Combustor for gas turbine, gas turbine, and assembling method of gas turbine

Abstract

The acoustic device of the combustor of the gas turbine according to one embodiment has: a first region existing in at least either of a pair of positions sandwiching the combustor in the radial direction of the combustor on the downstream side of the combustor; a pair of second regions existing in positions sandwiching the combustor in the radial direction at positions in which at least a part of the axial position of the combustor overlaps the pair of positions and the circumferential position of the combustor is different from the pair of positions; and a third region located on the upstream side of the combustor with respect to the first region and the second region. The thickness of the acoustic device in the radial direction in the pair of second regions is smaller than the thickness of the acoustic device in the radial direction in the first region, and the thickness of the acoustic device in the radial direction in the third region is larger than the thickness of the acoustic device in the radial direction in the pair of second regions.

Description

Technical Field

[0001] This disclosure relates to a burner for a gas turbine, a gas turbine, and a method for assembling a gas turbine. This application claims priority based on Japan Patent Application No. 2021-049675, filed on March 24, 2021, the contents of which are incorporated herein by reference. Background Technology

[0002] A gas turbine consists of a compressor, a burner, and a turbine. Air is taken in by the compressor and compressed to high pressure, which is then sent to the burner.

[0003] In the combustor, fuel is burned by blowing high-pressure air through it. The high-temperature combustion gases produced by the combustion are then fed to the turbine, which drives the turbine.

[0004] The turbine and the compressor rotate about the same axis of rotation, so the turbine is driven in this way, and the compressor is also driven to take in air and compress it as described above.

[0005] Gas turbines operating in this manner experience combustion vibrations during fuel combustion, which contribute to the noise and vibration during turbine operation.

[0006] Therefore, in order to suppress the sound and vibration caused by the combustion vibration, the burner is provided, for example, with a sound liner consisting of a perforated plate and a cover covering its outer side to absorb higher frequency sound, or with a sound attenuator having a large resonance space to absorb lower frequency sound (see, for example, Patent Document 1).

[0007] Prior art literature

[0008] Patent documents

[0009] Patent Document 1: Japanese Patent Application Publication No. 2013-117231 Summary of the Invention

[0010] The problem that the invention aims to solve

[0011] Generally, in industrial gas turbines, multiple gas turbine burners are arranged circumferentially around the gas turbine. Furthermore, based on the relationship between the turbine blades and the radial position of the burners within the gas turbine, the burners are positioned close to the radially inner side of the gas turbine. Therefore, there is a tendency for the spacing between adjacent burners in the circumferential direction of the gas turbine to become smaller.

[0012] Because compressed air from the compressor has difficulty flowing through the space between adjacent burners in the circumferential direction of the gas turbine, the flow of compressed air into the burners may be subject to greater deviations due to the circumferential position of the burners. Therefore, this can lead to localized increases in flame temperature within the combustion chamber, potentially resulting in increased combustion vibration and NOx levels.

[0013] In view of the above, the object of at least one embodiment of the present disclosure is to suppress deviations in the circumferential position of the combustion chamber for the flow of compressed air into the combustion chamber.

[0014] Solution for solving the problem

[0015] (1) The gas turbine burner of at least one embodiment of the present disclosure includes:

[0016] Combustion tube; and

[0017] A sound-emitting device is disposed on the outer periphery of the combustion cylinder.

[0018] The acoustic device has:

[0019] A first region exists at least one of a pair of locations located downstream of the combustion chamber and sandwiching the combustion chamber radially.

[0020] A pair of second regions, existing at least partially overlapping the pair of locations in the axial direction of the combustion chamber, and at a location in the radial direction that sandwiches the combustion chamber, and where the circumferential position of the combustion chamber differs from the pair of locations; and

[0021] The third region is located upstream of the combustion chamber relative to the first and second regions.

[0022] The radial thickness of the acoustic device in the pair of second regions is smaller than the radial thickness of the acoustic device in the first region.

[0023] The radial thickness of the acoustic device in the third region is greater than the radial thickness of the acoustic device in the pair of second regions.

[0024] (2) At least one embodiment of the gas turbine of this disclosure includes a plurality of gas turbine burners with the structure described in (1) above.

[0025] The plurality of gas turbine burners are arranged circumferentially along the gas turbine.

[0026] Two gas turbine burners that are circumferentially adjacent to each other in the gas turbine are arranged such that the region of one of the two gas turbine burners within a pair of second regions of the gas turbine burner, and the region of the other of the two gas turbine burners within a pair of second regions of the gas turbine burner, are adjacent to each other in the circumferential direction of the gas turbine.

[0027] (3) The assembly method of the gas turbine according to at least one embodiment of the present disclosure includes the step of arranging a plurality of gas turbine burners with the structure of (1) above in the casing of the gas turbine along the circumferential direction of the gas turbine.

[0028] In the configuration process, a plurality of gas turbine burners are arranged such that, in two gas turbine burners that are adjacent in the circumferential direction of the gas turbine, one region of one of the pair of second regions in one gas turbine burner and the other region of the pair of second regions in the other gas turbine burner are adjacent in the circumferential direction of the gas turbine.

[0029] Invention Effects

[0030] According to at least one embodiment of the present disclosure, the flow of compressed air into the combustion chamber can suppress deviations caused by the circumferential position of the combustion chamber. Attached Figure Description

[0031] Figure 1 This is a schematic structural diagram showing several embodiments of a gas turbine.

[0032] Figure 2 This is a cross-sectional view showing several embodiments of a burner.

[0033] Figure 3 This is a schematic side view of the burner of several embodiments, viewed circumferentially from the gas turbine's central axis.

[0034] Figure 4A yes Figure 3 AA-direction sectional view.

[0035] Figure 4B yes Figure 3 BB-direction sectional view.

[0036] Figure 4C yes Figure 3 CC-direction sectional view in the middle.

[0037] Figure 5A This is an unfolded diagram showing the sound devices of several embodiments unfolded along the circumference of the combustion cylinder.

[0038] Figure 5B This is an unfolded diagram showing the sound devices of several embodiments unfolded along the circumference of the combustion cylinder.

[0039] Figure 6 It is a schematic diagram used to illustrate the spacing between adjacent burners in the circumferential direction of a gas turbine.

[0040] Figure 7 It is a schematic diagram used to illustrate the spacing between adjacent burners in the circumferential direction of a gas turbine.

[0041] Figure 8 yes Figure 3 AA-direction sectional view.

[0042] Figure 9 This is a cross-sectional view of the burner as seen from the downstream side along the first central axis on the upstream side of the combustion chamber.

[0043] Figure 10 This is a flowchart of an assembly method for a gas turbine according to one embodiment. Detailed Implementation

[0044] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. The dimensions, materials, shapes, and relative arrangements of the constituent components described in the embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0045] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" indicate relative or absolute configurations, not only in a strict sense, but also in a state of relative displacement by angle or distance with tolerance or to the extent that the same function can be obtained.

[0046] For example, expressions such as "same," "equal," and "homogeneous" that indicate the equality of things not only indicate a state of strict equality, but also indicate a state of difference in the degree to which the same function can be obtained, where there is a tolerance.

[0047] For example, the descriptions of shapes such as quadrilaterals and cylindrical shapes not only refer to quadrilaterals and cylindrical shapes in a strict geometric sense, but also to shapes that include concave and convex parts, chamfered parts, etc., within the range where the same effect can be obtained.

[0048] On the other hand, expressions such as "possessing," "containing," "equipped with," "including," or "having" a constituent element are not exclusive expressions that exclude the existence of other constituent elements.

[0049] (Regarding gas turbines 1)

[0050] Figure 1 This is a schematic structural diagram showing several embodiments of a gas turbine.

[0051] Reference Figure 1 An example of a gas turbine, which is an application object of a gas turbine burner in several embodiments, will be described.

[0052] like Figure 1 As shown, the gas turbine 1 in several embodiments includes a compressor 2 for generating compressed air as an oxidant, a gas turbine burner 4 for generating combustion gases using compressed air and fuel, and a turbine 6 configured to rotate driven by the combustion gases. In the case of the gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6, and power is generated using the rotational energy of the turbine 6. In the following description, the gas turbine burner 4 will also be simply referred to as burner 4.

[0053] Specific structural examples of each part in the gas turbine 1 of several embodiments will be described.

[0054] Several embodiments of the compressor 2 include a compressor chamber 10, an air intake 12 located on the inlet side of the compressor chamber 10 for intake air, a rotor 8 arranged to pass through both the compressor chamber 10 and the turbine chamber 22 (described later), and various blades disposed within the compressor chamber 10. The various blades include inlet guide blades 14 located on the air intake 12 side, multiple stationary blades 16 fixed to the compressor chamber 10 side, and multiple moving blades 18 arranged alternately with respect to the stationary blades 16 on the rotor 8. It should be noted that the compressor 2 may also include other components such as an extraction chamber (not shown). In such a compressor 2, air intake from the air intake 12 is compressed by the multiple stationary blades 16 and the multiple moving blades 18 to become high-temperature, high-pressure compressed air. Furthermore, the high-temperature, high-pressure compressed air is delivered from the compressor 2 to the subsequent burner 4.

[0055] Several embodiments of the burner 4 are disposed within the housing 20. For example... Figure 1 As shown, multiple burners 4 are arranged in a ring around the rotor 8 within the housing 20. Fuel and compressed air generated by the compressor 2 are supplied to the burners 4, causing the fuel and compressed air to combust, thereby producing combustion gas, which serves as the working fluid of the turbine 6. The combustion gas is then transported from the burners 4 to the subsequent turbine 6. It should be noted that detailed structural examples of the burners 4 in several embodiments will be described later.

