Multi-can combustor gas turbine and method for retrofitting multi-can combustor gas turbine

Abstract

To reduce harmful components contained in combustion gas.SOLUTION: A multi-can combustor gas turbine 1 comprises: a compressor 2 that houses an impeller; a turbine 3 that houses a turbine wheel; a shaft that connects the impeller and the turbine wheel; a coupling part 5 that houses the shaft and is provided between the compressor and the turbine; a plurality of connection parts 5b that is provided at the coupling part and arranged in a rotational direction of the shaft; and a plurality of combustors 100 including one or more first combustors 100a that are connected to the connection part and have a combustion chamber formed therein, and one or more second combustors 100b that are connected to the connection part and have a combustion chamber formed therein that has a larger volume than the first combustor.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present disclosure relates to a multi-can combustor gas turbine and a method for retrofitting the same.

Background Art

[0002] Conventionally, as shown in Patent Documents 1 and 2, for example, a multi-can combustor gas turbine including a compressor and a turbine is known. In the multi-can combustor gas turbine, a plurality of combustors are provided between the compressor and the turbine. Power is generated by combustion of fuel in each combustor.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Patent Document 2

Summary of the Invention

Problems to be Solved by the Invention

[0004] In recent years, in order to reduce carbon dioxide emissions, it has been considered to use a low-calorie fuel such as ammonia instead of a hydrocarbon-based fuel. However, since ammonia is a difficult-to-burn fuel, when ammonia is used as a fuel in a conventional multi-can combustor gas turbine, combustion becomes insufficient and there is a risk of discharging harmful components such as NOx.

[0005] An object of the present disclosure is to provide a multi-can combustor gas turbine capable of reducing harmful components contained in combustion gas and a method for retrofitting the same.

Means for Solving the Problems

[0006] To solve the above problems, the multi-can combustor gas turbine of the present disclosure includes a compressor that houses an impeller, A turbine that houses a turbine impeller, A shaft that connects the impeller and the turbine impeller, A connecting portion that houses the shaft and is provided between the compressor and the turbine, A plurality of connecting portions provided in the connecting portion and arranged in the rotational direction of the shaft, One or more first combustors connected to the connecting portion and having a combustion chamber formed therein, and a plurality of combustors including one or more second combustors connected to the connecting portion and having a combustion chamber formed therein with a larger volume than the first combustor, Comprising.

[0007] The combustor is A burner is provided at one end, and the other end is connected to the connecting portion, The combustion chamber is Including a primary region located on the burner side and a secondary region located on the connecting portion side rather than the primary region, The shapes and sizes of the secondary regions of the first combustor and the second combustor may be substantially the same.

[0008] A multi-can combustor gas turbine is A flame transfer pipe connecting the primary regions of at least two of the combustors, May further include.

[0009] In order to solve the above problems, a method for modifying a multi-can combustor gas turbine according to the present disclosure is A method for modifying a multi-can combustor gas turbine including a compressor that houses an impeller, a turbine that houses a turbine impeller, a shaft that connects the impeller and the turbine impeller, a connecting portion that houses the shaft and is provided between the compressor and the turbine, and a plurality of connecting portions provided in the connecting portion and arranged in the rotational direction of the shaft, Connecting one or more first combustors having a combustion chamber formed therein to the connecting portion, Connecting one or more second combustors having a combustion chamber formed therein with a larger volume than the first combustor to the connecting portion, includes

Advantages of the Invention

[0010] According to the present disclosure, harmful components contained in combustion gas can be reduced.

Brief Description of the Drawings

[0011]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Modes for Carrying Out the Invention

[0012] Embodiments of the present disclosure will be described below with reference to the accompanying drawings. The dimensions, materials, and other specific numerical values shown in the embodiments are merely examples for ease of understanding and do not limit the present disclosure unless otherwise specified. In the present specification and drawings, elements having substantially the same function and configuration are denoted by the same reference numerals, and redundant description is omitted, and elements not directly related to the present disclosure are not shown.

[0013] FIG. 1 is a view showing the appearance of a multi-can combustor gas turbine 1 according to an embodiment. FIG. 2 is a schematic view simply showing the configuration of the multi-can combustor gas turbine 1 according to the embodiment. As shown in FIGS. 1 and 2, the multi-can combustor gas turbine 1 has a compressor 2 and a turbine 3. An impeller 2a is accommodated in the compressor 2. A turbine wheel 3a is accommodated in the turbine 3. Further, the multi-can combustor gas turbine 1 includes a shaft 4 that connects the impeller 2a and the turbine wheel 3a. The impeller 2a and the turbine wheel 3a rotate integrally via the shaft 4.

[0014] The compressor 2 and the turbine 3 are spaced apart from each other in the rotational axis direction of the shaft 4. A connecting portion 5 is provided between the compressor 2 and the turbine 3. The shaft 4 is accommodated in the connecting portion 5. That is, the multi-can combustor gas turbine 1 includes a connecting portion 5 in which the shaft 4 is accommodated and which is provided between the compressor 2 and the turbine 3. An attachment surface 5a is provided on the connecting portion 5. The attachment surface 5a faces the compressor 2 side, is on the radially outer side of the shaft 4 than the compressor 2, and extends over the entire circumference of the compressor 2. The attachment surface 5a has a tapered shape that inclines so as to be located on the radially outer side of the shaft 4 as it goes from the compressor 2 side toward the turbine 3 side. Note that the attachment surface 5a may face the turbine 3 side. Further, the attachment surface 5a is not limited to the tapered shape, and may extend, for example, in a direction orthogonal to the rotational axis direction of the shaft 4.

[0015] A plurality of connection portions 5b to which a combustor 100 described later is connected are provided on the attachment surface 5a. The connection portion 5b may be constituted by a hole or a groove to which the combustor 100 is connected. Alternatively, the connection portion 5b may be formed in a protruding shape protruding from the attachment surface 5a. In any case, the connection portion 5b only needs to be connected to the combustor 100, and its shape and number are not limited. The plurality of connection portions 5b are arranged in the rotational direction of the shaft 4. Here, the plurality of connection portions 5b are arranged at equal intervals in the rotational direction of the shaft 4. However, the intervals between two adjacent connection portions 5b may be partially different.

