Gas turbine combustor and gas turbine

Abstract

To suppress the generation of CO by improving the combustibility of first-stage combustion gas, and suppress the generation of NOx by improving the mixing properties of the first-stage combustion gas and second-stage premixed gas in a gas turbine combustor and a gas turbine.SOLUTION: A gas turbine combustor comprises: a combustion tube having a cylindrical shape; a fuel supply unit for supplying a fuel gas to the inside of the combustion tube; a premixed gas supply unit for supplying a premixed gas, in which a fuel and air are mixed, to the inside of the combustion tube on the downstream side of the fuel supply unit in a combustion gas flow direction; and a deflection member that protrudes toward the center side of the combustion tube from the inner wall surface of the combustion tube between the fuel supply unit and the premixed gas supply unit to deflect a combustion gas flow.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present disclosure relates to gas turbine combustors and gas turbines. [Background technology]

[0002] A gas turbine comprises a compressor, combustor, and turbine. The compressor compresses the air it takes in to produce high-temperature, high-pressure compressed air. The combustor supplies fuel to the compressed air and burns it to produce high-temperature, high-pressure combustion gas. The turbine is driven by the combustion gas, which drives a generator connected to the same shaft.

[0003] Increasing the combustion temperature is one way to improve the efficiency and power output of gas turbines. However, it is necessary to reduce the NOx generated during combustion, and a premixed combustion system is used to lower the maximum flame temperature. However, the premixed combustion system is prone to combustion oscillation, an unstable phenomenon, and an acoustic device is required. However, the acoustic device requires purging air to suppress flame flashback, which reduces the amount of air available for combustion and raises the issue of increasing NOx.

[0004] Two-stage combustion is a technology that can solve these problems. With two-stage combustion, when the flame temperature is low at low loads, air is supplied from the second-stage nozzle, which increases the flame temperature upstream and suppresses CO emissions. Furthermore, under high loads, the two-stage combustion method increases the fuel-to-air ratio from the second-stage nozzle compared to the first-stage nozzle, thereby keeping the temperature of the first-stage flame region, which has a longer residence time, low and achieving overall low NOx emissions. [Prior art documents] [Patent documents]

[0005] [Patent Document 1] Japanese Patent Application Laid-Open No. 2007-113888 Summary of the Invention [Problem to be solved by the invention]

[0006] However, in the two-stage combustion system, at low loads, low-temperature air is supplied from the second-stage nozzle to mix with the first-stage combustion gas. This causes a rapid drop in the mainstream gas temperature, resulting in insufficient combustion of the fuel supplied from the first-stage nozzle and the generation of CO. Furthermore, at high loads, if the premixed gas supplied from the second-stage nozzle does not penetrate the first-stage combustion gas sufficiently, the first-stage combustion gas and the second-stage premixed gas will not mix properly. This leaves a high-temperature region of the premixed gas supplied from the second-stage nozzle, resulting in the generation of NOx.

[0007] The present disclosure has been made to solve the above-described problems, and an object of the present disclosure is to provide a gas turbine combustor and a gas turbine that suppress the generation of CO by improving the combustibility of first-stage combustion gas, and that suppress the generation of NOx by improving the mixability of the first-stage combustion gas with second-stage premixed gas. [Means for solving the problem]

[0008] To achieve the above object, a gas turbine combustor of the present disclosure includes: a cylindrical combustion liner; a fuel supply unit that supplies a fuel gas into an interior of the combustion liner; a premixed gas supply unit that supplies a premixed gas of mixed fuel and air into the interior of the combustion liner, downstream of the fuel supply unit in a flow direction of the combustion gas; and a deflection member that protrudes from an inner wall surface of the combustion liner toward a center of the combustion liner between the fuel supply unit and the premixed gas supply unit and deflects the flow of the combustion gas.

[0009] The gas turbine disclosed herein also includes a compressor that generates high-temperature, high-pressure compressed air by compressing air, a gas turbine combustor that supplies fuel gas to the compressed air and burns it to generate high-temperature, high-pressure combustion gas, and a turbine that is driven by the combustion gas. [Effects of the Invention]

[0010] According to the gas turbine combustor and the gas turbine of the present disclosure, the generation of CO can be suppressed by improving the combustibility of the first-stage combustion gas, and the generation of NOx can be suppressed by improving the mixability between the first-stage combustion gas and the second-stage premixed gas. [Brief explanation of the drawings]