[0056] Several embodiments of the turbine 6 include a turbine housing 22 and various blades disposed within the turbine housing 22. The various blades include multiple stationary blades 24 fixed to the side of the turbine housing 22 and multiple moving blades 26 arranged alternately with respect to the stationary blades 24 on the rotor 8. It should be noted that the turbine 6 may also include other components such as outlet guide vanes. In the turbine 6, combustion gases drive the rotor 8 to rotate by passing through the multiple stationary blades 24 and the multiple moving blades 26. This, in turn, drives a generator connected to the rotor 8.

[0057] The exhaust chamber 30 is connected to the downstream side of the turbine chamber 22 via the exhaust engine chamber 28. The combustion gases after driving the turbine 6 are discharged to the outside through the exhaust engine chamber 28 and the exhaust chamber 30.

[0058] (Regarding burner 4)

[0059] Figure 2 This is a cross-sectional view showing several embodiments of a burner.

[0060] Reference Figure 2 The detailed structure of the burner 4 in several embodiments will be described.

[0061] like Figure 2 As shown, in several embodiments, the burner 4 has multiple burners arranged in a ring around the rotor 8 (see reference). Figure 1 Each burner 4 includes a burner bushing 46 disposed in a burner chamber 40 defined by the housing 20, pilot burners 50 disposed within the burner bushing 46, and a plurality of premixed burners (main burners) 60. The burner 4 also includes an outer cylinder 45 disposed inside the housing 20 on the outer periphery of the inner cylinder 47 of the burner bushing 46. An air passage 43 for compressed air flow is formed on the outer periphery of the inner cylinder 47 and the inner periphery of the outer cylinder 45.

[0062] It should be noted that the burner 4 may also include other components such as a bypass pipe (not shown) for bypassing combustion gases.

[0063] For example, the burner bushing 46 has an inner cylinder 47 disposed around the pilot burner 50 and a plurality of premixed burners 60, and a tail cylinder 48 connected to the front end of the inner cylinder 47. It should be noted that the inner cylinder 47 and the tail cylinder 48 can also be formed as an integral combustion chamber. In the following description, the case where the inner cylinder 47 and the tail cylinder 48 are formed as an integral combustion chamber will also be included, and the burner bushing 46 will be referred to as the combustion chamber 46.

[0064] The pilot burner 50 is configured along the central axis AXc of the combustion chamber 46. Furthermore, a plurality of premixed combustion burners 60 are arranged separately from each other in a manner that surrounds the pilot burner 50.

[0065] In the burner 4 with the above-described structure, high-temperature, high-pressure compressed air generated by the compressor 2 is supplied from the compressor outlet to the burner chamber 40, and flows from the burner chamber 40 into the burner cylinder 66 via the air passage 43. This compressed air and fuel supplied from the fuel port 62 are premixed within the burner cylinder 66. At this time, the premixed gas mainly forms a swirling flow using a vortex generator (not shown) and flows into the burner cylinder 46. Furthermore, the compressed air and fuel injected from the pilot burner 50 via the fuel port 52 are mixed within the burner cylinder 46 and ignited by a ignition source (not shown) to produce combustion gases. At this time, a portion of the combustion gases diffuses with the flame and is ignited by the premixed gas flowing into the burner cylinder 46 from each premixed burner 60. That is, by using the pilot flame generated by the pilot fuel injected from the pilot burner 50, flame stabilization for stable combustion of the premixed gas (premixed fuel) from the premixed burner 60 can be achieved.

[0066] (Regarding sound equipment 100)

[0067] Figure 3 This is a schematic side view of several embodiments of the burner 4, viewed circumferentially from the central axis of the rotor 8, i.e., the central axis AX of the gas turbine 1. Figure 3 In the diagram, the central axis AX of the gas turbine 1 extends in the left-right direction below the burner 4.

[0068] The burner 4 in several embodiments includes an acoustic device 100 disposed on the outer periphery of the combustion cylinder 46.

[0069] Figure 4A yes Figure 3 Sectional view in direction AA.

[0070] Figure 4B yes Figure 3 BB-direction sectional view.

[0071] Figure 4C yes Figure 3 CC-direction sectional view in the middle.

[0072] It should be noted that, in Figure 4A , Figure 4B and Figure 4C The image shows a cross-section of the plate cut along the thickness direction of the plate of the combustion chamber 46 and the outer casing 150 (described later), and is therefore depicted with a single solid line. Thus, the area enclosed by the solid line corresponds to the internal space of the combustion chamber 46 and the resonance chamber (resonance space) 160 of the acoustic device 100 (described later). Figure 4A In the paper, for components whose surface is near the paper (the first plate component 181 described later), the surface is represented by shading.

[0073] Figure 5A This is an unfolded view of the sound device 100 of several embodiments, unfolded along the circumference of the combustion cylinder 46, which is equivalent to... Figure 4A The diagram shows the unfolded view of the inner acoustic device 101 from the I-direction view.

[0074] Figure 5B This is an unfolded view of the sound device 100 of several embodiments, unfolded along the circumference of the combustion cylinder 46, which is equivalent to... Figure 4A The diagram shows the unfolded view of the outer acoustic device 103 from direction II.

[0075] It should be noted that, in Figure 5A and Figure 5B In the diagram, the axial position of the combustion chamber 46 is indicated by a single-dotted line. Figure 3 The locations of the AA-direction view section, BB-direction view section and CC-direction view section.

[0076] Several embodiments of the acoustic device 100 are used to attenuate combustion vibrations and have a housing 150 forming a plurality of independent resonance chambers (resonance spaces) 160. The housing 150 forms an inner acoustic device 101 disposed radially inside the combustion chamber 46 and an outer acoustic device 103, which is different from the inner acoustic device 101, disposed at a position radially outside the combustion chamber 46 than the inner acoustic device 101. That is, the acoustic device 100 in several embodiments includes an inner acoustic device 101 and an outer acoustic device 103.

[0077] The plate components constituting the outer shell 150 are respectively fixed directly or indirectly to the outer surface of the combustion cylinder 46.

[0078] For example, when the functions of attenuating combustion vibrations at different frequencies via the inner acoustic device 101 and the outer acoustic device 103 are distributed, functions that can be effective even with a relatively small volume can be assigned to the inner acoustic device 101, which is located radially inside the combustion chamber 46 and has a smaller volume. Conversely, functions that require a larger volume can be assigned to the outer acoustic device 103, which is located radially outside the combustion chamber 46 and has a larger volume.

[0079] Thus, based on the sound device 100 of several embodiments, the functions allocated to the inner sound device 101 and the outer sound device 103 can be easily and reasonably set from the perspective of volume.

[0080] In several embodiments of the sound device 100, the inner sound device 101 constitutes a sound liner 201, and the outer sound device 103 constitutes a sound attenuator 203.

[0081] The acoustic liner 201 is an acoustic device that reduces higher-frequency vibrations caused by combustion vibrations, while the acoustic attenuator 203 is an acoustic device that reduces lower-frequency vibrations caused by combustion vibrations. Therefore, the acoustic attenuator 203 requires a larger resonance space compared to the acoustic liner 201.

[0082] Therefore, the sound liner 201, which can be effective even with a relatively small volume, is preferably assigned to the inner sound device 101, which is located radially inside the combustion chamber 46 and whose volume is easily reduced. On the other hand, the sound attenuator 203, which requires a relatively large volume, is preferably assigned to the outer sound device 103, which is located radially outside the combustion chamber 46 and whose volume is easily increased.

[0083] Thus, according to the sound device 100 of several embodiments, the functions allocated to the inner sound device 101 and the outer sound device 103 can be reasonably set from the perspective of volume.

[0084] For example, Figure 5A and Figure 5B As shown, the inner acoustic device 101 and outer acoustic device 103 in several embodiments each have multiple independent resonance chambers (resonance spaces) 160. For example... Figure 5A and Figure 5B As shown, adjacent resonant chambers 160 are separated by a partition member 151 indicated by dashed lines.

[0085] It should be noted that, for each resonance chamber 160, the partition plate (not shown) can also be arranged in the resonance chamber 160 in a manner that extends the resonance space within the resonance chamber 160 in a bent or serpentine manner.

[0086] exist Figure 5A and Figure 5B In the diagram, the vertical direction is along the axial direction of the central axis AXc of the combustion chamber 46, and the horizontal direction is the circumferential direction of the combustion chamber 46 centered on the central axis AXc. In the following description, the axial direction along the central axis AXc of the combustion chamber 46 will also be referred to as the axial direction of the combustion chamber 46, or simply the axial direction, and the circumferential direction centered on the central axis AXc of the combustion chamber 46 will also be referred to as the circumferential direction of the combustion chamber 46, or simply the circumferential direction. Similarly, in the following description, the radial direction centered on the central axis AXc of the combustion chamber 46 will also be referred to as the radial direction of the combustion chamber 46, or simply the radial direction.

[0087] Regarding the axial direction of the combustion chamber 46, the side where the combustion gas outlet 46d is located is designated as the downstream side, and the other side where the pilot burner 50 and the like are located is designated as the upstream side.