[0016] In addition, the multi-can combustor gas turbine 1 includes an intake air flow path 6 indicated by a dashed arrow in FIG. 2. The intake air flow path 6 is provided from the compressor 2 across the inside of the connecting portion 5. It can also be said that the compressor 2 is provided in the intake air flow path 6. Air supplied to the combustor 100 flows through the intake air flow path 6. The compressor 2 is provided with an intake port 2b through which air is taken in from the outside. The intake port 2b is the upstream end of the intake air flow path 6. The air taken in from the intake port 2b passes through the compressor 2 and the connecting portion 5 and is sent to the combustor 100. The compressor 2 compresses the air by the rotation of the impeller 2a and discharges it to the combustor 100.

[0017] In addition, the multi-can combustor gas turbine 1 includes an exhaust gas flow path 7 indicated by a chain line arrow in FIG. 2. The exhaust gas flow path 7 is provided from the turbine 3 across the inside of the connecting portion 5. It can also be said that the turbine 3 is provided in the exhaust gas flow path 7. Combustion gas discharged from the combustor 100 flows through the exhaust gas flow path 7. The turbine 3 is provided with an exhaust port 3b through which the combustion gas is discharged to the outside. The exhaust port 3b is the downstream end of the exhaust gas flow path 7. The combustion gas discharged from the combustor 100 passes through the turbine 3 and is sent to the exhaust port 3b. The turbine 3 generates rotational power as the turbine impeller 3a is rotated by the combustion gas in the process of flowing through the exhaust gas flow path 7. This rotational power is transmitted to the impeller 2a via the shaft 4, and the rotation of the impeller 2a compresses the air in the compressor 2.

[0018] In this embodiment, the above multi-can combustor gas turbine 1 is applied to the gas turbine system GS. Here, the outline of the gas turbine system GS will be described, and then the combustor 100 provided in the multi-can combustor gas turbine 1 will be described.

[0019] FIG. 3 is a schematic diagram showing the configuration of the gas turbine system GS according to the embodiment. As shown in FIG. 3, the gas turbine system GS includes a multi-can combustor gas turbine 1, a generator 20, a burner 30, an ammonia tank 40, and a flow control valve 50.

[0020] The generator 20 is connected to the multi-can combustor gas turbine 1. The generator 20 generates electricity using the rotational power generated by the multi-can combustor gas turbine 1.

[0021] The burner 30 injects ammonia as fuel into the interior of the combustor 100. The burner 30 has a substantially cylindrical shape. The burner 30 is attached to a casing 101, which will be described later, of the combustor 100. The tip of the burner 30 is located inside the casing 101, and the rear end of the burner 30 is located outside the casing 101. The burner 30 can be a component of the combustor 100. Also, the burner 30 can be a component of the multi-can combustor gas turbine 1.

[0022] An injection valve (not shown) is provided at the tip of the burner 30. An ammonia tank 40 is connected to the rear end of the burner 30. Liquid ammonia is stored in the ammonia tank 40. A flow rate control valve 50 is provided in the flow path connecting the ammonia tank 40 and the burner 30. The ammonia stored in the ammonia tank 40 is supplied to the burner 30. The flow rate control valve 50 controls the flow rate of the ammonia supplied from the ammonia tank 40 to the burner 30. Note that various devices (for example, a shut-off valve, a check valve, various sensors, etc.), which are not shown in FIG. 1, may be provided in the flow path connecting the ammonia tank 40 and the burner 30.

[0023] The combustor 100 of the multi-can combustor gas turbine 1 includes a casing 101. The casing 101 is configured in a substantially bottomed cylindrical shape having a bottom surface 101a and an outer wall portion 101b. A connected portion 101c is provided at an end of the outer wall portion 101b opposite to the bottom surface 101a. The connected portion 101c is connected to a connection portion 5b provided on the attachment surface 5a of the connecting portion 5. Note that the connected portion 101c is connected to the connection portion 5b by a fixing member such as a bolt or by welding or the like. An opening 101d connected to the intake air passage 6 in the connecting portion 5 is formed in the connected portion 101c. Further, a burner 30 is inserted through the bottom surface 101a of the casing 101. The burner 30 is located substantially at the center of the bottom surface 101a. In other words, the burner 30 is provided on the central axis of the casing 101. Thus, the combustor 100 has a burner 30 provided at one end and the other end is connected to the connection portion 5b of the connecting portion 5.

[0024] A liner 110 is housed inside the casing 101. The liner 110 is configured in a substantially bottomed cylindrical shape having a bottom portion 110a and a side wall portion 110b. The central axis of the liner 110 substantially coincides with the central axis of the casing 101. Therefore, the central axis of the liner 110 coincides with the central axis of the burner 30. Hereinafter, the central axis of the liner 110 may be simply referred to as the "central axis" or "center". Also, the direction orthogonal to the central axis, that is, the radial direction of the liner 110 is simply referred to as the "radial direction".

[0025] The outer diameter of the liner 110 is smaller than the inner diameter of the casing 101. Thereby, an annular space is formed between the liner 110 and the casing 101. Also, the bottom portion 110a of the liner 110 is spaced apart from the bottom surface 101a of the casing 101 in the central axis direction. Therefore, a gap is formed between the bottom surface 101a of the casing 101 and the bottom portion 110a of the liner 110.

[0026] At the bottom 110a of the liner 110, a burner insertion hole 110c is formed. The tip of the burner 30 is inserted into the burner insertion hole 110c. The inner diameter of the burner insertion hole 110c is larger than the outer diameter of the burner 30. Thereby, an annular air introduction part 111 penetrating the bottom 110a in the central axis direction is formed at the bottom 110a of the liner 110. That is, the air introduction part 111 is provided in the vicinity of the burner 30, more precisely, around the burner 30.

[0027] Further, the liner 110 includes a large-diameter part 112, a reduced-diameter part 113, and a small-diameter part 114. The large-diameter part 112 is located closer to the burner 30 than the reduced-diameter part 113 and the small-diameter part 114. Also, the small-diameter part 114 is located axially separated from the burner 30 more than the large-diameter part 112 and the reduced-diameter part 113. The inner diameter of the small-diameter part 114 is smaller than the inner diameter of the large-diameter part 112. The reduced-diameter part 113 connects the large-diameter part 112 and the small-diameter part 114. The reduced-diameter part 113 has a smaller diameter as it goes from the large-diameter part 112 toward the small-diameter part 114. That is, the reduced-diameter part 113 has a tapered shape. However, the reduced-diameter part 113 may extend in the radial direction. An opening 114a connected to the exhaust passage 7 in the connection part 5 is formed at the end of the small-diameter part 114 located on the side opposite to the reduced-diameter part 113.

