JP2016023916A - Gas turbine combustor - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine combustor capable of realizing stable combustion in a series of operation processes from the ignition of a gas turbine to a rated load by accurately controlling a fuel-air ratio of a premixed fuel-air mixture, and improving efficiency, reducing NOx, and decreasing the number of parts.SOLUTION: A gas turbine combustor 2 comprises: a combustion chamber 50 burning fuel and air to generate combustion gas; and a burner 5 supplying the fuel and the air to the combustion chamber 50, the gas turbine combustor 2 being configured so that the burner 5 includes an annular fuel nozzle 92 that includes an annular pipe 38 in which a plurality of fuel injection holes injecting the fuel is formed and a plurality of supply pipes 37 connected to the annular pipe 38; and an air hole plate 32 provided downstream of the annular fuel nozzle 92 to be apart from the annular fuel nozzle 92, and having a plurality of air holes 33 formed therein to face the respective fuel injection holes.SELECTED DRAWING: Figure 2

Description

  The present invention relates to a gas turbine combustor.

  In recent years, gas turbines equipped with a compressor, a combustor, a turbine, and the like have been required to have higher efficiency and lower NOx due to regulations and social requirements for environmental protection. As a method for improving the efficiency of the gas turbine, there is a method of raising the temperature of the flame formed in the combustor and raising the temperature of the combustion gas at the turbine inlet. However, as the flame temperature rises, the amount of NOx emissions increases. there is a possibility.

  On the other hand, as a combustor that suppresses NOx emission, there is a combustor that employs premixed combustion. Premixed combustion is a combustion method in which an air-fuel mixture prepared by mixing fuel and air is supplied to a combustion chamber and burned. In a combustor that employs this premixed combustion, a burner including a premixer and a combustion chamber disposed downstream of the burner in the flow direction of the air-fuel mixture are provided. The premixer is a device that mixes fuel and air to generate an air-fuel mixture, and the air-fuel mixture generated by the premixer is supplied to the combustion chamber and burns in the combustion chamber. Thus, by mixing fuel and air in advance and supplying them to the combustion chamber, the temperature of the flame formed in the combustion chamber becomes uniform, and the amount of NOx emitted from the combustor is suppressed. However, when the temperature of the air mixed with the fuel rises or the hydrogen content contained in the fuel increases, the combustion speed increases, and so-called backfire occurs in which the flame formed in the combustion chamber flows backward into the premixer. Can happen. As a gas turbine combustor that suppresses the NOx emission amount and is excellent in resistance to flashback, there is one described in Patent Document 1 or 2, for example.

  In the gas turbine combustors described in Patent Documents 1 and 2, an air hole plate in which a large number of air holes are formed facing the fuel nozzles is disposed downstream of the many fuel nozzles. By injecting fuel toward each air hole, a coaxial jet of fuel and air is ejected from each air hole into the combustion chamber. Thus, by ejecting the coaxial jet of fuel and air from the many air holes, mixing of the fuel and air is promoted, and the amount of NOx emission can be reduced. In addition, since air holes are formed at positions facing the fuel nozzles, the fuel injected from the fuel nozzles does not stay upstream of the air hole plate, preventing the backflow of the flame formed in the combustion chamber it can. Furthermore, by controlling the fuel flow rate ejected from each fuel nozzle and controlling the fuel-air ratio of the premixed gas in each air hole with high accuracy, stable combustion can be realized regardless of the operating state of the gas turbine.

  Furthermore, in the gas turbine combustor described in Patent Document 2, a vortex is generated near the tip of the fuel nozzle by inserting the tip of the fuel nozzle into the air hole, and this vortex further promotes mixing of fuel and air. Therefore, the reduction effect of NOx emission is improved.

Japanese Patent No. 4021117 Japanese Patent No. 4959620

  In the gas turbine combustor described in Patent Document 1 or 2, since the same number of fuel nozzles as the air holes are arranged, the number of parts is large, and there is a problem that the time required for ensuring structural reliability and the manufacturing cost increase. .

  Further, in the gas turbine combustor described in Patent Document 2, the air flow path of the air hole is narrowed by the tip of the fuel nozzle inserted into the air hole, so that the air flow velocity near the tip of the fuel nozzle becomes high, and the pressure loss There is a possibility that the efficiency of the gas turbine is reduced due to the increase in the amount of.

  The present invention has been made in view of the above-mentioned problems, and realizes stable combustion in a series of operation processes from ignition of a gas turbine to a rated load by accurately controlling the fuel-air ratio of the premixed gas, An object of the present invention is to provide a gas turbine combustor capable of improving efficiency, reducing NOx, and reducing the number of parts.

  In order to achieve the above object, a gas turbine combustor according to an aspect of the present invention includes a combustion chamber that burns fuel and air to generate combustion gas, and a burner that supplies the combustion chamber with fuel and air. In the gas turbine combustor, the burner includes an annular fuel nozzle having an annular pipe formed with a plurality of fuel injection holes for injecting fuel, and a plurality of supply pipes connected to the annular pipe, And an air hole plate which is disposed on the downstream side of the annular fuel nozzle so as to be spaced apart and which has a plurality of air holes facing the plurality of fuel injection holes.

  According to the present invention, the fuel-air ratio of the premixed gas is accurately controlled to realize stable combustion in a series of operation processes from ignition of the gas turbine to the rated load, and also high efficiency, low NOx, and the number of parts. Provided is a gas turbine combustor that can reduce the amount of gas.

