includes an upstream region R1, a direction changing region R2, and a downstream region R3. can be considered separately.
- the upstream region R1 is provided along the outer peripheral surface of the cylindrical body 12 between the air inlet 30 and the air inlet 35 in the axial direction X.
- the upstream region R1 is part of the air introduction passage 34.
- the downstream region R3 is provided along the inner peripheral surface of the cylindrical body 12 between the air inlet 35 and the fuel injector 13 in the axial direction X.
- Downstream region R3 is part of air chamber 33 .
- a turning region R2 connects the upstream region R1 to the downstream region R3.
- the direction change region R2 is adjacent to the upstream region R1 with a change in cross-sectional area perpendicular to the axial direction X between the upstream region R1 and the direction change region R2.
- a virtual boundary plane M between the upstream region R1 and the direction change region R2 is a virtual plane passing through the end E of the air inlet 35 on the second side in the axial direction X and perpendicular to the axial direction X.
- the imaginary boundary surface M passes through the end E on the second side in the axial direction X of the flow channel extending in the radial direction Y to connect the upstream region R1 to the downstream region R3 of the air flow channel 16, and the axial line It is an imaginary plane that is perpendicular to the direction X and located outside the edge E in the radial direction Y.
- a virtual boundary surface N between the direction change region R2 and the downstream region R3 is also a virtual plane passing through the end E of the air inlet 35 and orthogonal to the axial direction X. That is, the imaginary boundary surface N passes through the end E on the second side in the axial direction X of the flow channel extending in the radial direction Y to connect the upstream region R1 to the downstream region R3 of the air flow channel 16, and the axial line It is an imaginary plane that is perpendicular to the direction X and located inside the end E in the radial direction Y.
- the current plate 17 is arranged in the downstream region R3.
- the resonator 18 (first resonator) has an opening 41 , a diaphragm 42 and a resonance chamber 43 .
- the opening 41 opens to face the space (the direction changing region R2 or the downstream region R3) on the downstream side of the virtual boundary surface M in the air flow path 16 .
- the opening 41 directly faces the downstream region R3 and opens to the downstream region R3 on the inner peripheral surface of the support tube 24 .
- the opening 41 continues to the downstream region R3.
- the resonator 18 utilizes part of the support cylinder 24 .
- a diaphragm 42 is a channel that connects the opening 41 to the resonance chamber 43 .
- the resonance chamber 43 is a space larger than the diaphragm 42 .
- the area of the aperture 41, the length of the diaphragm 42, and the volume of the resonance chamber 43 are determined according to the frequency to be attenuated.
- the support cylinder 24 may project outward in the radial direction Y, and the resonator 18 may be located inside the projecting portion in the radial direction Y.
- a plate with an aperture 41 and a diaphragm 42 is located between the downstream region R3 and the resonance chamber 43. That is, the inner peripheral surface of the support tube 24 utilizes the inner surface in the radial direction Y of the plate of the resonator 18 .
- the opening 41 of the resonator 18 is open to the air flow path 16 upstream of the combustion chamber 31, the internal temperature of the resonator 18 is lower than when it is open to the combustion chamber. No cooling required. Therefore, a special cooling structure can be dispensed with, and an increase in NOx can be prevented without raising the combustion temperature to compensate for the cooling.
- the cross-sectional area perpendicular to the axial direction X changes at the boundary (virtual boundary plane M) between the upstream region R1 and the direction change region R2.
- the boundary virtual boundary plane M
- pressure waves that are air-transmitted from the combustion chamber 31 back through the air flow path 16 due to combustion oscillation are partially reflected or canceled.
- this reflection action causes the sound pressure in the space downstream of the upstream region R1 in the air flow path 16 to increase to the upstream region.
- the sound pressure tends to be higher than that of R1. Therefore, by opening the opening 41 in the space downstream of the upstream region R1 in the air flow path 16, the pressure wave transmitted from the combustion chamber 31 to the air flow path 16 can be effectively absorbed. vibration can be reduced.
- FIG. 4 is a diagram for explaining low-frequency pressure wave propagation in the combustor 4 of FIG.
- a pressure wave with a relatively low frequency that is, a pressure wave whose wavelength can be regarded as long relative to the size of the propagation space.
- the pressure wave P1 traveling backward through the air flow path 16 from the combustion chamber 31 travels along the axial direction X toward the first side, and is reflected on the wall surface of the turning region R2 on the first side in the axial direction X.
- the reflected wave P2 travels along the axial direction X toward the second side.
- the reflected wave P2 is divided into a component reflected at the end E of the air inlet 35 and other components.
- the wall-reflected component remains in the direction change region R2.
- the components that are not reflected at the edge E are divided into those that proceed to the upstream region R1 and those that remain in the direction change region R2 and the downstream region R3. Therefore, the pressure wave propagated to the upstream region R1 is smaller than the pressure wave in the space downstream of the imaginary boundary surface M. That is, the sound pressure in the direction changing region R2 and the downstream region R3 is higher than that in the upstream region R1. Therefore, by opening the opening 41 in the space downstream of the upstream region R1 in the air flow path 16, the pressure wave transmitted from the combustion chamber 31 to the air flow path 16 can be effectively absorbed.
