Gas turbine combustor

Abstract

A gas turbine combustor includes a cylinder that defines a combustion chamber, an air flow path for supplying air to the combustion chamber, and a resonator that includes an opening that opens to the air flow path. The air flow path includes an upstream region along an outer peripheral surface of the cylinder, a downstream region disposed along an inner peripheral surface of the cylinder, arranged on the first side in the axial direction with respect to the combustion chamber, and a direction conversion region that connects the upstream region and the downstream region in a radial direction of the cylinder, adjacent to the upstream region with a change in cross-sectional area orthogonal to the axial direction between the upstream region and the direction conversion region. The opening opens to a space in the air flow path that is downstream of the upstream region.

Description

Technical Field

[0001] This disclosure relates to a burner for a gas turbine engine. Background Technology

[0002] A gas turbine combustor equipped with a resonator is known to reduce vibrations caused by combustion. In Patent Document 1, a resonator is installed in the combustion tube defining the combustion chamber, and the resonator's resonating chamber opens into the combustion chamber. In Patent Document 2, a resonator is installed in a flow sleeve arranged radially outside the combustion tube defining the combustion chamber, and the resonator's resonating chamber opens into the airflow path defined by the flow sleeve.

[0003] Existing technical documents:

[0004] Patent documents:

[0005] Patent Document 1: Japanese Patent Application Publication No. 2018-159533;

[0006] Patent Document 2: Japanese Patent Application Publication No. 2013-234833. Summary of the Invention

[0007] The problem the invention aims to solve:

[0008] In the structure of Patent Document 1, the heat from the combustion chamber is directly transferred to the resonator, causing the resonator to become very hot. If the resonator is specifically cooled and the amount of cooling is compensated by increasing the combustion temperature, NOx may increase. In the structure of Patent Document 2, the heat transferred from the combustion chamber to the resonator is reduced, but there is room for improvement in vibration reduction.

[0009] Technical means to solve the problem:

[0010] One aspect of this disclosure is a gas turbine combustor comprising: a cylinder defining a combustion chamber, extending from a first side in an axial direction to a second side, with an outlet defined on the second side in the axial direction; an airflow path for supplying air to the combustion chamber; and at least one resonator including at least one opening leading to the airflow path. The airflow path includes: an upstream region along an outer peripheral surface of the cylinder; a downstream region along an inner peripheral surface of the cylinder, disposed relative to the combustion chamber on the first side in the axial direction and communicating with the combustion chamber; and a direction-changing region connecting the upstream region and the downstream region radially in the cylinder, adjacent to the upstream region between the upstream region and the direction-changing region, accompanied by a change in cross-sectional area orthogonal to the axial direction. The opening leads to a space in the airflow path downstream of the upstream region.

[0011] One aspect of this disclosure is a gas turbine combustor comprising: a cylinder defining a combustion chamber, extending from a first side in an axial direction to a second side, with an outlet defined on the second side in the axial direction; and an air flow path for supplying air to the combustion chamber. The air flow path includes: an upstream region along an outer peripheral surface of the cylinder; a downstream region along an inner peripheral surface of the cylinder, disposed relative to the combustion chamber on the first side in the axial direction and communicating with the combustion chamber; and a direction-changing region connecting the upstream region and the downstream region radially in the cylinder. The cylinder has a leakage orifice that bypasses the direction-changing region to communicate between the downstream region and the upstream region.

[0012] Invention effects:

[0013] According to one aspect of this disclosure, it is possible to effectively reduce vibrations caused by combustion without the need for a special cooling structure. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of a gas turbine engine;

[0015] Figure 2 This is a cross-sectional perspective view of the burner according to the first embodiment;

[0016] Figure 3 yes Figure 2 A cross-sectional view of the burner;

[0017] Figure 4 This is an explanation Figure 3 The attached diagram shows the propagation of low-frequency pressure waves in a burner;

[0018] Figure 5 This is an explanation Figure 3 The attached diagram shows the propagation of high-frequency pressure waves in a burner;

[0019] Figure 6 This is an explanation Figure 3 The attached figure shows the path difference of pressure wave propagation in the direction-switching region.

[0020] Figure 7 (A) in the diagram is shown Figure 3 A perspective view of a modified example of the resonator, (B) is a sectional view along line VIIB-VIIB of (A), and (C) is a sectional view along line VIIC-VIIC of (A).

[0021] Figure 8 (A) in the diagram is shown Figure 3 A sectional view of the main part of the first modified example of the burner, (B) is shown. Figure 3 A sectional view of the main part of a second variant of the burner, (C) is shown. Figure 3A cross-sectional view of the main part of the third variant of the burner;

[0022] Figure 9 This is a cross-sectional view of the main part of the burner in the second embodiment;

[0023] Figure 10 (A) in the diagram is shown Figure 9 A three-dimensional view of a modified example of the resonator, (B) is a cross-sectional view of (A) along the XB-XB line;

[0024] Figure 11 (A) in the diagram is shown Figure 9 A sectional view of the main part of the first modified example of the burner, (B) is shown. Figure 9 A cross-sectional view of the main part of a second variant of the burner;

[0025] Figure 12 This is a cross-sectional view of the main part of the burner according to the third embodiment;

[0026] Figure 13 (A) to (C) in the diagram are schematic diagrams showing the changing states of the airflow path in the burner;

[0027] Figure 14 This is a cross-sectional view of the main part of the burner according to the fourth embodiment;

[0028] Figure 15 This is a cross-sectional view of the main part of the burner according to the fifth embodiment. Detailed Implementation

[0029] The embodiments will now be described with reference to the accompanying drawings.

[0030] Figure 1 This is a schematic diagram of gas turbine engine 1. (As shown...) Figure 1 As shown, the gas turbine engine 1 (hereinafter referred to as the gas turbine) includes a rotating shaft 2, a compressor 3, a combustor 4, and a turbine 5. In the gas turbine 1, compressed air supplied from the compressor 3 is introduced into the combustor 4. The mixture of fuel supplied from the fuel supply line and compressed air supplied from the compressor 3 is burned in the combustor 4. The high-temperature, high-pressure combustion gas discharged from the combustor 4 drives the turbine 5. The turbine 5 is mechanically connected to a load 6 (e.g., a generator) and the compressor 3 via the rotating shaft 2.

