JP2019168144A - Gas turbine combustor and gas turbine comprising the same, and method of preventing combustion vibration of gas turbine combustor - Google Patents

Abstract

Provided is a gas turbine combustor capable of sufficiently suppressing combustion oscillation as compared with the conventional case. A combustor (4) comprising a first nozzle (54) and a plurality of second nozzles (63) arranged in a circumferential direction so as to surround the first nozzle (54). The fuel injection holes 59 have an angle difference θ [°] of 45 ° between any pair of the fuel injection holes 59 adjacent in the circumferential direction. The first nozzle 54 is arranged such that the fuel injection amount from one or more fuel injection holes 59 is different from the fuel injection amount from one or more other fuel injection holes 59. Is configured to inject fuel. [Selection diagram] FIG.

Description

  The present invention relates to a gas turbine combustor, a gas turbine including the same, and a combustion vibration suppressing method for the gas turbine combustor.

  During combustion in a gas turbine combustor (hereinafter sometimes simply referred to as “combustor”), pressure fluctuations may occur inside the combustor. And a combustion vibration can arise in a combustor by pressure fluctuation. Excessive combustion vibrations can lead to damage to the combustor and gas turbine. Therefore, a technique for suppressing combustion vibration of the combustor is desired.

  As a technique for suppressing combustion vibration of a gas turbine, a technique described in Patent Document 1 is known. Patent Document 1 describes a combustor including pilot fuel nozzles arranged in the circumferential direction. More specifically, in FIG. 1B described in Patent Document 1, a portion where the interval between a pair of adjacent pilot fuel nozzles is 90 ° is described.

Japanese Patent Laid-Open No. 11-294770 (especially refer to FIG. 1B)

  By the way, as a result of studies by the present inventors, it has been found that if there is a portion where the interval between the pilot fuel nozzles is too wide, combustion vibration may still be large.

  An object of at least one embodiment of the present invention is to provide a gas turbine combustor capable of sufficiently suppressing combustion vibration, a gas turbine including the gas turbine combustor, and a method for suppressing combustion vibration of the gas turbine combustor. .

  (1) A gas turbine combustor according to at least one embodiment of the present invention includes a first nozzle and a plurality of second nozzles arranged in a circumferential direction so as to surround the first nozzle. The first nozzle has n (n is an integer of 2 or more) fuel injection holes arranged in the circumferential direction, and the plurality of fuel injection holes are arbitrarily adjacent to each other in the circumferential direction. The angle difference θ [°] between the pair of fuel injection holes is set to satisfy 0 <n × θ / 360 <2, and the first nozzle has a fuel injection amount from one or more of the fuel injection holes. Is configured to inject fuel from all of the fuel injection holes so as to be different from the fuel injection amount from one or more of the other fuel injection holes.

  According to the configuration of (1) above, a deviation can be provided in the axial heat generation rate distribution of the flame in the combustion chamber. Thereby, concentration of heat generation can be avoided and combustion vibration of the combustor can be suppressed.

  (2) In some embodiments, in the configuration of the above (1), the plurality of fuel injection holes constitute a first injection hole group including one or more fuel injection holes and the first injection hole group. And a second injection hole group including one or more fuel injection holes other than the fuel injection hole to perform, wherein the first nozzle is connected to the first injection hole group and supplies fuel to the first injection hole group And a second fuel channel provided independently of the first fuel channel and connected to the second injection hole group for supplying fuel to the second injection hole group It is characterized by providing.

  According to the configuration of (2) above, independent fuel amount control is possible for each of the first injection hole group and the second injection hole group. Thereby, flexible combustion vibration avoidance operation according to a combustion situation can be performed.

  (3) In some embodiments, in the configuration of (1) or (2), the plurality of fuel injection holes include a first injection hole group including one or more fuel injection holes, and the first injection. A second injection hole group including one or more fuel injection holes other than the fuel injection holes constituting the hole group, the size of the fuel injection holes included in the first injection hole group, and the second injection hole group The size of the fuel injection hole included is different.

  According to the configuration of (3) above, it is possible to avoid the concentration of heat generation by changing the fuel injection amount in the circumferential direction without increasing the fuel flow path. For this reason, combustion vibration can be suppressed only by adjusting the diameter of the fuel injection hole.

  (4) In some embodiments, in any one of the configurations (1) to (3), the plurality of fuel injection holes include a first injection hole group including one or more fuel injection holes, And a second injection hole group including one or more fuel injection holes other than the fuel injection holes constituting the first injection hole group, and a fuel injection amount from each of the combustion injection holes constituting the first injection hole group And the fuel injection amount from each of the combustion injection holes constituting the second injection hole group, and the fuel injection holes included in the first injection hole group are continuously arranged in the circumferential direction. The fuel injection holes included in the second injection hole group are continuously arranged in the circumferential direction.

  According to the configuration of (4) above, the size of the flame can be ensured by continuously arranging the fuel injection holes in the circumferential direction. Thereby, generation | occurrence | production of the position where a flame does not exist in a circumferential direction position can be suppressed, and the fluctuation | variation of a pressure fluctuation can be suppressed. As a result, it is possible to suppress the occurrence of combustion vibration due to pressure fluctuation.

