JP2024013988A - Gas turbine combustor and gas turbine - Google Patents

Abstract

[Problem] In a gas turbine combustor and gas turbine, the generation of CO is suppressed by improving the combustibility of the combustion gas in the first stage, and the combustion gas in the first stage is mixed with the premixed gas in the second stage. By improving the performance, the generation of NOx is suppressed. [Solution] A cylindrical combustion tube, a fuel supply section that supplies fuel gas to the inside of the combustion tube, and a section where fuel and air are supplied to the inside of the combustion tube on the downstream side of the fuel supply section in the flow direction of the combustion gas. A premixed gas supply section that supplies mixed premixed gas, and a premixed gas supply section that protrudes from the inner wall surface of the combustion tube toward the center of the combustion tube between the fuel supply section and the premixed gas supply section to deflect the flow of combustion gas. A deflection member. [Selection diagram] Figure 1

Description

TECHNICAL FIELD This disclosure relates to gas turbine combustors and gas turbines.

A gas turbine includes a compressor, a combustor, and a turbine. The compressor compresses the air taken in to create high-temperature, high-pressure compressed air. The combustor supplies fuel to compressed air and burns it to obtain high-temperature, high-pressure combustion gas. The turbine is powered by combustion gases and drives a coaxially connected generator.

In order to increase the efficiency and output of gas turbines, it is possible to increase the combustion temperature. On the other hand, it is necessary to reduce NOx generated during combustion, and in order to lower the maximum flame temperature, a premix combustion method is adopted. However, in the premix combustion method, combustion vibration, which is an unstable phenomenon, is likely to occur, and an acoustic device is required. However, since the acoustic device needs to suppress flame flashback, purge air is required, which causes a problem that combustion air decreases and NOx increases.

There is a two-stage combustion method as a technology to solve such problems. In the two-stage combustion method, when the flame temperature is low due to low load, air is supplied from the second stage nozzle to increase the flame temperature on the upstream side and suppress the generation of CO. In addition, the two-stage combustion method lowers the temperature in the first-stage flame region, where residence time is longer, by increasing the ratio of fuel to air from the second-stage nozzle to the first-stage nozzle at high loads. It is possible to suppress this and achieve a reduction in NOx as a whole.

Japanese Patent Application Publication No. 2007-113888

However, in the two-stage combustion method, low-temperature air is supplied from the second-stage nozzle to the first-stage combustion gas and mixed with the first-stage combustion gas under low load. Therefore, the temperature of the main stream gas decreases rapidly, and the combustion of the fuel supplied from the first-stage nozzle becomes insufficient, which becomes a factor in the generation of CO. In addition, in the two-stage combustion system, under high load, if the penetration power of the premixed gas supplied from the second-stage nozzle to the first-stage combustion gas is insufficient, the first-stage combustion gas and two Mixing with the premixed gas in the first stage becomes insufficient. Then, there is a problem in that a high temperature region of the premixed gas supplied from the second stage nozzle remains and NOx is generated.

The present disclosure solves the above-mentioned problems, and suppresses the generation of CO by improving the combustibility of the first-stage combustion gas, and also improves the combustibility of the first-stage combustion gas and the second-stage premixed gas. An object of the present invention is to provide a gas turbine combustor and a gas turbine that suppress the generation of NOx by improving the mixing properties of NOx.

A gas turbine combustor of the present disclosure for achieving the above object includes a cylindrical combustion tube, a fuel supply section that supplies fuel gas to the inside of the combustion tube, and a gas turbine combustor that supplies combustion gas to the inside of the combustion tube. a premixed gas supply section that supplies a premixed gas in which fuel and air are mixed into the combustion tube on the downstream side in the flow direction; a deflecting member protruding from an inner wall surface toward the center of the combustion cylinder to deflect the flow of the combustion gas.