1 is an overall configuration diagram of a gas turbine plant including a gas turbine combustor according to a first embodiment of the present invention. It is a fragmentary sectional view showing the structure near the burner of the gas turbine combustor concerning a 1st embodiment of the present invention. It is the figure (AA arrow directional view of FIG. 2) which looked at the fuel nozzle and annular fuel nozzle which concern on 1st Embodiment of this invention from the downstream. It is a figure (BB sectional view taken on the line of FIG. 2) which shows the structure of the burner which concerns on 1st Embodiment of this invention. It is the figure (CC line arrow view of FIG. 2) which looked at the turning plate which concerns on 1st Embodiment of this invention from the downstream. It is a figure (EE sectional view taken on the line of FIG. 5) which shows the shape of the air hole formed in the turning plate which concerns on 1st Embodiment of this invention. It is a figure (DD line sectional view of Drawing 4) showing typically a fuel and air flow in a burner concerning a 1st embodiment of the present invention. It is a figure (FF line sectional view of Drawing 7) showing typically a fuel and air flow in a burner concerning a 1st embodiment of the present invention. It is a figure which shows the fuel staging in the gas turbine combustor which concerns on the 1st Embodiment of this invention. It is a figure (DD sectional view taken on the line of FIG. 4) which shows typically the flow of the fuel and air in the burner which concerns on 2nd Embodiment of this invention. It is a figure (G-G line sectional view of Drawing 10) showing typically the flow of fuel and air in the burner concerning a 2nd embodiment of the present invention. It is U (DD sectional view taken on the line of FIG. 4) which shows typically the flow of the fuel and air in the burner which concerns on 3rd Embodiment of this invention. It is a figure (DD line sectional view of Drawing 4) showing typically a fuel and air flow in a burner concerning an example of a 4th embodiment of the present invention. It is a figure (DD sectional view taken on the line of FIG. 4) which shows typically the flow of the fuel and air in the burner which concerns on another example of 4th Embodiment of this invention. It is sectional drawing of the gas turbine combustor which concerns on 5th Embodiment of this invention. It is the figure (HH arrow directional view of FIG. 15) which looked at the pilot burner and main burner which concern on 5th Embodiment of this invention from the downstream. It is a figure (II line arrow view of FIG. 15) which shows the downstream of the fuel nozzle with which the main burner which concerns on 5th Embodiment of this invention is equipped, and an annular fuel nozzle. It is a figure (JJ line sectional view of Drawing 15) showing the structure of the main burner concerning a 5th embodiment of the present invention. It is a whole block diagram of the gas turbine plant provided with the gas turbine combustor which concerns on 6th Embodiment of this invention. It is the figure (KK arrow line view of FIG. 19) which looked at the pilot burner and main burner which concern on 6th Embodiment of this invention from the downstream. It is a figure (LL sectional view taken on the line of FIG. 19) which shows the structure of the pilot burner and main burner which concern on 6th Embodiment of this invention. It is a figure (MM sectional view taken on the line of FIG. 19) which shows the structure of the pilot burner and main burner which concern on 6th Embodiment of this invention.

<First Embodiment>
A gas turbine combustor according to a first embodiment of the present invention will be described with reference to the drawings.

(Constitution)
1. Gas turbine plant First, the structure of the gas turbine plant provided with the gas turbine combustor which concerns on this embodiment is demonstrated.

  FIG. 1 is an overall configuration diagram of a gas turbine plant 1000 including a gas turbine combustor 2 according to the present embodiment. The gas turbine plant 1000 includes a compressor 1, a gas turbine combustor 2, a turbine 3, and a generator 30, and the compressor 1, the turbine 3, and the generator 30 are mutually connected by a common shaft 31. It is connected.

  The compressor 1 is rotationally driven by the turbine 3, pressurizes the suction air 100 sucked through an intake portion (not shown), generates high-pressure air 101, and supplies the high-pressure air 101 to the gas turbine combustor 2. The gas turbine combustor 2 mixes and burns high-pressure air 101 supplied from the compressor 1 and fuel supplied from a fuel system 200 (described later), and supplies the generated high-temperature combustion gas 102 to the turbine 3. The turbine 3 is rotationally driven by the expansion action of the combustion gas 102 supplied from the gas turbine combustor 2. The generator 30 is rotationally driven by the turbine 3 to generate electric power.

2. Gas Turbine Combustor The gas turbine combustor 2 includes a combustion chamber 50 and a burner 5 disposed inside a casing 4 of a gas turbine device, and a fuel header 40 and a fuel system 200 disposed outside the casing 4. I have.

  The combustion chamber 50 is a space formed inside the cylindrical combustor liner 10 and burns fuel and air supplied through the burner 5 to generate combustion gas 102.

  The side far from the burner 5 of the combustor liner 10 (the downstream side in the flow direction of the combustion gas 102) is inserted into one end of the transition piece inner cylinder 12. The transition piece inner cylinder 12 guides the combustion gas 102 generated in the combustion chamber 50 to the turbine 3, and the other end of the transition piece inner cylinder 12 is a pipe line (not connected) connecting the gas turbine combustor 2 and the turbine 3. Connected).

  A cylindrical flow sleeve 11 that covers the combustor liner 10 is provided on the outer peripheral side of the combustor liner 10. An annular space formed between the combustor liner 10 and the flow sleeve 11 constitutes an annular flow path 48 that guides the high-pressure air 101 from the compressor 1 to the upstream side of the burner 5.

  A 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 flow sleeve 11 far from the burner 5 (the downstream side in the flow direction of the combustion gas 102) is inserted into one end of the tail cylinder outer cylinder 13, and the other end of the tail cylinder outer cylinder 13 opens into the casing 4. doing. The annular space formed between the tail cylinder inner cylinder 12 and the tail cylinder outer cylinder 13 constitutes an annular channel 47 that guides the high-pressure air 101 flowing from the other end of the tail cylinder outer cylinder 13 to the annular channel 48. doing.

  The high-pressure air 101 that has flowed into the annular channel 47 convectively cools the tail cylinder inner cylinder 12 from the outer wall surface side of the tail cylinder inner cylinder 12. The high-pressure air 101 that has passed through the annular channel 47 and entered the annular channel 48 convectively cools the combustor liner 10. Further, a part of the high-pressure air 101 flowing through the annular channel 48 flows into the combustor liner 10 from a large number of cooling holes (not shown) provided in the wall surface of the combustor liner 10, and Used for film cooling. The remaining high-pressure air 101 that has not been used for film cooling passes through the annular flow path 48 and reaches the burner 5. The high-pressure air 101 that has reached the burner 5 is supplied to the combustion chamber 50 together with the fuel supplied from the fuel system 200 via the fuel header 40 to the burner 5 and burned.

  The fuel system 200 includes a common fuel system 20 connected to a fuel supply source (not shown), and first to fourth fuel systems 20A to 20D that are branched from the common fuel system 20. The common fuel system 20 is provided with a fuel cutoff valve (open / close valve) 21, and the first to fourth fuel systems 20 </ b> A to 20 </ b> D are provided with first to fourth fuel flow rate control valves 21 </ b> A to 21 </ b> D, respectively. The number of fuel systems that are branched from the common fuel system 20 is not limited to four.

  The fuel header 40 is partitioned into a first header portion 40A, a second header portion 40B, a third header portion 40C, and a fourth header portion 40D in order from the central axis (not shown) of the combustor liner 10 in the radial direction. The first to fourth fuel systems 20A to 20D are connected to the first to fourth header portions 40A to 40D, respectively. The fuel supplied from the first to fourth fuel systems 20A to 20D is supplied to the burner 5 via the first to fourth header portions 40A to 40D. The number of sections of the fuel header 40 is not limited to four.

