Combustor liner, combustor, and gas turbine

Abstract

A combustion cartridge (20) includes a tubular main body (21) and an air supply tube (40). An insertion opening (25) and a plurality of cooling flow paths (30) are formed in the main body. A portion of the air supply tube is inserted into the inner peripheral side of the main body from the insertion opening. A collision region flow path (33i) as a portion of the plurality of cooling flow paths has a collision region meandering flow path portion (34i). The collision region meandering flow path portion intersects a collision gas axis (Ai) extending in a flow direction of combustion gas flowing toward a tube central axis (At) of the air supply tube in the combustion gas, and extends from the collision gas axis toward a direction having an upstream side directional component along an edge of the insertion opening, and extends from the collision gas axis toward a direction having a downstream side directional component along the edge of the insertion opening. In the collision region meandering flow path portion, a portion in a range of a prescribed angle around the tube central axis and centered on the collision gas axis is not formed with an outlet.

Description

Technical Field

[0001] The present invention relates to a burner cylinder that defines a flow path for the flow of combustion gases, a burner having the burner cylinder, and a gas turbine having the burner.

[0002] This application claims priority based on Japanese Patent Application No. 2021-028331 filed on February 25, 2021, the contents of which are incorporated herein by reference. Background Technology

[0003] The combustor of a gas turbine includes a combustor canister that defines the flow path of the combustion gases and a combustor body into which air and fuel are injected. Inside the combustor canister, the combustion gases generated during fuel combustion flow simultaneously.

[0004] As a burner cartridge, for example, there is a burner cartridge disclosed in Patent Document 1. This burner cartridge includes a cylindrical body about an axis and an air supply pipe mounted on the body. The cylindrical body has an opening extending from its outer circumferential surface to its inner circumferential surface and multiple cooling flow paths for the flow of cooling medium. In some of the multiple cooling flow paths, the outlets of the cooling flow paths are formed at the edges of the openings. The air supply pipe supplies secondary combustion air to the inner circumferential side of the body. This air supply pipe has a cylindrical tube body and a lip provided on the tube body. A portion of the tube body is inserted into the inner circumferential side of the body from the opening and protrudes towards the inner circumferential side of the body. At both ends of the tube body, the aforementioned lip is provided at the end on the inner circumferential side of the body.

[0005] Previous technical documents

[0006] Patent documents

[0007] Patent Document 1: Japanese Patent Application Publication No. 2009-092373 Summary of the Invention

[0008] The technical problem to be solved by the invention

[0009] High-temperature combustion gases flow along the inner circumference of the main body in the burner cartridge described in Patent Document 1. A portion of these combustion gases collides with a portion of the air supply pipe located along the inner circumference of the main body. When the combustion gases collide with the air supply pipe, their dynamic pressure decreases, and their static pressure increases. As a result, in the burner cartridge described in Patent Document 1, a portion of the combustion gases flows backward into a cooling flow path with an outlet formed at the edge of the main body opening, potentially burning up the main body.

[0010] Therefore, the object of the present invention is to provide a technique for improving the durability of burner cartridges.

[0011] means for solving technical problems

[0012] As one aspect of the invention for achieving the above-mentioned objective, a burner cartridge comprises:

[0013] The main body, cylindrical in shape around a cylindrical axis, defines a combustion space around which combustion gases flow from the upstream side to the downstream side in a direction extending along the cylindrical axis. An air supply pipe is mounted on the main body and has the following components formed on the cylindrical body: an inner circumferential surface facing the combustion gases; an outer circumferential surface facing the side opposite to the inner circumferential surface; an insertion opening extending from the outer circumferential surface to the inner circumferential surface; and multiple cooling channels extending between the inner and outer circumferential surfaces in a direction along the inner circumferential surface, allowing cooling medium to flow within the body. A portion of the air supply pipe is inserted into the inner circumferential side of the main body from the insertion opening and protrudes towards the inner circumferential side of the main body. Each of the multiple cooling channels has an inlet for introducing cooling medium into its interior and an outlet for discharging the cooling medium flowing within its interior. Each of the multiple cooling channels has multiple openings surrounding a flow path as part of the multiple cooling channels. The multiple openings surrounding the flow path have a meandering flow path portion extending along the edge of the insertion opening. Of the plurality of opening-surrounding flow paths, at least one opening-surrounding flow path constitutes a collision region flow path. The collision region flow path has a collision region detour flow path section as the detour flow path section. The collision region detour flow path section intersects a collision gas axis extending in a radial direction relative to the central axis of the air supply pipe and in the flow direction of the combustion gas flowing toward the central axis of the pipe. It extends from the collision gas axis along the edge of the insertion opening in a direction having an upstream directional component, and from the collision gas axis along the edge of the insertion opening in a direction having a downstream directional component. In the collision region detour flow path section, the intersection point with the collision gas axis is located further upstream than the central axis of the pipe. In the collision region detour flow path section, within a range of angles about the central axis of the pipe and centered on the collision gas axis, the outlet with an opening on the inner circumferential surface is not formed.

[0014] When the combustion gas flowing within the main body collides with the air supply pipe, its dynamic pressure decreases and its static pressure increases. The static pressure rise region, where the combustion gas collides with the air supply pipe and its static pressure increases, is within a predetermined upstream angle relative to the pipe's central axis and a predetermined downstream angle relative to the colliding gas axis. Because this method has multiple openings surrounding the flow path with a meandering flow path extending along the edge of the insertion opening, the edge of the insertion opening can be cooled by the cooling medium flowing through the meandering flow path. However, in this method, in the portion of the meandering flow path in the collision region where the static pressure rises, an outlet for the collision region flow path is not formed. Therefore, in this method, even if the static pressure of the combustion gas within the main body rises in the static pressure rise region due to the collision with the air supply pipe, backflow of the combustion gas into the collision region flow path can be suppressed.

[0015] As one aspect of the invention for achieving the above-mentioned objective, the burner comprises:

[0016] The burner cartridge and burner of the aforementioned embodiment are disposed upstream of the insertion opening and are capable of injecting fuel into the combustion space. The burner includes: a burner frame having an annular fuel outlet centered on the cartridge axis; and a swirler disposed within the burner frame, capable of causing the fuel ejected from the fuel outlet to rotate about the cartridge axis. The swirler is configured such that the angle of the fuel ejected from the fuel outlet relative to the cartridge axis is a predetermined fuel rotation angle. The angle of the colliding gas axis relative to the cartridge axis is within ±15° of the fuel rotation angle.

[0017] Within the combustion space on the inner circumference of the main body, when the fuel rotates around the cylinder axis, the angle between the colliding gas axis and the cylinder axis, i.e., the collision axis angle, is approximately the fuel rotation angle. However, due to the ratio of fuel injection flow rate to combustion air injection flow rate and the rotation angle of the combustion air, this collision axis angle will vary to some extent. Therefore, the collision axis angle does not need to be exactly the same as the fuel rotation angle; it only needs to be within ±15° of the fuel rotation angle.

[0018] As one aspect of the invention for achieving the above-mentioned objectives, a gas turbine comprises:

[0019] The burner in one embodiment includes a compressor that delivers compressed air to the burner, and a turbine that can be driven by the combustion gas from the burner.

[0020] Invention Effects

[0021] In one aspect of the present invention, the durability of the burner cartridge can be improved. Attached Figure Description

[0022] Figure 1 This is a schematic diagram illustrating the structure of a gas turbine in one embodiment of the present invention.