[0088] In addition, in the following description, the axial direction along the central axis AX of the gas turbine 1 will be referred to as the axial direction of the gas turbine 1, the circumferential direction centered on the central axis AX of the gas turbine 1 will be referred to as the circumferential direction of the gas turbine 1, and the radial direction centered on the central axis AX of the gas turbine 1 will be referred to as the radial direction of the gas turbine 1.

[0089] Regarding the axial direction of the gas turbine 1, relative to the position of the burner 4, the side where the turbine 6 and exhaust chamber 30 are located is designated as the downstream side, and the other side where the compressor 2 is located is designated as the upstream side.

[0090] Regarding the circumferential position of the sound device 100, the circumferential position furthest from the central axis AX of the gas turbine 1 in the radial direction of the gas turbine 1 is set to 0 degrees. Furthermore, when observing the combustion chamber 46 from the axial downstream side, the angle of the circumferential position increases as it travels counterclockwise from the position of 0 degrees.

[0091] Multiple resonance chambers 160 of the inner acoustic device 101 are connected to the internal space of the combustion cylinder 46 via multiple acoustic holes (not shown) formed in the combustion cylinder 46.

[0092] For example, Figure 5A As shown, the multiple resonance chambers 160 of the outer acoustic device 103 communicate with the internal space of the combustion cylinder 46 in the region 119 where the inner acoustic device 101 is not provided via multiple acoustic holes (not shown) formed in the combustion cylinder 46.

[0093] It should be noted that, in Figure 5A and Figure 5B In the example shown, the plurality of sound holes that connect the plurality of resonance chambers 160 of the outer sound device 103 to the internal space of the combustion cylinder 46 are formed in the region on the axial downstream side of the combustion cylinder 46 in the sound device 100, but they may also be formed in a region other than this region. Similarly, the plurality of sound holes are formed in the circumferential direction of the combustion cylinder 46 in regions near 0 degrees and near 180 degrees, but they may also be formed in a region other than this region.

[0094] (Regarding the spacing between adjacent burners 4 in the circumferential direction of gas turbine 1)

[0095] Figure 6 and Figure 7 This is a schematic diagram illustrating the spacing between adjacent burners 4 in the circumferential direction of the gas turbine 1, and is as follows: Figure 3 The diagram shows the combustion chambers 46 of two adjacent burners 4 in the circumferential direction of the gas turbine 1, viewed radially from the outer side of the gas turbine 1, as shown in view VII. It should be noted that... Figure 6 For ease of explanation, the description of the sound device 100 has been omitted.

[0096] Generally, in industrial gas turbines, such as the gas turbine 1 in several embodiments, multiple burners 4 are arranged circumferentially along the gas turbine 1. Furthermore, based on the relationship between the rotor blades 26 of the turbine 6 and the radial position of the burners 4 within the gas turbine 1, the multiple burners 4 are arranged close to the radially inner side of the gas turbine 1. Therefore, the spacing between adjacent burners 4 in the circumferential direction of the gas turbine 1 tends to become relatively small.

[0097] like Figure 2 As shown, the compressed air for combustion introduced from the compressor 2 into the burner chamber 40 flows into the burner chamber 40 radially inward of the gas turbine 1, as indicated by arrow a, towards the axial downstream side of the gas turbine 1, at a position closer to the gas turbine 1 than the plurality of burners 4 adjacent to it in the circumferential direction. Furthermore, the flow of the compressed air for combustion introduced into the burner chamber 40, as indicated by arrows b and c, then turns radially outward of the gas turbine, and as indicated by arrows d and e, turns towards the axial upstream side of the gas turbine 1, flowing into the combustion chamber 46 from the axial upstream side.

[0098] As compressed air flows into the burner chamber 40, during its flow into the combustion cylinder 46, as shown by arrow c, a portion of the compressed air passes through the space (gap) 40a between the combustion cylinders 46 of adjacent burners 4 in the circumferential direction of the gas turbine 1 (see reference). Figure 6 Therefore, if the space 40a between adjacent combustion chambers 46 in the circumferential direction of the gas turbine 1 becomes too small, the deviation in the flow of compressed air into the combustion chambers 46 caused by the circumferential position of the combustion chambers 46 will become larger. As a result, localized increases in flame temperature may occur within the combustion chambers 46, potentially leading to increased combustion vibration, increased NOx, etc.

[0099] Furthermore, in industrial gas turbines, such as gas turbine 1 in several embodiments, a sound-absorbing device 100 is typically provided to attenuate combustion vibrations. Since this sound-absorbing device 100 is typically mounted on the outer periphery of the combustion chamber 46, the space 40a between adjacent combustion chambers 46 in the circumferential direction of the gas turbine 1 tends to become smaller (see reference). Figure 7 It should be noted that, in Figure 7 In the diagram, solid lines are used to schematically show the shape of the sound device 100 when the pair of second regions 113 and 114, described later, are provided. Additionally, in... Figure 7 In the diagram, the shape of a conventional sound device without the pair of second regions 113, 114 described later is schematically shown in the dashed line depicting a portion of the sound device 100.

[0100] Therefore, in the burner 4 of several embodiments, the sound device 100 is configured in such a way that it has a pair of first regions 111, 112 and a third region 120 as follows.

[0101] Here, the acoustic device 100 in several embodiments has a pair of first regions 111, 112, which are located downstream of the combustion cylinder 46 and exist at a pair of positions 111A, 112A that radially sandwich the combustion cylinder 46 (see reference). Figure 4A And then Figure 8 , Figure 9 The acoustic device 100 has a pair of second regions 113, 114, the axial positions of the combustion chamber 46 of which are at least partially overlapped with a pair of first regions 111, 112 (positions 111A, 112A), and the circumferential positions of the combustion chamber 46 differ from those of the first regions 111, 112 (positions 111A, 112A), existing at positions that radially sandwich the combustion chamber 46. The acoustic device 100 has a third region 120 located upstream of the combustion chamber 46 relative to the first regions 111, 112 and the second regions 113, 114. The radial thickness t11 of the acoustic device 100 in the pair of second regions 113, 114 is smaller than the radial thickness t12 of the acoustic device 100 in the first regions 111, 112. The radial thickness t20 of the acoustic device 100 in the third region 120 is greater than the radial thickness t11 of the acoustic device 100 in the pair of second regions 113, 114.

[0102] If the burner 4 in several embodiments has the above-described structure, then when multiple burners 4 are arranged in a circumferential configuration along the gas turbine 1, it is preferable to arrange multiple burners 4 in such a way that a pair of second regions 113, 114 exist along the circumferential configuration of the gas turbine 1 (see reference). Figure 7 Therefore, the thickness t11 of the acoustic devices 100 in the pair of second regions 113, 114 is smaller than the thickness t21 of the acoustic devices 100 in the pair of first regions 111, 112, thus easily ensuring the space 40a between adjacent combustion cylinders 46 in the circumferential direction of the gas turbine 1. Therefore, in the flow of compressed air into the combustion cylinder 46, deviations caused by the circumferential position of the combustion cylinder 46, as described above, can be suppressed. Therefore, a burner 4 capable of suppressing combustion vibration, NOx, and other generation can be realized.

[0103] It should be noted that the radial thickness of the sound device 100 in each embodiment refers to the radial distance of the combustion cylinder 46 from the outer peripheral surface of the combustion cylinder 46 on which the sound device 100 is disposed to the radially outer end face of the combustion cylinder 46 in the sound device 100. In addition, in the following description, the radial thickness of the sound device 100 will also be simply referred to as the thickness of the sound device 100.

[0104] In several embodiments of the burner 4, the sound device 100 may also be configured as follows.

[0105] In several embodiments of the burner 4, the combustion cylinder 46 has an outlet 46e for the combustion gas formed at the downstream end. The central axis AXc of the combustion cylinder 46 extends in different directions at the first central axis AXc1 on the upstream side of the combustion cylinder 46 and the second central axis AXc2 at the outlet 46e. A pair of first regions 111, 112 preferably intersect a first imaginary plane Pv1 including the first central axis AXc1 and the second central axis AXc2. A pair of second regions 113, 114 preferably intersect a second imaginary plane Pv2 including the first central axis AXc1 and orthogonal to the first imaginary plane Pv1.

[0106] In several embodiments, when multiple gas turbine burners 4 are arranged circumferentially along the gas turbine 1, if the multiple gas turbine burners 4 are arranged such that a pair of second regions 113, 114 exist along the circumferential direction of the gas turbine 1, as described above, it is easy to ensure the space 40a between adjacent combustion chambers 46 in the circumferential direction of the gas turbine 1. Furthermore, with the gas turbine burners 4 arranged in this way, region 111 and region 112 of one of a pair of first regions 111, 112, whose radial thickness t12 is greater than the radial thickness t11 of the pair of second regions 113, 114, are arranged radially in the gas turbine 1. Therefore, among the gas turbine burners 4 adjacent in the circumferential direction of the gas turbine 1, the pair of first regions 111, 112 are less likely to interfere with each other, thus easily ensuring the volume of the pair of first regions 111, 112.

[0107] Figure 8 yes Figure 3 The AA-direction sectional view in the figure is used to illustrate the positional and dimensional relationship between a pair of first regions 111, 112 and a pair of second regions 113, 114.

[0108] In burner 4 of several embodiments, such as Figure 8As shown, when viewed along the first central axis AXc1 on the upstream side of the combustion cylinder 46 in the central axis AXc of the combustion cylinder 46, at least a portion of the second region 113, 114 of at least one of the pair of second regions 113, 114 preferably exists radially outward from the line segment Lf connecting the two ends of the circumferential end 100b of the combustion cylinder 46 of the outer surface 100a of the pair of first regions 111, 112, where one of the second regions 113, 114 exists.