[0028] Here, the inner diameter of the large-diameter part 112 is substantially constant regardless of the position in the central axis direction. However, the inner diameter of the large-diameter part 112 may vary depending on the position in the central axis direction. For example, the large-diameter part 112 may have a tapered shape in which the diameter increases or decreases as it is separated from the burner 30. Similarly, the inner diameter of the small-diameter part 114 may vary depending on the position in the central axis direction. For example, the small-diameter part 114 may have a tapered shape in which the diameter increases or decreases as it is separated from the burner 30.

[0029] Furthermore, the entire liner 110 may have a tapered shape in which the diameter gradually decreases as it moves away from the burner 30 side. In this case, a certain range on the burner 30 side of the liner 110 becomes the large-diameter portion 112, and a certain range on the side away from the burner 30 becomes the small-diameter portion 114. Furthermore, the diameter of the liner 110 may be constant from the bottom 110a to the opening 114a. In any case, the shape of the liner 110 is not limited to the example in FIG. 1.

[0030] Inside the side wall portion 110b, that is, inside the liner 110, a combustion chamber 115 is formed. The air introduction portion 111 communicates the space formed between the bottom 110a of the liner 110 and the bottom surface 101a of the casing 101 with the combustion chamber 115. The air introduction portion 111 introduces air into the combustion chamber 115.

[0031] Here, the air introduction portion 111 that introduces air into the combustion chamber 115 is provided in the vicinity of the burner 30. That is, the air introduction portion 111 is provided separately from the burner 30. However, the air introduction portion 111 may be provided in the burner 30. In this case, for example, the air introduction portion 111 formed inside the burner 30 may open into the space formed between the bottom 110a of the liner 110 and the bottom surface 101a of the casing 101. Even in this case, the air introduced into the air introduction portion 111 is injected into the combustion chamber 115 via the burner 30. At this time, the air may be injected separately from the fuel, or may be mixed with the fuel in the burner 30 and injected as a mixture.

[0032] In addition, the liner 110 is provided with through holes 116 that penetrate the inside and outside of the side wall portion 110b. The through holes 116 penetrate the liner 110 in the radial direction. Here, a plurality of through holes 116 are provided in the liner 110. The plurality of through holes 116 are, for example, equally positioned in the central axis direction of the liner 110 and are arranged at intervals in the circumferential direction. However, only one through hole 116 may be provided in the liner 110. Also, when a plurality of through holes 116 are provided, the plurality of through holes 116 may have different positions in the central axis direction.

[0033] Here, the through-hole 116 is provided in the large-diameter portion 112. Further, the through-hole 116 is provided at a position separated from the burner 30 rather than at the central position in the central axis direction of the large-diameter portion 112. However, the through-hole 116 may be provided in the reduced-diameter portion 113 or the small-diameter portion 114. The through-hole 116 functions as a second air introduction portion for introducing air from the outside of the liner 110 into the combustion chamber 115. Hereinafter, the air introduced into the combustion chamber 115 from the through-hole 116 is referred to as dilution air.

[0034] Further, as shown by the dashed-line enclosure in FIG. 3, the combustion chamber 115 includes a primary region 115a located on the burner 30 side of the through-hole 116 and a secondary region 115b located on the connection portion 5b side of the connection portion 5, that is, on the opening 101d and opening 114a sides, rather than the primary region 115a. Here, the secondary region 115b is defined as a range axially separated from the burner 30 from the through-hole 116 (the end portion on the burner 30 side).

[0035] Further, the liner 110 is provided with a second through-hole 117 that penetrates the inside and outside of the side wall portion 110b. The second through-hole 117 penetrates the liner 110 in the radial direction. The second through-hole 117 is located on the opening 114a side of the through-hole 116. However, the second through-hole 117 may be located on the burner 30 side of the through-hole 116. Here, the second through-hole 117 is smaller than the through-hole 116. However, the size of the second through-hole 117 may be the same as that of the through-hole 116 or larger than the through-hole 116. Here, a plurality of second through-holes 117 are provided in the liner 110. The plurality of second through-holes 117 are, for example, equally positioned in the central axis direction of the liner 110 and are arranged at intervals in the circumferential direction. However, only one second through-hole 117 may be provided in the liner 110. Further, when a plurality of second through-holes 117 are provided, the plurality of second through-holes 117 may have different positions in the central axis direction.

[0036] Inside the liner 110, an annular guide member 118 is provided. The guide member 118 includes a guide surface 118a extending in the circumferential direction and a flange portion 118b extending radially outward from the guide surface 118a. The guide member 118 is provided radially inside the second through hole 117, and the second through hole 117 faces the guide surface 118a. A slight gap is formed between the guide surface 118a and the second through hole 117. Further, the flange portion 118b is provided at the end of the guide surface 118a on the burner 30 side. The radially outer side of the flange portion 118b is connected to the inner peripheral surface of the side wall portion 110b. Thereby, the space formed between the second through hole 117 and the guide surface 118a is sealed on the burner 30 side and opened on the opening 114a side.

[0037] Further, the combustor 100 includes a flow path forming member 120. The flow path forming member 120 is provided between the side wall portion 110b and the outer wall portion 101b. The flow path forming member 120 includes a partition wall portion 120a that is radially outside the side wall portion 110b and radially inside the outer wall portion 101b. The partition wall portion 120a is radially spaced from both the side wall portion 110b and the outer wall portion 101b. The partition wall portion 120a has an annular shape substantially parallel to the central axis direction and faces the outer wall portion 101b and the side wall portion 110b substantially in parallel. However, the partition wall portion 120a may have a tapered shape inclined with respect to the central axis. Alternatively, the diameter of the partition wall portion 120a may vary depending on the position in the central axis direction.

[0038] Further, the flow path forming member 120 includes a first end portion 120b and a second end portion 120c. The first end portion 120b is provided at the end of the partition wall portion 120a on the burner 30 side and extends radially outward from the partition wall portion 120a. The radially outer side of the first end portion 120b is connected to the outer wall portion 101b. The second end portion 120c is provided at the end of the partition wall portion 120a on the opening 114a side and extends radially inward from the partition wall portion 120a. The radially inner side of the second end portion 120c is connected to the side wall portion 110b.