[0023] Figure 2 This is a partial cross-sectional view of the burner in one embodiment of the present invention.

[0024] Figure 3 It is along Figure 2 A sectional view cut along line III-III.

[0025] Figure 4 This is a top view of a burner cylinder according to one embodiment of the present invention.

[0026] Figure 5 It is along Figure 4 A sectional view cut by the VV line.

[0027] Figure 6 This is a top view of a burner cylinder in a first variation of an embodiment of the present invention.

[0028] Figure 7 This is a top view of a burner cylinder in a second variation of an embodiment of the present invention. Detailed Implementation

[0029] Hereinafter, with reference to the accompanying drawings, an embodiment of the burner cylinder, burner and gas turbine according to the present invention, as well as various modifications of the burner cylinder, will be described.

[0030] "An Implementation Method of a Gas Turbine"

[0031] refer to Figure 1 The gas turbine of this embodiment will be described.

[0032] The gas turbine of this embodiment includes: a compressor 1 that compresses external air Ao to generate compressed air A; a plurality of burners 4 that burn fuel F in the compressed air A to generate combustion gas G; and a turbine 5 that is driven by the combustion gas G.

[0033] The compressor 1 has a compressor rotor 2 that rotates about a rotation axis Ar and a compressor housing 3 that covers the compressor rotor 2 in a manner that enables the compressor rotor 2 to rotate. The turbine 5 has a turbine rotor 6 that rotates about a rotation axis Ar and a turbine housing 7 that covers the turbine rotor 6 in a manner that enables the turbine rotor 6 to rotate.

[0034] The compressor 1 is positioned upstream of the turbine 5, along the direction of rotational axis Ar. The compressor rotor 2 and the turbine rotor 6 are located on the same rotational axis Ar and are interconnected to form a gas turbine rotor 8. This gas turbine rotor 8 may include, for example, a rotor connected to a generator GEN.

[0035] The gas turbine also includes an intermediate housing 9. The compressor housing 3, the intermediate housing 9, and the turbine housing 7 are arranged sequentially along the aforementioned axis of rotation and are interconnected. Multiple burners 4 are disposed in the intermediate housing 9.

[0036] Compressor 1 compresses external air Ao to generate compressed air A. This compressed air A flows into burner 4. Fuel F is also supplied to burner 4. Inside burner 4, fuel F burns to generate combustion gas G. This combustion gas G is sent into turbine 5, causing turbine rotor 6 to rotate. The rotation of turbine rotor 6 causes the rotor of generator GEN, connected to gas turbine rotor 8, to rotate. As a result, generator GEN generates electricity. Furthermore, in this embodiment, fuel F is primarily blast furnace gas (hereinafter referred to as BFG) from a steel plant's blast furnace, and depending on the circumstances, BFG may include coke oven gas (COG).

[0037] "An embodiment of a burner cylinder and a burner equipped with the burner cylinder"

[0038] refer to Figures 2-5 The burner cylinder of this embodiment and the burner 4 equipped with the burner cylinder will be described.

[0039] The burner 4 of this embodiment includes: a combustion chamber 20 serving as a burner cylinder, defining a combustion space S for the flow of combustion gas G; and a burner body 10 into which compressed air A and fuel F are injected. The combustion chamber 20 is disposed within an intermediate housing 9 in which compressed air A, compressed by the compressor 1, floats (see reference). Figure 1 ).

[0040] like Figure 2 and Figure 3 As shown, the burner body 10 includes an outer cylinder 11, a support cylinder 12, an inner cylinder 13, a burner 14, and an air injector 17. The outer cylinder 11, support cylinder 12, and inner cylinder 13 are all cylindrical around the cylinder axis Ac. Hereinafter, the direction in which the cylinder axis Ac extends will be defined as the cylinder axis direction Da, and one side of this cylinder axis direction Da will be designated as the upstream side Dau, and the other side as the downstream side Dad. Furthermore, the circumferential direction relative to the cylinder axis Ac will be simply referred to as the circumferential direction Dc.

[0041] The outer cylinder 11 has a cylindrical outer cylinder body 11a surrounding the cylinder axis Ac and a cap 11b that blocks the opening on the upstream side Dau of the outer cylinder body 11a. The downstream end of the outer cylinder body 11a, Dad, is used... Figure 1 The intermediate housing 9 is described as connected.

[0042] The support cylinder 12 is cylindrical around the cylinder axis Ac and is disposed on the inner circumference of the outer cylinder 11. An air inlet opening 12a is formed on the support cylinder 12, extending from the outer circumference to the inner circumference. The upstream end of the support cylinder 12, Dau, is connected to the cover 11b of the outer cylinder 11. In the intermediate shell (reference...) Figure 1 Compressed air A floating inside the support cylinder 12 flows into the inner circumference of the support cylinder 12 from the outer circumference through the air inlet opening 12a.

[0043] The inner cylinder 13 has a small-diameter main body 13a, an expanded-diameter main body 13b, and a large-diameter main body 13c. The small-diameter main body 13a, the expanded-diameter main body 13b, and the large-diameter main body 13c are all cylindrical around the cylinder axis Ac. The small-diameter main body 13a is disposed on the inner circumference of the support cylinder 12. The upstream end of the expanded-diameter main body 13b (Dau) is connected to the downstream end of the small-diameter main body 13a (Dad). The inner diameter of the expanded-diameter main body 13b gradually increases towards the downstream end (Dad). The inner diameter of the downstream end of the expanded-diameter main body 13b (Dad) is substantially the same as the inner diameter of the support cylinder 12. The upstream end of the large-diameter main body 13c (Dau) is connected to the downstream end of the expanded-diameter main body 13b (Dad) and the downstream end of the support cylinder 12 (Dad). Therefore, the inner cylinder 13 is supported by the support cylinder 12. The space on the inner circumference of the expanded-diameter main body 13b and the space on the inner circumference of the large-diameter main body 13c form a portion of the upstream end (Dau) of the combustion space S.

[0044] The burner 14 has a burner frame 15 and multiple fuel cyclones 16 for rotating gaseous fuel F around the cylinder axis Ac. The burner frame 15 has a burner cylinder 15a centered on the cylinder axis Ac and a central cylinder 15b disposed within the burner cylinder 15a. The burner cylinder 15a is disposed on the inner circumference of the small-diameter body 13a of the inner cylinder 13. The upstream side Dau portion of the burner cylinder 15a extends through the cover 11b portion of the outer cylinder 11. The burner cylinder 15a is fixed to the cover 11b portion of the outer cylinder 11. Both the upstream side Dau end and the downstream side Dad end of the burner cylinder 15a are open. Fuel F flows into the burner cylinder 15a from the opening at the upstream side Dau end. The central cylinder 15b is cylindrical around the cylinder axis Ac and is configured such that its central axis is located on the cylinder axis Ac. The annular space between the inner circumference of the burner cylinder 15a and the outer circumference of the central cylinder 15b forms a fuel flow path for the flow of fuel F. Therefore, the downstream end of the burner cylinder 15a (Dad) and the downstream end of the outer circumference of the central cylinder 15b (Dad) form an annular fuel outlet 14j centered on the cylinder axis Ac. Multiple fuel swirlers 16 are disposed within the fuel flow path. The ends of the fuel swirlers 16 that are radially outward relative to the cylinder axis Ac are connected to the inner circumference of the burner cylinder 15a, and the ends that are radially inward relative to the cylinder axis Ac are connected to the outer circumference of the central cylinder 15b. The central cylinder 15b is fixed to the burner cylinder 15a via the multiple fuel swirlers 16. The multiple fuel swirlers 16 are configured such that the angle of the fuel F ejected from the fuel outlet 14j into the combustion space S relative to the cylinder axis Ac is a predetermined fuel rotation angle θf. Specifically, the angle of the downstream Dad portion of the fuel cyclone separator 16 relative to the cylinder axis Ac is called the aforementioned fuel swirl angle θf. This fuel swirl angle θf is, for example, 40°.

