Gas turbine facility

Abstract

Gas turbine device (10), comprising: a housing (70; 71, 72); a burner (20) provided in the housing (70) for combusting fuel and oxidant, the burner (20) comprising a fuel nozzle part (60), a combustion chamber insert (61) and a transition piece (62), the fuel nozzle part (60) being provided at an upstream end portion of the combustion chamber insert (61), the transition piece (62) being connected to a downstream end portion of the combustion chamber insert (61); a cylinder (80) surrounding a periphery of the burner (20) to form a first annular space and a second annular space, the cylinder (80) having a cover member (80a) at an upstream end, the cover member (80a) being penetrated by the fuel nozzle part (60), the cover member (80a) closing the upstream end of the cylinder (80), a downstream end of the cylinder (80) being connected to an outer peripheral surface of the transition piece (62), the downstream end of the cylinder (80) being closed, the first annular space being formed between the cylinder (80) and the burner (20), the second annular space being formed between the housing (70) and the cylinder (80); a turbine (25) rotated by and discharging combustion gas from the burner (20); a heat exchanger (24) which cools the combustion gas discharged from the turbine (25) to form a cooled combustion gas and heats a portion of the cooled combustion gas; a first supply pipe (42) for combustion gas, which penetrates into the housing (70) and the cylinder (80) for conducting the part of the cooled combustion gas heated in the heat exchanger (24) into the first annular space, and a second combustion gas supply pipe (44) surrounding the first combustion gas supply pipe (42) which guides another part of the cooled combustion gas cooled in the heat exchanger (24) to the second annular space, wherein a temperature of the another part of the cooled combustion gas cooled in the heat exchanger (24) which is passed through the second combustion gas supply pipe (44) is lower than a temperature of the part of the cooled combustion gas heated in the heat exchanger (24) which is passed through the first combustion gas supply pipe (42).

Description

REGIONEmbodiments of the present invention relate to a gas turbine apparatus.GENERAL STATE OF THE ARTIn response to the demands for carbon dioxide reduction, resource conservation, and the like, power plants have ever greater efficiency. In particular, at present, the temperature of the working fluid of gas turbines and steam turbines is increased, combi cycles are applied, and the like. Moreover, research and development is being carried out on the recovery of carbon dioxide.FIG. 8 is a system diagram of a conventional gas turbine apparatus 300. FIG. 9 is a view schematically showing a vertical section of a combustor 313 provided in the conventional gas turbine apparatus 300. In the conventional gas turbine apparatus 300, a turbine using carbon dioxide and water vapor generated in a combustor as working fluid is operated, and a part of the carbon dioxide discharged from the turbine is circulated.As shown in FIG. 8, in the conventional gas turbine apparatus 300, oxygen separated by an air separator (not shown) is introduced into a pipe 340. The oxygen is then compressed in a compressor 310 and its flow rate is controlled by a flow control valve 311. The oxygen flowing through the flow control valve 311 is heated by receiving heat from the combustion gas described later in a heat exchanger 312, and is supplied to the burner 313.Fuel is supplied from a fuel supply source (not shown) to a pipe 341. The flow rate of the fuel is controlled by a flow control valve 314 and supplied to the burner 313. The fuel is hydrocarbon.As illustrated in FIG. 9, the oxygen supplied from the pipe 340 and the fuel supplied from the pipe 341 react (burn) in the burner 313. In this combustion, combustion gas containing carbon dioxide and water vapor is generated. The flow rates of fuel and oxygen are controlled to a stoichiometric mixing ratio (theoretical mixing ratio) in a state where they are fully mixed.The combustion gas generated in the combustor 313 is introduced into a turbine 315. Note that, for example, a generator 319 is coupled to the turbine 315 as shown in FIG. 8. The combustion gas that has performed expansion work in the turbine 315 flows through the heat exchanger 312. At this time, heat is released, and the oxygen flowing in the pipe 340 and the carbon dioxide flowing in a pipe 343 are heated.The combustion gas flowing through the heat exchanger 312 then flows through a radiator 316. At this time, the water vapor in the combustion gas condenses into water. The water flows through a pipe 342 and is discharged to the outside.The carbon dioxide separated from the water vapor is compressed in a compressor 317 interposed in the pipe 343 and becomes supercritical fluid. A portion of the compressed carbon dioxide is introduced into a pipe 344 branched from the pipe 343. The carbon dioxide introduced into the pipe 344 is controlled in flow rate by a flow