  The flow rate of fuel (hereinafter referred to as F1 fuel) supplied from the first fuel system 20A to the first header section 40A is adjusted by the first fuel flow control valve 21A, and the second fuel system 20B to the second header section 40B. The flow rate of the supplied fuel (hereinafter referred to as F2 fuel) is adjusted by the second fuel flow rate adjustment valve 21B, and the fuel (hereinafter referred to as F3 fuel) supplied from the third fuel system 20C to the third header portion 40C. The flow rate is adjusted by the third fuel flow rate adjustment valve 21C, and the flow rate of fuel (hereinafter referred to as F4 fuel) supplied from the fourth fuel system 20D to the fourth header portion 40D is adjusted by the fourth fuel flow rate adjustment valve 21D. Is done. The power generation amount of the gas turbine plant 1000 is controlled by individually adjusting the flow rates of the F1 to F4 fuels by the first to fourth fuel flow rate adjustment valves 21A to 21D.

3. Burner Next, the detailed configuration of the burner 5 will be described. FIG. 2 is a partial cross-sectional view showing a structure in the vicinity of the burner 5 of the gas turbine combustor 2 according to the present embodiment. The burner 5 includes a plurality of fuel nozzles 91, a plurality of annular fuel nozzles 92, and an air hole plate 32.

  Hereinafter, the structure of each member with which the burner 5 is provided is demonstrated. The burner 5 is divided into a plurality of concentric circular rows (eight in the present embodiment) centering on the central axis (not shown) of the combustor liner 10, and the plurality of annular rows are arranged on the inner periphery. From the side toward the outer peripheral side, the first row, the second row,.

4). 2. Fuel nozzle and annular fuel nozzle As shown in FIG. 2, the fuel nozzle 91 and the annular fuel nozzle 92 are supported by the fuel header 40, and the fuel system 200 faces the air hole plate 32 disposed on the downstream side. The fuel supplied from is injected. The fuel nozzle 91 is arranged over the entire circumference of the first row to the fourth row. On the other hand, one annular fuel nozzle 92 is arranged in each of the fifth to eighth rows. The annular fuel nozzle 92 includes an annular pipe 38 and a plurality of supply pipes 37 connected to the annular pipe 38. A plurality of fuel injection holes 36 for injecting fuel are provided on the downstream side surface of the annular pipe 38. It has been. In this embodiment, the fuel nozzles 91 are arranged from the first row to the fourth row, and the annular fuel nozzles 92 are arranged from the fifth row to the eighth row. However, the types of the fuel nozzles arranged in each annular row Is not limited to this.

  3 is a view of the fuel nozzle 91 and the annular fuel nozzle 92 as seen from the downstream side (a view taken along the line AA in FIG. 2). One fuel injection hole 36 is formed at the tip of the fuel nozzle 91. A plurality of fuel injection holes 36 are perforated at a predetermined interval (hereinafter referred to as an inter-hole distance) on the downstream side surface of the annular pipe 38 constituting the annular fuel nozzle 92. The annular pipe 38 constituting the eighth row of annular fuel nozzles 92 is formed discontinuously in the phase where the support 15 is attached in order to avoid interference with the support 15 shown in FIG. In FIG. 3, the first to fourth rows constitute the first burner portion 5A, the fifth row constitutes the second burner portion 5B, the sixth row constitutes the third burner portion 5C, The seventh row and the eighth row constitute the fourth burner portion 5D. The first to fourth fuel systems 20A to 20D are connected to the first to fourth burner portions 5A to 5D via the first to fourth header portions 40A to 40D, respectively. By individually adjusting the flow rates of the F1 to F4 fuel supplied from the first to fourth fuel systems 20A to 20D to the first to fourth burner portions 5A to 5D, fuel staging described later becomes possible.

  FIG. 4 is a diagram (cross-sectional view taken along the line BB in FIG. 2) showing the structure of the burner 5 according to the present embodiment. The F1 fuel supplied to the first burner portion 5A via the first header portion 40A flows into the fuel nozzle 91. The F2 to F4 fuel supplied through the second to fourth header sections 40B to 40D through the second to fourth burner sections 5B to 5D flows into the annular pipe 38 through the supply pipe 37 indicated by the dotted line in the drawing. The annular pipe 38 is a circular pipe with a hollow inside and is in communication with the entire circumference, and has a structure in which fuel is distributed throughout the circular pipe. The supply pipe 37 is connected to the annular pipe 38 at an appropriate interval so that the fuel flow rate flowing through the annular pipe 38 does not become uneven in the circumferential direction. In the annular fuel nozzle 92 arranged in the eighth row, since the annular pipe 38 is composed of a plurality of discontinuous pipe parts, it is necessary to connect at least one supply pipe 37 to each pipe part. is there.

5). Air Hole Plate The air hole plate 32 includes a base plate 32A and a swivel plate 32B as shown in FIG. The base plate 32 </ b> A and the swivel plate 32 </ b> B are attached to the fuel header 40 via the support 15 and are held inside the combustor liner 10 via the spring seal 14. The support 15 in the present embodiment is formed by bending a flat plate. By absorbing the thermal elongation in the circumferential direction of the air hole plate 32 by the bent structure, the structural reliability of the burner 5 can be improved. . Hereinafter, each structure of the base plate 32A and the turning plate 32B will be described.

6). As shown in FIG. 2, the base plate 32 </ b> A is a circular plate having the same central axis as the combustor liner 10, and is arranged on the downstream side of the plurality of fuel nozzles 91 and the annular fuel nozzle 92. Yes.

  A plurality of air holes 33 </ b> A are formed in the first to fourth rows of the base plate 32 </ b> A so as to face each of the plurality of fuel nozzles 91. That is, air holes 33A are formed in the first to fourth rows of the base plate 32A over the entire circumference. By disposing the fuel nozzle 91 and the air hole 33A so as to face each other, as shown in the enlarged view of FIG. 2, fuel injected from the fuel nozzle 91 (hereinafter referred to as a fuel jet) 34 is formed into an air hole. It passes through the base plate 32A as a coaxial jet whose outer periphery is covered with air (hereinafter referred to as an air jet) 35 passing through 33A.

  In the fifth to eighth rows of the base plate 32 </ b> A, a plurality of air holes 33 </ b> A are formed so as to face each of the plurality of fuel injection holes 36 provided in the plurality of annular fuel nozzles 92. That is, air holes 33A are formed in the fifth to eighth rows of the base plate 32A over the entire circumference.