[0031] (First Implementation)

[0032] Figure 2 This is a cross-sectional perspective view of the burner 4 according to the first embodiment. Figure 3 yes Figure 2A cross-sectional view of the burner 4. Furthermore, in the following description, the direction in which the axis C of the outer casing 11 and the cylinder 12 extends is referred to as the "axial direction X". In the axial direction X, the side opposite to the outlet 32 ​​of the cylinder 12 is referred to as the "first side", and the side opposite to the outlet 32 ​​is referred to as the "second side". The direction orthogonal to the axial direction X is referred to as the "radial Y". The direction extending circumferentially around the axis C is referred to as the "circumferential Z".

[0033] Combustor 4 (also known as a gas turbine combustor) is, for example, around gas turbine 1 (see reference). Figure 2 The combustor 4 is one of multiple canister-type burners arranged in a ring around the rotating shaft 2. However, the combustor 4 is not limited to this; for example, it can also be applied to a gas turbine with only one burner. Figure 2 and Figure 3 As shown, the burner 4 includes a housing 11, a cylinder 12, a fuel injector 13, an igniter 14, a fuel supply structure 15, an air flow path 16, a rectifier 17, and a resonator 18.

[0034] The outer casing 11 includes a cylindrical cover 21 and an end plate 22. The cylindrical cover 21 has a cylindrical shape, extending from the first side in the axial direction X ( Figure 3 (left side) to the second side ( Figure 3 (Right side) Extending. The shroud 21 has an air inlet 30 with an opening on the second side for air intake from the compressor 3 (see right side). Figure 1 The end plate 22 is disposed on a first side in the axial direction X relative to the cylinder 12 and has an inner surface facing the air flow path 16 described later. The end plate 22 closes the opening on the first side of the cylinder cover 21 and is fixed to the end of the first side of the cylinder cover 21 by fasteners.

[0035] The cylinder 12 is housed within the outer casing 11. The axis C of the cylinder 12 is aligned with the axis of the outer casing 11. The cylinder 12 includes a combustion cylinder 23 as a first cylinder and a support cylinder 24 as a second cylinder. The combustion cylinder 23 defines a combustion chamber 31 on its inner side. The exhaust port 32 of the combustion cylinder 23 opens on its second side. The support cylinder 24 is adjacent to the first side of the combustion cylinder 23 and is arranged coaxially with the combustion cylinder 23. The support cylinder 24 defines an air chamber 33 on its inner side in the radial direction Y. The material of the combustion cylinder 23 (e.g., a cobalt alloy or a nickel alloy) has higher heat resistance than the material of the support cylinder 24 (e.g., stainless steel). Alternatively, the cylinder 12 may function solely as the combustion cylinder 23, omitting the support cylinder 24.

[0036] Fuel injector 13 is housed in cylinder 12. Fuel injector 13 has a fuel injection port 13a that opens into combustion chamber 31. Fuel injection port 13a is configured to inject fuel F supplied from fuel supply structure 15 (described later) together with air A supplied from air chamber 33 into combustion chamber 31. Fuel injector 13 is disposed on a first side in the axial direction X relative to combustion chamber 31. In this embodiment, as an example, fuel injector 13 is disposed corresponding to the boundary between combustion cylinder 23 and support cylinder 24, dividing combustion chamber 31 and air chamber 33.

[0037] In addition, fuel F can be a gaseous fuel containing carbon (natural gas, propane) or hydrogen (hydrogen), but liquid fuel can also be used. Furthermore, fuel F and air A can be premixed into a mixture and injected into combustion chamber 31, or they can be mixed within combustion chamber 31.

[0038] Igniter 14 penetrates radially Y through the shroud 21 and the combustion chamber 23, with the ignition part 14a of igniter 14 protruding into the combustion chamber 31. When the burner 4 starts, the mixed gas injected from the fuel injector 13 into the combustion chamber 31 is ignited by igniter 14, generating a flame in the combustion chamber 31. The high-temperature, high-pressure combustion gas G generated in the combustion chamber 31 is discharged from the outlet 32.

[0039] The fuel supply structure 15 is not particularly limited in structure as long as it can supply fuel F from the fuel supply line outside the housing 11 to the fuel injector 13. In this embodiment, as an example, the fuel supply structure 15 includes a main pipe 25 and multiple branch pipes 26 and 27 branching off from the main pipe 25.

[0040] The main pipe 25 passes through the end plate 22 along the axis C of the cylinder 12 and extends along the axial direction X. One end of the main pipe 25 is disposed in the air chamber 33, and the other end of the main pipe 25 is disposed outside the outer casing 11. The main pipe 25 has a multi-pipe structure in which multiple cylindrical pipes are arranged concentrically, and multiple cylindrical fuel supply passages 25a and 25b are arranged concentrically inside it. Branch pipes 26 and 27 connect the main pipe 25 to the fuel injector 13. The interior of the branch pipe 26 communicates with the fuel supply passage 25a, and the interior of the branch pipe 27 communicates with the fuel supply passage 25b.

[0041] Branch pipes 26 and 27 have portions protruding radially outward from the main pipe 25 in the Y direction and portions extending axially in the X direction toward the fuel injector 13. The radial Y positions at which each branch pipe 26 and 27 connects to the fuel injector 13 are different. By adjusting the opening of a flow control valve that regulates the flow rate of each fuel supply path 25a and 25b, the flow rate of fuel F supplied to each part of the fuel injector 13 can be independently controlled.

[0042] Airflow path 16 is configured to draw air from compressor 3 (reference) Figure 1 The supplied air A is supplied to the combustion chamber 31. The air flow path 16 has a counter-flow shape that extends from the air inlet 30 to a first side in the axial direction X and turns back towards a second side in the axial direction X.

[0043] The airflow path 16 has an air inlet path 34 that forms a gap between the inner circumferential surface of the outer casing 11 and the outer circumferential surface of the cylinder 12. The air inlet path 34 will be supplied by the compressor 3 (see reference). Figure 1 Compressed air A is introduced through air inlet 30 and directed in the opposite direction to the flow direction of combustion gas G in combustion chamber 31. Alternatively, an axial flow system with the same flow direction for air A and combustion gas G can also be used.