  (5) In some embodiments, in any one of the configurations (1) to (4), the plurality of fuel injection holes include a first injection hole group including one or more fuel injection holes, And a second injection hole group including one or more fuel injection holes other than the fuel injection holes constituting the first injection hole group, and a fuel injection amount from each of the combustion injection holes constituting the first injection hole group And the amount of fuel injection from each of the combustion injection holes constituting the second injection hole group, and the portion occupied by the first injection hole group is at both ends in the circumferential direction of the first injection hole group. The angle difference θ2 [°] between the pair of arranged fuel injection holes is an area of 80 ° or more.

  According to the configuration of (5) above, the circumferential length of the first injection hole group can be secured, and the size of the flame caused by the combustion of the fuel injected from the first injection hole group can be secured. . Thereby, generation | occurrence | production of the position where a flame does not exist in a circumferential direction position can be suppressed, and the fluctuation | variation of a pressure fluctuation can be suppressed. As a result, it is possible to suppress the occurrence of combustion vibration due to pressure fluctuation.

  (6) In some embodiments, in any one of the configurations (1) to (5), the plurality of fuel injection holes are between any pair of fuel injection holes adjacent in the circumferential direction. The angle difference θ [°] is arranged such that 0.8 ≦ n × θ / 360 ≦ 1.2.

  According to the configuration of (6) above, it is easy to form a plurality of fuel injection holes, and the combustor can be easily designed.

  (7) In some embodiments, in any one of the configurations (1) to (6), a plurality of the fuel injection holes are formed at equal intervals in the circumferential direction of the gas turbine combustor. Features.

  According to the configuration of (7) above, combustion vibration can be suppressed by changing the fuel injection amount in the circumferential direction.

  (8) In some embodiments, in any one of the above configurations (1) to (7), the gas turbine combustor is configured to burn a mixed fuel of air and fuel. Features.

  With configuration (8) above, it is possible to suppress the combustion vibration of the combustor even when a mixed fuel that easily generates combustion vibration is used.

  (9) A gas turbine according to at least one embodiment of the present invention generates the gas turbine combustor according to any one of (1) to (8) above and compressed air supplied to the combustor. And a turbine driven by the combustion gas generated in the gas turbine combustor.

  According to the configuration of (9) above, a deviation can be provided in the axial heat generation rate distribution of the flame in the combustion chamber. Thereby, concentration of heat generation can be avoided and combustion vibration of the combustor can be suppressed. As a result, damage to the gas turbine due to combustion vibration of the combustor can be suppressed.

  (10) A combustion vibration suppressing method for a gas turbine combustor according to at least one embodiment of the present invention comprises: a first nozzle; and a plurality of second nozzles arranged in a circumferential direction so as to surround the first nozzle. The first turbine has n fuel injection holes arranged in the circumferential direction (n is an integer of 2 or more), and the plurality of the plurality of fuel injection holes are arranged in the circumferential direction. The fuel injection holes are arranged such that an angle difference θ [°] between any pair of the fuel injection holes adjacent in the circumferential direction is 0 <n × θ / 360 <2, and the first nozzle is The fuel is injected from all the fuel injection holes so that the fuel injection amount from one or more of the fuel injection holes is different from the fuel injection amount from one or more of the other fuel injection holes.

  According to the configuration of (10) above, a deviation can be provided in the axial heat generation rate distribution of the flame in the combustion chamber. Thereby, concentration of heat generation can be avoided and combustion vibration of the combustor can be suppressed.

  According to at least one embodiment of the present invention, it is possible to provide a gas turbine combustor capable of sufficiently suppressing combustion vibration, a gas turbine including the gas turbine combustor, and a combustion vibration suppressing method for the gas turbine combustor. .

It is a schematic structure figure showing a gas turbine concerning one embodiment of the present invention. It is the schematic which shows the combustor which concerns on one Embodiment of this invention. It is the schematic which shows the combustor which concerns on one Embodiment of this invention, Comprising: It is a figure which expands and shows the combustor vicinity. It is sectional drawing of the 1st combustion burner vicinity in the combustor which concerns on one Embodiment of this invention. It is a top view of the swirler in the combustor concerning one embodiment of the present invention. It is the sectional view on the AA line of FIG. It is a figure explaining the position of the fuel injection hole formed in the 1st combustion burner in the combustor concerning one embodiment of the present invention. It is a figure which shows the fuel flow path connected to the 1st combustion burner in the combustor which concerns on one Embodiment of this invention. It is a graph which shows the relationship between a fuel-injection ratio and the magnitude | size of a combustion vibration. It is a figure which shows the fuel flow path connected to the 1st combustion burner in the combustor which concerns on two embodiment of this invention.

  Hereinafter, some embodiments of the present invention will be described with reference to the accompanying drawings. However, the contents described in the following embodiments or the contents described in the drawings are merely examples, and can be arbitrarily changed and implemented without departing from the gist of the present invention. Moreover, each embodiment can be implemented in any combination of two or more. Furthermore, in each embodiment, the same code | symbol shall be attached | subjected about a common member, and the overlapping description is abbreviate | omitted for the simplification of description.

In addition, the dimensions, materials, shapes, relative arrangements, and the like of the components described in the embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples. Absent.
For example, expressions expressing relative or absolute arrangements such as “in a certain direction”, “along a certain direction”, “parallel”, “orthogonal”, “center”, “concentric” or “coaxial” are strictly In addition to such an arrangement, it is also possible to represent a state of relative displacement with an angle or a distance such that tolerance or the same function can be obtained.
For example, an expression indicating that things such as “identical”, “equal”, and “homogeneous” are in an equal state not only represents an exactly equal state, but also has a tolerance or a difference that can provide the same function. It also represents the existing state.
For example, expressions representing shapes such as quadrangular shapes and cylindrical shapes represent not only geometrically strict shapes such as quadrangular shapes and cylindrical shapes, but also irregularities and chamfers as long as the same effects can be obtained. A shape including a part or the like is also expressed.
On the other hand, the expressions “comprising”, “comprising”, “comprising”, “including”, or “having” one constituent element are not exclusive expressions for excluding the existence of the other constituent elements.

