JP4961415B2 - Gas turbine combustor - Google Patents

Description

  The present invention relates to a gas turbine combustor.

  Environmental regulations and social demands are increasing day by day, and even higher efficiency and lower NOx are required for gas turbines.

  As one measure for improving the efficiency of the gas turbine, it is conceivable to raise the turbine inlet gas temperature. In this case, however, there is a concern about an increase in NOx emissions as the flame temperature rises in the gas turbine combustor. .

  Patent Document 1 includes a fuel nozzle that supplies fuel to a combustion chamber, and an oxidant nozzle that is located downstream of the fuel nozzle and that supplies oxidant. A fuel combustion nozzle having a hole and a coaxial arrangement is disclosed. Moreover, in patent document 1, in order to enable re-ignition even if the flame produced | generated by the coaxial jet by fuel and air blows off, the outer peripheral side member of the plate provided with the oxidizer nozzle is formed thicker than the center side member. (Fig. 1).

JP 2005-106305 A

  However, Cited Document 1 does not consider NOx reduction.

  Therefore, an object of the present invention is to provide a structure that achieves both low NOx and combustion stability in a gas turbine combustor.

  According to the present invention, the combustion chamber side wall surface of the air hole plate has an inner peripheral side wall surface located on the downstream side of the combustion chamber with respect to the outer peripheral side wall surface, and an air hole on the wall surface of the connecting portion connecting the inner peripheral side wall surface and the outer peripheral side wall surface. The connecting portion wall surface is inclined with respect to the central axis so that the radial distance from the plate central axis decreases on the downstream side compared to the upstream side of the combustion chamber.

  ADVANTAGE OF THE INVENTION According to this invention, in a gas turbine combustor, the structure which makes low NOx and combustion stability compatible can be provided.

  Each example will be described below.

  FIG. 2 is a system diagram showing the overall configuration of the power generation gas turbine plant 1000.

  In FIG. 2, the power generation gas turbine pressurizes the suction air 100 to generate the high-pressure air 101, and the high-pressure air 101 generated by the compressor 1 and the fuel 200 are burned to generate the high-temperature combustion gas 102. The generated gas turbine combustor 2, the turbine 3 driven by the high-temperature combustion gas 102 generated by the gas turbine combustor 2, the generator 20 that is rotated by driving the turbine 3 to generate electric power, the compressor 1, the turbine 3 and the shaft 21 which connects the generator 20 integrally.

  The gas turbine combustor 2 is stored inside the casing 4.

  The gas turbine combustor 2 includes a burner 6 at its head, and a generally cylindrical combustor liner that separates high-pressure air and combustion gas inside the gas turbine combustor 2 on the downstream side of the burner 6. 10 is provided.

  On the outer periphery of the combustor liner 10, a flow sleeve 11 serving as an outer peripheral wall that forms an air flow path through which high-pressure air flows down is disposed. The flow sleeve 11 is larger in diameter than the combustor liner 10 and is disposed in a cylindrical shape that is substantially concentric with the combustor liner 10.

  On the downstream side of the combustor liner 10, a tail cylinder inner cylinder 12 for guiding the high-temperature combustion gas 102 generated in the combustion chamber 50 of the gas turbine combustor 2 to the turbine 3 is disposed. Further, a tail cylinder outer cylinder 13 is disposed on the outer peripheral side of the tail cylinder inner cylinder 12.

  The suction air 100 becomes high-pressure air 101 after being compressed by the compressor 1. After the high pressure air 101 is filled in the casing 4, the high pressure air 101 flows into the space between the tail cylinder inner cylinder 12 and the tail cylinder outer cylinder 13, and convectively cools the tail cylinder inner cylinder 12 from the outer wall surface.

  Further, the high-pressure air 101 flows down toward the combustor head through an annular flow path formed between the flow sleeve 11 and the combustor liner 10. The high pressure air 101 is used for convection cooling of the combustor liner 10 in the middle of flowing down.

  Further, a part of the high-pressure air 101 that flows down flows into the combustor liner from a number of cooling holes provided in the combustor liner 10 and is used for film cooling of the combustor liner 10.

