Gas turbine combustor and gas turbine

Abstract

A gas turbine combustor according to at least one embodiment of the present disclosure comprises a plurality of narrowing parts that protrude toward the inside of a combustion cylinder. The center axis of the combustion cylinder includes an upstream center axis, which linearly extends in an upstream region of the combustion cylinder, and extends in an ejection part in a direction that is different from the extension direction of the upstream center axis. The combustion cylinder includes a first region and a second region that are divided by a virtual plane which includes the center axis from the upstream region to the ejection part and which is orthogonal to a virtual flat plane that includes the center axis from the upstream region to the ejection part. A straight line obtained by extending the upstream center axis passes through the first region in the ejection part. The total value of projection areas of the narrowing parts present in the second region as viewed from the extension direction of the center axis is larger than the total value of projection areas of the narrowing parts present in the first region as viewed from the extension direction of the center axis.

Description

[Technical Field]

[0001] The present disclosure relates to gas turbine combustors and gas turbines. This application claims priority based on Japanese Patent Application No. 2022-039453, filed with the Japan Patent Office on March 14, 2022, the contents of which are incorporated herein by reference. [Background technology]

[0002] A combustor used in a gas turbine, for example, includes a fuel nozzle capable of supplying fuel and a combustion liner having an internal combustion region through which combustion gas generated by combustion of the fuel can flow. The fuel supplied from the fuel nozzle is burned to become fuel gas, which drives a turbine provided downstream via the combustion region of the combustion liner.

[0003] In the combustor of this type of gas turbine, the temperature of the combustion gas near the inner wall surface of the combustion liner is lower than that at the center, which delays the timing at which carbon monoxide (CO) contained in the combustion gas chemically reacts to carbon dioxide (CO2), and this can result in increased generation of carbon monoxide.To address this issue, Patent Document 1 discloses that by providing a throttle member on the inner wall surface of the combustion liner of the combustor, the combustion gas near the inner wall surface is directed toward the center, where it mixes with the high-temperature combustion gas, promoting combustion and suppressing the generation of carbon monoxide. [Prior art documents] [Patent documents]

[0004] [Patent Document 1] International Publication No. 2011 / 058931 Summary of the Invention [Problem to be solved by the invention]

[0005] When a gas turbine is operating at a partial load, the temperature of the combustion gas is relatively low, and the amount of carbon monoxide contained in the combustion gas is higher than when the gas turbine is operating at rated load. This makes it difficult to lower the lower limit of the operating load of the gas turbine.

[0006] As a result of extensive research, the inventors have found that the shape of the downstream region of the combustion liner causes a deviation in the temperature of the combustion gas in the circumferential direction. Therefore, it is desirable to suppress this deviation in the temperature of the combustion gas in order to suppress the generation of carbon monoxide.

[0007] In view of the above circumstances, at least one embodiment of the present disclosure has an object to provide a gas turbine combustor and a gas turbine that can suitably suppress the generation of carbon monoxide even during partial load operation of the gas turbine. [Means for solving the problem]

[0008] (1) A gas turbine combustor according to at least one embodiment of the present disclosure includes: a combustion tube having a combustion region formed inside through which combustion gas generated by combustion of fuel can flow, and an ejection portion formed at a downstream end thereof as an ejection port for the combustion gas; a plurality of throttle portions provided at intervals in the circumferential direction on the inner wall surface of the combustion cylinder, the throttle portions protruding toward the inside of the combustion cylinder; Equipped with a central axis of the combustion liner includes an upstream central axis that extends linearly in an upstream region of the combustion liner, and extends in a direction different from the extending direction of the upstream central axis at the outlet portion; the combustion liner includes a first region and a second region, the first region and the second region being separated by a virtual plane that is perpendicular to a virtual plane that includes the central axis from the upstream region to the outlet portion, and that includes the central axis from the upstream region to the outlet portion; a straight line extending from the upstream central axis passes through the first region in the outlet portion, The sum of the projected areas of the narrowed portions in the second region when viewed from the direction in which the central axis extends is greater than the sum of the projected areas of the narrowed portions in the first region when viewed from the direction in which the central axis extends.

[0009] (2) A gas turbine combustor according to at least one embodiment of the present disclosure, a combustion tube having a combustion region formed inside through which combustion gas generated by combustion of fuel can flow, and an ejection portion formed at a downstream end thereof as an ejection port for the combustion gas; a plurality of throttle portions provided at intervals in the circumferential direction on the inner wall surface of the combustion cylinder, the throttle portions protruding toward the inside of the combustion cylinder; Equipped with a central axis of the combustion liner includes an upstream central axis that extends linearly in an upstream region of the combustion liner, and extends in a direction different from the extending direction of the upstream central axis at the outlet portion; the combustion liner includes a first region and a second region, the first region and the second region being separated by a virtual plane that is perpendicular to a virtual plane that includes the central axis from the upstream region to the outlet portion, and that includes the central axis from the upstream region to the outlet portion; From a position corresponding to a reference position on the upstream central axis Spout a distance along the inner wall surface in the virtual plane to the outlet is shorter in the second region than in the first region; The sum of the projected areas of the narrowed portions in the second region when viewed from the direction in which the central axis extends is greater than the sum of the projected areas of the narrowed portions in the first region when viewed from the direction in which the central axis extends.

[0010] (3) A gas turbine according to at least one embodiment of the present disclosure includes: a compressor for generating compressed air; a gas turbine combustor having the configuration (1) or (2) above; a turbine that is rotationally driven by combustion gas generated by the gas turbine combustor; Equipped with. [Effects of the Invention]

[0011] According to at least one embodiment of the present disclosure, it is possible to provide a gas turbine combustor and a gas turbine that can suitably suppress the generation of carbon monoxide even during partial load operation of the gas turbine. [Brief explanation of the drawings]

