JP2018128215A - Gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To suppress generation of combustion vibration while suppressing an amount of NOx emission.SOLUTION: A gas turbine combustor 2 according to the present invention comprises a burner 6 that comprises a plurality of fuel nozzles 26 and an air hole plate 31 with a plurality of air holes 32 formed corresponding to the plurality of fuel nozzles 26, and a combustion chamber 5 disposed on a downstream side of the burner 6. A wall surface on the combustion chamber 5 side of the air hole plate 31 is divided into a plurality of first areas 34A, a second area 34B between the first areas 34A adjacent to each other in the circumferential direction, and an annular third area 34C surrounding the outer periphery of the plurality of first areas 34A. The plurality of air holes 32 are opened in the first areas 34A or the third area 34C while avoiding the second areas 34B, in which the air holes forming the outermost peripheral air hole row are opened in the third area 34C such that each one is situated on the extension of each of the second areas 34B and the air holes forming other air hole rows than the outermost peripheral air hole row are opened in the first areas 34A at a narrower pitch than the circumferential width of the second area 34B.SELECTED DRAWING: Figure 3

Description

  The present invention relates to a gas turbine combustor.

  From the viewpoint of environmental protection, gas turbines including a compressor, a combustor, a turbine, and the like are required to further suppress NOx emissions.

  One way to reduce NOx emissions is to employ a premixed combustion type combustor. In this type of combustor, since fuel and air are mixed in advance and supplied to the combustion chamber, the temperature of the flame formed in the combustion chamber is made uniform, and NOx emission is suppressed. However, if the temperature of the air rises or the hydrogen content of the fuel increases, the combustion speed increases, and a so-called backfire occurs in which the flame formed in the combustion chamber flows back into the premixer, which can burn the combustor. There is sex. On the other hand, the fuel nozzle and the air hole formed in the air hole plate arranged on the downstream side of the fuel nozzle are provided so as to correspond to each other, and the mixture of fuel and air is ejected from each air hole. A combustor has been proposed (see Patent Document 1). This combustor is excellent in resistance to flashback because the air-fuel mixture is ejected from the individual air holes, that is, the restricted flow paths. In addition, the rapid expansion of the flow path at the time of ejection from the air hole further promotes the mixing of the air-fuel mixture, and the effect of suppressing the NOx emission amount is also high.

JP 2003-148734 A

  However, in the combustor of Patent Document 1, when the fuel is uniformly injected from the fuel nozzle in order to suppress the NOx emission amount, the fuel-air ratio of the air-fuel mixture ejected from the air holes arranged on the outer peripheral side of the air hole plate Tend to be larger. For this reason, the combustion speed increases, and the combustion vibration may occur due to the repeated attachment and detachment of the flame to the combustion chamber side wall of the air hole plate.

  The present invention has been made in view of the above, and an object of the present invention is to provide a combustor capable of suppressing the generation of combustion vibration while suppressing the NOx emission amount.

  In order to achieve the above object, a gas turbine combustor according to the present invention has a plurality of fuel nozzles for injecting fuel, and a plurality of air holes formed corresponding to the plurality of fuel nozzles. A burner including an air hole plate provided downstream of the fuel nozzle in the fuel flow direction, and fuel and air injected from the plurality of air holes disposed downstream of the burner in the fuel flow direction. And a combustion chamber side wall surface of the air hole plate includes a plurality of fan-shaped first regions arranged in a circumferential direction around a center point, A plurality of concentric air holes, each of which is divided into a second region between first regions adjacent to each other in a direction and an annular third region surrounding an outer periphery of the plurality of first regions. Avoiding the second region so as to form a row, the second The air holes that open in the region or the third region and constitute the outermost air hole array are opened in the third region so that one is located on each extension of the second region, The air holes constituting the other air hole rows except for the outermost air hole row are opened in the first region at a pitch narrower than the circumferential width of the second region.

  ADVANTAGE OF THE INVENTION According to this invention, the combustor which can suppress generation | occurrence | production of combustion vibration, suppressing NOx discharge | emission amount can be provided.

It is a figure showing the example of 1 composition of the gas turbine plant to which the combustor concerning a 1st embodiment of the present invention is applied. It is a fragmentary sectional view which shows the structure of the burner vicinity of the combustor which concerns on 1st Embodiment of this invention. It is the figure which looked at the burner which concerns on 1st Embodiment of this invention from the downstream of the flow direction of combustion gas. FIG. 4 is a cross-sectional view taken along arrow IV-IV in FIG. 3. It is a fragmentary sectional view which shows the structure of the burner vicinity of the combustor which concerns on a comparative example. It is the figure which looked at the burner which concerns on a comparative example from the downstream of the flow direction of combustion gas. It is a fragmentary sectional view which shows the structure of the burner vicinity of the combustor which concerns on 2nd Embodiment of this invention. It is the figure which looked at the burner which concerns on 2nd Embodiment of this invention from the downstream of the flow direction of combustion gas. It is arrow sectional drawing by the arrow IX-IX line of FIG. It is the figure which looked at the burner which concerns on the modification of 2nd Embodiment of this invention from the downstream of the flow direction of a combustion gas. It is arrow sectional drawing by the arrow XI-XI line of FIG. It is a fragmentary sectional view which shows the structure of the burner vicinity of the combustor which concerns on 3rd Embodiment of this invention. It is the figure which looked at the burner which concerns on 3rd Embodiment of this invention from the downstream of the flow direction of combustion gas. It is arrow sectional drawing by the arrow XIV-XIV line | wire of FIG. It is a fragmentary sectional view which shows the structure of the burner vicinity of the combustor which concerns on 4th Embodiment of this invention. It is the figure which looked at the burner which concerns on 4th Embodiment of this invention from the downstream of the flow direction of combustion gas. It is a fragmentary sectional view which shows the structure of the burner vicinity of the combustor which concerns on 5th Embodiment of this invention. It is the figure which looked at the burner which concerns on 5th Embodiment of this invention from the downstream of the flow direction of combustion gas. It is the figure which looked at the burner which concerns on 6th Embodiment of this invention from the downstream of the flow direction of combustion gas. FIG. 20 is a cross-sectional view taken along line XX-XX in FIG. 19.