[0045] The air injector 17 has an air injection frame 18 and multiple air vortexes 19 for rotating compressed air A around the cylinder axis Ac. The air injection frame 18 is composed of a small-diameter body 13a of an inner cylinder 13 and a burner cylinder 15a. The annular space between the outer circumference of the burner cylinder 15a and the inner circumference of the small-diameter body 13a forms an airflow path for the compressed air A to flow. Compressed air A flowing into the inner circumference of the support cylinder 12 from the air inlet opening 12a of the support cylinder 12 flows into the airflow path through the gap between the outer circumference of the burner cylinder 15a and the end of the upstream side Dau of the small-diameter body 13a. The compressed air A flows in this airflow path and is ejected into the combustion space S from the air outlet 17j as primary combustion air A1. The air outlet 17j is annular about the cylinder axis Ac and is formed by the end of the downstream side Dad of the burner cylinder 15a and the end of the downstream side Dad of the small-diameter body 13a. Multiple air swirlers 19 are arranged within the airflow path. The radially outer end of each air swirler 19 relative to the cylinder axis Ac is connected to the inner circumferential surface of the small-diameter body 13a, and the radially inner end relative to the cylinder axis Ac is connected to the outer circumferential surface of the burner cylinder 15a. The multiple air swirlers 19 are configured such that the angle of the compressed air A (primary combustion air A1) ejected from the air outlet 17j into the combustion space S relative to the cylinder axis Ac is a predetermined air rotation angle. Specifically, the angle of the downstream Dad portion of the air swirler 19 relative to the cylinder axis Ac is the aforementioned air rotation angle. This air rotation angle is, for example, 35°.

[0046] The combustion chamber 20, serving as a burner casing, has a cylindrical body 21 surrounding a cylinder axis Ac and an air supply pipe 40 mounted on the body 21. The air supply pipe 40 is sometimes referred to as a scoop. The cylindrical body 21 defines the periphery of the combustion space S through which combustion gases G flow. The upstream end of the body 21, Dau, is connected to the downstream end of the inner cylinder 13, Dad. Furthermore, as... Figure 1 As shown, the downstream end of the main body 21, Dad, is connected to the combustion gas inlet 5i of the turbine 5.

[0047] The main body 21 has an inner peripheral surface 23i facing the combustion gas G, an outer peripheral surface 22o facing the side opposite to the inner peripheral surface 23i, a circular insertion opening 25 extending from the outer peripheral surface 22o to the inner peripheral surface 23i, and multiple cooling flow paths 30 for the flow of cooling medium between the inner peripheral surface 23i and the outer peripheral surface 22o. The cooling medium here is the intermediate shell (reference). Figure 1Compressed air A floats inside. Multiple cooling flow paths 30 each have: an inlet 30i, which opens on the outer peripheral surface 22o of the main body 21 and introduces compressed air A into it; and an outlet 30o, which opens on the inner peripheral surface 23i and discharges the compressed air A flowing inside. In this embodiment, an inlet 30i is formed at one end of the cooling flow path 30, and an outlet 30o is formed at the other end.

[0048] like Figure 5 As shown, the main body 21 has an outer side plate 22 and an inner side plate 23. One of the opposite faces of the outer side plate 22 forms the outer peripheral surface 22o of the main body 21, and the other face forms the mating surface 22c. Similarly, one of the opposite faces of the inner side plate 23 forms the mating surface 23c, and the other face forms the inner peripheral surface 23i of the main body 21. A plurality of long, recessed grooves 22d are formed on the mating surface 22c of the outer side plate 22. The mating surfaces 22c and 23c of the outer side plate 22 and the inner side plate 23 are joined together by welding or the like. Through the joining of the outer side plate 22 and the inner side plate 23, the opening of the long groove 22d formed in the outer side plate 22 is blocked by the inner side plate 23, and the long groove 22d becomes a cooling flow path 30. Therefore, a plurality of cooling flow paths 30 extend between the outer peripheral surface 22o and the inner peripheral surface 23i of the main body 21 in the direction along the inner peripheral surface 23i.

[0049] like Figure 2 , Figure 4 and Figure 5 As shown, the air supply pipe 40 has a cylindrical section 41 centered on the central axis At and a flange 42 fixed to the section 41. A portion of the section 41 is inserted into the inner circumference of the body 21 through an insertion opening 25 and protrudes towards the inner circumference of the body 21. Considering the difference in thermal deformation between the section 41 and the body 21, a small gap exists between the outer circumferential surface of the section 41 and the edge of the insertion opening 25. At both ends of the section 41, a flange 42 is fixed at the end protruding towards the outer circumferential surface of the body 21. This flange 42 protrudes from the section 41 in a radial direction relative to the central axis At. A plurality of pipe fixing blocks 45 are disposed between the flange 42 of the air supply pipe 40 and the outer circumferential surface 22o of the body 21. One surface of the pipe fixing block 45 engages with the outer circumferential surface 22o of the body 21, and the other surface of the pipe fixing block 45 engages with the flange 42 of the air supply pipe 40. The air supply pipe 40 is fixed to the main body 21 by a plurality of pipe fixing blocks 45. With the air supply pipe 40 fixed to the main body 21, the central axis At of the air supply pipe 40 extends radially relative to the cylinder axis Ac. The air supply pipe 40 will be located in the intermediate housing 9 (reference). Figure 1 Compressed air A floating inside is introduced into the inner periphery of the main body 21 as secondary combustion air A2.

[0050] like Figure 5 As shown, in this embodiment, among the plurality of cooling flow paths 30, the outlets 30o of two adjacent cooling flow paths 30 in the circumferential direction Dc are at different positions in the cylinder axial direction Da. Furthermore, in this embodiment, the inlet 30i of one cooling flow path 30 sometimes communicates with the inlet 30i of another cooling flow path 30. Also, in this embodiment, the outlet 30o of one cooling flow path 30 sometimes communicates with the outlet 30o of another cooling flow path 30. In this embodiment, among the plurality of cooling flow paths 30, a portion constitutes a plurality of normal flow paths 31, another portion constitutes a plurality of compensating flow paths 32, and the remaining portion constitutes a plurality of open surrounding flow paths 33.

