Combustor and gas turbine equipped therewith

Abstract

To enhance the durability of a combustion cylinder and a fuel manifold.SOLUTION: A combustor comprises a combustion cylinder which forms a cylindrical shape around an axial line, a secondary fuel nozzle which can inject secondary fuel in the combustion cylinder radially inward relative to the axial line, a fuel manifold arranged at an external peripheral side of the combustion cylinder, and forming a fuel space in which the secondary fuel can be temporarily accumulated, and a support pedestal for supporting the fuel manifold with an interval between the combustion cylinder and itself in the radial direction. The support pedestal has a support plate separating from the combustion cylinder to the outside of the radial direction, and spread in a circumferential direction with respect to the axial line, and support legs attached to the combustion cylinder, and supporting the support plate so that a space is formed between the support plate and the combustion cylinder.SELECTED DRAWING: Figure 3

Description

Technical Field

[0001] The present disclosure relates to a combustor and a gas turbine including the same.

Background Art

[0002] A gas turbine includes a compressor that compresses air, a combustor that burns fuel with the air compressed by the compressor to generate combustion gas, and a turbine that is driven by the combustion gas from the combustor.

[0003] The combustor described in Patent Document 1 below includes a combustion cylinder (or transition piece) in which fuel burns, a plurality of nozzles that inject fuel into the combustion cylinder, and a fuel manifold. It has a cylindrical shape around the combustor axis. Here, for the convenience of the following description, the direction in which the combustor axis extends is defined as the axial direction, and of the both sides in this axial direction, one side is the base end side and the other side is the tip end side. The nozzles include a primary fuel nozzle and a secondary fuel nozzle. The primary fuel nozzle is disposed on the base end side of the combustion cylinder and injects primary fuel toward the tip end side into the combustion cylinder. The secondary fuel nozzle is attached to the combustion cylinder at a position on the tip end side of the primary fuel nozzle and injects secondary fuel radially inward into the combustion cylinder. The fuel manifold is an annular space with respect to the combustor axis and forms a fuel space in which secondary fuel can be temporarily stored. The radially inner edge of this fuel space is defined by the combustion cylinder. Therefore, a part of the fuel manifold is formed by a part of the combustion cylinder.

Prior Art Documents

Patent Documents

[0004]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0005] The temperature of the combustion chamber is extremely high when fuel is burning inside. On the other hand, the temperature of the fuel manifold depends on the temperature of the fuel supplied to the fuel space when fuel is burning inside the combustion chamber, and does not reach the same high temperature as the combustion chamber. Specifically, when fuel is burning inside the combustion chamber, the temperature difference between the combustion chamber and the fuel manifold can exceed several hundred degrees. As a result, extremely high stress is generated at the connection point between the combustion chamber and the fuel manifold, reducing the durability of both the combustion chamber and the fuel manifold.

[0006] Therefore, the purpose of this disclosure is to provide a technology that can improve the durability of the combustion chamber and fuel manifold. [Means for solving the problem]

[0007] A combustor as one aspect of the present disclosure for achieving the above objective is: A combustion cylinder that is cylindrical around an axis and on which fuel can be burned on its inner circumference; a primary fuel nozzle that can inject primary fuel into the combustion cylinder in a direction having a component toward the tip side of the axial direction in which the axis extends, and a combustion cylinder attached to the combustion cylinder at a position toward the tip side of the primary fuel nozzle, and within the combustion cylinder, radially inward and radially outward in the radial direction with respect to the axis among A secondary fuel nozzle capable of injecting secondary fuel radially inward; a fuel manifold positioned on the outer circumference of the combustion cylinder, forming an annular shape with respect to the axis, capable of temporarily storing the secondary fuel and forming a fuel space that communicates with the secondary fuel nozzle; and a support base that supports the fuel manifold at a distance from the combustion cylinder in the radial direction. An acoustic attenuator having an acoustic cover that forms an acoustic space on the outer circumference of the combustion cylinder, The support base comprises a support plate spaced radially outward from the combustion cylinder and extending circumferentially with respect to the axis, and support legs attached to the combustion cylinder and supporting the support plate such that a space is formed between the support plate and the combustion cylinder. The fuel manifold is positioned radially outward from the support plate and supported by the support base. The support plate and support legs of the support base are composed of at least a part of the acoustic cover.

[0008] The temperature of the combustion chamber is extremely high when fuel is burning inside. On the other hand, the temperature of the fuel manifold depends on the temperature of the fuel supplied to the fuel space when fuel is burning inside the combustion chamber, and does not reach the same high temperature as the combustion chamber. Therefore, if the fuel manifold is directly connected to the outer surface of the combustion chamber, extremely high stress will be generated at the connection point between the combustion chamber and the fuel manifold.

[0009] In this embodiment, since a support base is interposed between the combustion chamber and the fuel manifold, the temperature gradient from the combustion chamber to the fuel manifold is gentler than the temperature gradient when the fuel manifold is directly connected to the outer surface of the combustion chamber. Moreover, the support base in this embodiment has a shape that is easily deformable. For this reason, in this embodiment, the stress generated from the combustion chamber to the fuel manifold can be kept low, and the durability of the combustion chamber and fuel manifold can be increased.