<First Embodiment>
(Constitution)
1. Gas Turbine Plant FIG. 1 is a diagram illustrating a configuration example of a gas turbine plant to which a gas turbine combustor (hereinafter, combustor) according to the present embodiment is applied.

  As shown in FIG. 1, the gas turbine plant 100 according to this embodiment includes a gas turbine 101 and a load device 8.

  The gas turbine 101 includes a compressor 1, a combustor 2, and a turbine 3. The compressor 1 is rotationally driven by the turbine 3, compresses air (suction air) 15 sucked from the atmosphere via an intake portion (not shown), generates high-pressure air 16, and supplies the high-pressure air 16 to the combustor 2. When the gas turbine 101 is in a rated load operation, the high-pressure air 16 has a high temperature of 400 ° C. or higher depending on the pressure ratio. The combustor 2 mixes and burns the high-pressure air 16 supplied from the compressor 1 with fuel (in this embodiment, gas fuel) supplied from a fuel system 200 (described later), and generates high-temperature combustion gas 18. It is generated and supplied to the turbine 3. The turbine 3 is rotationally driven by the expansion of the combustion gas 18 supplied from the combustor 2. The combustion gas 18 that has driven the turbine 3 is exhausted from the turbine 3 as exhaust gas 19. The load device (generator in the present embodiment) 8 is connected coaxially with the turbine 3 and converts the rotational power of the turbine 3 into electric power. In the present embodiment, the compressor 1, the turbine 3, and the generator 8 are connected to each other by the shaft 7, and a part of the rotational power obtained by the turbine 3 drives the compressor 1.

2. Combustor The combustor 2 is attached to the casing 4 of the gas turbine 101. The combustor 2 includes a combustor liner (inner cylinder) 10, a flow sleeve (outer cylinder) 11, a tail cylinder inner cylinder 12, a tail cylinder outer cylinder 13, a burner 6, a fuel system 200, and a control device 61.

  The inner cylinder 10 is provided on the downstream side in the flow direction of the combustion gas 18 of the burner 6. Hereinafter, “upstream” and “downstream” in the flow direction of the combustion gas 18 are referred to as “combustion gas upstream” and “combustion gas downstream”. The inner cylinder 10 is a cylindrical member, and separates the high-pressure air 16 supplied from the compressor 1 from the combustion gas 18 generated by the combustor 2. The outer cylinder 11 is a cylindrical member having an inner diameter larger than that of the inner cylinder 10, and is provided on the outer peripheral side of the inner cylinder 10 so as to cover the inner cylinder 10. In the present embodiment, the outer cylinder 11 is disposed concentrically with the inner cylinder 10. An annular space formed between the inner cylinder 10 and the outer cylinder 11 constitutes an annular flow path (first annular flow path) 23 through which high-pressure air 16 supplied from the compressor 1 to the combustor 2 flows. Yes. The high-pressure air 16 flowing through the first annular flow path 23 convectively cools the inner cylinder 10 from the outer wall surface side of the inner cylinder 10. A large number of holes (not shown) are formed in the wall surface of the inner cylinder 10. A part of the high-pressure air 16 flowing through the first annular flow path 23 flows into the inner cylinder 10 from a large number of holes formed in the wall surface of the inner cylinder 10, and flows along the inner peripheral surface of the inner cylinder 10. A cooling air film is formed to cool the inner peripheral surface of the inner cylinder 10 (film cooling), and the inner cylinder 10 is protected from the high-temperature combustion gas 18. Of the high-pressure air 16 flowing through the first annular flow path 23, the portion not used for film cooling of the inner cylinder 10 flows through the first annular flow path 23 and reaches the burner 6 as combustion air 17. Combustion air 17 reaching the burner 6 is injected into the combustion chamber 5 formed inside the inner cylinder 10 together with the fuel supplied from the fuel system 200 to the burner 6 and burned.

  The combustion chamber 5 is disposed downstream of the burner 6 in the fuel flow direction. In the combustion chamber 5, the air-fuel mixture of the fuel injected from the plurality of air holes 32 formed in the air hole plate 31 (described later) of the burner 6 and the combustion air 17 is burned to generate the combustion gas 18. . The side of the inner cylinder 10 far from the burner 6 (combustion gas downstream side) is inserted into one end of the tail cylinder inner cylinder 12. The other end of the transition piece inner cylinder 12 is connected to a pipe line (not shown) connecting the combustor 2 and the turbine 3. The transition piece inner cylinder 12 has a function of guiding the combustion gas 18 generated in the combustion chamber 5 to the turbine 3. A cylindrical tail cylinder outer cylinder 13 that covers the tail cylinder inner cylinder 12 is provided on the outer peripheral side of the tail cylinder inner cylinder 12. The side of the outer cylinder 11 far from the burner 6 (downstream side of the combustion gas) is inserted into one end of the tail cylinder outer cylinder 13. The other end of the transition piece outer cylinder 13 opens into the casing 4. An annular space formed between the transition piece inner cylinder 12 and the transition piece outer cylinder 13 is formed in the first annular flow path 23 with high-pressure air 16 supplied from the compressor 1 to the combustor 2 and filled in the casing 4. An annular channel (second annular channel) 25 for guiding is configured. The high-pressure air 16 flowing through the second annular channel 25 convectively cools the tail cylinder inner cylinder 12 from the outer wall surface side of the tail cylinder inner cylinder 12.

2-1. Fuel System The fuel system 200 includes a common fuel system 50 and first and second fuel systems 51 and 52. The common fuel system 50 is connected to a fuel supply source (not shown). The first and second fuel systems 51 and 52 branch in parallel from the common fuel system 50 and are connected to a fuel header 24 (described later) provided in the burner 6. The number of fuel systems branched from the common fuel system 50 is not limited to two.

  A fuel shut-off valve (open / close valve) 20 for shutting off the fuel is provided on the upstream side of the fuel flow direction at the portion where the first and second fuel systems 51 and 52 of the common fuel system 50 are branched. The first and second fuel systems 51 and 52 are provided with first and second fuel flow rate adjusting valves 21 and 22, respectively. The flow rate of the fuel flowing through the first and second fuel systems 51 and 52 is adjusted (controlled) by the first and second fuel flow rate adjusting valves 21 and 22. In this embodiment, a control signal from the control device 61 is input to adjust the opening degree of the first and second fuel flow rate adjusting valves 21 and 22, and the flow rate of the fuel flowing through the first and second fuel systems is individually controlled. Thus, the power generation amount of the gas turbine plant 100 is controlled.