[0044] The support cylinder 24 has a plurality of air inlets 35 arranged circumferentially in the Z direction on its first side. Alternatively, the air inlets of the support cylinder 24 can be large enough to include multiple air inlets 35. The air inlets 35 connect the air inlet passage 34 to the air chamber 33. Air A flowing in the air inlet passage 34 is introduced into the air chamber 33 on the radially Y-inward side of the support cylinder 24 through the air inlets 35. The air A introduced into the air chamber 33 flows toward the fuel injector 13, where it mixes with fuel F.

[0045] The rectifier plate 17 is configured within the support cylinder 24 orthogonal to the axis C. The rectifier plate 17 is positioned on the second side of the support cylinder 24, closer to the axial direction X than the air inlet 35. The outer periphery of the rectifier plate 17 is fixed to the support cylinder 24, and its inner periphery is fixed to the end plate 22 via a cylindrical bracket embedded in the mother tube 25. The rectifier plate 17 has a plurality of rectifier holes 17a. The rectifier plate 17 divides the air chamber 33 into two spaces arranged along the axial direction X. That is, the rectifier plate 17 divides the air chamber 33 into a pre-rectification space 33a and a post-rectification space 33b.

[0046] The pre-rectification space 33a is the space on the first side of the air chamber 33, adjacent to the air inlet 35. The post-rectification space 33b is the space on the second side of the air chamber 33, adjacent to the fuel injector 13. The rectifier 17 is located on the second side in the axial direction X, above the air inlet 35. The rectifier 17 rectifies the air A introduced into the air chamber 33 from the air inlet 35 into a uniform airflow toward the combustion chamber 31. Alternatively, the rectifier 17 may be omitted.

[0047] In this embodiment, the airflow path 16 is composed of an air inlet path 34, an air inlet 35, and an air chamber 33. The airflow path 16 can also be divided into an upstream region R1, a direction conversion region R2, and a downstream region R3.

[0048] The upstream region R1 is located along the outer circumferential surface of the cylinder 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 inlet path 34. The downstream region R3 is located along the inner circumferential surface of the cylinder 12 between the air inlet 35 and the fuel injector 13 in the axial direction X. The downstream region R3 is part of the air chamber 33. The direction-changing region R2 connects the upstream region R1 and the downstream region R3.

[0049] The direction-changing region R2 is adjacent to the upstream region R1, accompanied by a change in cross-sectional area orthogonal to the axial direction X, between the upstream region R1 and the direction-changing region R2. The virtual boundary surface M between the upstream region R1 and the direction-changing region R2 is a virtual surface that passes through the end E of the air inlet 35 on the second side of the axial direction X and is orthogonal to the axial direction X. That is, the virtual boundary surface M is a virtual surface that passes through the end E on the second side of the flow path extending radially Y to connect the upstream region R1 and the downstream region R3 in the air flow path 16, is orthogonal to the axial direction X, and is located on the outer side of the radial Y of the end E.

[0050] The virtual boundary surface N between the direction-changing region R2 and the downstream region R3 is also a virtual surface that passes through the end E of the air inlet 35 and is orthogonal to the axial direction X. That is, the virtual boundary surface N is a virtual surface that passes through the second side of the axial direction X of the flow path extending radially Y to connect the upstream region R1 and the downstream region R3 in the airflow path 16, is orthogonal to the axial direction X, and is located inside the radial direction Y of the end E. The rectifier plate 17 is disposed in the downstream region R3.

[0051] The resonator 18 (first resonator) includes an opening 41, a throttling section 42, and a resonance chamber 43. The opening 41 faces the space (direction reversal region R2 or downstream region R3) downstream of the virtual boundary surface M in the airflow path 16. In this embodiment, the opening 41 directly faces the downstream region R3, opening onto the downstream region R3 from the inner circumference of the support cylinder 24. The opening 41 is continuous with the downstream region R3. The resonator 18 utilizes a portion of the support cylinder 24. The throttling section 42 is the flow path connecting the opening 41 and the resonance chamber 43. The resonance chamber 43 is a space larger than the throttling section 42. The area of ​​the opening 41, the length of the throttling section 42, and the volume of the resonance chamber 43 are determined according to the desired attenuation frequency. Alternatively, the support cylinder 24 may protrude radially outward (Y-axis), with the resonator 18 located radially inward (Y-axis) of this protruding portion. In this case, the plate having the opening 41 and the throttling section 42 is located between the downstream region R3 and the resonance chamber 43. That is, the inner circumferential surface of the support cylinder 24 uses the radial Y inner surface of the plate of the resonator 18.

[0052] The opening 41 of the resonator 18 opens into the airflow path 16, which is upstream of the combustion chamber 31. Therefore, compared to the case where the opening is directed into the combustion chamber, the internal temperature of the resonator 18 is lower, and no special cooling is required for the resonator 18. Thus, NOx increases can be prevented without the need for a special cooling structure and without increasing the combustion temperature to compensate for the amount of cooling.

[0053] In the airflow path 16, the cross-sectional area orthogonal to the axial direction X changes at the boundary (virtual boundary surface M) between the upstream region R1 and the direction-changing region R2. Downstream of the virtual boundary surface M, pressure waves caused by combustion vibrations and transmitted from the combustion chamber 31 in a counter-current manner within the airflow path 16 are partially reflected or canceled out. If we focus on the transmission of pressure waves generated in the combustion chamber 31 to simplify pressure variations within the burner 4, this reflection tends to make the sound pressure level in the space downstream of the upstream region R1 in the airflow path 16 higher than that in the upstream region R1. Therefore, an opening 41 is provided in the space downstream of the upstream region R1 in the airflow path 16, thereby effectively absorbing pressure waves transmitted from the combustion chamber 31 to the airflow path 16 and reducing vibrations caused by combustion.