- FIG. 5 is a drawing for explaining high-frequency pressure wave propagation in the combustor 4 of FIG.
- a pressure wave with a relatively high frequency that is, a pressure wave whose wavelength can be regarded as short relative to the size of the propagation space is considered.
- the pressure wave traveling backward through the air flow path 16 from the combustion chamber 31 has a component P3 reflected on the wall surface of the direction change region R2 and an upstream region It splits into a component P4 which is transmitted to R1.
- a component P3 of the pressure wave reflected on the wall surface of the turning region R2 remains in the turning region R2 and the downstream region R3 (part of the component P3 may also be transmitted to the upstream region R1).
- the sound pressure in the direction changing region R2 and the downstream region R3 is higher than that in the upstream region R1. Therefore, by opening the opening 41 in the space downstream of the upstream region R1 in the air flow path 16, the pressure wave transmitted from the combustion chamber 31 to the air flow path 16 can be effectively absorbed.
- FIG. 6 is a drawing explaining the path difference of pressure wave propagation in the direction change region R2 of FIG.
- a path difference occurs between the inner peripheral path P5 and the outer peripheral path P6 in the curved path.
- a phase shift occurs between the phase of the pressure wave passing through the inner path P5 and the phase of the pressure wave passing through the outer path P6.
- the pressure waves partially cancel each other out due to interference in which the pressure waves having different phases are superimposed. Therefore, the sound pressure in the direction changing region R2 and the downstream region R3 is higher than that in the upstream region R1. Therefore, by opening the opening 41 in the space downstream of the upstream region R1 in the air flow path 16, the pressure wave transmitted from the combustion chamber 31 to the air flow path 16 can be effectively absorbed.
- the opening 41 of the resonator 18 faces the downstream region R3 and opens to the downstream region R3.
- the flow path cross-sectional area orthogonal to the axial direction X also changes at the imaginary boundary surface N between the direction change region R2 and the downstream region R3.
- the downstream region R3 is closer to the combustion chamber 31 than the turning region R2. Therefore, by opening the opening 41 of the resonator 18 to the downstream region R3, pressure waves can be absorbed more effectively.
- the opening 41 of the resonator 18 faces the post rectification space 33b and opens into the post rectification space 33b.
- the cross-sectional area of the flow path perpendicular to the axial direction X also changes in the rectifying holes 17 a of the rectifying plate 17 , and the pressure wave is partially reflected in the rectifying plate 17 . Therefore, by opening the opening 41 of the resonator 18 to the post straightening space 33b, the pressure wave can be absorbed more effectively.
- the gas introduced into the resonator 18 is not a fuel-containing gas such as an air-fuel mixture.
- the fuel content of the air-fuel mixture changes according to the engine output, and the speed of sound changes accordingly, making it difficult to design the resonance frequency. Since the resonator 18 opens into the air flow path 16, such problems can be avoided. It should be noted that a configuration in which a mixture of air and fuel flows in the air flow path 16 may be adopted.
- the resonator 18 is housed in the casing 11 and provided on the support cylinder 24 .
- the resonator 18 has, for example, a resonator main body 50 fitted to the outer peripheral surface of the support cylinder 24 .
- the resonator 18 is composed of a part of the support tube 24 and a resonator main body 50 .
- the resonator main body 50 is a cylindrical hollow member.
- the diaphragm 42 is a through hole formed in the inner peripheral wall of the resonator body 50 and the support cylinder 24 .
- the length of the diaphragm 42 in the radial direction Y can be determined by the thickness of the inner peripheral wall of the resonator body 50 .
- the opening 41 is an inner opening in the radial direction Y of the through hole of the support tube 24 .
- the openings 41 are arranged in the axial direction X and in the circumferential direction Z. As shown in FIG. All the openings 41 and diaphragms 42 are in communication with one resonance chamber 43, but the present invention is not limited to this, and the resonance chamber 43 may be divided into a plurality of cavities.
- the resonator 18 may be partially arranged in the circumferential direction Z instead of being arranged over the entire circumference of the outer peripheral surface of the support tube 24 .
- the resonator main body 50 may not be a hollow member, and may be a cover member covering the outer peripheral surface of the support tube 24 (the inner peripheral wall of the resonator main body 50 is eliminated). In that case, the gap between the inner peripheral surface of the cover member and the outer peripheral surface of the support tube 24 may be used as the resonance chamber 43 .
- the resonator 18 protrudes into the upstream region R1 from a portion of the support tube 24 adjacent to the resonator 18 in the axial direction X. That is, the outer peripheral surface of the resonator 18 is located radially Y outside the outer peripheral surface of the portion of the support tube 24 adjacent to the resonator 18 in the axial direction X. As shown in FIG. In this embodiment, the resonator main body 50 fitted on the support cylinder 24 is arranged so as to protrude from the support cylinder 24 to the upstream region R1. The inner peripheral surface of the support cylinder 24 extends linearly along the axial direction X. As shown in FIG.
- the outer surface of the resonator 18 facing the upstream region R1 may have a streamlined shape that gradually decreases in diameter toward both sides in the axial direction X. As shown in FIG.
- FIG. 7(A) is a perspective view showing a modification of the resonator 18 of FIG.
