Gas turbine combustor and gas turbine

Abstract

A gas turbine combustor according to at least one embodiment of the present disclosure includes a plurality of throttle portions that protrude toward the inside of a combustion cylinder. A center axis of the combustion cylinder includes an upstream-side center axis that extends linearly in a region on the upstream side of the combustion cylinder and extends in a direction different from the direction of extension of the upstream-side center axis in the injection portion. The combustion cylinder is a virtual plane that is orthogonal to an imaginary plane that includes the center axis from the region on the upstream side to the injection portion, and includes a first region and a second region with the imaginary plane that includes the center axis from the region on the upstream side to the injection portion as a boundary. A straight line that extends the upstream-side center axis passes through the first region in the injection portion. The total value of the projected areas when the throttle portions present in the second region are viewed from the direction of extension of the center axis is greater than the total value of the projected areas when the throttle portions present in the first region are viewed from the direction of extension of the center axis.

Description

Technical Field

[0001] This invention relates to a gas turbine burner and a gas turbine.

[0002] 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

[0003] A combustor for a gas turbine includes, for example, a fuel nozzle capable of supplying fuel, and a combustion chamber with an inner combustion zone through which combustion gases generated by the combustion of fuel can flow. The fuel supplied from the fuel nozzle is burned to become fuel gas, which drives a turbine located downstream of the combustion chamber.

[0004] In the combustor of such a gas turbine, because the temperature of the combustion gas near the inner wall of the combustion chamber is lower than that at the center, the time for the chemical reaction between carbon monoxide (CO) and carbon dioxide (CO2) in the combustion gas is delayed, sometimes increasing the production of carbon monoxide. To address this problem, Patent Document 1 discloses a technique in which a throttling device is provided on the inner wall of the combustion chamber of the combustor, causing the combustion gas near the inner wall to flow towards the center, thereby mixing with the high-temperature combustion gas to promote combustion and suppress the production of carbon monoxide.

[0005] Previous technical documents

[0006] Patent documents

[0007] Patent Document 1: International Publication No. 2011 / 058931 Summary of the Invention

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

[0009] When a gas turbine operates at partial load in a relatively low-temperature combustion gas environment, the amount of carbon monoxide in the combustion gas increases compared to rated operation. Therefore, it is difficult to lower the lower limit of the operating load for the gas turbine.

[0010] Therefore, the inventors conducted in-depth research and concluded that: due to the influence of the shape of the downstream region in the combustion chamber, a temperature deviation of the combustion gases occurs along the circumference. Therefore, in order to suppress the production of carbon monoxide, it is desirable to suppress this temperature deviation of the combustion gases.

[0011] In view of the above, the object of at least one embodiment of the present invention is to provide a gas turbine combustor and a gas turbine that can appropriately suppress the generation of carbon monoxide even when the gas turbine is operating under partial load.

[0012] means for solving technical problems

[0013] (1) The gas turbine combustor according to at least one embodiment of the present invention comprises:

[0014] A combustion chamber, having an inner combustion zone through which combustion gases generated by the combustion of fuel can flow, and having an outlet portion forming an outlet for the combustion gases at its downstream end; and

[0015] The throttling section has multiple sections spaced circumferentially on the inner wall of the combustion chamber and protrudes inward from the combustion chamber.

[0016] The central axis of the combustion chamber includes an upstream central axis that extends linearly in the upstream region of the combustion chamber, and extends in the ejection portion in a direction different from the extending direction of the upstream central axis.

[0017] The combustion chamber is an imaginary plane orthogonal to an imaginary plane including the central axis extending from the upstream region to the ejection portion, and includes a first region and a second region bounded by the imaginary plane including the central axis extending from the upstream region to the ejection portion.

[0018] A straight line extending from the upstream central axis passes through the first region in the ejection section.

[0019] The total projected area of ​​the throttling section in the second region when viewed from the direction of extension of the central axis is greater than the total projected area of ​​the throttling section in the first region when viewed from the direction of extension of the central axis.

[0020] (2) The gas turbine combustor according to at least one embodiment of the present invention comprises:

[0021] A combustion chamber, having an inner combustion zone through which combustion gases generated by the combustion of fuel can flow, and having an outlet portion forming an outlet for the combustion gases at its downstream end; and

[0022] The throttling section has multiple sections spaced circumferentially on the inner wall of the combustion chamber and protrudes inward from the combustion chamber.

[0023] The central axis of the combustion chamber includes an upstream central axis that extends linearly in the upstream region of the combustion chamber, and extends in the ejection portion in a direction different from the extending direction of the upstream central axis.

[0024] The combustion chamber is an imaginary plane orthogonal to an imaginary plane including the central axis extending from the upstream region to the ejection portion, and includes a first region and a second region bounded by the imaginary plane including the central axis extending from the upstream region to the ejection portion.

[0025] From the reference position on the upstream side central axis to the nozzle outlet, the distance traversed along the inner wall surface in the imaginary plane is shorter in the second region than in the first region.

[0026] The total projected area of ​​the throttling section in the second region when viewed from the direction of extension of the central axis is greater than the total projected area of ​​the throttling section in the first region when viewed from the direction of extension of the central axis.

[0027] (3) The gas turbine according to at least one embodiment of the present invention comprises:

[0028] The compressor generates compressed air;

[0029] A gas turbine combustor with the structure of (1) or (2) above; and

[0030] The turbine is driven by the rotation of combustion gases generated by the gas turbine combustor.

[0031] Invention Effects

[0032] According to at least one embodiment of the present invention, a gas turbine combustor and a gas turbine are provided that can appropriately suppress the generation of carbon monoxide even when the gas turbine is operating under partial load. Attached Figure Description

[0033] Figure 1 This is a diagram that schematically illustrates the structure of a gas turbine according to one embodiment of the present invention.

[0034] Figure 2 This is a diagram used to illustrate the structure around the burner of a gas turbine.

[0035] Figure 3A This is a cross-sectional view showing an example of the shape of the combustion chamber.

[0036] Figure 3B It means Figure 3A This diagram illustrates the positional relationship between the shape of the inner wall surface on the upstream side of the combustion chamber and the shape of the inner circumferential surface of the nozzle.

[0037] Figure 4A This is a cross-sectional view showing another example of the shape of the combustion chamber.

[0038] Figure 4BIt means Figure 4A This diagram illustrates the positional relationship between the shape of the inner wall surface on the upstream side of the combustion chamber and the shape of the inner circumferential surface of the nozzle.

[0039] Figure 5 This is a diagram showing an example of a throttling component with a throttling section, viewed from the axial downstream side.

[0040] Figure 6 It is about Figure 5 A perspective view of a portion of the throttling component shown.