[0054] Figure 4 This is an explanation Figure 3 The attached diagram shows the propagation of low-frequency pressure waves in burner 4. Figure 4 As shown, consider a pressure wave with a relatively low frequency, i.e., a pressure wave with a wavelength considered relatively long relative to the size of the propagation space. In this case, the pressure wave P1, traveling counterclockwise from the combustion chamber 31 in the airflow path 16, travels towards the first side along the axial direction X. At the first side along the axial direction X, it is reflected by the wall of the direction-switching region R2, and the reflected wave P2 travels towards the second side along the axial direction X. The reflected wave P2 is divided into a component reflected at end E of the air inlet 35 and other components. The component reflected by the wall remains in the direction-switching region R2. The component not reflected at end E is divided into a component traveling towards the upstream region R1 and a component remaining in the direction-switching region R2 and the downstream region R3. Therefore, the pressure wave propagating to the upstream region R1 is smaller than the pressure wave in the space downstream of the virtual boundary surface M. That is, the sound pressure in the direction-switching region R2 and the downstream region R3 is greater than that in the upstream region R1. Therefore, by having an opening 41 in the space of the air flow path 16 that is downstream of the upstream region R1, the pressure wave transmitted from the air in the combustion chamber 31 to the air flow path 16 can be effectively absorbed.

[0055] Figure 5 This is an explanation Figure 4 The attached diagram shows the propagation of high-frequency pressure waves in burner 4. Figure 5In this case, a pressure wave with a relatively high frequency, i.e., a pressure wave with a wavelength considered to be relatively short relative to the size of the propagation space, is considered. In this case, the pressure wave traveling counter-currently from the combustion chamber 31 in the airflow path 16 is divided into a component P3 reflected by the wall of the direction-switching region R2, and a component P4 that is directionally switched along the flow path axis of the direction-switching region R2 and transmitted upstream to the region R1. Component P3 of the pressure wave reflected by the wall of the direction-switching region R2 remains in both the direction-switching region R2 and the downstream region R3 (a portion of component P3 can also be transmitted to the upstream region R1). Therefore, the sound pressure level in the direction-switching region R2 and the downstream region R3 is higher than that in the upstream region R1. Therefore, by having an opening 41 in the space downstream of the upstream region R1 in the airflow path 16, the pressure wave transmitted from the air in the combustion chamber 31 to the airflow path 16 can be effectively absorbed.

[0056] Figure 6 This is an explanation Figure 3 The attached diagram shows the path difference of pressure wave propagation in the direction-reversal region R2. Figure 6 As shown, when the pressure wave propagates along the curved path of the direction-switching region R2, a path difference is generated between the inner circumferential path P5 and the outer circumferential path P6. This results in a phase shift between the pressure wave passing through the inner circumferential path P5 and the pressure wave passing through the outer circumferential path P6. At the virtual boundary surface M, the pressure waves partially cancel each other out due to interference from the superposition of these pressure waves with different phases. Therefore, the sound pressure level in the direction-switching region R2 and the downstream region R3 is higher than that in the upstream region R1. Therefore, by having an opening 41 in the airflow path 16, which is located downstream of the upstream region R1, the pressure wave transmitted from the combustion chamber 31 to the airflow path 16 can be effectively absorbed.

[0057] Specifically, the opening 41 of the resonator 18 faces and opens into the downstream region R3. The cross-sectional area of ​​the airflow path 16, orthogonal to the axial direction X, also changes in the virtual boundary N between the direction-switching region R2 and the downstream region R3. The downstream region R3 is closer to the combustion chamber 31 than the direction-switching region R2. Therefore, by opening the resonator 18 into the downstream region R3 through the opening 41, pressure waves can be absorbed more effectively.

[0058] More specifically, the opening 41 of the resonator 18 faces and opens into the rear rectification space 33b. In the rectification aperture 17a of the rectifier plate 17, the cross-sectional area of ​​the flow path orthogonal to the axial direction X also changes, causing partial reflection of the pressure wave within the rectifier plate 17. Therefore, by opening the resonator 18 through the opening 41 into the rear rectification space 33b, the pressure wave can be absorbed more effectively.

[0059] The resonator 18 opens into the airflow path 16, which only allows air to flow. Therefore, the gas introduced into the resonator 18 is not a fuel-containing gas like a mixed gas. The fuel content in the mixed gas varies depending on the engine output, causing the speed of sound to vary accordingly, making the design of the resonant frequency more difficult. The resonator 18 opening into the airflow path 16 avoids this problem. Alternatively, it could be configured such that a mixture of air and fuel flows through the airflow path 16.

[0060] The resonator 18 is housed in the housing 11 and disposed on the support cylinder 24. The resonator 18, for example, has a resonator body 50 that fits into the outer peripheral surface of the support cylinder 24. The resonator 18 is composed of a portion of the support cylinder 24 and the resonator body 50. The resonator body 50 is a cylindrical hollow component. The throttling section 42 is a through hole formed in the inner peripheral wall of the resonator body 50 and the support cylinder 24.

[0061] The radial Y length of the throttling section 42 is determined by the wall thickness of the inner circumferential wall of the resonator body 50. The opening 41 is the opening on the radial Y side inside the aforementioned through hole of the support cylinder 24. The openings 41 are arranged along the axial direction X and along the circumferential direction Z. All the openings 41 and the throttling section 42 communicate with a resonance chamber 43, but are not limited thereto; the resonance chamber 43 may also be divided into multiple cavities.

[0062] Alternatively, the resonator 18 may not be arranged around the entire outer circumference of the support cylinder 24, but rather partially arranged along the circumferential Z direction. The resonator body 50 may not be a hollow component, but may be a cover component that covers the outer circumferential surface of the support cylinder 24 (eliminating the inner circumferential wall of the resonator body 50). In this case, the gap between the inner circumferential surface of the cover component and the outer circumferential surface of the support cylinder 24 can be used as the resonance chamber 43.

[0063] The resonator 18 protrudes upstream of the support cylinder 24 from the portion adjacent to it in the axial direction X. That is, the outer peripheral surface of the resonator 18 is located radially outward from the outer peripheral surface of the portion adjacent to it in the axial direction X of the support cylinder 24. In this embodiment, the resonator body 50, externally mounted in the support cylinder 24, is configured to protrude upstream of the support cylinder 24 from the support cylinder 24 into the upstream region R1. The inner peripheral surface of the support cylinder 24 extends linearly along the axial direction X. Therefore, when the resonator 18 is mounted in the support cylinder 24, the air chamber 33 can be enlarged. The outer surface of the resonator 18 facing the upstream region R1 can be configured as a streamlined shape that gradually narrows towards both sides in the axial direction X.