- FIG. 7(B) is a cross-sectional view along the line VIIB-VIIB of FIG. 7(A).
- FIG. 7(C) is a sectional view taken along line VIIC-VIIC of FIG. 7(A).
- the resonator 18 may have a partition plate 44 that divides the resonance chamber 43 into a plurality of cavities 45.
- the plurality of cavities 45 communicate with the plurality of openings 41 respectively.
- the partition plate 44 divides the resonance chamber 43 into both the axial direction X and the circumferential direction Z. Specifically, the partition plate 44 has a portion extending in the axial direction X and a portion extending in the circumferential direction Z. As shown in FIG. Only one opening 41 may communicate with one cavity 45 , or a plurality of openings 41 may communicate with one cavity 45 .
- the partition plate 44 may have a shape that divides each cavity 45 into a polygonal shape (for example, a square, a hexagon, etc.) or a circular shape in a developed view viewed from the radial direction Y. As shown in FIG.
- FIG. 8(A) is a cross-sectional view of essential parts showing a first modification of the combustor 4 of FIG.
- the resonator 118 protrudes into the downstream region R3 from the portion of the support tube 24 adjacent to the resonator 18 in the axial direction X.
- the inner peripheral surface of the resonator 118 is located radially inward in the Y direction from the inner peripheral surface of the portion of the support tube 24 adjacent to the resonator 18 in the axial direction X.
- FIG. 8A is a cross-sectional view of essential parts showing a first modification of the combustor 4 of FIG.
- the resonator 118 protrudes into the downstream region R3 from the portion of the support tube 24 adjacent to the resonator 18 in the axial direction X.
- the inner peripheral surface of the resonator 118 is located radially inward in the Y direction from the inner peripheral surface of the portion of the support tube 24 adjacent to the resonator 18 in the axial
- the resonator main body 150 fitted in the support tube 24 is arranged to protrude from the support tube 24 to the downstream region R3.
- the outer peripheral surface of the support tube 24 can extend linearly along the axial direction X, for example.
- the resonator may be arranged at an intermediate position between the position of the resonator 18 in FIG. 3 and the position of the resonator 118 in FIG. 8(A).
- FIG. 8(B) is a cross-sectional view of essential parts showing a second modification of the combustor 4 of FIG.
- the resonator 18 is the same as that of the embodiment described above, but the cylindrical casing 221 is different.
- the tubular casing 221 has a bulging portion 221a that expands outward in the radial direction Y at a portion that faces the resonator 18 in the radial direction Y. As shown in FIG. This can prevent the portion of the upstream region R1 outside the resonator 18 in the radial direction Y from becoming narrow.
- FIG. 8(C) is a cross-sectional view of the essential parts showing a third modification of the combustor 4 of FIG.
- a resonator 318 (third resonator) protrudes outside the tubular casing 21 .
- the resonator 318 has a resonator body 350 connected to the outer peripheral surface of the support cylinder 24 .
- the resonator main body 350 has a hollow portion 350 a that defines a resonance chamber 343 and a tubular portion 350 b that protrudes inward in the radial direction Y from the resonator main body 350 .
- the hollow portion 350a is arranged outside the cylindrical casing 21 in the radial direction Y. Although the cylindrical casing 21 and the resonator main body 350 are in contact with each other in FIG. 8(C), they do not have to be in contact with each other.
- the tube portion 350b penetrates the tube casing 21 in the radial direction Y, traverses the upstream region R1 in the radial direction, and is connected to the support tube 24 .
- the support tube 24 has a through hole forming an opening 41 facing the downstream region R3 in its inner peripheral surface, and the internal space of the pipe portion 350b communicates with the through hole. That is, the inner space of the tube portion 350b and the through hole of the support cylinder 24 constitute the diaphragm 342.
- the degree of freedom of the volume of the resonance chamber 343 can be increased, and the degree of freedom of setting the frequency to be attenuated is improved.
- the resonance chamber 343 can be designed to be wide to reduce low frequency vibrations.
- FIG. 9 is a cross-sectional view of essential parts of the combustor 404 of the second embodiment.
- resonator 418 (second resonator) is provided on end plate 422 of casing 411 .
- the end plate 422 has a concave portion 422a annularly extending around the axis C so as to face the air chamber 33 .
- the resonator 418 is accommodated in the recess 422a.
- the resonator 418 is an annular hollow member similar to the recess 422a.
- the resonator 418 has an aperture 441 , a diaphragm 442 and a resonance chamber 443 .
- a resonance chamber 443 is an annular hollow space of the resonator 418 .
- a configuration may be adopted in which a part of the walls of the resonator 418 is omitted and the resonance chamber 443 is defined using the surface of the end plate 422 .
- the openings 441 are arranged around the axis C at intervals on the surface of the resonator 418 facing the air chamber 33 .
- the diaphragm 442 is a through hole that communicates the opening 441 with the resonance chamber 443 in the wall of the resonator 418 facing the air chamber 33 .
- An opening 441 of the resonator 418 directly faces the air chamber 33 and opens into the air chamber 33 .
- the opening 441 is continuous with the direction change region R2.
- the opening 441 opens in the direction changing region R2 inside the air inlet port 35 in the radial direction Y.