[0011] [Figure 1] FIG. 1 is a schematic diagram showing the overall configuration of a gas turbine. [Figure 2] FIG. 2 is a cross-sectional view illustrating the gas turbine combustor of the first embodiment. [Figure 3] FIG. 3 is a cross-sectional view showing the premixed gas supply unit. [Figure 4] FIG. 4 is a cross-sectional view taken along the line IV-IV in FIG. 2, illustrating the positional relationship between the premixed gas supply unit and the deflection member. [Figure 5] FIG. 5 is a cross-sectional view showing a modified example of the positional relationship between the premixed gas supply unit and the deflection member. [Figure 6] FIG. 6 is a cross-sectional view illustrating a premixed gas supply unit in a gas turbine combustor according to the second embodiment. [Figure 7] FIG. 7 is a cross-sectional view illustrating a gas turbine combustor according to the third embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0012] Preferred embodiments of the present disclosure will be described in detail below with reference to the drawings. Note that the present disclosure is not limited to these embodiments, and when there are multiple embodiments, the present disclosure also includes configurations that combine the embodiments. Furthermore, the components in the embodiments include those that can be easily imagined by a person skilled in the art, those that are substantially identical, and those that are within the so-called equivalent range.

[0013] [First embodiment] <Gas turbine> FIG. 1 is a schematic diagram showing the overall configuration of a gas turbine.

[0014] As shown in Fig. 1, a gas turbine 10 has a compressor 11, a combustor (gas turbine combustor) 12, and a turbine 13. The compressor 11 and the turbine 13 can rotate integrally by a rotary shaft 14. A generator 15 is connected to one axial end of the rotary shaft 14. A plurality of combustors 12 are arranged between the compressor 11 and the turbine 13 at intervals in the circumferential direction.

[0015] The compressor 11 generates high-temperature, high-pressure compressed air CA by compressing air A taken in through an air intake as it passes through multiple stator vanes and rotor blades. The combustor 12 supplies fuel gas FG to the compressed air CA to generate an air-fuel mixture MG, and burns the air-fuel mixture MG to generate high-temperature, high-pressure combustion gas CG. The turbine 13 drives and rotates a rotating shaft 14 as the combustion gas CG passes through the stator vanes and rotor blades, and discharges exhaust gas EG. The generator 15 is driven by the rotation of the rotating shaft 14 to generate electricity.

[0016] <Gas turbine combustor> FIG. 2 is a cross-sectional view illustrating the gas turbine combustor of the first embodiment.

[0017] As shown in FIG. 2, the combustor 12 includes a combustor body 21, a fuel supply unit 22, a premixed gas supply unit 23, and a deflection member 24.

[0018] The combustor body 21 has a cylindrical shape centered on the axis O1. However, the combustor body 21 is not limited to a cylindrical shape and may have an elliptical shape or a cylindrical shape whose area changes along the axial direction. The combustor body 21 has an outer cylinder 31, an inner cylinder 32, and a transition piece (combustion cylinder) 33. The combustor body 21 is configured by connecting the outer cylinder 31, the inner cylinder 32, and the transition piece 33 in series.

[0019] The fuel supply unit 22 supplies fuel gas FG to the inside of the combustor body 21. Specifically, the fuel supply unit 22 supplies a mixture MG of fuel gas FG and compressed air CA to the inside of the inner cylinder 32. The premixed gas supply unit 23 is arranged downstream of the fuel supply unit 22 in the flow direction of the combustion gas CG. The premixed gas supply unit 23 supplies fuel gas FG to the inside of the combustor body 21. Specifically, the premixed gas supply unit 23 supplies compressed air CA or a mixture MG of compressed air CA and fuel gas FG to the inside of the transition piece 33.

[0020] The deflection member 24 is disposed between the fuel supply unit 22 and the premixed gas supply unit 23 in the direction of the axis O1. In this case, the deflection member 24 is disposed closer to the premixed gas supply unit 23 than the fuel supply unit 22. The deflection member 24 protrudes from the inner wall surface of the combustor body 21 toward the center (axis O1) of the combustor body 21. Specifically, the deflection member 24 is fixed to the inner wall surface 33a of the transition piece 33, and deflects the flow of combustion gas CG flowing along the inner wall surface 33a of the transition piece 33 toward the center (axis O1) of the transition piece 33.

[0021] The combustor 12 will now be described in detail.

[0022] The outer cylinder 31 has one end in the direction of the axis O1 connected to a top hat portion 41, and the other end is open on the outer peripheral side, through which high-temperature, high-pressure compressed air CA generated by the compressor 11 (see FIG. 1) flows. One end of the inner cylinder 32 in the direction of the axis O1 is disposed inside the outer cylinder 31 and connected to the outer cylinder 31 via a connecting member 42. The connecting member 42 is ring-shaped and has a large number of through holes 42a formed therein. The connecting member 42, which has a large number of through holes 42a, functions as a throttle member for the compressed air CA.