[0012] [Figure 1] FIG. 1 is a diagram illustrating a schematic configuration of a gas turbine according to an embodiment of the present disclosure. [Figure 2] FIG. 2 is a diagram for explaining the configuration of a combustor and its surroundings of a gas turbine. [Figure 3A] FIG. 2 is a cross-sectional view showing an example of the shape of a combustion liner. [Figure 3B] 3B is a schematic diagram showing the positional relationship between the shape of the inner wall surface on the upstream side of the combustion liner shown in FIG. 3A and the shape of the inner circumferential surface of the ejection port. FIG. [Figure 4A] FIG. 10 is a cross-sectional view showing another example of the shape of the combustion liner. [Figure 4B] 4B is a schematic diagram showing the positional relationship between the shape of the inner wall surface on the upstream side of the combustion liner shown in FIG. 4A and the shape of the inner circumferential surface of the ejection port. FIG. [Figure 5] 1 is a view of an example of a throttle member having a throttle portion according to some embodiments, viewed from the downstream axial side. FIG. [Figure 6] FIG. 6 is a perspective view of a part of the diaphragm member shown in FIG. 5. [Figure 7A] FIG. 2 is a schematic view of a combustion liner developed in the circumferential direction to show an example of the arrangement position of a throttle portion. [Figure 7B] FIG. 10 is a schematic view of the combustion liner developed in the circumferential direction to show another example of the arrangement position of the throttle portion. [Figure 7C] FIG. 10 is a schematic view of the combustion liner developed in the circumferential direction to show yet another example of the arrangement position of the throttle portion. [Figure 7D] FIG. 10 is a schematic view of the combustion liner developed in the circumferential direction to show yet another example of the arrangement position of the throttle portion. [Figure 7E]FIG. 10 is a schematic view of the combustion liner developed in the circumferential direction to show yet another example of the arrangement position of the throttle portion. [Figure 7F] FIG. 10 is a schematic view of the combustion liner developed in the circumferential direction to show yet another example of the arrangement position of the throttle portion. [Figure 8] FIG. 8 is a view taken along the arrows VIII-VIII in FIG. 3A. [Figure 9] FIG. 10 is a diagram showing an example of a configuration for cooling a throttle portion. [Figure 10A] 10A and 10B are diagrams for explaining variations in the shape of the narrowed portion. [Figure 10B] 10A and 10B are diagrams for explaining variations in the shape of the narrowed portion. [Figure 10C] 10A and 10B are diagrams for explaining variations in the shape of the narrowed portion. DETAILED DESCRIPTION OF THE INVENTION

[0013] Hereinafter, several embodiments of the present disclosure will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of components described as embodiments or shown in the drawings are merely illustrative examples and are not intended to limit the scope of the present disclosure. For example, expressions expressing relative or absolute arrangement such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" not only express such an arrangement exactly, but also express a state in which there is a relative displacement with a tolerance or an angle or distance to the extent that the same function is obtained. For example, expressions such as "identical," "equal," and "homogeneous" that indicate that something is in an equal state not only indicate a state of strict equality, but also indicate a state in which there is a tolerance or a difference to the extent that the same function is obtained. For example, expressions representing shapes such as a square shape or a cylindrical shape not only represent shapes such as a square shape or a cylindrical shape in the strict geometric sense, but also represent shapes including uneven portions, chamfered portions, etc., to the extent that the same effect can be obtained. On the other hand, the expressions "comprise," "include," "have," "includes," or "have" of one element are not exclusive expressions that exclude the presence of other elements.

[0014] FIG. 1 is a diagram schematically illustrating a configuration of a gas turbine according to an embodiment of the present disclosure. FIG. 2 is a diagram for explaining the configuration of the vicinity of a combustor of a gas turbine.

[0015] (Regarding Gas Turbine 1) 1, the gas turbine 1 according to this embodiment includes a compressor 2, a combustor (gas turbine combustor) 3, and a turbine 4, and drives an external device such as a generator G. In the case of a gas turbine 1 for power generation, the generator G is connected to a rotor 5. The compressor 2 takes in atmospheric air, which is external air, compresses it, and supplies the compressed air to one or more combustors 3.

[0016] The combustor 3 generates high-temperature gas (combustion gas) by burning fuel supplied from the outside using air compressed by the compressor 2. In the gas turbine 1 according to one embodiment, a plurality of combustors 3 are arranged in an annular shape around the rotor 5. In the gas turbine 1 according to one embodiment, oil fuel (liquid fuel), which is a flammable liquid, is used as fuel, but gaseous fuel, which is a flammable gas, may also be used as fuel. The turbine 4 receives a supply of high-temperature combustion gas generated by the combustor 3 to generate a rotational driving force, and outputs the generated rotational driving force to the compressor 2 and external devices.

[0017] As shown in FIG. 2, a combustor installation space 8 for the combustor 3 is provided within the casing 7. The combustor installation space 8 is located between the outlet of the compressor 2 on the axially upstream side and the inlet of the turbine 4 on the axially downstream side. The combustor 3 is disposed in the combustor installation space 8, and compressed air flows into the combustor 3 from one end side. Meanwhile, fuel is supplied to the combustor 3 from the outside, and the fuel and air are mixed to generate high-temperature combustion gas, which then rotates and drives the turbine 4 located downstream.

[0018] More specifically, the combustor 3 according to some embodiments has a nozzle unit 10 and a combustion liner 20. The combustion liner 20 includes an inner liner 12 and a transition piece 14. Note that the inner liner 12 and the transition piece 14 may be integrally formed. The combustion liner 20 has an internal combustion chamber 18 in which fuel injected from the main nozzle 64 and the pilot nozzle 54 is combusted. That is, the fuel is mixed with compressed air supplied from the compressor 2 in a combustion region within the combustion liner 20 and then combusted to generate combustion gas. The combustion gas is supplied to the turbine 4 via the combustion liner 20. The nozzle section 10 has a pilot burner 50 and a plurality of main burners (premixed combustion burners) 60 .

[0019] The pilot burner 50 is disposed along the central axis AX of the combustion liner 20. A plurality of main burners 60 are arranged in the circumferential direction of the combustion liner 20 at intervals so as to surround the pilot burner 50. The pilot burner 50 has a pilot nozzle 54 connected to the fuel port 52, a pilot nozzle cylinder 56 arranged to surround the pilot nozzle 54, and a swirler (not shown) provided on the outer periphery of the pilot nozzle 54. The main burner 60 has a main nozzle 64 connected to the fuel port 62, a main nozzle cylinder 66 arranged to surround the main nozzle 64, and a swirler (not shown) provided on the outer periphery of the main nozzle 64.

[0020] In the combustor 3 having the above configuration, compressed air generated by the compressor 2 is supplied into the combustor installation space 8 and further flows from the combustor installation space 8 into the main nozzle cylinder 66. This compressed air and fuel supplied from the fuel port 62 are premixed in the main nozzle cylinder 66. At this time, the premixed air-fuel mixture forms a swirling flow mainly due to a swirler (not shown) and flows into the inner cylinder 12. In addition, the compressed air and fuel injected from the pilot burner 50 via the fuel port 52 are mixed and ignited by a pilot light (not shown), causing combustion, generating combustion gas. At this time, a portion of the combustion gas diffuses to the surroundings along with the flame, igniting and burning the premixed air-fuel flowing into the inner cylinder 12 from each main burner 60. In other words, the pilot flame of the pilot fuel injected from the pilot burner 50 can provide flame stabilization for stable combustion of the premixed air-fuel from the main burner 60.