  Note that the air hole 33A in the present embodiment is formed in a right circular column shape in which two circles constituting both openings and a bus bar are orthogonal to each other.

7). As shown in FIG. 2, the swirl plate 32B is a circular plate having the same central axis (not shown) as the combustor liner 10, and is disposed in close contact with the downstream end face of the base plate 32A. Yes. FIG. 5 is a view of the swivel plate 32B as seen from the downstream side (a view taken along the line CC in FIG. 2). The swivel plate 32B is formed with a plurality of air holes 33B (the same number as the air holes 33A) communicating with the plurality of air holes 33A formed in the base plate 32A. That is, the air holes 33B are formed over the entire circumference in each of the first to eighth annular rows of the swivel plate 32B.

  FIG. 6 is a diagram (a cross-sectional view taken along the line E-E in FIG. 5) showing the shape of the air hole 33 </ b> B formed in the swivel plate 32 </ b> B. As shown in FIG. 6, the air hole 33 </ b> B is formed in a slanted columnar shape in which two circles constituting both openings and a bus line connecting these two circles are not orthogonal to each other. That is, the air hole 33B is a turning air hole having a turning angle, and the downstream opening is shifted in the circumferential direction with respect to the upstream opening. Specifically, the central axis Y of the air hole 33B obtained by connecting the center of the upstream opening of the air hole 33B and the center of the downstream opening is the central axis X of the air hole 33A formed in the base plate 32A. Is inclined at a predetermined angle α ° in the circumferential direction. The predetermined angle α ° is a parameter that determines the jet direction of air and fuel at the downstream opening of the air hole 33B, and is set to an optimum value for each of the first to eighth annular rows.

  In the burner 5, when the inter-hole distance is set to be larger than the extinguishing distance, a flame adheres to the swivel plate 32B, and the stability of the flame is enhanced. On the other hand, when the inter-hole distance is set to be equal to or less than the extinguishing distance, a flame is formed away from the turning plate 32B. In the vicinity of the downstream side of the opening on the outlet side of the air hole 33B, the flow path rapidly expands toward the combustion chamber 50, so that the mixing of the fuel jet 34 and the air jet 35 proceeds rapidly. By forming the flame in the above position, the premixed gas in which the fuel and air are sufficiently mixed reaches the flame and burns, so that low NOx combustion can be realized. That is, both stable combustion and low NOx combustion can be realized by optimally adjusting the inter-hole distances in the first to eighth rows.

(Operation)
Next, the operation of the gas turbine combustor 2 according to the first embodiment of the present invention will be described.

  FIG. 7 is a diagram (cross-sectional view taken along the line DD in FIG. 4) schematically showing the flow of fuel and air in the annular fuel nozzle 92. FIG. 7 shows the flow of fuel and air in the annular fuel nozzles 92 arranged in the fifth row, but the same applies to the annular fuel nozzles arranged in the sixth to eighth rows. is there. Further, the flow of fuel and air in the fuel nozzles 91 arranged in the first row to the fourth row is the same as that in the prior art, and thus the description thereof is omitted.

  The high-pressure air 101 that has reached the upstream side of the base plate 32A through the annular flow path 48 shown in FIG. 2 flows into an air hole 33A formed in the base plate 32A as an air jet 35 as shown in FIG. The fuel supplied to the fuel header 40 flows into the supply pipe 37. The fuel that has passed through the supply pipe 37 and entered the annular pipe 38 is ejected from the fuel injection hole 36 as a fuel jet 34 and flows into the air hole 33A. In addition, in order to prevent the flow rate of fuel ejected from each fuel injection hole 36 from becoming uneven in the circumferential direction, the supply pipe 37 is connected to a position of the annular pipe 38 that does not face the fuel injection hole 36. The fuel jet 34 that has flowed into the air hole 33A passes through the air hole 33A while being rapidly mixed with the air jet 35, and enters the air hole 33B formed in the swirl plate 32B as an air-fuel mixture. As shown in FIG. 6, since the air hole 33B is inclined at a predetermined angle α ° in the circumferential direction with respect to the air hole 33A, the air-fuel mixture that has passed through the air hole 33B has a velocity component in the swirl direction. Is granted. Since the downstream opening of the air hole 33B opens into the combustion chamber 50, the flow path of the air-fuel mixture expands rapidly, and mixing is further promoted near the downstream opening of the air hole 33B. The mixture of the fuel jet 34 and the air jet 35 ejected from the air hole 33B is ejected into the combustion chamber 50 as a premixed gas 93 and combusted.

  FIG. 8 is a view schematically showing the flow of fuel and air in the annular fuel nozzle 92 (cross-sectional view taken along the line FF in FIG. 7). A wake vortex 39 is generated on the base plate 32 </ b> A side of the annular pipe 38 due to the interaction between the annular pipe 38 and the high-pressure air 101. The fuel jet 34 ejected from the fuel nozzle 36 flows into the air hole 33A while being mixed with the air jet 35 due to the strong turbulence of the wake vortex 39. Since the annular pipe 38 is disposed away from the upstream opening of the air hole 33A, the flow velocity of the air jet 35 does not increase in the upstream opening and inside of the air hole 33A.

FIG. 9 is a diagram showing fuel staging in the gas turbine combustor 2 according to the present embodiment. In FIG. 9, the horizontal axis indicates the elapsed time, and the vertical axis indicates the fuel flow rate.
As shown in FIG. 9, when the gas turbine is ignited, F1 to F3 fuel is supplied from the first to third fuel systems 20 </ b> A to 20 </ b> C, so that fuel is injected from the first to sixth rows of the burner 5. . On the other hand, since the F4 fuel is not supplied from the fourth fuel system 20D, the fuel is not injected from the seventh row and the eighth row of the burner 5.

  After the gas turbine is ignited, only F1 fuel is supplied (fuel is injected from only the first to fourth rows) and switched to single combustion until a rated speed no-load state (FSNL: Full Speed No Load) is reached. The turbine 3 is accelerated.

  When the turbine 3 speeds up to the rated speed, power generation is started and the gas turbine load is increased. As the gas turbine load increases, fuel is additionally supplied in the order of F2 fuel, F3 fuel, and F4 fuel so that the fuel-air ratio of the burner 5 falls within the stable combustion range. The row is expanded step by step to the sixth row of the burner 5, the seventh row and the eighth row of the burner 5. The gas turbine load reaches a rated speed full load (FSFL) in a combustion state in which fuel is injected from all of the first to eighth rows of the burner 5.

