Gas turbine burner and gas turbine

Abstract

A gas turbine burner of at least one embodiment includes: a cylindrical member; a plurality of premixing tubes arranged circumferentially inside the cylindrical member and each forming an outlet portion of a premixing passage; and a substrate supporting the plurality of premixing tubes. The substrate has: a plurality of through holes respectively provided corresponding to the plurality of premixing tubes for allowing the premixing passage to pass through the substrate; and a plurality of inclined holes extending obliquely with respect to the axial direction of the gas turbine burner in a region different from the region where the through holes are provided.

Description

Technical Field

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

[0002] This application claims priority based on Japanese Patent Application No. 2020-169720 filed with the Japan Patent Office on October 7, 2020, and incorporates its content herein. Background Art

[0003] In a gas turbine combustor adopting a premixing method, fuel and air are mixed inside a premixing pipe forming a premixing passage to generate a premixed gas. The generated premixed gas is ejected from the premixing pipe, and the premixed gas is combusted at a position downstream of the outlet of the premixing pipe (for example, refer to Patent Document 1).

[0004] Prior Art Documents

[0005] Patent Documents

[0006] Patent Document 1: Japanese Unexamined Patent Application Publication No. 2017-180906 Summary of the Invention

[0007] Problems to be Solved by the Invention

[0008] Generally, in a gas turbine combustor, a plurality of premixing pipes are arranged circumferentially along the gas turbine combustor. Moreover, these plurality of premixing pipes are supported by a substrate on an inner cylinder of the combustor. More specifically, a plurality of through-holes through which the premixing pipes pass are formed in the substrate, and the premixing pipes respectively penetrate through the through-holes, and the end portions on the outlet side protrude more downstream of the gas turbine combustor than the substrate.

[0009] In a gas turbine combustor having such a structure, a space surrounded by the outer peripheral surfaces of a plurality of premixing pipes, the inner peripheral surface of the inner cylinder, and the downstream side surface of the substrate is formed. If the premixed gas flows backward into this space and burns, it may cause damage to the premixing pipes. Therefore, in order to prevent the premixed gas from flowing backward into this space, sometimes a plurality of air holes penetrating the substrate are provided in a region of the substrate where the premixing pipes do not pass through, and air on the upstream side of the substrate is supplied into the above space from the air holes.

[0010] In addition, in a gas turbine combustor having the above structure, a pilot conical portion of a pilot nozzle exists inside a plurality of premixing pipes arranged circumferentially. Therefore, the cross-sectional shape of the premixing pipe, which is circular near the substrate, changes in a manner that approaches a partial circular ring shape as it approaches the outlet of the premixing pipe. Therefore, if the flow of air ejected from the above air holes deviates and a region with a relatively high flow velocity and a region with a relatively low flow velocity are generated near the outlet of the premixing pipe, it is possible that the premixed gas flows backward into the region with a relatively low flow velocity and burns, causing damage to the premixing pipe.

[0011] In view of the above, an object of at least one embodiment of the present disclosure is to suppress the backflow of the premixed gas in the gas turbine combustor, thereby suppressing damage to the gas turbine combustor.

[0012] Solution to the problem

[0013] (1) The gas turbine combustor of at least one embodiment of the present disclosure includes:

[0014] A cylindrical member;

[0015] A plurality of premixing tubes arranged circumferentially inside the cylindrical member, each forming an outlet portion of the premixing passage; and

[0016] A substrate that supports the plurality of premixing tubes,

[0017] wherein,

[0018] The substrate has:

[0019] A plurality of through holes respectively provided corresponding to the plurality of premixing tubes for allowing the premixing passage to pass through the substrate; and

[0020] A plurality of inclined holes extending obliquely with respect to the axial direction of the gas turbine combustor in a region different from the region where the through holes are provided.

[0021] (2) The gas turbine of at least one embodiment of the present disclosure includes the gas turbine combustor having the structure of (1) above.

[0022] Advantageous effects of the invention

[0023] According to at least one embodiment of the present disclosure, damage to the gas turbine combustor can be suppressed. Description of the drawings

[0024] Figure 1 is a schematic structural diagram showing a gas turbine of several embodiments.

[0025] Figure 2 is a cross-sectional view showing a combustor of several embodiments.

[0026] Figure 3 is a cross-sectional view showing a main part of a combustor of several embodiments.

[0027] Figure 4 is a schematic cross-sectional view of the inner cylinder.

[0028] Figure 5 is Figure 4 a sectional view taken along the direction V of

[0029] Figure 6 is Figure 4VI direction view cross-sectional view.

[0030] Figure 7 is to Figure 6 An enlarged view of a part. Detailed implementation mode

[0031] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. Among them, the dimensions, materials, shapes, relative configurations, etc. of the constituent components described in the embodiments or shown in the drawings are not intended to limit the scope of the present invention thereto, but are merely illustrative examples.

[0032] For example, expressions indicating relative or absolute configurations such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric", or "coaxial" not only represent such configurations in a strict sense, but also represent states of relative displacement with tolerances or angles and distances to the extent that the same functions can be obtained.