[0041] Figure 7A This is a schematic diagram showing the combustion chamber unfolded circumferentially to illustrate an example of the location of the throttling section.

[0042] Figure 7B This is a schematic diagram showing the combustion chamber unfolded circumferentially to illustrate another example of the throttling section's location.

[0043] Figure 7C This is a schematic diagram showing the combustion chamber unfolded circumferentially to illustrate another example of the location of the throttling section.

[0044] Figure 7D This is a schematic diagram showing the combustion chamber unfolded circumferentially to illustrate another example of the location of the throttling section.

[0045] Figure 7E This is a schematic diagram showing the combustion chamber unfolded circumferentially to illustrate another example of the location of the throttling section.

[0046] Figure 7F This is a schematic diagram showing the combustion chamber unfolded circumferentially to illustrate another example of the location of the throttling section.

[0047] Figure 8 yes Figure 3A View VIII-VIII.

[0048] Figure 9 This is a diagram illustrating an example of a structure used for cooling throttling.

[0049] Figure 10A It is a diagram used to illustrate the changes in the shape of the throttling section.

[0050] Figure 10B It is a diagram used to illustrate the changes in the shape of the throttling section.

[0051] Figure 10C It is a diagram used to illustrate the changes in the shape of the throttling section. Detailed Implementation

[0052] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. It should be noted that the dimensions, materials, shapes, and relative arrangements of the constituent components described as embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0053] For example, expressions such as "in a certain direction," "along a certain direction," "parallel," "orthogonal," "center," "concentric," or "coaxial" that indicate relative or absolute configuration not only indicate such configuration in a strict sense, but also indicate a state of relative displacement by tolerance or by an angle or distance that can achieve the same level of functionality.

[0054] For example, expressions such as "same," "equal," and "homogeneous" that indicate things are in the same state not only indicate the same state in a strict sense, but also indicate a state with a difference in the degree to which the same function can be obtained, where there is a tolerance.

[0055] For example, descriptions of shapes such as quadrilaterals or cylinders not only refer to quadrilaterals or cylinders in a strict geometric sense, but also include shapes with concave or convex parts or chamfers within the range where the same effect can be achieved.

[0056] On the other hand, the statement that a constituent element is "possesses", "sets", "includes", "includes" or "has" is not an exclusive statement that excludes the existence of other constituent elements.

[0057] Figure 1 This is a diagram that schematically illustrates the structure of a gas turbine according to one embodiment of the present invention.

[0058] Figure 2 This is a diagram used to illustrate the structure around the burner of a gas turbine.

[0059] (Regarding gas turbines 1)

[0060] like Figure 1 As shown, the gas turbine 1 according to this embodiment includes a compressor 2, a burner (gas turbine burner) 3, and a turbine 4, and is used, for example, to drive external equipment such as a generator G. In the case of a gas turbine 1 for power generation, a generator G is connected to the rotor 5.

[0061] Compressor 2 is used to draw in outside air, i.e., the atmosphere, and compress it, and then supply the compressed air to one or more burners 3.

[0062] The burner 3 uses air compressed by the compressor 2 to burn fuel supplied from the outside, thereby generating high-temperature gas (combustion gas). In one embodiment of the gas turbine 1, a plurality of burners 3 are arranged in a ring around the rotor 5. In one embodiment of the gas turbine 1, a combustible liquid, i.e., oil fuel (liquid fuel), is used as fuel, but a combustible gas, i.e., gaseous fuel, may also be used as fuel.

[0063] The turbine 4 receives the high-temperature combustion gas generated by the burner 3 to generate rotational driving force, and outputs the generated rotational driving force to the compressor 2 and external equipment.

[0064] like Figure 2 As shown, a burner mounting space 8 for a burner 3 is provided inside the carriage 7. The burner mounting space 8 is located between the outlet of the compressor 2 on the axial upstream side and the inlet of the turbine 4 on the axial downstream side. The burner 3 is disposed in the burner mounting space 8, and compressed air flows into the burner 3 from one end. On the other hand, fuel is supplied from the outside into the burner 3, which mixes with air to generate high-temperature combustion gas, and the combustion gas drives the turbine 4 on the downstream side to rotate.

[0065] More specifically, the burner 3 according to several embodiments has a nozzle section 10 and a combustion chamber 20. The combustion chamber 20 includes an inner cylinder 12 and a tail cylinder 14. Alternatively, the inner cylinder 12 and the tail cylinder 14 may be formed as one piece. The combustion chamber 20 has a combustion chamber 18 on its inner side, which is used for the combustion of fuel injected from the main nozzle 64 and the ignition nozzle 54. That is, after the fuel is mixed with compressed air supplied from the compressor 2 in the combustion zone within the combustion chamber 20, combustion gases are generated through combustion. The combustion gases are supplied to the turbine 4 via the combustion chamber 20.

[0066] The nozzle section 10 has an ignition burner 50 and multiple main burners (premixed burners) 60.

[0067] The ignition burner 50 is arranged along the central axis AX of the combustion cylinder 20. Furthermore, a plurality of main burners 60 are arranged separately from each other along the circumference of the combustion cylinder 20 in a manner that surrounds the ignition burner 50.

[0068] The ignition burner 50 includes: an ignition nozzle 54 connected to the fuel port 52; an ignition nozzle tube 56 arranged to surround the ignition nozzle 54; and a wetter (not shown) disposed on the outer periphery of the ignition nozzle 54.

[0069] The main burner 60 includes: a main nozzle 64 connected to a fuel port 62; a main nozzle tube 66 arranged to surround the main nozzle 64; and a blowpipe (not shown) disposed around the main nozzle 64.

[0070] In the burner 3 with the above-described structure, compressed air generated by the compressor 2 is supplied to the burner mounting space 8, and then flows from the burner mounting space 8 into the main nozzle cylinder 66. This compressed air is then premixed with fuel supplied from the fuel port 62 within the main nozzle cylinder 66. At this time, the premixed gas forms a swirling flow primarily through a vortex (not shown) and flows into the inner cylinder 12. Furthermore, the compressed air mixes with fuel injected from the ignition burner 50 via the fuel port 52, and is ignited by a seed ignition (not shown) to produce combustion gases. A portion of these combustion gases diffuses with the flame, thereby being ignited by the premixed gas flowing into the inner cylinder 12 from each main burner 60. In other words, a flame can be maintained for stable combustion of the premixed gas (premixed fuel) from the main burners 60 by an ignition flame generated by the ignition fuel injected from the ignition burner 50.

[0071] For ease of explanation, the terms upstream, downstream, upstream side, and downstream side used in the following description are based on the flow direction of the combustion gas flowing inside the combustion tube 20. That is, the side where the fuel nozzle (ignition nozzle 54, main nozzle 64) is provided with reference to the combustion tube 20 is called the upstream side, and the side where the combustion tube 20 is provided with reference to the fuel nozzle is called the downstream side.