(effect)
(1) In the present embodiment, the coaxial jet of the fuel jet 34 and the air jet 35 is ejected from the large number of air holes 33 to the combustion chamber 50, so the interface between the fuel and air is increased and the mixing of the fuel and air is further promoted. Is done. Thereby, the amount of NOx generated during combustion in the combustion chamber 50 can be suppressed.

  (2) In the present embodiment, in the fifth to eighth rows of the burner 5, instead of arranging the same number of fuel nozzles 91 as the air holes 33A, one annular fuel nozzle 92 is arranged one by one, and each annular fuel is arranged. The nozzle 92 is configured to include a number of supply pipes 37 smaller than the number of fuel injection holes 36 formed in each annular pipe 38. Thereby, the number of parts of the burner 5 can be reduced, and the structural reliability of the gas turbine combustor can be improved. Furthermore, since the flow area of the high-pressure air 101 formed between the air hole plate 32 and the fuel header 40 is enlarged, the flow velocity of the high-pressure air 101 passing between the base plate 32A and the fuel header 40 is reduced, and the pressure A decrease in gas turbine efficiency due to loss can be suppressed.

  (3) Since the air hole 33A is formed in the air hole plate 32 according to the present embodiment at a position facing the fuel nozzle hole 36 of the fuel nozzle 91 and the annular fuel nozzle 92, the air hole plate 32 and the fuel header. 40, the unburned mixture in the combustible range is not continuously formed in the space formed between the two. Therefore, the flame does not flow backward in this space and the air hole plate 32 is not melted, and the structural reliability of the combustor can be improved.

  (4) In the present embodiment, the fuel nozzle 91 and the annular fuel nozzle 92 are spaced apart from the upstream side of the air hole plate 32. Therefore, an increase in the flow velocity of the air jet 35 in the air hole 33A is suppressed as compared with the configuration of the prior art that promotes mixing of fuel and air by inserting the tip of the fuel nozzle 91 into the air hole 33A. Mixing of the fuel jet 34 and air is promoted by the wake vortex 39 of the high-pressure air 101 generated on the downstream side surface of the annular pipe 38. That is, NOx emissions can be reduced without reducing gas turbine efficiency due to an increase in pressure loss.

  (5) In this embodiment, since the annular fuel nozzles 92 are arranged one by one in the fifth to eighth rows of the burner 5, the fuel-air ratio in the air holes 33A in the same row is made uniform, and the flow rate in the burner 5 is The circumferential deviation of the fuel-air ratio can be reduced. Therefore, stable combustion can be realized in a series of operation processes from ignition of the gas turbine to the rated load by accurately controlling the fuel-air ratio of the premixed gas 93 ejected from each air hole 33B.

  (6) In this embodiment, the air hole 33B of the swivel plate 32B is inclined at an angle α ° in the circumferential direction with respect to the air hole 33A of the base plate 32A, and is downstream of the burner 5 by the air-fuel mixture ejected from the air hole 33B. A circulation flow is formed on the side. Thereby, a more stable flame can be formed.

  (7) In this embodiment, the fuel header 40 is partitioned into first to fourth header portions 40A to 40D, and the F1 to F4 fuel supplied to the first to fourth burner portions 5A to 5D are individually adjusted. can do. This enables fuel staging in which the number of air holes 33 for injecting fuel is changed in stages according to the fuel flow rate required in each operation process of the gas turbine, and realizes stable combustion during gas turbine partial load operation. In addition, the amount of NOx emission can be suppressed.

Second Embodiment
A gas turbine combustor according to a second embodiment of the present invention will be described with reference to the drawings.

(Constitution)
The configuration of the gas turbine combustor according to the present embodiment is substantially the same as that of the first embodiment, and is different in the configuration of the annular fuel nozzle 92. Hereinafter, the difference will be mainly described.

  10 and 11 are views schematically showing the flow of fuel and air in the annular fuel nozzle 92 (cross-sectional view taken along the line DD in FIG. 4 and cross-sectional view taken along the line GG in FIG. 10). In FIG.10 and FIG.11, the same code | symbol is attached | subjected to the part equivalent to 1st Embodiment.

  In the first embodiment, as shown in FIG. 7 or FIG. 8, one fuel injection hole 36 is formed in the annular pipe 38 so as to face one air hole 33A. As shown in FIG. 11, a plurality of (four in this embodiment) fuel injection holes 36 are formed in the annular pipe 38 so as to face one air hole 33 </ b> A. The number of fuel injection holes 36 perforated in the annular pipe 38 so as to face one air hole 33A is not limited to four.

(Operation)
Next, the operation of the gas turbine combustor 2 according to the fifth embodiment of the present invention will be described focusing on differences from the first embodiment.

  As shown in FIG. 11, the plurality of fuel jets 34 ejected from the plurality of fuel injection holes 36 formed to face the air holes 33 </ b> A are rapidly mixed with the air jets 35, respectively, at the upstream opening of the air holes 33 </ b> A. And flows into the air hole 33A. As shown in FIG. 10, the air-fuel mixture flowing into the air hole 33A flows into the air hole 33B, and then is supplied to the combustion chamber 50 as the pre-air mixture 93 and combusts, as in the first embodiment.

(effect)
According to the present embodiment, in addition to the effects obtained in the first embodiment, the following effects are obtained.

  In the present embodiment, since fuel is injected from the plurality of fuel injection holes 36 to each air hole 33A, the initial dispersion of the fuel is improved and the mixing of fuel and air is promoted. Thereby, the NOx emission amount can be further suppressed.

<Third Embodiment>
A gas turbine combustor according to a third embodiment of the present invention will be described with reference to the drawings.

(Constitution)
The configuration of the gas turbine combustor according to this embodiment is almost the same as that of the second embodiment, and is different in the configuration of the annular fuel nozzle 92. Hereinafter, the difference will be mainly described.

  12 is a diagram (cross-sectional view taken along the line DD in FIG. 4) schematically showing the flow of fuel and air in the annular fuel nozzle 92. FIG. In FIG. 12, parts that are the same as in the second embodiment are given the same reference numerals.

  As shown in FIG. 12, in the present embodiment, the inside of the annular pipe 38 is partitioned by a partition 43. In addition, the number and position of the partition 43 are not specifically limited.

(Operation)
Next, the operation of the gas turbine combustor 2 according to the third embodiment of the present invention will be described focusing on differences from the second embodiment.