[0033] For example, expressions indicating equal states of things such as "same", "equal", and "homogeneous" not only represent strictly equal states, but also represent states with tolerances or differences to the extent that the same functions can be obtained.

[0034] For example, expressions indicating shapes such as a quadrilateral shape and a cylindrical shape not only represent geometrically strict quadrilateral shapes, cylindrical shapes, etc., but also represent shapes including concavo-convex portions, chamfered portions, etc. within the range where the same effects can be obtained.

[0035] On the other hand, expressions such as "comprising", "containing", "equipped with", "including", or "having" a constituent element are not exclusive expressions that exclude the existence of other constituent elements.

[0036] (Regarding the gas turbine 1)

[0037] Figure 1 It is a schematic structural diagram showing a gas turbine of several embodiments. [[ID={31}]]

[0038] Refer to Figure 1 A gas turbine, which is an example of the application object of a gas turbine burner of several embodiments, will be described.

[0039] As Figure 1As shown, a gas turbine 1 of several embodiments includes: a compressor 2 that generates compressed air as an oxidant; a gas turbine combustor 4 that generates combustion gas using the compressed air and fuel; and a turbine 6 configured to rotate by being driven by the combustion gas. In the case of the gas turbine 1 for power generation, a generator (not shown) is connected to the turbine 6, and power is generated by the rotational energy of the turbine 6. In the following description, the gas turbine combustor 4 is also simply referred to as the combustor 4.

[0040] A specific structural example of each part in the gas turbine 1 of several embodiments will be described.

[0041] The compressor 2 of several embodiments includes: a compressor chamber 10; an air intake 12 provided on the inlet side of the compressor chamber 10 for taking in air; a rotor 8 disposed to penetrate through the compressor chamber 10 and a turbine chamber 22 described later; and various blades disposed in the compressor chamber 10. The various blades include: inlet guide vanes 14 provided on the air intake 12 side; a plurality of stationary blades 16 fixed to the compressor chamber 10 side; and a plurality of moving blades 18 planted on the rotor 8 in an alternating arrangement with respect to the stationary blades 16. It should be noted that the compressor 2 may also include other components such as an extraction chamber (not shown). In such a compressor 2, the air taken in from the air intake 12 is compressed by the plurality of stationary blades 16 and the plurality of moving blades 18, thereby becoming high-temperature and high-pressure compressed air. Then, the high-temperature and high-pressure compressed air is transported from the compressor 2 to the downstream combustor 4.

[0042] The combustor 4 of several embodiments is disposed within a housing 20. As Figure 1 shown, a plurality of the combustors 4 may be annularly arranged around the rotor 8 within the housing 20. Fuel and the compressed air generated by the compressor 2 are supplied to the combustor 4 and the fuel is burned, thereby generating combustion gas as the working fluid of the turbine 6. Then, the combustion gas is transported from the combustor 4 to the downstream turbine 6. It should be noted that a detailed structural example of the combustor 4 of several embodiments will be described later.

[0043] The turbine 6 of several embodiments includes a turbine chamber 22 and various blades disposed within the turbine chamber 22. The various blades include: a plurality of stationary blades 24 fixed to the turbine chamber 22 side; and a plurality of moving blades 26 planted on the rotor 8 in an alternating arrangement with respect to the stationary blades 24. It should be noted that the turbine 6 may also include other components such as outlet guide vanes. In the turbine 6, the combustion gas passes through the plurality of stationary blades 24 and the plurality of moving blades 26, thereby driving the rotor 8 to rotate. Thereby, the generator connected to the rotor 8 is driven.

[0044] On the downstream side of the turbine chamber 22, an exhaust chamber 30 is connected via an exhaust machine chamber 28. The combustion gas after driving the turbine 6 is discharged to the outside via the exhaust machine chamber 28 and the exhaust chamber 30.

[0045] (Regarding the burner 4)

[0046] Figure 2 It is a cross-sectional view of burners showing several embodiments. Figure 3 It is a cross-sectional view of the main part of burners showing several embodiments.

[0047] Refer to Figure 2 and Figure 3 to describe the detailed structure of the burner 4 of several embodiments.

[0048] As Figure 2 and Figure 3 shown, a plurality of burners 4 of several embodiments are arranged in a ring shape centered on the rotor 8 (refer to Figure 1 ). Each burner 4 includes: a burner liner 46 provided in the burner chamber 40 defined by the housing 20; and a pilot burner nozzle 50 and a plurality of premixed combustion nozzles (main combustion nozzles) 60, which are respectively arranged inside the burner liner 46. The burner 4 also includes an outer cylinder 45 provided on the outer peripheral side of the inner cylinder 47 of the burner liner 46 inside the housing 20. An air passage 43 for compressed air to flow is formed on the outer peripheral side of the inner cylinder 47 and the inner peripheral side of the outer cylinder 45.

[0049] It should be noted that the burner 4 may also have other components such as a bypass pipe (not shown) for bypassing the combustion gas.