  High-pressure air 101 that has not been used for film cooling of the combustor liner 10 flows into the combustor liner 10 from a number of air holes 32 provided in the air hole plate 33 provided on the upstream side wall surface of the combustion chamber 50.

  The high-pressure air 101 that has flowed into the combustor liner 10 from a large number of air holes 32 is combusted in the combustion chamber 50 together with the fuel 200 ejected from the fuel nozzle 31 to generate high-temperature combustion gas 102. This high-temperature combustion gas 102 is supplied to the turbine 3 through the transition piece inner cylinder 12.

  The high-temperature combustion gas 102 is discharged after driving the turbine 3 to become exhaust gas 103.

  The driving force obtained by the turbine 3 is transmitted to the compressor 1 and the generator 20 through the shaft 21.

  Part of the driving force obtained by the turbine 3 drives the compressor 1 to pressurize the air and generate high-pressure air. Further, another part of the driving force obtained by the turbine 3 rotates the generator 20 to generate electric power.

  Next, the configuration of the gas turbine combustor 2 will be described.

  In the burner 6 of the gas turbine combustor 2 of the present embodiment, a large number of fuel nozzles 31 for ejecting fuel are attached to the fuel nozzle header 30. The air hole plate 33 having a large number of air holes 32 corresponds to each of the fuel nozzles 31 and is located on the downstream side of the fuel nozzle 31.

  The A part detailed view and the B part detailed view of FIG. 15 represent the arrangement relationship between the pair of fuel nozzles 31 and the air holes 32 in the A part and the B part in the gas turbine combustor 2 described in FIG. 2.

  In part A, the air holes 32 provided in the fuel nozzle 31 and the air hole plate 33 are arranged so that the axes of both are located on the same line. On the other hand, in the part B, the central axis of the air hole 32 is inclined with respect to the central axis of the fuel nozzle 31 (details will be described later). Therefore, the cut surface shape of the air hole plate by a plane including the central axis of the air hole plate is expressed as shown in the B part detailed view. In addition, all the air hole shapes in FIGS. 1-14 are represented by a straight pipe shape for convenience. Like the A part and the B part, the air jet 36 flows around the fuel jet 35 inside the air hole. As many such coaxial jets of the fuel jet 35 and the air jet 36 as the number of pairs of the fuel nozzle 31 and the air holes 32 can be formed.

  In the air hole 32 provided in the air hole plate 33, the coaxial jet by the fuel jet 35 and the air jet 36 surrounding the outer peripheral side flows down. Therefore, the fuel concentration in the vicinity of the wall surface in the air hole 32 becomes substantially zero, and the potential for burnout due to flashback can be reduced.

  Further, by forming a large number of small coaxial jets of the fuel jet 35 and the air jet 36, the interface between the fuel and the air increases. Therefore, an air-fuel mixture in which mixing of the fuel jet 35 and the air jet 36 is promoted is formed on the outlet side of the air hole 32. By burning this air-fuel mixture in the combustion chamber 50 of the gas turbine combustor 2, the flame temperature can be made uniform and the amount of NOx generated can be suppressed.

  Further, the burner 6 is provided with two fuel systems of F1 fuel 201 and F2 fuel 202. Each fuel system includes fuel flow rate adjustment valves 211 and 212. The flow rate of the F1 fuel 201 is adjusted by the fuel flow rate adjustment valve 211, and the flow rate of the F2 fuel 202 is adjusted by the fuel flow rate adjustment valve 212. Then, the power generation amount of the gas turbine plant 1000 is controlled.

  FIG. 1 is a schematic cross-sectional view enlarging a peripheral portion of a fuel nozzle 31 and an air hole 32 in the gas turbine plant of FIG. FIG. 3A is a front view of the air hole plate 33 as viewed from the combustion chamber 50.

  In this embodiment, the air holes 32 are concentrically arranged in three rows, and six, twelve, and eighteen air holes 32 are provided from the inner peripheral side of the burner. Each air hole row is defined as a first row of air holes 32a, a second row of air holes 32b, and a third row of air holes 32c from the inner peripheral side.