  As shown in FIG. 12, it passes through the supply pipe 37 and flows into the annular pipe 38. The fuel that has flowed into the annular pipe 38 flows in the circumferential direction through the pipe portion partitioned by the partition 43, and is ejected as a fuel jet 34 from the fuel injection hole 36 formed in the pipe portion. Thereafter, the fuel jet 34 and the air jet 35 are rapidly mixed in the air hole 33A, pass through the air hole 33B formed in the swirl plate 32B, and are jetted into the combustion chamber 50 as the premixed air 93, as in the second embodiment. Burn.

(effect)
According to this embodiment, in addition to the effects obtained in the second embodiment, the following effects are obtained.

  In the present embodiment, since the annular pipe 38 is partitioned into a plurality of pipe parts by the partition 43, the circumferential deviation of the fuel flow rate can be reduced in the annular pipe 38, and the fuel injection formed in the annular fuel nozzle 92. The flow rate of the fuel jet 34 ejected from the hole 36 can be accurately controlled. Further, for example, by providing a throttle in the supply pipe 37, the flow rate of the fuel jet 34 can be finely controlled for each pipe portion. Accordingly, the fuel-air ratio of the premixed gas 93 ejected from the air holes 33B can be controlled more precisely and finely than in the first embodiment, so that the combustion stability is further improved.

<Fourth embodiment>
A gas turbine combustor according to a fourth embodiment of the present invention will be described with reference to the drawings.

(Constitution)
The configuration of the gas turbine combustor according to the present embodiment is substantially the same as that of the second embodiment, and is different in the configuration of the annular fuel nozzle 92. Hereinafter, the difference will be mainly described.

  FIG. 13 is a diagram (cross-sectional view taken along the line DD in FIG. 4) schematically showing the flow of fuel and air in the annular fuel nozzle 92 according to an example of the present embodiment. FIG. 14 is a diagram (cross-sectional view taken along the line DD of FIG. 4) schematically showing the flow of fuel and air in the annular fuel nozzle 92 according to another example of the present embodiment. In FIG. 13 and FIG. 14, the same reference numerals are given to the parts equivalent to the second embodiment.

  In the example shown in FIG. 13, the inner diameter of the annular pipe 38 is smoothly narrowed in the circumferential direction starting from the joining position with the supply pipe 37. On the other hand, in another example shown in FIG. 14, a throttle 44 is provided at a predetermined position of the annular pipe 38 starting from the connection position of the supply pipe 37. That is, in both the example shown in FIG. 13 and the other example shown in FIG. 14, the inner diameter of the annular pipe 38 is formed so as to decrease according to the distance from the connection position of the supply pipe 37.

(Operation)
Next, the operation of the gas turbine combustor 2 according to the fourth embodiment of the present invention will be described focusing on differences from the second embodiment.

  As shown in FIG. 13, the fuel supplied to the fuel header 40 passes through the supply pipe 37 and flows into the annular pipe 38. In the annular pipe 38, the fuel flows in the circumferential direction, and a part of the fuel is ejected from the fuel injection hole 36 toward the air hole 33A as a fuel jet 34. Therefore, the flow rate of the fuel flowing through the annular pipe 38 decreases every time it passes through the fuel injection hole 36. In the first embodiment, as shown in FIG. 10, since the inner diameter of the annular pipe 38 is constant, the absolute flow velocity in the circumferential direction of the fuel flowing through the annular pipe 38 decreases every time it passes through the fuel injection hole 36. Therefore, there is a concern that the flow rate of the fuel jet 34 decreases as the fuel injection hole 36 is farther from the supply pipe 37. On the other hand, in the present embodiment, the inner diameter of the annular pipe 38 is smoothly reduced according to the distance from the connection position of the supply pipe 37, so the absolute flow velocity in the circumferential direction of the fuel flowing through the annular pipe 38 is the second embodiment. It becomes uniform compared to the form. In the other example shown in FIG. 14 as well, the inner diameter of the annular pipe 38 is large on the supply pipe 37 side of the throttle 44 and small on the opposite side, so that the absolute flow velocity in the circumferential direction of the fuel flowing through the annular pipe 38 becomes substantially uniform.

(effect)
In this embodiment, in addition to the effects obtained in the second embodiment described above, the following effects are obtained.

  In the present embodiment, since the absolute flow velocity in the circumferential direction of the fuel flowing through the annular pipe 38 is made uniform compared to the first embodiment, the flow rate of the fuel jet 34 ejected from each fuel injection hole 36 is the connection position of the supply pipe 37. It is constant regardless of the distance from. As a result, the fuel-air ratio of the premixed gas 93 ejected from the air hole 33 to the combustion chamber 50 becomes constant in the circumferential direction, and the combustion stability is further improved.

<Fifth Embodiment>
A gas turbine combustor according to a fifth embodiment of the present invention will be described with reference to the drawings.

(Constitution)
The configuration of the gas turbine combustor according to the present embodiment is substantially the same as that of the first embodiment, and the following description will focus on differences.

  FIG. 15 is a cross-sectional view of the gas turbine combustor 2 according to the present embodiment. The gas turbine combustor 2 according to the present embodiment is a so-called multi-injection gas turbine combustor, and includes a pilot burner 41 disposed upstream of the combustion chamber 50 and on the central axis of the gas turbine combustor 2, and a pilot. A plurality of (six in this embodiment) main burners 42 are provided on the outer periphery of the burner 41. In FIG. 15, parts that are the same as in the first embodiment are given the same reference numerals.

  FIG. 16 is a view of the pilot burner 41 and the main burner 42 as viewed from the downstream (a view taken along the line HH in FIG. 15). FIG. 17 is a view of the fuel nozzle 91 and the annular fuel nozzle 92 included in the main burner 42 as seen from the downstream side (a view taken along the line II in FIG. 15). FIG. 18 is a diagram (a cross-sectional view taken along the line JJ in FIG. 15) illustrating the structure of the main burner 42. 16 to 18, the same reference numerals are given to the same parts as those in the first embodiment.

  The pilot burner 41 includes a plurality of fuel nozzles 91 arranged concentrically in three rows, and a part of an air hole plate 32 in which three air hole rows are formed facing the plurality of fuel nozzles 91. It has. On the other hand, each of the six main burners 42 includes six fuel nozzles 91 disposed in a circular shape, two annular fuel nozzles 92 disposed concentrically on the outer periphery of the plurality of fuel nozzles 91, and A plurality of fuel nozzles formed in the plurality of fuel nozzles 91 and the two annular fuel nozzles 92 and another part of the air hole plate 32 formed with three air hole arrays are provided. . That is, in this embodiment, the gas turbine combustor 2 employs a multi-burner structure including seven burners 41 and 42, and the seven burners 41 and 42 share the air hole plate 32. The pilot burner 41 and the main burner 72 are each divided into a plurality of concentric (three in this embodiment) annular rows, and the plurality of annular rows are firstly arranged from the inner peripheral side toward the outer peripheral side. These will be appropriately referred to as a column, a second column, and a third column.