  FIG. 1 is a schematic configuration diagram illustrating a gas turbine 100 according to an embodiment of the present invention. As shown in FIG. 1, a gas turbine 100 according to an embodiment includes a compressor 2 for generating compressed air as an oxidant supplied to a combustor 4, and combustion gas using compressed air and fuel. A combustor 4 (gas turbine combustor) for generating and a turbine 6 configured to be driven by the combustion gas generated in the combustor 4 are provided. In the case of the gas turbine 100 for power generation, a power generator (not shown) is connected to the turbine 6, and power is generated by the rotational energy of the turbine 6.

  The compressor 2 is provided on the compressor casing 10, the inlet side of the compressor casing 10, and penetrates both the compressor inlet 10 and the turbine casing 22 (described later). The rotor 8 provided in this way, and various blades disposed in the compressor casing 10. The various blades are an inlet guide blade 14 provided on the air intake 12 side, a plurality of stationary blades 16 fixed on the compressor casing 10 side, and a rotor so as to be alternately arranged with respect to the stationary blades 16. 8 and a plurality of blades 18 implanted in 8. The compressor 2 may include other components such as a bleed chamber (not shown). In such a compressor 2, the air taken in from the air intake 12 passes through the plurality of stationary blades 16 and the plurality of moving blades 18 and is compressed into high-temperature and high-pressure compressed air. The high-temperature and high-pressure compressed air is sent from the compressor 2 to the subsequent combustor 4.

  The combustor 4 is disposed in the casing 20. Although only one is shown in FIG. 1, a plurality of combustors 4 are arranged in a ring shape around the rotor 8 in the casing 20. The combustor 4 is supplied with fuel and compressed air generated by the compressor 2 and combusts the fuel to generate combustion gas that is a working fluid of the turbine 6. Then, the combustion gas is sent from the combustor 4 to the subsequent turbine 6.

  The turbine 6 includes a turbine casing 22 and various blades disposed in the turbine casing 22. The various blades include a plurality of stationary blades 24 fixed to the turbine casing 22 side, and a plurality of moving blades 26 implanted in the rotor 8 so as to be alternately arranged with respect to the stationary blades 24. . The turbine 6 may include other components such as an outlet guide vane (not shown). In the turbine 6, the combustion gas passes through the plurality of moving blades 26 extending from the plurality of stationary blades 24, so that the rotor 8 is rotationally driven. As a result, a generator (not shown) connected to the rotor 8 is driven.

  An exhaust chamber 30 is connected to the downstream side of the turbine casing 22 via an exhaust casing 28. The combustion gas after driving the turbine 6 is discharged to the outside through the exhaust casing 28 and the exhaust chamber 30.

  FIG. 2 is a schematic view showing a combustor 4 according to an embodiment of the present invention. Since FIG. 2 is a schematic diagram, the structure shown in FIG. 2 is partially different from the structure shown in FIG. The combustor 4 includes a combustor liner 46 provided in a combustor casing 40 defined by the casing 20, a first combustion burner 50 and a plurality of second combustion burners 60 respectively disposed in the combustor liner 46. ,including. Further, below the combustor casing 40, a casing inlet 42 for taking in the high-temperature and high-pressure compressed air generated by the compressor 2 (see FIG. 1) into the combustor casing 40 is formed. The combustor 4 may include other components such as a bypass pipe (not shown) for bypassing the combustion gas.

  The combustor liner 46 includes an inner cylinder 46a disposed around the first combustion burner 50 and the plurality of second combustion burners 60, and a tail cylinder 46b connected to the tip of the inner cylinder 46a. . The first combustion burner 50 is disposed along the central axis of the combustor liner 46.

  FIG. 3 is a schematic view showing the combustor 4 according to one embodiment of the present invention, and is an enlarged view showing the vicinity of the combustor 4. The first combustion burner 50 is, for example, a burner for burning a diffusion fuel supplied through a diffusion fuel flow path (not shown) to generate a diffusion combustion flame. Further, as will be described in detail later, the first combustion burner 50 is configured to burn a premixed fuel (premixed gas) from a swirler (swivel blade) 58 to generate a combustion flame. The first combustion burner 50 includes a first nozzle 54 connected to the fuel ports 52 a and 52 b, a cone 56 disposed so as to surround the first nozzle 54, and a swirler 58 provided on the outer periphery of the first nozzle 54. . The first nozzle 54 is, for example, a nozzle for injecting diffusion fuel and premixed fuel.

  The fuel port 52a is connected to a first fuel flow path 83 described with reference to FIG. The fuel port 52b is connected to a second fuel flow path 85, which will be described with reference to FIG. Both the first fuel channel 83 and the second fuel channel 85 are provided in the first nozzle 54 and are connected to a swirler 58 formed in the first combustion burner 50.