The gas turbine of the present disclosure also includes a compressor that generates high-temperature, high-pressure compressed air by compressing air, and a compressor that generates high-temperature, high-pressure combustion gas by supplying fuel gas to the compressed air and combusting it. and a turbine driven by the combustion gas.

According to the gas turbine combustor and gas turbine of the present disclosure, it is possible to suppress the generation of CO by improving the combustibility of the first-stage combustion gas, and also to suppress the generation of CO between the first-stage combustion gas and the second-stage combustion gas. The generation of NOx can be suppressed by improving the miscibility with the premixed gas.

FIG. 1 is a schematic diagram showing the overall configuration of a gas turbine. FIG. 2 is a sectional view showing the gas turbine combustor of the first embodiment. FIG. 3 is a sectional view showing the premixed gas supply section. FIG. 4 is a sectional view taken along the line IV-IV in FIG. 2 showing the arrangement relationship between the premixed gas supply section and the deflection member. FIG. 5 is a sectional view showing a modification of the arrangement relationship between the premixed gas supply section and the deflection member. FIG. 6 is a sectional view showing a premixed gas supply section in the gas turbine combustor of the second embodiment. FIG. 7 is a sectional view showing a gas turbine combustor according to a third embodiment.

Preferred embodiments of the present disclosure will be described in detail below with reference to the drawings. Note that the present disclosure is not limited to this embodiment, and if there are multiple embodiments, the present disclosure also includes a configuration in which each embodiment is combined. In addition, the components in the embodiments include those that can be easily imagined by those skilled in the art, those that are substantially the same, and those that are in the so-called equivalent range.

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

As shown in FIG. 1, the gas turbine 10 includes a compressor 11, a combustor (gas turbine combustor) 12, and a turbine 13. The compressor 11 and the turbine 13 can be rotated together by a rotating shaft 14. A generator 15 is connected to one end of the rotating shaft 14 in the axial direction. A plurality of combustors 12 are arranged between the compressor 11 and the turbine 13 at intervals in the circumferential direction.

In the compressor 11, air A taken in from an air intake port passes through a plurality of stationary blades and rotor blades and is compressed to generate high-temperature, high-pressure compressed air CA. The combustor 12 generates a mixture MG by supplying a fuel gas FG to the compressed air CA, and generates a high-temperature, high-pressure combustion gas CG by combusting the mixture MG. The turbine 13 drives and rotates the rotary shaft 14 as the combustion gas CG passes through the stationary blades and the rotor blades, and discharges the exhaust gas EG. The generator 15 is driven by the rotation of the rotating shaft 14 and generates electricity.

<Gas turbine combustor>
FIG. 2 is a sectional view showing the gas turbine combustor of the first embodiment.

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

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

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

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

The combustor 12 will be described in detail below.

The outer cylinder 31 has a top hat part 41 connected to one end in the direction of the axis O1, and has an open outer circumferential side at the other end to receive high-temperature, high-pressure compressed air CA generated by the compressor 11 (see FIG. 1). will flow in. One end of the inner cylinder 32 in the direction of the axis O1 is arranged inside the outer cylinder 31, and is connected to the outer cylinder 31 via a connecting member 42. The connecting member 42 has a ring shape and has a large number of through holes 42a formed therein. The connecting member 42 having a large number of through holes 42a functions as a restricting member for the compressed air CA.

The transition piece 33 has one end in the direction of the axis O1 located inside the other end of the outer cylinder 31 and outside the other end of the inner cylinder 32, and is supported by the inner cylinder 32 via a support member 43. be done. A ring-shaped air passage 44 is formed between the other end of the outer cylinder 31 and one end of the tail cylinder 33. The compressed air CA flows through the air passage 44 to the connecting member 42 side. Furthermore, a ring-shaped air passage 45 is formed between the other end of the inner cylinder 32 and one end of the tail cylinder 33. A portion of the compressed air CA flows into the transition piece 33 through the air passage 45 and functions as film air flowing along the inner wall surface 33a.