[0023] The transition piece 33 has one end in the axial direction O1 disposed inside the other end of the external cylinder 31 and outside the other end of the internal cylinder 32, and is supported by the internal cylinder 32 via a support member 43. A ring-shaped air passage 44 is formed between the other end of the external cylinder 31 and one end of the transition piece 33. The compressed air CA flows through the air passage 44 toward the connecting member 42. In addition, a ring-shaped air passage 45 is formed between the other end of the internal cylinder 32 and one end of the transition piece 33. A portion of the compressed air CA flows through the air passage 45 into the transition piece 33 and functions as film air flowing along the inner wall surface 33a.

[0024] A pilot combustion burner 53 and a main combustion burner 54 are arranged inside the inner cylinder 32. The pilot combustion burner 53 is arranged at the center (axial center O1) of the inner cylinder 32. A plurality of main combustion burners 54 are arranged around the pilot combustion burner 53 at intervals in the circumferential direction.

[0025] The pilot combustion burner 53 has a pilot cone 55 and a pilot nozzle 56. An end of the pilot cone 55 is supported by the inner cylinder 32. The pilot nozzle 56 is supported by the top hat portion 41 and is disposed inside the pilot cone 55. Although not shown, a swirler vane is provided on the outer periphery of the pilot nozzle 56. A pilot fuel line, not shown, is connected to the pilot nozzle 56.

[0026] The main combustion burner 54 has a support 57 and a main nozzle 58. An end of the support 57 is supported by the top hat portion 41. The main nozzle 58 is disposed inside the support 57. The main nozzle 58 has a swirler vane. A main fuel line (not shown) is connected to the main nozzle 58.

[0027] In the first embodiment, the fuel supply unit 22 has at least a pilot combustion burner 53 and a plurality of main combustion burners .

[0028] Therefore, the compressed air CA flows into the inner cylinder 32. The multiple main combustion burners 54 inject fuel gas FG into the compressed air CA to mix them and generate an air-fuel mixture (premixed air) MG, and the air-fuel mixture MG becomes a swirling flow and flows into the transition piece 33. Meanwhile, the pilot combustion burner 53 injects fuel gas FG into the compressed air CA to mix them and generate an air-fuel mixture MG. The air-fuel mixture MG is ignited by a pilot flame (not shown) and burns, becoming combustion gas CG, which is injected into the transition piece 33. At this time, a portion of the combustion gas CG is injected into the transition piece 33 so as to diffuse to the periphery with a flame, and the air-fuel mixture MG flowing from each main combustion burner 54 into the transition piece 33 is ignited and burns. In other words, the flame of the pilot fuel gas FG injected from the pilot combustion burner 53 can provide flame stabilization for stable combustion of the lean premixed fuel gas FG from the main combustion burner 54.

[0029] <Premixed gas supply unit> FIG. 3 is a cross-sectional view showing the premixed gas supply unit.

[0030] 2 and 3, the premixed gas supply unit 23 is disposed downstream of the fuel supply unit 22 and is capable of ejecting only compressed air CA into the interior of the transition piece 33, as well as ejecting a mixture of compressed air CA and fuel (premixed gas) MG. A plurality of premixed gas supply units 23 are disposed at intervals around the circumferential direction of the transition piece 33. The premixed gas supply unit 23 has an ejection portion for ejecting the mixture MG into the interior of the transition piece 33 disposed along the inner wall surface 33a of the transition piece 33.

[0031] The premixed gas supply unit 23 has a housing 61 , an ejection hole (ejection unit) 62 , an air nozzle 63 , and a fuel nozzle 64 .

[0032] The housing 61 is fixed by fitting into a mounting hole 33b formed in the transition piece 33 from the outside. A front surface 61a of the housing 61 is continuous with the inner wall surface 33a of the transition piece 33 without any steps. The ejection holes 62 are circular and are provided along the direction of the axis O2, which is the radial direction of the transition piece 33 perpendicular to the direction of the axis O1 of the housing 61. Note that the shape of the ejection holes 62 is not limited to the direction of the axis O2 perpendicular to the direction of the axis O1, and they may be inclined to one side or the other of the direction of the axis O1 or inclined in the circumferential direction of the transition piece 33. Furthermore, the shape of the ejection holes 62 is not limited to a circle, and they may be elliptical or polygonal (rectangular), for example.

[0033] The ejection hole 62 has an opening 62a at one axial end thereof that communicates with the interior of the transition piece 33, and the opening 62a opens to the inner wall surface 33a of the transition piece 33. The air nozzle 63 has a bell-mouth shape. The air nozzle 63 is concentric with the ejection hole 62, and its tip communicates with the ejection hole 62. An air line (not shown) is connected to the air nozzle 63. Compressed air CA from the compressor 11 (see FIG. 1) is supplied to the air line.