[0109] In several embodiments, when multiple gas turbine burners 4 are arranged circumferentially along the gas turbine 1, if the multiple gas turbine burners 4 are arranged such that a pair of second regions 113, 114 exist along the circumferential direction of the gas turbine 1, the direction in which one of the pair of first regions 111, 112 and the other region 112 are arranged is close to the radial direction of the gas turbine 1. According to the burners 4 of several embodiments, in at least one of the second regions 113, 114, the end portion 100b does not protrude circumferentially compared to the portion that protrudes most prominently in the circumferential direction of the gas turbine 1. Therefore, the size of the pair of first regions 111, 112 along the circumferential direction can be suppressed, and thus, the pair of first regions 111, 112 of adjacent gas turbine burners 4 in the circumferential direction of the gas turbine 1 are less likely to interfere with each other.

[0110] Figure 9 It is a cross-sectional view of the burner 4 as seen from the downstream side along the first central axis AXc1 on the upstream side of the combustion chamber 46, and is illustrated together with the four burners 4 adjacent to the gas turbine 1 in the circumferential direction.

[0111] In several implementations, such as Figure 9As shown, the plurality of gas turbine burners 4 include first to third gas turbine burners 4A, 4B, and 4C arranged sequentially along the circumference of the gas turbine 1. In the second gas turbine burner 4B, a point located on the first central axis AXc1 upstream of the combustion chamber 46 of the second gas turbine burner 4B, within the axial range of the second gas turbine burner 4B located in a pair of second regions 113 and 114, is designated as the second point P2. In the first gas turbine burner 4A, a point located on the first central axis AXc1 upstream of the combustion chamber 46 of the first gas turbine burner 4A, within the axial range of the first gas turbine burner 4A located in a pair of second regions 113 and 114, and at the same axial position as the second point P2 in the second gas turbine burner 4B, is designated as the first point P1. In the third gas turbine burner 4C, a point located on the first central axis AXc1 upstream of the combustion cylinder 46 of the third gas turbine burner 4C, within the axial range of the pair of second regions 113 and 114 of the third gas turbine burner 4C, and at the same axial position as the second point P2 in the second gas turbine burner 4B, is designated as the third point P3. A first tangent plane Pt1 is defined at the intersection point CP where the first line segment Lv1 connecting the second point P2 and the first point P1 intersects the outer surfaces 113a and 114a of the pair of second regions 113 and 114 in the second gas turbine burner 4B. The second tangent plane Pt2 is defined at the intersection position CP where the outer surfaces 113a and 114a of the second line segment Lv2 connecting the second point P2 and the third point P3 and the second gas turbine burner 4B intersect between the second point P2 and the third point P3.

[0112] In the second gas turbine burner 4B, a pair of first regions 111, 112 preferably exist between the first tangent plane Pt1 and the second tangent plane Pt2.

[0113] Therefore, the size of the first regions 111 and 112 along the circumference of the gas turbine 1 can be suppressed, so that the first regions 111 and 112 of the gas turbine combustors 4 adjacent to each other in the circumference of the gas turbine 1 do not easily interfere with each other.

[0114] For example, in several embodiments of the sound device 100, the size Lc of at least one of the regions 113 and 114 of a pair of second regions 113, 114 along the circumference of the combustion chamber 46 is preferably larger than the size Lax along the axial direction of the combustion chamber 46.

[0115] This ensures the volume of the acoustic devices 100 in the pair of second regions 113, 114, and allows for an increase in the spacing between adjacent burners 4 compared to the case where the size Lc along the circumference of the combustion cylinder 46 is smaller than the size Lax along the axial direction of the combustion cylinder 46.

[0116] It should be noted that the circumferential size Lc can be different in region 113 of one party and region 114 of the other party. Similarly, the axial size Lax can also be different in region 113 of one party and region 114 of the other party.

[0117] In several embodiments of the acoustic device 100, a portion of the third region 120 may also overlap circumferentially with at least a portion of the pair of second regions 113, 114.

[0118] Generally, when the burner 4 is installed in the casing 20 of the gas turbine 1, it is installed at an angle relative to the central axis AX of the gas turbine 1, with the burner 46 downstream of the combustion chamber 46 and closer to the axis of the rotor 8 of the gas turbine 1, i.e., the central axis AX of the gas turbine 1, than the burner 46 upstream of the combustion chamber 46. Therefore, if multiple burners 4 are arranged circumferentially along the gas turbine 1, the pitch circle of each burner 4 with respect to the central axis AXc of the combustion chamber 4 decreases towards the downstream side of the combustion chamber 46. Therefore, the spacing between adjacent combustion chambers 46 in the circumferential direction of the gas turbine 1 tends to decrease towards the downstream side of the combustion chamber 46. Conversely, the spacing between adjacent combustion chambers 46 in the circumferential direction of the gas turbine 1 tends to increase towards the upstream side of the combustion chamber 46.

[0119] Therefore, as described above, even if the third region 120, located upstream of the combustion chamber 46 compared to the pair of first regions 111, 112 and the pair of second regions 113, 114, overlaps circumferentially with at least a portion of the pair of second regions 113, 114, its impact on the flow of compressed air through the space 40a between adjacent combustion chambers 46 is relatively small. Furthermore, as described above, if the third region 120, located upstream of the combustion chamber 46 compared to the pair of first regions 111, 112 and the pair of second regions 113, 114, is allowed to overlap circumferentially with at least a portion of the pair of second regions 113, 114, it is easy to ensure the volume of the acoustic device 100 in the third region 120.

[0120] In several embodiments of the acoustic device 100, the radial thickness t12 of the acoustic device 100 in a pair of first regions 111, 112 can be more than twice the radial thickness t11 of the acoustic device 100 in a pair of second regions 113, 114.

[0121] By increasing the difference between the radial thickness t12 of the acoustic device 100 in a pair of first regions 111, 112 and the radial thickness t11 of the acoustic device 100 in a pair of second regions 113, 114, it is possible to increase the spacing between adjacent burners 4 while ensuring the volume of the acoustic device 100.

[0122] In several embodiments of the acoustic device 100, a fourth region 130 may also be provided, located upstream of the combustion chamber 46 relative to the third region 120, and having a different circumferential extent than the third region 120. The radial thickness t30 of the acoustic device 100 in the fourth region 130 is preferably greater than the radial thickness t11 of the acoustic device 100 in the pair of second regions 113, 114.

[0123] As described above, the spacing between adjacent combustion tubes 46 in the circumferential direction of the gas turbine 1 tends to increase as it moves towards the upstream side of the combustion tubes 46. Therefore, even if a fourth region 130 is provided that is located upstream of the third region 120, the impact on the flow of compressed air through the space 40a between adjacent combustion tubes 46 is relatively small.

[0124] By setting up the fourth region 130 as described above, it is possible to suppress the impact on the flow of compressed air through the space 40a between adjacent combustion cylinders 46 while ensuring the volume of the sound device 100.

[0125] In several embodiments of the acoustic device 100, as described above, the acoustic device 100 preferably has a plurality of independent resonating chambers 160. For example, Figure 5B As shown, at least one resonance chamber 160 may also be configured to span the region of at least one of a pair of first regions 111, 112 (i.e., at least either one of region 111 of one side and region 112 of the other side) and the third region 120.

[0126] Therefore, it is easy to ensure the volume of the resonance chamber 160.

[0127] It should be noted that, for example, such as Figure 5B As shown, at least one resonance chamber 160 may be arranged across the third region 120 and the fourth region 130, or across at least one of the regions 111 of one party and the region 112 of the other party, the third region 120, and the fourth region 130.

[0128] In several embodiments of the sound device 100, it is preferred that an inner sound device 101 is present in a pair of second regions 113, 114 but an outer sound device 103 is absent, and an inner sound device 101 and an outer sound device 103 are present in a pair of first regions 111, 112.

[0129] Therefore, it is easy to make the thickness t11 of the sound device 100 in the pair of second regions 113, 114 smaller than the thickness t12 of the sound device 100 in the pair of first regions 111, 112.

[0130] In several embodiments of the acoustic device 100, as described above, the inner acoustic device 101 and the outer acoustic device 103 preferably each have at least one resonance chamber 160.

[0131] Therefore, by making the frequencies of the attenuated combustion vibrations different in the inner acoustic device 101 and the outer acoustic device 103, the functions assigned to the resonance chamber 160 can be different.

[0132] In several embodiments of the acoustic device 100, for example, such as Figure 5B As shown, at least one resonance chamber 160 in the outer acoustic device 103 is preferably arranged across the region of at least one of a pair of first regions 111, 112 (i.e., at least either one of region 111 of one side and region 112 of the other side) and the third region 120.

[0133] Therefore, it is easy to ensure the volume of the resonance chamber 160.

[0134] It should be noted that, for example, such as Figure 5B As shown, at least one resonance chamber 160 in the outer acoustic device 103 may also be arranged across the third region 120 and the fourth region 130, or across at least one of the regions 111 and 112, the third region 120, and the fourth region 130.

[0135] (Regarding connecting member 180)

[0136] In several embodiments of the sound device 100, a connecting member 180 may also be provided to connect the circumferential end face 150a of the combustion tube 46 of the sound device 100 in a pair of first regions 111, 112 to the outer peripheral surface (outer surface 100a) of the sound device 100 in a pair of second regions 113, 114.