[0064] Figure 7 (A) in the diagram is shown Figure 3 A three-dimensional view of a modified example of the resonator 18. Figure 7 (B) in the diagram is a sectional view along line VIIB-VIIB of (A). Figure 7In this diagram, (C) is a sectional view along line VIIC-VIIC of (A). For example... Figure 7 As shown in (A) to (C), the resonator 18 may have a partition 44 that divides the resonant chamber 43 into a plurality of cavities 45. The plurality of cavities 45 are respectively connected to a plurality of openings 41.

[0065] The partition 44 divides the resonating chamber 43 along both the axial direction X and the circumferential direction Z. Specifically, the partition 44 has a portion extending along the axial direction X and a portion extending along the circumferential direction Z. It is possible for only one opening 41 to communicate with one cavity 45, or for multiple openings 41 to communicate with one cavity 45. In a developed view viewed from the radial direction Y, the partition 44 can be arranged to divide each cavity 45 into a polygonal (e.g., quadrilateral, hexagonal, etc.) or circular shape.

[0066] Therefore, even if sound pressures of opposite phase are distributed in both the axial direction (X) and the circumferential direction (Z), interference between sound pressures of opposite phase is prevented. Thus, the reduction in resonance volume caused by sound pressure interference is prevented, and resonance can be induced at the designed frequency.

[0067] Figure 8 (A) in the diagram is shown Figure 3 A cross-sectional view of the main part of the first modified example of burner 4. (See image) Figure 8 As shown in (A), in the burner 104 of the first modified example, the resonator 118 protrudes downstream of the portion of the support cylinder 24 adjacent to the resonator 18 in the axial direction X towards the downstream region R3. That is, the inner circumferential surface of the resonator 118 is located radially inward of the inner circumferential surface of the portion of the support cylinder 24 adjacent to the resonator 18 in the axial direction X. In this embodiment, the resonator body 150 embedded in the support cylinder 24 is configured to protrude downstream of the support cylinder 24 towards the downstream region R3. The outer circumferential surface of the support cylinder 24 may, for example, extend linearly along the axial direction X. Thus, when the resonator 118 is provided in the support cylinder 24, the narrowing of the upstream region R1 can also be prevented. Alternatively, the resonator may also be configured in Figure 3 The position of resonator 18 and Figure 8 The position of resonator 118 in (A) is in the middle.

[0068] Figure 8 (B) in the text is shown Figure 3 A cross-sectional view of the main part of the second variant of burner 4. (See image) Figure 8 As shown in (B) of the diagram, in the burner 204 of the second variation, the resonator 18 is the same as in the aforementioned embodiment, but the casing 221 is different. The casing 221 has a bulge 221a that expands radially outward in the Y direction at the portion opposite to the resonator 18 in the radial direction Y. This prevents the portion of the resonator 18 in the upstream region R1 from narrowing in the radial direction Y.

[0069] Figure 8 (C) in the diagram is shown Figure 3 A cross-sectional view of the main part of the third variant of burner 4. (See image) Figure 8 As shown in (C), in the burner 304 of the third modification, the resonator 318 (third resonator) protrudes outward from the casing 21. The resonator 318 has a resonator body 350 connected to the outer peripheral surface of the support cylinder 24. The resonator body 350 has a hollow portion 350a defining the resonance chamber 343 and a tube portion 350b protruding radially inward from the resonator body 350.

[0070] The hollow section 350a is positioned on the outer side of the cylindrical cover 21 in the radial Y direction. Additionally, in Figure 8 In (C), the casing 21 and the resonator body 350 are in contact with each other, but they may not be in contact. The tube portion 350b passes through the casing 21 radially and crosses the upstream region R1 radially, connecting with the support tube 24. The support tube 24 has a through hole on its inner circumferential surface forming an opening 41 facing the downstream region R3, which communicates with the internal space of the tube portion 350b. That is, the internal space of the tube portion 350b and the through hole of the support tube 24 constitute a throttling section 342. As a result, the degree of freedom in the volume of the resonant chamber 343 can be increased, and the degree of freedom in setting the attenuation frequency can be improved. For example, it is possible to design an enlarged resonant chamber 343 and reduce low-frequency vibrations.

[0071] (Second Implementation)

[0072] Figure 9 This is a cross-sectional view of the main part of the burner 404 according to the second embodiment. (See attached image.) Figure 9 As shown, in the burner 404, a resonator 418 (second resonator) is disposed on the end plate 422 of the housing 411. The end plate 422 has a recess 422a opposite to the air chamber 33 and extending annularly about axis C. The resonator 418 is accommodated in the recess 422a. The resonator 418 is an annular hollow member similar to the recess 422a.

[0073] The resonator 418 has an opening 441, a throttling section 442, and a resonating chamber 443. The resonating chamber 443 is an annular hollow space within the resonator 418. Alternatively, it can be configured such that a portion of the wall in the resonator 418 is omitted, and the resonating chamber 443 is defined using the surface of the end plate 422. The openings 441 are arranged at intervals around axis C on the surface of the resonator 418 opposite to the air chamber 33. The throttling section 442 is a through hole in the wall of the resonator 418 opposite to the air chamber 33, connecting the opening 441 and the resonating chamber 443.

[0074] The opening 441 of the resonator 418 directly faces the air chamber 33 and opens into it. The opening 441 is continuous with the direction-changing region R2. The opening 441 opens into the direction-changing region R2 radially inward than the air inlet 35. The opening 441 opens along the axial direction X toward the combustion chamber 31. Specifically, the axis of the opening 441 is substantially parallel to the axis C. The axis of the throttling section 442 extends along the axial direction X.

[0075] The cross-sectional area of ​​the airflow path 16 changes orthogonally to the axial direction X in the virtual boundary surface M. Downstream of the virtual boundary surface M, the pressure wave is partially reflected or canceled out. Therefore, the opening 441 of the resonator 418 opens towards the direction conversion region R2, thereby effectively absorbing the pressure wave. Furthermore, the opening 441 faces the axial direction X, thus effectively absorbing the pressure wave transmitted from the combustion chamber 31 along the axial direction X. The resonator provided in the burner 404 can be only the resonator 418, or it can also use the resonator 18 of the first embodiment (or any one of the resonators 118, 218, and 318 of the first to fourth variations). Other structures are the same as those described in the first embodiment, so descriptions are omitted.