[0051] The multiple opening-surrounding flow paths 33 each have: a meandering flow path 34 extending along the edge of the insertion opening 25; an upstream flow path 35 extending from the end of the upstream side Dau of the meandering flow path 34 towards the upstream side Dau in the direction of the cylinder axis Da; and a downstream flow path 36 extending from the end of the downstream side Dad of the meandering flow path 34 towards the downstream side Dad in the direction of the cylinder axis Da. Both the upstream flow path 35 and the downstream flow path 36 are straight flow path sections extending in the direction of the cylinder axis Da. On the other hand, since the meandering flow path 34 is along the edge of the circular insertion opening 25, it is an arc-shaped flow path section. An inlet 30i of the opening-surrounding flow path 33 is formed in one of the upstream flow path section 35 and the downstream flow path section 36. This inlet 30i communicates with the inlet 30i of one of the multiple normal flow paths 31. Furthermore, the outlet 30o of the opening surrounding the flow path 33 is formed on the other side of the upstream flow path section 35 and the downstream flow path section 36. This outlet 30o is common to the outlet 30o of another normal flow path 31 among the plurality of normal flow paths 31. The inlet 30i and outlet 30o of the opening surrounding the flow path 33 are not formed on the detour flow path section 34.

[0052] Here, the line extending in the radial direction relative to the tube's central axis At and in the flow direction of the combustion gas G flowing toward the tube's central axis At is defined as the collision gas axis Ai. In this embodiment, the flow direction of the combustion gas G flowing toward the tube's central axis At relative to the cylinder axis Ac is approximately the same as the aforementioned fuel rotation angle θf, which is 40°. Therefore, the angle formed by the collision gas axis Ai relative to the cylinder axis Ac in this embodiment, i.e., the collision axis angle θi, is 40°. The intersection of the collision gas axis Ai and the outer peripheral surface of the air supply pipe 40 constitutes the main collision position 41p.

[0053] Multiple openings surrounding a portion of the flow path 33 constitute multiple collision region flow paths 33i, while the remainder constitute multiple non-collision region flow paths 33n. The detour flow path portion 34 of the collision region flow path 33i constitutes the collision region detour flow path portion 34i. Here, as... Figure 4 As shown, in the circumferential direction Dc, with the pipe center axis At as a reference, the side where the main collision position 41p exists is designated as the first circumferential side Dc1, and the opposite side is designated as the second circumferential side Dc2. The collision region bypass flow path 34i of each of the multiple collision region flow paths 33i exists on the first circumferential side Dc1, with the pipe center axis At as a reference. On the other hand, the bypass flow path 34 of each of the multiple non-collision region flow paths 33n exists on the second circumferential side Dc2, with the pipe center axis At as a reference.

[0054] Each of the multiple collision region flow paths 33i has a collision region bypass flow path section 34i that intersects with the collision gas axis Ai. The intersection position 34p that intersects with the collision gas axis Ai is located on the upstream side Dau, which is higher than the tube center axis At, and on the first circumferential side Dc1, which is higher than the tube center axis At.

[0055] When the combustion gas G flowing within the main body 21 collides with the air supply pipe 40, its dynamic pressure decreases and its static pressure increases. The static pressure increase region R, where the static pressure of the combustion gas G increases due to the collision with the air supply pipe 40, is within a predetermined angle (θu+θd) centered on the collision gas axis Ai, around the central axis At of the pipe. Specifically, the static pressure increase region R is within a predetermined upstream angle θu from the collision gas axis Ai towards the upstream side Dau, and within a predetermined downstream angle θd from the collision gas axis Ai towards the downstream side Dad. Here, the predetermined angle (θu+θd) varies according to the flow velocity of the combustion gas G immediately before colliding with the air supply pipe 40. Therefore, the predetermined angle (θu+θd) is 60°±20°. Specifically, the upstream angle θu and the downstream angle θd are 30°±10°. In addition, in this embodiment, the upstream angle θu and the downstream angle θd are 30°.

[0056] The collision region meandering flow path 34i extends from the collision gas axis Ai along the edge of the insertion opening 25 in a direction having an upstream Dau component, and also extends from the collision gas axis Ai along the edge of the insertion opening 25 in a direction having a downstream Dad component. The end of the portion extending from the collision gas axis Ai in the direction having an upstream Dau component connects to the upstream flow path 35 of the collision region flow path 33i. Furthermore, the end of the portion extending from the collision gas axis Ai in the direction having a downstream Dad component connects to the downstream flow path 36 of the collision region flow path 33i.

[0057] As described above, no inlet 30i and outlet 30o are formed on the respective meandering flow path 34 of the multiple openings surrounding the flow path 33. Therefore, in the part of the collision region meandering flow path 34i that exists in the static pressure rise region R within the range of the upstream side angle θu from the collision gas axis Ai to the upstream side Dau and the range of the downstream side angle θd from the collision gas axis Ai to the downstream side Dad, no inlet 30i and outlet 30o are formed.

[0058] Here, among the multiple collision region flow paths 33i, the collision region flow path 33i closest to the insertion opening 25 in the collision region detour flow path section 34i is designated as the first collision region flow path 33i1. The collision region flow path 33i adjacent to the first collision region flow path 33i1 along the first circumferential side Dcl is designated as the second collision region flow path 33i2, and the collision region flow path 33i adjacent to the second collision region flow path 33i2 along the first circumferential side Dcl is designated as the third collision region flow path 33i3. Figure 5 As shown, the width w1 of the first collision region flow path 33i1 is larger than the width w2 of the second collision region flow path 33i2 and the width w3 of the third collision region flow path 33i3. Therefore, the cross-sectional area of ​​the first collision region flow path 33i1 is larger than the cross-sectional area of ​​the second collision region flow path 33i2 and the cross-sectional area of ​​the third collision region flow path 33i3.

[0059] The plurality of normal flow paths 31 and the plurality of compensated flow paths 32 are all straight flow paths extending in the direction of cylinder axis Da. One of the inlet 30i and the outlet 30o is formed at the upstream end of the plurality of normal flow paths 31 and the plurality of compensated flow paths 32 on the Daa. Furthermore, the other of the inlet 30i and the outlet 30o is formed at the downstream end of the plurality of normal flow paths 31 and the plurality of compensated flow paths 32 on the Daa.

[0060] Multiple compensation flow paths 32 exist within the circumferential Dc region of at least one of the multiple open surrounding flow paths 33, specifically the detour flow path portion 34 of the open surrounding flow path 33, and are positioned identically in the cylindrical axial direction Da relative to a portion of the detour flow path portion 34 of the at least one open surrounding flow path 33. In this embodiment, the inlet 30i of each of the multiple compensation flow paths 32 is formed at the end in the cylindrical axial direction Da near the insertion opening 25.

[0061] As described above, the plurality of normal flow paths 31 are the flow paths in the plurality of cooling flow paths 30 other than the plurality of open surrounding flow paths 33 and the plurality of compensating flow paths 32. In this embodiment, a portion of the plurality of normal flow paths 31 is adjacent to a detour flow path portion 34 of an open surrounding flow path 33 on the side of the circumferential direction Dc away from the insertion opening 25. As described above, since the detour flow path portion 34 is arc-shaped and the normal flow path 31 is straight, there are portions with shorter distances and portions with longer distances between the normal flow path 31 and the detour flow path portion 34 in the circumferential direction Dc. Among the plurality of compensating flow paths 32, a portion of the compensating flow path 32a is disposed between the normal flow path 31 and the detour flow path portion 34 in the portion with longer distances and undertakes the function of cooling that portion. Furthermore, among the multiple compensation flow paths 32, other compensation flow paths 32b are arranged between each other of the upstream side flow path portion 35 or the downstream side flow path portion 36 of two adjacent openings surrounding the flow path 33 in the circumferential direction Dc, and undertake the function of cooling the portion between them.