  Further, in order to form a swirling flow in the combustion chamber 50, the first row of air holes 32a is disposed so as to be inclined by θ with respect to the burner axial direction (the central axis of the fuel nozzle). FIG. 3B shows a view in which the first row of air holes 32a are cut in the circumferential direction of the burner.

  Further, the fuel system of the present embodiment is divided into two systems: a system that supplies F1 fuel 201 and a system that supplies F2 fuel 202. Here, the F1 fuel 201 is supplied to the fuel nozzle 31a (first fuel nozzle group) corresponding to the first row of air holes 32a, and the F2 fuel 202 is supplied to the second row of air holes 32b and the third row of air holes. The fuel nozzles 31b and 31c (second fuel nozzle group) corresponding to 32c are supplied.

  In the present embodiment, the first row of air holes 32a supplied with the F1 fuel 201 has the inner peripheral burner 51, and the second row of air holes 32b and the third row of air holes 32c supplied with the F2 fuel 202 have the outer peripheral burner. 52. And the part enclosed by the dashed-dotted line of FIG.

  The combustion chamber side wall surface of the air hole plate 33 is a surface on which the air hole outlets are distributed. In the combustion chamber side wall surface, the inner peripheral side wall surface is located on the downstream side of the combustion chamber from the outer peripheral side wall surface. Therefore, the outlets in the first row of air holes 32a located on the inner peripheral side wall surface are located on the downstream side of the combustion chamber as compared with the outlets in the third row of air holes 32c located on the outer peripheral side wall surface. In addition, the connecting part wall surface connecting the inner peripheral wall surface and the outer peripheral side wall surface has the connecting part wall surface at the central axis so that the radial distance from the central axis of the air hole plate decreases on the downstream side compared to the upstream side of the combustion chamber. Inclines against. Therefore, the connection portion wall surface of the air hole plate has a truncated cone shape.

  With such an air hole plate shape, the outer peripheral burner 52 is disposed upstream of the inner peripheral burner 51 in the burner axial direction.

  FIG. 4 shows a schematic shape of a flame and a fluid flow obtained by using the burner of this embodiment.

  The combustion chamber side wall surface of the air hole plate 33 constituting the inner peripheral burner 51 is perpendicular to the burner axis (that is, the central axis of the air hole plate). Therefore, the stagnation regions 42a and 42b are formed in a region near the outlet of the first row of air holes 32a.

  In the vicinity of the stagnation regions 42a and 42b, the flow is stagnated and the flow velocity becomes slow, and there is a portion where the combustion speed and the flow velocity are locally balanced. A flame 41 is formed with a portion where the combustion speed and the flow velocity are balanced as a base point. Furthermore, the air holes 32a in the first row are arranged to be inclined with respect to the burner shaft (the central axis of the air hole plate), and thus a circulation flow 40 is generated. By this circulating flow 40, high-temperature combustion gas is transported from the downstream to the upstream of the flame 41, and thermal energy is transported from the downstream to the upstream. Therefore, the unburned air-fuel mixture supplied from the air holes 32 to the combustion chamber is heated to increase the reactivity, and the combustion stability can be improved. From the above, the inner peripheral burner 51 can be a burner with high combustion stability.

  On the other hand, the outer peripheral burner 52 includes a connecting portion 43 that connects the inner peripheral side wall surface and the outer peripheral side wall surface. The connecting portion wall surface is inclined such that the radial distance of the connecting portion wall surface from the central axis of the air hole plate decreases on the downstream side as compared with the upstream side of the combustion chamber. The connecting portion wall surface between the outlet of the second row of air holes 32b and the outlet of the third row of air holes 32c is inclined with respect to the burner axis, so that it is difficult to stagnate. Therefore, no flame is formed in the vicinity of the air hole plate 33 constituting the outer peripheral burner 52. Therefore, as shown in FIG. 4, a flame 41 using the inner peripheral burner 51 as a fire type is formed. In addition, the radial distance from the central axis of the air hole plate of the connection part wall surface is such that the connection part wall surface is inclined so as to decrease the downstream side compared to the upstream side of the combustion chamber. Prevents itching.