[0076] Figure 10 (A) in the diagram is shown Figure 9 A three-dimensional view of a modified example of the resonator 418. Figure 10 In this diagram, (B) is a cross-sectional view along line XB-XB of (A). For example... Figure 10 As shown in (A) and (B), the resonator 418 may have a partition 444 that divides the resonance chamber 443 into multiple cavities 445. The multiple cavities 445 are respectively connected to multiple openings 441.

[0077] The partition 444 divides the resonant chamber 443 circumferentially along the Z direction. It can have only one opening 441 communicating with one cavity 445, or multiple openings 441 communicating with one cavity 445. Viewed from the axial direction X, the partition 444 can be configured to divide the cavities 445 in a fan-shaped configuration.

[0078] Therefore, even if sound pressures of opposite phases are distributed in the circumferential Z direction, interference between sound pressures of opposite phases is prevented. This prevents the reduction in resonance volume caused by sound pressure interference and enables resonance to occur at the designed frequency. Furthermore, each cavity 445 can also be divided radially. If each cavity 445 is divided radially Y, interference between sound pressures of opposite phases is prevented even if there are sound pressure distributions of opposite phases in the radial Y direction.

[0079] Figure 11 (A) in the diagram is shown Figure 9 A sectional view of the main part of a first modified example of burner 404. (See image) Figure 11As shown in (A), in the burner 504 of the first modified example, the resonator 518 protrudes from the end plate 522 toward the air chamber 33 along the axial direction X. The shape of the resonator 518 itself is the same as that of the resonator 418 described above. This can mitigate the local thinning of the end plate 522. In addition, the resonator 518 as a whole can be located on the second side of the end plate 522 in the axial direction X, i.e., in the air chamber 33.

[0080] Figure 11 (B) in the text is shown Figure 9 A cross-sectional view of the main part of a second variant of burner 404. (See image) Figure 11 As shown in (B) of the second modified burner 604, the resonator 618 (third resonator) protrudes outward from the end plate 622. The resonator 618 has a resonator body 650 connected to the outer surface of the end plate 622. The resonator body 650 is disposed on the outside of the housing 11, and a resonance chamber 643 is defined therein. Furthermore, in Figure 11 In (B), the resonator body 650 and the end plate 622 are in contact with each other, but they may not be in contact. The end plate 622 has a through hole extending along the axial direction X that communicates with the resonance chamber 643.

[0081] The through hole in the end plate 622 constitutes a throttling section 642. The wall in the resonator body 650 that contacts the surface of the end plate 622 (the wall that forms part of the throttling section 642) can be omitted. Alternatively, the resonator body 650 may not contact the surface of the end plate 622. The end plate 622 has an opening 641 on the surface defining its air chamber 33 (the surface on the second side in the axial direction X), which serves as the inlet of the throttling section 642. This increases the freedom of designing the volume of the resonant chamber 643 and improves the freedom of setting the attenuation frequency. For example, it is possible to design an enlarged resonant chamber 643 and reduce low-frequency vibrations.

[0082] (Third Implementation)

[0083] Figure 12 This is a cross-sectional view of the main parts of the burner 704 according to the third embodiment. (See attached image.) Figure 12As shown, the burner 704 has resonators 718A and 718B that partially open radially outward from the air inlet 35 in the direction conversion region R2. Resonator 718A is disposed on the casing 721, with its opening 741A positioned radially outward from the direction conversion region R2 and opening radially inward from the direction Y. Resonator 718B is disposed on the end plate 722, with its opening 741B positioned on a first side in the axial direction X of the direction conversion region R2 and opening to a second side in the axial direction X. The burner 704 may also include the resonator 18 of the first embodiment, or the resonator 418 of the second embodiment. Other structures are the same as those described in the first embodiment, and therefore will not be described further.

[0084] Figure 13 (A) to (C) in the diagram are schematic diagrams showing the changing states of the airflow path 16 of the burner 4. In addition, for ease of understanding, each element in this changing state corresponding to each element of the first embodiment is labeled with the same reference numerals as in the first embodiment, even if the shape is different.

[0085] exist Figure 13 In (A), the outer shell 11 is configured such that the upstream region R1, the direction-changing region R2, and the downstream region R3 are all annular, extending around the axis of the cylinder 12. Figure 13 In (B), the cylinder 12 is covered by a guide member 19 housed in a shell (not shown). The guide member 19 is configured such that the upstream region R1, the direction-changing region R2, and the downstream region R3 are all annular, extending around the axis of the cylinder 12. Figure 13 In (C), the outer shell 11 is configured such that: the direction conversion 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.

[0086] exist Figure 13 In any of (A) to (C), the virtual boundary surface M between the upstream region R1 and the direction-switching region R2 is a virtual surface that passes through the second end E of the airflow path 16, which extends radially along the Y direction to connect the upstream region R1 and the downstream region R3, and is orthogonal to the axial direction X. On the virtual boundary surface M, the cross-sectional area of ​​the airflow path 16 in the axial direction X changes, and the opening of the resonator (not shown) opens into the space downstream of the virtual boundary surface M of the airflow path 16.

[0087] (Fourth Implementation)

[0088] Figure 14 This is a cross-sectional view of the main parts of the burner 804 according to the fourth embodiment. (See attached image.) Figure 14As shown, in the burner 804, a resonator 818 is disposed in the cylinder 812 (specifically, the support cylinder 824) and opens to the downstream region R3. The cylinder 812 has a plurality of leakage holes 812a that connect the resonator 818's resonant chamber 843 to the upstream region R1. The leakage holes 812a are located on a second side relative to the axial direction X of the direction-changing region R2. The leakage holes 812a connect the downstream region R3 to the upstream region R1 via the resonator 818 in a manner that bypasses the direction-changing region R2.