2-2. FIG. 2 is a partial cross-sectional view showing the structure near the burner of the combustor according to the present embodiment.

  As shown in FIG. 2, the combustor 2 according to this embodiment includes one burner 6. The burner 6 is disposed at the end of the inner cylinder 10 on the upstream side of the combustion gas so that the center axis 80 coincides with the center axis 81 of the inner cylinder 10. The burner 6 is divided into a plurality of concentric circular rings (three in this embodiment) centered on the central axis 80. In the following description, the plurality of annular rows of the burner 6 are appropriately referred to as a first row, a second row, and a third row, respectively, from the inner peripheral side toward the outer peripheral side. The burner 6 includes a fuel header 24, a plurality of fuel nozzles 26, and an air hole plate 31.

Fuel Header The fuel header 24 is provided on the upstream side of the combustion gas of the inner cylinder 10. In the present embodiment, the fuel header 24 is partitioned into a first fuel header 24A and a second fuel header 24B in order from the central axis 80 of the burner 6 toward the radially outer side. A first fuel system 51 is connected to the first fuel header 24A, and a second fuel system 52 is connected to the second fuel header 24B. The first and second fuel headers 24 </ b> A and 24 </ b> B distribute the fuel supplied from the fuel supply source via the first and second fuel systems 51 and 52 to the fuel nozzle 26.

Fuel Nozzle A plurality of fuel nozzles 26 are supported by the fuel header 24. The fuel nozzle 26 injects the fuel distributed from the fuel header 24 into the combustion chamber 5 through the air holes 32 formed in the air hole plate 31. In the present embodiment, the plurality of fuel nozzles 26 are concentrically arranged in the first to third rows, and are provided over the entire circumference of each row.

  In the present embodiment, the plurality of fuel nozzles 26 includes a first fuel nozzle 26A and a second fuel nozzle 26B. The first fuel nozzle 26A is supported by the first fuel header 24A, and the second fuel nozzle 26B is supported by the second fuel header 24B. The first fuel nozzles 26A are arranged in the first row, and the second fuel nozzles 26B are arranged in the second and third rows. The fuel distributed from the first fuel header 24A to the first fuel nozzle 26A is injected from the tip of the first fuel nozzle 26A and supplied to the combustion chamber 5. The fuel distributed from the second fuel header 24B to the second fuel nozzle 26B is injected from the tip of the second fuel nozzle 26B and supplied to the combustion chamber 5.

Air hole plate The air hole plate 31 is a disk-shaped plate coaxial with the inner cylinder 10. The air hole plate 31 is held inside the inner cylinder 10 via the spring seal 30. The spring seal 30 is provided between the outer peripheral surface of the air hole plate 31 and the inner cylinder 10. In the present embodiment, the air hole plate 31 is provided on the downstream side in the fuel flow direction of the plurality of fuel nozzles 26 so as to be separated from the tips of the plurality of fuel nozzles 26. That is, the plurality of fuel nozzles 26 are not inserted into the plurality of air holes 32 formed in the air hole plate 31.

  The air hole plate 31 has a plurality of air holes 32. In the present embodiment, the plurality of air holes 32 are concentrically arranged in the first to third rows, and are provided over the entire circumference of each row. The plurality of air holes 32 are formed so that one air hole 32 corresponds to the fuel nozzle 26 on the downstream side in the fuel flow direction of one fuel nozzle 26. As described above, by providing the plurality of fuel nozzles 26 and the plurality of air holes 32 so as to correspond to each other (facing each other), the air-fuel mixture 29 of the fuel and the combustion air 17 can be ejected from each air hole 32. .

  The air hole 32 is formed in a slanted cylindrical shape in which the two ellipses constituting the upstream and downstream openings in the fuel flow direction and the generatrix are not orthogonal to each other. Hereinafter, the upstream and downstream openings of the air holes 32 in the fuel flow direction are referred to as “inlet” and “outlet”. The plurality of air holes 32 are swirl air holes having a swirl angle, and their outlets are deviated from the inlet in the circumferential direction of the air hole plate 31. That is, the air hole 32 is formed such that a central axis obtained by connecting the centers of the inlet and the outlet is inclined with respect to the air hole plate 31 in the circumferential direction. Thereby, the swirl component is given to the air-fuel mixture 29 flowing through the air holes 32.

  3 is a view of the burner according to the present embodiment as viewed from the downstream side in the flow direction of the combustion gas, and FIG. 4 is a cross-sectional view taken along line IV-IV in FIG.

  As shown in FIG. 3, in the present embodiment, the wall surface (combustion wall surface) 34 on the combustion chamber side of the air hole plate 31 has a plurality of fan-shaped first regions 34 </ b> A arranged around the center point C in the circumferential direction. And a second region 34B between the first regions 34A adjacent in the circumferential direction, and an annular third region 34C surrounding the outer periphery of the plurality of first regions 34A.

  The plurality of air holes 32 formed in the air hole plate 31 are open to the first area 34A or the third area 34C, avoiding the second area 34B so as to constitute a plurality of concentric air hole arrays. That is, the second region 34B is formed by unevenly forming the openings of the air holes 32 in the first region 34A in the circumferential direction, and the air holes 32 are not opened (the openings of the air holes 32 are formed). Is not). In the present embodiment, the second region 34B extends linearly outward from the center point C in the radial direction. In the following description, among the plurality of air holes 32, the air holes 32 that open to the first area 34A are appropriately referred to as inner air holes 32A, and the air holes 32 that open to the third area 34C are appropriately referred to as outer air holes 32C.

  In the present embodiment, the inner air holes 32A are arranged in the first and second rows. The inner air holes 32A constitute other air hole arrays excluding the outermost air hole array. In the present embodiment, the outermost air hole row refers to an air hole row formed in the third region 34C and configured by the outer air holes 32C. In the present embodiment, the inner air holes 32A open to the first region 34A at a pitch narrower than the circumferential width W of the second region 34B. That is, in the combustion wall surface 34 of the air hole plate 31, the pitch of the openings of the inner air holes 32A disposed adjacently in the circumferential direction across the second region 34B is the inner air hole disposed in the first region 34A. It is wider than the pitch of the openings of 32A.