- the opening 441 opens in the axial direction X so as to face the combustion chamber 31 .
- the axis of the opening 441 is substantially parallel to the axis C.
- the axis of the diaphragm 442 extends in the axial direction X. As shown in FIG.
- the cross-sectional area of the flow path perpendicular to the axial direction X changes at the imaginary boundary surface M, and the pressure wave is partially reflected or canceled on the downstream side of the imaginary boundary surface M. Therefore, by opening the opening 441 of the resonator 418 to the direction changing region R2, the pressure wave can be effectively absorbed. Moreover, since the opening 441 is oriented in the axial direction X, pressure waves transmitted in the axial direction X from the combustion chamber 31 can be effectively absorbed.
- the resonator provided in the combustor 404 may be the resonator 418 alone, or the resonator 18 of the first embodiment (or any of the resonators 118, 218, and 318 of the first to fourth modifications) may be used in combination. Since the rest of the configuration is the same as that of the above-described first embodiment, description thereof will be omitted.
- FIG. 10(A) is a perspective view showing a modification of the resonator 418 of FIG.
- FIG. 10(B) is a cross-sectional view along line XB-XB of FIG. 10(A).
- the resonator 418 may have partition plates 444 that divide the resonance chamber 443 into a plurality of cavities 445 .
- a plurality of cavities 445 communicate with a plurality of openings 441 respectively.
- the partition plate 444 divides the resonance chamber 443 in the circumferential direction Z. Only one opening 441 may communicate with one cavity 445 , or multiple openings 441 may communicate with one cavity 445 .
- the partition plate 444 may have a shape that divides each cavity 445 into sectors when viewed from the axial direction X. As shown in FIG.
- each cavity 445 may be divided in the radial direction. If each cavity 445 is divided in the radial direction Y, even if there is an opposite-phase sound pressure distribution in the radial direction Y, interference between opposite-phase sound pressures can be prevented.
- FIG. 11(A) is a cross-sectional view of essential parts showing a first modification of the combustor 404 of FIG.
- the resonator 518 protrudes in the axial direction X from the end plate 522 toward the air chamber 33 .
- the shape of the resonator 518 itself is the same as the resonator 418 described above.
- local thinning of the end plate 522 can be alleviated.
- the entire resonator 518 may be located on the second side in the axial direction X, ie, the air chamber 33 , relative to the end plate 522 .
- FIG. 11(B) is a cross-sectional view of essential parts showing a second modification of the combustor 404 of FIG.
- the resonator 618 protrudes outside the end plate 622 .
- Resonator 618 has a resonator body 650 connected to the outer surface of end plate 622 .
- the resonator body 650 is arranged outside the casing 11 and defines a resonance chamber 643 therein.
- the resonator main body 650 and the end plate 622 are in contact with each other in FIG. 11B, they may not be in contact with each other.
- the end plate 622 has a through hole extending in the axial direction X communicating with the resonance chamber 643 .
- the through hole of the end plate 622 constitutes a diaphragm 642.
- a wall of the resonator body 650 that is in surface contact with the end plate 622 may be omitted.
- the resonator main body 650 does not have to be in surface contact with the end plate 622 .
- the end plate 622 has an opening 641 serving as an inlet for the throttle 642 on the surface defining the air chamber 33 (the surface on the second side in the axial direction X). According to this, the degree of freedom of the volume of the resonance chamber 643 can be increased, and the degree of freedom of setting the frequency to be attenuated is improved.
- the resonance chamber 643 can be designed to be wide to reduce low frequency vibrations.
- FIG. 12 is a cross-sectional view of the essential parts of the combustor 704 of the third embodiment.
- the combustor 704 has resonators 718A and 718B that are open to portions of the direction change region R2 outside the air inlet 35 in the radial direction Y.
- the resonator 718A is provided in the cylinder casing 721, and the opening 741A of the resonator 718A is arranged outside in the radial direction Y of the direction changing region R2 and opens inward in the radial direction Y.
- the resonator 718B is provided on the end plate 722, and the opening 741B of the resonator 718B is arranged on the first side in the axial direction X of the direction changing region R2 and opens toward the second side in the axial direction X. .
- the combustor 704 may be further provided with the resonator 18 of the first embodiment, or may be further provided with the resonator 418 of the second embodiment. Since the rest of the configuration is the same as that of the above-described first embodiment, description thereof will be omitted.
- FIGS. 13A to 13C are schematic diagrams showing variations of the air flow path 16 of the combustor 4.
- FIG. 13A to 13C are schematic diagrams showing variations of the air flow path 16 of the combustor 4.
- FIG. 13B For ease of understanding, the elements of this variation corresponding to the elements of the first embodiment are denoted by the same reference numerals as those of the first embodiment, even if their shapes are different.
- the casing 11 is configured such that all of the upstream region R1, the direction change region R2 and the downstream region R3 are annular extending around the axis of the cylinder 12.
- the cylindrical body 12 is covered with a guide member 19 housed in a casing (not shown).
- the guide member 19 is configured such that the upstream region R1, the direction change region R2, and the downstream region R3 are all annular and extend around the axis of the tubular body 12.