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

Pilot combustion burner 53 has a pilot cone 55 and a pilot nozzle 56. The pilot cone 55 has an end supported by the inner cylinder 32. The pilot nozzle 56 is supported by the top hat portion 41 and arranged inside the pilot cone 55. Although not shown, swirler vanes are provided on the outer periphery of the pilot nozzle 56. A pilot fuel line (not shown) is connected to the pilot nozzle 56.

The main combustion burner 54 has a strut 57 and a main nozzle 58. The end portion of the support column 57 is supported by the top hat portion 41 . The main nozzle 58 is arranged inside the column 57. Note that the main nozzle 58 has swirler vanes. The main nozzle 58 is connected to a main fuel line (not shown).

Note that in the first embodiment, the fuel supply section 22 includes at least a pilot combustion burner 53 and a plurality of main combustion burners 54.

Therefore, the compressed air CA flows into the inner cylinder 32. The plurality of main combustion burners 54 eject and mix fuel gas FG with respect to the compressed air CA to generate a mixture (premixture) MG, and the mixture MG becomes a swirling flow and flows into the transition pipe 33. flows inside. On the other hand, the pilot combustion burner 53 injects and mixes the fuel gas FG with respect to the compressed air CA to generate a mixture MG, and the mixture MG is ignited and combusted by a pilot flame (not shown), and the combustion gas CG and is ejected into the transition pipe 33. At this time, a part of the combustion gas CG is ejected into the transition piece 33 so as to spread around it with flame, and the mixture MG that has flowed into the inside of the transition piece 33 from each main combustion burner 54 is ignites and burns. That is, the flame of the pilot fuel gas FG ejected from the pilot combustion burner 53 can perform flame stabilization for stably burning the lean premix fuel gas FG from the main combustion burner 54.

<Premixed gas supply section>
FIG. 3 is a sectional view showing the premixed gas supply section.

As shown in FIGS. 2 and 3, the premixed gas supply section 23 is disposed downstream of the fuel supply section 22, and can inject only compressed air CA into the transition piece 33. It is possible to eject a mixture (premixed gas) MG of fuel and fuel. A plurality of premixed gas supply units 23 are arranged at intervals in the circumferential direction of the transition piece 33. In the premixed gas supply unit 23 , a part for ejecting the air-fuel mixture MG into the interior of the transition piece 33 is arranged along the inner wall surface 33 a of the transition piece 33 .

The premixed gas supply section 23 includes a housing 61 , a jet hole (spout section) 62 , an air nozzle 63 , and a fuel nozzle 64 .

The housing 61 is fitted and fixed from the outside into a mounting hole 33b formed in the transition piece 33. The front surface 61a of the housing 61 is continuous with the inner wall surface 33a of the transition piece 33 without any difference in level. The ejection hole 62 has a circular shape and is provided along the axis O2 direction, which is the radial direction of the transition piece 33, which is perpendicular to the axis O1 direction of the housing 61. Note that the ejection hole 62 is not limited to a shape along the axis O2 direction perpendicular to the axis O1 direction, but may be inclined to one side or the other side of the axis O1 direction, or formed around the circumference of the transition piece 33. It may also be tilted in the direction. Further, the ejection hole 62 is not limited to a circular shape, but may be an elliptical shape, a polygonal shape (rectangular shape), or the like.

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

A plurality of fuel nozzles 64 are provided around the jet hole 62 in the housing 61 along a direction perpendicular to the axis O2 direction. The fuel nozzle 64 communicates with the jet hole 62 . The fuel nozzle 64 is connected to a fuel line (not shown), and the fuel line is provided with an on-off valve (flow rate adjustment valve).

Therefore, compressed air CA is supplied to the air nozzle 63 from the air line. Then, the air nozzle 63 spouts compressed air CA to the jet hole 62 . On the other hand, fuel gas FG is supplied to the fuel nozzle 64 from the fuel line. Then, the fuel nozzle 64 spouts the fuel gas FG into the jet hole 62 . As a result, the premixed gas supply section 23 jets out the mixture MG of the compressed air CA and the fuel gas FG from the jet hole 62 toward the inside of the transition piece 33 .