[0072] Furthermore, the direction along the central axis AX of the combustion cylinder 20 will be simply referred to as the axial direction, the circumferential direction centered on the central axis AX will be simply referred to as the circumferential direction, and the radial direction centered on the central axis AX will be simply referred to as the radial direction.

[0073] Furthermore, the main flow of combustion gases within the combustion chamber 20 is appropriately referred to as the "mainstream".

[0074] Figure 3A This is a cross-sectional view showing an example of the shape of the combustion chamber.

[0075] Figure 3B It means Figure 3A The diagram shows the positional relationship between the shape of the inner wall surface on the upstream side of the combustion tube and the shape of the inner circumferential surface of the nozzle when viewed from the downstream side along the first central axis on the upstream side of the combustion tube.

[0076] Figure 4A This is a cross-sectional view showing another example of the shape of the combustion chamber.

[0077] Figure 4B It means Figure 4A The diagram shows the positional relationship between the shape of the inner wall surface on the upstream side of the combustion tube and the shape of the inner circumferential surface of the nozzle when viewed from the downstream side along the first central axis on the upstream side of the combustion tube.

[0078] like Figure 3A and Figure 4A As shown, in the burner 3 according to several embodiments, the combustion chamber 20 has an ejection portion 20e forming an outlet 20d for combustion gas formed at the downstream end. The central axis AX of the combustion chamber 20 extends in different directions on the first central axis AXv on the upstream side of the combustion chamber 20 and the second central axis AX2 in the ejection portion 20e.

[0079] in addition, Figure 3A and Figure 4A This represents the cross-section represented on the imaginary plane Pv1, which includes the region from the upstream side of the combustion chamber 20 to the ejector 20e, along the central axis AX.

[0080] like Figure 3A and Figure 4A As shown, in the burner 3 according to several embodiments, the inner cylinder 12 has an inner wall surface 12i that is a cylinder centered on a first central axis AX1 extending in a straight line.

[0081] like Figure 3A and Figure 4A As shown, in the burner 3 according to several embodiments, the tail tube 14 has a shape that is bent in a manner different from the extension direction of the central axis AX in the connection portion with the inner cylinder 12 and the central axis AX (second central axis AX2) in the ejection portion 20e. The tail tube 14 is formed in a manner in which the cross-sectional shape orthogonal to the central axis AX gradually changes from a circular shape in the connection portion with the inner cylinder 12 to a partially annular shape in the ejection portion 20e along the central axis AX.

[0082] And, as Figure 3A and Figure 4A As shown, in the burner 3 according to several embodiments, the tail tube 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 as it moves toward the downstream side.

[0083] like Figure 3A and Figure 4A As shown, in the burner 3 according to several embodiments, the tail tube 14 is an imaginary surface orthogonal to the aforementioned imaginary plane Pv1, and includes a first region R1 and a second region R2 bounded by an imaginary surface Pv2 that includes the central axis AX extending from the upstream region to the ejection portion 20e. Furthermore, in Figure 3A and Figure 4A In the middle, the imaginary surface Pv2 includes the central axis AX extending from the upstream region to the ejection section 20e, which is consistent with... Figure 3A and Figure 4A The planes orthogonal to the paper in the diagram. That is, in... Figure 3A and Figure 4A In the middle, the central axis AX is equivalent to Figure 3A and Figure 4A The cross section of the imaginary surface Pv2 as shown on the paper.

[0084] Here, region R1 is... Figure 3A and Figure 4A The region separated by the central axis AX, and the region through which the straight line L1 extending from the first central axis AX1 (upstream central axis) of the combustion cylinder 20 downstream passes in the ejector section 20e (reference). Figure 3B and Figure 4B ).

[0085] Furthermore, region R1 is in Figure 3A and Figure 4A Within the two regions separated by the central axis AX, the region on the longer side of the imaginary plane Pv1, from the position corresponding to the reference position Pr on the first central axis AX1 to the nozzle 20d, is located along the inner wall surface 20i.

[0086] That is, in Figure 3A and Figure 4A On the paper, Figure 3A and Figure 4A The distance X1 traversed by the inner wall surface 20i of the combustion tube 20 in the first region R1 from the position corresponding to the reference position Pr on the first central axis AX1 to the nozzle 20d is compared to the distance X1 traversed by the inner wall surface 20i of the combustion tube 20 in the first region R1. Figure 3A and Figure 4A The distance X2 that the inner wall surface 20i of the combustion tube 20 of the second region R2 travels from the position corresponding to the reference position Pr of the first central axis AX1 to the nozzle 20d is.

[0087] In addition, the reference position Pr on the first central axis AX1 can be, for example, the front end position of the fuel nozzle (ignition nozzle 54, main nozzle 64) on the first central axis AX1, or the position of the upstream or downstream end of the inner cylinder 12.

[0088] exist Figure 3A In the burner 3 shown, the first region R1 is the region that is higher than the central axis AX, and the second region R2 is the region that is lower than the central axis AX.

[0089] exist Figure 4A In the burner 3 shown, the first region R1 is the region that is lower than the central axis AX, and the second region R2 is the region that is higher than the central axis AX.

[0090] like Figure 3A and Figure 4AAs shown, the burner 3 according to several embodiments is provided with a throttling section 71. Multiple throttling sections 71 are provided at circumferential intervals on the inner wall surface 20i of the combustion chamber 20 and protrude radially inwards towards the combustion chamber 20. The throttling section 71 guides the relatively low-temperature combustion gas flowing near the inner wall surface 20i of the combustion chamber 20 towards the center of the combustion chamber 20. Thus, the relatively low-temperature combustion gas flowing near the inner wall surface 20i mixes with the relatively high-temperature combustion gas flowing in the center of the combustion chamber 20, thereby promoting combustion. Details regarding the throttling section 71 will be described in detail later.

[0091] (The challenges faced by existing gas turbine combustors)

[0092] In existing gas turbine combustors, the temperature of the combustion gases near the inner wall of the combustion chamber is lower than that in the center, thus delaying the chemical reaction between carbon monoxide (CO) and carbon dioxide (CO2) in the combustion gases, resulting in increased carbon monoxide production. In particular, during partial-load operation of the gas turbine at the relatively lower combustion gas temperature, the amount of carbon monoxide in the combustion gases is greater than during rated operation. Therefore, it is difficult to reduce the lower limit of the operating load of the gas turbine.

[0093] Therefore, the inventors conducted in-depth research and came to the following conclusion: due to the influence of the shape of the downstream region in the combustion chamber, a temperature deviation of the combustion gas is generated along the circumference.