- the casing 11 is configured so that the direction change region R2 is cylindrical around the axis of the cylinder 12, and the upstream region R1 and the downstream region R3 are annular extending around the axis of the cylinder 12. It is
- the imaginary boundary surface M between the upstream region R1 and the direction change region R2 is the diameter of the air flow path 16 to connect the upstream region R1 to the downstream region R3. It is a virtual plane that passes through the end E on the second side in the axial direction X of the flow path that extends in the direction Y and that is perpendicular to the axial direction X.
- FIG. A change in the cross-sectional area of the air flow path 16 in the axial direction X occurs at the imaginary boundary plane M, and the opening of the resonator (not shown) opens into the space downstream of the imaginary boundary plane M of the air flow path 16 .
- FIG. 14 is a cross-sectional view of essential parts of a combustor 804 of the fourth embodiment.
- resonator 818 is provided in cylinder 812 (specifically, support cylinder 824) and opens to downstream region R3.
- the tubular body 812 has a plurality of leak holes 812a that communicate the resonance chamber 843 of the resonator 818 with the upstream region R1.
- the leak hole 812a is arranged on the second side in the axial direction X with respect to the direction change region R2.
- the leak hole 812a communicates the downstream region R3 with the upstream region R1 via a resonator 818 so as to bypass the direction changing region R2.
- each leak hole 812a is 0.1 mm or more and 10 mm or less.
- the diameter of the leak hole 812a is smaller than the diameters of the opening 841 and the diaphragm 842 of the resonator 818 .
- the diameter of each leak hole 812a can be 1/10 or more of the height of the leak hole 812a (that is, the length of the channel axis of the leak hole 812a).
- the total opening area of the leak holes 812a may be set to 1/2 or less of the cross-sectional area of the upstream region R1 in the plane perpendicular to the flow direction.
- the leak hole 812a allows acoustic energy to escape from the downstream region R3 to the upstream region R1, further effectively reducing vibration caused by combustion. Since the rest of the configuration is the same as that of the above-described first embodiment, description thereof will be omitted.
- Resonator 818 of FIG. 14 is similar to resonator 118 of FIG. 8A, but may be similar to resonator 18 of FIG. 3 or similar to resonator 318 of FIG. 8C. good. If it is similar to the resonator 318 of FIG. 8C, the leak hole 812a may be formed in the support cylinder 24 or may be formed in the tube portion 350b.
- FIG. 15 is a cross-sectional view of the essential parts of the combustor 904 of the fifth embodiment.
- combustor 904 does not include a resonator.
- the cylinder 912 (specifically, the support cylinder 924) has a plurality of leak holes 912a that connect the downstream region R3 to the upstream region R1.
- the leak hole 912a is arranged on the second side in the axial direction X with respect to the direction change region R2.
- the leak hole 912a bypasses the direction change region R2 and communicates the downstream region R3 with the upstream region R1.
- each leak hole 912a is 0.1 mm or more and 10 mm or less. Specifically, the diameter of each leak hole 912a can be 1/10 or more of the height of the leak hole 912a (that is, the length of the channel axis of the leak hole 912a). As a result, it is possible to effectively reduce the pressure wave while improving the workability by laser or the like. Furthermore, the total opening area of the leak holes 912a may be set to 1/2 or less of the cross-sectional area of the upstream region R1 in the plane perpendicular to the flow direction. The leak hole 912a allows acoustic energy to escape from the downstream region R3 to the upstream region R1, and can effectively reduce vibration caused by combustion without a resonator. Since the rest of the configuration is the same as that of the above-described first embodiment, description thereof will be omitted.
- each embodiment and each modified example have been described as examples of the technology disclosed in the present application.
- the technology in the present disclosure is not limited to this, and can be applied to embodiments in which changes, replacements, additions, omissions, etc. are made as appropriate.
- some configurations or methods in one embodiment or variation may be applied to other embodiments or variations, and some configurations of an embodiment or variation may be applied to other embodiments or variations.
- a cylinder defining a combustion chamber, the cylinder extending from a first axial side toward a second axial side and defining an outlet on said second axial side; an air flow path for supplying air to the combustion chamber; at least one resonator having at least one opening that opens to the air flow path and a resonance chamber that communicates with the opening;
- the air flow path is an upstream region along the outer peripheral surface of the cylinder; a downstream region along the inner peripheral surface of the cylindrical body, arranged on the first side in the axial direction with respect to the combustion chamber, and communicating with the combustion chamber;
- a direction change region that connects the upstream region to the downstream region in the radial direction of the tubular body, the direction change region changing the cross-sectional area perpendicular to the axial direction between the upstream region and the direction change region a turning region adjacent to the upstream region;
- the gas turbine combustor wherein the opening of the resonator opens into a space downstream of the upstream region in the air flow path.
- the at least one resonator comprises a first resonator;
- the at least one resonator includes a second resonator; 6.
- [Item 7] further comprising an end plate disposed on the first side in the axial direction with respect to the cylinder and having an inner surface facing the air flow path; 7.
- [Item 8] Further comprising a casing that houses the cylindrical body, An air introduction path including the upstream region is provided between the casing and the cylindrical body, The cylinder has a first cylinder that defines the combustion chamber and a second cylinder that is adjacent to the first cylinder on the first side in the axial direction and defines an air chamber that includes the downstream region.