<Deflection member 24>
FIG. 4 is a sectional view taken along the line IV-IV in FIG. 2 showing the arrangement relationship between the premixed gas supply section and the deflection member.

As shown in FIGS. 2 and 3, the deflection member 24 is provided on the inner wall surface 33a of the transition piece 33 on the upstream side of the premixed gas supply section 23 in the flow direction of the combustion gas CG. The deflection member 24 protrudes from the inner wall surface 33a of the transition piece 33 toward the center (axis O1) of the combustor main body 21 and toward the downstream side in the flow direction of the combustion gas CG. The deflection member 24 has a mounting portion 24a and a deflection portion 24b. The attachment portion 24a is fixed to the inner wall surface 33a of the transition piece 33 by, for example, welding. The deflecting portion 24b is integrally provided at the end of the mounting portion 24a at a predetermined angle. That is, the deflection member 24 is arranged as a separate member from the transition piece 33.

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

Further, the premixed gas supply section 23 and the deflection member 24 have a predetermined positional relationship. That is, the distance L between the deflection member 24 and the premixed gas supply section 23 in the axis O1 direction is greater than 10 times the radial length H1 of the transition piece 33 in the deflection member 24 protruding from the inner wall surface 33a of the transition piece 33. Preferably short. That is, it is preferable that the relationship between the distance L and the radial length H1 is L<10H1. Furthermore, it is preferable that the relationship between the distance L and the radial length H1 is L<7H1.

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

Since the deflection member 24 deflects the flow of the combustion gas CG, a low-velocity region of the combustion gas CG is formed on the downstream side. The relationship between the distance L and the radial length H1 (L<7H) in the premixed gas supply section 23 and the deflection member 24 is set in consideration of the backstep flow at this time. That is, by applying the relationship between the distance L and the radial length H1 (L<7H), the combustion gas CG deflected by the deflection member 24 flows toward the ejection hole 62 of the premixed gas supply section 23. This makes it difficult for the flow of the combustion gas CG to affect the penetrating force of the air-fuel mixture MG ejected from the ejection hole 62 of the premixed gas supply section 23.

Further, as shown in FIGS. 3 and 4, a plurality of premixed gas supply sections 23 (four in this embodiment, but several (without limitation). The deflection member 24 is arranged at a position facing the plurality of premixed gas supply sections 23 in the axial direction of the transition piece 33 (direction of the axis O1). That is, the deflection member 24 and the premixed gas supply section 23 are arranged at substantially the same position in the circumferential direction.

That is, the deflection member 24 has a ring shape. The deflection member 24 is arranged over the entire circumference of the inner wall surface 33a of the transition piece 33. Therefore, the deflection member 24 directs the combustion gas CG around the entire circumference of the inner wall surface 33a flowing toward the premixed gas supply section 23 side along the inner wall surface 33a of the transition piece 33 toward the center (axis O1) of the combustor main body 21. Deflect it so that it flows towards.

However, the deflection member 24 is not limited to the shape described above. FIG. 5 is a sectional view showing a modification of the arrangement relationship between the premixed gas supply section and the deflection member.

As shown in FIGS. 3 and 5, a plurality of premixed gas supply sections 23 are arranged at intervals in the circumferential direction of the transition piece 33. The plurality of deflection members 24A are arranged at positions facing the plurality of premixed gas supply sections 23 in the axial direction of the transition piece 33 (direction of the axis O1).

That is, a plurality of deflecting members 24A (eight in this embodiment) are arranged. Some (four in this embodiment) of the plurality of deflection members 24A are arranged at positions facing the four premixed gas supply sections 23 in the direction of the axis O1. The remaining four deflection members 24A are arranged at positions facing the intermediate position of the four premixed gas supply sections 23 in the direction of the axis O1. Therefore, among the combustion gas CG flowing along the inner wall surface 33a of the transition piece 33, the plurality of deflection members 24A directs at least the combustion gas CG flowing toward the ejection hole 62 of each premixed gas supply section 23 into the combustor main body. 21 (axis center O1) side.