  In the present embodiment, the outer air holes 32C are arranged in the third row and constitute the outermost hole row. The outer air holes 32C open to the third region 34C so that one of the outer air holes 32C is located on each extension of the second region 34B. In the present embodiment, in the combustion wall surface 34 of the air hole plate 31, the circumferential width W of the second region 34B is equal to or less than the major diameter Dc of the opening of the outer air hole 31C.

  As shown in FIG. 4, a combustion gas flow path 46 is formed on the combustion wall surface 34 of the air hole plate 31 corresponding to the second region 34B. In the present embodiment, the combustion gas flow path 46 refers to the combustion gas that has been pushed toward the base of the flame 42 in the combustion wall surface 34 of the air hole plate 31 by the circulating flow 41 of the combustion gas 18 generated in the combustion chamber 5. Is a flow path for guiding the air to the outer air hole 32C. In the present embodiment, the combustion gas flow path 46 includes a wall surface corresponding to the second region 34B of the combustion wall surface 34 of the air hole plate 31, and an inner air hole disposed adjacent to the circumferential direction across the second region 34B. It is composed of a space surrounded by the air-fuel mixture 29 ejected from 32A.

(Operation)
As shown in FIG. 2, the combustion air 17 that has reached the burner 6 passes between the plurality of fuel nozzles 26 and flows toward the central axis 80 of the burner 6. It flows into the air hole 32. On the other hand, the fuel distributed from the first and second fuel systems 51 and 52 to the first and second fuel nozzles 26A and 26B via the first and second fuel headers 24A and 24B is supplied to the first and second fuel nozzles 26A and 26B. It is injected from the tip, supplied to the plurality of air holes 32, and mixed with the combustion air 17 to generate an air-fuel mixture 29. In the present embodiment, since the air holes 32 are swirl air holes, a force component in the swirl direction is applied to the air-fuel mixture 29 flowing through the air holes 32. Thereby, a swirl flow 40 is formed in the combustion chamber 5, and a flame 42 is formed in the combustion chamber 5 by the circulating flow 41 generated by the swirl flow 40.

  A part of the high-temperature combustion gas 18 generated in the combustion chamber 5 is swept away by the circulation flow 41 as the circulation combustion gas 43 toward the base of the flame 42 on the combustion wall surface 34 of the air hole plate 31. As shown in FIG. 3, the circulating combustion gas 43 swept toward the base of the flame 42 passes through the combustion gas passage 46 formed corresponding to the second region 34B of the combustion wall surface 34 of the air hole plate 31. To the outer air hole 32C.

(effect)
(1) Suppression of NOx Emission and Combustion Vibration FIG. 5 is a partial sectional view showing the structure near the burner of the combustor according to the comparative example, and FIG. 6 is a view of the burner according to the comparative example from the downstream side in the combustion gas flow direction. It is a figure.

  As shown in FIG. 6, a plurality of air holes H are opened at an equal pitch over the entire circumference of each row on the combustion wall surface of the air hole plate P included in the burner B according to the comparative example. That is, the air hole plate P included in the burner B according to the comparative example does not have the above-described second region 34B.

  As shown in FIG. 5, even in the combustor according to the comparative example, a part of the combustion gas G generated in the combustion chamber D is swept to the base of the flame F by the circulation flow C. Then, heat is supplied from the combustion gas G pushed to the base of the flame F to the air-fuel mixture M1 ejected from the plurality of air holes H1 arranged in the first row of the air hole plate P. It is formed stably.

  In general, the fuel-air ratio (fuel / air mass flow ratio) of the air-fuel mixture M1 ejected from the plurality of air holes H1 arranged in the first row of the air hole plate P is arranged in the second and third rows. The fuel / air ratio of the air-fuel mixture ejected from the plurality of air holes H2 and H3 is made larger, and the flame formed by the air-fuel mixture M1 ejected from the plurality of air holes H1 arranged in the first row is made higher in temperature. With this, the flame can be made more stable. On the other hand, in order to suppress the NOx emission amount, when the fuel supplied to the combustor is constant, the fuel-air ratio of the air-fuel mixture M1 ejected from the plurality of air holes H1 arranged in the first row and the second and third The ratio of the fuel supplied to the plurality of air holes H1 arranged in the first row is reduced so that the fuel-air ratio of the air-fuel mixture ejected from the plurality of air holes H2, H3 arranged in the row becomes equal, and the second , It is necessary to increase the ratio of fuel supplied to the plurality of air holes H2 and H3 arranged in three rows. In this case, the fuel-air ratio of the air-fuel mixture ejected from the plurality of air holes H2 and H3 arranged in the second and third rows is increased, and the mixture is ejected from the plurality of air holes H2 and H3 arranged in the second and third rows. As the combustion speed of the flame formed by the air-fuel mixture is increased, the flame is likely to adhere to the air hole plate P. As a result, the flame formed by the air-fuel mixture ejected from the plurality of air holes H2 and H3 arranged in the second and third rows repeatedly attaches and detaches to the combustion wall surface on the radially outer side of the air hole plate P. And combustion vibration may occur.

  In the present embodiment, the combustion wall surface 34 of the air hole plate 31 is partitioned into a first region 34A, a second region 34B, and a third region 34C, and the plurality of air holes 32 are avoided from the second region 34B. Openings are made in the third region 34C, and the outer air holes 32C are opened in the third region 34C so that each one is located on the extension of the second region 34B. Therefore, the circulating combustion gas 43 can be guided to the outer air hole 32C through the combustion gas passage 46 formed corresponding to the second region 34B. Thereby, in addition to the air-fuel mixture 29 ejected from the inner air hole 32A, heat can also be supplied to the air-fuel mixture 29 ejected from the outer air hole 32C. Therefore, the flame formed by the air-fuel mixture 29 ejected from the outer air holes 32C can be stably attached to the combustion wall surface 34 of the air hole plate 31 and is attached to the combustion wall surface 34 on the radially outer peripheral side of the air hole plate 31. The variation in the axial direction of the formed flame can be suppressed, and the repeated attachment and detachment of the flame to the combustion wall surface 34 of the air hole plate 31 can be suppressed. From the above, the ratio of the fuel supplied to the plurality of air holes 32 arranged in the first row is reduced, and the ratio of the fuel supplied to the plurality of air holes 32 arranged in the second and third rows is increased. Combustion vibration can be suppressed while suppressing the discharge amount.