[0039] The space formed between the outer wall portion 101b and the side wall portion 110b is radially partitioned by the partition wall portion 120a. Specifically, the partition wall portion 120a is provided radially outside the liner 110 than the side wall portion 110b, and forms an inner flow path 122 between the partition wall portion 120a and the side wall portion 110b. Further, the outer wall portion 101b is provided radially outside the liner 110 than the partition wall portion 120a, and forms an outer flow path 124 between the partition wall portion 120a and the outer wall portion 101b. That is, the space formed between the outer wall portion 101b and the side wall portion 110b is partitioned by the partition wall portion 120a into an inner flow path 122 located radially inside the partition wall portion 120a and an outer flow path 124 located radially outside the partition wall portion 120a.

[0040] The inner flow path 122 communicates with the air introduction portion 111. Further, the outer flow path 124 is connected to the intake flow path 6 at the opening 101d. Among the outer flow path 124, the end portion on the burner 30 side is sealed by the first end portion 120b. Further, among the inner flow path 122, the end portion on the opening 101d side is sealed by the second end portion 120c.

[0041] And a plurality of communication holes 126 are formed in the partition wall portion 120a. The communication holes 126 are formed in the partition wall portion 120a at a plurality of positions spaced apart from each other in the central axis direction of the liner 110, and communicate the inner flow path 122 and the outer flow path 124. In other words, the inner flow path 122 and the outer flow path 124 are connected via a plurality of communication holes 126. Further, a plurality of communication holes 126 are formed spaced apart from each other in the circumferential direction. Here, the communication holes 126 are smaller than the through holes 116. Here, although all the plurality of communication holes 126 have the same size, a plurality of communication holes 126 having different sizes and shapes may be provided. The size, shape, and number of the communication holes 126 are merely examples and are not particularly limited.

[0042] In the inner flow path 122, a partition wall 130 is provided that partitions the inner flow path 122 in the central axis direction of the liner 110. The partition wall 130 is formed in an annular shape, with the inner diameter side end connected to the side wall portion 110b and the outer diameter side end connected to the partition wall portion 120a. By the partition wall 130, the inner flow path 122 is partitioned into a first inner flow path 122a located on the burner 30 side and a second inner flow path 122b located on the opening 114a side. The first inner flow path 122a communicates with the air introduction portion 111. Also, the second inner flow path 122b communicates with the through hole 116. Therefore, the through hole 116 communicates the second inner flow path 122b and the combustion chamber 115. Further, the through hole 116 is formed at a position spaced apart from the burner 30 in the central axis direction relative to the partition wall 130. Furthermore, since the primary region 115a is provided on the burner 30 side relative to the through hole 116, the partition wall 130 is located radially outside the primary region 115a.

[0043] Also, the communication holes 126 are provided on both one side and the other side in the central axis direction with the partition wall 130 as a boundary. In FIG. 1, the number of communication holes 126 provided on the burner 30 side relative to the partition wall 130 is equal to the number of communication holes 126 provided on the opening 114a side relative to the partition wall 130. However, the number of communication holes 126 provided on the burner 30 side and the opening 114a side relative to the partition wall 130 may be different.

[0044] Also, on the side wall portion 110b of the liner 110, a flame transfer hole 140 is formed. The flame transfer hole 140 opens into the combustion chamber 115 and penetrates the side wall portion 110b in the radial direction. A flame transfer pipe 142 is connected to the flame transfer hole 140. The flame transfer pipe 142 penetrates the flow path forming member 120 and the casing 101 and extends from the side wall portion 110b of the liner 110 to the outside of the casing 101.

[0045] In the multi-can combustor gas turbine 1, a plurality of connection parts 5b are provided in the connection part 5, and the combustors 100 are respectively connected to all the connection parts 5b. Therefore, the multi-can combustor gas turbine 1 includes a plurality of combustors 100 arranged annularly so as to surround the compressor 2. Both ends of the flame transfer pipe 142 are connected to the flame transfer holes 140 of different combustors 100 respectively. That is, the flame transfer pipe 142 connects the combustion chambers 115 of two combustors 100, more specifically, the primary regions 115a of two combustors 100.

[0046] FIG. 3 shows one flame transfer hole 140 and one flame transfer pipe 142. However, two flame transfer holes 140 are formed in the liner 110, and two flame transfer pipes 142 are connected to one combustor 100. For example, the combustion chamber 115 of the combustor 100 communicates with the combustion chambers 115 of two adjacent combustors 100 through two flame transfer pipes 142. Through the flame transfer pipes 142, the combustion chambers 115 of all the combustors 100 communicate with each other.

[0047] Note that the number of the flame transfer holes 140 and the flame transfer pipes 142 is not particularly limited. Also, the two combustors 100 connected by one flame transfer pipe 142 do not necessarily have to be adjacent to each other. Any two combustors 100 may be connected by the flame transfer pipe 142. Further, for example, two combustors 100 may be connected by a plurality of flame transfer pipes 142. Furthermore, for example, one annular flame transfer pipe 142 may be provided, and a plurality of branch pipes branched from the flame transfer pipe 142 may be connected to each of the combustors 100. In any case, the flame transfer pipe 142 only needs to connect at least two combustors 100.

[0048] Also, among the plurality of combustors 100, at least one combustor 100 is provided with an ignition device. The number of the combustors 100 provided with the ignition device is not limited. For example, all the combustors 100 may be provided with the ignition devices. In this case, the flame transfer holes 140 and the flame transfer pipes 142 are not essential components.

[0049] FIG. 4 is a diagram for explaining the operation of the gas turbine system GS according to the embodiment. As shown in FIG. 4, an intake air passage 6 formed in the connection part 5 is connected to the outer flow passage 124, and the air compressed by the compressor 2 is supplied to the outer flow passage 124. The air sent to the outer flow passage 124 is guided toward the burner 30 along the separation partition part 120a as indicated by the arrow of the dashed line in the figure. Then, the air flowing through the outer flow passage 124 flows into the first inner flow passage 122a and the second inner flow passage 122b from the communication hole 126.

[0050] The air flowing into the first inner flow passage 122a is injected from the air introduction part 111 into the combustion chamber 115, particularly the primary region 115a. Further, ammonia whose flow rate is adjusted by the flow rate control valve 50 is supplied to the burner 30 as fuel. Fuel is injected from an injection valve provided at the tip of the burner 30 into the combustion chamber 115. At this time, the fuel may be injected from the burner 30 in the central axis direction. Alternatively, the fuel may be injected from the burner 30 in a direction that expands radially as it separates from the burner 30.