[0010] A gas turbine as one aspect of the present disclosure for achieving the above objectives is: The combustion chamber comprises the aforementioned embodiment of a combustion chamber, a compressor capable of compressing air to generate compressed air used for the combustion of fuel in the combustion chamber, and a turbine driven by the combustion gas generated by the combustion of fuel in the combustion chamber. [Effects of the Invention]

[0011] In one aspect of this disclosure, the durability of the combustion chamber and fuel manifold can be increased. [Brief explanation of the drawing]

[0012] [Figure 1] This is a schematic diagram showing the configuration of a gas turbine in one embodiment of the present disclosure. [Figure 2] This is a cross-sectional view of the area around the combustor of a gas turbine in the first embodiment of the present disclosure. [Figure 3] This is a cross-sectional view of the fuel manifold and the area around the second fuel nozzle of the combustor in the first embodiment of the present disclosure. [Figure 4] Figure 3 shows a cross-sectional view along line IV-IV. [Figure 5] Cross-sectional view around the fuel manifold and the second fuel nozzle of the combustor in the second embodiment according to the present disclosure. [Figure 6] Cross-sectional view taken along line VI-VI in FIG. 5. [Figure 7] Cross-sectional view around the combustor of the gas turbine in the third embodiment according to the present disclosure. [Figure 8] Cross-sectional view around the fuel manifold and the second fuel nozzle of the combustor in the third embodiment according to the present disclosure. [Figure 9] Cross-sectional view taken along line IX-IX in FIG. 8. [Figure 10] Cross-sectional view around the fuel manifold and the second fuel nozzle of the combustor in a modification of the fourth embodiment according to the present disclosure.

Modes for Carrying Out the Invention

[0013] Hereinafter, various embodiments of the combustor according to the present disclosure and the gas turbine including the same will be described in detail with reference to the drawings.

[0014] 「Embodiment of Gas Turbine」 The embodiment of the gas turbine will be described with reference to FIG. 1.

[0015] As shown in FIG. 1, the gas turbine 10 in the present embodiment includes a compressor 20 capable of compressing outside air A to generate compressed air, a plurality of combustors 40 capable of burning fuel F in the compressed air to generate combustion gas G, and a turbine 30 drivable by the combustion gas G.

[0016] The compressor 20 has a compressor rotor 21 that rotates about the rotor axis Ar, a compressor casing 25 that covers the compressor rotor 21, and a plurality of stator blade rows 26. The turbine 30 has a turbine rotor 31 that rotates about the rotor axis Ar, a turbine casing 35 that covers the turbine rotor 31, and a plurality of stator blade rows 36. In the following, the direction in which the rotor axis Ar extends is the rotor axis direction Da, one side of both sides in the rotor axis direction Da is the upstream side Dau of the axis, and the other side is the downstream side Dad of the axis.

[0017] The compressor 20 is arranged on the upstream side Dau of the axis with respect to the turbine 30. The compressor rotor 21 and the turbine rotor 31 are located on the same rotor axis Ar and are connected to each other to form a gas turbine rotor 11. For example, a rotor of a generator GEN is connected to this gas turbine rotor 11. The gas turbine 10 further includes an intermediate casing 14 arranged between the compressor casing 25 and the turbine casing 35. Compressed air from the compressor 20 flows into the intermediate casing 14. The plurality of combustors 40 are arranged side by side in the circumferential direction with respect to the rotor axis Ar and are attached to the intermediate casing 14. The compressor casing 25, the intermediate casing 14, and the turbine casing 35 are connected to each other to form a gas turbine casing 15.

[0018] The compressor rotor 21 has a rotor shaft 22 that extends in the rotor axis direction Da about the rotor axis Ar, and a plurality of moving blade rows 23 attached to the rotor shaft 22. The plurality of moving blade rows 23 are arranged side by side in the rotor axis direction Da. Each moving blade row 23 is composed of a plurality of moving blades arranged side by side in the circumferential direction with respect to the rotor axis Ar. On the downstream side Dad of each axis of the plurality of moving blade rows 23, one of the plurality of stator blade rows 26 is arranged. Each stator blade row 26 is provided inside the compressor casing 25. Each stator blade row 26 is composed of a plurality of stator blades arranged side by side in the circumferential direction with respect to the rotor axis Ar.

[0019] The turbine rotor 31 has a rotor shaft 32 extending in the direction Da of the rotor axis with respect to the rotor axis Ar, and a plurality of rotor blade rows 33 attached to the rotor shaft 32. The plurality of rotor blade rows 33 are arranged in the direction Da of the rotor axis. Each rotor blade row 33 is composed of a plurality of rotor blades arranged in the circumferential direction with respect to the rotor axis Ar. One of a plurality of stator blade rows 36 is located upstream Dau of each axis of the plurality of rotor blade rows 33. Each stator blade row 36 is located inside the turbine casing 35. Each stator blade row 36 is composed of a plurality of stator blades arranged in the circumferential direction with respect to the rotor axis Ar. The region in the annular space between the inner circumference of the turbine casing 35 and the outer circumference of the rotor shaft 32 where the plurality of stator blade rows 36 and the plurality of rotor blade rows 33 are arranged forms a combustion gas flow path 39 through which combustion gas G from the combustor 40 flows.

[0020] A fuel line 46 is connected to the combustor 40. The combustor 40 can generate combustion gas G by burning fuel F from the fuel line 46 in compressed air from the compressor 20.

[0021] "First Embodiment of a Combustor" A first embodiment of the combustor will be described with reference to Figures 2 to 4.

[0022] As shown in Figure 2, the combustor 40 in this embodiment includes a flange 41, an inner cylinder 43, a combustion cylinder (or tail cylinder) 44, a plurality of primary fuel pipes 47, a plurality of primary fuel nozzles 48, a secondary fuel pipe 51, a branched secondary fuel pipe 52, a plurality of secondary fuel nozzles 53, a fuel manifold 55, and a plurality of support bases 57.