[0050] For example, the burner liner 46 has: an inner cylinder 47 disposed around the pilot burner nozzle 50 and a plurality of premixed combustion nozzles 60; and a tail cylinder 48 connected to the front end of the inner cylinder 47. [[ID=३३]]

[0051] The pilot burner nozzle 50 is arranged along the central axis of the burner liner 46 (the central axis AX of the burner 4). Moreover, a plurality of premixed combustion nozzles 60 are arranged separately so as to surround the pilot burner nozzle 50.

[0052] The pilot burner nozzle 50 has: a pilot nozzle (nozzle) 54 connected to the fuel port 52; a pilot burner cylinder 57 arranged so as to surround the pilot nozzle 54; and a swirler 58 provided on the outer periphery of the pilot nozzle 54.

[0053] The premixed combustion burner 60 has: a main nozzle (nozzle) 64 connected to a fuel port 62; a main burner cylinder 66 disposed so as to surround the nozzle 64; and a swirler 70 provided on the outer periphery of the nozzle 64. It should be noted that in the following description, the main burner cylinder 66 is also simply referred to as the premixing tube 66.

[0054] That is, the burner 4 of several embodiments includes a plurality of premixing tubes 66, which are arranged circumferentially inside an inner cylinder 47 as a cylindrical member, and each forms an outlet portion 68 of a premixing passage 67.

[0055] The extending direction of the inner cylinder 47 having a cylindrical shape is the same as the extending direction of the central axis AX of the burner 4. In the following description, the extending direction of the central axis AX of the burner 4 is also simply referred to as the axial direction. Regarding the axial direction, the direction on the downstream side of the flow of the premixed gas is also simply referred to as the downstream side, and the direction on the upstream side of the flow of the premixed gas is also simply referred to as the upstream side.

[0056] In addition, in the following description, the circumferential direction centered on the central axis AX of the burner 4 is also simply referred to as the circumferential direction, and the radial direction centered on the central axis AX of the burner 4 is also simply referred to as the radial direction.

[0057] (Regarding the substrate 100)

[0058] Figure 4 It is a schematic cross-sectional view of the inner cylinder, schematically showing a cross-section along the radial direction near the substrate.

[0059] Figure 5 It is Figure 4 a sectional view taken along the V direction.

[0060] Figure 6 It is Figure 4 a sectional view taken along the VI direction.

[0061] Figure 7 It is a view obtained by magnifying a part of Figure 6 .

[0062] It should be noted that for the convenience of explanation, the description of nozzles 54, 64, etc. is omitted in Figures 4 to 7 . In addition, in Figure 7 , the outer peripheral shape of the outlet opening forming portion 69 of the extension portion 65, which is shown in the V-direction view of Figure 4 and will be described later, is represented by a double-dashed line.

[0063] The burner 4 of several embodiments includes a substrate 100 that supports a plurality of premixing tubes. The substrate 100 of several embodiments is configured to support the premixing tube 66 and the pilot burner tube 57 inside the inner cylinder 47. The substrate 100 of several embodiments is configured to support the pilot conical portion 56 formed on the downstream side of the pilot burner tube 57 in the pilot burner tube 57, but it may also be configured to support the pilot burner tube 57 at a position upstream of the pilot conical portion 56.

[0064] Specifically, a pilot burner support hole 105, which is a through hole penetrating the substrate 100, and a plurality of premixing tube support holes 106 are formed on the substrate 100 of several embodiments. That is, the substrate 100 of several embodiments has a pilot burner support hole 105 provided corresponding to the pilot burner tube 57. The substrate 100 of several embodiments has a plurality of through holes, that is, a plurality of premixing tube support holes 106, which are respectively provided corresponding to the plurality of premixing tubes 66 and through which the premixing passage 67 passes through the substrate 100.

[0065] The pilot burner tube 57 is inserted into the pilot burner support hole 105. The premixing tubes 66 are respectively inserted into the plurality of premixing tube support holes 106.

[0066] On the substrate 100 of several embodiments, the pilot burner tube 57 is joined, for example, by welding. On the substrate 100 of several embodiments, the plurality of premixing tubes 66 are respectively joined, for example, by welding.

[0067] The substrate 100 of several embodiments is fixed to the inner cylinder 47, for example, by welding the outer peripheral portion of the substrate 100 to the inner peripheral surface of the inner cylinder 47.

[0068] In several embodiments, the region of the premixing tube 66 where the outlet portion 68 of the premixing passage 67 is formed (for example, the region protruding toward the downstream side of the substrate 100) is also referred to as the extension portion 65.

[0069] On the substrate 100 of several embodiments, a plurality of air holes 110 penetrating the substrate 100 are formed in a region 100R different from the region where the pilot burner support hole 105 and the premixing tube support holes 106 are provided. A part of the plurality of air holes 110 is an inclined hole 111 extending obliquely with respect to the axial direction, and the remaining part is a parallel hole 113 extending parallel to the axial direction.

[0070] It should be noted that the air holes 110 will be described in detail later.