[0034] A plurality of fuel nozzles 64 are provided around the ejection holes 62 in the housing 61 along a direction perpendicular to the direction of the axis O2. The fuel nozzles 64 communicate with the ejection holes 62. The fuel nozzles 64 are connected to a fuel line (not shown), and an opening / closing valve (flow rate adjustment valve) is provided in the fuel line.

[0035] Therefore, compressed air CA is supplied from the air line to the air nozzle 63. Then, the air nozzle 63 ejects the compressed air CA to the ejection holes 62. Meanwhile, fuel gas FG is supplied from the fuel line to the fuel nozzle 64. Then, the fuel nozzle 64 ejects the fuel gas FG to the ejection holes 62. As a result, the premixed gas supply unit 23 ejects a mixture MG of the compressed air CA and the fuel gas FG from the ejection holes 62 toward the inside of the transition piece 33.

[0036] <Deflection member 24> FIG. 4 is a cross-sectional view taken along the line IV-IV in FIG. 2, illustrating the positional relationship between the premixed gas supply unit and the deflection member.

[0037] As shown in FIGS. 2 and 3 , the deflection member 24 is provided on the inner wall surface 33a of the transition piece 33 upstream of the premixed gas supply unit 23 in the flow direction of the combustion gas CG. The deflection member 24 protrudes from the inner wall surface 33a of the transition piece 33 toward the center (axial center O1) of the combustor body 21 and downstream in the flow direction of the combustion gas CG. The deflection member 24 has an attachment portion 24a and a deflection portion 24b. The attachment portion 24a is fixed to the inner wall surface 33a of the transition piece 33 by, for example, welding. The deflection portion 24b is provided integrally with the end of the attachment portion 24a at a predetermined angle. In other words, the deflection member 24 is provided as a separate member from the transition piece 33.

[0038] The deflection member 24 is fixed such that the deflection portion 24b is at a predetermined deflection angle θ with respect to the inner wall surface 33a of the transition piece 33. This deflection angle θ is preferably in the range of, for example, 30 degrees or more and less than 90 degrees. In this case, the inner diameter of the transition piece 33 is the same on the upstream side and the downstream side of the deflection member 24.

[0039] The premixed gas supply unit 23 and the deflection member 24 have a predetermined positional relationship. That is, the distance L between the deflection member 24 and the premixed gas supply unit 23 in the direction of the axis O1 is preferably shorter than 10 times the radial length H1 of the transition piece 33 of the part of the deflection member 24 that protrudes from the inner wall surface 33a of the transition piece 33. That is, the relationship between the distance L and the radial length H1 is preferably L<10H1. Furthermore, the relationship between the distance L and the radial length H1 is preferably L<7H1.

[0040] Here, the distance L is the distance in the direction of the axis O1 from the downstream end of the deflection member 24 in the direction of the axis O1 to the ejection hole 62 of the premixed gas supply unit 23. Furthermore, the radial length H1 is the length of the transition piece 33 in the radial direction (direction of the axis O2) from the inner wall surface 33a of the transition piece 33 to the tip of the deflection member 24.

[0041] The deflector 24 deflects the flow of the combustion gas CG, thereby forming a low-velocity region of the combustion gas CG downstream. The relationship (L<7H) between the distance L and the radial length H1 in the premixed gas supply unit 23 and the deflector 24 is set taking into account the backstep flow at this time. That is, by applying the relationship (L<7H) between the distance L and the radial length H1, the combustion gas CG deflected by the deflector 24 is less likely to flow toward the ejection holes 62 of the premixed gas supply unit 23, and the flow of the combustion gas CG is less likely to affect the penetration force of the mixture MG ejected from the ejection holes 62 of the premixed gas supply unit 23.

[0042] 3 and 4, a plurality of premixed gas supply units 23 (four in this embodiment, but the number is not limited) are arranged at intervals (preferably at equal intervals) in the circumferential direction of the transition piece 33. The deflection member 24 is arranged at a position facing the plurality of premixed gas supply units 23 in the axial direction (direction of the axis O1) of the transition piece 33. In other words, the deflection member 24 and the premixed gas supply units 23 are arranged at approximately the same position in the circumferential direction.

[0043] That is, the deflection member 24 has a ring shape. The deflection member 24 is disposed around the entire circumference of the inner wall surface 33a of the transition piece 33. Therefore, the deflection member 24 deflects the combustion gas CG along the inner wall surface 33a of the transition piece 33, which flows toward the premixed gas supply section 23, all around the inner wall surface 33a, so as to flow toward the center (axial center O1) of the combustor main body 21.