[0023] The flange 41 extends radially from the combustor axis Ac. Both the inner cylinder 43 and the combustion cylinder 44 are located within the intermediate casing 14. Both the inner cylinder 43 and the combustion cylinder 44 are cylindrical around the combustor axis Ac. For the purposes of the following explanation, the direction in which the combustor axis (hereinafter simply referred to as the axis) Ac extends will be called the axial direction Dc. Of the two sides of this axial direction Dc, one side will be called the tip side Dct and the other side will be called the base side Dcb. As shown in Figure 1, the tip side Dct is the downstream side Da of the rotor axis in the rotor axis direction Da, and the base side Dcb is the upstream side Dau of the rotor axis in the rotor axis direction Da. Furthermore, the axis Ac is inclined with respect to the rotor axis Ar such that it approaches the rotor axis Ar as it approaches the tip side Dct. The circumferential direction with respect to the axis Ac will simply be called the circumferential direction Dcc. The radial direction with respect to the axis Ac will simply be called the radial direction Dr. In this radial direction Dr, the side approaching the axis Ac is called the radially inner Dri, and the side opposite to this radially inner Dri is called the radially outer Dro.

[0024] The intermediate casing 14 has a combustor mounting hole 14h that penetrates from the outside to the inside of the intermediate casing 14. The flange 41 is attached to the intermediate casing 14 with bolts 42 so as to close the combustor mounting hole 14h. The inner cylinder 43 is attached to the flange 41. Multiple primary fuel nozzles 48 are arranged on the inner circumference side of the inner cylinder 43. The combustion cylinder 44 is connected to the tip side Dct portion of the inner cylinder 43 via a sealing member or the like. The combustion cylinder 44 is supported by a cylinder support 45 or the like fixed to the inner surface of the intermediate casing 14.

[0025] Each of the multiple primary fuel nozzles 48 extends in the axial direction Dc and has a hole formed therein for injecting fuel. Each of the multiple primary fuel nozzles 48 is capable of injecting primary fuel in a direction having a directional component toward the tip side Dct. Each of the multiple primary fuel nozzles 48 is fixed to the flange 41. Of the multiple primary fuel nozzles 48, one nozzle is a pilot nozzle 48p and the other multiple nozzles are main nozzles 48m. The pilot nozzle 48p is positioned on the axial direction Ac. The multiple main nozzles 48m are arranged around the pilot nozzle 48p in the circumferential direction Dcc.

[0026] The multiple primary fuel lines 47 are all pipes that branch off from the fuel line 46 and are fixed to the flange 41. Of the multiple primary fuel lines 47, one is a pilot fuel line 47p, and the other multiple fuel lines are main fuel lines 47m. The pilot fuel line 47p is connected to the pilot nozzle 48p. Each of the multiple main fuel lines 47m is connected to one of the multiple main nozzles 48m.

[0027] Multiple secondary fuel nozzles 53 are mounted in the combustion chamber 44 at a position Dct closer to the tip than multiple primary fuel nozzles 48, and are aligned in the circumferential direction Dcc. Each of the multiple secondary fuel nozzles 53 is capable of injecting secondary fuel into the combustion chamber 44 radially inward Dri.

[0028] The fuel manifold 55 is located on the outer circumference of the combustion chamber 44, at a point Dct closer to the tip of the primary fuel nozzle 48 and at a point Dcb closer to the base of the secondary fuel nozzle 53. The fuel manifold 55 is formed in an annular shape with respect to the axis Ac. The fuel manifold 55 forms an annular shape with respect to the axis Ac and creates a fuel space 56 in which secondary fuel can be temporarily stored. The aforementioned secondary fuel piping 51 is connected to this fuel manifold 55. This secondary fuel piping 51 is also a pipe branched from the fuel line 46 and is fixed to the flange 41. The fuel manifold 55 and the multiple secondary fuel nozzles 53 are connected by multiple branched secondary fuel pipes 52. Therefore, the fuel manifold 55 communicates with the multiple secondary fuel nozzles 53 via the multiple branched secondary fuel pipes 52 so that secondary fuel in the fuel space 56 can be supplied to the multiple secondary fuel nozzles 53.

[0029] As shown in Figures 3 and 4, the multiple support bases 57 support the fuel manifold 55 with a gap between them and the combustion cylinder 44 in the radial direction Dr. The multiple support bases 57 are arranged in the circumferential direction Dcc. Each support base 57 has a support plate 58 that is spaced radially outward from the combustion cylinder 44 in Dro and extends in the circumferential direction Dcc, and multiple support legs 59 that are attached to the combustion cylinder 44 and support the support plate 58 so that a space is formed between the support plate 58 and the combustion cylinder 44. All of the multiple support legs 59 are plate-shaped members that extend in the circumferential direction Dcc. Some of the multiple support legs 59 are connected to the base end side Dcb of the support plate 58, and the remaining some of the support legs 59 are connected to the tip end side Dct of the support plate 58. Some of the support legs 59 and the remaining some of the support legs 59 are spaced apart in the axial direction Dc and face each other. Therefore, a space is formed between the support plate 58 and the combustion cylinder 44.

[0030] A portion of the annular fuel manifold 55 is connected by welding or other means to a support plate 58 of at least one of the multiple support bases 57.

[0031] The temperature of the combustion chamber 44 is extremely high when fuel is burning inside. On the other hand, the temperature of the fuel manifold 55 depends on the temperature of the fuel supplied to the fuel space 56 when fuel is burning inside the combustion chamber 44, and does not get as hot as the combustion chamber 44. For this reason, if the fuel manifold 55 were to be directly connected to the outer surface of the combustion chamber 44, extremely high stress would be generated at the connection point between the combustion chamber 44 and the fuel manifold 55.

[0032] On the other hand, in this embodiment, since a support base 57 is interposed between the combustion cylinder 44 and the fuel manifold 55, the temperature gradient from the combustion cylinder 44 to the fuel manifold 55 is gentler than the temperature gradient when the fuel manifold 55 is directly connected to the outer surface of the combustion cylinder 44. Moreover, the support base 57 in this embodiment has a shape that is easily deformable. For this reason, in this embodiment, the stress generated from the combustion cylinder 44 to the fuel manifold 55 can be kept low, and the durability of the combustion cylinder 44 and the fuel manifold 55 can be increased.