[0021] For convenience of explanation, the expressions upstream, downstream, upstream side, downstream side, etc. used in the following explanation are based on the flow direction of the combustion gas flowing inside the combustion liner 20. In other words, the side where the fuel nozzles (pilot nozzle 54, main nozzle 64) are provided relative to the combustion liner 20 is referred to as the upstream side, and the side where the combustion liner 20 is provided relative to the fuel nozzles is referred to as the downstream side. In addition, the direction along the central axis AX of the combustion liner 20 is also simply referred to as the axial direction, the circumferential direction centered on the central axis AX is also simply referred to as the circumferential direction, and the radial direction centered on the central axis AX is also simply referred to as the radial direction. Furthermore, the main flow of the combustion gas flowing inside the combustion tube 20 will be referred to as the "main flow" as appropriate.

[0022] FIG. 3A is a cross-sectional view showing an example of the shape of a combustion liner. FIG. 3B is a schematic diagram showing the positional relationship between the shape of the inner wall surface on the upstream side of the combustion liner and the shape of the inner circumferential surface of the outlet when the combustion liner shown in FIG. 3A is viewed from the downstream side along the first central axis on the upstream side of the combustion liner. FIG. 4A is a cross-sectional view showing another example of the shape of the combustion liner. FIG. 4B is a schematic diagram showing the positional relationship between the shape of the inner wall surface on the upstream side of the combustion liner and the shape of the inner circumferential surface of the outlet when the combustion liner shown in FIG. 4A is viewed from the downstream side along the first central axis on the upstream side of the combustion liner.

[0023] 3A and 4A, in a combustor 3 according to some embodiments, a combustion liner 20 has an outlet portion 20e that forms an outlet port 20d for combustion gas formed at the downstream end. A first central axis AX1 on the upstream side of the combustion liner 20 and a second central axis AX2 in the outlet portion 20e extend in different directions. 3A and 4A show cross sections appearing on a virtual plane Pv1 including the central axis AX from the upstream region of the combustion liner 20 to the ejection portion 20e.

[0024] As shown in FIGS. 3A and 4A, in the combustor 3 according to some embodiments, the inner cylinder 12 has an inner wall surface 12i that is the inner circumferential surface of a cylinder centered on a first central axis line AX1 that extends linearly. 3A and 4A, in the combustor 3 according to some embodiments, the transition piece 14 has a curved shape such that the extending direction of the central axis AX at least at the connection portion with the inner cylinder 12 differs from the central axis AX (second central axis AX2) at the discharge portion 20e. The transition piece 14 is formed such that the cross-sectional shape perpendicular to the central axis AX gradually changes from a circular shape at the connection portion with the inner cylinder 12 to a partial annular shape at the discharge portion 20e along the central axis AX. As shown in FIGS. 3A and 4A , in the combustor 3 according to some embodiments, the transition piece 14 changes to a flattened shape in a cross section parallel to the imaginary plane Pv1, such that the distance between the central axis AX and the inner wall surface 14i gradually decreases toward the downstream side.

[0025] 3A and 4A, in the combustor 3 according to some embodiments, the transition piece 14 includes a first region R1 and a second region R2, with a boundary being defined by a virtual plane Pv2, which is orthogonal to the above-described virtual plane Pv1 and includes a central axis AX from the upstream region to the discharge portion 20e. In FIGS. 3A and 4A, the virtual plane Pv2 includes the central axis AX from the upstream region to the discharge portion 20e and is orthogonal to the paper surface of FIGS. 3A and 4A. That is, in FIGS. 3A and 4A, the central axis AX corresponds to a cross section of the virtual plane Pv2 that appears on the paper surface of FIGS. 3A and 4A. Here, the first region R1 is one of the two regions separated by the central axis AX in Figures 3A and 4A, through which a straight line L1 extending downstream from the first central axis AX1 (upstream central axis) on the upstream side of the combustion tube 20 passes in the discharge section 20e (see Figures 3B and 4B). 3A and 4A, the first region R1 is one of the two regions separated by the central axis AX from a position corresponding to the reference position Pr on the first central axis AX1. Spout This is the region that is the longest distance along the inner wall surface 20i within the virtual plane Pv1 to the outlet 20d.

[0026] 3A and 4A, the inner wall surface 20i of the combustion liner 20 in the first region R1 shown in FIGS. 3A and 4A is measured from a position corresponding to the reference position Pr on the first central axis AX1. Spout The distance X1 traced to the outlet 20d is the distance from the position corresponding to the reference position Pr on the first central axis AX1 along the inner wall surface 20i of the combustion liner 20 in the second region R2 shown in FIGS. 3A and 4A. Spout This is longer than the distance X2 traveled to the outlet 20d. The reference position Pr on the first center axis AX1 may be, for example, the tip position of the fuel nozzle (pilot nozzle 54, main nozzle 64) on the first center axis AX1, or may be the position of the upstream or downstream end of the inner cylinder 12.

[0027] In the combustor 3 shown in FIG. 3A, the first region R1 is a region above the central axis AX in the drawing, and the second region R2 is a region below the central axis AX in the drawing. In the combustor 3 shown in FIG. 4A, the first region R1 is a region below the central axis AX in the drawing, and the second region R2 is a region above the central axis AX in the drawing.

[0028] 3A and 4A, in the combustor 3 according to some embodiments, a plurality of throttle portions 71 are provided at intervals in the circumferential direction on the inner wall surface 20i of the combustion liner 20, protruding radially inward of the combustion liner 20. The throttle portions 71 are intended to guide the relatively low-temperature combustion gas flowing near the inner wall surface 20i of the combustion liner 20 toward the center of the combustion liner 20. This allows the relatively low-temperature combustion gas flowing near the inner wall surface 20i to mix with the relatively high-temperature combustion gas flowing through the center of the combustion liner 20, thereby promoting combustion. The throttle portions 71 will be described in detail later.

[0029] (Issues facing conventional gas turbine combustors) In conventional gas turbine combustors, the temperature of the combustion gas near the inner wall of the combustion liner is lower than that at the center, which delays the timing at which carbon monoxide (CO) contained in the combustion gas chemically reacts to carbon dioxide (CO2), resulting in increased carbon monoxide generation. In particular, during partial load operation of the gas turbine, when the temperature of the combustion gas is relatively low, the amount of carbon monoxide contained in the combustion gas increases compared to rated operation. This makes it difficult to lower the lower limit of the gas turbine's operating load.

[0030] As a result of extensive research, the inventors have found that the shape of the downstream region of the combustion liner causes a deviation in the temperature of the combustion gas in the circumferential direction. Specifically, it was found that if the throttling section 71, which will be described in detail later, were not provided, the temperature of the combustion gas would tend to be lower in the relatively downstream region of the transition piece 14 in the second region R2, which is relatively radially outer than in the first region R1.

