Burner assembly, gas turbine combustor, and gas turbine

Abstract

The invention provides a burner assembly, a gas turbine combustor, and a gas turbine. The burner assembly is provided with a plurality of burners for mixing fuel and air, and each of the plurality of burners includes: at least one fuel nozzle for injecting the fuel; and a mixing flow path into which the fuel injected from the at least one fuel nozzle and the air flow, the at least one fuel nozzle each including a protruding portion protruding further upstream than an inlet of the mixing flow path in a flow direction of the air, and the at least one fuel nozzle each including at least one fuel injection hole formed in a side surface of the protruding portion, the top surface of the protruding portion includes a convex curved surface.

Description

[0001] This invention is a divisional application of the invention patent with application number 202080097048.2. The application date of the parent case is July 10, 2020, and the invention name of the parent case is "burner assembly, gas turbine burner and gas turbine". Technical Field

[0002] The present invention relates to a burner assembly and a gas turbine combustor. Background Art

[0003] As a technology for achieving flashback resistance and reducing NOx for fuels with a high risk of flashback (for example, hydrogen), there is a technology for forming a plurality of independent short flames using a burner assembly (cluster burner).

[0004] In this technology, a plurality of mixing flow paths for mixing fuel and air are arranged to reduce the scale of fuel mixing, thereby achieving high mixing performance even if the swirl flow is not actively used in mixing the fuel and air.

[0005] Patent Document 1 discloses a burner assembly for achieving low NOx and suppressing flashback. Each burner of the burner assembly includes a fuel nozzle and a mixing flow path for fuel and air to flow in, and the fuel nozzle includes a protrusion that protrudes upstream from the inlet of the mixing flow path in the flow direction of the air. In addition, a fuel injection hole is formed on the side of the protrusion, and the fuel injected from the fuel injection hole flows into the inlet of the mixing flow path together with the air, so that the fuel and the air are mixed.

[0006] Patent Document 1 states that by injecting fuel from a protrusion that protrudes upstream of the inlet of the mixing flow path in the direction of air flow, fuel and air can be effectively mixed, thereby suppressing the deviation of the fuel concentration in the mixing flow path and achieving low NOx. In addition, it is described that since air flows into a position upstream of the inlet of the mixing flow path and downstream of the fuel injection hole, the high concentration of fuel near the flow path wall on the downstream side of the fuel injection hole is suppressed, thereby suppressing flashback.

[0007] Prior Art Literature

[0008] Patent Literature

[0009] Patent Document 1: Japanese Patent Application Publication No. 2019-168198 Summary of the invention

[0010] Problems to be solved by the invention

[0011] The burner assembly described in Patent Document 1 has room for further improvement from the viewpoint of suppressing flashback.

[0012] In view of the above circumstances, an object of the present invention is to provide a burner assembly and a gas turbine combustor capable of suppressing flashback.

[0013] Solutions to Solve Problems

[0014] In order to achieve the above-mentioned object, the burner assembly of the present invention is a burner assembly having a plurality of burners for mixing fuel and air, wherein:

[0015] The plurality of burners respectively include:

[0016] at least one fuel nozzle for injecting the fuel; and

[0017] a mixing flow path into which the fuel and air injected from the at least one fuel nozzle flow,

[0018] The at least one fuel nozzle includes a protrusion that protrudes upstream of an inlet of the mixing flow path in the flow direction of the air.

[0019] The at least one fuel nozzle includes at least one fuel injection hole formed on a side surface of the protrusion,

[0020] The top surface of the protrusion includes a convex curved surface.

[0021] Effects of the Invention

[0022] According to the present invention, a burner assembly and a gas turbine combustor capable of suppressing flashback are provided. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 1 is a schematic configuration diagram showing a gas turbine 100 according to an embodiment.

[0024] Figure 2 It is a cross-sectional view showing the vicinity of the combustor 4 .

[0025] Figure 3 This is a partial schematic perspective view showing a part of the burner assembly 32 ( 32A) according to one embodiment.

[0026] Figure 4 This is a schematic diagram of a portion of the burner assembly 32 (32A) viewed from the upstream side in the air flow direction along the central axis L ( Figure 2 An example of a view in the A direction.

[0027] Figure 5 It is shown Figure 4 Schematic diagram of a portion of the BB section.

[0028] Figure 6 It is shown Figure 4Schematic diagram of a portion of the CC section.

[0029] Figure 7 This is a schematic cross-sectional view showing a portion of a burner assembly 032 of a comparative example.

[0030] Figure 8 It is shown Figure 7 FIG. 5 is a graph showing the distribution of the flow velocity (axial flow velocity) in the direction along the central axis O in the region S2 .

[0031] Fig. 9 It is shown Figure 5 Graph showing the distribution of flow velocity in the direction along the central axis O in region S1.