[0033] "Second Embodiment of a Combustor" A second embodiment of the combustor will be described with reference to Figures 5 and 6.

[0034] The combustor in this embodiment, like the combustor 40 in the first embodiment described with reference to Figure 2, comprises a flange 41, an inner cylinder 43, a combustion chamber 44, a plurality of primary fuel pipes 47, a plurality of primary fuel nozzles 48, a secondary fuel pipe 51, a branched secondary fuel pipe 52, a plurality of secondary fuel nozzles 53, and a fuel manifold 55a. Furthermore, as shown in Figures 5 and 6, the combustor 40a in this embodiment includes an acoustic attenuator 60.

[0035] The acoustic attenuator 60 has an acoustic cover 61 that, in cooperation with a portion of the plate forming the combustion cylinder 44, forms an acoustic space 62 on the outer circumference of the combustion cylinder 44. A portion of the plate forming the combustion cylinder 44, which defines a portion of this acoustic space 62, has a plurality of through holes 63 that connect the inside of the combustion cylinder 44 with the acoustic space 62.

[0036] The acoustic cover 61 has a top plate 65 spaced radially outward Dro from the combustion cylinder 44, and a pair of side plates 66 connecting the top plate 65 and the combustion cylinder 44. The top plate 65 faces the outer surface of the combustion cylinder 44 and forms an annular shape around axis Ac. The pair of side plates 66 form an annular shape around axis Ac and face each other with a gap in the axial direction Dc. Of the pair of side plates 66, one side plate 66 is connected to the base end Dcb edge of the top plate 65, and the other side plate 66 is connected to the tip end Dct edge of the top plate 65.

[0037] Similar to the first embodiment, the fuel manifold 55a is in communication with a plurality of secondary fuel nozzles 53 via a plurality of branched secondary fuel pipes 52, so that secondary fuel in the fuel space 56a can be supplied to a plurality of secondary fuel nozzles 53.

[0038] The fuel manifold 55a is positioned radially outward from the acoustic cover 61 described above and is connected to the acoustic cover 61. Therefore, in this embodiment, the acoustic cover 61 functions as a support base 57a for the fuel manifold 55a. Specifically, the top plate 65 of the acoustic cover 61 constitutes the support plate 58a of the support base 57a, and the pair of side plates 66 of the acoustic cover 61 constitute the support legs 59a of the support base 57a.

[0039] As described above, in this embodiment as well, the acoustic cover 61 functions as a support base 57a, so, similar to the first embodiment, the stress generated from the combustion cylinder 44 to the fuel manifold 55a can be kept low, and the durability of the combustion cylinder 44 and the fuel manifold 55a can be increased.

[0040] Furthermore, in this embodiment, as described above, the acoustic cover 61 functions as a support base 57a, so there is no need to provide a separate support base, and the number of components of the combustor 40a can be reduced.

[0041] Furthermore, in this embodiment, a portion of the fuel manifold 55a is formed by having a portion of the top plate 65 of the acoustic cover 61. Therefore, in this embodiment, when the acoustic cover 61 is provided on the fuel manifold 55a on the radially outer side Dro, the structure of the acoustic cover 61 and the fuel manifold 55a can be simplified.

[0042] "Third Embodiment of a Combustor" A third embodiment of the combustor will be described with reference to Figures 7 to 9.

[0043] As shown in Figure 7, the combustor 40b in this embodiment, like the combustors 40 and 40a in the above embodiments, comprises a flange 41, an inner cylinder 43, a combustion cylinder 44, a plurality of primary fuel pipes 47, a plurality of primary fuel nozzles 48, a secondary fuel pipe 51, a branched secondary fuel pipe 52, a plurality of secondary fuel nozzles 53, and a fuel manifold 55b. Furthermore, the combustor 40b in this embodiment, like the combustor 40a in the second embodiment, comprises an acoustic attenuator 60A.

[0044] As shown in Figures 8 and 9, the acoustic attenuator 60A in this embodiment includes a first acoustic attenuator 60Aa and a second acoustic attenuator 60Ab located radially outward from the first acoustic attenuator 60Aa (Dro). The first acoustic attenuator 60Aa is a resonator that suppresses noise using the principle of Helmholtz resonance and is sometimes called an acoustic liner. On the other hand, the second acoustic attenuator 60Ab is a resonator that suppresses noise in a specific frequency range using the principle of air column resonance and is sometimes called an acoustic damper.

[0045] The first acoustic attenuator 60Aa has a first acoustic cover 61a that, together with a portion of the plate forming the combustion cylinder 44, forms a first acoustic space 62a on the outer circumference of the combustion cylinder 44. A portion of the plate forming the combustion cylinder 44, which defines a portion of the first acoustic space 62a, has a plurality of through holes 63 that connect the inside of the combustion cylinder 44 to the first acoustic space 62a. The first acoustic cover 61a has a first top plate 65a that is spaced radially outward Dro from the combustion cylinder 44, and a pair of first side peripheral plates 66a that connect the first top plate 65a to the combustion cylinder 44. The first top plate 65a faces the outer surface of the combustion cylinder 44 and forms an annular shape around axis Ac. This first top plate 65a defines the radially outward Dro edge of the first acoustic space 62a. The pair of first side peripheral plates 66a form an annular shape around axis Ac and face each other with a gap in the axial direction Dc. Of the pair of first side periphery plates 66a, the first base periphery plate 66ab of the base end Dcb is connected to the base end Dcb edge of the first top plate 65a. Also, of the pair of first side periphery plates 66a, the first tip periphery plate 66at of the tip end Dct is connected to the tip end Dct edge of the first top plate 65a.