[0044] However, the deflection member 24 is not limited to the above-mentioned shape. Fig. 5 is a cross-sectional view showing a modified example of the positional relationship between the premixed gas supply unit and the deflection member.

[0045] 3 and 5, a plurality of premixed gas supply units 23 are arranged at intervals in the circumferential direction of the transition piece 33. A plurality of deflection members 24A are arranged at positions facing the plurality of premixed gas supply units 23 in the axial direction of the transition piece 33 (the direction of the axis O1).

[0046] That is, a plurality of deflection members 24A (eight in this embodiment) are disposed. Some (four in this embodiment) of the plurality of deflection members 24A are disposed at positions facing the four premixed gas supply units 23 in the direction of the axis O1. The remaining four deflection members 24A are disposed at positions facing the intermediate positions of the four premixed gas supply units 23 in the direction of the axis O1. Therefore, the plurality of deflection members 24A deflect at least the combustion gas CG flowing toward the ejection holes 62 of each premixed gas supply unit 23, out of the combustion gas CG flowing along the inner wall surface 33a of the transition piece 33, so that the combustion gas CG flows toward the center (axis O1) of the combustor body 21.

[0047] The combustor 12 generates vibrations (combustion vibrations) when fuel is burned. The combustion vibrations are a cause of noise and vibrations during operation of the gas turbine 10. For this reason, an acoustic damper 71 is provided for the combustor 12, which serves as a vibration generating source through which the combustion gas CG flows. The acoustic damper 71 is provided in the transition piece 33 of the combustor 12. When the combustion gas CG flows in the transition piece 33, the acoustic damper 71 takes in air vibrations (pressure waves) caused by the combustion vibrations of the combustion gas CG through a through-hole in the transition piece 33, thereby attenuating the pressure fluctuations. The deflection member 24 (24A) is disposed downstream of the acoustic damper 71 in the flow direction of the combustion gas CG.

[0048] <Combustor action> 2, in the fuel supply unit 22, a plurality of main combustion burners 54 inject fuel gas FG into compressed air CA to generate an air-fuel mixture (premixed air) MG, and the air-fuel mixture MG flows into the transition piece 33. The pilot combustion burner 53 injects fuel gas FG into compressed air CA to generate an air-fuel mixture MG, which is ignited and combusted, and combustion gas CG is injected into the transition piece 33. Then, the fuel gas FG injected from the main combustion burners 54 is ignited by the diffusion flame (or premixed flame) injected from the pilot combustion burner 53, resulting in lean combustion.

[0049] The combustion gas CG generated by combustion of the fuel gas FG supplied from the fuel supply unit 22 flows through the transition piece 33 toward the premixed gas supply unit 23. At this time, the deflection member 24 (24A) deflects the direction of the combustion gas CG flowing along the inner wall surface 33a of the transition piece 33 so that the combustion gas flows toward the center (axial center O1) of the combustor main body 21. In this state, the premixed gas supply unit 23 ejects compressed air CA or an air-fuel mixture MG from the ejection holes 62 toward the inside of the transition piece 33.

[0050] During low-load operation of the gas turbine 10 (see FIG. 1 ), the premixed gas supply unit 23 injects compressed air CA into the transition piece 33 toward the combustion gas CG generated by combustion of the fuel gas FG supplied from the fuel supply unit 22. At this time, in the region of the transition piece 33 where the deflection member 24 (24A) is arranged, the flow direction of the combustion gas CG is deflected toward the center of the transition piece 33 by the deflection member 24 (24A), causing the flow to become turbulent. In addition, a portion of the combustion gas CG flows from the tip of the deflection member 24 (24A) toward the inner wall surface 33a of the transition piece 33, generating a vortex and causing flame stabilization. Therefore, when the compressed air CA is injected from the premixed gas supply unit 23 toward the disturbed flow of the combustion gas CG, the combustion gas CG and the compressed air CA are appropriately mixed, promoting the combustion reaction, ensuring appropriate combustion of the combustion gas CG, and suppressing the generation of CO.

[0051] On the other hand, during high-load operation of the gas turbine 10 (see FIG. 1 ), the premixed gas supply unit 23 injects a mixture MG of compressed air CA and fuel gas FG into the transition piece 33 in response to combustion gas CG generated by combustion of fuel gas FG supplied from the fuel supply unit 22. At this time, in the region of the transition piece 33 where the deflection member 24 (24A) is arranged, the flow direction of the combustion gas CG is deflected toward the center of the transition piece 33 by the deflection member 24 (24A). As a result, in the region forward of the ejection holes 62 in the premixed gas supply unit 23, the combustion gas CG flows toward the center of the transition piece 33. As a result, the premixed gas supply unit 23 has sufficient penetration power to inject the mixture MG toward the combustion gas CG, and the combustion gas CG and the mixture MG are properly mixed, promoting a combustion reaction. Therefore, the fuel gas FG supplied from the premixed gas supply unit 23 can be properly combusted, and the generation of NOx is suppressed.