[0032] Fig.10 This is a partial schematic perspective view showing a part of the burner assembly 32 ( 32B) according to another embodiment.

[0033] Fig.11 This is a schematic diagram of a portion of the burner assembly 32 (32B) viewed from the upstream side in the air flow direction along the central axis L ( Figure 2 An example of a view in the A direction.

[0034] Fig.12 It is shown Fig.11 Schematic diagram of a portion of the CC section.

[0035] Fig.13 It is shown Fig.11 Schematic diagram of a portion of the FF cross section.

[0036] Fig.14 The burner assembly 32 (32A) is shown as follows: Figure 4 Diagram of the flow of fuel and air in the CC section.

[0037] Fig.15 The burner assembly 32 (32A) is shown as follows: Fig.14 Graph showing the distribution of flow velocity in the direction along the central axis O in region S4.

[0038] Fig.16 The burner assembly 32 (32B) is shown Fig.12 Graph showing the distribution of flow velocity in the direction along the central axis O in region S3.

[0039] Description of reference numerals:

[0040] 2... compressor; 4... burner; 6... turbine; 8... rotor; 10... compressor chamber; 12, 48... inlet; 14... inlet guide vanes; 16, 24... stationary vanes; 18, 26... moving vanes; 20... casing; 22... turbine chamber; 25... combustion cylinder; 28... exhaust chamber; 30... exhaust chamber; 32 (32A, 32B)... burner assembly; 34... cylindrical member; 35... support portion; 36... air flow path; 40... chamber; 42... burner; 42a ...first burner; 42b...second burner; 43...fuel nozzle; 43a...first fuel nozzle; 43b...second fuel nozzle; 44...side; 45...edge; 46, 46a, 46b...mixing flow path; 50...protrusion; 53...fuel injection hole; 54...top surface; 55...flow path wall; 56...convex curved surface; 58, 58ab...partition wall; 59...end surface; 60...convex curve; 61...end; 62...concave curve; 63...wall surface; 100...gas turbine. DETAILED DESCRIPTION

[0041] Hereinafter, several embodiments of the present invention will be described with reference to the drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of the components described as embodiments or shown in the drawings are not intended to limit the scope of the present invention and are merely illustrative examples.

[0042] For example, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" that indicate relative or absolute configurations not only indicate such a configuration strictly, but also indicate a state of relative displacement at an angle or distance with a tolerance or a degree that can achieve the same function.

[0043] For example, expressions such as “same”, “equal”, and “homogeneous” indicating a state in which things are equal not only indicate a state in which things are strictly equal, but also indicate a state in which there is a tolerance or a difference to the extent that the same function can be obtained.

[0044] For example, expressions indicating shapes such as a quadrilateral and a cylindrical shape not only indicate shapes such as a quadrilateral and a cylindrical shape in a strict geometric sense, but also indicate shapes including concave and convex portions, chamfered portions, and the like within a range that can obtain the same effect.

[0045] On the other hand, expressions such as “set,” “have,” “have,” “include,” or “have” a constituent element are not exclusive expressions that exclude the existence of other constituent elements.

[0046] Figure 11 is a schematic diagram showing a gas turbine 100 according to an embodiment of the present invention. Figure 1 As shown, a gas turbine 100 according to an embodiment includes a compressor 2 for compressing air as an oxidant supplied to a combustor 4 (i.e., generating compressed air), a combustor 4 (gas turbine combustor) for generating combustion gas using compressed air and fuel, and a turbine 6 configured to be driven by the combustion gas exhausted from the combustor 4. In the case of the gas turbine 100 for power generation, a generator (not shown) is connected to the turbine 6, and power generation is performed using the rotational energy of the turbine 6.

[0047] The above-mentioned combustion gas is generated by burning a mixed gas of fuel and air in the combustor 4 provided in the gas turbine 100. Examples of the fuel burned in the combustor 4 include hydrogen, methane, light oil, heavy oil, jet fuel, natural gas, gasified coal, etc., and any one of them or any combination of two or more thereof can be burned.

[0048] The compressor 2 includes a compressor chamber 10, an air intake port 12 provided on the inlet side of the compressor chamber 10 and for taking in air, a rotor 8 provided so as to penetrate the compressor chamber 10 and the turbine chamber 22 together, and various blades arranged in the compressor chamber 10. The various blades include an inlet guide vane 14 provided on the air intake port 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 a manner alternately arranged with the stationary blades 16. In such a compressor 2, the air taken in from the air intake port 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 sent from the compressor 2 to the combustor 4 of the subsequent stage.

[0049] A plurality of combustors 4 are arranged at intervals in the circumferential direction around the rotor 8. Fuel and compressed air generated in the compressor 2 are supplied to the combustor 4, and the fuel is combusted to generate combustion gas as a working fluid of the turbine 6. The combustion gas is then sent from the combustor 4 to the turbine 6 at the subsequent stage.