[0051] Note that the injection valve provided in the burner 30 is a pressure injection valve or an air flow injection valve. The pressure injection valve is a type of valve that atomizes a liquid by utilizing the pressure difference inside and outside the pressure injection valve. The air flow injection valve is a type of valve that generates a film of the liquid to be injected and atomizes the liquid by utilizing the shearing force between the film and the air. However, the configuration of the injection valve is not particularly limited. Here, liquid ammonia is used as fuel, but gaseous ammonia may also be used. Further, as fuel supplied to the combustion chamber 115, in addition to ammonia, other fuels such as natural gas or hydrogen may be used.

[0052] Fuel injected from the burner 30 is mixed with air injected from the air introduction part 111 to generate an air-fuel mixture. That is, the air-fuel mixture is supplied to the combustion chamber 115. Then, in at least one combustor 100, the air-fuel mixture is ignited by an ignition device. As a result, a combustion action occurs in the combustion chamber 115 of the combustor 100 provided with the ignition device. Further, a flame propagates from the combustor 100 provided with the ignition device to other combustors 100 through the flame transfer pipe 142. As a result, a combustion action occurs in the combustion chambers 115 of all the combustors 100. The combustion gas generated by combustion is discharged into the exhaust passage 7 in the connection part 5 connected to the opening 114a.

[0053] Here, in the primary region 115a, the flow rates of air and fuel are adjusted so that the equivalence ratio of the air-fuel mixture becomes fuel-rich at about 1.0 to 1.5. Therefore, the combustion in the primary region 115a is rich combustion. On the other hand, the liner 110 is formed with through holes 116, and dilution air is supplied to the combustion chamber 115 from the second inner flow path 122b through the through holes 116. In the secondary region 115b, the dilution air is mixed with the air-fuel mixture, and the combustion in the secondary region 115b becomes lean combustion. Thus, in the present embodiment, rich combustion is performed in the primary region 115a, and lean combustion is performed in the secondary region 115b.

[0054] Also, the air flowing into the first inner flow path 122a is injected into the combustion chamber 115 from the air introduction part 111 after cooling the side wall part 110b of the liner 110. On the other hand, the air flowing into the second inner flow path 122b is introduced into the combustion chamber 115 from the through holes 116 as dilution air after cooling the side wall part 110b of the liner 110. In other words, the side wall part 110b on the burner 30 side of the partition wall 130 is cooled by the air supplied to the burner 30. On the other hand, the side wall part 110b on the opening 114a side of the partition wall 130 is cooled by the air introduced into the combustion chamber 115 from the through holes 116.

[0055] Further, a second through-hole 117 is provided in the secondary region 115b. The air flowing into the combustion chamber 115 from the second through-hole 117 flows along the side wall portion 110b of the liner 110. As a result, the range surrounding the secondary region 115b in the side wall portion 110b of the liner 110 is cooled.

[0056] As described above, combustion gas is generated in each of the plurality of combustors 100. The combustion gas generated in each of the plurality of combustors 100 is aggregated in the connecting portion 5 and sent to the turbine 3. The turbine blade wheel 3a rotates due to the combustion gas passing through the turbine 3, and rotational power is generated. The combustion gas that has passed through the turbine 3 is discharged to the outside of the multi-can combustor gas turbine 1.

[0057] Here, in the gas turbine system GS of the present embodiment, ammonia is used as fuel. Ammonia is a flame-retardant fuel, and if combustion becomes insufficient, emissions such as NOx, unburned NH3, and N2O generated from ammonia may be discharged. Therefore, in the present embodiment, one or a plurality of combustors 100 in which a relatively large-volume combustion chamber 115 is formed inside are provided in the multi-can combustor gas turbine 1.

[0058] FIG. 5 is a diagram for explaining the first combustor 100a and the second combustor 100b. As described above, the multi-can combustor gas turbine 1 includes a plurality of combustors 100. The plurality of combustors 100 include two types of combustors 100 having different volumes of the combustion chamber 115. Here, the combustor 100 having a relatively small volume of the combustion chamber 115 is referred to as the first combustor 100a, and the combustor 100 having a relatively large volume of the combustion chamber 115 is referred to as the second combustor 100b. That is, the multi-can combustor gas turbine 1 includes one or a plurality of first combustors 100a connected to the connection portion 5b and having a combustion chamber 115 formed therein, and one or a plurality of second combustors 100b connected to the connection portion 5b and having a combustion chamber 115 with a larger volume than the first combustor 100a formed therein.

[0059] Note that the first combustor 100a and the second combustor 100b differ only in the size of the combustion chamber 115, and other configurations and operations are the same. Specifically, the casings 101 of the first combustor 100a and the second combustor 100b have the same diameter but different lengths in the central axis direction. Similarly, the liners 110 of the first combustor 100a and the second combustor 100b have the same diameter but different lengths in the central axis direction. Therefore, the flow path widths of the inner flow path 122 and the outer flow path 124 formed between the casing 101 and the liner 110 are the same for the first combustor 100a and the second combustor 100b, and the lengths of the inner flow path 122 and the outer flow path 124 in the central axis direction are different for the first combustor 100a and the second combustor 100b.

[0060] However, the diameters of either one or both of the casing 101 and the liner 110 may be different between the first combustor 100a and the second combustor 100b. Also, the volumes and flow path widths of either one or both of the inner flow path 122 and the outer flow path 124 may be different between the first combustor 100a and the second combustor 100b.

[0061] In addition, the first combustor 100a and the second combustor 100b have substantially the same shape and size on the right side of the two-dot chain line in FIG. 5. That is, the shapes and sizes of the secondary regions 115b of the first combustor 100a and the second combustor 100b are substantially the same. Furthermore, the first combustor 100a and the second combustor 100b have substantially the same shape and size from the connection position of the flame transfer pipe 142 to the connected portion 101c. As a result, the connection portion 5b of the connecting portion 5 is shared between the first combustor 100a and the second combustor 100b. As a result, the assembly work of the first combustor 100a and the second combustor 100b is simplified. Also, it becomes easier to change the attachment positions of the first combustor 100a and the second combustor 100b.