[0094] Specifically, without the throttling section 71 described in detail later, it is found that in the relatively downstream region of the tailstock 14, the temperature of the combustion gas in the second region R2 tends to be lower than that in the first region R1 in the relatively radially outer region.

[0095] Therefore, in the burner 3 according to several embodiments, as will be described in detail later, the total value S2 of the projected area of ​​the throttling section 71 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 area of ​​the throttling section 71 present in the first region R1 when viewed from the extension direction of the central axis AX.

[0096] Thus, by making the total projected area S2 of the throttling section 71 present in the second region R2 when viewed from the extension direction of the central axis AX larger than the total projected area S1 of the throttling section 71 present in the first region R1 when viewed from the extension direction of the central axis AX, the second region R2 more easily guides the combustion gas flowing near the inner wall surface 20i of the combustion chamber 20 towards the center of the combustion chamber 20 than the first region R1. This allows the relatively lower-temperature combustion gas in the second region R2 to mix with the higher-temperature combustion gas, further promoting combustion. Therefore, the temperature difference between the combustion gas in the second region R2 and the combustion gas in the first region R1 can be suppressed, and carbon monoxide production can be appropriately suppressed even when the gas turbine 1 is operating under partial load.

[0097] Furthermore, according to the gas turbine 1 equipped with the burner 3 according to several embodiments, combustion gas at a relatively low temperature in the second region R2 can be mixed with high-temperature combustion gas to further promote combustion. Therefore, the temperature difference between the combustion gas in the second region R2 and the combustion gas in the first region R1 can be suppressed, and carbon monoxide production can be appropriately suppressed even when the gas turbine 1 is operating under partial load.

[0098] Furthermore, the projected area of ​​each throttling section 71 when viewed from the extension direction of the central axis AX is the projected area of ​​the throttling section 71 when viewed from the tangential direction of the central axis AX at the position on the central axis AX and the position closest to the throttling section 71.

[0099] In the following description, the projected area of ​​the throttling section 71 when viewed from the extension direction of the central axis AX will also be referred to simply as the projected area.

[0100] (Details about the throttling section 71)

[0101] Figure 5 This is a diagram showing an example of a throttling member 70 according to several embodiments having a throttling section 71, viewed from the axial downstream side.

[0102] Figure 6 It is about Figure 5 A perspective view of a portion of the throttling component 70 shown.

[0103] like Figure 5 and Figure 6 As shown, the throttling member 70 according to several embodiments includes: an annular ring portion 72; and a throttling portion 71, which is a plurality of protrusions formed on the ring portion 72 at circumferential intervals. In the throttling member 70 according to several embodiments, the throttling portion 71 has a shape in which the protrusions protruding axially relative to the ring portion 72 are bent radially inward.

[0104] In addition, Figure 5 In this process, when the throttling component 70 is installed on the combustion cylinder 20, the two intersection positions of the throttling component 70 with the aforementioned imaginary plane Pv1 are set as circumferential angular positions of 0 degrees and 180 degrees. Furthermore, the angular positions existing in the first region R1 within the intersection positions with the imaginary plane Pv1 are set as 0 degrees, and the angular positions existing in the second region R2 are set as 180 degrees.

[0105] Figure 7A This is a schematic diagram showing the combustion chamber 20 unfolded circumferentially to illustrate an example of the placement of the throttling section 71. Figure 5 The throttling section 71 of the throttling component 70 shown is configured.

[0106] Figure 7B This is a schematic diagram showing the combustion chamber 20 unfolded circumferentially to illustrate another example of the configuration of the throttling section 71.

[0107] Figure 7C This is a schematic diagram showing the combustion chamber 20 unfolded circumferentially to illustrate another example of the configuration of the throttling section 71.

[0108] Figure 7D This is a schematic diagram showing the combustion chamber 20 unfolded circumferentially to illustrate another example of the configuration of the throttling section 71.

[0109] Figure 7E This is a schematic diagram showing the combustion chamber 20 unfolded circumferentially to illustrate another example of the configuration of the throttling section 71.

[0110] Figure 7F This is a schematic diagram showing the combustion chamber 20 unfolded circumferentially to illustrate another example of the configuration of the throttling section 71.

[0111] exist Figures 7A to 7F The text indicates the relative axial and circumferential positions of the throttling section 71, the height of the throttling section 71, and the protrusion heights h1 and h2 extending radially inward from the inner wall surface 20i of the combustion chamber 20 (reference). Figure 3A and Figure 4A ).

[0112] In addition, Figures 7A to 7F In the diagram, the position of the left end of the throttling section 71 in the left-right direction indicates the axial position of the throttling section 71, and the size of the throttling section 71 in the left-right direction indicates the protrusion heights h1 and h2 of the throttling section 71 (reference). Figure 3A and Figure 4A ).

[0113] exist Figures 7A to 7F In the example shown, the total projected area S2 of the throttling section 71 present in the second region R2 is greater than the total projected area S1 of the throttling section 71 present in the first region R1.

[0114] For example, in Figure 7A In the example shown, the number of throttling sections 71 (hereinafter also referred to as the first throttling section 711) arranged in the first region R1 is the same as the number of throttling sections 71 (hereinafter also referred to as the second throttling section 712) arranged in the second region R2. However, each throttling section 71 is formed in such a way that the protrusion height h2 of the second throttling section 712 is higher than the protrusion height h1 of the first throttling section 711.

[0115] For example, in Figure 7B In the example shown, the number of first throttling sections 711 and the number of second throttling sections 712 are the same. However, each throttling section 71 is formed such that the circumferential size w2 of the second throttling section 712 is larger than the circumferential size w1 of the first throttling section 711.

[0116] For example, in Figure 7C and Figure 7D In the example shown, the projected areas of the first throttling section 711 and the second throttling section 712 are the same. However, in the second region, by further configuring the second throttling section 712 at different positions in the axial direction, the total projected area S2 of the throttling section 71 present in the second region R2 is greater than the total projected area S1 of the throttling section 71 present in the first region R1.

[0117] In addition, Figure 7C In the example shown, the second throttling section 712 located on the upstream side of the axial direction and the second throttling section 712 located on the downstream side of the axial direction are positioned at the same circumferential position.

[0118] Furthermore, in Figure 7D In the example shown, the second throttling section 712 configured on the upstream side of the axial direction and the second throttling section 712 configured on the downstream side of the axial direction are configured at different circumferential positions.

[0119] For example, in Figure 7E and Figure 7F In the example shown, each throttling section 71 is formed such that the protrusion height h2 of the second throttling section 712 is higher than the protrusion height h1 of the first throttling section 711. Furthermore, in Figure 7E and Figure 7F In the example shown, in the second region, a second throttling section 712 is further configured at different positions in the axial direction.