Note that the combustor 12 generates vibrations (combustion vibrations) when the fuel burns. Combustion vibration causes noise and vibration when the gas turbine 10 is operating. Therefore, an acoustic damper 71 is provided to the combustor 12 as a vibration generation source through which the combustion gas CG flows. The acoustic damper 71 is provided in the transition piece 33 in the combustor 12. The acoustic damper 71 absorbs air vibrations (pressure waves) caused by combustion vibrations of the combustion gas CG through the through hole of the transition piece 33 when the combustion gas CG flows in the transition piece 33, thereby damping pressure fluctuations. The deflection member 24 (24A) is arranged on the downstream side of the acoustic damper 71 in the flow direction of the combustion gas CG.

<Function of the combustor>
As shown in FIG. 2, in the fuel supply unit 22, the plurality of main combustion burners 54 eject fuel gas FG into the compressed air CA to generate a mixture (premixture) MG, and the mixture MG is tailed. It flows into the inside of the cylinder 33. The pilot combustion burner 53 injects a fuel gas FG into the compressed air CA to generate a mixture MG, the mixture MG is ignited and combusted, and the combustion gas CG is injected into the transition pipe 33 . Then, the fuel gas FG ejected from the main combustion burner 54 is ignited by the diffusion flame (or premixed flame) ejected from the pilot combustion burner 53, resulting in lean combustion.

Combustion gas CG generated by combustion of the fuel gas FG supplied from the fuel supply section 22 flows through the transition piece 33 toward the premixed gas supply section 23 side. At this time, the deflection member 24 (24A) deflects the combustion gas CG flowing along the inner wall surface 33a of the transition piece 33 so that it flows toward the center (axis O1) of the combustor main body 21. In this state, the premixed gas supply section 23 jets the compressed air CA or the mixture MG from the jet hole 62 toward the inside of the transition piece 33 .

During low-load operation of the gas turbine 10 (see FIG. 1), the premixed gas supply section 23 supplies compressed air CA to the combustion gas CG generated by combustion of the fuel gas FG supplied from the fuel supply section 22. It ejects into the tail pipe 33. At this time, in the region of the transition piece 33 where the deflection member 24 (24A) is arranged, the flow direction of the combustion gas CG is deflected by the deflection member 24 (24A) toward the center of the transition piece 33, and the flow is disturbed. be done. Further, a part of the combustion gas CG flows around from the tip of the deflection member 24 (24A) to the inner wall surface 33a side of the transition piece 33, generates a vortex, and is flame-stabilized. Therefore, the compressed air CA is ejected from the premixed gas supply section 23 to the combustion gas CG whose flow is disturbed, so that the combustion gas CG and the compressed air CA are appropriately mixed and the combustion reaction is promoted. , appropriate combustion of the combustion gas CG is ensured, and the generation of CO is suppressed.

On the other hand, during high-load operation of the gas turbine 10 (see FIG. 1), the premixed gas supply section 23 supplies compressed air to the combustion gas CG generated by combustion of the fuel gas FG supplied from the fuel supply section 22. A mixture MG of CA and fuel gas FG is injected into the transition pipe 33. At this time, in the region of the transition piece 33 where the deflection member 24 (24A) is arranged, the flow direction of the combustion gas CG is deflected toward the center of the transition piece 33 by the deflection member 24 (24A). Then, in the area in front of the jet hole 62 in the premixed gas supply section 23, the combustion gas CG flows toward the center of the transition piece 33. Then, the premixed gas supply section 23 has sufficient penetrating force to eject the air-fuel mixture MG toward the combustion gas CG, and the combustion gas CG and the air-fuel mixture MG are appropriately mixed to promote the combustion reaction. Therefore, the fuel gas FG supplied from the premixed gas supply unit 23 can be appropriately combusted, and the generation of NOx is suppressed.