[0071] (Regarding the shape of the extension portion 65)

[0072] In the burner 4 of several embodiments, the pilot conical portion 56 of the pilot burner tube 57 exists inside the plurality of premixing tubes 66 arranged circumferentially. Therefore, the cross-sectional shape of the premixing tube 66, which is circular near the substrate 100, continuously changes in a manner that approaches a partial circular ring shape as it approaches the outlet of the premixing passage 67 (the outlet opening forming portion 69 of the extension portion 65). That is, the outlet opening forming portion 69 of the extension portion 65 has: a first circumferential edge 69a having an arc shape on the radially outer side; a second circumferential edge 69b having an arc shape on the radially inner side; and a pair of radial edges 69c extending radially in a manner that connects the circumferential end of the first circumferential edge 69a to the circumferential end of the second circumferential edge 69b. It should be noted that, as Figure 6 and Figure 7 shown, the corner portion 69d connecting the first circumferential edge 69a and the second circumferential edge 69b to the radial edge 69c is preferably rounded.

[0073] In the burner 4 of several embodiments, in order to ensure the area of the outlet opening of the premixing passage 67, the gaps G1 between the adjacent premixing tubes 66 in the circumferential direction, the gap G2 between the premixing tube 66 and the inner cylinder 47, and the gap G3 between the premixing tube 66 and the pilot conical portion 56 tend to become smaller toward the downstream side.

[0074] In the burner 4 having the above structure, the high-temperature and high-pressure compressed air generated by the compressor 2 is supplied into the burner chamber 40 from the chamber inlet 42 (refer to Figure 2 ), and then flows into the premixing tube 66 from the burner chamber 40 via the air passage 43. And this compressed air and the fuel supplied from the fuel port 62 are premixed in the premixing tube 66. At this time, the premixed gas mainly forms a swirling flow through the swirler 70 and flows into the burner liner 46. In addition, the compressed air and the fuel injected from the pilot burner 50 via the fuel port 52 are mixed in the burner liner 46 and ignited by a pilot flame (not shown) to generate combustion gas. At this time, a part of the combustion gas diffuses around along with the flame, and thus the premixed gas flowing into the burner liner 46 from each premixed combustion burner 60 is ignited and burned. That is, through the pilot flame formed by the pilot fuel injected from the pilot burner 50, flame stabilization for stable combustion of the premixed gas (premixed fuel) from the premixed combustion burner 60 can be achieved.

[0075] In the burner 4 having the above structure, a space S having the above gaps G1, G2, G3 is formed, that is, a space S surrounded by the outer peripheral surface 66o of the plurality of premixing tubes 66, the inner peripheral surface 471 of the inner cylinder 47, and the downstream surface 100d of the substrate 100.

[0076] If the premixed gas flows backward into this space S and burns, it may cause damage (burnout) to the premixing pipe 66. Therefore, in order to prevent the premixed gas from flowing backward into this space S, in the burner 4 of several embodiments, a plurality of air holes 110 penetrating the substrate 100 are provided in the region 100R of the substrate 100 where the premixing pipe 66 and the pilot burner cylinder 57 do not penetrate, and air on the upstream side of the substrate 100 is supplied into the space S from the air holes 110.

[0077] However, as described above, in the burner 4 having the above structure, the cross-sectional shape of the premixing pipe 66 that is circular near the substrate 100 continuously changes in such a way that it approaches a partial circular ring shape as it approaches the outlet opening forming portion 69 of the outlet of the premixing passage 67, i.e., the outlet of the extension portion 65.

[0078] Therefore, if the flow of the air (dilution air) ejected from the air holes 110 deviates and a region with a relatively high flow rate of dilution air and a region with a relatively low flow rate are generated in the downstream region of the space S, there may be a flashback where the premixed gas flows backward into the region with a relatively low flow rate and burns, damaging the premixing pipe 66.

[0079] If the dilution air can be ejected from the air holes 110 toward the region with a relatively low flow rate, the reduction in the flow rate of the dilution air in the downstream region of the space S can be suppressed. However, in the region 100R of the substrate 100 where the premixing pipe 66 and the pilot burner cylinder 57 do not penetrate, due to reasons such as the narrow gap between the premixing pipe 66 and the inner cylinder 47 or the narrow gap between the premixing pipe 66 and the pilot burner cylinder 57, there are regions where it is difficult to provide the air holes 110. That is, there are limitations in the arrangement of the air holes 110 on the substrate 100.

[0080] According to the burner 4 of several embodiments, a part of the plurality of air holes 110 are inclined holes 111 that extend obliquely with respect to the axial direction. Therefore, according to the burner 4 of several embodiments, when there are limitations in the arrangement of the air holes 110 on the substrate 100, by providing the inclined holes 111, it is possible to supply to the region where the dilution air is desired to be supplied. Thereby, the backward flow of the premixed gas into the space S surrounded by the outer peripheral surface 66o of the plurality of premixing pipes 66, the inner peripheral surface 471 of the inner cylinder 47, and the downstream surface 100d of the substrate 100 can be suppressed, and the damage to the premixing pipe caused by flashback can be suppressed. Therefore, the damage to the gas turbine burner can be suppressed.