[0120] In addition, Figure 7E In the example shown, the second throttling section 712 located on the upstream side of the axial direction and the second throttling section 712 located on the downstream side of the axial direction are positioned at the same circumferential position.

[0121] Furthermore, in Figure 7FIn the example shown, the second throttling section 712 configured on the upstream side of the axial direction and the second throttling section 712 configured on the downstream side of the axial direction are configured at different circumferential positions.

[0122] For example, in Figures 7C to 7F In the example shown, the second throttling section 712 on the axial upstream side is disposed on the inner cylinder 12, and the second throttling section 712 on the axial downstream side is disposed on the tail cylinder 14 (see reference). Figure 3A and Figure 4A ).

[0123] Thus, in the burner 3 according to several embodiments, for example, as Figure 7A , Figure 7E and Figure 7F As shown, the radial height (protrusion height h2) of the combustion tube 20 with respect to at least one of the second throttling sections 712 can be higher than the radial height (protrusion height h1) with respect to the first throttling section 711.

[0124] Therefore, in the second region R2, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 is easily guided towards the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas to easily promote combustion.

[0125] In the burner 3 according to several embodiments, for example, in Figure 7A , Figure 7E and Figure 7F In the example shown, the protrusion height h2 of at least one of the second throttling sections 712 can be more than 1.5 times and less than 3.0 times the protrusion height h1 of the first throttling section 711.

[0126] The higher the protrusion height h2 of the second throttling section 712, the easier it is to guide the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 towards the center of the combustion cylinder 20. However, it may disrupt the mainstream flow of the combustion gas and have an adverse effect on the combustion efficiency.

[0127] exist Figure 7A , Figure 7E and Figure 7F In the example shown,

[0128] The protrusion height h2 of the second throttling section 712 is set to be more than 1.5 times and less than 3.0 times the protrusion height h1 of the first throttling section 711, thereby suppressing the influence on the mainstream flow of combustion gases, and guiding the combustion gases flowing near the inner wall surface 20i of the combustion cylinder 20 in the second region R2 toward the center of the combustion cylinder 20, mixing with the high-temperature combustion gases and promoting combustion.

[0129] In the burner 3 according to several embodiments, for example, as Figure 7B As shown, the circumferential size w2 of at least one of the second throttling sections 712 can be greater than the circumferential size of the first throttling section 711. w 1. Large.

[0130] Therefore, in the second region R2, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 is easily guided towards the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas to easily promote combustion.

[0131] In the burner 3 according to several embodiments,

[0132] like Figure 3A and Figure 4A As shown, the upstream surface of the throttling section 71 can be an inclined surface 71u that is inclined toward the central axis AX toward the downstream side of the combustion chamber 20. The angle θ2 of the inclined surface 71u of at least one of the second throttling sections 712 with respect to the inner wall surface 20i can be larger than the angle θ1 of the inclined surface 71u of the first throttling section 711 with respect to the inner wall surface 20i.

[0133] 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 cylinder 20 towards the center of the combustion cylinder 20.

[0134] By making the angle θ2 of the inclined surface 7lu of at least one of the second throttling sections 712 relative to the inner wall surface 20i larger than the angle θ1 of the inclined surface 71u of the first throttling section 711 relative to the inner wall surface 20i, in the second region R2, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 is easily guided towards the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas to easily promote combustion.

[0135] In the burner 3 according to several embodiments, the angle θ2 of the inclined surface 71u of at least one of the second throttling sections 712 inclined relative to the inner wall surface 20i can be more than 50 degrees and less than 85 degrees.

[0136] 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 cylinder 20 towards the center of the combustion cylinder 20. However, it may disrupt the mainstream flow of the combustion gas and have an adverse effect on the combustion efficiency.

[0137] By setting the angle θ2 of the inclined surface 71u of at least one of the second throttling sections 712 inclined relative to the inner wall surface 20i to 50 degrees or more and 85 degrees or less, the influence on the mainstream flow of combustion gas is suppressed, and the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 in the second region R2 is guided towards the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas to promote combustion.

[0138] Figure 8 yes Figure 3A The VIII-VIII view omits the description of the tail tube 14.

[0139] For example, such as Figure 8 As shown, the burner 3 according to several embodiments includes a plurality of main nozzles 64, which are arranged circumferentially spaced within the combustion chamber 20 (inner chamber 12). When viewed from the extension direction of the central axis AX, at least one of the throttling section 71 may be located between two adjacent main nozzles 64 in the circumferential direction.

[0140] When viewed from the extension direction of the central axis AX, the area between two adjacent main nozzles 64 in the circumferential direction tends to have a lower temperature of the combustion gas than the area overlapping the main nozzles 64 when viewed from the extension direction of the central axis AX.

[0141] By configuring at least one of the throttling sections 71 to be located between two adjacent main nozzles 64 in the circumferential direction when viewed from the extension direction of the central axis AX, and in a position where the temperature of the combustion gas tends to decrease when viewed from the extension direction of the central axis AX, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 is guided towards the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas, thus promoting combustion.

[0142] In the burner 3 according to several embodiments, for example, as Figure 3A , Figure 4A and Figures 7C to 7F As shown, the second throttling section 712 can be provided at a first position P1 along the central axis AX and a second position P2 along the central axis AX that is different from the first position P1 (more downstream than the first position P1).

[0143] Therefore, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 can be guided towards the center of the combustion cylinder 20 by the second throttling section 712 provided at the first position P1 and the second position P2, so that the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 in the second region R2 can be mixed more with the high temperature combustion gas, thereby promoting combustion.

[0144] In the burner 3 according to several embodiments, for example, Figure 3A and Figure 4A As shown, the combustion chamber 20 may include an inner cylinder 12 and a tail cylinder 14 disposed downstream of the inner cylinder 12. The first position P1 may be a position inside the inner cylinder 12. The second position P2 may be a position inside the tail cylinder 14.

[0145] In the burner 3 according to several embodiments, for example, as Figure 3A and Figure 4A As shown, a gap 13 is formed at the connection between the inner cylinder 12 and the tail cylinder 14, and compressed air is introduced into the combustion cylinder 20 as cooling air through this gap 13. Therefore, by providing a throttling section 71 (second throttling section 712) on the inner wall surface 14i of the tail cylinder 14, the temperature drop of the combustion gas in the region further downstream than the second position P2 can be suppressed.

[0146] In the burner 3 according to several embodiments, for example, Figure 7D and Figure 7F As shown, the second throttling section 712 located at the second position P2 may have a different circumferential configuration position than the second throttling section 712 located at the first position P1.