[0089] The diameter of each leakage hole 812a is 0.1 mm or more and 10 mm or less. The diameter of the leakage hole 812a is smaller than the diameter of the opening 841 of the resonator 818 and the throttling part 842. Specifically, the diameter of each leakage hole 812a can be set to be more than 1 / 10 of the height of the leakage hole 812a (i.e., the length of the flow path axis of the leakage hole 812a). This improves the machinability of lasers and the like, and effectively reduces pressure waves. Furthermore, the total opening area of ​​the leakage holes 812a can be set to be less than 1 / 2 of the cross-sectional area of ​​the plane perpendicular to the flow direction of the upstream region R1. The leakage holes 812a can release sound energy from the downstream region R3 to the upstream region R1, which can more effectively reduce vibrations caused by combustion. In addition, other structures are the same as those in the first embodiment described above, so descriptions are omitted.

[0090] Figure 14 The resonator 818 and Figure 8 The resonator 118 in (A) is similar, but can be used with Figure 3 Similar to resonator 18, it can also be used with Figure 8 The resonator 318 in (C) is similar. In relation to... Figure 8 In a similar case to the resonator 318 in (C), the leakage hole 812a can be formed in the support cylinder 24 or in the tube 350b.

[0091] (Fifth Implementation)

[0092] Figure 15 This is a cross-sectional view of the main parts of the burner 904 according to the fifth embodiment. Figure 15 As shown, the burner 904 does not have a resonator. The cylinder 912 (specifically the support cylinder 924) has a plurality of drainage holes 912a that connect the downstream region R3 with the upstream region R1. The drainage holes 912a are located on a second side relative to the axial direction X of the direction-changing region R2. The drainage holes 912a bypass the direction-changing region R2 to connect the downstream region R3 with the upstream region R1.

[0093] The diameter of each leakage hole 912a is 0.1 mm or more and 10 mm or less. Specifically, the diameter of each leakage hole 912a can be set to be more than 1 / 10 of the height of the leakage hole 912a (i.e., the length of the flow path axis of the leakage hole 912a). This improves the machinability of lasers and the like, and effectively reduces pressure waves. Furthermore, the total opening area of ​​the leakage holes 912a can be set to be less than 1 / 2 of the cross-sectional area of ​​the plane perpendicular to the flow direction of the upstream region R1. The leakage holes 912a can release sound energy from the downstream region R3 to the upstream region R1, effectively reducing vibrations caused by combustion even without a resonator. Other structural details are the same as in the first embodiment described above, so further explanation is omitted.

[0094] As described above, various embodiments and modifications have been illustrated in this application as examples of the disclosed technology. However, the technology in this disclosure is not limited to this and can also be applied to embodiments with appropriate changes, substitutions, additions, omissions, etc. Furthermore, the constituent elements described in the foregoing embodiments or modifications can be combined to form new embodiments. For example, a portion of the structure or method in one embodiment or modification can be applied to other embodiments or modifications, and a portion of the structure in an embodiment or modification can be separated from other structures in that embodiment or modification and arbitrarily extracted. In addition, the constituent elements described in the drawings and detailed description include not only the constituent elements necessary to solve the problem, but also, for the purpose of illustrating the above technology, non-essential constituent elements for solving the problem.

[0095] The following items are disclosures of preferred embodiments.

[0096] [Project 1]

[0097] A gas turbine burner comprising:

[0098] The cylinder, which defines the combustion chamber, extends from a first side in the axial direction to a second side, and defines the exhaust port on the second side in the axial direction;

[0099] An airflow path for supplying air to the combustion chamber; and

[0100] At least one resonator having at least one opening to the airflow path and a resonating chamber communicating with the opening, the airflow path comprising:

[0101] The upstream region extends along the outer circumferential surface of the cylinder.

[0102] The downstream region, which is disposed along the inner circumferential surface of the cylinder on the first side relative to the combustion chamber in the axial direction, communicates with the combustion chamber; and

[0103] A direction-changing region connects the upstream region and the downstream region radially within the cylinder. Between the upstream region and the direction-changing region, the upstream region is adjacent to the upstream region due to a change in cross-sectional area orthogonal to the axial direction.

[0104] The opening of the resonator opens into a space downstream of the upstream region in the airflow path.

[0105] [Project 2]

[0106] According to the gas turbine combustor described in Project 1, wherein,

[0107] The at least one resonator includes a first resonator.

[0108] The opening of the first resonator opens into the downstream region in the airflow path.

[0109] [Project 3]

[0110] According to the gas turbine burner of Project 2, the first resonator is disposed in the cylinder.

[0111] [Project 4]

[0112] According to the gas turbine burner of Project 3, the outer peripheral surface of the first resonator is located radially outward than the outer peripheral surface of the portion of the cylinder adjacent to the first resonator in the axial direction.

[0113] [Project 5]

[0114] According to the gas turbine burner of Project 3 or 4, the inner circumferential surface of the first resonator is located radially inward of the inner circumferential surface of the portion of the cylinder adjacent to the first resonator in the axial direction.

[0115] [Project 6]

[0116] The gas turbine combustor according to any one of items 1 to 5, wherein,

[0117] The at least one resonator includes a second resonator.

[0118] The opening of the second resonator opens toward the direction conversion region.

[0119] [Project 7]

[0120] According to the gas turbine combustor described in Project 6, wherein...

[0121] The gas turbine burner also includes an end plate disposed on the first side in the axial direction relative to the cylinder, having an inner surface facing the airflow path.

[0122] The second resonator is disposed on the end plate.

[0123] [Project 8]

[0124] The gas turbine combustor according to any one of items 1 to 7, wherein,

[0125] The gas turbine burner also includes a housing that accommodates the cylinder.

[0126] An air inlet path, including the upstream region, exists between the outer casing and the cylindrical body.

[0127] The cylinder body has: a first cylinder defining the combustion chamber; and a second cylinder adjacent to the first cylinder on the first side in the axial direction, defining an air chamber including the downstream region.

[0128] The opening of the at least one resonator opens into the air chamber.

[0129] [Project 9]

[0130] The gas turbine combustor according to any one of items 1 to 8, wherein,

[0131] The gas turbine burner also has a rectifier plate with rectifier orifices that divides the space downstream of the upstream region in the airflow path into a pre-rectifier space and a post-rectifier space.

[0132] The opening of the at least one resonator opens into the rear rectifier space.