  The second combustion burner 60 is a burner for burning premixed gas, for example. The second combustion burner 60 includes a second nozzle 63 connected to the fuel port 62, a burner cylinder 66 disposed so as to surround the second nozzle 63, a swirler 70 provided on the outer periphery of the second nozzle 63, Is provided. The second nozzle 63 is a nozzle for injecting premixed fuel, for example. In the circumferential direction of the first nozzle 54, eight (or a plurality of second nozzles 63) may be arranged apart from each other so as to surround the first nozzle 54. In FIG. 3, only two second nozzles 63 are shown.

  In the combustor 4, the high-temperature and high-pressure compressed air generated by the compressor 2 is supplied into the combustor compartment 40 from the compartment inlet 42 (see FIG. 2). The compressed air flowing into the combustor casing 40 and the fuel injected from the swirler 58 of the first combustion burner 50 through the fuel ports 52 a and 52 b are mixed in the cone 56. The mixed fuel is ignited and burned by a seed fire (not shown), and combustion gas is generated. The combustion gas is then swirled by swirler 58 and flows into combustor liner 46. A part of the combustion gas diffuses to the surroundings with a flame. As a result, the mixed fuel flowing from the second combustion burner 60 into the combustor liner 46 is ignited and burned.

  FIG. 4 is a cross-sectional view of the vicinity of the first combustion burner 50 in the combustor 4 according to one embodiment of the present invention. For simplification of illustration, a diffusion fuel injection hole for injecting diffusion fuel from the first nozzle 54 is not shown. Eight swirlers 58 (only two are shown in FIG. 4) are formed around the first nozzle 54 so as to protrude outward from the outer peripheral surface of the first nozzle 54. Inside the swirler 58, an internal space 84 connected to the first fuel flow path 83 or the second fuel flow path 85 is formed. Further, each of the swirlers 58 is formed with a fuel injection hole 59 (see FIG. 7, not shown in FIG. 4) communicating with the inner space 84.

  Here, as described above, the first fuel flow path 83 is connected to the fuel port 52a. Therefore, the fuel supplied to the inner space 84 of the swirler 58 through the fuel port 52 a and the first fuel flow path 83 is injected through the fuel injection hole 59 formed in the swirler 58. The second fuel flow path 85 is connected to the fuel port 52b. Therefore, the fuel supplied to the inner space 84 of the swirler 58 through the fuel port 52 b and the second fuel flow path 85 is also injected through the fuel injection hole 59 formed in the swirler 58. The injected fuel is mixed with compressed air in the air flow path 34 and burned.

  The fuel combusted in the combustor 4 is a mixed fuel of compressed air (a form of air) and fuel. That is, the combustor 4 is configured to burn a mixed fuel of air and fuel. Although details will be described later, in the gas turbine 100, the combustion vibration of the combustor 4 is sufficiently suppressed. Therefore, even when a mixed fuel that easily generates combustion vibration is used, the combustion vibration of the combustor 4 can be suppressed.

  FIG. 5 is a front view of the swirler 58 in the combustor 4 according to the embodiment of the present invention. The swirler 58 has a streamline shape in plan view. Since the swirler 58 having such a shape is arranged on the outer periphery of the first nozzle 54, the swirler 58 swirls into the compressed air flowing through the air passage 34 (see FIG. 4) formed between the first nozzle 54 and the cone 56. Power is granted. Thereby, the compressed air flows into the cone 56 as a swirling air flow.

  The swirler 58 has a back surface 581 located on the fuel port 52 (see FIG. 3) side and a blade vent surface 582 located on the combustor liner 46 (see FIG. 3) side. Among these, fuel injection holes 59 (though fuel injection holes 59 formed in the back surface 581 are not shown) penetrating in the thickness direction are formed in the back surface 581 and the blade surface 582, respectively.

  6 is a cross-sectional view taken along line AA in FIG. The eight swirlers 58 are arranged at equal intervals on the outer periphery of the first nozzle 54. Further, an inner space 84 connected to either the first fuel channel 83 or the second fuel channel 85 is formed inside each swirler 58. Specifically, the first fuel flow path 83 is connected to the inner spaces 84 of the five swirlers 58 located in the upper half (including the horizontal direction) of the eight swirlers 58. On the other hand, the second fuel flow path 85 provided independently of the first fuel flow path 83 is connected to the inner spaces 84 of the three swirlers 58 located in the lower half. As described above, the fuel flow path connected to the inner space 84 of the swirler 58 is different for each inner space 84, so that the fuel injection hole 59 (see FIG. 7; not shown in FIG. 6) communicating with the inner space 84 is provided. The fuel injection amount can be changed for each fuel injection hole 59.

  FIG. 7 is a view for explaining the position of the fuel injection hole 59 formed in the first combustion burner 50 in the combustor 4 according to the embodiment of the present invention. In FIG. 7, for the eight swirlers 58, the blade flank surface 582 is shown. As shown in FIG. 7, the eight swirlers 58a, 58b, 58c, 58d, 58e, 58f, 58g, and 58h have fuel injection holes 59a, 59b, 59c, 59d, 59e, 59f, and 59g at their respective edges. , 59h are formed. Accordingly, the first nozzle 54 has eight fuel injection holes 59 arranged in the circumferential direction via the swirler 58. In the combustor 4, as an example, the eight fuel injection holes 59 are arranged at equal intervals on the same circumference around the point P that is the axial center of the cylindrical first nozzle 54.