[0137] Details about connecting member 180 will be explained later.

[0138] In several embodiments of the burner 4, the thickness t12 of the acoustic device 100 in a pair of first regions 111, 112 differs from the thickness t11 of the acoustic device 100 in a pair of second regions 113, 114. Therefore, the rigidity of the acoustic device 100 differs between the pair of first regions 111, 112 and the pair of second regions 113, 114. Specifically, the rigidity of the acoustic device 100 in the pair of second regions 113, 114 is less than that in the pair of first regions 111, 112. Therefore, if the mixture of fuel and compressed air for combustion burns in the burner 4 and the temperature of the combustion chamber 46 rises, there is a tendency for the combustion chamber 46 to deform, causing one region 113 of the pair of second regions 113, 114 to separate from the other region 114, and one region 111 of the pair of first regions 111, 112 to approach the other region 112. Such deformation of the combustion chamber 46 is also referred to as lateral elliptical deformation.

[0139] In several embodiments of the sound device 100, by connecting the aforementioned end face 150a of the sound device 100 to the outer peripheral surface 100a of the sound device 100 in a pair of second regions 113, 114 via the connecting member 180, the sound device 100 in the pair of second regions 113, 114 is not easily deformed, and thus the lateral elliptical deformation of the combustion cylinder 46 as described above can be suppressed.

[0140] For example, the connecting member 180 preferably includes at least one first plate member 181 arranged in the thickness direction along the axial direction of the combustion cylinder 46.

[0141] exist Figure 4A In the middle, the surface of the first plate member 181 faces the front side of the paper surface and the depth side of the paper surface. Therefore, in Figure 4A As described above, the surface of the plate of the first plate member 181 is represented by shading.

[0142] In several embodiments of the burner 4, the aforementioned end face 150a of the acoustic device 100 in a pair of first regions 111, 112 intersects with the outer peripheral surface 100a of the acoustic device in a pair of second regions 113, 114. Therefore, a recess 191 formed by the end face 150a and the outer peripheral surface 100a exists on the surface of the burner 4.

[0143] As described above, the first plate member 181 is a plate member that connects the end face 150a to the outer peripheral surface 100a, and is arranged in the thickness direction along the axial direction of the combustion chamber 46. That is, the first plate member 181 is a rib-like member whose periphery is connected to the end face 150a and the outer peripheral surface 100a, and extends along the circumferential and radial directions of the combustion chamber 46. Therefore, the first plate member 181 functions to suppress the lateral elliptical deformation of the combustion chamber 46, which is such that the plate member 153 having the end face 150a tilts relative to the plate member 155 having the outer peripheral surface 100a. Therefore, the lateral elliptical deformation of the combustion chamber 46 can be suppressed by a relatively simple plate-shaped member.

[0144] Additionally, for example, the connecting member 180 preferably includes at least one second plate member 182 whose surface extends axially along the combustion cylinder 46. The second plate member 182 preferably connects the circumferential end face 150a of the combustion cylinder 46 of the acoustic device 100 in at least one of the at least one pair of first regions 111, 112 (i.e., at least either one of region 111 or the other region 112) to the outer peripheral surface 100a of the acoustic device 100 in a pair of second regions 113, 114.

[0145] It should be noted that, in Figure 4A The image shows a cross-section of the plate cut along the thickness direction of the second plate member 182.

[0146] Therefore, the lateral elliptical deformation of the combustion chamber 46 described above can be suppressed by using a relatively simple plate-shaped component. Furthermore, by providing the second plate component 182, as explained below, the flow turbulence of compressed air flowing in the direction connecting one region 111 of the pair of first regions 111 and 112 to the other region 112 along the outer peripheral surface 100a of the acoustic devices 100 in the pair of second regions 113 and 114 can be suppressed. That is, the aforementioned recess 191 exists on the surface of the burner 4. Therefore, without the second plate component 182, the flow of compressed air flowing in the direction connecting one region 111 of the pair of first regions 111 and 112 to the other region 112 along the outer peripheral surface 100a of the acoustic devices 100 in the pair of second regions 113 and 114 would be turbulent when passing through the aforementioned recess 191.

[0147] The second plate member 182 connects the end faces 150a of the acoustic device 100 in the pair of first regions 111, 112 to the outer peripheral faces 100a of the acoustic device 100 in the pair of second regions 113, 114, and extends along the axial direction of the combustion cylinder 46 with the surface of the plate. Therefore, the second plate member 182 can cover the recess 191 in a way that makes the depth of the recess 191 shallower.

[0148] Therefore, by providing the second plate member 182, it is possible to suppress the flow disturbance of compressed air in the direction that connects one region 111 of the pair of first regions 111 and 112 to the other region 112 along the outer peripheral surface 100a of the acoustic device 100 in the pair of second regions 113 and 114.

[0149] It should be noted that the direction of compressed air flowing along the outer peripheral surface 100a of the acoustic device 100 in the pair of second regions 113, 114, connecting one region 111 of the pair of first regions 111, 112 to the other region 112, is either from the direction of the first region 111 toward the other region 112 or the opposite direction. Therefore, it is sufficient to provide the second plate member 182 in the region of the first region 111 or the other region 112 located downstream of the flow of compressed air; it is not necessary to provide the second plate member 182 in the region located upstream. It should be noted that in Figure 4A In the example shown, the compressed air flows from below the paper surface that becomes the radially inner side of the gas turbine 1 to above the paper surface that becomes the radially outer side of the gas turbine 1. Therefore, it is preferable to provide a second plate member 182 in one of the regions 111. That is, in several embodiments, the flow of compressed air flowing in the direction that connects one of the regions 111 and the other region 112 of the pair of first regions 111 and 112 along the outer peripheral surface 100a of the acoustic device 100 in the pair of second regions 113 and 114 is equivalent to... Figure 2 The flow of compressed air is indicated by arrow c.

[0150] Alternatively, for example, the first plate member 181 and the second plate member 182 described above can be provided, with the second plate member 182 covering the recess 191, and at least one first plate member 181 disposed in the recess 191 covered by the second plate member 182.

[0151] That is, the connecting member 180 preferably includes at least one second plate member 182 and at least one first plate member 181 as described below. Here, the second plate member 182 is preferably a plate member whose surface extends along the axial direction of the combustion cylinder 46. The first plate member 181 is preferably a plate member disposed in the area surrounded by the second plate member 182, the circumferential end face 150a of the combustion cylinder 46 with respect to the sound device 100 in a pair of first regions 111, 112, and the outer peripheral surface 100a of the sound device 100 in a pair of second regions 113, 114, and disposed in the thickness direction along the axial direction of the combustion cylinder 46.

[0152] Therefore, the effects described above regarding the first plate member 181 and the second plate member 182 can be achieved. Furthermore, the first plate member 181 is disposed in the region surrounded by the second plate member 182, the end faces 150a of the acoustic devices 100 in the pair of first regions 111, 112, and the outer peripheral surfaces 100a of the acoustic devices 100 in the pair of second regions 113, 114. This suppresses the influence of the first plate member 181 on the flow of compressed air flowing in the direction connecting one region 111 of the pair of first regions 111, 112 to the other region 112 along the outer peripheral surfaces 100a of the acoustic devices 100 in the pair of second regions 113, 114.

[0153] For example, in several embodiments of the sound device 100, the thickness of the plate member 153 having a circumferential end face 150a of the combustion cylinder 46 of the sound device 100 in a pair of first regions 111, 112 is preferably thicker than the thickness of the plate member 156 having an outer peripheral surface 100a of the sound device 100 in a pair of first regions 111, 112.

[0154] By increasing the thickness of the plate member 153, the lateral elliptical deformation of the combustion cylinder 46 can be suppressed.

[0155] When the burners 4 of the above-described embodiments are arranged in the gas turbine 1, two burners 4 that are circumferentially adjacent in the gas turbine are preferably arranged in such a way that region 113 of one of the pair of second regions 113, 114 of the burner 4 of one of the burners 4 and region 114 of the other of the pair of second regions 113, 114 of the burner 4 of the other burner 4 are circumferentially adjacent in the gas turbine (see reference). Figure 7 ).

[0156] This allows for a wider spacing between the two burners 4. Consequently, the flow of compressed air into the combustion chamber 46 can suppress deviations caused by the circumferential position of the combustion chamber 46, as described above. Therefore, a gas turbine 1 capable of suppressing combustion vibrations, NOx, and other emissions can be achieved.

[0157] (Assembly method of gas turbine)

[0158] Figure 10 This is a flowchart illustrating an assembly method for a gas turbine according to one embodiment. It should be noted that... Figure 10 The flowchart shown is a diagram illustrating the configuration of the burner 4 in the above-described embodiments.

[0159] The assembly method of the gas turbine according to one embodiment is the assembly method of the gas turbine 1 of the above-described embodiments. The assembly method of the gas turbine according to one embodiment includes a step S10 of arranging a plurality of burners 4 of the above-described embodiments circumferentially within the casing 20 of the gas turbine 1.

[0160] In the configured process S10, for example, Figure 7 As shown, multiple gas turbine burners 4 are arranged such that one region 113 of a pair of second regions 113, 114 of one gas turbine burner 4 is adjacent to the other region 114 of a pair of second regions 113, 114 of the other gas turbine burner 4 in the circumferential direction of the gas turbine 1.