[0050] The turbine 6 includes a turbine casing 22 and various blades arranged in the turbine casing 22. The various blades include a plurality of stationary blades 24 fixed to the turbine casing 22 side, and a plurality of moving blades 26 implanted on the rotor 8 in a manner alternately arranged with respect to the stationary blades 24. 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. As a result, a generator (not shown) connected to the rotor 8 is driven.

[0051] In addition, an exhaust chamber 30 is connected to the downstream side of the turbine casing 22 via the exhaust casing 28. The combustion gas after driving the turbine 6 is discharged to the outside via the exhaust casing 28 and the exhaust chamber 30.

[0052] Figure 2 2 is a cross-sectional view showing the vicinity of the burner 4. The burner 4 includes a burner assembly 32, a bottomed cylindrical casing 20 accommodating the burner assembly 32, and a combustion tube 25 forming a space for flame formation on the downstream side of the burner assembly 32. Figure 2 In FIG. 1 , a dashed line indicates a central axis L common to the housing 20, the burner assembly 32, and the combustion tube 25. The burner assembly 32 is arranged inside the housing 20 of the combustor 4. In the illustrated exemplary embodiment, the burner assembly 32 is held inside a cylindrical member 34 arranged inside the housing 20, and the cylindrical member 34 is supported by the housing 20 via a plurality of support portions 35 arranged at intervals around the central axis L. An air flow path 36 for the compressed air flowing in from the machine room 40 is formed between the outer peripheral surfaces of the housing 20 and the cylindrical member 34 (between the outer peripheral surfaces of the housing 20 and the burner assembly 32).

[0053] The compressed air flowing into the air flow path 36 from the machine room 40 passes through the axial gap 23 between the burner assembly 32 and the bottom surface 21 of the housing 20, and flows into a plurality of mixing flow paths 46, which will be described later, provided in the burner assembly 32 together with the fuel. The fuel and air mixed in the burner assembly 32 are ignited by an ignition device (not shown), thereby forming a flame in the combustion tube 25 to generate combustion gas.

[0054] Figure 3 This is a partial schematic perspective view showing a part of the burner assembly 32 ( 32A) according to one embodiment. Figure 4 This is a schematic diagram of a portion of the burner assembly 32 (32A) viewed from the upstream side in the air flow direction along the central axis L ( Figure 2 An example of a view in the A direction. Figure 5 It is shown Figure 4 Schematic diagram of a portion of the BB section. Figure 6 It is shown Figure 4 Schematic diagram of a portion of the CC section.

[0055] For example Figure 3 or Figure 4 As shown, the burner assembly 32 includes a plurality of burners 42 for mixing fuel and air.

[0056] For example Figure 3~Figure 5 As shown in any of the figures, the burner 42 includes a plurality of fuel nozzles 43 for injecting fuel, and a fuel injected from the plurality of fuel nozzles 43 and a fuel from the engine room 40 (see Figure 1 as well as Figure 2 ) flows into the mixing flow path 46 into which the compressed air supplied by the burner 42 flows. In the illustrated exemplary embodiment, the burner 42 includes one mixing flow path 46 and four fuel nozzles 43 arranged around one mixing flow path 46, and fuel is injected from the four surrounding fuel nozzles into one mixing flow path 46. In other words, four mixing flow paths 46 are arranged around one fuel nozzle 43, and one fuel nozzle 43 injects fuel into four mixing flow paths 46.

[0057] The mixing channels 46 are respectively configured as through holes extending parallel to each other, and the central axis O of each mixing channel 46 extends in a direction along the central axis L of the housing 20. In the illustrated exemplary embodiment, the central axis O of each mixing channel 46 is parallel to the central axis L of the housing 20.

[0058] For example Figure 5 As shown, each fuel nozzle 43 includes a protrusion 50 that protrudes upstream of the inlet 48 of the mixing flow path 46 in the air flow direction. In addition, each fuel nozzle 43 includes a plurality of fuel injection holes 53 formed on the side surface 44 of the protrusion 50. Figure 4 In the illustrated exemplary embodiment, four fuel injection holes 53 are formed on the side surface 44 of the protrusion 50 at positions corresponding to the four mixing channels 46 around the protrusion 50. The fuel injection holes 53 may extend in a direction perpendicular to the central axis O of the mixing channel 46 in such a manner as to inject fuel toward the central axis O of the mixing channel 46, or may extend in a direction inclined relative to the direction perpendicular to the central axis O.