  Note that the number n of the fuel injection holes 59 is arbitrary, and is not limited to n = 8 as described above. Therefore, the number n of the fuel injection holes 59 may be arbitrarily determined as an integer in the range of 2 or more according to the number of the two or more swirlers 58. In addition, the fuel injection hole 59 is provided in the first nozzle 54 through the swirler 58 as described above, but may be formed in a member other than the swirler 58, and the fuel injection hole 59 may be directly formed on the outer periphery of the first nozzle 54. An injection hole 59 may be formed.

  In the combustor 4, the eight fuel injection holes 59 have an angular difference θ (= 360 / n between any pair of adjacent fuel injection holes 59 in the circumferential direction of the first nozzle 54. In the example shown in FIG. = 8) [°] is arranged such that 0 <n × θ / 360 <2. Specifically, as an example, the angle difference θ between any pair of adjacent fuel injection holes 59 is 45 °. The angle difference θ between the pair of fuel injection holes 59a and 59b is an angle difference θ obtained by connecting the center of gravity of the fuel injection hole 59a, the point P, and the center of gravity of the fuel injection hole 59b. .

  The angle θ is not limited to 45 ° as described above (in the case of n = 8), but from the viewpoint of ease of design of the combustor 4, any pair of adjacent fuel injection holes 59. Are preferably formed so as to be at equal intervals or close to equal intervals. Specifically, as the lower limit value of the range of θ, as described above, 0 <n × θ / 360, preferably 0.2 ≦ n × θ / 360, more preferably 0.4 ≦ n × θ / 360. More preferably, 0.6 ≦ n × θ / 360, and particularly preferably 0.8 ≦ n × θ / 360. Further, as the upper limit, as described above, n × θ / 360 <2, preferably n × θ / 360 ≦ 1.8, more preferably n × θ / 360 ≦ 1.6, and still more preferably n × θ. /360≦1.4, particularly preferably n × θ / 360 ≦ 1.2. And among the fuel injection holes 59 of the combustor 4, it is preferable that the angle difference θ between all adjacent fuel injection holes 59 satisfies the above range.

  However, among θ satisfying the above range, among them, θ is preferable such that any pair of adjacent fuel injection holes 59 are equally spaced. Therefore, in the example shown in FIG. 7 (n = 8), the angle difference θ between the pair of fuel injection holes 59a and 59b around the point P is 45 ° as described above. Similarly, the angle difference θ between another pair of adjacent fuel injection holes 59 is 45 °. As described above, since the plurality of fuel injection holes 59 are formed at equal intervals in the circumferential direction of the combustor 4, the fuel injection amount can be changed in the circumferential direction, and combustion vibration can be suppressed. However, the angle difference θ may be different for each adjacent fuel injection hole 59.

  FIG. 8 is a view showing the first fuel flow path 83 and the second fuel flow path 85 connected to the first combustion burner 50 in the combustor 4 according to the embodiment of the present invention. In FIG. 8, the first fuel channel 83 and the second fuel channel 85 are indicated by thick solid lines.

In the combustor 4, among the eight fuel injection holes 59, the first fuel flow flows into the upper half (including the horizontal direction) fuel injection holes 59 a, 59 b, 59 c, 59 d, and 59 e that are continuously arranged in the circumferential direction. A path 83 is connected. Accordingly, the first fuel flow path 83 (see also FIG. 3) branches in the middle and is connected to each of the fuel injection holes 59a, 59b, 59c, 59d, and 59e. Similarly, the second fuel flow path 85 provided independently of the first fuel flow path 83 is connected to the lower half fuel injection holes 59f, 59g, and 59h that are continuously arranged in the circumferential direction. . Accordingly, the second fuel flow path 85 (see also FIG. 3) branches in the middle and is connected to each of the fuel injection holes 59f, 59g, 59h.
Hereinafter, the fuel injection holes 59a, 59b, 59c, 59d, and 59e are collectively referred to as a “first injection hole group 59A”. The fuel injection holes 59f, 59g, and 59h are collectively referred to as “second injection hole group 59B”.

  Therefore, in the combustor 4, the first nozzle 54 is connected to the first injection hole group 59 </ b> A, and the first fuel flow path 83 for supplying fuel to the first injection hole group 59 </ b> A, and the first fuel flow path 83. And a second fuel flow path 85 that is connected to the second injection hole group 59B and supplies fuel to the second injection hole group 59B. Thus, by providing the two first fuel flow paths 83 and the second fuel flow paths 85, independent fuel amount control is possible for each of the first injection hole group 59A and the second injection hole group 59B. Become. Thereby, flexible combustion vibration avoidance operation according to a combustion situation can be performed.

  In the combustor 4, five fuel injection holes 59 are connected to the first fuel flow path 83, and three fuel injection holes 59 are connected to the second fuel flow path 85. Therefore, if the amount of fuel flowing through the first fuel passage 83 and the amount of fuel flowing through the second fuel passage 85 are the same, the fuel injection holes 59 (first injection holes) connected to the first fuel passage 83 The amount of fuel injected from each of the groups 59A) is smaller than the amount of fuel injected from each of the fuel injection holes 59 (second injection hole group 59B) connected to the second fuel flow path 85. That is, in the first nozzle 54 of the fuel device 4, the fuel injection amount from one or more fuel injection holes 59 is different from the fuel injection amount from one or more other fuel injection holes 59. Fuel is injected from all the fuel injection holes 59.