[0031] Therefore, in the combustor 3 according to some embodiments, as will be described in detail later, the total value S2 of the projected areas of the throttling portions 71 present in the second region R2 when viewed from the extending direction of the central axis line AX is made larger than the total value S1 of the projected areas of the throttling portions 71 present in the first region R1 when viewed from the extending direction of the central axis line AX. In this way, by making the total value S2 of the projected areas of the throttling portions 71 in the second region R2 when viewed in the direction to which the central axis AX extends larger than the total value S1 of the projected areas of the throttling portions 71 in the first region R1 when viewed in the direction to which the central axis AX extends, the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 is more easily guided toward the center of the combustion liner 20 in the second region R2 than in the first region R1. As a result, the relatively low-temperature combustion gas in the second region R2 mixes with the high-temperature combustion gas, further promoting combustion. Therefore, the difference in temperature between the combustion gas in the second region R2 and the combustion gas in the first region R1 can be reduced, and carbon monoxide generation can be effectively suppressed even during partial load operation of the gas turbine 1.

[0032] Furthermore, in the gas turbine 1 including the combustor 3 according to some embodiments, the combustion gas having a relatively low temperature in the second zone R2 is mixed with the combustion gas having a high temperature, thereby further promoting combustion. Therefore, the difference in temperature between the combustion gas in the second zone R2 and the combustion gas in the first zone R1 can be reduced, and the generation of carbon monoxide can be suitably suppressed even during partial load operation of the gas turbine 1.

[0033] The projected area of ​​each of the throttling sections 71 when viewed from the extension direction of the central axis AX is the projected area of ​​each of the throttling sections 71 when viewed from the tangential direction of the central axis AX at a position on the central axis AX that is closest to each of the throttling sections 71. In the following description, the projected area of ​​the throttle portion 71 when viewed from the extending direction of the central axis line AX will also be simply referred to as the projected area.

[0034] (Details of the throttle portion 71) FIG. 5 is a view of an example of a throttle member 70 having a throttle portion 71 according to some embodiments, as viewed from the downstream side in the axial direction. FIG. 6 is a perspective view of a part of the diaphragm member 70 shown in FIG. 5 and 6, a throttle member 70 according to some embodiments has an annular ring portion 72 and throttle portions 71, which are multiple protrusions formed at intervals in the circumferential direction on the ring portion 72. In the throttle member 70 according to some embodiments, the throttle portions 71 have a shape in which protrusions protruding in the axial direction relative to the ring portion 72 are bent radially inward. 5, when the throttling member 70 is attached to the combustion liner 20, the two intersection positions between the throttling member 70 and the above-mentioned virtual plane Pv1 are defined as 0 degree and 180 degree angular positions in the circumferential direction. Of the intersection positions with the virtual plane Pv1, the angular position that exists in the first region R1 is defined as 0 degree, and the angular position that exists in the second region R2 is defined as 180 degree.

[0035] FIG. 7A is a schematic view of the combustion liner 20 developed in the circumferential direction to show an example of the arrangement position of the throttle portion 71, and shows the arrangement of the throttle portion 71 of the throttle member 70 shown in FIG. FIG. 7B is a schematic view of the combustion liner 20 developed in the circumferential direction to show another example of the arrangement position of the throttle portion 71. FIG. 7C is a schematic view in which the combustion liner 20 is developed in the circumferential direction to show yet another example of the arrangement position of the throttle portion 71. FIG. 7D is a schematic view in which the combustion liner 20 is developed in the circumferential direction to show yet another example of the arrangement position of the throttle portion 71. FIG. 7E is a schematic view in which the combustion liner 20 is developed in the circumferential direction to show yet another example of the arrangement position of the throttle portion 71. FIG. 7F is a schematic view of the combustion liner 20 developed in the circumferential direction to show yet another example of the arrangement position of the throttle portion 71.

[0036] Figures 7A to 7F show the relative axial and circumferential positions of the throttling portion 71 and the height of the throttling portion 71, i.e., the protruding heights h1 and h2 radially inward from the inner wall surface 20i of the combustion liner 20 (see Figures 3A and 4A). In Figures 7A to 7F, the position of the left end of the constriction portion 71 in the left-right direction shown in the figure represents the axial position of the constriction portion 71, and the size of the constriction portion 71 in the left-right direction shown in the figure represents the protruding heights h1 and h2 of the constriction portion 71 (see Figures 3A and 4A).

[0037] In all of the examples shown in Figures 7A to 7F, the total value S2 of the projected areas of the throttling portions 71 present in the second region R2 is greater than the total value S1 of the projected areas of the throttling portions 71 present in the first region R1. For example, in the example shown in Figure 7A, the number of throttling sections 71 (hereinafter also referred to as first throttling sections 711) arranged in the first region R1 is the same as the number of throttling sections 71 (hereinafter also referred to as second throttling sections 712) arranged in the second region R2, but each throttling section 71 is formed so that the protruding height h2 of the second throttling section 712 is higher than the protruding height h1 of the first throttling section 711.

[0038] For example, in the example shown in Figure 7B, the number of first throttling portions 711 and the number of second throttling portions 712 are the same, but each throttling portion 71 is formed so that the circumferential size w2 of the second throttling portion 712 is larger than the circumferential size w1 of the first throttling portion 711.

[0039] For example, in the example shown in Figures 7C and 7D, the projected area of ​​each of the first throttling sections 711 and the projected area of ​​each of the second throttling sections 712 are the same, but by further arranging the second throttling section 712 at a different axial position in the second region, the total projected area S2 of the throttling sections 71 present in the second region R2 is configured to be larger than the total projected area S1 of the throttling sections 71 present in the first region R1. In the example shown in FIG. 7C, the second throttle portion 712 arranged on the axially upstream side and the second throttle portion 712 arranged on the axially downstream side are arranged at the same circumferential position. In the example shown in FIG. 7D, the second throttle portion 712 arranged on the axially upstream side and the second throttle portion 712 arranged on the axially downstream side are arranged at different circumferential positions.

[0040] 7E and 7F, each of the throttling portions 71 is formed so that the protruding height h2 of the second throttling portion 712 is greater than the protruding height h1 of the first throttling portion 711. In addition, in the example shown in Figures 7E and 7F, a second throttling portion 712 is further disposed at a different position in the axial direction in the second region. In the example shown in FIG. 7E, the second throttle portion 712 arranged on the axially upstream side and the second throttle portion 712 arranged on the axially downstream side are arranged at the same circumferential position. In the example shown in FIG. 7F, the second throttle portion 712 arranged on the axially upstream side and the second throttle portion 712 arranged on the axially downstream side are arranged at different circumferential positions.