[0147] The inventors and others conducted in-depth research and discovered that:

[0148] If the second throttling section 712 located at the second position P2 is positioned differently in the circumferential direction from the second throttling section 712 located at the first position P1, the effect of guiding combustion gases by the second throttling section 712 located at the second position P2 is improved compared to the case where the second throttling section 712 located at the first position P1 is positioned in the same circumferential direction.

[0149] By making the circumferential configuration position of the second throttling section 712 provided at the first position P1 different from that of the second throttling section 712 provided at the second position P2, the effect of guiding combustion gas can be improved by the second throttling section 712 provided at the second position P2.

[0150] (Regarding the cooling of the throttling section 71)

[0151] Figure 9 This is a diagram illustrating an example of the structure used for cooling throttling section 71, and is a schematic cross-sectional view of the vicinity of throttling section 71 viewed from the circumferential direction.

[0152] In the burner 3 according to several embodiments,

[0153] The combustion chamber 20 may have a through hole 23, which is located at a position that overlaps with the throttling section 71 when viewed radially outward from the central axis AX, i.e., at a position that overlaps with the throttling section 71 in the axial direction.

[0154] As a result, the air (compressed air) flowing outside the combustion chamber 20 can flow toward the throttling section 71 through the through hole 23, thereby cooling the throttling section 71 which is exposed to high temperature combustion gases.

[0155] In addition, the through hole 23 can be provided in a manner that corresponds to all the throttling parts 71, or it can be provided in a manner that, at least in the second throttling part 712, the projected area of ​​each part corresponds only to the second throttling part 712 which is larger than the first throttling part 711.

[0156] (Regarding the change in the shape of the throttling section 71)

[0157] Figure 10A , Figure 10B and Figure 10C This is a diagram used to illustrate the change in the shape of the throttling section 71, and it is a diagram schematically showing the shape of the throttling section 71 when viewed from the axial direction.

[0158] For example, such as Figure 10A and Figure 10B As shown, a protrusion 71b that further protrudes radially inward can also be provided on the radially inner end 71a of the throttling section 71. Furthermore, the protrusion 71b can be as follows: Figure 10A It can be set at position 1 as shown, or as... Figure 10B As shown, it is arranged in multiple locations with circumferential spacing (in) Figure 10B (Two locations are shown in the example).

[0159] Thus, by providing a protrusion 71b that protrudes further toward the radially inward side on the end 71a of the throttling section 71, the number of combustion gas vortices generated by guiding the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 toward the center of the combustion cylinder 20 can be increased, thereby promoting combustion by mixing more of the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 with the high-temperature combustion gas.

[0160] And, for example, such as Figure 10C As shown, a through hole 71c extending axially can also be provided in the throttling section 71. This can suppress the pressure loss of the combustion gas. Furthermore, the effect of guiding the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 towards the center of the combustion cylinder 20 differs between the region where the through hole 71c is provided in the circumferential direction and the region where the through hole 71c is not provided. Therefore, the number of combustion gas vortices generated by guiding the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 towards the center of the combustion cylinder 20 can be increased, allowing the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 to mix more with the high-temperature combustion gas, thereby promoting combustion.

[0161] The present invention is not limited to the above-described embodiments, but also includes modifications to the above-described embodiments or appropriate combinations thereof.

[0162] For example, regarding Figures 7A to 7F Variations in the shape or configuration of the throttling section 71 shown can be appropriately combined so that the total projected area S2 of the throttling sections 71 present in the second region R2 is greater than the total projected area S1 of the throttling sections 71 present in the first region R1.

[0163] And, for example, Figure 3A , Figure 4A and Figures 7C to 7F As shown, the second throttling section 712 has two rows in the axial direction, but it can also have three or more rows.

[0164] The contents described in the above embodiments can be understood, for example, as follows.

[0165] (1) A gas turbine combustor (combustor 3) according to at least one embodiment of the present invention comprises: a combustion chamber 20, a combustion zone in which combustion gases generated by the combustion of fuel are formed on the inner side, and an ejection portion 20e having an ejection port 20d formed at the downstream end of the combustion gas; and

[0166] Throttling sections 71 are provided circumferentially spaced on the inner wall surface 20i of the combustion chamber 20 and protrude inwards from the combustion chamber 20. The central axis AX of the combustion chamber 20 includes an upstream central axis (first central axis AX1) extending linearly in the upstream region of the combustion chamber 20, and extends in the ejection section 20e in a direction different from the extending direction of the upstream central axis (first central axis AX1). The combustion chamber 20 is an imaginary plane orthogonal to an imaginary plane Pv1 including the central axis AX from the upstream region to the ejection section 20e, and includes a first region R1 and a second region R2 bounded by an imaginary plane Pv2 including the central axis AX from the upstream region to the ejection section 20e. A straight line L1 extending the upstream central axis (first central axis AX1) passes through the first region R1 in the ejection section 20e. The total value S2 of the projected area of ​​the throttling section 71 (second throttling section 712) 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 area of ​​the throttling section 71 (first throttling section 711) in the first region R1 when viewed from the extension direction of the central axis AX.

[0167] According to the structure described in (1) above, by making the total value S2 of the projected area of ​​the throttling section 71 (second throttling section 712) present in the second region R2 when viewed from the extension direction of the central axis AX greater than the total value S1 of the projected area of ​​the throttling section 71 (first throttling section 711) present in the first region R1 when viewed from the extension direction of the central axis AX, the second region R2 makes it easier for the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 to be guided towards the center of the combustion cylinder 20 than the first region R1. As a result, the combustion gas with a relatively lower temperature in the second region R2 can be mixed with the combustion gas with a higher temperature, thereby further promoting combustion. Therefore, the temperature difference between the combustion gas in the second region R2 and the combustion gas in the first region R1 can be suppressed, and the generation of carbon monoxide can be appropriately suppressed even when the gas turbine 1 is operating under partial load.

[0168] (2) The gas turbine combustor (combustor 3) according to at least one embodiment of the present invention comprises: a combustion chamber 20, having a combustion region formed on its inner side through which combustion gases generated by the combustion of fuel can flow, and having an ejection portion 20e having an ejection port 20d formed at the downstream end of the combustion gas; and a throttling portion 71, having a plurality of such portions spaced apart circumferentially on the inner wall surface 20i of the combustion chamber 20, and protruding toward the inner side of the combustion chamber 20. The central axis AX of the combustion chamber 20 includes an upstream central axis (first central axis AX1) extending linearly in the upstream region of the combustion chamber 20, and extends in the ejection portion 20e in a direction different from the extending direction of the upstream central axis (first central axis AX1). The combustion chamber 20 is an imaginary plane orthogonal to an imaginary plane Pv1 that includes the central axis AX extending from the upstream region to the nozzle 20e, and includes a first region R1 and a second region R2 bounded by the imaginary plane Pv2 that includes the central axis AX extending from the upstream region to the nozzle 20e. The second region R2 is shorter than the first region R1 in the distance traveled along the inner wall surface 20i within the imaginary plane Pv1 from a position corresponding to a reference position on the upstream central axis (first central axis AX1) to the nozzle 20d. The total projected area S2 of the throttling section 71 (second throttling section 712) present in the second region R2 when viewed from the extension direction of the central axis AX is greater than the total projected area S1 of the throttling section 71 (first throttling section 711) present in the first region R1 when viewed from the extension direction of the central axis AX.