[0081] In addition, in the gas turbine 1 equipped with the burner 4 of several embodiments, the damage to the burner 4 can be suppressed, and the reliability of the gas turbine 1 can be improved.

[0082] (Regarding the inclined hole 111)

[0083] In the burner 4 of several embodiments, a plurality of inclined holes 111 are preferably formed in a region between two circumferentially adjacent premixing tube support holes 106.

[0084] In the burner 4 of several embodiments, the plurality of inclined holes 111 preferably include a first hole 111A which is located at a position radially outside the center position C of the premixing tube support hole 106 and extends obliquely with respect to the axial direction in such a manner that it faces radially outward as it approaches the downstream end 111d from the upstream end 111u. That is, in the burner 4 of several embodiments, the central axis x1 of the first hole 111A extends obliquely with respect to the axial direction in such a manner that it faces radially outward as it moves from the upstream side to the downstream side.

[0085] As described above, in the burner 4 of several embodiments, there is a tendency for the gap G2 between the premixing tube 66 and the inner cylinder 47 to become smaller as it approaches the downstream side. Therefore, it is difficult for dilution air to flow into the gap G2 between the premixing tube 66 and the inner cylinder 47, and there is a tendency for the flow rate of the dilution air in the gap between the premixing tube and the inner cylinder to decrease.

[0086] In the burner 4 of several embodiments, the dilution air blown out from the first hole 111A flows toward the radially outer side, and thus easily flows into the gap G2 between the premixing tube 66 and the inner cylinder 47. Therefore, it is possible to suppress a decrease in the flow rate of the dilution air in the gap G2 and to suppress backflow of the premixed gas into the gap G2.

[0087] In the burner 4 of several embodiments, the first hole 111A preferably extends obliquely with respect to the axial direction in such a manner that, as it approaches the downstream end 111d from the upstream end 111u, it faces the central position side of the outlet opening 69e of the premixing tube 66 corresponding to the first hole 111A among the plurality of premixing tubes 66 in the circumferential direction. That is, in the burner 4 of several embodiments, the central axis x1 of the first hole 111A extends obliquely with respect to the axial direction in such a manner that, as it moves from the upstream side to the downstream side, it faces the central position side of the outlet opening 69e of the premixing tube 66 corresponding to the first hole 111A in the circumferential direction.

[0088] It should be noted that the premixing tube 66 corresponding to the first hole 111A refers to the premixing tube 66 that forms the gap G2 which is the supply destination of the dilution air blown out from the first hole 111A among the plurality of gaps G2 formed between the inner cylinder 47 corresponding to the plurality of premixing tubes 66 respectively.

[0089] As described above, in the burner 4 of several embodiments, there is a tendency for the gap G2 between the premixing pipe 66 and the inner cylinder 47 to become smaller toward the downstream side. Therefore, it is difficult for dilution air to flow into the gap G2 between the premixing pipe 66 and the inner cylinder 47. In particular, in the vicinity of the region G21 on the extension line of the line segment L connecting the central axis AX of the burner 4 and the center position C of each premixing pipe support hole 106 among the circumferential positions of the gap G2, the distance between the outer peripheral surface 66o of the premixing pipe 66 and the inner peripheral surface 471 of the inner cylinder 47 is the smallest, and compared with the regions other than the region G21 in the gap G2, it is farther from the region of the substrate 100 where the air holes 110 can be arranged. Therefore, in the above-mentioned region G21, compared with the regions other than the region G21 in the gap G2, there is a tendency for the flow rate of the dilution air to further decrease, and this tendency becomes significant as it moves toward the downstream side.

[0090] In the burner 4 of several embodiments, by configuring the first hole 111A to extend obliquely with respect to the axial direction in the circumferential direction as described above, it is possible to blow dilution air from the first hole 111A toward the downstream-side region in the gap G2. Thereby, it is possible to ensure the flow rate of the dilution air in the region G21 near the outlet opening 69e of the premixing pipe 66, and it is possible to suppress the backflow of the premixed gas into this region G21.

[0091] In the burner 4 of several embodiments, it is preferable to provide at least one first hole 111A with respect to one premixing pipe 66. In the burner 4 of several embodiments, regarding the first hole 111A, for example, as Figure 6 and Figure 7 shown, two (a pair) of first holes 111A can be provided with respect to one premixing pipe 66 across the premixing pipe 66. The pair of first holes 111A can also be two pairs or more.

[0092] It should be noted that the inclination directions of the pair of first holes 111A arranged across the premixing pipe 66 in the circumferential direction are opposite to each other, and preferably inclined toward the central position side of the outlet opening 69e of the premixing pipe 66.

[0093] In the burner 4 of several embodiments, when viewed from the downstream side, at least a part of the plurality of inclined holes 111 can also be arranged in the region of the substrate 100 that overlaps the outlet opening 69e of the premixing pipe 66. That is, in the burner 4 of several embodiments, for example, as Figure 7 shown, the first hole 111A can also be formed at a position where the first hole 111A is covered by the extension part 65 of the premixing pipe 66 when viewed from the downstream side.