  As in this embodiment, the coaxial jet flowing through the internal flow path of the air hole 32 rapidly expands from the internal flow path to the combustion chamber space, so that fuel and air are rapidly mixed. Further, even after the fuel and air flow into the combustion chamber, the mixing of the fuel and air further proceeds.

  When the mixing of fuel and air sufficiently proceeds, the local combustion temperature is made uniform, which is effective for reducing NOx. That is, in the burner composed of a large number of coaxial jets of fuel and air as in this embodiment, the fuel is burned at a position where the mixing of the fuel and air has sufficiently progressed, that is, away from the outlet of the air hole 32. It is preferable to form the flame 41 at a different position.

  In the present embodiment, as shown in FIG. 4, the flame 41 is stably formed with an inner peripheral burner 51 that is a burner having high combustion stability as a base point. Therefore, in the combustion chamber side wall surface of the air hole plate, the inner peripheral side wall surface is formed on the downstream side of the combustion chamber from the outer peripheral side wall surface, so that the outlet of the second row of air holes 32b provided in the outer peripheral burner 52 and the third row. A flame 41 is formed away from the outlet of the air hole 32c. That is, the mixing of the fuel and the air proceeds not only at the effect of sudden expansion at the outlet of the air hole 32 but also between reaching the flame 41 from the outlet of the air hole 32. Therefore, in the outer peripheral burner 52, the flame temperature is made uniform and low NOx combustion is realized.

  Thus, by providing the inner peripheral burner and the outer peripheral burner of the present embodiment, it is possible to provide a structure that achieves both low NOx and combustion stability.

  In the present embodiment, the connecting portion wall surface connecting the inner peripheral side wall surface and the outer peripheral side wall surface is tapered. However, this can also be realized by connecting the inner peripheral burner 51 and the outer peripheral burner 52 with a curved line as shown in FIG.

  Further, in this embodiment, two fuel systems, that is, an F1 fuel 201 supplied to the inner peripheral burner 51 and an F2 fuel 202 supplied to the outer peripheral burner 52 are provided.

  Here, increasing the ratio of the fuel flow rate to the air flow rate is an effective method for improving the combustion stability. That is, by increasing the fuel flow rate of the F1 fuel 201 as compared with the fuel flow rate of the F2 fuel 202, the ratio of the fuel flow rate to the air flow rate in the inner burner 51 increases, and the flame temperature rises. Therefore, the combustion stability of the inner peripheral burner 51 can be improved.

  However, merely increasing the flow rate of the F1 fuel 201 ejected from the inner peripheral burner 51 changes the flow rate of the fuel 200 supplied to the entire burner 6, and thus the obtained output also changes. Therefore, the flow rate ratio of the F1 fuel 201 is increased and simultaneously the flow rate ratio of the F2 fuel 202 is decreased. Therefore, the ratio of the fuel flow rate to the air flow rate in the inner peripheral burner 51 is increased without increasing the fuel flow rate of the fuel 200 supplied to the entire burner 6.

  Since the flow rate of the fuel 200 supplied to the entire burner 6 is not changed in this way, the output obtained is not changed. Therefore, the combustion stability of the inner peripheral burner 51 can be improved, and an increase in the NOx emission amount discharged from the entire burner 6 can be suppressed.

  FIG. 6 shows a modification in which the width of the connecting portion wall surface connecting the inner peripheral wall surface and the outer peripheral wall surface of the air hole plate is widened. Specifically, the inner peripheral burner 51 has a structure that is tapered from the outermost peripheral position (position A in the drawing) of the air hole 32a to the outer peripheral direction.

  Here, FIG. 7 is a front view of FIG. 6 viewed from the combustion chamber 50 side.

  FIG. 8 shows a schematic shape of a flame and a fluid flow obtained by using the burner of FIG. In FIG. 8, the position where the flow velocity and the combustion speed are balanced is formed in the stagnation region 42, that is, the inner region of the first row of air holes 32 a. Therefore, the flame 41 is formed as shown in FIG.