[0062] And the combustion chamber 115 of the second combustor 100b is longer in the central axis direction and has a larger volume than the combustion chamber 115 of the first combustor 100a. Therefore, in the second combustor 100b, it is possible to ensure a longer residence time of the combustion gas than in the first combustor 100a. As a result, the emissions contained in the entire combustion gas discharged from the multi-can combustor gas turbine 1 are reduced. In particular, in the second combustor 100b, the primary region 115a, which is relatively hotter than the secondary region 115b in the combustion chamber 115, is longer in the central axis direction and has a larger volume. The longer residence time of the combustion gas in the primary region 115a further improves the effect of suppressing emissions in the multi-can combustor gas turbine 1.

[0063] Further, the flame transfer pipe 142 is connected within a range of the same shape to each other between the first combustor 100a and the second combustor 100b. Therefore, the flame transfer pipe 142 connected to the first combustor 100a and the flame transfer pipe 142 connected to the second combustor 100b can be made common. Also, the flame transfer pipe 142 is connected to the primary region 115a closer to the burner 30 than the secondary region 115b and upstream of the through hole 116 into which dilution air flows. Therefore, the ignition performance by the flame propagating from the flame transfer pipe 142 is improved compared to the case where the flame transfer pipe 142 is connected to the secondary region 115b.

[0064] As described above, according to the multi-can combustor gas turbine 1, by providing the second combustor 100b having a relatively large volume of the combustion chamber 115, the emissions contained in the combustion gas can be reduced. Note that, among the plurality of combustors 100 provided in the multi-can combustor gas turbine 1, the arrangements of the first combustor 100a and the second combustor 100b are not particularly limited. As an example, the multi-can combustor gas turbine 1 is installed on an installation table (not shown) in the posture shown in FIG. 2. At this time, it is assumed that the first combustor 100a has a dimension that fits within the radial range of the connecting portion 5. On the other hand, it is assumed that the second combustor 100b has a dimension such that a part thereof protrudes outside the radial direction of the connecting portion 5. In this case, if the second combustor 100b, which is long in the central axis direction, is provided, for example, below the shaft 4, the second combustor 100b may interfere with the installation table.

[0065] Therefore, for example, the first combustor 100a may be provided below the shaft 4, and the second combustor 100b may be provided above the shaft 4. Alternatively, the first combustor 100a may be provided in a range where the second combustor 100b interferes with the installation base, and the second combustor 100b may be provided in a range where the second combustor 100b does not interfere with the installation base.

[0066] Also, not limited to the installation base, when there is a range where the second combustor 100b interferes with the components or peripheral devices of the multi-can combustor gas turbine 1, the second combustor 100b may be provided within a range where there is no interference. In this way, by increasing the number of second combustors 100b included in the plurality of combustors 100 as much as possible, the emission suppression effect in the multi-can combustor gas turbine 1 is improved.

[0067] Note that the internal configuration of the combustor 100 described in the above embodiment is merely an example. Hereinafter, a modified example of the internal configuration of the combustor 100 will be described. In the following, in the modified example, a configuration different from the above embodiment will be described, and the same components as those in the above embodiment will be denoted by the same reference numerals, and detailed descriptions thereof will be omitted. Therefore, the modified example described below has the same configuration as the above embodiment in parts where no special notice is given.

[0068] FIG. 6 is a schematic diagram showing the configuration of a gas turbine system GS according to a modified example. In the gas turbine system GS according to the modified example, only the internal configuration of the combustor 100 of the multi-can combustor gas turbine 1 is different from that of the above embodiment. In the combustor 100 according to the modified example, a first liner 210 and a second liner 220 are provided instead of the liner 110 of the above embodiment. The first liner 210 and the second liner 220 are accommodated inside the casing 101. The first liner 210 and the second liner 220 have a substantially cylindrical shape. The first liner 210 and the second liner 220 are separate from each other, that is, they are constituted by different members.

[0069] Within the casing 101, the first liner 210 is provided closer to the burner 30 side than the second liner 220. The outer diameters of the first liner 210 and the second liner 220 are smaller than the inner diameter of the casing 101. Thereby, an outer flow path 124 is formed between the first liner 210 and the second liner 220 and the casing 101.

[0070] The central axes of the first liner 210 and the second liner 220 substantially coincide with the central axis of the casing 101 and the burner 30. The first liner 210 is configured in a substantially bottomed cylindrical shape having a bottom portion 210a and a side wall portion 210b. A burner insertion hole 210c is formed in the bottom portion 210a of the first liner 210. The tip of the burner 30 is inserted through the burner insertion hole 210c. The inner diameter of the burner insertion hole 210c is larger than the outer diameter of the burner 30. Thereby, an annular air introduction portion 111 penetrating the bottom portion 210a in the central axis direction is formed in the bottom portion 210a of the first liner 210.

[0071] The first liner 210 also includes a large diameter portion 212, a reduced diameter portion 213, and a small diameter portion 214. The large diameter portion 212 is located closer to the burner 30 side than the reduced diameter portion 213 and the small diameter portion 214. The small diameter portion 214 is located axially spaced from the burner 30 compared to the large diameter portion 212 and the reduced diameter portion 213. The inner diameter of the small diameter portion 214 is smaller than the inner diameter of the large diameter portion 212. The reduced diameter portion 213 connects the large diameter portion 212 and the small diameter portion 214. The reduced diameter portion 213 decreases in diameter as it goes from the large diameter portion 212 toward the small diameter portion 214. That is, the reduced diameter portion 213 has a tapered shape. However, the reduced diameter portion 213 may extend in the radial direction. An opening 214a is formed at the end of the small diameter portion 214 located on the side opposite to the reduced diameter portion 213.

[0072] In the modification, the inner diameter of the large-diameter portion 212 of the first liner 210 is substantially constant regardless of the position in the central axis direction. However, the inner diameter of the large-diameter portion 212 may vary depending on the position in the central axis direction. For example, the large-diameter portion 212 may have a tapered shape in which the diameter increases or decreases as it is separated from the burner 30. Similarly, the inner diameter of the small-diameter portion 214 may vary depending on the position in the central axis direction. For example, the small-diameter portion 214 may have a tapered shape in which the diameter increases or decreases as it is separated from the burner 30.

[0073] Furthermore, the entire first liner 210 may have a tapered shape in which the diameter gradually decreases as it is separated from the burner 30 side. Furthermore, the first liner 210 may have a constant diameter from the bottom 210a to the opening 214a. In any case, the shape of the first liner 210 is not limited to the example in FIG. 6.