[0062] In the cooling flow path 30, the temperature of the cooling medium flowing near the outlet 30o is higher than the temperature of the cooling medium flowing near the inlet 30i. Therefore, the cooling capacity near the outlet 30o is lower than the cooling capacity near the inlet 30i. Consequently, when the outlet 30o positions of two adjacent cooling flow paths 30 in the circumferential direction Dc are the same in the cylinder axial direction Da, the cooling capacity of the portions of the two cooling flow paths 30 near their respective outlets 30o becomes very low. In this embodiment, since the outlet 30o positions of two adjacent cooling flow paths 30 in the circumferential direction Dc are different in the cylinder axial direction Da, it is possible to prevent the cooling capacity of the portions of the two cooling flow paths 30 near their respective outlets 30o from becoming very low.

[0063] In this embodiment, the main body 21 has a plurality of openings surrounding a flow path 33 having a meandering flow path portion 34 extending along the edge of the insertion opening 25. Therefore, in this embodiment, the edge of the insertion opening 25 can be cooled by the cooling medium flowing through the meandering flow path portion 34.

[0064] In this embodiment, a collision region detour flow path portion 34i is formed along the edge of the insertion opening 25 in the static pressure rise region R around the air supply pipe 40. In this collision region detour flow path portion 34i, the portion within the static pressure rise region R does not have an outlet 30o of the collision region flow path 33i. Therefore, even if the combustion gas G in the main body 21 collides with the air supply pipe 40 and the static pressure of the combustion gas G rises within the static pressure rise region R, the backflow of the combustion gas G into the collision region flow path 33i can be suppressed.

[0065] Furthermore, in this embodiment, among the multiple collision region flow paths 33i, the cross-sectional area of ​​the first collision region flow path 33i1, which is closest to the insertion opening 25, is larger than that of the other collision region flow paths 33i. Therefore, the flow rate of compressed air flowing as the cooling medium in the first collision region flow path 33i1 is greater than the flow rate of compressed air flowing as the cooling medium in the other collision region flow paths 33i. Moreover, in this embodiment, the inlet 30i of each of the multiple compensation flow paths 32 is formed at the end near the insertion opening 25 in the cylindrical axial direction Da. Therefore, in this embodiment, the portion of the main body 21 near the insertion opening 25 can be actively cooled.

[0066] In this embodiment, from the above viewpoint, it is possible to prevent the main body 21 near the air supply pipe 40 from being burned, and to improve the durability of the combustion chamber 20.

[0067] "First variation of the burner canister"

[0068] refer to Figure 6 A first modified example of the burner cylinder in the above embodiment will be described.

[0069] The burner cartridge in this modified example is also a burner cartridge 20a, similar to that in the first embodiment. The burner cartridge 20a in this modified example differs from the burner cartridge 20 in the first embodiment in the shape and arrangement of multiple cooling flow paths, but the other structures are the same.

[0070] In this modified example, similar to the above embodiment, among the plurality of cooling flow paths 30, a portion constitutes a plurality of open surrounding flow paths 33a, another portion constitutes a compensation flow path 32, and the remaining portion constitutes a normal flow path 31.

[0071] In this variation, all the multiple open surrounding flow paths 33a are collision region flow paths 33i. That is, the multiple open surrounding flow paths 33a in this variation do not include the non-collision region flow path 33n in the above embodiment.

[0072] The multiple collision region flow paths 33i each have a collision region detour flow path portion 34i that extends along the edge of the insertion opening 25 and is arc-shaped, just like the collision region flow path 33i in the above embodiment.

[0073] Each of the multiple collision region flow paths 33i has a collision region bypass flow path 34i that intersects the collision gas axis Ai, similar to the embodiment described above. The intersection position 34p with the collision gas axis Ai is located upstream of the pipe center axis At (Dau) and circumferentially closer to the pipe center axis At (Dc). The collision region bypass flow path 34i extends from the collision gas axis Ai along the edge of the insertion opening 25 in a direction having an upstream Dau component, and also extends from the collision gas axis Ai along the edge of the insertion opening 25 in a direction having a downstream Dad component. In the collision region bypass flow path 34i, the portion existing in the static pressure rise region R does not have an inlet 30i and an outlet 30o.

[0074] Among the multiple collision region flow paths 33i, the first collision region flow path 33i1a, which is closest to the insertion opening 25, differs from the first collision region flow path 33i1 in the above embodiment in that it does not have an upstream flow path 35 and a downstream flow path 36. Therefore, in the collision region flow path 33i1a of this modified example, the collision region flow path 33i1a has an inlet 30i at one end and an outlet 30o at the other end. However, as mentioned above, the outlet 30o is not formed within the static pressure rise region R. On the other hand, among the multiple collision region flow paths 33i, the second collision region flow path 33i2 and the third collision region flow path 33i3, like the second collision region flow path 33i2 and the third collision region flow path 33i3 in the first embodiment, have an upstream flow path 35 and a downstream flow path 36 in addition to the collision region flow path 34i.

[0075] In this modified example, similarly to the first embodiment described above, a collision region detour flow path portion 34i is formed along the edge of the insertion opening 25 in the static pressure rise region R around the air supply pipe 40. In this collision region detour flow path portion 34i, the portion within the static pressure rise region R does not have an outlet 30o of the collision region flow path 33i. Therefore, even if the combustion gas G in the main body 21 collides with the air supply pipe 40 and the static pressure of the combustion gas G rises within the static pressure rise region R, the backflow of the combustion gas G into the collision region flow path 33i can be suppressed.

[0076] As described above, if a collision region meandering flow path 34i exists in the static pressure rise region R around the air supply pipe 40, it is not necessary to substantially cover the entire circumference of the insertion opening 25 with multiple openings surrounding the meandering flow path 34i of the flow path 33, as in the first embodiment described above. Furthermore, as long as the collision region flow path 33i has the collision region meandering flow path 34i, it may not have an upstream flow path 35 and a downstream flow path 36. Additionally, an inlet 30i and an outlet 30o may be formed in the collision region meandering flow path 34i.

[0077] In this modified example, among the multiple compensation flow paths 32, the inlet 30i of a portion of the compensation flow paths 32 is formed at the end near the insertion opening 25 in the cylindrical axial direction Da. Furthermore, in this modified example, the inlet 30i of another portion of the compensation flow paths 32c is formed at the end away from the insertion opening 25 in the cylindrical axial direction Da. That is, the inlet 30i of each of the compensation flow paths 32 may not be formed at the end near the insertion opening 25 in the cylindrical axial direction Da.

[0078] "Second variation of the burner canister"

[0079] refer to Figure 7 A second variation of the combustion cylinder in the first embodiment will be described.

[0080] The burner cartridge in this modified example is also a burner cartridge 20b, similar to the burner cartridge in the first embodiment described above. The burner cartridge 20b in this modified example differs from the burner cartridge 20 in the first embodiment in the shape of its multiple meandering flow paths, but the other structures are the same.

[0081] In the above-described embodiment, the detour flow path 34 is arc-shaped, consistent with the shape of the circular insertion opening 25. On the other hand, in this modified example, the detour flow path 34b is formed by joining multiple straight sections, rather than being arc-shaped. Even with this shape, as long as the detour flow path 34b extends along the edge of the insertion opening 25, it achieves substantially the same effect as the detour flow path 34 in the above-described embodiment. However, since the pressure loss of compressed air A is smaller in the arc-shaped detour flow path 34 compared to this shape, it is preferable to have an arc-shaped detour flow path 34 when manufacturing it is not difficult.