  Next, the gas turbine combustor of Example 2 will be described with reference to FIG.

  The configuration of the gas turbine combustor according to the present embodiment is the same as the configuration of the gas turbine combustor according to the first embodiment. Therefore, the description of the configuration common to both is omitted and only the configuration that is different is omitted. This will be described below.

  FIG. 9 is an enlarged schematic cross-sectional view of the peripheral portion of the fuel nozzle 31 and the air hole 32, and FIG. 10 is a front view of the air hole plate 33 viewed from the combustion chamber 50.

  In this embodiment, the thickness of the air hole plate 33 is substantially the same in the radial direction. That is, the combustion chamber side wall surface of the air hole plate and the fuel nozzle side wall surface are parallel.

  In the present embodiment, since the thickness of the air hole plate 33 is substantially the same in the radial direction, the internal flow path lengths of all the air holes are also the same. Therefore, the pressure loss generated when the air jet 36 passes through the air hole 32 can be made constant regardless of the position of the air hole 32.

  Further, in order to make all the distances from the ejection holes of the fuel nozzles 31 to the inlets of the air holes 32 the same as the lengths of the fuel nozzles 31 in the third row, the fuel nozzles 31 in the first row and the second row. The length of the. Thereby, the pressure loss generated when the air jet 36 flows into the air hole 32 can be made constant regardless of the position of the air hole 32.

  In this way, the pressure loss generated when the air jet 36 passes through the air hole 32 and when the air jet 36 flows into the air hole 32 is made constant regardless of the position of the air hole 32. The pressure difference between the upstream side and the downstream side of the air hole plate 33 is constant regardless of the position of the air hole 32.

  By doing so, it is possible to prevent a deviation in the flow rate of the air jet 36 depending on the position of the air hole 32 in the air hole plate 33.

  Therefore, since the ratio of the air flow rate to the fuel flow rate can be made constant regardless of the position of the air hole 32 in the air hole plate 33, an unintended local increase in the flame temperature can be prevented and low NOx combustion can be achieved. can do.

  Thus, sufficient combustion stability is secured in the inner burner 51 and low NOx combustion is realized in the outer burner 52, so that both combustion stability and low NOx combustion can be achieved.

  Next, the gas turbine combustor of Example 3 will be described with reference to FIG.

  The configuration of the gas turbine combustor according to the present embodiment is the same as the configuration of the gas turbine combustor according to the first embodiment. Therefore, the description of the configuration common to both is omitted and only the configuration that is different is omitted. This will be described below.

  FIG. 11 is an enlarged schematic cross-sectional view of the peripheral portion of the fuel nozzle 31 and the air hole 32, and FIG. 12 is a front view of the air hole plate 33 viewed from the combustion chamber 50.

  In the present embodiment, the configuration of the inner peripheral burner 51 is the same as that of the first embodiment. However, the air hole diameters of the air holes 32 b and 32 c provided in the outer peripheral burner 52 differ depending on the arrangement positions on the air hole plate 33. That is, among the air holes arranged in the outer peripheral burner 52, the third row of air holes 32c has a larger hole diameter when the distance between the second row of air holes 32b is larger and the smaller one has a hole diameter. Reduce.

  This will be specifically described with reference to FIG.

  First, attention is paid to the air holes 32 c-1 that are part of the air holes 32 c in the third row among the air holes 32 arranged in the outer peripheral burner 52. The positions of the air holes 32c-1 in the circumferential direction are provided between the air holes 32b in the second row adjacent to the air holes 32c-1 and arranged in the circumferential direction. That is, since the third row of air holes 32c-1 and the second row of air holes 32b are farthest apart, the diameter of the holes is increased as shown.

  On the other hand, attention is paid to a portion of the air hole 32c-2 in the third row that is different from the air hole 32c-1. Here, since the air holes 32c-2 are close to the air holes 32b in the second row, the diameter of the air holes 32c-2 is reduced as illustrated.