[0094] Thus, for example, the inclined holes 111 are arranged at positions relatively close to the region where the flow rate of the dilution air, such as the gap G2 described above, tends to decrease. Therefore, the dilution air blown out from the inclined holes 111 easily flows into the region where the flow rate of the dilution air tends to decrease. As a result, it is possible to suppress the decrease in the flow rate of the dilution air in this region and to suppress the backflow of the premixed gas into this region.

[0095] In the burner 4 of several embodiments, the plurality of inclined holes 111 preferably include a second hole 111B, which is located at a position radially inward of the center position C of the premixing tube support hole 106 and extends obliquely with respect to the axial direction in such a manner that it faces radially inward as it approaches the downstream end 111d from the upstream end 111u. That is, in the burner 4 of several embodiments, the central axis x2 of the second hole 111B extends obliquely with respect to the axial direction in such a manner that it faces radially inward as it moves from the upstream side to the downstream side.

[0096] As described above, in the burner 4 of several embodiments, the gap G3 between the premixing tube 66 and the pilot conical portion 56 tends to become smaller as it moves toward the downstream side. Therefore, it is difficult for the dilution air to flow into the gap G3 between the premixing tube 66 and the pilot conical portion 56, and there is a tendency for the flow rate of the dilution air in this gap G3 to decrease.

[0097] In the burner 4 of several embodiments, the dilution air blown out from the second hole 111B flows radially inward, so it easily flows into the gap G3 between the premixing tube 66 and the pilot conical portion 56. Therefore, it is possible to suppress the decrease in the flow rate of the dilution air in this gap G3 and to suppress the backflow of the premixed gas into this gap G3.

[0098] In the burner 4 of several embodiments, the second hole 111B preferably extends obliquely with respect to the axial direction in such a manner that as it approaches the downstream end 111d from the upstream end 111u, it faces the central position side of the outlet opening 69e of the premixing tube 66 corresponding to the second hole 111B among the plurality of premixing tubes 66 in the circumferential direction. That is, in the burner 4 of several embodiments, the central axis x2 of the second hole 111B extends obliquely with respect to the axial direction in such a manner that as it moves from the upstream side to the downstream side, it faces the central position side of the outlet opening 69e of the premixing tube 66 corresponding to the second hole 111B in the circumferential direction.

[0099] It should be noted that the premixing tube 66 corresponding to the second hole 111B refers to the premixing tube 66 that forms the gap G3 which is the supply destination of the dilution air blown out from the second hole 111B among the plurality of gaps G3 formed between the pilot conical portion 56 corresponding to each of the plurality of premixing tubes 66.

[0100] As described above, in the burner 4 of several embodiments, the gap G3 between the premixing tube 66 and the pilot cone portion 56 tends to become smaller toward the downstream side. Therefore, it is difficult for dilution air to flow into the gap G3 between the premixing tube 66 and the pilot cone portion 56. In particular, in the circumferential position in the gap G3, in the region G31 near the line segment L connecting the central axis AX of the burner 4 and the center position C of each premixing tube support hole 106, the distance between the outer peripheral surface 66o of the premixing tube 66 and the outer peripheral surface 561 of the pilot cone portion 56 is the smallest, and compared with the region other than the region G31 in the gap G3, it is farther from the region in the substrate 100 where the air holes 110 can be arranged. Therefore, in the above-mentioned region G31, compared with the region other than the region G31 in the gap G3, the flow velocity of the dilution air tends to be further reduced, and this tendency becomes more significant toward the downstream side.

[0101] In the burner 4 of several embodiments, by configuring the second hole 111B to extend obliquely with respect to the axial direction in the circumferential direction as described above, it is possible to blow dilution air from the second hole 111B toward the downstream side region in the gap G3. Thereby, it is possible to ensure the flow velocity of the dilution air in the region G31 near the outlet opening 69e of the premixing tube 66, and it is possible to suppress the backflow of the premixed gas into the region G31.

[0102] In the burner 4 of several embodiments, at least one second hole 111B is preferably provided with respect to one premixing tube 66. In the burner 4 of several embodiments, regarding the second hole 111B, for example, as Figure 6 and Figure 7 shown, two (a pair) of second holes 111B can be provided with respect to one premixing tube 66 with the premixing tube 66 interposed therebetween. The pair of second holes 111B can also be two pairs or more.

[0103] It should be noted that the inclination directions of the pair of second holes 111B arranged with the premixing tube 66 interposed therebetween are opposite to each other in the circumferential direction, and preferably inclined toward the central position side of the outlet opening 69e of the premixing tube 66.

[0104] In the burner 4 of several embodiments, for example, by comparing Figure 5 and Figure 6 it can be clearly seen that the second hole 111B can also be formed at a position where the second hole 111B is covered by the pilot cone portion 56 when viewed from the downstream side.

[0105] The present disclosure is not limited to the above embodiments, and may also include a mode obtained by modifying the above embodiments, and a mode obtained by appropriately combining these modes.

[0106] The content described in each of the above embodiments can be understood as follows, for example.