control valve 318 and discharged to the outside.Meanwhile, a remaining part of the carbon dioxide flows into the pipe 343. The carbon dioxide is then heated in the heat exchanger 312 and fed to a burner housing 350 in which the burner 313 is housed, as shown in Fig. 9. The temperature of the carbon dioxide flowing through the heat exchanger 312 is about 700° C. Here, the burner housing 350 is configured by an upstream housing 351 aand a downstream housing 351 b.The carbon dioxide introduced into the upstream casing 351 aflows between the downstream casing 351 band a combustor liner 352 and a transition piece (tail pipe) 353 to the turbine 315.When the carbon dioxide flows between the downstream casing 351 band the combustor liner and the transition piece 353, the carbon dioxide cools the combustor liner 352 and the transition piece 353. The cooling process is carried out, for example, by film cooling (porous) (porous film cooling) or the like. A part of the carbon dioxide is introduced into the combustor liner 352 and the transition piece 353 from holes 354, 356 of a film cooling part (porous), dilution holes 355, and so on, as shown in FIG. 9. In addition, the carbon dioxide is also used to cool vanes 360 and blades 361 of turbine 315.The carbon dioxide introduced into the combustor liner 352 and the transition piece 353 is introduced into the turbine 315 together with the combustion gas generated by the combustion. As previously indicated, the carbon dioxide circulates within the system other than the carbon dioxide discharged from the tube 344.Here, the upstream housing 351 aand the downstream housing 351 bare exposed to high temperature carbon dioxide. The upstream case 351 aand the downstream case 351 bare therefore made of an expensive Ni-based alloy.JP 2016 008590 A describes gas turbine equipment. The gas turbine equipment includes a combustor provided in a combustor casing and burning fuel and an oxidant; a cylindrical body separating a space between the combustor casing and the combustor; a turbine rotated with the combustion gas discharged from the combustor; and a heat exchanger cooling the combustion gas discharged from the turbine. Further, there is provided a piping through which a part of the combustion gas cooled in the heat exchanger flows through the heat exchanger to be heated, this piping for high-temperature combustion gas introducing the combustion gas heated in the heat exchanger into the burner housing, into a space between the burner and the cylindrical body; a piping introducing the other part of the combustion gas cooled by the heat exchanger into a space between the combustion chamber housing and the cylindrical body; and a piping discharging a remainder of the combustion gas cooled by the heat exchanger to the outside.RELEVANT REFERENCESPatent ReferenceReference 1: JP 2000-337107 ASUMMARY OF THE INVENTIONOBJECTS TO BE SOLVED BY THE INVENTIONAs described above, in the conventional gas turbine apparatus 300, the burner casing 350 exposed to the high temperature carbon dioxide needs to be made of the expensive Ni-based alloy. Accordingly, the manufacturing cost of the gas turbine apparatus increases.The object to be achieved by the present invention is to provide a gas turbine device in which a casing located on the periphery of a burner can consist of cost-effective materials.MEANS FOR ACHIEVING THE OBJECTSA gas turbine apparatus according to an embodiment includes: a casing; a combustor provided in the casing to combust fuel and oxidant, the combustor including a fuel nozzle part, a combustor liner, and a transition piece, the fuel nozzle part being provided at an upstream end portion of the combustor liner, the transition piece being connected to a downstream end portion of the combustor liner; a cylinder surrounding a periphery of the burner to form a first annular space and a second annular space, the cylinder having a cap member at an upstream end, the cap member being penetrated by the fuel nozzle part, the cap member closing the upstream end of the cylinder, a downstream end of the cylinder being connected to an outer peripheral surface of the transition piece, the downstream end of the cylinder being closed, the first annular space being formed between the cylinder and the burner, the second annular space being formed between the housing and the cylinder; a turbine rotated by combustion gas from the burner and discharging it; a heat exchanger cooling the combustion gas discharged from the turbine to form a cooled combustion gas, and heating a part of the cooled combustion gas; a first combustion gas supply pipe penetrating the housing and the cylinder for guiding the part of the cooled combustion gas heated in the heat exchanger into the first annular space, and a second combustion gas supply pipe surrounding the first combustion gas supply pipe guiding another part of the cooled combustion gas cooled in the heat exchanger to the second annular space, wherein a temperature of the other part of the cooled combustion gas cooled in the heat exchanger guided by the