[Second embodiment]
FIG. 6 is a sectional view showing a premixed gas supply section in the gas turbine combustor of the second embodiment. The basic configuration of the second embodiment is the same as that of the first embodiment described above, and will be explained using FIG. Reference numerals are given and detailed explanations are omitted.

As shown in FIGS. 1 and 6, the premixed gas supply section 23A is disposed downstream of the fuel supply section 22, and is capable of spouting only the compressed air CA into the transition piece 33. It is possible to inject a mixture MG of fuel and fuel. The premixed gas supply section 23A is arranged such that a jetting section for ejecting the fuel gas FG into the transition tube 33 projects from the inner wall surface 33a of the transition tube 33 into the transition tube 33.

The premixed gas supply section 23A includes a housing 61, an ejection hole (ejection section) 62, an air nozzle 63, a fuel nozzle 64, and a guide section 65.

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

A plurality of fuel nozzles 64 are provided around the jet hole 62 . The fuel nozzle 64 communicates with the jet hole 62 .

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

That is, the guide portion 65 protrudes from the inner wall surface 33a of the transition tube 33 toward the transition tube 33, so that the jet hole 62 is extended to the inside of the transition tube 33. In this case, the radial length H2 of the transition piece 33 at the guide portion 65 protruding from the inner wall surface 33a of the transition piece 33 is the radial length H2 of the transition piece 33 at the deflection member 24 protruding from the inner wall surface 33a of the transition piece 33. It is preferable to set it to H1 or more.

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

Therefore, with respect to the combustion gas CG generated by combustion of the fuel gas FG supplied from the fuel supply section 22, the premixed gas supply section 23A generates compressed air CA or a mixture of compressed air CA and fuel gas FG. is ejected into the transition pipe 33. At this time, in the premixed gas supply section 23A, since the ejection hole 62 is extended to the inside of the transition piece 33 by the guide section 65, the penetrating force of the mixture MG is improved. Further, since the flow direction of the combustion gas CG is deflected toward the center of the transition piece 33 by the deflection member 24, the combustion gas CG and the air-fuel mixture MG are appropriately mixed to promote the combustion reaction. Therefore, the fuel gas FG supplied from the premixed gas supply section 23 can be appropriately combusted, and the generation of CO and NOx is suppressed.

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

As shown in FIG. 7, the combustor 12A includes a combustor main body 21, a fuel supply section 22, a premixed gas supply section 23, and a deflection member 24. A plurality of premixed gas supply sections 23 (two in this embodiment, but the number is not limited) are arranged at intervals in the axial direction of the combustor main body 21 (transition piece 33).

The plurality of premixed gas supply sections 23 are arranged downstream of the fuel supply section 22, and are capable of injecting only compressed air CA into the transition piece 33, as well as supplying a mixture MG of compressed air CA and fuel. It is possible to squirt. The plurality of premixed gas supply units 23 have the same configuration.

Therefore, for the combustion gas CG generated by combustion of the fuel gas FG supplied from the fuel supply section 22, each premixed gas supply section 23 supplies a mixture of the compressed air CA or the compressed air CA and the fuel gas FG. MG is injected into the transition pipe 33. At this time, the flow direction of the combustion gas CG is deflected toward the center of the transition piece 33 by the deflection member 24, so that the combustion gas CG and the air-fuel mixture MG are appropriately mixed to promote the combustion reaction. Therefore, the fuel gas FG supplied from the premixed gas supply section 23 can be appropriately combusted, and the generation of CO and NOx is suppressed.