  As described above, in the combustor 4, fuel is injected from all the fuel injection holes 59 provided in the first nozzle 54, while the fuel injection amount from the first injection hole group 59 </ b> A and the second injection hole group 59 </ b> B. The fuel injection amount is different. By doing in this way, deviation can be provided in the axial heat rate distribution of the flame in the combustor liner 46 (combustion chamber). That is, if the fuel injection amount is large, the combustion speed increases, so that the flame position approaches the first nozzle 54. On the other hand, as the fuel injection amount decreases, the combustion speed decreases, and the flame position moves away from the first nozzle 54. Thereby, concentration of heat generation can be avoided and combustion vibration of the combustor 4 can be suppressed.

  Further, in each of the first injection hole group 59A and the second injection hole group 59B, the fuel injection holes 59 are continuously arranged in the circumferential direction, so that the fuel injection is continuously performed in the circumferential direction. The size of can be secured. Thereby, generation | occurrence | production of the position where a flame does not exist in a circumferential direction position can be suppressed, and the fluctuation | variation of a pressure fluctuation can be suppressed. As a result, it is possible to suppress the occurrence of combustion vibration due to pressure fluctuation.

  The number of fuel injection holes 59 included in the first injection hole group 59A is not particularly limited as long as it is 1 or more. Further, the number of fuel injection holes 59 included in the second injection hole group 59B is not particularly limited as long as it is 1 or more. However, from the viewpoint of sufficiently ensuring the size of the flame caused by the combustion of the fuel injected from the fuel injection holes 59, the portion occupied by the first injection hole group 59A is disposed at both ends in the circumferential direction of the first injection hole group 59A. The angle difference θ2 [°] between the pair of fuel injection holes 59 is preferably in the region of 80 ° or more. The angle difference θ2 is more preferably 90 ° or more, and particularly preferably 120 ° or more. In the example shown in FIG. 8, the portion occupied by the first injection hole group 59A is 180 ° as the angle difference θ2 between the pair of fuel injection holes 59c and 59g arranged at both ends in the circumferential direction of the first injection hole group 59A. It is an area that becomes.

  As described above, by setting the angle difference θ2 to 80 ° or more, the circumferential length of the first injection hole group 59A is secured, and the flame resulting from the combustion of the fuel injected from the first injection hole group 59A. The size of can be secured. Thereby, generation | occurrence | production of the position where a flame does not exist in a circumferential direction position can be suppressed, and the fluctuation | variation of a pressure fluctuation can be suppressed. As a result, it is possible to suppress the occurrence of combustion vibration due to pressure fluctuation.

  Further, in the example shown in FIG. 8, two injection holes, a first injection hole group 59A including a fuel injection hole 59 with a small fuel injection amount and a second injection hole group 59B including a fuel injection hole 59 with a large fuel injection amount. Although a group is shown, the number of injection hole groups may be three or more. That is, three or more injection hole groups each including one or more fuel injection holes 59 having the same fuel injection amount may be provided, and the fuel injection amount may be different in each injection hole group. And as needed, three or more fuel flow paths for supplying fuel to three or more injection hole groups can be provided. Even if the number of fuel injection holes 59 constituting the injection hole group is only one, it is referred to as an “injection hole group” for convenience.

  FIG. 9 is a graph showing the relationship between the fuel injection ratio R and the magnitude of combustion vibration. This graph is a graph obtained using the above-described combustor 4 by the study of the present inventors. However, the shape of this graph is merely an example, and other shapes are not excluded. In the graph, the “fuel injection ratio R” on the horizontal axis is injected from each fuel injection hole 59 included in the first injection hole group 59 </ b> A with respect to the fuel injection amount injected from each fuel injection hole 59 of the combustor 4. Represents the ratio of fuel injection amount.

The fuel injection ratio R indicates that the number of fuel injection holes 59 constituting the first injection hole group 59A is m _A (m _A = 5 in the example shown in FIG. 7), and the entire fuel injection holes 59 of the first injection hole group 59A. The amount of fuel supplied to G _A is G _A , the number of fuel injection holes constituting the second injection hole group 59B is m _B (m _B = 3 in the example shown in FIG. 7), and the fuel injection holes 59 of the second injection hole group 59B. When the amount of fuel supplied to the whole of defining and G _B, is represented by the following formula (1). Incidentally, _{G A} is the fuel flow rate in the first fuel passage 83 of the (see FIG. 8). Also, _{G B} is the fuel flow rate in the second fuel flow path 85 of the (see FIG. 8).

In the graph shown in FIG. 9, a point A (R = 0) represents a state in which fuel is not injected from each fuel injection hole 59 of the first injection hole group 59A. In this case, since R _A / m _A = 0, R = 0. Hereinafter, this state is referred to as “first injection hole group 59 </ b> A closed state”. Point B (R = R ₁ ) indicates that the fuel injection amount from each fuel injection hole 59 of the first injection hole group 59A and the fuel injection amount from each fuel injection hole 59 of the second injection hole group 59B are Represents an equal state. In this case, since G _A / m _A = G _B / m _B , R = R ₁ = 1. Hereinafter, this state is referred to as “equal state”. Furthermore, the point C (R = R ₂ ) represents a state where fuel is not injected from each fuel injection hole 59 of the second injection hole group 59B. In this _case, since it is G B _{/ m} B = _0, it is _{R = R 2 = (m A} + m B) / m A. Hereinafter, this state is referred to as “second injection hole group 59B closed state”.