[0041] For example, in the examples shown in FIGS. 7C to 7F, the second throttle portion 712 on the axially upstream side is disposed on the inner cylinder 12, and the second throttle portion 712 on the axially downstream side is disposed on the inner cylinder 12. side The second throttle portion 712 is preferably disposed in the transition piece 14 (see FIGS. 3A and 4A).

[0042] In this manner, in the combustor 3 according to some embodiments, as shown in, for example, Figures 7A, 7E, and 7F, the radial height (protruding height h2) of the combustion liner 20 for at least one of the second throttling sections 712 may be greater than the radial height (protruding height h1) for the first throttling section 711. This makes it easier to guide the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 in the second region R2 toward the center of the combustion liner 20, and makes it easier to mix with the high-temperature combustion gas and promote combustion.

[0043] In some embodiments of the combustor 3, for example, in the examples shown in Figures 7A, 7E, and 7F, the protruding height h2 of at least one of the second throttling portions 712 may be 1.5 to 3.0 times the protruding height h1 of the first throttling portion 711.

[0044] The higher the protruding height h2 of the second throttling portion 712, the easier it is to guide the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20, but there is a risk that this will disrupt the main flow of the combustion gas and have a negative impact on combustion efficiency. In the examples shown in Figures 7A, 7E, and 7F, the protruding height h2 of at least one of the second throttling sections 712 is set to be 1.5 to 3.0 times the protruding height h1 of the first throttling section 711, thereby suppressing the impact on the mainstream flow of the combustion gas and guiding the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 in the second region R2 toward the center of the combustion liner 20, where it mixes with the high-temperature combustion gas and promotes combustion.

[0045] In some embodiments of the combustor 3, as shown in FIG. 7B, for example, the circumferential size w2 of at least one of the second throttling sections 712 may be larger than the circumferential size w1 of the first throttling section 711. This makes it easier to guide the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 in the second region R2 toward the center of the combustion liner 20, and makes it easier to mix with the high-temperature combustion gas and promote combustion.

[0046] 3A and 4A , in the combustor 3 according to some embodiments, the upstream surface of the throttling portion 71 may be an inclined surface 71u that is inclined so as to approach the central axis line AX toward the downstream side of the combustion liner 20. An angle θ2 at which the inclined surface 71u of at least one of the second throttling portions 712 is inclined with respect to the inner wall surface 20i may be larger than an angle θ1 at which the inclined surface 71u of the first throttling portion 711 is inclined with respect to the inner wall surface 20i.

[0047] The greater the angle of inclination of the inclined surface 71u relative to the inner wall surface 20i, the easier it is to guide the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 toward the center of the combustion liner 20. By making the angle θ2 at which the inclined surface 71u of at least one of the second throttling sections 712 is inclined relative to the inner wall surface 20i larger than the angle θ1 at which the inclined surface 71u of the first throttling section 711 is inclined relative to the inner wall surface 20i, it becomes easier to guide the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 toward the center of the combustion tube 20, making it easier to mix with the high-temperature combustion gas and promote combustion.

[0048] In the combustor 3 according to some embodiments, the angle θ2 at which the inclined surface 71u of at least one of the second throttle portions 712 is inclined with respect to the inner wall surface 20i may be equal to or greater than 50 degrees and equal to or less than 85 degrees.

[0049] The greater the angle at which the inclined surface 71u is inclined relative to the inner wall surface 20i, the easier it is to guide the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20, but there is a risk that this will disrupt the main flow of the combustion gas and have a negative impact on combustion efficiency. By setting the angle θ2 at which the inclined surface 71u of at least one of the second constriction sections 712 is inclined relative to the inner wall surface 20i to be greater than or equal to 50 degrees and less than or equal to 85 degrees, the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 in the second region R2 can be guided toward the center of the combustion tube 20, where it can be mixed with the high-temperature combustion gas and combustion can be promoted, while suppressing the impact on the mainstream flow of the combustion gas.

[0050] FIG. 8 is a view taken along the line VIII-VIII in FIG. 3A, and the transition piece 14 is not shown. 8, the combustor 3 according to some embodiments includes a plurality of main nozzles 64 arranged at intervals in the circumferential direction inside the combustion liner 20 (inner liner 12). At least one of the throttle portions 71 is preferably located between two of the main nozzles 64 adjacent to each other in the circumferential direction when viewed from the direction in which the central axis line AX extends.

[0051] In the region between two circumferentially adjacent main nozzles 64 as viewed in the direction in which the central axis AX extends, the temperature of the combustion gas tends to be lower than in the region overlapping with the main nozzles 64 as viewed in the direction in which the central axis AX extends. By arranging at least one of the constriction sections 71 so as to be located between two circumferentially adjacent main nozzles 64 when viewed from the direction in which the central axis line AX extends, the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 at a position where the temperature of the combustion gas tends to be low when viewed from the direction in which the central axis line AX extends can be guided toward the center of the combustion liner 20, where it can be mixed with the high-temperature combustion gas to promote combustion.

[0052] In some embodiments of the combustor 3, as shown in, for example, FIGS. 3A, 4A, and 7C to 7F, the second throttling portion 712 may be provided at a first position P1 along the central axis AX and at a second position P2 along the central axis AX that is different from the first position P1 (downstream of the first position P1). As a result, the second throttling section 712 provided at the first position P1 and the second position P2 can guide the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20, so that in the second region R2, the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 can be mixed with more high-temperature combustion gas, promoting combustion.

[0053] In the combustor 3 according to some embodiments, as shown in, for example, FIGS. 3A and 4A , the combustion liner 20 may include an inner liner 12 and a transition piece 14 disposed downstream of the inner liner 12. The first position P1 may be a position within the inner liner 12. The second position P2 may be a position within the transition piece 14.

[0054] 3A and 4A, the combustor 3 according to some embodiments is configured such that a gap 13 is formed at the connection between the inner tube 12 and the transition piece 14, and compressed air is introduced into the combustion tube 20 from this gap 13 as cooling air. Therefore, by providing the throttling portion 71 (second throttling portion 712) on the inner wall surface 14i of the transition piece 14, a decrease in the temperature of the combustion gas can be suppressed in the region downstream of the second position P2.

[0055] In some embodiments of the combustor 3, for example, as shown in FIGS. 7D and 7F, the second throttling portion 712 provided at the second position P2 may be disposed at a different circumferential position from the second throttling portion 712 provided at the first position P1.

[0056] As a result of careful consideration by the inventors, when the second throttle portion 712 provided at the second position P2 is disposed at a different circumferential position from the second throttle portion 712 provided at the first position P1, the second throttle portion 712 provided at the second position P2 has a larger circumferential width than when the second throttle portion 712 provided at the first position P1 is disposed at the same circumferential position. Ta It has been found that the second throttle portion 712 enhances the effect of guiding the combustion gases. By making the circumferential position of the second throttling portion 712 provided at the second position P2 different from that of the second throttling portion 712 provided at the first position P1, the effectiveness of guiding the combustion gas by the second throttling portion 712 provided at the second position P2 can be enhanced.