(2) Suppression of high-frequency combustion vibration As one type of combustion vibration, there is a high-frequency vibration that can be generated by the propagation of pressure waves generated in the combustor in the circumferential direction and radial direction.

  In the present embodiment, since the circulating combustion gas 43 can be guided to the outer air hole 32C through the combustion gas flow path 46 formed corresponding to the second region 34B, the air-fuel mixture 29 injected from the inner air hole 32A. Can be divided in the circumferential direction by the circulating combustion gas 43. Thereby, propagation of the pressure wave generated in the combustor in the circumferential direction can be suppressed, and occurrence of combustion vibration having a high frequency can be suppressed.

(3) Suppression of decrease in heat supply efficiency Generally, as the width W of the second region 34B (that is, the combustion gas passage 46) is increased, the circulating combustion gas 43 with respect to the air-fuel mixture 29 ejected from the outer air holes 32C The amount of heat supplied from can be increased, and combustion vibration can be further suppressed by that amount. On the other hand, if the width W of the second region 34B is too large, the circulating combustion gas 43 may leak out of the burner 6 from the gap between the outer air holes 32C adjacent in the circumferential direction. If it does so, the supply efficiency of the heat | fever with respect to the air-fuel mixture 29 which ejects from 32 C of outer air holes falls, and the heat supplied to the air-fuel mixture 29 which ejects from 32 C of outer air holes reduces, and a flame may become unstable. There is.

  In this embodiment, since the width W of the second region 34B is set to be equal to or smaller than the major axis of the opening of the outer air hole 32C, the heat from the circulating combustion gas 43 is supplied to the air-fuel mixture 29 ejected from the outer air hole 32C without leakage. can do. Thereby, it can avoid that the supply efficiency of the heat | fever with respect to the air-fuel mixture 29 ejected from the outer side air hole 32C falls, and can ensure the stability of a flame.

Second Embodiment
(Constitution)
7 is a partial cross-sectional view showing a structure near the burner of the combustor according to the present embodiment, FIG. 8 is a view of the burner according to the present embodiment as viewed from the downstream side in the flow direction of the combustion gas, and FIG. It is arrow sectional drawing by the arrow IX-IX line. 7-9, the same code | symbol is attached | subjected to the part equivalent to the said 1st Embodiment, and description is abbreviate | omitted suitably.

  As shown in FIGS. 7 to 9, the combustor according to the present embodiment is different from the combustor 2 according to the first embodiment in that the air hole plate 131 includes a groove portion 47. Other configurations are the same as those of the combustor 2 according to the first embodiment.

  As shown in FIG. 8, the groove 47 is formed in a straight line along the second region 34 </ b> B on the combustion wall surface 34 of the air hole plate 131. As shown in FIG. 9, the groove portion 47 is provided as a concave portion recessed from the combustion wall surface 34 of the air hole plate 131 to the upstream side in the flow direction of the air-fuel mixture 29 (inlet side of the inner air hole 32 </ b> A). In this embodiment, the groove part 47 is formed so that a cross section becomes a rectangular shape. The depth D of the groove 47 is smaller than the circumferential width W of the second region 34B. In the present embodiment, the depth D of the groove portion 47 refers to a length from the combustion wall surface 34 of the air hole plate 131 of the groove portion 47 toward the upstream side in the flow direction of the air-fuel mixture 29. In the present embodiment, the combustion gas flow path 59 is an inner air hole disposed adjacent to the inner wall surface of the groove portion 47 formed in the combustion wall surface 34 of the air hole plate 131 and the second region 34B in the circumferential direction. It is composed of a space surrounded by the air-fuel mixture 29 ejected from 32A. In the present embodiment, the configuration in which the groove portions 47 are provided corresponding to all the second regions 34B is illustrated, but the groove portions 47 may be provided corresponding to only some of the second regions 34B.

(effect)
In the present embodiment, in addition to the same effects as in the first embodiment, the following effects can be obtained.

  In this embodiment, the groove part 47 is provided in the combustion wall surface 34 of the air hole plate 131 along the 2nd area | region 34B. Therefore, the combustion gas channel 59 can be secured larger by the groove portion 47 than the combustion gas channel 46 of the first embodiment. Therefore, the circulating combustion gas 43 can be more reliably guided to the outer air hole 32C, and heat can be supplied to the air-fuel mixture 29 ejected from the outer air hole 32C. Thereby, combustion vibration can be more reliably suppressed. In addition, in the present embodiment, since the depth D of the groove 47 is smaller than the width W of the second region 34B, the strength of the air hole plate 131 can be ensured.

<Modification>
10 is a view of the burner according to this modification as viewed from the downstream side in the flow direction of the combustion gas, and FIG. 11 is a cross-sectional view taken along line XI-XI in FIG. 10 and 11, the same reference numerals are given to the same parts as those in the second embodiment, and the description will be omitted as appropriate.

  As shown in FIGS. 10 and 11, the combustor according to this modification is different from the combustor according to the second embodiment in that the air hole plate 231 includes a round groove portion 60 instead of the groove portion 47. Other configurations are the same as those of the combustor 2 according to the second embodiment.

  As shown in FIG. 10, the round groove portion 60 is formed linearly along the second region 31 </ b> B on the combustion wall surface 34 of the air hole plate 231. As shown in FIG. 11, the round groove 60 has a semicircular cross section. The radius length (depth) R of the round groove 60 is smaller than the circumferential width W of the second region 31B. In this modification, the combustion gas channel 55 is disposed adjacent to the inner circumferential surface of the round groove portion 60 formed on the combustion wall surface 34 of the air hole plate 231 in the circumferential direction across the second region 34B. The space is surrounded by the air-fuel mixture 29 ejected from the inner air hole 32A. In addition, in this modification, although the structure which provided the circular groove part 60 corresponding to all the 2nd area | regions 34B is illustrated, the circular groove part 60 is provided corresponding only to some 2nd area | regions 34B. May be.