[0046] The second acoustic attenuator 60Ab has a second acoustic cover 61b that, together with a portion of the first top plate 65a, forms a second acoustic space 62b radially outward Dro of the first acoustic cover 61a. A portion of the first top plate 65a that defines the second acoustic space 62b has a plurality of through holes 64 that connect the first acoustic space 62a and the second acoustic space 62b. The second acoustic cover 61b has a second top plate 65b that is spaced radially outward Dro from the first top plate 65a, and a pair of second side peripheral plates 66b that connect the second top plate 65b and the first top plate 65a. The second top plate 65b faces the first top plate 65a and forms an annular shape around the axis Ac. This second top plate 65b defines the radially outward Dro edge of the second acoustic space 62b. The pair of second side periphery plates 66b form an annular shape around the axis Ac and face each other with a gap in the axial direction Dc. Of the pair of second side periphery plates 66b, the second base periphery plate 66bb on the base end side Dcb is connected to the base end side Dcb edge of the second top plate 65b. Of the pair of second side periphery plates 66b, the second tip periphery plate 66bt on the tip end side Dct is connected to the tip end side Dct edge of the second top plate 65b.

[0047] The fuel manifold 55b is positioned such that the fuel space 56b is located radially outward Dro from the first top plate 65a and towards the tip Dct from the second tip side peripheral plate 66bt. The distance d1 from the outer circumferential surface of the combustion cylinder 44 to the edge of the radially outward Dro of the fuel manifold 55b is less than or equal to the distance d2 from the outer circumferential surface of the combustion cylinder 44 to the edge of the radially outward Dro of the second top plate 65b. The portion of the combustor 40b including the combustion cylinder 44 is inserted into the intermediate casing 14 through the combustor mounting hole 14h of the intermediate casing 14 when assembled to the intermediate casing 14. For this reason, the size of the cross-section perpendicular to the axis Ac in this insertion portion is limited by the size of the combustor mounting hole 14h. Therefore, the distance d1 from the outer circumferential surface of the combustion cylinder 44 to the edge of the radially outward Dro of the fuel manifold 55b is limited as described above to ensure that the combustor 40b can be assembled to the intermediate casing 14.

[0048] The fuel manifold 55b is positioned radially outward from the first acoustic cover 61a described above and is connected to the first acoustic cover 61a. Therefore, in this embodiment, the first acoustic cover 61a functions as a support base 57b for the fuel manifold 55b. Specifically, the first top plate 65a of the first acoustic cover 61a constitutes the support plate 58b of the support base 57b, and the pair of first side peripheral plates 66a of the first acoustic cover 61a constitute the support legs 59b of the support base 57b.

[0049] As described above, in this embodiment as well, the first acoustic cover 61a functions as a support base 57b, so, similar to the embodiments described above, the stress generated from the combustion cylinder 44 to the fuel manifold 55b can be kept low, and the durability of the combustion cylinder 44 and the fuel manifold 55b can be increased.

[0050] Furthermore, in this embodiment, as in the second embodiment, the first acoustic cover 61a functions as a support base 57b, eliminating the need to provide a separate support base and reducing the number of components in the combustor 40b.

[0051] Furthermore, in this embodiment, a portion of the fuel manifold 55b is formed by having a portion of the second tip-side peripheral plate 66bt of the second acoustic cover 61b and a portion of the first top plate 65a of the first acoustic cover 61a. Therefore, in this embodiment, when the fuel manifold 55b is provided on the radially outer Dro of the first acoustic cover 61a and the tip-side Dct of the second acoustic cover 61b, the structure of the first acoustic cover 61a, the second acoustic cover 61b and the fuel manifold 55b can be simplified.

[0052] "Various variations" In the combustion chambers 40, 40a, and 40b of the above embodiments, the fuel manifolds 55, 55a, and 55b are directly connected to the support plate 58, or to the top plates 65, 65a of the acoustic covers 61, 61a that function as support plates. However, as shown in the combustion chamber 40c of Figure 10, a manifold support 67 may be provided on the radially outer Dro of the first top plate 65a of the first acoustic cover 61a, and the fuel manifold 55c may be connected to this manifold support 67. That is, the support base 57c of the fuel manifold 55c may consist of the top plate 65a of the first acoustic cover 61a as a support plate 58b, the side circumferential plate 66a of the first acoustic cover 61a as a support leg 59b, and the manifold support 67.

[0053] In this way, by providing the manifold support 67, the temperature gradient from the combustion chamber 44 to the fuel manifold 55c becomes gentler than the temperature gradient without the manifold support 67. Moreover, by providing the manifold support 67, the support base 57c becomes more easily deformed than without the manifold support 67. For this reason, by providing the manifold support 67, the stress generated from the combustion chamber 44 to the fuel manifold 55c can be kept lower than without the manifold support 67, thereby increasing the durability of the combustion chamber 44 and the fuel manifold 55c.

[0054] The modified example shown in Figure 10 is a modified example of the support base 57b in the third embodiment, but the manifold support 67 may also be added to the support base 57 in the first embodiment and the support base 57a in the second embodiment.

[0055] In each of the embodiments and modifications described above, the fuel manifolds 55, 55a, 55b, and 55c are connected to the secondary fuel nozzles 53 by branched secondary fuel piping 52. However, if the fuel manifolds 55, 55a, 55b, and 55c can be positioned so that they contact the secondary fuel nozzles 53, the branched secondary fuel piping 52 may be omitted.

[0056] Furthermore, this disclosure is not limited to the embodiment and modifications described above. Various additions, modifications, substitutions, partial deletions, etc., are possible without departing from the conceptual idea and spirit of the present invention derived from the claims and their equivalents.

[0057] "Addendum" The combustors 40, 40a, 40b, and 40c in the above embodiments can be understood, for example, as follows.