[0057] (Cooling of the throttle portion 71) FIG. 9 is a diagram showing an example of a configuration for cooling the throttle portion 71, and is a schematic cross-sectional view of the vicinity of the throttle portion 71 as viewed from the circumferential direction. In the combustor 3 according to some embodiments, the combustion liner 20 may have a through-hole 23 that opens at a position that overlaps with the throttling portion 71 when viewed radially outward from the central axis AX, i.e., at a position that overlaps with the throttling portion 71 in the axial direction. This allows the air (compressed air) flowing outside the combustion liner 20 to flow toward the throttle portion 71 via the through holes 23, thereby cooling the throttle portion 71 that is exposed to high-temperature combustion gas. In addition, the through holes 23 may be provided to correspond to all of the throttling sections 71, or may be provided to correspond to only the second throttling sections 712 whose respective projected areas are larger than those of the first throttling sections 711, at least among the second throttling sections 712.

[0058] (Variations in the shape of the throttle portion 71) 10A, 10B, and 10C are diagrams for explaining variations in the shape of the throttle portion 71, and are diagrams that schematically show the shape of the throttle portion 71 when viewed from the axial direction. 10A and 10B, a protrusion 71b that protrudes further radially inward may be provided on a radially inner end 71a of the throttle portion 71. Note that the protrusion 71b may be provided in one location as shown in Fig. 10A, or may be provided in multiple locations (two locations in the example shown in Fig. 10B) spaced apart in the circumferential direction as shown in Fig. 10B. In this way, by providing a protrusion 71b that protrudes further radially inward at the radially inner end 71a of the constriction section 71, the number of vortices of the combustion gas generated by guiding the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20 can be increased, and the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 can be mixed with more high-temperature combustion gas, promoting combustion.

[0059] 10C , for example, through-holes 71c penetrating in the axial direction may be provided in the constricted portion 71. This can suppress pressure loss of the combustion gas. Furthermore, since the effect of guiding the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 toward the center of the combustion liner 20 differs between the region where the through-holes 71c are provided in the circumferential direction and the region where the through-holes 71c are not provided, the number of vortices of the combustion gas generated by guiding the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 toward the center of the combustion liner 20 can be increased, and the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 can be mixed with more high-temperature combustion gas, promoting combustion.

[0060] The present disclosure is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments and appropriate combinations of these modifications. For example, with regard to the variations in shape and arrangement of the throttling portion 71 shown in Figures 7A to 7F, they may be appropriately combined so that the total value S2 of the projected area of ​​the throttling portion 71 present in the second region R2 is greater than the total value S1 of the projected area of ​​the throttling portion 71 present in the first region R1. Also, as shown in, for example, FIGS. 3A, 4A, and 7C to 7F, the second throttle portions 712 are provided in two rows in the axial direction, but three or more rows may be provided.

[0061] The contents described in each of the above embodiments can be understood, for example, as follows. (1) A gas turbine combustor (combustor 3) according to at least one embodiment of the present disclosure includes a combustion liner 20 having a combustion region formed therein through which combustion gas generated by combustion of fuel can flow, the combustion liner 20 having an ejection portion 20e forming an ejection port 20d for the combustion gas formed at a downstream end thereof, and a plurality of throttle portions 71 provided at an inner wall surface 20i of the combustion liner 20 at intervals in the circumferential direction and protruding toward an inside of the combustion liner 20. A central axis AX of the combustion liner 20 includes an upstream central axis (first central axis AX1) extending linearly in an upstream region of the combustion liner 20, and extends in a direction different from the extending direction of the upstream central axis (first central axis AX1) in the ejection portion 20e. The combustion liner 20 includes a first region R1 and a second region R2, with a boundary defined by a virtual plane Pv2, which is orthogonal to a virtual plane Pv1 including the central axis AX from the upstream region to the discharge portion 20e and which includes the central axis AX from the upstream region to the discharge portion 20e. A straight line L1 extending from the upstream central axis (first central axis AX1) passes through the first region R1 at the discharge portion 20e. A total value S2 of the projected areas of the throttling portions 71 (second throttling portions 712) in the second region R2 when viewed from the direction of extension of the central axis AX is greater than a total value S1 of the projected areas of the throttling portions 71 (first throttling portions 711) in the first region R1 when viewed from the direction of extension of the central axis AX.

[0062] According to the configuration (1) described above, the sum S2 of the projected areas of the throttle portions 71 (second throttle portions 712) present in the second region R2 when viewed in the direction to which the central axis AX extends is larger than the sum S1 of the projected areas of the throttle portions 71 (first throttle portions 711) present in the first region R1 when viewed in the direction to which the central axis AX extends. This makes it easier for the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 to be guided toward the center of the combustion liner 20 in the second region R2 than in the first region R1. As a result, the relatively low-temperature combustion gas in the second region R2 mixes with the high-temperature combustion gas, further promoting combustion. Therefore, the difference in temperature between the combustion gas in the second region R2 and the combustion gas in the first region R1 can be reduced, and carbon monoxide generation can be effectively suppressed even during partial load operation of the gas turbine 1.

[0063] (2) A gas turbine combustor (combustor 3) according to at least one embodiment of the present disclosure includes: a combustion liner 20 having a combustion region formed therein through which combustion gas generated by combustion of fuel can flow, the combustion liner 20 having an ejection portion 20e forming an ejection port 20d for the combustion gas formed at a downstream end thereof; and a plurality of throttle portions 71 provided at an inner wall surface 20i of the combustion liner 20 at intervals in the circumferential direction and protruding toward an inside of the combustion liner 20. A central axis AX of the combustion liner 20 includes an upstream central axis (first central axis AX1) extending linearly in an upstream region of the combustion liner 20, and extends in a direction different from the extending direction of the upstream central axis (first central axis AX1) in the ejection portion 20e. The combustion liner 20 includes a first region R1 and a second region R2, which are separated by a virtual plane Pv2 that is perpendicular to a virtual plane Pv1 that includes the central axis AX from the upstream region to the ejection portion 20e and that includes the central axis AX from the upstream region to the ejection portion 20e. Spout outlet 20d The distance traced along the inner wall surface 20i within the imaginary plane Pv1 to the second region R2 is shorter than that of the first region R1. The total value S2 of the projected areas of the throttle portions 71 (second throttle portions 712) present in the second region R2 when viewed from the extension direction of the central axis AX is greater than the total value S1 of the projected areas of the throttle portions 71 (first throttle portions 711) present in the first region R1 when viewed from the extension direction of the central axis AX.