[0133] [Project 10]

[0134] According to any one of items 1 to 9, the gas turbine burner wherein the resonating chamber of the at least one resonator is disposed outside the housing.

[0135] [Project 11]

[0136] The gas turbine combustor according to any one of items 1 to 10, wherein,

[0137] The at least one opening includes a plurality of openings arranged along the axial direction and circumferentially about the axial direction, and the at least one resonator has: a partition that divides the resonating chamber into a plurality of cavities respectively communicating with the plurality of openings, and divides the resonating chamber circumferentially.

[0138] [Project 12]

[0139] According to the gas turbine burner of Project 11, the baffle further divides the resonant chamber along the axial direction or the radial direction.

[0140] [Project 14]

[0141] According to any one of items 1 to 12, the gas turbine burner has a drain hole that bypasses the direction conversion region to connect the downstream region with the upstream region.

[0142] [Project 15]

[0143] A gas turbine burner comprising:

[0144] A cylindrical body, which defines a combustion chamber, extends from a first side along an axial direction to a second side, and defines an outlet on the second side along the axial direction; and

[0145] An airflow path for supplying air to the combustion chamber;

[0146] The airflow path includes:

[0147] The upstream region extends along the outer circumferential surface of the cylinder.

[0148] The downstream region, which is disposed along the inner circumferential surface of the cylinder on the first side relative to the combustion chamber in the axial direction, communicates with the combustion chamber; and

[0149] A direction-reversing region that connects the upstream region and the downstream region radially within the cylinder.

[0150] The cylinder has a leakage hole that bypasses the direction conversion region to connect the downstream region with the upstream region.

[0151] Symbol explanation:

[0152] 1: Gas turbine;

[0153] 4: Burner;

[0154] 11: Outer shell;

[0155] 12: Cylinder body;

[0156] 13: Fuel injector;

[0157] 16: Airflow path;

[0158] 17: Rectifier board;

[0159] 17a: Rectifier port;

[0160] 18: Resonator;

[0161] 21: Tube cover;

[0162] 22: End plate;

[0163] 23: Combustion tube (first tube);

[0164] 24: Support cylinder (second cylinder);

[0165] 31: Combustion chamber;

[0166] 32: Discharge outlet;

[0167] 33b: Rear rectifier space;

[0168] 33: Air chamber;

[0169] 33a: Pre-rectification space;

[0170] 34: Air intake path;

[0171] 35: Air inlet;

[0172] 41: Opening;

[0173] 42: Throttling section;

[0174] 43: Resonance Chamber;

[0175] 44: partition;

[0176] 45: Cavity;

[0177] A: Air;

[0178] C: Axis;

[0179] E: End;

[0180] F: Fuel;

[0181] G: Combustion gas;

[0182] M, N: Virtual boundary surfaces;

[0183] R1: Upstream region;

[0184] R2: Direction reversal region;

[0185] R3: Downstream region;

[0186] X: Axis direction;

[0187] Y: Radial direction;

[0188] Z: Zhou Xiang.

Claims

1. A gas turbine combustor, comprising: The cylinder, which defines the combustion chamber, extends from a first side in the axial direction to a second side, and defines the exhaust port on the second side in the axial direction; An airflow path for supplying air to the combustion chamber; At least one resonator having at least one opening to the airflow path and a resonating chamber communicating with the opening; as well as Rectifier board, The airflow path includes: The upstream region extends along the outer circumferential surface of the cylinder. The downstream region, which is disposed along the inner circumferential surface of the cylinder on the first side relative to the combustion chamber in the axial direction, communicates with the combustion chamber; and A direction-changing region connects the upstream region and the downstream region radially within the cylinder. The upstream region is adjacent to the direction-changing region due to a change in cross-sectional area orthogonal to the axial direction. The opening of the resonator opens into a space downstream of the upstream region in the airflow path. The rectifier plate has rectifier holes that divide the space downstream of the upstream region in the airflow path into a pre-rectifier space and a post-rectifier space. The opening of the at least one resonator opens into the rear rectifier space.

2. The gas turbine combustor according to claim 1, The at least one resonator includes a first resonator. The opening of the first resonator opens into the downstream region in the airflow path.

3. The gas turbine combustor according to claim 2, The first resonator is disposed in the cylinder.

4. The gas turbine combustor according to claim 3, The outer peripheral surface of the first resonator is located radially outward from the outer peripheral surface of the portion of the cylinder adjacent to the first resonator in the axial direction.

5. The gas turbine combustor according to claim 3 or 4, The inner circumferential surface of the first resonator is located radially inward of the inner circumferential surface of the portion of the cylinder adjacent to the first resonator in the axial direction.

6. The gas turbine combustor according to any one of claims 1 to 4, The at least one resonator includes a second resonator. The opening of the second resonator opens toward the direction conversion region.

7. The gas turbine combustor according to claim 6, It also includes an end plate, which is disposed on the first side in the axial direction relative to the cylinder, and has an inner surface facing the airflow path. The second resonator is disposed on the end plate.

8. The gas turbine combustor according to any one of claims 1 to 4, It also has an outer shell to house the cylindrical body. An air inlet path, including the upstream region, exists between the outer casing and the cylindrical body. The cylinder body has: a first cylinder defining the combustion chamber; and a second cylinder adjacent to the first cylinder on the first side in the axial direction, defining an air chamber including the downstream region. The opening of the at least one resonator opens into the air chamber.

9. The gas turbine combustor according to any one of claims 1 to 4, It also has an outer shell to house the cylindrical body. The resonant chamber of the at least one resonator is disposed outside the housing.

10. The gas turbine combustor according to any one of claims 1 to 4, The at least one opening includes a plurality of openings arranged along the axial direction and circumferentially arranged about the axial direction. The at least one resonator has: a partition that divides the resonating chamber into a plurality of cavities respectively communicating with the plurality of openings, and divides the resonating chamber along the circumferential direction.

11. The gas turbine combustor according to claim 10, The partition further divides the resonance chamber along the axial direction or the radial direction.

12. The gas turbine combustor according to any one of claims 1 to 4, wherein, The cylinder has a leakage hole that bypasses the direction conversion region to connect the downstream region with the upstream region.

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