[0059] For example Figure 5 As shown, the top surface 54 of the protrusion 50 (the end surface of the protrusion 50 in the direction of the axis O, that is, the front end of the protrusion 50) includes a convex surface 56. In the illustrated exemplary embodiment, the top surface 54 of the protrusion 50 is entirely composed of the smoothly curved convex surface 56. The top surface 54 of the protrusion 50 can be formed into a streamlined shape, for example.

[0060] For example Figure 4 as well as Figure 6 As shown, the flow path wall 55 forming the mixing flow path 46 is formed in a tubular shape so as to divide the mixing flow path 46 having a circular cross section inside, and functions as a mixing tube for mixing fuel and air. Figure 4 As shown, for convenience, any two burners 42 whose mixing flow paths 46 are closest to each other among the plurality of burners 42 are referred to as the first burner 42 (42a) and the second burner 42 (42b). Figure 4 as well as Figure 6As shown, the flow path wall 55 forming the mixing flow path 46 (46a) of the first burner 42a and the flow path wall 55 forming the mixing flow path 46 (46b) of the second burner 42b share a partition wall portion 58 (58ab) that separates the mixing flow path 46a of the first burner 42a from the mixing flow path 46b of the second burner 42b. Figure 4 In the illustrated exemplary embodiment, the flow channel wall 55 of the mixing flow channel 46 and the flow channel walls 55 of a plurality of mixing flow channels 46 (four mixing flow channels 46 in the illustrated embodiment) surrounding the mixing flow channel 46 share the partition wall portion 58 .

[0061] In addition, if Figure 6 As shown in FIG. 1 , the thickness t of the partition wall portion 58ab in the CC cross section of the burner assembly 32A is constant in the direction along the central axis O of the first burner 42a. In addition, the end surface 59 on the upstream side in the air flow direction of the partition wall portion 58ab is formed in a flat shape. In addition, the thickness t of the partition wall portion 58ab is as follows: Figure 4 As shown in FIG. 1 , the distance from the CC section increases. Figure 4 as well as Figure 6 As shown, the CC section is a section (first section) passing through the center C1 of the inlet 48 of the mixing flow path 46a of the first burner 42a and the center C2 of the inlet 48 of the mixing flow path 46b of the second burner 42b and along the central axis O of the mixing flow path 46 of the first burner 42a.

[0062] Here, with Figure 7 The comparative scheme shown is used to illustrate the effects of the burner assembly 32A.

[0063] Figure 7 This is a schematic cross-sectional view showing a portion of a burner assembly 032 of a comparative example. Figure 8 It is shown Figure 7 FIG. 5 is a graph showing the distribution of the flow velocity (axial flow velocity) in the direction along the central axis O in the region S2 . Fig. 9 It is shown Figure 5 Graph showing the distribution of flow velocity in the direction along the central axis O in region S1.

[0064] exist Figure 7 In the comparative scheme shown, the top surface 054 of the protrusion 050 of the fuel nozzle 043 is a plane, and an edge 045 is formed at the connection position between the top surface 054 of the protrusion 050 and the side surface 044 of the protrusion 050. Therefore, the flow of air is peeled off at the edge 045, as shown in FIG. Figure 8 As shown, a region with a low flow velocity and a high fuel concentration is likely to be formed near the fuel injection hole 053 (near the fuel jet). As a result, the risk of flashback or backfire from the outlet of the mixing flow path 046 is likely to increase.

[0065] In contrast, in the burner assembly 32A of the above-described embodiment, since the top surface of the protruding portion 50 of the fuel nozzle 43 includes the convex curved surface 56, it is possible to suppress the peeling of the flow from the top surface 54 of the fuel nozzle 43 toward the side surface 44. Fig. 9 As shown, a region with a low flow velocity and a high fuel concentration is less likely to form near the fuel injection hole 53. As a result, the risk of flashback and flame holding can be reduced. Therefore, the burn damage of the burner 42 caused by flashback and flame holding can be suppressed.

[0066] Next, use Figure 10~Figure 13 A burner assembly 32 ( 32B) according to another embodiment will be described.

[0067] Fig.10 This is a partial schematic perspective view showing a part of the burner assembly 32 ( 32B) according to another embodiment. Fig.11 This is a schematic diagram of a portion of the burner assembly 32 (32B) viewed from the upstream side in the air flow direction along the central axis L ( Figure 2 An example of a view in the A direction. Fig.12 It is shown Fig.11 Schematic diagram of a portion of the CC section. Fig.13 It is shown Fig.11 Schematic diagram of a portion of the FF cross section.

[0068] Figure 10~Figure 13 The burner assembly 32B shown is different from the burner assembly 32A only in the shape of the end surface 59 of the partition wall portion 58. The other structures are the same as those of the burner assembly 32A, so the same reference numerals are used and the description thereof is omitted.