[0169] According to the structure described in (2) above, by making the total value S2 of the projected area of ​​the throttling section 71 (second throttling section 712) present in the second region R2 when viewed from the extension direction of the central axis AX greater than the total value S1 of the projected area of ​​the throttling section 71 (first throttling section 711) present in the first region R1 when viewed from the extension direction of the central axis AX, the second region R2 makes it easier for the combustion gas flowing near the inner wall surface 20i of the combustion chamber 20 to be guided towards the center of the combustion chamber 20 than the first region R1. As a result, the combustion gas with a relatively lower temperature in the second region R2 can be mixed with the combustion gas with a higher temperature, thereby further promoting combustion. Therefore, the temperature difference between the combustion gas in the second region R2 and the combustion gas in the first region R1 can be suppressed, and the generation of carbon monoxide can be appropriately suppressed even when the gas turbine 1 is operating under partial load.

[0170] (3) In several embodiments, in the structure described in (1) or (2) above, the radial height (protrusion height h2) of the combustion tube 20 with respect to at least one of the throttling section 71 (second throttling section 712) present in the second region R2 may be higher than the radial height (protrusion height h1) of the throttling section 71 (first throttling section 711) present in the first region R1.

[0171] According to the structure described in (3) above, in the second region R2, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 is easily guided to the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas to easily promote combustion.

[0172] (4) In several embodiments, in the structure described in (3) above, the radial height (protrusion height h2) of the combustion tube 20 with respect to at least one of the throttling section 71 (second throttling section 712) present in the second region R2 can be more than 1.5 times and less than 3.0 times the radial height (protrusion height h1) of the throttling section 71 (first throttling section 711) present in the first region R1.

[0173] The higher the radial height (protrusion height h2) of the throttling section 71 (second throttling section 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 cylinder 20 towards the center of the combustion cylinder 20. However, it may disrupt the mainstream flow of the combustion gas and have an adverse effect on the combustion efficiency.

[0174] According to the structure described above (4), the influence on the mainstream flow of combustion gas is suppressed, and the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 in the second region R2 is guided to the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas to promote combustion.

[0175] (5) In several embodiments, in any of the structures described in (1) to (4) above, the circumferential size w2 of the combustion tube 20 with respect to at least one of the throttling section 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.

[0176] According to the structure described in (5) above, in the second region R2, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 is easily guided to the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas to easily promote combustion.

[0177] (6) In several embodiments, in any of the structures described in (1) to (5) above, the upstream side surface (inclined surface 71u) of the throttling section 71 may be an inclined surface 71u that is inclined toward the central axis AX toward the downstream side of the combustion chamber 20. The angle θ2 of the inclined surface 71u of at least one of the throttling sections 71 (second throttling section 712) present in the second region R2 with respect to the inner wall surface 20i may be larger than the angle θ1 of the inclined surface 71u of the throttling section 71 (first throttling section 711) present in the first region R1 with respect to the inner wall surface 20i.

[0178] 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 cylinder 20 towards the center of the combustion cylinder 20.

[0179] According to the structure described above (6), in the second region R2, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 is easily guided to the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas to easily promote combustion.

[0180] (7) In several embodiments, in the structure described in (6) above, the angle θ2 of the inclined surface 71u of at least one of the throttling section 71 (second throttling section 712) present in the second region R2 with respect to the inner wall surface 20i can be more than 50 degrees and less than 85 degrees.

[0181] 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 cylinder 20 towards the center of the combustion cylinder 20. However, it may disrupt the mainstream flow of the combustion gas and have an adverse effect on the combustion efficiency.

[0182] According to the structure described above (7), the influence on the mainstream flow of combustion gas is suppressed, and the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 in the second region R2 is guided to the center of the combustion cylinder 20, and mixed with the high-temperature combustion gas to promote combustion.

[0183] (8) In several embodiments, in any of the structures described in (1) to (7) above, a plurality of fuel nozzles (main nozzles 64) may be provided, which are spaced apart in the circumferential direction within the combustion chamber 20. When viewed from the extension direction of the central axis AX, at least one of the throttling sections 71 may be located between two adjacent fuel nozzles (main nozzles 64) in the circumferential direction.

[0184] According to the structure described above (8), when viewed from the extension direction of the central axis AX, the temperature of the combustion gas is in a position of decreasing tendency. The combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 is guided to the center of the combustion cylinder 20 and mixed with the high-temperature combustion gas to promote combustion.

[0185] (9) In several embodiments, in any of the structures in (1) to (8) above, the throttling section 71 (second throttling section 712) present in the second region R2 can be provided at a first position P1 along the central axis AX and a second position P2 along the central axis AX that is different from the first position P1.

[0186] Based on the structure described in (9) above,

[0187] By providing throttling sections 71 (second throttling section 712) at positions 1 P1 and 2 P2, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 can be guided towards the center of the combustion cylinder 20. Therefore, in the second region R2, the combustion gas flowing near the inner wall surface 20i of the combustion cylinder 20 is mixed more with the high-temperature combustion gas, thereby promoting combustion.

[0188] (10) In several embodiments, in the structure described in (9) above, the combustion chamber 20 may include a first combustion chamber (inner chamber 12) and a second combustion chamber (tail chamber 14) disposed downstream of the first combustion chamber (inner chamber 12). The first position P1 may be a position inside the first combustion chamber (inner chamber 12). The second position P2 may be a position inside the second combustion chamber (tail chamber 14).

[0189] Sometimes, cooling air is introduced from the connection between the first combustion chamber (inner chamber 12) and the second combustion chamber (tail chamber 14). In this case, as long as a throttling section 71 (second throttling section 712) is provided on the inner wall surface 14i of the second combustion chamber (tail chamber 14), the temperature drop of the combustion gas can be suppressed in a region further downstream than the second position P2.

[0190] According to the structure described above (10), it is possible to suppress the temperature drop of the combustion gas in a region further downstream than the second position P2.