[0074] A first combustion chamber 215 is formed inside the large-diameter portion 212, the reduced-diameter portion 213, and the small-diameter portion 214. That is, the first combustion chamber 215 is formed inside the first liner 210. Also, a primary region 215a shown by the dashed line in the figure is formed inside the large-diameter portion 212. And a flow path forming member 120 is provided on the radially outer side of the first liner 210. Also in the modification, an inner flow path 122 and an outer flow path 124 are provided on the radially outer side of the first liner 210. Also in the modification, a partition wall 130 is provided between the side wall portion 210b of the first liner 210 and the partition wall portion 120a. Therefore, the inner flow path 122 facing the side wall portion 210b is partitioned by the partition wall 130 into a first inner flow path 122a and a second inner flow path 122b.

[0075] In addition, a flame transfer hole 140 is formed in the large-diameter portion 212. A flame transfer pipe 142 is connected to the flame transfer hole 140. In a modified example, the flame transfer pipe 142 is connected to the first combustion chamber 215 provided in the first liner 210. Also, here, the flame transfer pipe 142 is connected to the primary region 215a in the first combustion chamber 215. Therefore, in the modified example, among the plurality of burners 100, the first combustion chambers 215, more precisely, the primary regions 215a are connected to each other by the flame transfer pipe 142.

[0076] The second liner 220 is composed of a substantially cylindrical member having openings 220a and 220b formed at both ends. The second liner 220 includes a second large-diameter portion 222, a second reduced-diameter portion 223, and a second small-diameter portion 224. The second large-diameter portion 222 is located closer to the burner 30 side than the second reduced-diameter portion 223 and the second small-diameter portion 224. Also, the second small-diameter portion 224 is located axially separated from the burner 30 compared to the second large-diameter portion 222 and the second reduced-diameter portion 223. The inner diameter of the second small-diameter portion 224 is smaller than the inner diameter of the second large-diameter portion 222. The second reduced-diameter portion 223 connects the second large-diameter portion 222 and the second small-diameter portion 224. The second reduced-diameter portion 223 has a diameter that decreases as it extends from the second large-diameter portion 222 toward the second small-diameter portion 224. That is, the second reduced-diameter portion 223 has a tapered shape. However, the second reduced-diameter portion 223 may extend in the radial direction. An opening 220a is formed at the end of the second large-diameter portion 222 on the burner 30 side. Also, an opening 220b connected to the exhaust flow path 7 is formed at the end of the second small-diameter portion 224 located on the side opposite to the second reduced-diameter portion 223.

[0077] Note that in the modified example, the inner diameter of the second large-diameter portion 222 of the second liner 220 is substantially constant regardless of the position in the central axis direction. However, the inner diameter of the second large-diameter portion 222 may vary depending on the position in the central axis direction. For example, the second large-diameter portion 222 may have a tapered shape in which the diameter increases or decreases as it moves away from the burner 30. Similarly, the inner diameter of the second small-diameter portion 224 may vary depending on the position in the central axis direction. For example, the second small-diameter portion 224 may have a tapered shape in which the diameter increases or decreases as it moves away from the burner 30.

[0078] Furthermore, the entire second liner 220 may have a tapered shape in which the diameter gradually decreases as it moves away from the burner 30 side. Furthermore, the diameter of the second liner 220 may be constant from the opening 220a to the opening 220b. In any case, the shape of the second liner 220 is not limited to the example in FIG. 6.

[0079] A second combustion chamber 225 is formed inside the second large-diameter portion 222, the second reduced-diameter portion 223, and the second small-diameter portion 224. That is, the second combustion chamber 225 is formed inside the second liner 220. Also, a secondary region 225a indicated by a dashed line in the figure is formed inside the second large-diameter portion 222. A second through-hole 117 is formed in the second large-diameter portion 222, and a guide member 118 is provided in the secondary region 225a. However, the second through-hole 117 may be provided in the large-diameter portion 212 of the first liner 210.

[0080] The small-diameter portion 214 of the first liner 210 is inserted through the opening 220a of the second liner 220. Therefore, the inner diameter of the second large-diameter portion 222 of the second liner 220 is larger than the outer diameter of the small-diameter portion 214 of the first liner 210. The end portion of the small-diameter portion 214 of the first liner 210 where the opening 214a is formed is located inside the second liner 220. The outer peripheral surface of the small-diameter portion 214 of the first liner 210 faces the inner peripheral surface of the second large-diameter portion 222 of the second liner 220 in the radial direction. At this time, the outer peripheral surface of the small-diameter portion 214 and the inner peripheral surface of the second large-diameter portion 222 are separated. In other words, the second liner 220 overlaps with the first liner 210.

[0081] Through the opening 214a, the first combustion chamber 215 inside the first liner 210 and the second combustion chamber 225 inside the second liner 220 communicate with each other. That is, the first liner 210 and the second liner 220 constitute one liner, and the first combustion chamber 215 and the second combustion chamber 225 constitute one combustion chamber.

[0082] Also, an annular flow path 230 is formed between the inner peripheral surface of the second large-diameter portion 222 of the second liner 220 and the outer peripheral surface of the small-diameter portion 214 of the first liner 210. The tip of the second large-diameter portion 222, i.e., the opening 220a, is axially spaced from the reduced-diameter portion 213 of the first liner 210. Thereby, the flow path 230 communicates with the second inner flow path 122b. That is, the flow path 230 functions as a second air introduction portion that introduces dilution air from the second inner flow path 122b into the second combustion chamber 225. Therefore, also in the modified example, the same operations and effects as those of the combustor 100 according to the above embodiment are achieved.

[0083] In the modified example, the first liner 210 and the second liner 220 are assumed to be separate bodies. However, the first liner 210 and the second liner 220 may be integrally formed.

[0084] Although not shown, in the multi-can combustor gas turbine 1 according to the modified example, a plurality of combustors 100 are also provided. The plurality of combustors 100 include a first combustor 100a having a relatively small combustion chamber volume and a second combustor 100b having a relatively large combustion chamber volume among the combustors 100 shown in FIG. 6. In the modified example, the second liner 220 is substantially the same for the first combustor 100a and the second combustor 100b. That is, in the modified example, the second liner 220 is shared between the first combustor 100a and the second combustor 100b. On the other hand, in the modified example, the lengths of the casing 101 and the first liner 210 in the central axis direction are different between the first combustor 100a and the second combustor 100b.