second combustion gas supply pipe is lower than a temperature of the part of the cooled combustion gas heated in the heat exchanger guided by the first combustion gas supply pipe.A gas turbine apparatus according to another embodiment includes: a casing; a burner provided in the casing to combust fuel and oxidant; a cylinder provided in a longitudinal direction between the casing and the burner, the cylinder partitioning a space between the casing and the burner into an exterior space and an interior space; a turbine rotated by combustion gas from the burner and discharging it; a heat exchanger cooling the combustion gas discharged from the turbine to form a cooled combustion gas and heating a part of the cooled combustion gas; a first combustion gas supply pipe guiding the part of the cooled combustion gas heated in the heat exchanger to the interior space; a flow channel formed in a casing wall having an inner surface and an outer surface, the flow channel being formed between the inner surface and the outer surface of the casing wall, the flow channel being formed along the inner surface and the outer surface of the casing, the flow channel communicating with the exterior; and a second combustion gas supply pipe that supplies another part of the cooled combustion gas cooled in the heat exchanger to the flow channel.BRIEF DESCRIPTION OF THE DRAWINGSFIG. 1 is a system diagram of a gas turbine apparatus of a first embodiment. FIG. 2 is a view schematically showing a vertical section of a combustor and a combustor casing provided in the gas turbine apparatus of the first embodiment. FIG. 3 is a schematic view showing a vertical section of the combustor and the combustor casing having a different structure and provided in the gas turbine apparatus of the first embodiment. FIG. 4 is a system diagram of a gas turbine apparatus of a second embodiment. FIG. 5 is a schematic view showing a vertical section of a combustor and a combustor casing provided in the gas turbine apparatus of the second embodiment. FIG. 6 is a cross section corresponding to an A-A cross section of FIG. 5, and is a view showing a part of another flow passage in the combustor casing of the gas turbine apparatus of the second embodiment. FIG. 7 is a cross section corresponding to a B-B cross section of FIG. 5, and is a view showing a part of another flow passage in the combustor casing of the gas turbine apparatus of the second embodiment. FIG. 8 is a system diagram of a conventional gas turbine apparatus. FIG. 9 is a view schematically showing a vertical section of a combustor provided in the conventional gas turbine apparatus.DETAILED DESCRIPTIONHereinafter, embodiments of the present invention will be described with reference to the drawings.(First Embodiment)FIG. 1 is a system diagram of a gas turbine apparatus 10 of a first embodiment. As shown in FIG. 1, the gas turbine apparatus 10 includes a combustor 20 that burns fuel and oxidant, a pipe 40 that supplies fuel to the combustor 20, and a pipe 41 that supplies oxidant to the combustor 20.The pipe 40 includes a flow control valve 21 that controls a flow rate of the fuel to be supplied to the burner 20. Here, for example, hydrocarbon such as methane and natural gas is used as the fuel. Moreover, for example, coal gasification fuel gas containing carbon monoxide, hydrogen, and the like can also be used as the fuel.The pipe 41 includes a flow control valve 22 that controls a flow rate of the oxidizing agent supplied to the burner 20. Moreover, a compressor 23 is provided on the pipe 41 that compresses the oxidizing agent. Oxygen separated from the atmosphere by an air separator (not shown) is used as the oxidizing agent. The oxidizing agent flowing through the pipe 41 is heated by flowing through a heat exchanger 24 described later, and is supplied to the burner 20.The fuel and the oxidant that are passed through the burner 20 cause reaction (combustion) in a combustion region and are converted into combustion gas. Here, it is preferable that no excess oxidant (oxygen) or fuel remains in the combustion gas discharged from the combustor 20 in the gas turbine apparatus 10. Accordingly, the flow rates of the fuel and the oxidizing agent are controlled to give, for example, a stoichiometric mixing ratio (equivalent ratio 1). Note that the equivalence ratio mentioned herein is an equivalence ratio (total equivalence ratio) when it is assumed that the fuel and the oxygen are mixed uniformly.The gas turbine apparatus 10 includes a turbine 25 rotated by the combustion gas discharged from the combustor 20. For example, a generator 26 is coupled to this turbine 25. The combustion gas discharged from the burner 20 mentioned here contains a combustion product consisting of the fuel and the oxidant and the carbon dioxide (combustion gas extracted with water vapor) described later supplied to the burner 20.The combustion gas discharged from the turbine 25 is sent to a pipe 42 and cooled by passing through the heat exchanger 24. At this time, the oxidizing agent flowing through the pipe 41 and the