  As described above, the air holes 32c are arranged on the inner side of the air holes 32c in the third row, and the diameter of the air holes 32c is enlarged or reduced according to the distance between the air holes 32b in the adjacent second row. Accordingly, the remaining amount of the air hole plate 33 between the third row of air holes 32 c and the second row of air holes 32 b is made substantially equal on the air hole plate 33.

  On the side wall surface of the combustion chamber of the air hole plate 33, the regions 43a and 43b where the air holes 32 are not provided are made small to prevent the flow from stagnating. By eliminating the place where the flow stagnates in this way, a point where the combustion speed and the flow velocity balance in the vicinity of the regions 43a and 43b is not generated, and the flame 41 becomes difficult to form in the vicinity of the regions 43a and 43b.

  On the other hand, as in the first embodiment, a stable flame 41 is formed in the inner peripheral burner 51 with the position where the flow velocity is balanced with the combustion speed in the vicinity of the stagnation 42.

  Therefore, the flame 41 is formed in the outer peripheral burner 52 at a position separated from the outlets of the air holes 32b and 32c. Therefore, since the flame 41 is formed at a position where the fuel and air are sufficiently mixed, the flame temperature is made uniform, and the outer burner 52 achieves low NOx combustion.

  Thus, sufficient combustion stability is secured in the inner burner 51 and low NOx combustion is realized in the outer burner 52, so that both combustion stability and low NOx combustion can be achieved.

  Next, the gas turbine combustor of Example 4 will be described with reference to FIG.

  The configuration of the gas turbine combustor according to the present embodiment is the same as the configuration of the gas turbine combustor according to the first embodiment. Therefore, the description of the configuration common to both is omitted and only the configuration that is different is omitted. This will be described below.

  In the present embodiment, seven burners 6 shown in the first embodiment are combined to constitute one combustion device.

  FIG. 13 is an enlarged schematic cross-sectional view of the peripheral portion of the fuel nozzle 31 and the air hole 32, and FIG. 14 is a front view of the air hole plate 33 viewed from the combustion chamber 50.

  As shown in FIG. 13, one burner is disposed at the center, and six burners are disposed on the outer peripheral side of the burner. Two fuel systems are connected to each burner 6. Further, all the burners 6 employ the burner structure shown in FIG.

  As shown in FIG. 13, by dividing the fuel system into an inner peripheral burner 51 and an outer peripheral burner 52 of each burner 6, the number of burners to be burned can be controlled according to the gas turbine load. Therefore, it is possible to stably burn by changing the flow rates of the F1 fuel 201 and the F2 fuel 202 of each burner from the start condition of the gas turbine to the 100% load condition.

  Moreover, it can also be set as one combustion apparatus combining the structure of the burner 6 shown in Examples 1-3.

  Thus, the configuration of this embodiment can achieve both combustion stability and low NOx combustion.

  The present invention can be applied not only to a gas turbine combustor for power generation, but also to a cogeneration system capable of supplying both heat and power, or a gas turbine combustor as a mechanical drive engine such as a pump / compressor.