[0069] like Fig.10 As shown, in the burner assembly 32B, the end surface 59 (end surface on the upstream side in the air flow direction) of the partition wall portion 58 that partitions the two closest mixing flow paths 46 has a saddle shape. The shape of the end surface 59 of the partition wall portion 58 will be described in detail below.

[0070] like Fig.11 As shown, in the burner assembly 32B, for convenience, when any two adjacent burners 42 among the multiple burners 42 are referred to as the first burner 42 (42a) and the second burner 42 (42b), the flow path wall 55 forming the mixing flow path 46 (46a) of the first burner 42a and the flow path wall 55 forming the mixing flow path 46 (46b) of the second burner 42b share a partition wall portion 58 (58ab) that separates the mixing flow path 46a of the first burner 42a from the mixing flow path 46b of the second burner 42b.

[0071] like Fig.12 As shown, the thickness t of the partition wall portion 58ab in the CC section of the burner assembly 32B decreases at the end portion 61 on the upstream side in the air flow direction in the partition wall portion 58ab as it approaches the upstream side in the air flow direction. In addition, in the above-mentioned CC section, the end surface 59 on the upstream side in the air flow direction in the partition wall portion 58ab includes a convex curve 60. In the illustrated exemplary embodiment, in the above-mentioned CC section, the end surface 59 of the partition wall portion 58ab is composed of a smoothly curved convex curve 60 as a whole. In the above-mentioned CC section, the end surface 59 of the partition wall portion 58ab can be formed into a streamlined shape, for example. It should be noted that, as Fig.11 as well as Fig.12 As shown, the CC section is a section (first section) passing through the center C1 of the inlet 48 of the mixing flow path 46a of the first burner 42a and the center C2 of the inlet 48 of the mixing flow path 46b of the second burner 42b and along the central axis O of the mixing flow path 46a of the first burner 42a.

[0072] Here, if Fig.11 as well as Fig.13 As shown, for convenience, two fuel nozzles 43 having the protrusion 50 adjacent to the above-mentioned partition wall portion 58ab among the four fuel nozzles 43 of the first burner 42a are referred to as the first fuel nozzle 43 (43a) and the second fuel nozzle 43 (43b). That is, the protrusion 50 of the second fuel nozzle 43b is located on the side opposite to the protrusion 50 of the first fuel nozzle 43a across the plane V including the above-mentioned CC section.

[0073] like Fig.13 As shown, the height H of the partition wall portion 58ab increases as it approaches the protrusion 50 of the first fuel nozzle 43a from the position of the plane V (the position of the CC cross section), and increases as it approaches the protrusion 50 of the second fuel nozzle 43b from the position of the plane V. Fig.13 In the FF cross section of the burner assembly 32B shown in FIG. 1 , the end surface 59 on the upstream side in the air flow direction in the partition wall portion 58ab includes a concave curve 62 connecting the side surface 44 of the protrusion 50 of the first fuel nozzle 43a and the side surface 44 of the protrusion 50 of the second fuel nozzle 43b. Fig.11 As shown, the FF cross section is a cross section perpendicular to a straight line U connecting a center C1 of an inlet 48 of a mixing flow channel 46a of a first burner 42a and a center C2 of an inlet 48 of a mixing flow channel 46b of a second burner 42b.

[0074] Here, the effects of the burner assembly 32B will be described in comparison with the burner assembly 32A.

[0075] Fig.14 The burner assembly 32A is shown in FIG. Figure 4 Diagram of the flow of fuel and air in the CC section. Fig.15 The burner assembly 32A is shown in FIG. Fig.14 Graph showing the distribution of flow velocity in the direction along the central axis O in region S4. Fig.16 The burner assembly 32B is shown Fig.12 Graph showing the distribution of flow velocity in the direction along the central axis O in region S3.

[0076] In the burner assembly 32B, for example Fig.12 As shown in the figure, the top surface 54 of the protruding portion 50 of the fuel nozzle 43 also includes a convex curved surface 56, so that similarly to the burner assembly 32A, it is possible to suppress the peeling of the flow from the top surface 54 of the fuel nozzle 43 toward the side surface 44. Therefore, it is difficult to form a region with a low flow velocity and a high fuel concentration near the fuel injection hole 53. As a result, the risk of the above-mentioned flashback and flame holding can be reduced. Therefore, the burning loss of the burner 42 caused by flashback and flame holding can be suppressed.

[0077] In addition, if Fig.14 As shown, in the burner assembly 32A, the end surface 59 of the partition wall 58 is formed in a flat shape, so the edge 45 is formed at the connection position between the wall surface 63 of the partition wall 58 (the wall surface of the flow path wall 55 of the mixing flow path 46) and the end surface 59 of the partition wall 58, and the flow of air is separated at the edge 45. Therefore, as shown in FIG. Fig.15 As shown, a region with a low flow velocity and a high fuel concentration may be formed in a limited range near the inlet 48 of the mixing flow path 46. As a result, there is a limited risk of flashback from the outlet of the mixing flow path 46.