[0058] (1) The combustors 40, 40a, 40b, and 40c in the first embodiment are: A combustion cylinder 44 that is cylindrical around an axis Ac and on which fuel can be burned on its inner circumference, a primary fuel nozzle 48 that can inject primary fuel in the direction having a component toward the tip side Dct of the tip side Dct and the base side Dcb in the axial direction Dc on which the axis Ac extends, and a component attached to the combustion cylinder 44 at a position toward the tip side Dct from the primary fuel nozzle 48, and within the combustion cylinder 44, radially inner Dri and radially outer Dro in the radial direction Dr with respect to the axis Ac, of which radially inner D The combustion chamber comprises a secondary fuel nozzle 53 capable of injecting secondary fuel toward ri, fuel manifolds 55, 55a, 55b, 55c arranged on the outer circumference of the combustion chamber 44, forming an annular shape with respect to the axis Ac, capable of temporarily storing the secondary fuel and communicating with the secondary fuel nozzle 53, and support bases 57, 57a, 57b, 57c that support the fuel manifolds 55, 55a, 55b, 55c at a distance from the combustion chamber 44 in the radial direction Dr. The support bases 57, 57a, 57b, and 57c each have support plates 58, 58a, and 58b that are spaced radially outward from the combustion cylinder 44 in the direction Dro and extend circumferentially in the direction Dcc with respect to the axis Ac, and support legs 59, 59a, and 59b that are attached to the combustion cylinder 44 and support the support plates 58, 58a, and 58b so that a space is formed between the support plates 58, 58a, and 58b and the combustion cylinder 44. The fuel manifolds 55, 55a, 55b, and 55c are positioned radially outward from the support plates 58, 58a, and 58b in the direction Dro and are supported by the support bases 57, 57a, 57b, and 57c.

[0059] The temperature of the combustion chamber 44 is extremely high when fuel is burning inside. On the other hand, the temperature of the fuel manifolds 55, 55a, 55b, and 55c depends on the temperature of the fuel supplied to the fuel spaces 56, 56a, and 56b when fuel is burning inside the combustion chamber 44, and does not become as hot as the combustion chamber 44. Therefore, if the fuel manifolds 55, 55a, 55b, and 55c were directly connected to the outer surface of the combustion chamber 44, extremely high stress would be generated at the connection point between the combustion chamber 44 and the fuel manifolds 55, 55a, 55b, and 55c.

[0060] In this embodiment, since support bases 57, 57a, 57b, and 57c are interposed between the combustion cylinder 44 and the fuel manifolds 55, 55a, 55b, and 55c, the temperature gradient from the combustion cylinder 44 to the fuel manifolds 55, 55a, 55b, and 55c is gentler than the temperature gradient when the fuel manifolds 55, 55a, 55b, and 55c are directly connected to the outer surface of the combustion cylinder 44. Moreover, the support bases 57, 57a, 57b, and 57c in this embodiment have a shape that is easily deformable. For this reason, in this embodiment, the stress generated from the combustion cylinder 44 to the fuel manifolds 55, 55a, 55b, and 55c can be kept low, and the durability of the combustion cylinder 44 and the fuel manifolds 55, 55a, 55b, and 55c can be increased.

[0061] (2) The combustors 40, 40a, 40b, and 40c in the second embodiment are In the combustors 40, 40a, 40b, and 40c of the first embodiment described above, the support legs 59, 59a, and 59b are connected to the edges of the support plates 58, 58a, and 58b.

[0062] In this embodiment, the support legs 59, 59a, and 59b are connected to the edges of the support plates 58, 58a, and 58b so that a space is formed between the support plates 58, 58a, and 58b and the combustion cylinder 44. Therefore, in this embodiment, the support bases 57, 57a, 57b, and 57c are easily deformed, and the stress generated from the combustion cylinder 44 to the fuel manifolds 55, 55a, 55b, and 55c can be kept low.

[0063] (3) The combustor 40c in the third embodiment is In the combustor 40c of the first or second embodiment, the support base 57c has a manifold support 67 provided on the radially outer Dro of the support plate 58b. The fuel manifold 55c is connected to the manifold support 67.

[0064] Because the support base 57c has a manifold support 67, the temperature gradient from the combustion chamber 44 to the fuel manifold 55c becomes gentler than the temperature gradient without the manifold support 67. Moreover, because the support base 57c has a manifold support 67, the support base 57c is more easily deformed than if it did not have a manifold support 67. Therefore, because the support base 57c has a manifold support 67, the stress generated from the combustion chamber 44 to the fuel manifold 55c can be kept lower than if it did not have a manifold support 67, thereby increasing the durability of the combustion chamber 44 and the fuel manifold 55c.

[0065] (4) The combustors 40, 40a, 40b, and 40c in the fourth embodiment are: In the combustors 40, 40a, 40b, 40c of any one of the first to third embodiments, a branch secondary fuel pipe 52 is provided connecting the fuel manifolds 55, 55a, 55b, 55c and the secondary fuel nozzle 53 so that the secondary fuel in the fuel spaces 56, 56a, 56b can be delivered to the secondary fuel nozzle 53.

[0066] (5) The combustors 40a, 40b, and 40c in the fifth embodiment are: In the combustors 40a, 40b, 40c of any one of the first to fourth embodiments, there is an acoustic attenuator 60, 60Aa having an acoustic cover 61, 61a that forms an acoustic space 62, 62a on the outer circumference of the combustion cylinder 44. The support plates 58a, 58b and support legs 59a, 59b of the support bases 57a, 57b, 57c are composed of at least a part of the acoustic cover 61, 61a.

[0067] In this embodiment, since the support plates 58a, 58b and support legs 59a, 59b of the support bases 57a, 57b, 57c are composed of at least a part of the acoustic covers 61, 61a, similar to the first embodiment, the stress generated from the combustion cylinder 44 to the fuel manifolds 55a, 55b, 55c can be kept low, and the durability of the combustion cylinder 44 and the fuel manifolds 55a, 55b, 55c can be increased.