  As shown in FIG. 17, a plurality of fuel injection holes 36 for injecting fuel are perforated on the downstream side surface of the annular fuel nozzle 92, and downstream of the fuel injection hole 36 in the perforation direction is as shown in FIG. The air hole 33 formed in the air hole plate 32 is located in the air hole plate 32. As shown in FIG. 18, the annular fuel nozzle 92 includes an annular pipe 38 formed of a circular pipe and a plurality of supply pipes 37 connected to the upstream side surface of the annular pipe 38. Here, the position where the supply pipe 37 is connected is not particularly limited as long as it is not a position facing the fuel injection hole 36 drilled in the downstream side surface. Further, the number of supply pipes is not particularly limited as long as it is less than the number of fuel injection holes 36.

  As shown in FIGS. 15 and 16, the first fuel system 20 </ b> A is connected to the first burner portion 5 </ b> A configured of the first to third rows of the pilot burner 41, and two of the six main burners 42 are connected. The second fuel system 20B is connected to the second burner section 5B configured by the first row of the main burners 42, and the second fuel system 20B is configured by the first row of the other four main burners 42 among the six main burners 42. A third fuel system 20C is connected to the 3 burner section 5C, and a fourth fuel system 20D is connected to a fourth burner section 5D configured by the second row and the third row of the six main burners 42.

  In this embodiment, only the fuel nozzles 91 are disposed in the first to third rows of the pilot burner 41. However, the annular fuel nozzle 92 is provided in any one of the first to third rows of the pilot burner 41. It may be arranged.

(Operation)
Next, the operation of the gas turbine combustor 2 according to the fifth embodiment of the present invention will be described focusing on differences from the first embodiment.

  The fuel supplied to the fuel nozzle 91 and the annular fuel nozzle 92 via the fuel header 40 is ejected as a premixed gas from the air hole 33B as shown in FIG. 15, and downstream of the pilot burner 41 and the main burner 42. Each forms a swirl flow 60. A circulating flow 61 is generated by the swirling flow 60, and a flame surface 62 is formed.

  Also in this embodiment, fuel staging is possible by individually adjusting the F1 to F4 fuel supplied to the first to fourth burner portions 40A to 40D.

(effect)
As described above, also in the present embodiment in which the present invention is applied to the multi-injection gas turbine combustor, the same effects as in the first embodiment can be obtained.

<Sixth Embodiment>
A gas turbine combustor according to a sixth embodiment of the present invention will be described with reference to the drawings.

(Constitution)
The configuration of the gas turbine plant provided with the gas turbine combustor according to the present embodiment is substantially the same as that of the first embodiment, and hereinafter, differences will be mainly described.

  FIG. 19 is an overall configuration diagram of a gas turbine plant 1000 including the gas turbine combustor 2 according to the sixth embodiment of the present invention. In FIG. 19, illustration of the fuel system is omitted. FIG. 20 is a view (a view taken along the line KK in FIG. 19) of the pilot burner 41 and the main burner 42 according to the present embodiment as viewed from the downstream side. 21 and 22 are views (a cross-sectional view taken along the line LL and a cross-sectional view taken along the line MM in FIG. 19) showing the structure of the pilot burner 41 and the main burner 42 according to the present embodiment. 19 to 22, parts that are the same as in the first embodiment are given the same reference numerals.

  The gas turbine combustor 2 according to the present embodiment is a so-called diffusion premixed gas turbine combustor, and includes a pilot burner 41 disposed upstream of the combustion chamber 50 and on the central axis of the gas turbine combustor 2, and a pilot And a main burner 42 disposed on the outer periphery of the burner 41.

  The pilot burner 41 is a diffusion combustion type burner that realizes stable combustion, and includes a pilot fuel nozzle 81 disposed upstream of the combustion chamber 50 and on the central axis of the gas turbine combustor 2, and a pilot fuel nozzle 81. And an air introduction pipe 75 arranged around the outer periphery.

  The main burner 42 is a premixed combustion type burner that realizes low NOx combustion, and includes an annular fuel nozzle 92, a plurality of main fuel nozzles 82, a premixer 74, and a flame holder 73. The annular fuel nozzle 92 is disposed on the upstream side of the premixer 74, and the plurality of main fuel nozzles 82 are disposed in the middle of the premixer 74. The flame holder 73 is disposed on the downstream side of the premixer 74. The annular fuel nozzle 92 includes an annular pipe 38 disposed in the upstream opening of the premixer 74 and a plurality of supply pipes 37 connected to the annular pipe 38.

(Operation)
Next, the operation of the gas turbine combustor 2 according to the sixth embodiment of the present invention will be described.

  The fuel supplied to the pilot fuel nozzle 81 via the fuel header 40 is directly injected into the combustion chamber 50 and together with a part of the high-pressure air 101 supplied from the compressor 1 to the combustion chamber 50 via the air introduction pipe 75. Burns and forms a flame.

  The fuel supplied from the fuel header 40 to the plurality of main fuel nozzles 82 is injected into an intermediate portion of the premixer 74. The fuel supplied from the fuel header 40 to the plurality of supply pipes 37 flows into the annular pipe 38, flows in the annular pipe 38 in the circumferential direction, and travels from the fuel injection hole 36 toward the upstream opening of the premixer 74. The fuel jet 34 is formed. The fuel jet 34 is mixed in the premixer 74 with the high-pressure air 101 supplied from the compressor 1 to the premixer 74 and the fuel injected into the intermediate portion of the premixer 74 from the plurality of main fuel nozzles 82. A lean premixed gas is jetted into the combustion chamber 50. The flame holder 73 forms a circulation flow of the lean premixed gas at the downstream side opening of the premixer 74 and realizes stable combustion.

(effect)
In the present embodiment, an annular fuel nozzle 92 is disposed near the upstream opening of the premixer 74, and the annular fuel nozzle 92 is supplied in a number smaller than the number of fuel injection holes 36 formed in the annular pipe 38. The piping 37 is provided. As a result, stable combustion, high efficiency, and low NOx equivalent to those of the conventional diffusion premixed gas turbine combustor can be realized, the number of parts of the main burner 42 can be reduced, and the structural reliability of the gas turbine combustor 2 can be reduced. Can be increased.