  In this graph, in the closed state (point A) of the first injection hole group 59A, the fuel injection amount from each fuel injection hole 59 of the second injection hole group 59B is made constant, and each fuel injection of the first injection hole group 59A is performed. When fuel is gradually injected from the hole 59 (when R is increased), the magnitude of the combustion vibration is reduced. At this time, the deviation of the fuel injection amount between the fuel injection amount from each fuel injection hole 59 of the first injection hole group 59A and the fuel injection amount from each fuel injection hole 59 of the second injection hole group 59B is gradually reduced. Become. Then, the magnitude of the combustion vibration increases again at the point D as a boundary, and reaches a uniform state (point B).

  Next, from the equal state (point B), the fuel injection amount from each fuel injection hole 59 of the first injection hole group 59A is made constant, and this time the fuel from each fuel injection hole 59 of the second injection hole group 59B. When the injection amount is decreased little by little (when R is increased), the magnitude of the combustion vibration decreases. At this time, the deviation of the fuel injection amount between the fuel injection amount from each fuel injection hole 59 of the first injection hole group 59A and the fuel injection amount from each fuel injection hole 59 of the second injection hole group 59B gradually increases. Become. Then, the magnitude of the combustion vibration becomes larger again at the point E as a boundary, and the second injection hole group 59B is closed (point C).

  For example, as shown in FIG. 9, as a reason for suppressing the combustion vibration, the present inventors have considered as follows. By injecting fuel from both the first injection hole group 59A and the second injection hole group 59B, it is possible to suppress the occurrence of a portion where no flame is formed. In addition to this, an intentional deviation can be provided in the axial heating rate distribution of the flame in the combustor liner 46 by changing the fuel amount. And when the present inventors examined, it is thought that heat | fever concentration is avoided by these interactions and the combustion vibration of the combustor 4 can fully be suppressed as shown, for example in FIG.

  In the example shown in FIG. 8, the magnitude of the fuel injection ratio R may be changed as appropriate according to the operating conditions such as the fuel properties, the structure of the combustor 4, and the operation duration. That is, by controlling a fuel amount adjusting valve (not shown) or the like according to the actual operating situation and adjusting at least one of the fuel amounts supplied to the first injection hole group 59A or the second injection hole group 59B, The injection amount can be adjusted. Thereby, the fuel injection ratio R can be changed, and the combustion vibration can be flexibly suppressed according to the actual driving situation.

  In the gas turbine 100 including the combustor 4 as described above, the combustion vibration of the combustor 4 is suppressed as described above. Therefore, damage to the gas turbine 100 due to combustion vibration of the combustor 4 can be suppressed. Further, by using the combustor 4, all the fuel injection holes 95 are arranged so that the fuel injection amount from one or more fuel injection holes 59 is different from the fuel injection amount from one or more other fuel injection holes 59. The combustion vibration suppression method of the combustor which can suppress the combustion vibration of the combustor 4 by injecting fuel from the fuel can be provided.

  In the above example, the fuel injection hole 59 in the first combustion burner 50 is focused. For example, the fuel injection amount is focused on two or more fuel injection holes (not shown) in the second combustion burner 60. Deviations can be provided. In the first combustion burner 50, a mixed fuel of compressed air and fuel is injected, and diffusion fuel is injected through diffusion fuel injection holes (not shown). Therefore, two or more diffusion fuel injection holes may be provided, and a deviation may be provided in the diffusion fuel injection amount.

  In the above example, the fuel injection holes 59 of the combustor 4 are divided into two injection hole groups (first injection hole group 59A and second injection hole group 59B), and fuel injection from these two injection hole groups is performed. The amount was changed. However, for example, the fuel injection holes 59 of the combustor 4 are divided into three injection hole groups (a first injection hole group, a second injection hole group, and a third injection hole group). The fuel injection amount may be changed. In this case, for example, the first injection hole group and the second injection hole group are considered as one different group, and the fuel injection amount is determined by the above method for two groups, that is, the other injection group and the third injection hole group. Can be determined. Then, it is only necessary to determine the fuel injection amounts of the first injection hole group and the second injection hole group constituting the other group with reference to the fuel amount injected in the different group. And by these methods, the fuel injection quantity in three injection hole groups (a 1st injection hole group, a 2nd injection hole group, and a 3rd injection hole group) can be determined. The same applies when there are four or more injection hole groups.

  FIG. 10 is a view showing a fuel flow path connected to the first combustion burner 50A in the combustor (not shown) according to the second embodiment of the present invention. In the example shown in FIG. 8 and the like, two independent fuel flow paths (the first fuel flow path 83 and the second fuel flow path 85) are provided for supplying fuel to the fuel injection holes 59. . However, in the combustor according to the two embodiments of the present invention, only the first fuel flow path 83 is provided, and the second fuel flow path 85 is not provided. As shown in FIG. 10, the first fuel flow path 83 branches in the middle, and fuel is supplied to the eight fuel injection holes 59.

  As shown in FIG. 10, the size of the fuel injection holes 59 included in the first injection hole group 59A is different from the size of the fuel injection holes 59 included in the second injection hole group 59B. Specifically, the size of the fuel injection holes 59 included in the first injection hole group 59A is smaller than the size of the fuel injection holes 59 included in the second injection hole group 59B. Thus, the fuel injection amount injected from each of the three combustion injection holes 59 constituting the second injection hole group B is injected from each of the five combustion injection holes 59 constituting the first injection hole group A. More than the fuel injection amount.