[0068] Furthermore, in this embodiment, since the acoustic covers 61 and 61a function as support bases 57a, 57b, and 57c, there is no need to provide separate support bases, and the number of components in the combustors 40a, 40b, and 40c can be reduced.

[0069] (6) The combustors 40b and 40c in the sixth embodiment are In the combustors 40b and 40c of the fifth embodiment, the acoustic attenuator 60A includes a first acoustic attenuator 60Aa and a second acoustic attenuator 60Ab positioned radially outward Dro of the first acoustic attenuator 60Aa. The first acoustic attenuator 60Aa has a first acoustic cover 61a that, together with a part of the plate forming the combustion cylinder 44, forms a first acoustic space 62a on the outer circumference side of the combustion cylinder 44. The first acoustic cover 61a includes a first top plate 65a that extends radially outward Dro from the combustion cylinder 44 and extends circumferentially Dcc to define the radially outward Dro edge of the first acoustic space 62a, and a first side circumferential plate 66a that extends circumferentially Dcc and connects the axial end Dc of the first top plate 65a to the combustion cylinder 44 to define the axial Dc edge of the first acoustic space 62a. The support plate 58b of the support bases 57b and 57c is made of the first top plate 65a. The support legs 59b of the support bases 57b and 57c are made of the first side periphery plate 66a.

[0070] In this embodiment, as in the fifth embodiment, the support plates 58b and support legs 59b of the support bases 57b and 57c are composed of at least a part of the first acoustic cover 61a. Therefore, as in the fifth embodiment, the stress generated from the combustion cylinder 44 to the fuel manifolds 55b and 55c can be kept low, and the durability of the combustion cylinder 44 and the fuel manifolds 55b and 55c can be increased.

[0071] (7) The combustor 40b in the seventh embodiment is In the combustor 40b of the sixth embodiment, the second acoustic attenuator 60Ab has a second acoustic cover 61b that, together with a part of the first top plate 65a, forms a second acoustic space 62b on the radially outer Dro of the first acoustic cover 61a. The second acoustic cover 61b has a second top plate 65b that extends radially outward from the first top plate 65a and extends in the circumferential direction Dcc to define the edge of the radially outer Dro of the second acoustic space 62b, and a second side circumferential plate 66b that extends in the circumferential direction Dcc and connects the end of the second top plate 65b in the axial direction Dc with the first top plate 65a to define the edge of the axial direction Dc of the second acoustic space 62b. The distance d1 from the outer circumferential surface of the combustion cylinder 44 to the edge of the radially outer Dro of the fuel manifold 55b is less than or equal to the distance d2 from the outer circumferential surface of the combustion cylinder 44 to the edge of the radially outer Dro of the second top plate 65b.

[0072] The portion of the combustor 40b including the combustion tube 44 may be inserted into the gas turbine casing 14 through the combustor mounting hole 14h of the casing 14 when it is assembled to the casing 14. In this case, the size of the cross-section perpendicular to the axis Ac at this insertion portion is limited by the size of the combustor mounting hole 14h. Therefore, the distance d1 from the outer circumferential surface of the combustion tube 44 to the radially outer edge Dro of the fuel manifold 55b is limited as described above to ensure that the combustor 40b can be assembled to the casing 14.

[0073] (8) The combustor 40b in the eighth aspect is In the combustor 40b of the seventh embodiment, the first side periphery plate 66a has a first tip-side periphery plate 66at connected to the tip-side Dct of the first top plate 65a and defining the edge of the tip-side Dct of the first acoustic space 62a. The second side periphery plate 66b has a second tip-side periphery plate 66bt connected to the tip-side Dct of the second top plate 65b and defining the edge of the tip-side Dct of the second acoustic space 62b. The second tip-side periphery plate 66bt is located on the base-side Dcb of the first tip-side periphery plate 66at. The fuel manifold 55b is arranged such that the fuel space 56b is located radially outward Dro of the first top plate 65a and on the tip-side Dct of the second tip-side periphery plate 66bt.

[0074] In this embodiment, the space radially outward Dro from the first top plate 65a of the first acoustic cover 61a and towards the tip Dct from the second tip side peripheral plate 66bt of the second acoustic cover 61b can be effectively utilized.

[0075] (9) The combustor 40b in the ninth embodiment is In the combustor 40b of the eighth embodiment, a portion of the fuel manifold 55b is formed having a portion of the second tip-side peripheral plate 66bt and a portion of the first top plate 65a.

[0076] In this embodiment, when the first acoustic cover 61a is located radially outward Dro and the second acoustic cover 61b is located at the tip side Dct of the fuel manifold 55b, the structures of the first acoustic cover 61a, the second acoustic cover 61b, and the fuel manifold 55b can be simplified.

[0077] The gas turbine 10 in the above embodiments can be understood, for example, as follows. (10) The gas turbine 10 in the tenth embodiment is The system comprises a combustor 40, 40a, 40b, 40c according to any one of the first to ninth embodiments, a compressor 20 capable of compressing air to generate compressed air used for the combustion of fuel in the combustion chamber 44, and a turbine 30 that can be driven by the combustion gas generated by the combustion of fuel in the combustion chamber 44. [Explanation of symbols]