[0078] On the other hand, in the burner assembly 32B, if Fig.12 As described in the above, the thickness t of the partition wall 58 decreases at the end 61 on the upstream side of the air flow direction in the partition wall 58 as it approaches the upstream side of the air flow direction. In addition, in the CC cross section, the end surface 59 on the upstream side of the air flow direction in the partition wall 58 includes a convex curve 60. This can suppress the separation of the flow near the inlet 48 of the mixing flow path 46. Therefore, as Fig.16 As shown, near the inlet 48 of the mixing flow path 46, a region with a low flow velocity and a high fuel concentration is not easily formed near the wall surface 63 of the partition wall portion 58. As a result, the risk of flashback and flame holding can be reduced. Therefore, the burning damage of the burner 42 caused by flashback and flame holding can be suppressed.

[0079] In addition, in the burner assembly 32B, if Fig.13 As described in the above description, the height H of the partition wall portion 58 increases as the position of the plane V (the position of the CC cross section) approaches the protrusion 50 of the first fuel nozzle 43a, and increases as the position of the plane V approaches the protrusion 50 of the second fuel nozzle 43b. Fig.13 In the FF cross section shown, the end surface 59 on the upstream side in the air flow direction in the partition wall portion 58ab includes a concave curve 62 connecting the side surface 44 of the protrusion 50 of the first fuel nozzle 43a and the side surface 44 of the protrusion 50 of the second fuel nozzle 43b. As a result, the air flowing from the side surface 44 of the protrusion 50 to the end surface 59 of the partition wall portion 58 can be smoothly guided to the inside of the mixing flow path 46, so that it is difficult to form a region with a low flow velocity and a high fuel concentration near the inlet 48 of the mixing flow path 46 and near the wall surface 63 of the partition wall portion 58. Therefore, the burning of the burner 42 caused by flashback and flame holding can be suppressed.

[0080] The present invention is not limited to the above-described embodiment, and includes modifications to the above-described embodiment, or appropriate combinations of these embodiments.

[0081] For example, in the above-mentioned embodiment, the multiple fuel nozzles 43 and the flow path walls 55 forming the multiple mixing flow paths 46 are illustrated as a burner assembly 32A, 32B that is integrally formed as a component and cannot be separated, but each fuel nozzle and each mixing flow path can also be constructed as a component, and the multiple fuel nozzles and the multiple mixing flow paths can also be composed of any number of components.

[0082] In the above-described embodiment, each burner 42 is provided with a plurality of fuel nozzles 43 , but each burner 42 may have only one fuel nozzle 43 , and it is sufficient to have at least one fuel nozzle 43 .

[0083] The contents described in each of the above-mentioned embodiments can be understood, for example, as follows.

[0084] (1) The burner assembly of the present invention is a burner assembly (for example, the burner assembly 32 (32A, 32B)) including a plurality of burners (for example, the burner 42) for mixing fuel and air, wherein:

[0085] The plurality of burners respectively include:

[0086] at least one fuel nozzle (such as the above-mentioned fuel nozzle 43) for injecting the fuel; and

[0087] a mixing flow path (such as the above-mentioned mixing flow path 46) into which the fuel and air injected from the at least one fuel nozzle flow,

[0088] The at least one fuel nozzle includes a protrusion (for example, the protrusion 50) protruding upstream of an inlet (for example, the inlet 48) of the mixing flow path in the flow direction of the air.

[0089] The at least one fuel nozzle includes at least one fuel injection hole (such as the above-mentioned fuel injection hole 53) formed on a side surface of the protrusion (such as the above-mentioned side surface 44),

[0090] The top surface of the protrusion (eg, the top surface 54 described above) includes a convex surface (eg, the convex surface 56 described above).

[0091] According to the burner assembly described in (1) above, the top surface of the protruding portion of the fuel nozzle includes a convex curved surface, so that the peeling of the flow from the top surface of the fuel nozzle toward the side surface can be suppressed. Therefore, it is difficult to form a region with a low flow velocity and a high fuel concentration near the fuel injection hole (near the fuel jet). As a result, the risk of flashback from the outlet of the mixing flow path can be reduced.

[0092] (2) In some embodiments, in addition to the burner assembly described in (1) above,

[0093] The plurality of burners include a first burner (for example, the first burner 42 (42a) described above), and a second burner (for example, the second burner 42 (42b) described above) having the mixing flow path closest to the mixing flow path of the first burner,

[0094] A flow path wall forming the mixing flow path of the first burner (e.g., the flow path wall 55 described above) and a flow path wall forming the mixing flow path of the second burner (e.g., the flow path wall 55 described above) share a partition wall portion (e.g., the partition wall portion 58 (58ab) described above) that separates the mixing flow path of the first burner from the mixing flow path of the second burner,

[0095] At an end portion of the partition wall portion on the upstream side in the air flow direction (eg, the end portion 61 ), a thickness of the partition wall portion (eg, the thickness t) decreases toward the upstream side in the air flow direction.