[0107] (1) The gas turbine combustor 4 of at least one embodiment of the present disclosure includes: a cylindrical member (inner cylinder 47); a plurality of premixing tubes 66 arranged circumferentially inside the cylindrical member (inner cylinder 47) and each forming an outlet portion 68 of a premixing passage 67; and a substrate 100 that supports the plurality of premixing tubes 66. The substrate 100 has: a plurality of through holes (premixing tube support holes 106) respectively provided corresponding to the plurality of premixing tubes 66 for allowing the premixing passage 67 to pass through the substrate 100; and a plurality of inclined holes 111 extending obliquely with respect to the axial direction of the gas turbine combustor 4 in a region 100R different from the region where the through holes (premixing tube support holes 106) are provided.

[0108] According to the structure of the above (1), when there are restrictions on the arrangement of the air holes 110 on the substrate 100, by providing the inclined holes 111, it is possible to supply to the region where dilution air is desired to be supplied. As a result, it is possible to suppress the backflow of the premixed gas into the space S surrounded by the outer peripheral surface 66o of the plurality of premixing tubes 66, the inner peripheral surface 471 of the inner cylinder 47, and the downstream surface 100d of the substrate 100, and it is possible to suppress damage to the premixing tubes 66 caused by flashback, and thus it is possible to suppress damage to the gas turbine combustor 4.

[0109] (2) In several embodiments, based on the structure of the above (1), it may be that the plurality of inclined holes 111 include a first hole 111A that is located at a position radially outside the center position C of the plurality of through holes (premixing tube support holes 106) and extends obliquely with respect to the axial direction in a manner that faces radially outside as it approaches the downstream end 111d from the upstream end 111u.

[0110] According to the structure of the above (2), the dilution air blown out from the first hole 111A flows toward the radially outside, so it is easy to flow into the gap G2 between the premixing tube 66 and the inner cylinder 47. Therefore, it is possible to suppress a decrease in the flow rate of the dilution air in the gap G2 and suppress the backflow of the premixed gas into the gap G2.

[0111] (3) In several embodiments, based on the structure of the above (2), it may be that the first hole 111A extends obliquely with respect to the axial direction in such a manner that as it approaches the downstream end 111d from the upstream end 111u, in the circumferential direction of the combustor 4, it faces the central position side of the outlet opening 69e of the premixing tube 66 corresponding to the first hole 111A among the plurality of premixing tubes 66.

[0112] According to the structure of (3) above, dilution air can be blown out from the first hole 111A toward the smaller gap G2 between the outer peripheral surface 66o of the premixing tube 66 and the inner peripheral surface 471 of the inner cylinder 47. Thereby, the flow rate of the dilution air in this gap G2 can be ensured, and the backflow of the premixed gas into this gap G2 can be suppressed.

[0113] (4) In several embodiments, based on any of the structures in (1) to (3) above, it may be that the plurality of inclined holes 111 include a second hole 111B, which is located at a position radially inward of the central position C of the plurality of through holes (premixing tube support holes 106), and extends obliquely with respect to the axial direction in such a manner that it faces radially inward as it approaches the downstream end 111d from the upstream end 111u.

[0114] According to the structure of (4) above, the dilution air blown out from the second hole 111B flows radially inward, so it is easy to flow into the gap G3 between the premixing tube 66 and the pilot conical portion 56. Therefore, the reduction in the flow rate of the dilution air in this gap G3 can be suppressed, and the backflow of the premixed gas into this gap G3 can be suppressed.

[0115] (5) In several embodiments, based on the structure of (4) above, it may be that the second hole 111B extends obliquely with respect to the axial direction in such a manner that: as it approaches the downstream end 111d from the upstream end 111u, in the circumferential direction of the burner 4, it faces the central position side of the outlet opening 69e of the premixing tube 66 corresponding to the second hole 111B among the plurality of premixing tubes 66.

[0116] According to the structure of (5) above, dilution air can be blown out from the second hole 111B toward the smaller gap G3 between the outer peripheral surface 66o of the premixing tube 66 and the outer peripheral surface 561 of the pilot conical portion 56. Thereby, the flow rate of the dilution air in this gap G3 can be ensured, and the backflow of the premixed gas into this gap G3 can be suppressed.

[0117] (6) In several embodiments, based on any of the structures in (1) to (5) above, it may be that when viewed from the downstream side, at least a part of the plurality of inclined holes 111 are arranged in a region of the substrate 100 that overlaps with the outlet opening 69e of the premixing tube 66.

[0118] According to the structure of (6) above, since the inclined holes 111 are arranged at a position relatively close to the region where the flow rate of the dilution air tends to decrease, the dilution air blown out from the inclined holes 111 is likely to flow into the region where the flow rate of the dilution air tends to decrease. Therefore, the reduction in the flow rate of the dilution air in this region can be suppressed, and the backflow of the premixed gas into this region can be suppressed.

[0119] (7) The gas turbine 1 of at least one embodiment of the present disclosure includes the gas turbine burner 4 having any one of the structures (1) to (6) described above.