[0082] Other variations

[0083] In the above embodiments and variations, the fuel rotation angle θf and the collision axis angle θi are approximately the same. However, due to the ratio of the fuel injection flow rate to the primary combustion air injection flow rate A1 and the rotation angle of the primary combustion air A1, the collision axis angle θi sometimes varies within the range of fuel rotation angle θf ± 15° relative to the fuel rotation angle θf. Therefore, the angle of the collision gas axis Ai relative to the cylinder axis Ac, i.e., the collision axis angle θi, is not limited to 40°, but can be any angle within the range of 40° ± 15°.

[0084] In some burners, the combustion gas G does not rotate around the cylinder axis Ac within the combustion space. In this case, the colliding gas axis Ai extends towards the cylinder axis Da. That is, the angle of the colliding gas axis Ai relative to the cylinder axis Ac, i.e., the colliding axis angle θi, can be 0°.

[0085] In the above embodiments and variations, the air supply pipe 40 is installed on the main body 21 of the combustion chamber 20. However, when the length of the large-diameter main body 13c of the inner cylinder 13 in the cylinder axis direction Da is relatively long, the air supply pipe 40 is sometimes also installed on the large-diameter main body 13c. In this case, the main body of the combustion chamber equipped with the air supply pipe 40 becomes the large-diameter main body 13c of the inner cylinder 13.

[0086] In the above embodiments and variations, fuel F is primarily BFG. However, fuel F can also be other fuels. Specifically, fuel F can be natural gas or COG, etc.

[0087] Postscript

[0088] The burner cylinder in the above-described embodiments and variations can be understood as follows.

[0089] (1) The burner cylinder in the first embodiment has the following features:

[0090] The main body 21, cylindrical in shape around a cylindrical axis Ac, defines a combustion space S around which combustion gas G flows from the upstream side Dau to the downstream side Dad in the axial direction Da extending from the cylindrical axis Ac; and an air supply pipe 40 is installed on the main body 21. The cylindrical main body 21 has the following components: an inner circumferential surface 23i facing the combustion gas G; an outer circumferential surface 22o facing the side opposite to the inner circumferential surface 23i; an insertion opening 25 extending from the outer circumferential surface 22o to the inner circumferential surface 23i; and a plurality of cooling flow paths 30 extending between the inner circumferential surface 23i and the outer circumferential surface 22o in a direction along the inner circumferential surface 23i, enabling the cooling medium to flow internally. A portion of the air supply pipe 40 is inserted into the inner circumferential side of the main body 21 from the insertion opening 25 and protrudes towards the inner circumferential side of the main body 21. The plurality of cooling flow paths 30 each have an inlet 30i capable of introducing cooling medium into its interior and an outlet 30o capable of discharging the cooling medium flowing within its interior. Each of the plurality of cooling flow paths 30 has a plurality of open surrounding flow paths 33 as part of the plurality of cooling flow paths 30. Each of the plurality of open surrounding flow paths 33 has a meandering flow path portion 34 extending along the edge of the insertion opening 25. At least one of the plurality of open surrounding flow paths 33 constitutes a collision region flow path 33i. The collision region flow path 33i has a collision region meandering flow path portion 34i as the meandering flow path portion 34. The collision region meandering flow path 34i intersects with a collision gas axis Ai extending in a radial direction relative to the central axis At of the air supply pipe 40 and in the flow direction of the combustion gas G flowing toward the central axis At. The collision gas axis Ai extends from the edge of the insertion opening 25 in a direction having the upstream Dau component, and from the edge of the insertion opening 25 in a direction having the downstream Dad component. In the collision region meandering flow path 34i, the intersection position 34p with the collision gas axis Ai is located further upstream than the central axis At. In the collision region meandering flow path 34i, within a predetermined angle (θu+θd) centered on the collision gas axis Ai around the central axis At, the outlet 30o, which opens onto the inner circumferential surface 23i, is not formed.

[0091] When the combustion gas G flowing within the main body 21 collides with the air supply pipe 40, its dynamic pressure decreases and its static pressure increases. The static pressure rise region R, where the static pressure of the combustion gas G increases due to its collision with the air supply pipe 40, is within a predetermined upstream angle θu from the colliding gas axis Ai towards the upstream side Dau, and within a predetermined downstream angle θd from the colliding gas axis Ai towards the downstream side Dad. Because this method has multiple openings surrounding the flow path 33 with a meandering flow path section 34 extending along the edge of the insertion opening 25, the edge of the insertion opening 25 can be cooled by the cooling medium flowing through the meandering flow path section 34. However, in this method, the portion within the static pressure rise region R of the collision region meandering flow path section 34i does not form an outlet 30o of the collision region flow path 33i having the collision region meandering flow path section 34i. Therefore, in this method, even if the combustion gas G in the main body 21 collides with the air supply pipe 40 and the static pressure of the combustion gas G rises in the static pressure rising region R, it is possible to suppress the backflow of the combustion gas G into the collision region flow path 33i.

[0092] (2) Regarding the burner cartridge in the second method

[0093] According to the burner cartridge in the first method, wherein...

[0094] The specified angle (θu+θd) is 60°±20°.

[0095] The specified angle (θu+θd) varies depending on the flow velocity of the combustion gas G immediately preceding the collision with the air supply pipe 40. Therefore, the specified angle (θu+θd) is 60°±20°.

[0096] (3) Regarding the burner cartridge in the third method

[0097] According to the burner cartridge in the first or second method, wherein...

[0098] The collision gas axis Ai is at an angle θi of 40°±15° relative to the cylinder axis Ac.

[0099] Within the combustion space S on the inner circumference of the main body 21, when the fuel F rotates around the cylinder axis Ac, the angle of the colliding gas axis Ai relative to the cylinder axis Ac, i.e., the colliding axis angle θi, is approximately 40°. However, due to the ratio of the injection flow rate of fuel F to the injection flow rate of primary combustion air A1, and the rotation angle of primary combustion air A1, this colliding axis angle θi will vary to some extent. Therefore, the colliding axis angle θi is not limited to 40°; any angle within the range of 40° ± 15° is acceptable.

[0100] (4) Regarding the burner cartridge in the fourth method

[0101] The burner cartridge is provided according to any one of the first to the third methods, wherein...

[0102] The plurality of openings surrounding the flow path 33 have an upstream flow path 35 extending from the end of the upstream side Dau of the meandering flow path 34 toward the upstream side Dau in the direction Da of the cylinder axis. The upstream flow path 35 has one of the inlet 30i and the outlet 30o.

[0103] (5) Regarding the burner cartridge in the fifth method

[0104] The burner cartridge is provided according to any one of the first to fourth methods, wherein...

[0105] The plurality of openings surrounding the flow path 33 have a downstream flow path 36 extending from the end of the downstream side Dad of the meandering flow path 34 toward the downstream side Da in the direction of the cylinder axis.

[0106] (6) Regarding the burner cartridge in the sixth method

[0107] The burner cartridge is provided according to any one of the first to the third methods, wherein...

[0108] The plurality of openings surrounding the flow path 33 have: an upstream flow path portion 35 extending from the end of the upstream side Dau of the meandering flow path portion 34 toward the upstream side Dau in the cylindrical axis direction Da; and a downstream flow path portion 36 extending from the end of the downstream side Dad of the meandering flow path portion 34 toward the downstream side Da in the cylindrical axis direction Da. One of the inlet 30i and the outlet 30o is formed on the upstream flow path portion 35, and the other of the inlet 30i and the outlet 30o is formed on the downstream flow path portion 36. Neither the inlet 30i nor the outlet 30o is formed on the meandering flow path portion 34.