[0096] According to the burner assembly described in (2) above, at the end portion on the upstream side in the air flow direction in the partition wall portion, the thickness of the partition wall portion decreases as it moves toward the upstream side in the air flow direction, so that it is possible to suppress the flow peeling on the surface of the partition wall portion near the inlet of the mixing flow path. Therefore, near the inlet of the mixing flow path, it is difficult to form a region with a low flow velocity and a high fuel concentration near the wall surface of the partition wall portion, thereby reducing the risk of flashback and the risk of flame holding.

[0097] (3) In some embodiments, in addition to the burner assembly described in (2) above,

[0098] When a section of the partition wall portion that passes through the center of the inlet of the mixing flow path of the first burner and the center of the inlet of the mixing flow path of the second burner and along the central axis of the mixing flow path of the first burner is defined as a first section (for example, the CC section described above),

[0099] An end surface on the upstream side in the air flow direction of the partition wall portion (for example, the end surface 59 described above) includes a convex curve (for example, the convex curve 60 described above) in the first cross section.

[0100] According to the burner assembly described in (3) above, the end surface on the upstream side in the air flow direction in the partition wall portion includes a convex curve in the first cross section, so that the flow peeling on the surface of the partition wall portion can be suppressed near the inlet of the mixing flow path. Therefore, near the inlet of the mixing flow path, it is difficult to form a region with a low flow velocity and a high fuel concentration near the wall surface of the partition wall portion, thereby reducing the risk of flashback and the risk of flame holding.

[0101] (4) In some embodiments, in addition to the burner assembly described in (3) above,

[0102] The first burner includes a first fuel nozzle (such as the first fuel nozzle 43 (43a) described above) and a second fuel nozzle (such as the second fuel nozzle 43 (43b) described above) as the at least one fuel nozzle for injecting fuel.

[0103] The protruding portion of the first fuel nozzle is disposed adjacent to the partition wall portion,

[0104] The protrusion of the second fuel nozzle is provided adjacent to the partition wall on the opposite side of the protrusion of the first fuel nozzle across a plane including the first cross section (for example, the above-mentioned plane V),

[0105] The height of the partition wall portion (for example, the height H described above) increases as it approaches the protruding portion of the first fuel nozzle from the first cross section.

[0106] According to the burner assembly described in (4) above, the height of the partition wall increases as the protrusion of the first fuel nozzle approaches from the first cross section, so that the air flowing from the side of the protrusion of the first fuel nozzle to the end face of the partition wall can be smoothly guided to the inside of the mixing flow path, so that it is difficult to form a region with a low flow rate and a high fuel concentration near the wall surface of the partition wall near the inlet of the mixing flow path. Therefore, the burning of the burner caused by flashback and flame holding can be suppressed.

[0107] (5) In some embodiments, in addition to the burner assembly described in (4) above,

[0108] In a cross section (e.g., the above-mentioned FF cross section) that is orthogonal to a straight line (e.g., the above-mentioned straight line U) connecting the center of the inlet of the mixing flow passage of the first burner and the center of the inlet of the mixing flow passage of the second burner, the end surface of the partition wall portion includes a concave curve (e.g., the above-mentioned concave curve 62) connecting the side surface of the protrusion of the first fuel nozzle and the side surface of the protrusion of the second fuel nozzle.

[0109] According to the burner assembly described in (5) above, a concave curve connecting the side of the protrusion of the first fuel nozzle and the side of the protrusion of the second fuel nozzle is included in the cross section orthogonal to the above straight line, so that the air flowing from the side of the protrusion of the first fuel nozzle and the side of the protrusion of the second fuel nozzle to the end face of the partition wall can be smoothly guided to the inside of the mixing flow path, so that it is difficult to form a region with low flow velocity and high fuel concentration near the inlet of the mixing flow path and the wall surface of the partition wall. Therefore, the burning loss of the burner caused by flashback and flame holding can be suppressed.

[0110] (6) The gas turbine combustor of the present invention (for example, the combustor 4 described above) includes:

[0111] The burner assembly as described in any one of (1) to (5) above; and

[0112] The combustion tube (for example, the combustion tube 25 described above) forms a space for flame formation on the downstream side of the burner assembly.

[0113] According to the gas turbine combustor described in (6), the burner assembly described in any one of (1) to (5) can reduce the risk of flashback and flame holding, thereby enabling the combustor to be used stably.