[0120] According to the structure described in (7) above, damage to the gas turbine burner 4 can be suppressed, and the reliability of the gas turbine 1 can be improved.

[0121] Explanation of reference numerals:

[0122] 1... Gas turbine;

[0123] 4... Gas turbine burner (burner);

[0124] 46... Burner liner;

[0125] 47... Inner cylinder;

[0126] 56... Pilot conical part;

[0127] 57... Pilot burner tube;

[0128] 60... Premixed combustion burner (main combustion burner);

[0129] 65... Extension part;

[0130] 66... Main burner tube (premixing tube);

[0131] 67... Premixing passage;

[0132] 68... Outlet part;

[0133] 69... Outlet opening forming part;

[0134] 69e... Outlet opening;

[0135] 100... Substrate;

[0136] 106... Premixing tube support hole;

[0137] 110... Air hole;

[0138] 111... Tapered hole;

[0139] 111A... First hole;

[0140] 111B... Second hole.

Claims

1. A gas turbine combustor, comprising: a cylindrical member; a plurality of premixing tubes arranged circumferentially inside the cylindrical member, each forming an outlet portion of a premixing passage; and a substrate that supports the plurality of premixing tubes, wherein the substrate has: a plurality of through-holes respectively provided corresponding to the plurality of premixing tubes for allowing the premixing passage to pass through the substrate; and a plurality of inclined holes extending obliquely with respect to the axial direction of the gas turbine combustor in a region different from the region where the through-holes are provided, the plurality of inclined holes include a first hole located at a position radially outside the center position of the plurality of through-holes and extending obliquely with respect to the axial direction in a manner of facing radially outside as approaching the downstream end from the upstream end, the downstream end of the first hole opens in a region of the substrate that is sandwiched between the inner circumferential surface of the cylindrical member and the outer circumferential surface of the premixing tube in the radial direction of the gas turbine combustor.

2. The gas turbine combustor according to claim 1, wherein the substrate includes a plurality of parallel holes parallel to the axial direction, the first hole is located in the circumferential direction at a position closer to the center position of the through-holes than a row of parallel holes linearly arranged along the radial direction among the plurality of parallel holes.

3. A gas turbine combustor, comprising: a cylindrical member; a plurality of premixing tubes arranged circumferentially inside the cylindrical member, each forming an outlet portion of a premixing passage; and a substrate that supports the plurality of premixing tubes, wherein the substrate has: a plurality of through-holes respectively provided corresponding to the plurality of premixing tubes for allowing the premixing passage to pass through the substrate; and a plurality of inclined holes extending obliquely with respect to the axial direction of the gas turbine combustor in a region different from the region where the through-holes are provided, the plurality of inclined holes include a first hole located at a position radially outside the center position of the plurality of through-holes and extending obliquely with respect to the axial direction in a manner of facing radially outside as approaching the downstream end from the upstream end, the first hole extends obliquely with respect to the axial direction in such a manner that as approaching the downstream end from the upstream end, in the circumferential direction of the gas turbine combustor, it faces the central position side of the outlet opening of the premixing tube corresponding to the first hole among the plurality of premixing tubes.

4. The gas turbine combustor according to any one of claims 1 to 3, wherein the plurality of inclined holes include a second hole located at a position radially inside the center position of the plurality of through-holes and extending obliquely with respect to the axial direction in a manner of facing radially inside as approaching the downstream end from the upstream end.

5. A gas turbine combustor, comprising: a cylindrical member; a plurality of premixing tubes arranged circumferentially inside the cylindrical member, each forming an outlet portion of a premixing passage; and a substrate that supports the plurality of premixing tubes, wherein the substrate has: a plurality of through-holes respectively provided corresponding to the plurality of premixing tubes for allowing the premixing passage to pass through the substrate; and A plurality of inclined holes that extend obliquely with respect to the axial direction of the gas turbine burner in a region different from the region where the through holes are provided. The plurality of inclined holes include second holes that are located at a position radially inward of the central position of the plurality of through holes and extend obliquely with respect to the axial direction in such a manner that they face radially inward as they approach the downstream end from the upstream end. The second holes extend obliquely with respect to the axial direction in such a manner that, as they approach the downstream end from the upstream end, they face the central position side of the outlet opening of the premixing tube corresponding to the second holes among the plurality of premixing tubes in the circumferential direction of the gas turbine burner.

6. A gas turbine burner comprising: A cylindrical member; A plurality of premixing tubes arranged circumferentially inside the cylindrical member and respectively forming outlet portions of premixing passages; and A substrate that supports the plurality of premixing tubes, wherein the substrate has: A plurality of through holes respectively provided corresponding to the plurality of premixing tubes and allowing the premixing passages to pass through the substrate; and A plurality of inclined holes that extend obliquely with respect to the axial direction of the gas turbine burner in a region different from the region where the through holes are provided, When viewed from the downstream side, at least a part of the plurality of inclined holes are arranged in a region of the substrate that overlaps with the outlet openings of the premixing tubes.

7. A gas turbine, wherein the gas turbine includes the gas turbine burner according to any one of claims 1 to 6.

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