- a straightening plate further comprising a straightening plate that has a straightening hole and divides the space downstream of the upstream region in the air flow path into a pre-straightening space and a post-straightening space; 9.
- the at least one opening includes a plurality of openings aligned in the axial direction and circumferentially about the axial direction; Items 1 to 1, wherein the at least one resonator has a partition plate that divides the resonance chamber into a plurality of cavities communicating with the plurality of openings, the partition plate dividing the resonance chamber in the circumferential direction. 11.
- a cylinder defining a combustion chamber, the cylinder extending from a first axial side toward a second axial side and defining an outlet on the second axial side; an air flow path for supplying air to the combustion chamber, The air flow path is an upstream region along the outer peripheral surface of the cylinder; a downstream region along the inner peripheral surface of the cylindrical body, arranged on the first side in the axial direction with respect to the combustion chamber, and communicating with the combustion chamber; a turning region that connects the upstream region to the downstream region in the radial direction of the cylinder; A gas turbine combustor, wherein the tubular body has a leak hole that bypasses the turning region and communicates the downstream region with the upstream region.
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Abstract
Description
図2は、第1実施形態の燃焼器4の断面斜視図である。図3は、図2の燃焼器4の断面図である。なお、以下の説明では、ケーシング11及び筒体12の軸線Cが延びる方向を「軸線方向X」と称する。軸線方向Xにおいて、筒体12の排出口32とは反対側を「第1側」と称し、排出口32側を「第2側」と称する。軸線方向Xに直交する方向は、「径方向Y」と称する。軸線C周りに周状に延びる方向は、「周方向Z」と称する。
図9は、第2実施形態の燃焼器404の要部断面図である。図9に示すように、燃焼器404では、レゾネータ418(第2レゾネータ)は、ケーシング411のエンドプレート422に設けられている。エンドプレート422は、空気室33に対向して軸線C周りに環状に延びる凹部422aを有する。レゾネータ418は、凹部422aに収容されている。レゾネータ418は、凹部422aと相似な環状の中空部材である。
図12は、第3実施形態の燃焼器704の要部断面図である。図12に示すように、燃焼器704は、方向転換領域R2のうち空気導入口35よりも径方向Yの外側の部分に開口したレゾネータ718A、718Bを有する。レゾネータ718Aは、筒ケーシング721に設けられており、レゾネータ718Aの開口741Aは、方向転換領域R2の径方向Yの外側に配置され、径方向Y内側に向けて開口している。レゾネータ718Bは、エンドプレート722に設けられており、レゾネータ718Bの開口741Bは、方向転換領域R2の軸線方向Xの第1側に配置され、軸線方向Xの第2側に向けて開口している。燃焼器704には、第1実施形態のレゾネータ18が更に設けられてもよいし、第2実施形態のレゾネータ418が更に設けられてもよい。なお、他の構成は前述した第1実施形態と同様であるため説明を省略する。
図14は、第4実施形態の燃焼器804の要部断面図である。図14に示すように、燃焼器804では、レゾネータ818は、筒体812(具体的には、支持筒824)に設けられ、下流領域R3に開口している。筒体812は、レゾネータ818の共鳴室843を上流領域R1に連通させる複数のリーク孔812aを有する。リーク孔812aは、方向転換領域R2よりも軸線方向Xの第2側に配置されている。リーク孔812aは、方向転換領域R2をバイパスするように、レゾネータ818を介して下流領域R3を上流領域R1に連通させる。
図15は、第5実施形態の燃焼器904の要部断面図である。図15に示すように、燃焼器904は、レゾネータを備えていない。筒体912(具体的には、支持筒924)は、下流領域R3を上流領域R1に連通させる複数のリーク孔912aを有する。リーク孔912aは、方向転換領域R2よりも軸線方向Xの第2側に配置されている。リーク孔912aは、方向転換領域R2をバイパスして下流領域R3を上流領域R1に連通させる。