[Actions and effects of this embodiment]
The gas turbine combustor according to the first aspect includes a combustor main body 21 having a cylindrical shape, a fuel supply section 22 that supplies fuel gas FG into the inside of the combustor main body 21, and a combustion gas CG that is larger than the fuel supply section 22. A premixed gas supply section 23, 23A that supplies the mixture (premixed gas) MG into the combustor main body 21 on the downstream side in the flow direction, and a fuel supply section 22 and a premixed gas supply section 23, 23A. Deflection members 24 and 24A are provided between which protrude from the inner wall surface of the combustor body 21 toward the center of the combustor body 21 and deflect the flow of the combustion gas CG.

According to the gas turbine combustor according to the first aspect, the fuel supply section 22 supplies the fuel gas FG to the combustor main body 21, and the combustion gas CG generated by combustion of the fuel gas FG is supplied to the premixed gas supply section. Flows to the 23 side. At this time, the direction of the combustion gas CG is deflected by the deflection members 24 and 24A so that it flows toward the center (axis O1) of the combustor main body 21. Then, the premixed gas supply section 23 supplies the mixture MG to the combustor main body 21 in this state.

Therefore, for example, during low-load operation of the gas turbine 10, the direction of the combustion gas CG is deflected by the deflection members 24, 24A, and the flow is disturbed. Then, the combustion gas CG and the compressed air CA ejected from the premixed gas supply section 23 are appropriately mixed to promote the combustion reaction, ensuring appropriate combustion of the combustion gas CG, and suppressing the generation of CO. Can be done.

Further, for example, during high-load operation of the gas turbine 10, the direction of the combustion gas CG is deflected by the deflection members 24 and 24A. Then, the penetration force of the mixture MG ejected from the premixed gas supply section 23 increases, the combustion gas CG and the mixture MG are appropriately mixed, the combustion reaction is promoted, and the fuel gas FG is appropriately combusted. This makes it possible to suppress the generation of NOx.

The gas turbine combustor according to the second aspect is the gas turbine combustor according to the first aspect, and further includes jetting of the air-fuel mixture MG into the interior of the combustor main body 21 in the premixed gas supply sections 23 and 23A. A hole (spout part) 62 is arranged along the inner wall surface of the combustor main body 21 . Thereby, it is possible to eliminate protrusions on the inner wall surface of the combustor main body 21 and improve the fluidity of the combustion gas CG.

The gas turbine combustor according to the third aspect is the gas turbine combustor according to the first aspect, and further includes jetting of the mixture MG into the interior of the combustor main body 21 in the premixed gas supply sections 23 and 23A. A hole (spout part) 62 is arranged to protrude into the interior of the combustor body 21 from the inner wall surface of the combustor body 21 . Thereby, it is possible to improve the penetrating force of the air-fuel mixture MG ejected from the ejection holes 62 of the premixed gas supply sections 23 and 23A with respect to the combustion gas CG.

The gas turbine combustor according to the fourth aspect is the gas turbine combustor according to the first to third aspects, and further includes combustion between the deflection members 24, 24A and the premixed gas supply sections 23, 23A. The distance L in the axial direction of the combustor body 21 is shorter than 10 times the radial length H1 of the combustor body 21 at the deflection members 24, 24A protruding from the inner wall surface of the combustor body 21. Thereby, the combustion gas CG directed toward the injection hole 62 side of the premixed gas supply sections 23, 23A can be appropriately reduced by the deflection members 24, 24A.

The gas turbine combustor according to the fifth aspect is the gas turbine combustor according to the first to fourth aspects, and further includes premixed gas supply sections 23 and 23A extending in the circumferential direction of the combustor main body 21. A plurality of deflection members 24, 24A are arranged at intervals, and the deflection members 24, 24A are arranged at positions facing the plurality of premixed gas supply sections 23, 23A in the axial direction of the combustor main body 21. Thereby, the deflection members 24, 24A can appropriately reduce the influence of the combustion gas CG on the air-fuel mixture MG ejected from the premixed gas supply sections 23, 23A.