[0085] Therefore, in the modified example, the volume and shape of the second combustion chamber 225 and the secondary region 225a are the same between the first combustor 100a and the second combustor 100b. On the other hand, in the modified example, the second combustor 100b has a longer first combustion chamber 215 and primary region 215a and a larger volume than the first combustor 100a in the central axis direction. Also, in the modified example, the shape and size from the connection point of the flame transfer pipe 142 to the connected portion 101c are substantially the same between the first combustor 100a and the second combustor 100b. As described above, the multi-can combustor gas turbine 1 according to the modified example realizes the same operations and effects as the multi-can combustor gas turbine 1 according to the above-described embodiment.

[0086] Note that the combustor 100 described in the above embodiment and modified example is merely an example. The combustor 100 provided in the multi-can combustor gas turbine 1 is not limited to the internal configuration described in the above embodiment and modified example. The multi-can combustor gas turbine 1 may include, for example, a conventionally known combustor 100.

[0087] Also, the plurality of combustors 100 included in the multi-can combustor gas turbine 1 may include the combustor 100 of the above embodiment and the combustor 100 of the above modified example. In this case, for example, the first combustor 100a may be configured by the combustor 100 according to the embodiment, and the second combustor 100b may be configured by the combustor 100 according to the modified example. Thus, the plurality of combustors 100 included in the multi-can combustor gas turbine 1 do not necessarily have the same internal configuration. In other words, the plurality of combustors 100 included in the multi-can combustor gas turbine 1 may include one or more combustors 100 having different internal configurations.

[0088] As described above, the embodiments of the present disclosure have been described with reference to the accompanying drawings. Needless to say, the present disclosure is not limited to such embodiments. It is obvious that those skilled in the art can conceive of various modification examples or correction examples within the scope described in the claims, and it is naturally understood that those also belong to the technical scope of the present disclosure.

[0089] In the above-described embodiment, as an example where the volume of the combustion chamber 115 of the second combustor 100b is larger than that of the combustion chamber 115 of the first combustor 100a, the case where the second combustor 100b is longer than the first combustor 100a in the central axis direction has been described. However, the lengths of the first combustor 100a and the second combustor 100b in the central axis direction may be the same, and the volume of the two may be made different by making the diameter of the second combustor 100b larger than the diameter of the first combustor 100a. The same applies to the above-described modification example.

[0090] In the above-described embodiment, the case where the shapes and sizes of the secondary regions 115b of the first combustor 100a and the second combustor 100b are substantially the same has been described. However, the shapes and sizes of the secondary regions 115b of the first combustor 100a and the second combustor 100b may be different. The same applies to the above-described modification example.

[0091] In the above, the case where two types of first combustor 100a and second combustor 100b with different volumes are provided has been described. However, in addition to the first combustor 100a and the second combustor 100b, one or more types of combustors with volumes different from those of the first combustor 100a and the second combustor 100b may be provided. For example, a third combustor having a volume between the first combustor 100a and the second combustor 100b may be added. Further, a fourth combustor having a volume different from that of the third combustor may be further added. In any case, it is sufficient that two or more types of combustors with different volumes are provided.

[0092] In the above, in the gas turbine system GS, an example where the rotational power generated by the multi-can combustor gas turbine 1 is used as energy for driving the generator 20 has been described. However, in the gas turbine system GS, the rotational power generated by the multi-can combustor gas turbine 1 may be used for other purposes. Examples of other purposes include, for example, driving a moving body such as a ship.

[0093] In the above, an example in which the multi-can combustor gas turbine 1 is applied to the gas turbine system GS has been described. However, the multi-can combustor gas turbine 1 may be used in devices other than the gas turbine system GS. Examples of devices other than the gas turbine system GS include, for example, industrial furnaces for changing the shape or properties of materials by combustion in a combustor.

[0094] Further, the present disclosure is applicable to a method for retrofitting an existing multi-can combustor gas turbine. That is, the method for retrofitting a multi-can combustor gas turbine includes connecting one or more first combustors in which a combustion chamber is formed inside to a connection part of an existing multi-can combustor gas turbine including a compressor that houses an impeller, a turbine that houses a turbine wheel, a shaft that connects the impeller and the turbine wheel, a connection part that houses the shaft and is provided between the compressor and the turbine, and a plurality of connection parts that are provided in the connection part and arranged in the rotational direction of the shaft, and connecting one or more second combustors in which a combustion chamber having a larger volume than the first combustor is formed inside to the connection part.

Description of Reference Numerals

[0095] 1 Multi-can combustor gas turbine 2 Compressor 2a Impeller 3 Turbine 3a Turbine wheel 4 Shaft 5 Connection part 5b Connection part 30 Burner 100 Combustor 100a First combustor 100b Second combustor 115 Combustion chamber 115a, 215a Primary region 115b, 225a Secondary region 142 Flame transfer pipe 215 First combustion chamber 225 Second combustion chamber

Claims

1. a compressor that houses an impeller; a turbine that houses a turbine impeller wheel; a shaft that connects the impeller and the turbine impeller wheel; a connecting portion that houses the shaft and is provided between the compressor and the turbine; a plurality of connecting portions provided in the connecting portion and arranged in the rotational direction of the shaft; one or more first combustors connected to the connecting portion and having a combustion chamber formed therein, and a plurality of combustors including one or more second combustors connected to the connecting portion and having a combustion chamber formed therein with a larger volume than the first combustor; A multi-can combustor gas turbine comprising:

2. The combustor: A burner is provided at one end, and the other end is connected to the connecting portion. The combustion chamber: includes a primary region located on the burner side and a secondary region located on the connecting portion side rather than the primary region. The shapes and sizes of the secondary regions of the first combustor and the second combustor are substantially the same. The multi-can combustor gas turbine according to claim 1.

3. A flame transfer pipe connecting the primary regions of at least two of the combustors. The multi-can combustor gas turbine according to claim 2, further comprising:

4. A method for retrofitting a multi-can combustor gas turbine comprising a compressor that houses an impeller, a turbine that houses a turbine impeller wheel, a shaft that connects the impeller and the turbine impeller wheel, a connecting portion that houses the shaft and is provided between the compressor and the turbine, and a plurality of connecting portions provided in the connecting portion and arranged in the rotational direction of the shaft, the method comprising: connecting one or more first combustors having a combustion chamber formed therein to the connecting portion; connecting one or more second combustors having a combustion chamber formed therein with a larger volume than the first combustor to the connecting portion; A method for retrofitting a multi-can combustor gas turbine including:

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