以下の項目のそれぞれは、好ましい実施形態の開示である。
[項目1]
燃焼室を画定する筒体であって、軸線方向の第1側から第2側に向けて延び、前記軸線方向の前記第2側に排出口を画定する筒体と、
前記燃焼室に空気を供給するための空気流路と、
前記空気流路に開口する少なくとも1つの開口と前記開口に連通する共鳴室とを有する少なくとも1つのレゾネータと、を備え、
前記空気流路は、
前記筒体の外周面に沿っている上流領域と、
前記筒体の内周面に沿っていて、前記燃焼室に対して前記軸線方向の前記第1側に配置され、前記燃焼室に連通した下流領域と、
前記筒体の径方向において前記上流領域を前記下流領域に接続する方向転換領域であって、前記上流領域と前記方向転換領域との間で前記軸線方向に直交する断面積の変化を伴って前記上流領域に隣接する方向転換領域と、を含み、
前記レゾネータの前記開口は、前記空気流路のうち前記上流領域よりも下流の空間に開口している、ガスタービン燃焼器。
[項目2]
前記少なくとも1つのレゾネータは、第1レゾネータを含み、
前記第1レゾネータの前記開口は、前記空気流路のうち前記下流領域に開口している、項目1に記載のガスタービン燃焼器。
[項目3]
前記第1レゾネータは、前記筒体に配置されている、項目2に記載のガスタービン燃焼器。
[項目4]
前記第1レゾネータの外周面は、前記筒体のうち前記第1レゾネータと前記軸線方向に隣接する部分の外周面よりも前記径方向外方に位置している、項目3に記載のガスタービン燃焼器。
[項目5]
前記第1レゾネータの内周面は、前記筒体のうち前記第1レゾネータと前記軸線方向に隣接する部分の内周面よりも前記径方向内方に位置している、項目3又は4に記載のガスタービン燃焼器。
[項目6]
前記少なくとも1つのレゾネータは、第2レゾネータを含み、
前記第2レゾネータの前記開口は、前記方向転換領域に開口している、項目1乃至5のいずれかに記載のガスタービン燃焼器。
[項目7]
前記筒体に対して前記軸線方向の前記第1側に配置され、前記空気流路に面する内面を有するエンドプレートを更に備え、
前記第2レゾネータは、前記エンドプレートに配置されている、項目6に記載のガスタービン燃焼器。
[項目8]
前記筒体を収容するケーシングを更に備え、
前記ケーシングと前記筒体との間に、前記上流領域を含む空気導入路があり、
前記筒体は、前記燃焼室を画定する第1筒と、前記軸線方向の前記第1側にて前記第1筒に隣接し、前記下流領域を含む空気室を画定する第2筒を有し、
前記少なくとも1つのレゾネータの前記開口は、前記空気室に開口している、項目1乃至7のいずれか1項に記載のガスタービン燃焼器。
[項目9]
整流孔を有し、前記空気流路のうち前記上流領域よりも下流の前記空間を、プレ整流空間とポスト整流空間とに区切る整流板を更に備え、
前記少なくとも1つのレゾネータの前記開口は、前記ポスト整流空間に開口している、項目1乃至8のいずれかに記載のガスタービン燃焼器。
[項目10]
前記少なくとも1つのレゾネータの前記共鳴室は、前記ケーシングの外部に配置されている、項目1乃至9のいずれかに記載のガスタービン燃焼器。
[項目11]
前記少なくとも1つの開口は、前記軸線方向に並んで且つ前記軸線方向周りの周方向に並んだ複数の開口を含み、
前記少なくとも1つのレゾネータは、前記複数の開口のそれぞれに連通する複数の空洞に前記共鳴室を分割する仕切板であって、前記共鳴室を前記周方向に分割する仕切板を有する、項目1乃至10のいずれかに記載のガスタービン燃焼器。
[項目12]
前記仕切板は、前記共鳴室を更に前記軸線方向又は前記径方向に分割している、項目11に記載のガスタービン燃焼器。
[項目14]
前記筒体は、前記方向転換領域をバイパスして前記下流領域を前記上流領域に連通させるリーク孔を有する、項目1乃至12のいずれかに記載のガスタービン燃焼器。
[項目15]
燃焼室を画定する筒体であって、軸線方向の第1側から第2側に向けて延び、前記軸線方向の前記第2側に排出口を画定する筒体と、
前記燃焼室に空気を供給するための空気流路と、を備え、
前記空気流路は、
前記筒体の外周面に沿っている上流領域と、
前記筒体の内周面に沿っていて、前記燃焼室に対して前記軸線方向の前記第1側に配置され、前記燃焼室に連通した下流領域と、
前記筒体の径方向において前記上流領域を前記下流領域に接続する方向転換領域と、を含み、
前記筒体は、前記方向転換領域をバイパスして前記下流領域を前記上流領域に連通させるリーク孔を有する、ガスタービン燃焼器。
4 燃焼器
11 ケーシング
12 筒体
13 燃料噴射器
16 空気流路
17 整流板
17a 整流孔
18 レゾネータ
21 筒ケーシング
22 エンドプレート
23 燃焼筒(第1筒)
24 支持筒(第2筒)
31 燃焼室
32 排出口
33b ポスト整流空間
33 空気室
33a プレ整流空間
34 空気導入路
35 空気導入口
41 開口
42 絞り
43 共鳴室
44 仕切板
45 空洞
A 空気
C 軸線
E 端
F 燃料
G 燃焼ガス
M,N 仮想境界面
R1 上流領域
R2 方向転換領域
R3 下流領域
X 軸線方向
Y 径方向
Z 周方向
Claims (14)
- 燃焼室を画定する筒体であって、軸線方向の第1側から第2側に向けて延び、前記軸線方向の前記第2側に排出口を画定する筒体と、
前記燃焼室に空気を供給するための空気流路と、
前記空気流路に開口する少なくとも1つの開口と前記開口に連通する共鳴室とを有する少なくとも1つのレゾネータと、を備え、
前記空気流路は、
前記筒体の外周面に沿っている上流領域と、
前記筒体の内周面に沿っていて、前記燃焼室に対して前記軸線方向の前記第1側に配置され、前記燃焼室に連通した下流領域と、
前記筒体の径方向において前記上流領域を前記下流領域に接続する方向転換領域であって、前記上流領域と前記方向転換領域との間で前記軸線方向に直交する断面積の変化を伴って前記上流領域に隣接する方向転換領域と、を含み、