[0161] Therefore, the thickness t11 of the acoustic devices 100 in the pair of second regions 113, 114 is smaller than the thickness t12 of the acoustic devices 100 in the pair of first regions 111, 112, thus easily ensuring the space 40a between adjacent combustion chambers 46 in the circumferential direction of the gas turbine 1. Consequently, in the flow of compressed air into the combustion chambers 46, deviations caused by the circumferential position of the combustion chambers 46, as described above, can be suppressed. Therefore, a gas turbine burner 4 capable of suppressing combustion vibrations, NOx, and other emissions can be realized.

[0162] This disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations thereof.

[0163] For example, the sound-emitting device 100 of the above-described embodiments has a first region 111, 112 located at a pair of positions 111A, 112A that radially sandwich the combustion cylinder 46. However, the sound-emitting device 100 of the above-described embodiments may also have only one of the first region 111 at position 111A and the first region 112 at position 112A. It should be noted that if the first regions 111, 112 are present at both of the pair of positions 111A, 112A, the volume of the sound-emitting device 100 can be easily ensured.

[0164] The contents described in the above embodiments shall be understood as follows.

[0165] (1) A gas turbine combustor 4 according to at least one embodiment of the present disclosure includes a combustion chamber 46 and an acoustic device 100 disposed on the outer periphery of the combustion chamber 46. The acoustic device 100 has a first region 111, 112 located downstream of the combustion chamber 46 and present at least one of a pair of positions that radially sandwich the combustion chamber 46. The acoustic device 100 has a pair of second regions 113, 114, the axial positions of the combustion chamber 46 of the pair of second regions 113, 114 of which at least a portion overlap with the pair of positions 111A, 112A, and the circumferential positions of the combustion chamber 46 of the pair of second regions 113, 114 are different from the pair of positions 111A, 112B and are present at the positions that radially sandwich the combustion chamber 46. The acoustic device 100 has a third region 120 located upstream of the combustion chamber 46 relative to the first regions 111, 112 and the second regions 113, 114. The radial thickness t11 of the acoustic device 100 in the pair of second regions 113 and 114 is smaller than the radial thickness t12 of the acoustic device 100 in the first regions 111 and 112. The radial thickness t20 of the acoustic device 100 in the third region 120 is larger than the radial thickness t11 of the acoustic device 100 in the pair of second regions 113 and 114.

[0166] When multiple gas turbine burners 4 with the structure described in (1) are arranged circumferentially along the gas turbine 1, if multiple gas turbine burners 4 are arranged such that a pair of second regions 113, 114 exist along the circumferential direction of the gas turbine 1, the thickness t11 of the acoustic device 100 in the pair of second regions 113, 114 is smaller than the thickness t12 of the acoustic device 100 in the first regions 111, 112. Therefore, it is easy to ensure the space 40a between adjacent combustion tubes 46 in the circumferential direction of the gas turbine 1. As a result, in the flow of compressed air into the combustion tube 46, the deviation caused by the circumferential position of the combustion tube 46, as described above, can be suppressed. Therefore, a gas turbine burner 4 capable of suppressing combustion vibration, NOx, and other generation can be realized.

[0167] (2) In several embodiments, based on the structure of (1) above, it is preferred that the first regions 111, 112 exist on both sides of a pair of positions 111A, 112A.

[0168] Based on the structure described in (2) above, it is easy to ensure the volume of the sound device 100.

[0169] (3) In several embodiments, based on the structure described in (1) or (2) above, the combustion cylinder 46 has an outlet 46e for the combustion gas formed at the downstream end. The central axis AXc of the combustion cylinder 46 extends in different directions through the first central axis AXc1 on the upstream side of the combustion cylinder 46 and the second central axis AXc2 in the outlet 46e. The first regions 111, 112 preferably intersect with a first imaginary plane Pv1 that includes the second central axis AXc2 of the first central axis AXc1. A pair of second regions 113, 114 preferably intersect with a second imaginary plane Pv2 that includes the first central axis AXc1 and is orthogonal to the first imaginary plane Pv1.

[0170] When multiple gas turbine burners 4 with the structure described in (3) are arranged circumferentially along the gas turbine 1, if the multiple gas turbine burners 4 are arranged such that a pair of second regions 113, 114 exist along the circumferential direction of the gas turbine 1, then as described above, it is easy to ensure the space 40a between adjacent combustion tubes 46 in the circumferential direction of the gas turbine 1. Furthermore, when the gas turbine burners 4 are arranged in this way, the region 111 and the region 112 of the first regions 111, 112, whose radial thickness t11 is greater than the radial thickness t12 of the pair of second regions 113, 114, are arranged radially in the gas turbine 1. Therefore, the first regions 111, 112 are less likely to interfere with each other among the gas turbine burners 4 adjacent in the circumferential direction of the gas turbine 1, thus it is easy to ensure the volume of the first regions 111, 112.

[0171] (4) In several embodiments, based on any of the structures in (1) to (3) above, it is preferred that, when viewed along the first central axis AXc1 on the upstream side of the combustion cylinder 46 in the central axis AXc of the combustion cylinder 46, at least a portion of the second region 113, 114 of at least one of the pair of second regions 113, 114 exists at a position radially outward of the combustion cylinder than the line segment Lf connecting the two ends of the circumferential end 100b of the combustion cylinder 46 of the outer surface 100a of the first regions 111, 112, where one of the second regions 113, 114 exists.

[0172] When multiple gas turbine burners 4 with the structure described above (4) are arranged circumferentially along the gas turbine 1, if multiple gas turbine burners 4 are arranged such that a pair of second regions 113, 114 exist along the circumferential direction of the gas turbine 1, the direction in which one region 111 of the first regions 111, 112 and the other region 112 are arranged is close to the radial direction of the gas turbine 1. According to the structure described above (4), in at least one of the second regions 113, 114 of the pair of second regions 113, 114, the end portion 100b does not protrude circumferentially compared to the portion that protrudes most in the circumferential direction of the gas turbine 1. Therefore, the size of the first regions 111, 112 along the circumferential direction can be suppressed, so that the first regions 111, 112 of adjacent gas turbine burners 4 in the circumferential direction of the gas turbine 1 do not easily interfere with each other.

[0173] (5) In several embodiments, based on any of the structures in (1) to (4) above, it is preferred that the circumferential size Lc of at least one of the regions 113 and 114 of the pair of second regions 113 and 114 is larger than the axial size Lax of the combustion cylinder 46.

[0174] According to the structure described above (5), the volume of the acoustic device 100 in a pair of second regions 113, 114 is ensured, and the spacing between adjacent burners 4 can be increased compared to the case where the circumferential size Lc of the combustion tube 46 is smaller than the axial size Lax of the combustion tube 46.

[0175] (6) In several embodiments, based on any of the structures in (1) to (5) above, a portion of the third region 120 may overlap with at least a portion of a pair of second regions 113, 114 in the circumferential direction.

[0176] As described above, with the structure of (6) above, even if the third region 120, located upstream of the combustion chamber 46 from the first regions 111, 112 and the pair of second regions 113, 114, overlaps with at least a portion of the pair of second regions 113, 114 in the circumferential direction, the impact on the flow of compressed air through the space 40a between adjacent combustion chambers 46 is relatively small. Furthermore, with the structure of (6) above, if the third region 120, located upstream of the combustion chamber 46 from the first regions 111, 112 and the pair of second regions 113, 114, is allowed to overlap with at least a portion of the pair of second regions 113, 114 in the circumferential direction, the volume of the acoustic device 100 in the third region 120 can be easily ensured.

[0177] (7) In several embodiments, based on any of the structures in (1) to (6) above, it is preferred that the radial thickness t12 of the acoustic device 100 in the first regions 111, 112 is more than twice the radial thickness t11 of the acoustic device 100 in a pair of second regions 113, 114.

[0178] According to the structure described above (7), by increasing the difference between the radial thickness t12 of the acoustic device 100 in the first regions 111 and 112 and the radial thickness t11 of the acoustic device 100 in a pair of second regions 113 and 114, the spacing between adjacent burners 4 can be increased while ensuring the volume of the acoustic device 100.

[0179] (8) In several embodiments, based on any of the structures in (1) to (7) above, a fourth region 130 may also be provided, located upstream of the third region 120 on the combustion chamber 46, and having a different circumferential extent than the third region 120. Preferably, the thickness t30 of the acoustic device 100 in the fourth region 130 along the radial direction is greater than the radial thickness t11 of the acoustic device 100 in the pair of second regions 113, 114.

[0180] As described above, the spacing between adjacent combustion tubes 46 in the circumferential direction of the gas turbine 1 tends to increase as it moves towards the upstream side of the combustion tubes 46. Therefore, even if a fourth region 130 is provided that is located upstream of the third region 120, the impact on the flow of compressed air through the space 40a between adjacent combustion tubes 46 is relatively small.

[0181] According to the structure described above (8), the volume of the sound device 100 can be ensured while suppressing the influence of the flow of compressed air through the space 40a between adjacent combustion cylinders 46.

[0182] (9) In several embodiments, based on any of the structures in (1) to (8) above, it is preferred that the acoustic device 100 has a plurality of mutually independent resonance chambers 160. Alternatively, at least one resonance chamber 160 may be arranged across the first region 111, 112 and the third region 120.

[0183] According to the structure described above (9), the volume of the resonance chamber 160 can be easily ensured by setting the resonance chamber 160 across the first region 111, 112 and the third region 120.