The gas turbine combustor according to the sixth aspect is the gas turbine combustor according to the first to fifth aspects, and further includes the premixed gas supply sections 23 and 23A extending in the axial direction of the combustor main body 21. Multiple locations are placed at intervals. Thereby, by improving the mixability of the combustion gas CG generated by combustion of the fuel gas FG supplied from the fuel supply section 22 and the air-fuel mixture MG supplied from the premixed gas supply sections 23 and 23A, Generation of NOx can be suppressed.

The gas turbine according to the seventh aspect includes a compressor 11 that generates high-temperature and high-pressure compressed air CA by compressing air A, and a high-temperature and high-pressure compressor 11 that generates high-temperature and high-pressure compressed air CA by supplying fuel gas FG to the compressed air CA and combusting it. The present invention includes a combustor 12 according to a first aspect to a sixth aspect that generates combustion gas CG, and a turbine 13 that is driven by the combustion gas CG. As a result, it is possible to suppress the generation of CO by improving the combustibility of the first-stage combustion gas FG, and improve the mixing properties of the first-stage combustion gas CG and the second-stage mixture MG. By doing so, the generation of NOx can be suppressed.

In addition, in the embodiment described above, the pilot combustion burner 53 and the plurality of main combustion burners 54 were provided as the fuel supply section 22, but the configuration is not limited to this.

10 Gas Turbine 11 Compressor 12, 12A Combustor (Gas Turbine Combustor)
13 Turbine 14 Rotating shaft 21 Combustor body 22 Fuel supply section 23, 23A Premixed gas supply section 24, 24A Deflection member 31 Outer tube 32 Inner tube 33 Transition tube (combustion tube)
33a Inner wall surface 41 Top hat part 42 Connecting member 43 Support member 44, 45 Air passage 53 Pilot combustion burner 54 Main combustion burner 55 Pilot cone 56 Pilot nozzle 57 Support column 58 Main nozzle 61, 61A Housing 62 Nozzle hole (spout part)
63 Air nozzle 64 Fuel nozzle 65 Guide part 71 Acoustic damper A Air CA Compressed air FG Fuel gas MG Mixture CG Combustion gas EG Exhaust gas O1, O2 Axial center

Claims (7)

A cylinder-shaped combustion tube,
a fuel supply unit that supplies fuel gas to the inside of the combustion cylinder;
a premixed gas supply section that supplies a premixed gas in which fuel and air are mixed into the combustion cylinder on the downstream side of the fuel supply section in the flow direction of combustion gas;
a deflection member that protrudes from an inner wall surface of the combustion cylinder toward the center of the combustion cylinder between the fuel supply part and the premixed gas supply part and deflects the flow of the combustion gas;
A gas turbine combustor comprising: In the premixed gas supply section, an ejection section for ejecting the premixed gas into the inside of the combustion tube is arranged along an inner wall surface of the combustion tube.
A gas turbine combustor according to claim 1. The premixed gas supply section is arranged such that a jetting section for ejecting the premixed gas into the interior of the combustion tube protrudes from an inner wall surface of the combustion tube into the inside of the combustion tube.
A gas turbine combustor according to claim 1. A distance L between the deflection member and the premixed gas supply section in the axial direction of the combustion tube is shorter than 10 times a radial length H1 of the combustion tube in the deflection member protruding from an inner wall surface of the combustion tube. ,
A gas turbine combustor according to any one of claims 1 to 3. A plurality of the premixed gas supply sections are arranged at intervals in the circumferential direction of the combustion tube, and the deflection member is located at a position facing the plurality of premixed gas supply sections in the axial direction of the combustion tube. be placed,
A gas turbine combustor according to claim 1. A plurality of the premixed gas supply units are arranged at intervals in the axial direction of the combustion cylinder,
A gas turbine combustor according to claim 1. A compressor that generates high-temperature, high-pressure compressed air by compressing air;
The gas turbine combustor according to claim 1, which generates high-temperature, high-pressure combustion gas by supplying fuel gas to the compressed air and combusting it;
a turbine driven by the combustion gas;
A gas turbine equipped with

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