[0109] In this configuration, no outlet 30o with an opening surrounding the flow path 33 is formed on the detour flow path portion 34 extending along the edge of the insertion opening 25. Therefore, in this configuration, the backflow of combustion gas G in the detour flow path portion 34 can be suppressed.

[0110] (7) Regarding the burner tube in the seventh method

[0111] The burner cartridge is provided according to any one of the first to sixth methods, wherein...

[0112] The plurality of cooling flow paths 30 have a compensating flow path 32 extending toward the cylinder axis direction Da as part of the plurality of cooling flow paths 30. The compensating flow path 32 exists in the circumferential Dc region relative to the cylinder axis Ac of at least one of the plurality of open surrounding flow paths 33, where the detour flow path portion 34 of the open surrounding flow path 33 exists, and is located at the same position in the cylinder axis direction Da relative to a part of the detour flow path portion 34 of the at least one open surrounding flow path 33.

[0113] Sometimes, a detour flow path 34, which surrounds a flow path 33 with an opening, is provided on the side of the circumferential direction Dc relative to the cylinder axis Ac, away from the insertion opening 25, as one of a plurality of cooling flow paths 30, extending linearly in the cylinder axis direction Da. In this case, there is a shorter portion and a longer portion between the normal flow path 31 and the detour flow path 34 in the circumferential direction Dc. Among the plurality of compensation flow paths 32, a portion of the compensation flow path 32 is located between the normal flow path 31 and the detour flow path 34 in the circumferential direction Dc, at the longer portion. Therefore, in this configuration, the longer portion between the normal flow path 31 and the detour flow path 34 in the circumferential direction Dc can be cooled by the cooling medium flowing in the compensation flow path 32.

[0114] (8) Regarding the burner cartridge in the eighth method

[0115] According to the burner cartridge in the seventh embodiment, wherein...

[0116] The inlet 30i of the compensation flow path 32 is formed at one end of the two ends of the compensation flow path 32 along the cylindrical axis direction Da, near the side of the insertion opening 25.

[0117] In this method, the area near the insertion opening 25 can be actively cooled by the cooling medium flowing into the compensation flow path 32 from the inlet 30i.

[0118] (9) Regarding the burner cartridge in the ninth method

[0119] The burner cartridge is provided according to any one of the first to eighth methods, wherein...

[0120] The plurality of opening-encircling flow paths 33 have a plurality of collision region flow paths 33i. Among the plurality of collision region flow paths 33i, the collision region detour flow path portion 34i of the first collision region flow path 33i1 is closer to the insertion opening 25 than the collision region detour flow path portions 34i of the other collision region flow paths 33i besides the first collision region flow path 33i1, and the flow path cross-sectional area of ​​the first collision region flow path 33i1 is larger than the flow path cross-sectional area of ​​the other collision region flow paths 33i.

[0121] In this method, since the cross-sectional area of ​​the flow path 33i1 in the first collision region is larger than that in the other collision region flow paths 33i, the flow rate of the cooling medium flowing in the first collision region flow path 33i1 is greater than that flowing in the other collision region flow paths 33i. Therefore, in this method, the aforementioned static pressure rise region R and the vicinity of the insertion opening 25 can be actively cooled.

[0122] (10) Regarding the burner cartridge in the tenth method

[0123] The burner cartridge is provided according to any one of the first to ninth methods, wherein...

[0124] In the plurality of cooling flow paths 30, the outlets 30o of two adjacent cooling flow paths 30 on the circumferential direction Dc relative to the cylinder axis Ac are not at the same position on the cylinder axis direction Da.

[0125] In the cooling flow path 30, the temperature of the cooling medium flowing near the outlet 30o is higher than the temperature of the cooling medium flowing near the inlet 30i. Therefore, the cooling capacity near the outlet 30o is lower than the cooling capacity near the inlet 30i. Consequently, when the outlet 30o positions of two adjacent cooling flow paths 30 in the circumferential direction Dc are the same in the cylinder axial direction Da, the cooling capacity of the portions of the two cooling flow paths 30 near their respective outlets 30o becomes very low. In this embodiment, since the outlet 30o positions of two adjacent cooling flow paths 30 in the circumferential direction Dc are different in the cylinder axial direction Da, it is possible to prevent the cooling capacity of the portions of the two cooling flow paths 30 near their respective outlets 30o from becoming very low.

[0126] The burners in the above-described embodiments and variations can be understood as follows.

[0127] (11) Regarding the burner in the eleventh method, it comprises:

[0128] The burner cartridge of any one of the first to tenth embodiments; and the burner 14, disposed upstream of the insertion opening 25 on the Dau side, capable of injecting fuel F into the combustion space S. The burner 14 includes: a burner frame 15 having an annular fuel outlet 14j centered on the cartridge axis Ac; and a swirler 16 disposed within the burner frame 15, capable of causing the fuel F ejected from the fuel outlet 14j to rotate around the cartridge axis Ac. The swirler 16 is configured such that the angle of the fuel F ejected from the fuel outlet 14j relative to the cartridge axis Ac is a predetermined fuel rotation angle θf. The angle of the colliding gas axis Ai relative to the cartridge axis Ac is within the range of the fuel rotation angle θf ± 15°.

[0129] Within the combustion space S on the inner circumference of the main body 21, when the fuel F rotates around the cylinder axis Ac, the angle of the colliding gas axis Ai relative to the cylinder axis Ac, i.e., the colliding axis angle θi, is approximately equal to the fuel rotation angle θf. However, due to the ratio of the injection flow rate of fuel F to the injection flow rate of primary combustion air A1 and the rotation angle of primary combustion air A1, this colliding axis angle θi will vary to some extent. Therefore, the colliding axis angle θi does not need to be exactly the same as the fuel rotation angle θf; it only needs to be within the range of ±15° of the fuel rotation angle θf.

[0130] (12) Regarding the burner in the twelfth method

[0131] According to the burner in the eleventh embodiment, it further comprises:

[0132] An air injector 17, positioned further upstream of the insertion opening 25 on the Dau side, injects air into the combustion space S, thereby enabling the fuel F injected from the burner 14 to diffuse and burn in the combustion space S.

[0133] The gas turbines in the above-described embodiments and variations can be understood as follows.

[0134] (13) Regarding the gas turbine in the thirteenth method, it has the following features:

[0135] The burner in the eleventh or twelfth embodiment; the compressor 1, capable of supplying compressed air A into the burner; and the turbine 5, capable of being driven by the combustion gas G from the burner.

[0136] Industrial availability

[0137] In one aspect of the invention, the durability of the burner casing can be improved.