[0184] (10) In several embodiments, based on any of the structures in (1) to (9) above, it is preferred that the sound device 100 includes: an inner sound device 101 disposed radially inside the combustion chamber 46; and an outer sound device 103 different from the inner sound device 101, at least a portion of which is disposed radially outside the combustion chamber 46 than the inner sound device 101.

[0185] Based on the structure described in (10), for example, when the functions such as different frequencies of attenuated combustion vibrations are distributed between the inner acoustic device 101 and the outer acoustic device 103, functions that can be effective even with a relatively small volume can be assigned to the inner acoustic device 101, which is located radially inward and has a smaller volume. Conversely, functions requiring a larger volume can be assigned to the outer acoustic device 103, which is located radially outward and has a larger volume. Thus, based on the structure described in (10), the functions assigned to the inner acoustic device 101 and the outer acoustic device 103 can be easily and reasonably determined from a volume perspective.

[0186] (11) In several embodiments, based on the structure of (10) above, it is preferred that an inner sound device 101 is present in a pair of second regions 113, 114 but no outer sound device 103 is present, and an inner sound device 101 and an outer sound device 103 are present in the first regions 111, 112.

[0187] Based on the structure described above (11), it is easy to make the thickness t11 of the sound device 100 in the pair of second regions 113, 114 smaller than the thickness t12 of the sound device 100 in the first regions 111, 112.

[0188] (12) In several embodiments, based on the structure of (10) or (11) above, it is preferred that the inner acoustic device 101 and the outer acoustic device 103 each have at least one resonance chamber 160.

[0189] According to the structure described above (12), the functions assigned to the resonance chamber 160 can be different, for example, by making the frequencies of the attenuated combustion vibrations different in the inner sound device 101 and the outer sound device 103.

[0190] (13) In several embodiments, based on the structure described in (12) above, it is preferable that at least one resonance chamber 160 of the outer acoustic device 103 is arranged across the first region 111, 112 and the third region 120.

[0191] According to the structure described above (13), the volume of the resonance chamber 160 can be easily ensured by setting the resonance chamber 160 across the first region 111, 112 and the third region 120.

[0192] (14) In several embodiments, based on any of the structures in (10) to (13) above, it is preferred that the inner sound device 101 constitutes the sound liner 201 and the outer sound device 103 constitutes the sound attenuator 203.

[0193] The acoustic liner 201 is an acoustic device 100 that can reduce higher-frequency vibrations caused by combustion vibrations, while the acoustic attenuator 203 is an acoustic device 100 that can reduce lower-frequency vibrations caused by combustion vibrations. Therefore, the acoustic attenuator 203 requires a larger resonance space compared to the acoustic liner 201.

[0194] Therefore, the sound liner 201, which can function effectively even with a relatively small volume, is preferably assigned to the inner sound device 101, which is located radially inward and whose volume is easily reduced. Conversely, the sound attenuator 203, which requires a relatively large volume, is preferably assigned to the outer sound device 103, which is located radially outward and whose volume is easily increased.

[0195] Thus, based on the structure described above (14), the functions allocated to the inner sound device 101 and the outer sound device 103 can be reasonably set from the perspective of volume.

[0196] (15) In several embodiments, based on any of the structures in (1) to (14) above, it may also be provided with a connecting member 180 that connects the circumferential end face 150a of the combustion tube 46 of the sound device 100 in the first regions 111, 112 to the outer peripheral face 100a of the sound device 100 in a pair of second regions 113, 114.

[0197] According to the structure described above (15), the connecting member 180 connects the end face 150a of the sound device 100 in the first regions 111 and 112 with the outer peripheral surface (outer surface 100a) of the sound device 100 in a pair of second regions 113 and 114, thereby suppressing the lateral elliptical deformation of the combustion tube 46 as described above.

[0198] (16) In several embodiments, based on the structure described in (15) above, it is preferred that the connecting member 180 includes at least one first plate member 181 arranged in the thickness direction along the axial direction of the combustion cylinder 46.

[0199] Based on the structure described above (16), the lateral elliptical deformation of the combustion tube 46 can be suppressed by a relatively simple component such as a plate-shaped component.

[0200] (17) In several embodiments, based on the structure described in (15) or (16) above, it is preferable that the connecting member 180 includes at least one second plate member 182 whose surface extends axially along the combustion chamber 46. Preferably, the second plate member 182 connects the circumferential end face 150a of the combustion chamber 46 with respect to the acoustic device 100 in the first regions 111, 112 to the outer peripheral surface 100a of the acoustic device 100 in a pair of second regions 113, 114.

[0201] According to the structure described in (17), the lateral elliptical deformation of the combustion chamber 46 described above can be suppressed by a relatively simple component such as a plate-shaped component. In addition, according to the structure described in (17), the flow turbulence of compressed air flowing in the direction connecting one region 111 of the first regions 111 and the other region 112 along the outer peripheral surface 100a of the sound device 100 in the pair of second regions 113 and 114 can be suppressed.

[0202] (18) In several embodiments, based on the structure described in (15) above, it is preferable that the connecting member 180 includes at least one second plate member 182 and at least one first plate member 181 as described below. Here, it is preferable that the second plate member 182 is a plate member whose surface extends along the axial direction of the combustion cylinder 46. It is preferable that the first plate member 181 is a plate member disposed in the region surrounded by the second plate member 182, the circumferential end face 150a of the combustion cylinder 46 with respect to the acoustic device 100 in the first regions 111, 112, and the outer peripheral surface 100a of the acoustic device 100 in a pair of second regions 113, 114, and disposed in such a way that the plate thickness direction is along the axial direction of the combustion cylinder 46.

[0203] According to the structure described in (18), the first plate member 181 achieves the same effect as the structure described in (16), and the second plate member 182 achieves the same effect as the structure described in (17). Furthermore, according to the structure described in (18), the first plate member 181 is disposed in the area surrounded by the second plate member 182, the end face 150a of the acoustic device 100 in the first regions 111 and 112, and the outer peripheral surface 100a of the acoustic device 100 in the pair of second regions 113 and 114. Therefore, the influence of the first plate member 181 on the flow of compressed air flowing in the direction connecting one region 111 of the first regions 111 and the other region 112 along the outer peripheral surface 100a of the acoustic device 100 in the pair of second regions 113 and 114 can be suppressed.

[0204] (19) In several embodiments, based on any of the structures in (1) to (18) above, it is preferred that the thickness of the plate member 153 having the circumferential end face 150a of the combustion tube 46 of the acoustic device 100 in the first regions 111, 112 is greater than the thickness of the plate member 156 having the outer peripheral surface 100a of the acoustic device 100 in the first regions 111, 112.

[0205] According to the structure described above (19), by increasing the thickness of the plate member 153 having the end face 150a, the transverse elliptical deformation of the combustion tube 46 as described above can be suppressed.

[0206] (20) The gas turbine 1 of at least one embodiment of the present disclosure includes a plurality of gas turbine burners 4 with any of the structures described in (1) to (19) above. The plurality of gas turbine burners 4 are arranged circumferentially along the gas turbine 1. Two gas turbine burners 4 that are adjacent in the circumferential direction of the gas turbine 1 are arranged such that region 113 of one of a pair of second regions 113, 114 of one of the two gas turbine burners 4 and region 114 of the other of the two gas turbine burners 4 are adjacent in the circumferential direction of the gas turbine.

[0207] According to the structure described above (20), the distance between the two gas turbine burners 4 can be increased. As a result, the deviation caused by the circumferential position of the burner 46 can be suppressed during the flow of compressed air into the combustion chamber 46. Therefore, a gas turbine 1 capable of suppressing combustion vibration, NOx, and other emissions can be realized.

[0208] (21) In several embodiments, based on the structure described in (20) above, a plurality of gas turbine burners 4 include first to third gas turbine burners 4A, 4B, and 4C arranged sequentially along the circumference of the gas turbine 1. In the second gas turbine burner 4B, a point located within the axial range of the second gas turbine burner 4B in the pair of second regions 113 and 114, and located on the central axis AXc (first central axis AXc1) of the second gas turbine burner 4B, is designated as the second point P2. In the first gas turbine burner 4A, a point located within the axial range of the first gas turbine burner 4A in the pair of second regions 113 and 114, located on the central axis AXc (first central axis AXc1) of the first gas turbine burner 4A, and located at the same axial position as the second point P2 in the second gas turbine burner 4B, is designated as the first point P1. In the third gas turbine burner 4C, a point located on the central axis AXc (first central axis AXc1) of the third gas turbine burner 4C, which exists within the axial range of the pair of second regions 113 and 114 in the third gas turbine burner 4C, and at the same axial position as the second point P2 in the second gas turbine burner 4B, is designated as the third point P3. The first tangent plane Pt1 is defined at the intersection point CP where the first line segment Lv1 connecting the second point P2 and the first point P1 and the outer surfaces 113a and 114a of the pair of second regions 113 and 114 in the second gas turbine burner 4B intersect between the second point P2 and the first point P1. The second tangent plane Pt2 is defined at the intersection position CP where the outer surfaces 113a and 114a of the second line segment Lv2 connecting the second point P2 and the third point P3 and the second gas turbine burner 4B intersect between the second point P2 and the third point P3.

[0209] The first regions 111 and 112 in the second gas turbine burner 4B can exist between the first tangent plane Pt1 and the second tangent plane Pt2.