[0064] According to the configuration (2) described above, the sum S2 of the projected areas of the throttle portions 71 (second throttle portions 712) present in the second region R2 when viewed in the direction to which the central axis AX extends is larger than the sum S1 of the projected areas of the throttle portions 71 (first throttle portions 711) present in the first region R1 when viewed in the direction to which the central axis AX extends. This makes it easier for the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 to be guided toward the center of the combustion liner 20 in the second region R2 than in the first region R1. As a result, the relatively low-temperature combustion gas in the second region R2 mixes with the high-temperature combustion gas, further promoting combustion. Therefore, the difference in temperature between the combustion gas in the second region R2 and the combustion gas in the first region R1 can be reduced, and carbon monoxide generation can be effectively suppressed even during partial load operation of the gas turbine 1.

[0065] (3) In some embodiments, in the configuration of (1) or (2) above, the radial height (protruding height h2) of the combustion tube 20 for at least one of the throttling sections 71 (second throttling section 712) present in the second region R2 may be higher than the radial height (protruding height h1) for the throttling section 71 (first throttling section 711) present in the first region R1.

[0066] According to the above configuration (3), the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 in the second region R2 can be more easily guided toward the center of the combustion liner 20, and is more easily mixed with the high-temperature combustion gas to promote combustion.

[0067] (4) In some embodiments, in the configuration of (3) above, the radial height (protruding height h2) of the combustion tube 20 for at least one of the throttling sections 71 (second throttling section 712) present in the second region R2 may be 1.5 to 3.0 times the radial height (protruding height h1) of the throttling section 71 (first throttling section 711) present in the first region R1.

[0068] The higher the radial height (protruding height h2) of the throttling portion 71 (second throttling portion 712) present in the second region R2, the easier it is to guide the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20, but there is a risk that this will disrupt the mainstream flow of the combustion gas and have a negative impact on combustion efficiency. According to the configuration (4) above, while suppressing the influence on the mainstream flow of the combustion gas, the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 in the second region R2 can be guided toward the center of the combustion liner 20, where it can be mixed with the high-temperature combustion gas to promote combustion.

[0069] (5) In some embodiments, in any of the configurations (1) to (4) above, the circumferential size w2 of the combustion tube 20 for at least one of the throttling sections 71 (second throttling section 712) present in the second region R2 may be larger than the circumferential size w1 of the throttling section 71 (first throttling section 711) present in the first region R1.

[0070] According to the configuration (5) above, the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 in the second region R2 can be more easily guided toward the center of the combustion liner 20, and is more easily mixed with the high-temperature combustion gas to promote combustion.

[0071] (6) In some embodiments, in any of the configurations (1) to (5) above, the upstream surface (inclined surface 71u) of the throttling portion 71 may be an inclined surface 71u that is inclined so as to approach the central axis AX toward the downstream side of the combustion liner 20. The angle θ2 at which the inclined surface 71u of at least one of the throttling portions 71 (second throttling portion 712) in the second region R2 is inclined relative to the inner wall surface 20i may be larger than the angle θ1 at which the inclined surface 71u of the throttling portion 71 (first throttling portion 711) in the first region R1 is inclined relative to the inner wall surface 20i.

[0072] The greater the angle of inclination of the inclined surface 71u relative to the inner wall surface 20i, the easier it is to guide the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 toward the center of the combustion liner 20. According to the above configuration (6), the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 in the second region R2 can be more easily guided toward the center of the combustion liner 20, and is more easily mixed with the high-temperature combustion gas to promote combustion.

[0073] (7) In some embodiments, in the configuration of (6) above, the angle θ2 at which the inclined surface 71u of at least one of the throttling portions 71 (second throttling portion 712) present in the second region R2 is inclined relative to the inner wall surface 20i may be greater than or equal to 50 degrees and less than or equal to 85 degrees.

[0074] The greater the angle at which the inclined surface 71u is inclined relative to the inner wall surface 20i, the easier it is to guide the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20, but there is a risk that this will disrupt the main flow of the combustion gas and have a negative impact on combustion efficiency. According to the configuration (7) above, while suppressing the influence on the mainstream flow of the combustion gas, the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 in the second region R2 can be guided toward the center of the combustion liner 20, where it can be mixed with the high-temperature combustion gas to promote combustion.

[0075] (8) In some embodiments, in any of the configurations (1) to (7) above, a plurality of fuel nozzles (main nozzles 64) may be provided inside the combustion liner 20 and spaced apart in the circumferential direction of the combustion liner 20. At least one of the throttle portions 71 may be located between two circumferentially adjacent fuel nozzles (main nozzles 64) when viewed from the direction in which the central axis line AX extends.

[0076] According to the configuration (8) above, the combustion gas flowing near the inner wall surface 20i of the combustion liner 20 at a position where the temperature of the combustion gas tends to be low when viewed from the extending direction of the central axis AX can be guided toward the center of the combustion liner 20, where it can be mixed with the high-temperature combustion gas to promote combustion.

[0077] (9) In some embodiments, in any of the configurations (1) to (8) above, the throttling portion 71 (second throttling portion 712) present in the second region R2 may be provided at a first position P1 along the central axis AX and at a second position P2 along the central axis AX that is different from the first position P1.

[0078] According to the configuration (9) above, the throttling section 71 (second throttling section 712) provided at the first position P1 and the second position P2 can guide the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 toward the center of the combustion tube 20, so that in the second region R2, the combustion gas flowing near the inner wall surface 20i of the combustion tube 20 can be mixed with more high-temperature combustion gas to promote combustion.

[0079] (10) In some embodiments, in the configuration of (9) above, the combustion liner 20 may include a first combustion liner (inner liner 12) and a second combustion liner (transition piece 14) disposed downstream of the first combustion liner (inner liner 12). The first position P1 may be a position within the first combustion liner (inner liner 12). The second position P2 may be a position within the second combustion liner (transition piece 14).

[0080] There are cases where cooling air is introduced from the connection between the first combustion liner (inner liner 12) and the second combustion liner (transition piece 14). In such a case, if the throttle section 71 (second throttle section 712) is provided on the inner wall surface 14i of the second combustion liner (transition piece 14), it is possible to suppress a decrease in the temperature of the combustion gas in the region downstream of the second position P2. According to the above configuration (10), it is possible to suppress a decrease in the temperature of the combustion gas in the region downstream of the second position P2.

[0081] (11) In some embodiments, in the configuration of (9) or (10) above, among the throttling portions 71 (second throttling portions 712) present in the second region R2, the throttling portion 71 (second throttling portion 712) provided at the second position P2 may be arranged in a different circumferential position from the throttling portion 71 (second throttling portion 712) among the throttling portions 71 (second throttling portions 712) present in the second region R2 that is provided at the first position P1.