前記レゾネータの前記開口は、前記空気流路のうち前記上流領域よりも下流の空間に開口している、ガスタービン燃焼器。 - 前記少なくとも1つのレゾネータは、第1レゾネータを含み、
前記第1レゾネータの前記開口は、前記空気流路のうち前記下流領域に開口している、請求項1に記載のガスタービン燃焼器。 - 前記第1レゾネータは、前記筒体に配置されている、請求項2に記載のガスタービン燃焼器。
- 前記第1レゾネータの外周面は、前記筒体のうち前記第1レゾネータと前記軸線方向に隣接する部分の外周面よりも前記径方向外方に位置している、請求項3に記載のガスタービン燃焼器。
- 前記第1レゾネータの内周面は、前記筒体のうち前記第1レゾネータと前記軸線方向に隣接する部分の内周面よりも前記径方向内方に位置している、請求項3又は4に記載のガスタービン燃焼器。
- 前記少なくとも1つのレゾネータは、第2レゾネータを含み、
前記第2レゾネータの前記開口は、前記方向転換領域に開口している、請求項1乃至4のいずれか1項に記載のガスタービン燃焼器。 - 前記筒体に対して前記軸線方向の前記第1側に配置され、前記空気流路に面する内面を有するエンドプレートを更に備え、
前記第2レゾネータは、前記エンドプレートに配置されている、請求項6に記載のガスタービン燃焼器。 - 前記筒体を収容するケーシングを更に備え、
前記ケーシングと前記筒体との間に、前記上流領域を含む空気導入路があり、
前記筒体は、前記燃焼室を画定する第1筒と、前記軸線方向の前記第1側にて前記第1筒に隣接し、前記下流領域を含む空気室を画定する第2筒を有し、
前記少なくとも1つのレゾネータの前記開口は、前記空気室に開口している、請求項1乃至4のいずれか1項に記載のガスタービン燃焼器。 - 整流孔を有し、前記空気流路のうち前記上流領域よりも下流の前記空間を、プレ整流空間とポスト整流空間とに区切る整流板を更に備え、
前記少なくとも1つのレゾネータの前記開口は、前記ポスト整流空間に開口している、請求項1乃至4のいずれか1項に記載のガスタービン燃焼器。 - 前記少なくとも1つのレゾネータの前記共鳴室は、前記ケーシングの外部に配置されている、請求項1乃至4のいずれか1項に記載のガスタービン燃焼器。
- 前記少なくとも1つの開口は、前記軸線方向に並んで且つ前記軸線方向周りの周方向に並んだ複数の開口を含み、
前記少なくとも1つのレゾネータは、前記複数の開口のそれぞれに連通する複数の空洞に前記共鳴室を分割する仕切板であって、前記共鳴室を前記周方向に分割する仕切板を有する、請求項1乃至4のいずれか1項に記載のガスタービン燃焼器。 - 前記仕切板は、前記共鳴室を更に前記軸線方向又は前記径方向に分割している、請求項11に記載のガスタービン燃焼器。
- 前記筒体は、前記方向転換領域をバイパスして前記下流領域を前記上流領域に連通させるリーク孔を有する、請求項1乃至4のいずれか1項に記載のガスタービン燃焼器。
- 燃焼室を画定する筒体であって、軸線方向の第1側から第2側に向けて延び、前記軸線方向の前記第2側に排出口を画定する筒体と、
前記燃焼室に空気を供給するための空気流路と、を備え、
前記空気流路は、
前記筒体の外周面に沿っている上流領域と、
前記筒体の内周面に沿っていて、前記燃焼室に対して前記軸線方向の前記第1側に配置され、前記燃焼室に連通した下流領域と、
前記筒体の径方向において前記上流領域を前記下流領域に接続する方向転換領域と、を含み、
前記筒体は、前記方向転換領域をバイパスして前記下流領域を前記上流領域に連通させるリーク孔を有する、ガスタービン燃焼器。
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US5644918A (en) * | 1994-11-14 | 1997-07-08 | General Electric Company | Dynamics free low emissions gas turbine combustor |
JP2004509313A (ja) * | 2000-09-21 | 2004-03-25 | シーメンス ウエスチングハウス パワー コーポレイション | ガスタービン発電所の燃焼不安定性を抑制するモジュラー形共鳴器 |
JP2004183944A (ja) * | 2002-12-02 | 2004-07-02 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼器、及びこれを備えたガスタービン |
US20130019602A1 (en) * | 2011-07-22 | 2013-01-24 | General Electric Company | System for damping oscillations in a turbine combustor |
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US5644918A (en) * | 1994-11-14 | 1997-07-08 | General Electric Company | Dynamics free low emissions gas turbine combustor |
JP2004509313A (ja) * | 2000-09-21 | 2004-03-25 | シーメンス ウエスチングハウス パワー コーポレイション | ガスタービン発電所の燃焼不安定性を抑制するモジュラー形共鳴器 |
JP2004183944A (ja) * | 2002-12-02 | 2004-07-02 | Mitsubishi Heavy Ind Ltd | ガスタービン燃焼器、及びこれを備えたガスタービン |
US20130019602A1 (en) * | 2011-07-22 | 2013-01-24 | General Electric Company | System for damping oscillations in a turbine combustor |
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