[0191] (11) In several embodiments, in the structure described in (9) or (10) above, the circumferential arrangement positions of the throttling section 71 (second throttling section 712) located at the second position P2 in the throttling section 71 (second throttling section 712) located at the first position P1 in the throttling section 71 (second throttling section 712) located in the throttling section 71 (second throttling section 712) located in the second region R2 may be different.

[0192] According to the structure described above (11), the effect of guiding combustion gases by the throttling section 71 (second throttling section 712) provided at the second position P2 can be improved.

[0193] (12) In several embodiments, in any of the structures described in (1) to (11) above, the combustion chamber 20 may have a through hole 23 that opens at a position overlapping with the throttling section 71 when viewed from the central axis AX toward the radially outward.

[0194] According to the structure described above (12), the air (compressed air) flowing outside the combustion chamber 20 can flow through the through hole 23 toward the throttling section 71, thereby cooling the throttling section 71 which is exposed to high temperature combustion gases.

[0195] (13) The gas turbine 1 according to at least one embodiment of the present invention includes: a compressor 2 for generating compressed air; a gas turbine combustor (combustor 3) of any of the structures in (1) to (12) above; and a turbine 4 driven by the rotation of combustion gas generated by the gas turbine combustor (combustor 3).

[0196] According to the structure described above (13), the combustion gas with a relatively low temperature in the second region R2 can be mixed with the combustion gas with a high temperature to further promote combustion. Therefore, the temperature difference between the combustion gas in the second region R2 and the combustion gas in the first region R1 can be suppressed, and the generation of carbon monoxide can be appropriately suppressed even when the gas turbine 1 is operating under partial load.

[0197] Symbol Explanation

[0198] 1-Gas turbine, 2-Compressor, 3-Burner (gas turbine burner), 4-Turbine, 12-Inner cylinder, 12i-Inner wall surface, 14-Tail cylinder, 14i-Inner wall surface, 20-Combustion cylinder, 20d-Injection outlet, 20e-Injection section, 20i-Inner wall surface, 23-Through hole, 64-Main nozzle (fuel nozzle), 70-Throttling component, 71-Throttling section, 71u-Inclined surface, 711-First throttling section, 712-Second throttling section.

Claims

1. A gas turbine combustor, comprising: A combustion chamber, having an inner combustion zone through which combustion gases generated by the combustion of fuel can flow, and having an outlet portion forming an outlet for the combustion gases at its downstream end; and The throttling section has multiple sections spaced circumferentially on the inner wall of the combustion chamber and protrudes inward from the combustion chamber. The central axis of the combustion chamber includes an upstream central axis that extends linearly in the upstream region of the combustion chamber, and extends in the ejection portion in a direction different from the extending direction of the upstream central axis. The combustion chamber is an imaginary plane orthogonal to an imaginary plane including the central axis extending from the upstream region to the ejection portion, and includes a first region and a second region bounded by the imaginary plane including the central axis extending from the upstream region to the ejection portion. A straight line extending from the upstream central axis passes through the first region in the ejection section. The total projected area of ​​the throttling section in the second region when viewed from the direction of extension of the central axis is greater than the total projected area of ​​the throttling section in the first region when viewed from the direction of extension of the central axis. The radial height of the combustion chamber of at least one of the throttling sections present in the second region is higher than the radial height of the throttling section present in the first region.

2. A gas turbine combustor, comprising: A combustion chamber, having an inner combustion zone through which combustion gases generated by the combustion of fuel can flow, and having an outlet portion forming an outlet for the combustion gases at its downstream end; and The throttling section has multiple sections spaced circumferentially on the inner wall of the combustion chamber and protrudes inward from the combustion chamber. The central axis of the combustion chamber includes an upstream central axis that extends linearly in the upstream region of the combustion chamber, and extends in the ejection portion in a direction different from the extending direction of the upstream central axis. The combustion chamber is an imaginary plane orthogonal to an imaginary plane including the central axis extending from the upstream region to the ejection portion, and includes a first region and a second region bounded by the imaginary plane including the central axis extending from the upstream region to the ejection portion. From the reference position on the upstream side central axis to the nozzle outlet, the distance traversed along the inner wall surface in the imaginary plane is shorter in the second region than in the first region. The total projected area of ​​the throttling section in the second region when viewed from the direction of extension of the central axis is greater than the total projected area of ​​the throttling section in the first region when viewed from the direction of extension of the central axis. The radial height of the combustion chamber of at least one of the throttling sections present in the second region is higher than the radial height of the throttling section present in the first region.

3. The gas turbine combustor according to claim 1 or 2, wherein, The radial height of the combustion chamber of at least one of the throttling sections present in the second region is more than 1.5 times and less than 3.0 times the radial height of the throttling section present in the first region.

4. The gas turbine combustor according to claim 1 or 2, wherein, The circumferential size of the combustion chamber of at least one of the throttling sections present in the second region is larger than the circumferential size of the throttling section present in the first region.

5. The gas turbine combustor according to claim 1 or 2, wherein, The upstream surface of the throttling section is an inclined surface that slopes towards the central axis as it moves toward the downstream side of the combustion chamber. The angle at which the inclined surface of at least one of the throttling sections present in the second region is inclined relative to the inner wall surface is greater than the angle at which the inclined surface of the inclined surface of the throttling section present in the first region is inclined relative to the inner wall surface.

6. The gas turbine combustor according to claim 5, wherein, The angle of inclination of the inclined surface of at least one of the throttling sections present in the second region relative to the inner wall surface is more than 50 degrees and less than 85 degrees.

7. The gas turbine combustor according to claim 1 or 2, comprising a plurality of fuel nozzles spaced apart circumferentially within the combustion chamber. At least one of the throttling sections is located between two adjacent fuel nozzles in the circumferential direction when viewed from the extension direction of the central axis.

8. The gas turbine combustor according to claim 1 or 2, wherein, The throttling section in the second region is located at a first position along the central axis and at a second position along the central axis that is different from the first position.

9. The gas turbine combustor according to claim 8, wherein, The combustion chamber includes a first combustion chamber and a second combustion chamber disposed downstream of the first combustion chamber. The first position is the position inside the first combustion chamber. The second position is the position inside the second combustion chamber.

10. The gas turbine combustor according to claim 8, wherein, The throttling section in the second region, located at the second position, has a different circumferential configuration position than the throttling section in the second region, located at the first position.

11. The gas turbine combustor according to claim 1 or 2, wherein, The combustion chamber has a through hole that opens at a position overlapping the throttling section when viewed from the central axis toward the radially outward direction.

12. A gas turbine comprising: The compressor generates compressed air; The gas turbine combustor as claimed in claim 1 or 2; and The turbine is driven by the rotation of combustion gases generated by the gas turbine combustor.

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