[0138] Symbol Explanation

[0139] 1-Compressor, 2-Compressor rotor, 3-Compressor housing, 4-Burner, 5-Turbine, 5i-Combustion gas inlet, 6-Turbine rotor, 7-Turbine housing, 8-Gas turbine rotor, 9-Intermediate housing, 10-Burner body, 11-Outer cylinder, 11a-Outer cylinder body, 11b-Cover, 12-Support cylinder, 12a-Air inlet opening, 13-Inner cylinder, 13a-Small diameter body, 13b-Expanded diameter body, 13c-Large diameter body, 14-Burner, 14j-Fuel injection outlet, 15-Burner frame, 15a-Burner cylinder 15b - Center cylinder, 16 - Fuel cyclone separator, 17 - Air injector, 17j - Air injection outlet, 18 - Air injection frame, 19 - Air cyclone separator, 20, 20a, 20b - Combustion cylinder (burner cylinder), 21 - Main body, 22 - Outer side plate, 22o - Outer peripheral surface, 22c - Joint surface of outer side plate 22, 22d - Long groove, 23 - Inner side plate, 23i - Inner peripheral surface, 23c - Joint surface of inner side plate 23, 25 - Insertion opening, 30 - Cooling flow path, 30i - Inlet, 30o - Outlet, 31 - Normal flow path, 32, 3 2a, 32b, 32c - Compensation flow path; 33, 33a - Opening surrounding flow path; 33i - Collision area flow path; 33n - Non-collision area flow path; 33i1, 33i1a - First collision area flow path; 33i2 - Second collision area flow path; 33i3 - Third collision area flow path; 34, 34b - Detour flow path section; 34i - Collision area detour flow path section; 34p - Intersection position; 35 - Upstream side flow path section; 36 - Downstream side flow path section; 40 - Air supply pipe; 41 - Pipe section; 41p - Main collision position; 42 - Flange section; 45 - Pipe fixing block, A-compressed air, Ao-external air, A1-primary combustion air, A2-secondary combustion air, F-fuel, G-combustion gas, S-combustion space, R-static pressure rise zone, Ar-rotation axis, Ac-cylinder axis, Ai-collision gas axis, At-pipe center axis, Da-cylinder axis direction, Dau-upstream side, Dad-downstream side, Dc-circumferential, Dc1-first circumferential side, Dc2-second circumferential side, θi-collision axis angle, θu-upstream side angle, θd-downstream side angle, θf-fuel rotation angle.

Claims

1. A burner cylinder, comprising: The main body, cylindrical in shape around a cylindrical axis, defines the periphery of a combustion space for the flow of combustion gases from the upstream side to the direction having the composition of the downstream side in the direction extending along the cylindrical axis; and An air supply pipe is installed on the main body. The following components are formed on the cylindrical main body: The inner circumferential surface faces the combustion gas. The outer peripheral surface faces the side opposite to the inner peripheral surface; An insertion opening extends from the outer peripheral surface to the inner peripheral surface; and Multiple cooling flow paths extend between the inner and outer peripheral surfaces, along the inner peripheral surface, enabling the cooling medium to flow internally. A portion of the air supply pipe is inserted from the insertion opening into the inner circumference of the body and protrudes towards the inner circumference of the body. The plurality of cooling flow paths each have an inlet for introducing cooling medium into their interior and an outlet for discharging the cooling medium flowing inside their interior. The plurality of cooling flow paths have multiple openings surrounding the flow path as part of the plurality of cooling flow paths. The plurality of openings surrounding the flow path have a meandering flow path portion extending along the edge of the insertion opening. Of the plurality of open surrounding flow paths, at least one open surrounding flow path constitutes a collision region flow path. The collision region flow path has a collision region detour flow path section as the detour flow path section. The detour flow path in the collision region intersects with the collision gas axis, which extends in the direction of combustion gas flow toward the central axis of the air supply pipe. This flow direction is radial relative to the central axis of the pipe and extends from the collision gas axis along the edge of the insertion opening in a direction having an upstream component, and also from the collision gas axis along the edge of the insertion opening in a direction having a downstream component. In the meandering flow path of the collision region, the intersection point with the axis of the colliding gas is located further upstream than the central axis of the pipe. In the meandering flow path of the collision region, within a range of a predetermined angle centered on the axis of the collision gas, the outlet with an opening on the inner circumferential surface is not formed, the predetermined angle being the angle around the central axis of the tube.

2. The burner canister according to claim 1, wherein, The specified angle is 60°±20°.

3. The burner canister according to claim 1, wherein, The collision gas axis is at an angle of 40°±15° relative to the cylinder axis.

4. The burner canister according to any one of claims 1 to 3, wherein, The plurality of openings surrounding the flow path have an upstream flow path portion extending from the upstream end of the meandering flow path portion toward the upstream side in the direction of the cylinder axis. The upstream flow path has one of the inlet and the outlet.

5. The burner canister according to any one of claims 1 to 3, wherein, The plurality of openings surrounding the flow path have a downstream flow path portion extending from the downstream end of the meandering flow path portion toward the downstream side in the direction of the cylinder axis.

6. The burner canister according to any one of claims 1 to 3, wherein, The plurality of openings surrounding the flow path have an upstream flow path portion extending from the upstream end of the meandering flow path portion toward the upstream side in the direction of the cylinder axis, and a downstream flow path portion extending from the downstream end of the meandering flow path portion toward the downstream side in the direction of the cylinder axis. One of the inlet and the outlet is formed on the upstream flow path, the other of the inlet and the outlet is formed on the downstream flow path, and neither the inlet nor the outlet is formed on the detour flow path.

7. The burner canister according to any one of claims 1 to 3, wherein, The plurality of cooling flow paths include a compensating flow path extending in the direction of the cylinder axis as part of the plurality of cooling flow paths. The compensation flow path exists in the circumferential region relative to the cylinder axis of at least one of the plurality of open surrounding flow paths, where the detour flow path portion of the open surrounding flow path exists, and the position in the cylinder axis direction is the same relative to a portion of the detour flow path portion of the at least one open surrounding flow path.

8. The burner canister according to claim 7, wherein, The inlet of the compensation flow path is formed at one end of the cylinder axis of the compensation flow path, near the insertion opening.

9. The burner canister according to any one of claims 1 to 3, wherein, The plurality of openings surrounding the flow path have a plurality of collision region flow paths. In the plurality of collision region flow paths, the collision region detour flow path portion of the first collision region flow path is closer to the insertion opening than the collision region detour flow path portions of the other collision region flow paths besides the first collision region flow path. The cross-sectional area of ​​the flow path in the first collision region is larger than the cross-sectional area of ​​the flow paths in the other collision regions.

10. The burner canister according to any one of claims 1 to 3, wherein, In the plurality of cooling flow paths, the outlets of two adjacent cooling flow paths in the circumferential direction relative to the cylinder axis are located at different positions in the direction of the cylinder axis.

11. A burner comprising: Burner canister according to any one of claims 1 to 10; and A burner, positioned upstream of the insertion opening, is capable of injecting fuel into the combustion space. The burner includes: a burner frame having a fuel injection outlet in an annular shape centered on the cylinder axis; and a swirler disposed within the burner frame, capable of causing the fuel ejected from the fuel injection outlet to rotate about the cylinder axis. The cyclone separator is configured such that the angle of the fuel ejected from the fuel injection outlet relative to the cylinder axis is a predetermined fuel rotation angle. The angle between the collision gas axis and the cylinder axis is within the range of the fuel rotation angle ±15°.

12. The burner according to claim 11, further comprising: An air injector, positioned upstream of the insertion opening, injects air into the combustion space, thereby enabling the fuel injected from the burner to diffuse and burn within the combustion space.

13. A gas turbine comprising: The burner according to claim 11 or 12; A compressor capable of supplying compressed air to the burner; and The turbine is capable of being driven by the combustion gases from the burner.

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