  Even if the round groove portion 60 is provided on the combustion wall surface 34 of the air hole plate 231 as in this modification, the same effect as in the second embodiment can be obtained. In addition, in this modified example, since the round groove portion 60 having a semicircular cross section is provided, corners and corner portions where thermal stress is likely to be concentrated can be reduced, and the reliability of the air hole plate 231 is correspondingly reduced. Sex can be secured. In this modification, the configuration in which the round groove 60 having a semicircular cross section is described. However, for example, the same effect as described above can be obtained by providing the groove having a semielliptical cross section.

<Third Embodiment>
(Constitution)
12 is a partial cross-sectional view showing a structure near the burner of the combustor according to the present embodiment, FIG. 13 is a view of the burner according to the present embodiment as viewed from the downstream side in the flow direction of the combustion gas, and FIG. It is arrow sectional drawing by the arrow XIV-XIV line. 12-14, the same code | symbol is attached | subjected to the part equivalent to the said 1st Embodiment, and description is abbreviate | omitted suitably.

  As shown in FIGS. 12 to 14, the combustor according to this embodiment is different from the combustor 2 according to the first embodiment in that an air hole plate 331 includes a side wall portion 48. Other configurations are the same as those of the combustor 2 according to the first embodiment.

  As shown in FIG. 13, the side wall portion 48 is provided linearly along the second region 34 </ b> B on both sides in the width direction of the second region 34 </ b> B on the combustion wall surface 34 of the air hole plate 331. As shown in FIG. 14, the side wall 48 is provided so as to protrude from the combustion wall surface 34 of the air hole plate 331 toward the downstream side (combustion chamber 5 side) in the flow direction of the air-fuel mixture 29. The height E of the side wall portion 48 is a size that does not block the flow of the air-fuel mixture 29 ejected from the inner air holes 32A adjacent to each other in the circumferential direction across the second region 34B. The width is smaller than the circumferential width W of the two regions 34B. In the present embodiment, the height of the side wall portion 48 refers to a length from the combustion wall surface 34 of the air hole plate 331 of the side wall portion 48 toward the downstream side in the flow direction of the air-fuel mixture 29. In the present embodiment, the combustion gas flow path 56 includes a wall surface corresponding to the second region 34B of the combustion wall surface 34 of the air hole plate 331, a wall surface facing the second region 34B of the side wall portion 48, and a second region. It is composed of a space surrounded by the air-fuel mixture 29 that is ejected from the inner air holes 32A that are arranged adjacent to each other in the circumferential direction across 34B. In the present embodiment, the configuration in which the side wall portions 48 are provided corresponding to all the second regions 34B is illustrated, but the side wall portions 48 may be provided only for some of the second regions 34B. good.

(effect)
In the present embodiment, in addition to the same effects as in the first embodiment, the following effects can be obtained.

  In the present embodiment, side wall portions 48 are provided along the second region 34B on both sides in the width direction of the second region 34B. Therefore, the circulating combustion gas 43 flowing through the second region 34B (that is, the combustion gas flow path 56) is less likely to receive interference from the surrounding flow. Therefore, the heat of the circulating combustion gas 43 can be more reliably supplied to the air-fuel mixture 29 ejected from the outer air holes 32C.

  In the present embodiment, the configuration in which the side wall portion 48 is provided along the second region 34B on both sides in the width direction of the second region 34B is illustrated. However, in addition to the side wall portion 48, the groove portion 47 and the round groove portion 60 are provided. It may be provided. In this case, the heat of the circulating combustion gas 43 can be more reliably supplied to the air-fuel mixture 29 ejected from the outer air holes 32C.

<Fourth embodiment>
(Constitution)
FIG. 15 is a partial cross-sectional view showing the structure near the burner of the combustor according to the present embodiment, and FIG. 16 is a view of the burner according to the present embodiment as viewed from the downstream side in the flow direction of the combustion gas. 15 and 16, the same reference numerals are given to the same parts as those in the first embodiment, and the description will be omitted as appropriate.

  As shown in FIGS. 15 and 16, the combustor according to this embodiment is different from the combustor 2 according to the first embodiment in that an air hole plate 431 includes a cooling hole 49. Other configurations are the same as those of the combustor 2 according to the first embodiment.

  The air hole plate 431 according to this embodiment includes a plurality of cooling holes 49. In the configuration illustrated in FIG. 16, four cooling holes 49 are provided in the second region 34B of the combustion wall surface 34 of the air hole plate 431, and 12 cooling holes 49 are provided in the combustion wall surface 34 of the air hole plate 431. Is provided. The plurality of cooling holes 49 are open at linear intervals in the second region 34 </ b> B of the combustion wall surface 34 of the air hole plate 431. In the present embodiment, a part of the combustion air 17 that has reached the burner 6 flows into the cooling hole 49 as a cooling medium, and is ejected from the opening in the second region 34B of the combustion wall surface 34 of the air hole plate 431 into the combustion chamber 5. To do. The inner diameter of the cooling hole 49 is such that the strength of the air hole plate 431 does not decrease, and the combustion air 17 ejected from the cooling hole 49 is reduced in the second region 34B of the combustion wall surface 34 of the air hole plate 431. The flow rate is set to a level that does not hinder the flow (impede the flow of the circulating combustion gas 43 toward the outer air hole 32C). In the present embodiment, the configuration in which the cooling holes 49 are provided corresponding to all the second regions 34B is illustrated, but the cooling holes 49 may be provided corresponding to only some of the second regions 34B. good. Moreover, although the structure which provided the four cooling holes 49 in the combustion wall surface 34 of the air hole plate 431 is illustrated, the number of the cooling holes 49 does not need to be four, three or less may be sufficient and five or more But it ’s okay.

(effect)
In the present embodiment, in addition to the same effects as in the first embodiment, the following effects can be obtained.

  In the present embodiment, a cooling hole 49 opening in the second region 34B of the combustion wall surface 34 of the air hole plate 431 is provided. Therefore, even when the combustion wall surface 34 of the air hole plate 431 can be excessively heated by the high-temperature circulating combustion gas 43, the combustion wall surface 34 of the air hole plate 431 is cooled by flowing the combustion air 17 through the cooling holes 49. be able to. Therefore, the combustion wall surface 34 of the air hole plate 431 can be suppressed from being excessively heated, and the reliability of the air hole plate 431 can be ensured.