[0052] [Second embodiment] Fig. 6 is a cross-sectional view showing a premixed gas supply unit in a gas turbine combustor according to a second embodiment. The basic configuration of the second embodiment is similar to that of the first embodiment described above, and will be described with reference to Fig. 2. Members having similar functions to those of the first embodiment described above are denoted by the same reference numerals, and detailed description thereof will be omitted.

[0053] 1 and 6, the premixed gas supply unit 23A is disposed downstream of the fuel supply unit 22, and is capable of injecting only the compressed air CA into the interior of the transition piece 33, as well as injecting a mixture MG of the compressed air CA and fuel. The premixed gas supply unit 23A is disposed such that the outlet for the fuel gas FG into the interior of the transition piece 33 protrudes from the inner wall surface 33a of the transition piece 33 into the interior of the transition piece 33.

[0054] The premixed gas supply unit 23A has a housing 61, an ejection hole (ejection unit) 62, an air nozzle 63, a fuel nozzle 64, and a guide unit 65.

[0055] The housing 61A is fitted and fixed from the outside into a mounting hole 33b formed in the transition piece 33. The front surface 61a of the housing 61 is continuous without any steps with the inner wall surface 33a of the transition piece 33. The ejection holes 62 are provided along the direction of the axis O2, which is the radial direction of the transition piece 33 perpendicular to the direction of the axis O1 of the housing 61. The tip of the air nozzle 63 communicates with the ejection holes 62.

[0056] A plurality of fuel nozzles 64 are provided around the ejection holes 62. The fuel nozzles 64 communicate with the ejection holes 62.

[0057] The guide portion 65 extends from the front surface 61a of the housing 61 into the interior of the transition piece 33. The guide portion 65 has a cylindrical shape, is arranged concentrically with the ejection hole 62, and has the same inner diameter as the inner diameter of the ejection hole 62. The guide portion 65 is not limited to a circular shape, and may be an elliptical shape or a polygonal shape (rectangular shape), etc. Furthermore, the guide portion 65 is preferably shaped to match the ejection hole 62, but may have a different shape. Furthermore, the guide portion 65 is preferably provided around the entire circumference of the ejection hole 62, but may be provided only partially on the deflection member 24 side, for example.

[0058] That is, the guide portion 65 protrudes from the inner wall surface 33a of the transition piece 33 toward the transition piece 33, thereby extending the ejection holes 62 to the inside of the transition piece 33. In this case, it is preferable that the radial length H2 of the transition piece 33 at the guide portion 65 protruding from the inner wall surface 33a of the transition piece 33 is equal to or greater than the radial length H1 of the transition piece 33 at the deflection member 24 protruding from the inner wall surface 33a of the transition piece 33.

[0059] The deflection member 24 is provided upstream in the flow direction of the combustion gas CG from the premixed gas supply portion 23 on the inner wall surface 33a of the transition piece 33. The deflection member 24 protrudes from the inner wall surface 33a of the transition piece 33 toward the center (axial center O1) of the combustor body 21 and downstream in the flow direction of the combustion gas CG.

[0060] Therefore, the premixed gas supply unit 23A injects compressed air CA or a mixture MG of compressed air CA and fuel gas FG into the transition piece 33 in response to the combustion gas CG generated by the combustion of the fuel gas FG supplied from the fuel supply unit 22. At this time, the premixed gas supply unit 23A has the ejection holes 62 extended to the inside of the transition piece 33 by the guide unit 65, thereby improving the penetration force of the mixture MG. Furthermore, the flow direction of the combustion gas CG is deflected toward the center of the transition piece 33 by the deflection member 24, so the combustion gas CG and the mixture MG are appropriately mixed, accelerating the combustion reaction. Therefore, the fuel gas FG supplied from the premixed gas supply unit 23 can be appropriately combusted, and the generation of CO and NOx is suppressed.

[0061] [Third embodiment] 7 is a cross-sectional view showing a gas turbine combustor according to the third embodiment. Note that members having the same functions as those in the first embodiment described above are denoted by the same reference numerals, and detailed description thereof will be omitted.

[0062] 7, the combustor 12A includes a combustor body 21, a fuel supply unit 22, a premixed gas supply unit 23, and a deflection member 24. A plurality of premixed gas supply units 23 (two in this embodiment, but the number is not limited) are arranged at intervals in the axial direction of the combustor body 21 (transition piece 33).