<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 one embodiment can be replaced with the configuration of another embodiment, and the configuration of another embodiment can be added to the configuration of one embodiment. Moreover, it is also possible to add, delete, and replace other configurations for a part of the configuration of each embodiment.

  In the first to fifth embodiments, the case where the air holes 33 are formed over the entire circumference of each annular row has been described. However, the essential effect of the present invention is that the fuel-air ratio of the premixed gas in each air hole is accurately controlled to achieve stable combustion in a series of operation processes from ignition of the gas turbine to the rated load, and NOx emission amount As long as this essential effect is obtained, the air holes 33 are not necessarily formed over the entire circumference of each annular row.

  In the first to fourth embodiments, the case where eight air hole rows are formed in the air hole plate 32 has been described. However, as long as the essential effects of the present invention described above are obtained, the number of air hole rows is not necessarily 8 rows, and may be 7 rows or less or 9 rows or more.

  In the first to fifth embodiments, the case where the tip of the fuel nozzle 91 is separated from the upstream opening of the air hole 33 has been described. However, as long as the above-described essential effects of the present invention are obtained, it is not always necessary to separate the tip of the fuel nozzle 91 from the upstream opening of the air hole 33A. The tip of the fuel nozzle 91 is inserted into the air hole 33. Also good. In this case, the flow velocity of the air jet 35 is increased due to the reduction of the air flow path area at the upstream opening of the air hole 33, and the mixing of the fuel and air injected from the fuel nozzle 91 is further promoted. However, an increase in the flow velocity of the air jet 35 is accompanied by an increase in pressure loss, which may lead to a decrease in gas turbine efficiency. Therefore, it is necessary to consider the tradeoff between low NOx and high efficiency.

  In each embodiment, the case where the tip of the fuel nozzle 91 is formed in a simple cylindrical shape has been described. However, as long as the above-described essential effects of the present invention are obtained, the fuel nozzle 91 is not necessarily formed in a cylindrical shape. A protrusion protruding in the radial direction may be provided at the tip of the nozzle 91. Thereby, a vortex flow is generated in the vicinity of the tip of the fuel nozzle 91, and the mixing of fuel and air can be further promoted. Further, like the annular fuel nozzle 92 described in the second embodiment, a plurality of fuel injection holes 36 may be formed at the tip of the fuel nozzle 91. Thereby, the initial dispersion of the fuel is increased, and the mixing of fuel and air can be further promoted.

  Moreover, although each embodiment demonstrated the case where the supply piping 37 and the annular piping 38 of the annular fuel nozzle 92 were comprised with the circular pipe, as long as the essential effect of this invention mentioned above was acquired, it comprised with a circular pipe. There is no need, and it may be constituted by a square tube or the like.

DESCRIPTION OF SYMBOLS 1 Compressor 2 Gas turbine combustor 3 Turbine 4 Casing 5 Burner 5A 1st burner part 5B 2nd burner part 5C 3rd burner part 5D 4th burner part 10 Combustor liner 11 Flow sleeve 12 Cylinder inner cylinder 13 Outer cylinder outer Cylinder 14 Spring seal 15 Support 20 Common fuel system 20A 1st fuel system 20B 2nd fuel system 20C 3rd fuel system 20D 4th fuel system 21 Fuel cutoff valve 21A 1st fuel flow control valve 21B 2nd fuel flow control valve 21C 1st 3 Fuel flow rate adjusting valve 21D Fourth fuel flow rate adjusting valve 30 Generator 31 Shaft 32 Air hole plate 32A Base plate 32B Swivel plate 33 Air hole 33A Air hole 33B formed in the base plate Air hole 34 formed in the swirl plate Fuel jet 35 Air jet 36 Fuel injection hole 37 Supply pipe 38 Annular pipe 39 Wake 40 Fuel header 40A 1st header part 40B 2nd header part 40C 3rd header part 40D 4th header part 41 Pilot burner 42 Main burner 43 Partition 44 Restriction 47, 48 Annular channel 50 Combustion chamber 60 Swirling flow 61 Circulating flow 62 Flame Surface 73 Flame holder 74 Premixer 75 Air introduction pipe 81 Pilot fuel nozzle 82 Main fuel nozzle 91 Fuel nozzle 92 Annular fuel nozzle 93 Premixed air 100 Suction air 101 High pressure air 102 Combustion gas 200 Fuel system 1000 Gas turbine plant

Claims (6)

A combustion chamber that burns fuel and air to generate combustion gases;
In a gas turbine combustor comprising a burner for supplying fuel and air to the combustion chamber,
The burner is
An annular fuel nozzle having an annular pipe formed with a plurality of fuel injection holes for injecting fuel and a plurality of supply pipes connected to the annular pipe;
A gas turbine combustor comprising: an air hole plate that is spaced apart from the downstream side of the annular fuel nozzle and has a plurality of air holes facing the plurality of fuel injection holes. The gas turbine combustor according to claim 1.
The gas turbine combustor, wherein the annular pipe has two or more fuel injection holes facing each of the plurality of air holes. The gas turbine combustor according to claim 1.
The gas turbine combustor characterized in that the number of the plurality of supply pipes is smaller than the number of fuel injection holes formed in the annular pipe. The gas turbine combustor according to claim 3.
The annular pipe is partitioned into a plurality of piping parts including at least one of the plurality of fuel injection holes, and at least one of the plurality of supply pipes is connected to each of the plurality of piping parts. Gas turbine combustor. The gas turbine combustor according to claim 3.
A gas characterized in that a flow passage cross-sectional area of the annular pipe at a position where the plurality of fuel injection holes are formed is formed so as to become smaller according to a distance from a position where the plurality of supply pipes are connected. Turbine combustor. A combustion chamber that burns fuel and air to generate combustion gases;
A diffusion combustion type pilot burner having a fuel nozzle for injecting fuel into the combustion chamber and an air introduction pipe for supplying air to the combustion chamber;
A gas turbine combustor provided with a premixed combustion type main burner disposed on an outer peripheral side of the pilot burner and supplying a premixed mixture of fuel and air to the combustion chamber;
The main burner is
An annular fuel nozzle having an annular pipe formed with a plurality of fuel injection holes and a plurality of supply pipes connected to the annular pipe;
A gas turbine combustor comprising: a premixer that mixes air with fuel injected from the plurality of fuel injection holes to generate a premixed gas.

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