<Fifth Embodiment>
(Constitution)
FIG. 17 is a partial cross-sectional view showing the structure in the vicinity of the burner of the combustor according to the present embodiment, and FIG. 18 is a view of the burner according to the present embodiment as viewed from the downstream side in the flow direction of the combustion gas. 17 and 18, the same reference numerals are given to the same parts as those in the first embodiment, and the description will be omitted as appropriate.

  As shown in FIGS. 17 and 18, the combustor according to this embodiment is different from the combustor 2 according to the first embodiment in that it includes a multi-burner 58 having a plurality of burners 6 (seven in this embodiment). Other configurations are the same as those of the combustor 2 according to the first embodiment.

  In the combustor according to the present embodiment, one burner 6 is arranged as the central burner 35 so as to coincide with the central axis 81 of the inner cylinder 10 at the center of the combustion portion, and other plural (six in the present embodiment) are arranged. A burner 6 is arranged as an outer peripheral burner 36 around the central burner 35. In the present embodiment, the central burner 35 and the outer peripheral burner 36 share the air hole plate 31. That is, the air hole plate 531 according to the present embodiment corresponds to the outer peripheral burner 36 on the outer peripheral side of the plurality of air holes 32 corresponding to the central burner 35 and the plurality of air holes 32 formed corresponding to the central burner 35. A plurality of air holes 32 are formed.

  As shown in FIG. 17, in the present embodiment, the first fuel system 51 is connected to the first fuel header 24A of the center burner 35, and the second fuel system 52 is connected to the second fuel header 24B. On the other hand, the third fuel system 53 is connected to the first fuel header 24A of the outer peripheral burner 36, and the fourth fuel system 54 is connected to the second fuel header 24B. The third and fourth fuel systems 53 and 54 are branched in parallel with the first and second fuel systems 51 and 52 from the common fuel system 50 (see FIG. 1). The third and fourth fuel systems 53 and 54 are provided with third and fourth fuel flow rate adjustment valves (not shown). The third and fourth fuel flow rate adjustment valves have the same structure as the first and second fuel flow rate adjustment valves 21 and 22 (see FIG. 1) provided in the first and second fuel systems. The flow rate of the fuel flowing through the four fuel system is adjusted by the third and fourth fuel flow rate adjusting valves. In the present embodiment, a control signal from the control device 61 (see FIG. 1) is input to adjust the opening degree of the first to fourth fuel flow rate adjustment valves, and the flow rate of the fuel flowing through the first to fourth fuel systems is individually determined. By controlling the power generation, the power generation amount of the gas turbine plant 100 is controlled.

(Operation)
The combustion air 17 that has reached the burner 6 passes between the plurality of fuel nozzles 26 of the outer burner 36 and flows into the plurality of air holes 32 corresponding to the outer burner 36 of the air hole plate 531, while The air passes through the plurality of fuel nozzles 26 and flows into the plurality of air holes 32 corresponding to the central burner 35 of the air hole plate 531. On the other hand, the fuel distributed from the first to fourth fuel systems 51 to 54 to the first and second fuel nozzles 26A and 26B via the first and second fuel headers 24A and 24B is supplied to the first and second fuel nozzles 26A and 26B. It is injected from the tip and supplied to a plurality of air holes 32 corresponding to the central burner 35 and the outer peripheral burner 36, and mixed with the combustion air 17 to generate an air-fuel mixture 29. Similar to the first embodiment, a force component in the swirling direction is applied to the air-fuel mixture 29 generated by the plurality of air holes 32, thereby forming a swirl flow 40 in the combustion chamber 5, and circulation generated by the swirl flow 40. A flame 42 is formed in the combustion chamber 5 by the flow 41.

  The circulating combustion gas 43 urged by the circulating flow 41 toward the combustion wall surface 34 of the air hole plate 531 is formed on the combustion wall surface 34 of the air hole plate 531 corresponding to the second region 34B of the central burner 35 and the outer peripheral burner 36. Then, the air is guided to the outer air hole 32C through the combustion gas flow path 46.

(effect)
Even in the case of a combustor including a multi-burner 58 as in the present embodiment, the same effects as in the first embodiment can be obtained. In addition, in the present embodiment, the following effects can be obtained.

  In the present embodiment, in a combustor including a multi-burner 58 in which a plurality of outer peripheral burners 36 are arranged around the central burner 35, the first and second fuel systems 51, 51 are connected to the first and second fuel headers 24 A and 24 B of the central burner 35. 52, and the third and fourth fuel systems 53 and 54 are connected to the first and second fuel headers 24A and 24B of the outer peripheral burner 36, respectively. Therefore, it is possible to flexibly cope with a load change of the gas turbine plant 100. Moreover, since the capacity | capacitance per combustor can be changed only by changing the number of burners provided in a combustor, a combustor with a different capacity | capacitance can be provided easily.

<Sixth Embodiment>
(Constitution)
19 is a view of the burner according to the present embodiment as viewed from the downstream side in the flow direction of the combustion gas, and FIG. 20 is a cross-sectional view taken along the line XX-XX in FIG. 19 and 20, parts that are the same as in the first embodiment are given the same reference numerals, and descriptions thereof will be omitted as appropriate.

  As shown in FIG. 19, the combustor according to this embodiment is different from the combustor 2 according to the first embodiment in the shape of the second region 34 </ b> B included in the air hole plate 631. Other configurations are the same as those of the combustor 2 according to the first embodiment.

  The second region 34 </ b> B of the air hole plate 631 according to the present embodiment is formed in a meandering shape that meanders in the circumferential direction along the combustion wall surface 34 of the air hole plate 631. That is, in the present embodiment, the plurality of air holes 32 formed in the air hole plate 31 open to the first area 34A while avoiding the second area 34B so that the second area 34B of the air hole plate 631 meanders. ing. In the present embodiment, the width of the second region 34B is substantially constant from the center point C to the outer air hole 32C.