[0210] According to the structure described above (21), the size of the first regions 111 and 112 along the circumferential direction of the gas turbine 1 can be suppressed. Therefore, the first regions 111 and 112 are less likely to interfere with each other in the gas turbine burners 4 that are adjacent to each other in the circumferential direction of the gas turbine 1.

[0211] (22) The gas turbine assembly method of at least one embodiment of the present disclosure is an assembly method of gas turbine 1, including a step S10 of arranging a plurality of gas turbine burners 4 with any of the structures described in (1) to (19) in the casing 20 of the gas turbine 1 along the circumferential direction of the gas turbine 1. In the arrangement step S10, a plurality of gas turbine burners 4 are arranged such that one region 113 of a pair of second regions 113, 114 of one gas turbine burner 4 is adjacent to the other region 114 of a pair of second regions 113, 114 of the other gas turbine burner 4 in the circumferential direction of the gas turbine 1.

[0212] According to the method described in (22) above, the thickness t11 of the acoustic devices 100 in the pair of second regions 113, 114 is smaller than the thickness t12 of the acoustic devices 100 in the first regions 111, 112, thus easily ensuring the space 40a between adjacent combustion cylinders 46 in the circumferential direction of the gas turbine 1. Therefore, in the flow of compressed air into the combustion cylinder 46, deviations caused by the circumferential position of the combustion cylinder 46, as described above, can be suppressed. Thus, a gas turbine burner 4 capable of suppressing combustion vibrations, NOx, and other emissions can be realized.

[0213] Explanation of reference numerals in the attached figures:

[0214] 1...gas turbine;

[0215] 4...Gas turbine burners (combustion units);

[0216] 46... Combustion tube (burner bushing);

[0217] 100... Sound devices;

[0218] 101...Inner sound components;

[0219] 103...External acoustic components;

[0220] 111, 112... First area;

[0221] 113, 114... a pair of second areas;

[0222] 120...Third Zone;

[0223] 130...Fourth Region;

[0224] 160... Resonance Chamber (Resonance Space);

[0225] 180... connecting components;

[0226] 181...First plate component;

[0227] 182...Second plate component;

[0228] 201... sound accompaniment;

[0229] 203... Sound attenuator.

Claims

1. A burner for a gas turbine, wherein, The gas turbine burner includes: Combustion tube; and A sound-emitting device is disposed on the outer periphery of the combustion cylinder. The acoustic device has: A first region is located downstream of the combustion chamber and exists at least one of a pair of locations that radially sandwich the combustion chamber. A pair of second regions, wherein the axial position of the combustion chamber at least partially overlaps with the pair of positions, and the circumferential position of the combustion chamber differs from the pair of positions, existing at a position that sandwiches the combustion chamber in the radial direction; as well as The third region is located upstream of the combustion chamber relative to the first and second regions. The radial thickness of the acoustic device in the pair of second regions is smaller than the radial thickness of the acoustic device in the first region. The radial thickness of the acoustic device in the third region is greater than the radial thickness of the acoustic device in the pair of second regions.

2. The gas turbine burner according to claim 1, wherein, The first region exists on both sides of the pair of locations.

3. The gas turbine burner according to claim 1 or 2, wherein, The combustion chamber has an outlet portion for the combustion gas formed at the downstream end. The central axis of the combustion chamber extends in different directions from the first central axis on the upstream side of the combustion chamber and the second central axis in the ejection section. The first region intersects with a first imaginary plane including the first central axis and the second central axis. The pair of second regions intersect with a second imaginary plane that includes the first central axis and is orthogonal to the first imaginary plane.

4. The gas turbine burner according to any one of claims 1 to 3, wherein, When viewed along the first central axis of the combustion cylinder on the upstream side of the combustion cylinder's central axis, at least a portion of the second region of at least one of the pair of second regions exists radially outward of the combustion cylinder than the line segment connecting the two ends of the combustion cylinder's circumferential ends that sandwich the second region of one of the two regions.

5. The gas turbine burner according to any one of claims 1 to 4, wherein, The circumferential size of the combustion chamber is larger than the axial size of the combustion chamber in at least one of the regions of the pair of second regions.

6. The gas turbine burner according to any one of claims 1 to 5, wherein, A portion of the third region overlaps with at least a portion of the pair of second regions in the circumferential direction of the combustion chamber.

7. The gas turbine burner according to any one of claims 1 to 6, wherein, The radial thickness of the acoustic device in the first region is more than twice the radial thickness of the acoustic device in the pair of second regions.

8. The gas turbine burner according to any one of claims 1 to 7, wherein, The gas turbine burner further has a fourth region, which is located upstream of the third region, and the circumferential extent of the combustion chamber differs from that of the third region. The thickness of the acoustic device in the fourth region along the radial direction is greater than the radial thickness of the acoustic device in the pair of second regions.

9. The gas turbine burner according to any one of claims 1 to 8, wherein, The acoustic device has multiple independent resonance chambers. At least one of the resonating chambers is arranged across the first region and the third region.

10. The gas turbine burner according to any one of claims 1 to 9, wherein, The sound device includes: an inner sound device disposed on the radially inner side of the combustion chamber; and an outer sound device, different from the inner sound device, at least a portion of which is disposed on the radially outer side of the combustion chamber than the inner sound device.

11. The gas turbine burner according to claim 10, wherein, The inner acoustic device is present in the pair of second regions, but the outer acoustic device is absent. The inner acoustic device and the outer acoustic device are present in the first region.

12. The gas turbine burner according to claim 10 or 11, wherein, The inner acoustic device and the outer acoustic device each have at least one resonance chamber.

13. The gas turbine burner according to claim 12, wherein, At least one resonating chamber of the outer acoustic device is disposed across the first region and the third region.

14. The gas turbine burner according to any one of claims 10 to 13, wherein, The inner acoustic device forms an acoustic liner. The external acoustic device constitutes an acoustic attenuator.

15. The gas turbine burner according to any one of claims 1 to 14, wherein, The gas turbine burner also includes a connecting member that connects the circumferential end face of the combustion cylinder with respect to the acoustic device in the first region to the outer peripheral surface of the acoustic device in the pair of second regions.

16. The gas turbine burner according to claim 15, wherein, The connecting member includes at least one first plate member arranged in a manner that extends along the axial direction of the combustion chamber in the plate thickness direction.

17. The gas turbine burner according to claim 15 or 16, wherein, The connecting member includes at least one second plate member whose surface extends axially along the combustion chamber. The second plate member connects at least the circumferential end face of the combustion tube of the sound device in the first region with respect to the outer peripheral face of the sound device in the pair of second regions.

18. The gas turbine burner according to claim 15, wherein, The connecting component includes: At least one second plate member, the surface of which extends axially along the combustion chamber; and At least one first plate member is disposed in a region surrounded by the second plate member, the circumferential end face of the combustion chamber with respect to the acoustic device in the first region, and the outer peripheral face of the acoustic device in the pair of second regions, arranged such that the plate thickness direction is along the axial direction of the combustion chamber.

19. The gas turbine burner according to any one of claims 1 to 17, wherein, The thickness of the plate member having the circumferential end face of the combustion chamber of the sound device in the first region is greater than the thickness of the plate member having the outer peripheral face of the sound device in the first region.

20. A gas turbine, wherein, The gas turbine includes a plurality of gas turbine burners as described in any one of claims 1 to 19. The plurality of gas turbine burners are arranged circumferentially along the gas turbine. Two gas turbine burners that are circumferentially adjacent to each other in the gas turbine are arranged such that the region of one of the two gas turbine burners within a pair of second regions of the gas turbine burner, and the region of the other of the two gas turbine burners within a pair of second regions of the gas turbine burner, are adjacent to each other in the circumferential direction of the gas turbine.

21. The gas turbine according to claim 20, wherein, The plurality of gas turbine burners include a first gas turbine burner, a second gas turbine burner, and a third gas turbine burner arranged sequentially along the circumference of the gas turbine. In the second gas turbine burner, a point located within the axial range of the second gas turbine burner in the pair of second regions, and on the central axis of the second gas turbine burner, is designated as the second point. In the first gas turbine burner, a point located within the axial range of the first gas turbine burner in the pair of second regions, on the central axis of the first gas turbine burner, and at the same axial position as the second point in the second gas turbine burner, is designated as the first point. In the third gas turbine burner, a point located within the axial range of the third gas turbine burner existing in the pair of second regions, on the central axis of the third gas turbine burner, and at the same axial position as the second point in the second gas turbine burner, is designated as the third point. The first tangent plane is defined at the intersection of the outer surface of the first line segment connecting the second point and the first point and the outer surface of the pair of second regions in the second gas turbine burner, where the second point and the first point intersect. When the second line segment connecting the second point and the third point and the outer surface of the pair of second regions in the second gas turbine burner intersect at the intersection between the second point and the third point, the tangent plane of the outer surface that is tangent to the outer surface is defined as the second tangent plane. The first region in the second gas turbine burner exists between the first tangential plane and the second tangential plane.

22. A method for assembling a gas turbine, wherein, The assembly method of the gas turbine includes the step of arranging the gas turbine burners according to any one of claims 1 to 19 within the casing of the gas turbine along the circumferential direction of the gas turbine. In the configuration process, a plurality of gas turbine burners are arranged such that, in two gas turbine burners that are adjacent in the circumferential direction of the gas turbine, one region of one of the pair of second regions in one gas turbine burner and the other region of the pair of second regions in the other gas turbine burner are adjacent in the circumferential direction of the gas turbine.

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