[0063] The plurality of premixed gas supply units 23 are arranged downstream of the fuel supply unit 22, and are capable of injecting only compressed air CA into the transition piece 33, as well as injecting a mixture MG of compressed air CA and fuel. The plurality of premixed gas supply units 23 have the same configuration.

[0064] Therefore, each premixed gas supply unit 23 injects compressed air CA or a mixture MG of compressed air CA and fuel gas FG into the transition piece 33 in response to the combustion gas CG generated by the combustion of the fuel gas FG supplied from the fuel supply unit 22. At this time, the flow direction of the combustion gas CG is deflected toward the center of the transition piece 33 by the deflection member 24, so that the combustion gas CG and the mixture MG are appropriately mixed, facilitating the combustion reaction. Therefore, the fuel gas FG supplied from the premixed gas supply unit 23 can be appropriately combusted, and the generation of CO and NOx is suppressed.

[0065] [Effects of this embodiment] A gas turbine combustor according to the first aspect includes: a cylindrical combustor body 21; a fuel supply unit 22 that supplies a fuel gas FG into the inside of the combustor body 21; a premixed gas supply unit 23, 23A that supplies an air-fuel mixture (premixed gas) MG into the inside of the combustor body 21 downstream of the fuel supply unit 22 in a flow direction of the combustion gas CG; and deflection members 24, 24A that protrude from an inner wall surface of the combustor body 21 toward a center of the combustor body 21 between the fuel supply unit 22 and the premixed gas supply unit 23, 23A and deflect the flow of the combustion gas CG.

[0066] According to the gas turbine combustor according to the first aspect, the fuel supply unit 22 supplies the fuel gas FG to the combustor body 21, and the combustion gas CG generated by combustion of the fuel gas FG flows toward the premixed gas supply unit 23. At this time, the direction of the combustion gas CG is deflected by the deflection members 24, 24A so as to flow toward the center (axis O1) of the combustor body 21. Then, in this state, the premixed gas supply unit 23 supplies the air-fuel mixture MG to the combustor body 21.

[0067] Therefore, for example, during low-load operation of the gas turbine 10, the direction of the combustion gas CG is deflected by the deflection members 24, 24A, and the flow is disturbed. As a result, the combustion gas CG and the compressed air CA ejected from the premixed gas supply unit 23 are appropriately mixed, promoting the combustion reaction, ensuring appropriate combustion of the combustion gas CG, and suppressing the generation of CO.

[0068] Furthermore, for example, during high load operation of the gas turbine 10, the direction of the combustion gas CG is deflected by the deflection members 24, 24A. This increases the penetration force of the mixture MG ejected from the premixed gas supply unit 23, and the combustion gas CG and the mixture MG are appropriately mixed to promote the combustion reaction, ensuring appropriate combustion of the fuel gas FG and suppressing the generation of NOx.

[0069] A gas turbine combustor according to a second aspect is the gas turbine combustor according to the first aspect, further comprising: an ejection hole (ejection portion) 62 for ejecting the air-fuel mixture MG into the combustor body 21 in the premixed gas supply portion 23, 23A, which is disposed along an inner wall surface of the combustor body 21. This enables to eliminate any protrusions on the inner wall surface of the combustor body 21 and improve the fluidity of the combustion gas CG.

[0070] A gas turbine combustor according to a third aspect is the gas turbine combustor according to the first aspect, further including an ejection hole (ejection portion) 62 of the air-fuel mixture MG toward the inside of the combustor body 21 in the premixed gas supply portion 23, 23A, disposed to protrude from the inner wall surface of the combustor body 21 into the combustor body 21. This can improve the penetration force of the air-fuel mixture MG ejected from the ejection hole 62 of the premixed gas supply portion 23, 23A with respect to the combustion gas CG.

[0071] A gas turbine combustor according to a fourth aspect is the gas turbine combustor according to any of the first to third aspects, further comprising: a distance L in the axial direction of the combustor body 21 between the deflection member 24, 24A and the premixed gas supply portion 23, 23A that is shorter than 10 times a length H1 of the deflection member 24, 24A protruding from the inner wall surface of the combustor body 21 in the radial direction. Thus, the combustion gas CG heading toward the ejection hole 62 of the premixed gas supply portion 23, 23A can be appropriately reduced by the deflection member 24, 24A.