  As shown in FIG. 20, in the present embodiment, the combustion gas channel 57 is a wall surface corresponding to the second region 34 </ b> B of the combustion wall surface 34 of the air hole plate 31, similar to the combustion gas channel 46 according to the first embodiment. And a space surrounded by the air-fuel mixture 29 ejected from the inner air holes 32A disposed adjacent to each other in the circumferential direction across the second region 34B.

(effect)
Even when the second region 34B of the air hole plate 31 has a meandering shape as in the present embodiment, the same effect as in the first embodiment can be obtained. In addition, in the present embodiment, the following effects can be obtained.

  In the present embodiment, since the second region 34B of the air hole plate 31 has a meandering shape, when the circulating combustion gas 43 flows toward the outer air hole 32C while meandering the second region 34B, it is ejected from the inner air hole 32A. This prevents the air-fuel mixture 29 from interfering with the circulating combustion gas 43.

<Others>
The present invention is not limited to the above-described embodiments, and includes various modifications. For example, each of the above-described embodiments has been described in detail for easy understanding of the present invention, and is not necessarily limited to one having all the configurations described. For example, a part of the configuration of an embodiment can be replaced with the configuration of another embodiment, and the configuration of another embodiment can be added to the configuration of an embodiment. It is also possible to delete a part of the configuration of each embodiment.

  In each embodiment mentioned above, the composition which provided three 2nd fields 34B in combustion wall surface 34 of air hole plate 31 was illustrated. However, the essential effect of the present invention is to provide a combustor capable of suppressing the generation of combustion vibration while suppressing the NOx emission amount, and is not necessarily limited to the above-described configuration as long as this essential effect is obtained. . For example, the number of the second regions 34B provided on the combustion wall surface 34 of the air hole plate 31 may be two, or four or more.

  Further, in each of the above-described embodiments, the configuration in which the burner 6 is divided into three concentric annular rows is illustrated. However, as long as the essential effects of the present invention described above are obtained, the configuration is not necessarily limited to that described above. For example, the number of annular rows may be two, or four or more.

  Moreover, in each embodiment mentioned above, the structure which has arrange | positioned so that the several air hole 32 may comprise a concentric air hole row | line was illustrated. However, as long as the essential effects of the present invention described above are obtained, the configuration is not necessarily limited to that described above. As long as the plurality of air holes 32 are arranged in an annular shape, it is not always necessary to form a concentric air hole array, and the centers of the plurality of air hole arrays are different in each array. The structure which is made may be sufficient.

  In the fifth embodiment described above, the configuration in which the second region 34 </ b> B is provided on the combustion wall surface 34 of the air hole plate 31 corresponding to the central burner 35 and the plurality of outer peripheral burners 36 is exemplified. However, as long as the essential effects of the present invention described above are obtained, the configuration is not necessarily limited to that described above. For example, it is good also as a structure which provides the 2nd area | region 34B corresponding to only some burners among the center burner 35 and the some outer periphery burner 36. FIG. In general, the flame 42 formed by the outer peripheral burner 36 is stabilized by supplying heat from the flame 42 formed by the central burner 35. Therefore, when the flame 42 formed by the central burner 35 becomes unstable, the flame 42 formed by the outer peripheral burner 36 also becomes unstable due to the influence, and the combustion of the combustor 2 becomes unstable. Therefore, by providing the second region 34B corresponding to only the central burner 35 on the combustion wall surface 34 of the air hole plate 31, combustion vibration of the central burner 35 is suppressed, and combustion of the combustor 2 is stabilized.

  In the fifth embodiment described above, the configuration in which the number, shape, and circumferential position of the second regions 34B corresponding to the central burner 35 and the plurality of outer peripheral burners 36 are the same is illustrated. However, as long as the essential effects of the present invention described above are obtained, the configuration is not necessarily limited to that described above. For example, the number, shape, and circumferential position of the second region 34B may be different for each burner. That is, the number of the second regions 34B corresponding to some of the central burner 35 and the plurality of outer peripheral burners 36 may be two or four or more. Moreover, it is good also as a structure which provides the groove part 47 or the round-shaped groove part 60, and the side wall part 48 in the 2nd area | region 34B corresponding to a one part burner.

5 Combustion chamber 6 Burner 18 Combustion gas 26 Fuel nozzle 31 Air hole plate 32 Air hole 34A First region 34B Second region 34C Third region

Claims (6)

An air hole plate having a plurality of fuel nozzles for injecting fuel and a plurality of air holes formed corresponding to the plurality of fuel nozzles and provided downstream of the fuel flow direction of the plurality of fuel nozzles A burner comprising
A combustion chamber that is disposed downstream of the burner in the fuel flow direction, and that burns fuel and air injected from the plurality of air holes to generate combustion gas;
The combustion chamber side wall surface of the air hole plate has a plurality of fan-shaped first regions arranged in the circumferential direction around a center point, a second region between first regions adjacent in the circumferential direction, and a plurality of regions. Is divided into an annular third region surrounding the outer periphery of the first region,
The plurality of air holes open to the first region or the third region avoiding the second region so as to constitute a plurality of concentric air hole rows,
The air holes constituting the outermost air hole row are opened in the third region so that one of the air holes is located on each extension of the second region,
The air holes constituting the other air hole rows except for the outermost air hole row open to the first region at a pitch narrower than the circumferential width of the second region. Turbine combustor. The gas turbine combustor according to claim 1.
The gas turbine combustor according to claim 1, wherein a width of the second region in the circumferential direction is formed to be equal to or less than a major axis of air hole openings constituting the outermost air hole array. The gas turbine combustor according to claim 2.
The gas hole combustor, wherein the air hole plate includes a groove portion formed along the second region on a wall surface on the combustion chamber side. The gas turbine combustor according to claim 2.
The air hole plate is formed so as to protrude from the wall surface on the combustion chamber side toward the combustion chamber, and includes side wall portions provided along the second region on both sides in the width direction of the second region. Characteristic gas turbine combustor. The gas turbine combustor according to claim 2.
The gas turbine combustor, wherein the air hole plate includes a cooling hole opened in the second region. The gas turbine combustor according to claim 1.
A gas turbine combustor comprising a plurality of the burners, wherein one burner is disposed at the center as a central burner, and the other plurality of burners is disposed as an outer peripheral burner around the central burner.

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