It is a partial structure figure which shows the detail of the arrangement condition of the fuel nozzle header which comprises the fuel supply part of the gas turbine combustor in Example 1, a fuel nozzle, and an air hole plate. 1 is a plant system diagram showing a schematic configuration of a gas turbine plant to which a gas turbine combustor of Example 1 is applied. It is the front view which looked at the air hole plate of Example 1 shown in FIG. 1 from the combustion chamber side. It is the figure which showed the flow state of the fuel flow and air flow in a combustion chamber in arrangement | positioning of the fuel nozzle header which comprises the fuel supply part of the gas turbine combustor in Example 1, a fuel nozzle, and an air hole plate. It is a partial structure figure (modification) which shows the details of arrangement conditions of a fuel nozzle header which constitutes a fuel supply part of a gas turbine combustor in Example 1, a fuel nozzle, and an air hole plate. It is a partial structure figure (modification) which shows the details of arrangement conditions of a fuel nozzle header which constitutes a fuel supply part of a gas turbine combustor in Example 1, a fuel nozzle, and an air hole plate. It is the front view (modified example) which looked at the air hole plate of Example 1 shown in FIG. 6 from the combustion chamber side. The figure (modification) which showed the flow state of the fuel flow and air flow in a combustion chamber in arrangement of a fuel nozzle header which constitutes a fuel supply part of a gas turbine combustor which is Example 1, a fuel nozzle, and an air hole plate is there. It is a partial structure figure which shows the detail of the arrangement condition of the fuel nozzle header which comprises the fuel supply part of the gas turbine combustor which is Example 2, a fuel nozzle, and an air hole plate. It is the front view which looked at the air hole plate of Example 2 shown in FIG. 9 from the combustion chamber side. It is a partial structure figure which shows the detail of the arrangement | positioning condition of the fuel nozzle header which comprises the fuel supply part of the gas turbine combustor which is Example 3, a fuel nozzle, and an air hole plate. It is the front view which looked at the air hole plate of Example 3 shown in FIG. 11 from the combustion chamber side. It is a partial structure figure which shows the detail of the arrangement condition of the fuel nozzle header which comprises the fuel supply part of the gas turbine combustor which is Example 4, a fuel nozzle, and an air hole plate. It is the front view which looked at the air hole plate of Example 4 shown in FIG. 13 from the combustion chamber side. It is the figure which expanded the A section and B section of FIG.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Compressor 2 Gas turbine combustor 3 Turbine 4 Casing 6 Burner 10 Combustor liner 11 Flow sleeve 12 Cylinder inner cylinder 13 Cylinder outer cylinder 20 Generator 21 Shaft 30 Fuel nozzle header 31 Fuel nozzle 32 Air hole 33 Air hole plate 35 Fuel jet 36 Air jet 40 Circulating flow 41 Flame 42 Stagnation 43 Connection portions 43a and 43b Region 50 Combustion chamber 51 Inner peripheral burner 52 Outer peripheral burner 100 Suction air 101 High-pressure air 102 High-temperature combustion gas 200 Fuel 201 F1 fuel 202 F2 fuel 211, 212 Fuel Flow Control Valve 1000 Gas Turbine Plant

Claims (4)

A combustion chamber supplied with fuel and air;
An air hole plate located on the upstream side wall surface of the combustion chamber and having a plurality of air holes;
A gas turbine combustor comprising a fuel nozzle disposed upstream of each air hole,
The combustion chamber side wall surface of the air hole plate has an inner peripheral side wall surface located on the downstream side of the combustion chamber from the outer peripheral side wall surface,
The connection wall surface is connected to the center wall so that the radial distance from the central axis of the air hole plate of the connection wall surface connecting the inner peripheral wall surface and the outer peripheral wall surface is reduced on the downstream side compared to the combustion chamber upstream side. A gas turbine combustor which is inclined with respect to an axis. A combustion chamber supplied with fuel and air;
An air hole plate located on the upstream side wall surface of the combustion chamber and having a plurality of air holes;
A first fuel nozzle group disposed on the upstream side of each air hole and provided on the center axis side of the air hole plate, and a second fuel nozzle located on the outer peripheral side of the first fuel nozzle group Group,
A gas turbine combustor comprising two fuel systems for supplying fuel to the fuel nozzle group,
The combustion chamber side wall surface of the air hole plate has an inner peripheral side wall surface located on the downstream side of the combustion chamber from the outer peripheral side wall surface,
The connection wall surface is connected to the center wall so that the radial distance from the central axis of the air hole plate of the connection wall surface connecting the inner peripheral wall surface and the outer peripheral wall surface is reduced on the downstream side compared to the combustion chamber upstream side. Having a structure inclined with respect to the axis;
The gas turbine combustor, wherein a fuel flow rate supplied from the first fuel nozzle group is larger than a fuel flow rate supplied from the second fuel nozzle group.   3. The gas turbine combustor according to claim 1, wherein the air holes arranged in the air hole plate are inclined with respect to a central axis of the air hole plate. A gas turbine combustor according to claim 1 or 2,
A gas turbine combustor, wherein the thickness of the air hole plate is constant in the radial direction.

Images