[0114] (7) A gas turbine according to the present invention (for example, the above-mentioned gas turbine 100 ) includes:

[0115] A compressor (such as compressor 2 described above);

[0116] a gas turbine combustor (for example, the combustor 4 described above) configured to be supplied with air compressed by the compressor and fuel and to combust the fuel to generate combustion gas; and

[0117] a turbine (such as turbine 6 described above) driven by the combustion gases produced by the gas turbine combustor,

[0118] The gas turbine combustor is the gas turbine combustor described in (6) above.

[0119] According to the gas turbine described in (7) above, the gas turbine combustor described in (6) above is provided, so that the risk of flashback and the risk of flame holding can be reduced, and burner damage can be suppressed, thereby stably operating the gas turbine.

Claims

1. A burner assembly comprising a plurality of burners for mixing fuel and air, wherein: The plurality of burners respectively include: at least one fuel nozzle for injecting the fuel; and a mixing flow path into which the fuel injected from the at least one fuel nozzle and the air flow from the inlet, When the mixing flow path is viewed in the axial direction from the upstream side of the mixing flow path, the at least one fuel nozzle that supplies the fuel to the mixing flow path is arranged around the mixing flow path so as not to overlap with the mixing flow path. The at least one fuel nozzle includes a protrusion protruding upstream of an inlet of the mixing flow path in a flow direction of the air, and at least one fuel injection hole formed on a side surface of the protrusion. An end surface on the upstream side of the protrusion in the flow direction of the air, that is, a top surface of the protrusion includes a convex curved surface.

2. The burner assembly according to claim 1, wherein: The plurality of burners include a first burner and a second burner having the mixing flow path closest to the mixing flow path of the first burner, A flow path wall forming the mixing flow path of the first burner and a flow path wall forming the mixing flow path of the second burner share a partition wall portion that separates the mixing flow path of the first burner from the mixing flow path of the second burner. At an end portion of the partition wall portion on the upstream side in the flow direction of the air, a thickness of the partition wall portion decreases toward the upstream side in the flow direction of the air.

3. The burner assembly according to claim 2, wherein: When a section of the partition wall portion that passes through the center of the inlet of the mixing flow path of the first burner and the center of the inlet of the mixing flow path of the second burner and along the central axis of the mixing flow path of the first burner is defined as a first section, An end surface on the upstream side in the air flow direction of the partition wall portion includes a convex curve in the first cross section.

4. The burner assembly according to claim 3, wherein: The first burner includes a first fuel nozzle and a second fuel nozzle as the at least one fuel nozzle for injecting fuel. The protruding portion of the first fuel nozzle is disposed adjacent to the partition wall portion, The protrusion of the second fuel nozzle is provided adjacent to the partition wall on the opposite side to the protrusion of the first fuel nozzle across a plane including the first cross section. The height of the partition wall portion increases as it approaches the protruding portion of the first fuel nozzle from the first cross section.

5. The burner assembly according to claim 4, wherein: In a cross section orthogonal to a straight line connecting the center of the inlet of the mixing flow passage of the first burner and the center of the inlet of the mixing flow passage of the second burner, the end surface of the partition wall portion includes a concave curve connecting the side surface of the protrusion of the first fuel nozzle and the side surface of the protrusion of the second fuel nozzle.

6. A burner assembly comprising a plurality of burners for mixing fuel and air, wherein: The plurality of burners respectively include: at least one fuel nozzle for injecting the fuel; and a mixing flow path into which the fuel injected from the at least one fuel nozzle and the air flow from the inlet, The plurality of burners include a first burner and a second burner having the mixing flow path closest to the mixing flow path of the first burner, The mixing flow path of the first burner and the mixing flow path of the second burner are separated by a partition wall. When the mixing flow path is viewed in the axial direction from the upstream side of the mixing flow path, the at least one fuel nozzle that supplies the fuel to the mixing flow path is arranged radially outside the mixing flow path, The at least one fuel nozzle includes a protrusion protruding from an upstream end of the partition wall toward the upstream side in the flow direction of the air, and at least one fuel injection hole formed on a side surface of the protrusion. An end surface of the protrusion on the upstream side in the flow direction of the air, that is, a top surface of the protrusion includes a convex curved surface.

7. A gas turbine combustor, wherein: The gas turbine combustor comprises: The burner assembly according to any one of claims 1 to 6; and A combustion tube forms a space for flame formation on the downstream side of the burner assembly.

8. A gas turbine, wherein: The gas turbine comprises: compressor; a gas turbine combustor configured to be supplied with air compressed by the compressor and fuel and to combust the fuel to generate combustion gas; and a turbine driven by said combustion gases produced by said gas turbine combustor, The gas turbine combustor is the gas turbine combustor according to claim 7.

Images