[0078] 10: Gas Turbine 11: Gas turbine rotor 14: Intermediate casing 14h: Combustion device mounting hole 15: Gas turbine casing 20: Compressor 21: Compressor rotor 22: Rotor shaft 23: Moving blade row 25: Compressor casing 26: Stationary Wing Arrow 30: Turbine 31: Turbine Rotor 32: Rotor shaft 33: Moving blade row 35: Turbine casing 36: Static Wing Arrow 39: Combustion gas flow path 40, 40a, 40b, 40c: Combustor 41: Flange 42: Bolt 43: Inner cylinder 44: Combustion tube (or tail tube) 45: Cylinder support 46: Fuel line 47:Primary fuel piping 47p: Pilot fuel piping 47m: Main fuel piping 48: Primary fuel nozzle 48p: Pilot nozzle 48m: Main nozzle 51: Secondary fuel piping 52: Branch secondary fuel piping 53: Secondary fuel nozzle 55, 55a, 55b, 55c: Fuel manifold 56,56a,56b:Fuel space 57,57a,57b,57c: Support stand 58,58a,58b: Support plate 59,59a,59b: Support legs 60,60A: Acoustic attenuator 60Aa: First acoustic attenuator 60Ab: Second acoustic attenuator 61: Acoustic cover (support stand) 61a: First acoustic cover (support stand) 61b: Second sound cover 62: Acoustic Space 62a: First acoustic space 62b:Second acoustic space 63, 64: Through hole 65: Top plate (support plate) 65a: First top plate (support plate) 65b: Second top plate 66: Side circumferential plate (support leg) 66a: First side circumferential plate (support leg) 66ab: First proximal peripheral plate 66at: First tip side circumferential plate 66b:Second side circumferential plate 66bb: Second proximal peripheral plate 66bt: Second tip side circumferential plate 67: Manifold receiver A: Outside air F:Fuel G: Combustion gas Ar: Rotor axis Ac: Combustor axis (or simply axis) Da: Rotor axis direction Dau: Axis upstream side Dad: Downstream side of the axis Dc: Axial direction Dcb: proximal side Dct: Tip side Dcc: Circumferential direction Dr: Radial direction Dri: Radial inner side Dro: Radial outward

Claims

1. A combustion cylinder that is cylindrical around an axis and on the inner circumference where fuel can be burned, The combustion cylinder contains a primary fuel nozzle capable of injecting primary fuel in a direction having a component toward the tip side of the axial direction in which the axis extends, A secondary fuel nozzle is attached to the combustion cylinder at a position closer to the tip than the primary fuel nozzle, and is capable of injecting secondary fuel into the combustion cylinder toward the radially inward direction of the radial direction relative to the axis, A fuel manifold is positioned on the outer circumference of the combustion cylinder, forming an annular shape with respect to the axis, capable of temporarily storing the secondary fuel, and forming a fuel space that communicates with the secondary fuel nozzle. A support base that supports the fuel manifold with a gap between it and the combustion cylinder in the radial direction, An acoustic attenuator having an acoustic cover that forms an acoustic space on the outer circumference of the combustion cylinder, Equipped with, The support base comprises a support plate spaced radially outward from the combustion cylinder and extending circumferentially with respect to the axis, and support legs attached to the combustion cylinder and supporting the support plate such that a space is formed between the support plate and the combustion cylinder. The fuel manifold is positioned radially outward of the support plate and supported by the support base. The support plate and support legs of the support base are composed of at least a part of the acoustic cover. Combustion device.

2. In the combustor according to claim 1, The support legs are connected to the edge of the support plate. Combustion device.

3. In the combustor according to claim 1 or 2, The support base has a manifold holder provided on the radially outer side of the support plate, The fuel manifold is connected to the manifold receiver, Combustion device.

4. In the combustor according to claim 1 or 2, The fuel manifold is provided with a branched secondary fuel pipe connecting the secondary fuel nozzle so that the secondary fuel in the fuel space can be delivered to the secondary fuel nozzle. Combustion device.

5. In the combustor according to claim 1 or 2, The sound attenuator comprises a first sound attenuator and a second sound attenuator positioned radially outward of the first sound attenuator. The first acoustic attenuator has a first acoustic cover that, in cooperation with a part of the plate forming the combustion cylinder, forms a first acoustic space on the outer circumference side of the combustion cylinder. The first acoustic cover comprises a first top plate that extends circumferentially away from the combustion cylinder radially outward and defines the radially outer edge of the first acoustic space, and a first side circumferential plate that extends circumferentially and connects the axial end of the first top plate to the combustion cylinder, defining the axial edge of the first acoustic space. The support plate of the support base is composed of the first top plate, The support legs of the support base are made of the first side periphery plate. Combustion device.

6. In the combustor according to claim 5, The second acoustic attenuator has a second acoustic cover that, in cooperation with a part of the first top plate, forms a second acoustic space on the radially outer side of the first acoustic cover. The second acoustic cover comprises a second top plate that extends radially outward from the first top plate and circumferentially to define the radially outer edge of the second acoustic space, and a second side circumferential plate that extends circumferentially and connects the axial end of the second top plate to the first top plate to define the axial edge of the second acoustic space. The distance from the outer circumferential surface of the combustion cylinder to the radially outer edge of the fuel manifold is less than or equal to the distance from the outer circumferential surface of the combustion cylinder to the radially outer edge of the second top plate. Combustion device.

7. In the combustor according to claim 6, The first side peripheral plate is connected to the front end of the first top plate and has a first front peripheral plate that defines the front edge of the first acoustic space, The second side peripheral plate is connected to the front end of the second top plate and has a second front end peripheral plate that defines the front edge of the second acoustic space, The second tip-side peripheral plate is located closer to the base end than the first tip-side peripheral plate. The fuel manifold is positioned such that the fuel space is radially outward from the first top plate and toward the tip side from the second tip side peripheral plate. Combustion device.

8. In the combustor according to claim 7, A portion of the fuel manifold is formed having a portion of the second tip side peripheral plate and a portion of the first top plate, Combustion device.

9. A combustor according to claim 1 or 2, A compressor capable of compressing air to generate compressed air used for the combustion of fuel in the combustion chamber, A turbine that can be driven by combustion gases generated by the combustion of fuel in the aforementioned combustion chamber, A gas turbine equipped with a gas turbine.

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