[0082] According to the configuration of (11) above, the effect of guiding the combustion gas can be enhanced by the throttle portion 71 (second throttle portion 712) provided at the second position P2.

[0083] (12) In some embodiments, in any of the configurations (1) to (11) above, the combustion liner 20 may have a through hole 23 that opens at a position overlapping with the throttling portion 71 when viewed radially outward from the central axis AX.

[0084] According to the configuration (12) above, the air (compressed air) flowing outside the combustion liner 20 can be directed toward the throttling portion 71 via the through-holes 23, thereby cooling the throttling portion 71 that is exposed to high-temperature combustion gas.

[0085] (13) A gas turbine 1 according to at least one embodiment of the present disclosure includes a compressor 2 that generates compressed air, a gas turbine combustor (combustor 3) having any of the configurations described above in (1) to (12), and a turbine 4 that is rotationally driven by combustion gas generated by the gas turbine combustor (combustor 3).

[0086] According to the configuration of (13) above, the combustion gas having a relatively low temperature in the second region R2 is mixed with the combustion gas having a high temperature, thereby further promoting combustion. Therefore, the difference in temperature between the combustion gas in the second region R2 and the combustion gas in the first region R1 can be reduced, and the generation of carbon monoxide can be suitably suppressed even during partial load operation of the gas turbine 1. [Explanation of symbols]

[0087] 1. Gas turbine 2 Compressor 3 Combustor (gas turbine combustor) 4 Turbines 12 Inner cylinder 12i Inner wall 14 Tailpiece 14i Inner wall 20 Combustion tube 20d outlet 20e Outlet 20i Inner wall 23 Through hole 64 Main nozzle (fuel nozzle) 70 Aperture member 71 Constriction section 71u sloped surface 711 First throttle section 712 Second throttle section

Claims

1. a combustion tube having a combustion region formed inside through which combustion gas generated by combustion of fuel can flow, and an ejection portion formed at a downstream end thereof as an ejection port for the combustion gas; a plurality of throttle portions provided at intervals in the circumferential direction on the inner wall surface of the combustion cylinder, the throttle portions protruding toward the inside of the combustion cylinder; Equipped with a central axis of the combustion liner having a shape that gradually curves to include a first central axis that extends linearly in an upstream region of the combustion liner and a second central axis that extends in a direction different from the extension direction of the first central axis in the outlet portion; the combustion liner includes a first region and a second region, the first region and the second region being separated by a virtual plane that is perpendicular to a virtual plane that includes the central axis from the upstream region to the outlet portion, and that includes the central axis from the upstream region to the outlet portion; a straight line extending from the first central axis passes through the first region in the ejection portion, a total value of projected areas of the narrowed portions in the second region when viewed from the direction to which the central axis extends is greater than a total value of projected areas of the narrowed portions in the first region when viewed from the direction to which the central axis extends. Gas turbine combustor.

2. a combustion tube having a combustion region formed inside through which combustion gas generated by combustion of fuel can flow, and an ejection portion formed at a downstream end thereof as an ejection port for the combustion gas; a plurality of throttle portions provided at intervals in the circumferential direction on the inner wall surface of the combustion cylinder, the throttle portions protruding toward the inside of the combustion cylinder; Equipped with a central axis of the combustion liner having a shape that gradually curves to include a first central axis that extends linearly in an upstream region of the combustion liner and a second central axis that extends in a direction different from the extension direction of the first central axis in the outlet portion; the combustion liner includes a first region and a second region, the first region and the second region being separated by a virtual plane that is perpendicular to a virtual plane that includes the central axis from the upstream region to the outlet portion, and that includes the central axis from the upstream region to the outlet portion; a distance along the inner wall surface in the virtual plane from a position corresponding to a reference position on the first central axis to the ejection port is shorter in the second region than in the first region; a total value of projected areas of the narrowed portions in the second region when viewed from the direction to which the central axis extends is greater than a total value of projected areas of the narrowed portions in the first region when viewed from the direction to which the central axis extends, The combustion liner includes an inner liner and a transition piece, The reference position is either the position of the upstream or downstream end of the inner cylinder on the first central axis, or the position of the tip of a fuel nozzle disposed inside the combustion cylinder. Gas turbine combustor.

3. a radial height of at least one of the throttling portions present in the second region of the combustion liner is greater than a radial height of the throttling portion present in the first region; The gas turbine combustor according to claim 1 or 2.

4. a radial height of the combustion liner for at least one of the throttling portions present in the second region is 1.5 to 3.0 times the radial height of the throttling portion present in the first region; The gas turbine combustor according to claim 3 .

5. a size in the circumferential direction of the combustion liner of at least one of the throttle portions present in the second region is larger than a size in the circumferential direction of the throttle portion present in the first region; The gas turbine combustor according to claim 1 or 2.

6. the upstream surface of the throttle portion is an inclined surface that is inclined so as to approach the central axis as it goes toward the downstream side of the combustion liner, an angle at which the inclined surface of at least one of the narrowed portions present in the second region is inclined with respect to the inner wall surface is larger than an angle at which the inclined surface of the narrowed portion present in the first region is inclined with respect to the inner wall surface; The gas turbine combustor according to claim 1 or 2.

7. an inclination angle of the inclined surface of at least one of the narrowed portions present in the second region with respect to the inner wall surface of 50 degrees or more and 85 degrees or less; The gas turbine combustor according to claim 6 .

8. a plurality of fuel nozzles arranged in the combustion chamber at intervals in a circumferential direction of the combustion chamber; Equipped with At least one of the throttle portions is located between two of the fuel nozzles that are adjacent to each other in the circumferential direction when viewed from the direction in which the central axis extends. The gas turbine combustor according to claim 1 or 2.

9. The throttle portion in the second region is provided at a first position along the central axis and a second position along the central axis that is different from the first position. The gas turbine combustor according to claim 1 or 2.

10. The combustion liner includes a first combustion liner and a second combustion liner disposed downstream of the first combustion liner, the first position is a position within the first combustion cylinder, the second position is a position within the second combustion cylinder; The gas turbine combustor according to claim 9.

11. Among the throttle portions present in the second region, the throttle portion provided at the second position has a different circumferential position from that of the throttle portion present in the second region and the throttle portion provided at the first position. The gas turbine combustor according to claim 9.

12. The combustion liner has a through hole that opens at a position overlapping with the throttle portion when viewed radially outward from the central axis. The gas turbine combustor according to claim 1 or 2.

13. a compressor for generating compressed air; The gas turbine combustor according to claim 1 or 2; a turbine that is rotationally driven by combustion gas generated by the gas turbine combustor; Equipped with Gas turbine.

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