  By doing in this way, like the combustor 4 described with reference to FIG. 8 described above, it is possible to change the fuel injection amount in the circumferential direction without increasing the fuel flow path, and to avoid the concentration of heat generation. For this reason, combustion vibration can be suppressed only by adjusting the diameter of the fuel injection hole.

2 Compressor 4 Combustor 6 Turbine 8 Rotor 10 Compressor casing 12 Inlet 14 Inlet guide vanes 16 and 24 Stator vanes 18 and 26 Rotor blade 20 Casing 22 Turbine casing 28 Exhaust casing 30 Exhaust chamber 34 Air passage 40 Combustor vehicle Chamber 42 Entrance 46a Inner cylinder 46b Trailing cylinder 50, 50A First combustion burners 52, 62, 62a, 62b Fuel port 54 First nozzle 56 Cone 58, 58a, 58b, 58c, 58d, 58e, 58f, 58g, 58h , 70 Swirler 59 Fuel injection holes 59, 59a, 59b, 59c, 59d, 59e, 59f, 59g, 59h Fuel injection holes 59A First injection hole group 59B Second injection hole group 60 Second combustion burner 63 Second nozzle 66 Burner Cylinder 83 First fuel flow path 84 Inner space 85 Second fuel flow path 100 Gas turbine 581 Rear surface 582 Blade surface

Claims (10)

A gas turbine combustor comprising: a first nozzle; and a plurality of second nozzles arranged in a circumferential direction so as to surround the first nozzle,
The first nozzle has n (n is an integer of 2 or more) fuel injection holes arranged in the circumferential direction,
The plurality of fuel injection holes are arranged such that an angle difference θ [°] between any pair of fuel injection holes adjacent in the circumferential direction is 0 <n × θ / 360 <2.
The first nozzle injects fuel from all the fuel injection holes such that the fuel injection amount from one or more of the fuel injection holes is different from the fuel injection amount from one or more of the other fuel injection holes. A gas turbine combustor configured as described above. The plurality of fuel injection holes include a first injection hole group including one or more fuel injection holes, and a second injection hole including one or more fuel injection holes other than the fuel injection holes constituting the first injection hole group. Including groups,
The first nozzle is
A first fuel flow path connected to the first injection hole group for supplying fuel to the first injection hole group;
A second fuel flow path provided independently of the first fuel flow path, connected to the second injection hole group, and for supplying fuel to the second injection hole group, The gas turbine combustor according to claim 1. The plurality of fuel injection holes include a first injection hole group including one or more fuel injection holes, and a second injection hole including one or more fuel injection holes other than the fuel injection holes constituting the first injection hole group. Including groups,
The size of the fuel injection hole included in the first injection hole group and the size of the fuel injection hole included in the second injection hole group are different from each other. Gas turbine combustor. The plurality of fuel injection holes include a first injection hole group including one or more fuel injection holes, and a second injection hole including one or more fuel injection holes other than the fuel injection holes constituting the first injection hole group. Including groups,
The fuel injection amount from each of the combustion injection holes constituting the first injection hole group is different from the fuel injection amount from each of the combustion injection holes constituting the second injection hole group,
The fuel injection holes included in the first injection hole group are continuously arranged in the circumferential direction,
The gas turbine combustor according to any one of claims 1 to 3, wherein the fuel injection holes included in the second injection hole group are continuously arranged in the circumferential direction. The plurality of fuel injection holes include a first injection hole group including one or more fuel injection holes, and a second injection hole including one or more fuel injection holes other than the fuel injection holes constituting the first injection hole group. Including groups,
The fuel injection amount from each of the combustion injection holes constituting the first injection hole group is different from the fuel injection amount from each of the combustion injection holes constituting the second injection hole group,
The portion occupied by the first injection hole group is an area of 80 ° or more as an angle difference θ2 [°] between a pair of fuel injection holes arranged at both ends in the circumferential direction of the first injection hole group. The gas turbine combustor according to any one of claims 1 to 4. The plurality of fuel injection holes are arranged such that an angle difference θ [°] between any pair of fuel injection holes adjacent in the circumferential direction is 0.8 ≦ n × θ / 360 ≦ 1.2. The gas turbine combustor according to any one of claims 1 to 5, wherein The gas turbine combustor according to any one of claims 1 to 6, wherein a plurality of the fuel injection holes are formed at equal intervals in the circumferential direction of the gas turbine combustor. The gas turbine combustor according to any one of claims 1 to 7, wherein the gas turbine combustor is configured to burn a mixed fuel of air and fuel. A gas turbine combustor according to any one of claims 1 to 8,
A compressor for generating compressed air to be supplied to the gas turbine combustor;
A turbine driven by combustion gas generated in the gas turbine combustor;
A gas turbine comprising: A method for suppressing combustion vibration of a gas turbine combustor comprising: a first nozzle; and a plurality of second nozzles arranged in a circumferential direction so as to surround the first nozzle,
The first nozzle has n (n is an integer of 2 or more) fuel injection holes arranged in the circumferential direction,
The plurality of fuel injection holes are arranged such that an angle difference θ [°] between any pair of fuel injection holes adjacent in the circumferential direction is 0 <n × θ / 360 <2.
The first nozzle injects fuel from all the fuel injection holes such that the fuel injection amount from one or more of the fuel injection holes is different from the fuel injection amount from one or more of the other fuel injection holes. A method for suppressing combustion vibration of a gas turbine combustor, characterized in that:

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