[0072] A gas turbine combustor according to a fifth aspect is the gas turbine combustor according to any of the first to fourth aspects, further comprising: a plurality of premixed gas supply units 23, 23A disposed circumferentially of the combustor body 21 at intervals therebetween; and the deflection member 24, 24A disposed at a position facing the plurality of premixed gas supply units 23, 23A in the axial direction of the combustor body 21. Thus, the deflection member 24, 24A can appropriately reduce the influence of the combustion gas CG on the air-fuel mixture MG ejected from the premixed gas supply unit 23, 23A.

[0073] A gas turbine combustor according to a sixth aspect is the gas turbine combustor according to any of the first to fifth aspects, further comprising: a plurality of premixed gas supply units 23, 23A disposed at intervals in the axial direction of the combustor body 21. Thus, mixability between the combustion gas CG generated by combustion of the fuel gas FG supplied from the fuel supply unit 22 and the air-fuel mixture MG supplied from the premixed gas supply units 23, 23A is improved, thereby suppressing the generation of NOx.

[0074] A gas turbine according to a seventh aspect includes a compressor 11 that generates high-temperature, high-pressure compressed air CA by compressing air A, a combustor 12 according to any one of the first to sixth aspects that generates high-temperature, high-pressure combustion gas CG by supplying fuel gas FG to the compressed air CA and combusting it, and a turbine 13 that is driven by the combustion gas CG. This makes it possible to suppress the generation of CO by improving the combustibility of the first-stage combustion gas FG, and to suppress the generation of NOx by improving the mixing efficiency of the first-stage combustion gas CG and the second-stage air-fuel mixture MG.

[0075] In the above-described embodiment, the pilot combustion burner 53 and the plurality of main combustion burners 54 are provided as the fuel supply unit 22, but the present invention is not limited to this configuration. [Explanation of symbols]

[0076] 10. Gas turbine 11 Compressor 12, 12A Combustor (gas turbine combustor) 13 Turbine 14 Rotation axis 21 Combustor body 22 Fuel supply section 23, 23A Premixed gas supply unit 24,24A Deflection member 31 Outer cylinder 32 Inner cylinder 33 Tail tube (combustion tube) 33a Inner wall surface 41 Top Hat Club 42 Connecting member 43 Support member 44,45 Air passage 53 Pilot combustion burner 54 Main combustion burner 55 Pilot Cone 56 Pilot nozzle 57 Pillars 58 Main nozzle 61,61A Housing 62 Spout hole (spout part) 63 Air Nozzle 64 Fuel Nozzle 65 Guide part 71 Acoustic damper A. Air CA Compressed Air FG Fuel Gas MG mixture CG burning gas EG exhaust gas O1,O2 axis center

Claims

1. a cylindrical combustion tube; a fuel supply unit that supplies fuel gas to the inside of the combustion tube; a premixed gas supply unit that is located downstream of the fuel supply unit in the direction of flow of the combustion gas and supplies a premixed gas obtained by mixing fuel and air into the combustion tube; a deflection member that protrudes from an inner wall surface of the combustion liner toward a downstream side in a flow direction of the combustion gas at a center side of the combustion liner between the fuel supply unit and the premixed gas supply unit and deflects the flow of the combustion gas; Equipped with The deflection member is provided as a separate member from the combustion cylinder, and has an attachment portion and a deflection portion, the attachment portion is fixed to the inner wall surface of the combustion cylinder, and the deflection portion protrudes so as to be separated from the inner wall surface of the combustion cylinder. Gas turbine combustor.

2. The premixed gas supply unit has a jetting portion for jetting the premixed gas into the combustion liner, the jetting portion being disposed along an inner wall surface of the combustion liner. The gas turbine combustor according to claim 1 .

3. the premixed gas supply unit is disposed such that an ejection portion for ejecting the premixed gas into the inside of the combustion liner protrudes from an inner wall surface of the combustion liner into the inside of the combustion liner; The gas turbine combustor according to claim 1 .

4. a distance L between the deflection member and the premixed gas supply portion in the axial direction of the combustion liner is shorter than 10 times a radial length H1 of the deflection member protruding from an inner wall surface of the combustion liner; The gas turbine combustor according to any one of claims 1 to 3.

5. a plurality of the premixed gas supply units are arranged at intervals in the circumferential direction of the combustion liner, and the deflection member is arranged at a position facing the plurality of premixed gas supply units in the axial direction of the combustion liner; The gas turbine combustor according to claim 1 .

6. The premixed gas supply unit is arranged in plurality at intervals in the axial direction of the combustion liner. The gas turbine combustor according to claim 1 .

7. A compressor that generates high-temperature, high-pressure compressed air by compressing air; the gas turbine combustor according to claim 1, wherein a fuel gas is supplied to the compressed air and combusted to generate high-temperature and high-pressure combustion gas; a turbine driven by the combustion gas; A gas turbine comprising:

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