carbon dioxide flowing through the pipe 42 are heated due to the heat radiation from the combustion gas.The combustion gas that has passed through the heat exchanger 24 flows through a radiator 27, and the combustion gas flows through the radiator 27, and thereby the water vapor included in the combustion gas is removed. At this time, the water vapor in the combustion gas condenses into water. The water is discharged to the outside through a pipe 43, for example.Here, as described above, when the flow rates of the fuel and the oxidizing agent are controlled to have the stoichiometric mixing ratio (equivalent ratio 1), components of the combustion gas that has been extracted from the water vapor (dry combustion gas) are mostly carbon dioxides. Note that sometimes a small amount, for example, 0.2 or less of carbon monoxide is mixed in the combustion gas that has been extracted from the water vapor, but hereinafter, the combustion gas that has been extracted from the water vapor is simply referred to as carbon dioxide.The carbon dioxide is compressed by a compressor 28 interposed in the pipe 42 and becomes a supercritical fluid. A portion of the compressed carbon dioxide passes through the tube 42 and is heated in the heat exchanger 24. The carbon dioxide is then directed into a cylinder 80 surrounding a periphery of the burner 20. The temperature of the carbon dioxide having flowed through the heat exchanger 24 becomes about 700° C. Note that the pipe 42 that supplies this high-temperature carbon dioxide into the cylinder 80 functions as a high-temperature combustion gas supply pipe.Another portion of the compressed carbon dioxide is introduced into a pipe 44 branching from the pipe 42. The carbon dioxide introduced into the pipe 44 is controlled in terms of its flow speed by a flow control valve 29 and is conducted between a burner housing 70 and the cylinder 80 as a cooling medium. The temperature of the carbon dioxide that is introduced between the burner housing 70 and the cylinder 80 through the pipe 44 is about 400° C. Note that the pipe 44 functions as a low-temperature combustion gas supply pipe.Meanwhile, the remaining part of the compressed carbon dioxide is introduced into a pipe 45 branching from the pipe 42. The carbon dioxide introduced into the pipe 45 is controlled in flow rate by a flow control valve 30 and discharged to the outside. Note that the pipe 45 functions as an exhaust pipe. The carbon dioxide discharged to the outside can be used, for example, for EOR (Enhanced Oil Recovery) or the like on drilling fields.Next, a structure of the combustor casing 70 of the gas turbine apparatus 10 of the first embodiment will be described in detail.FIG. 2 is a view schematically illustrating a vertical section of the combustor 20 and the combustor casing 70 provided in the gas turbine apparatus 10 of the first embodiment.As shown in FIG. 2, the combustor 20 includes a fuel nozzle part 60, a combustor liner 61, and a transition piece 62 (tail pipe). The fuel nozzle part 60 sprays the fuel supplied from the pipe 40 and the oxidizing agent supplied from the pipe 41 into the combustor liner 61. For example, the fuel is sprayed from a center, and the oxidant is sprayed from a periphery of the center. The burner 20 is accommodated inside the burner housing 70.The burner housing 70 is provided along a longitudinal direction of the burner 20 so as to surround the burner 20. The burner housing 70 is divided into, for example, two parts in the longitudinal direction of the burner 20. The burner housing 70 is configured of, for example, an upstream housing 71 on an upstream side and a downstream housing 72 on a downstream side. Note that the burner housing 70 functions as a housing.The upstream housing 71 is formed of, for example, a cylinder in which one end (upstream end) is closed and the other end (downstream end) is opened. At a center of the one end, an opening 71a is formed in which the fuel nozzle part 60 is inserted. In addition, the pipe 44 is coupled to one side of the upstream casing 71. The pipe 44 is fitted on and connected to, for example, an opening 71 bformed at the side part of the upstream housing 71.The downstream housing 72 is formed of a cylinder in which both ends are opened. One end of the downstream casing 72 is connected to the upstream casing 71, and the other end of the downstream casing 72 is connected to, for example, a casing surrounding the turbine 25.As illustrated in FIG. 2, the cylinder 80 is provided, which surrounds a periphery of the burner 20 and partitions a space between the burner housing 70 and the burner 20 in the burner housing 70. A predetermined space is maintained between the burner 20 and the cylinder 80.One end (upstream end) of the cylinder 80 is closed, and an opening 81 is formed into which the fuel nozzle part 60 is inserted. The other end (downstream end) of the cylinder 80 is closed, and an opening 82 into which a downstream end of the transition piece 62 penetrates is formed.The cylinder 80 is formed by, for example, connecting a plate-shaped lid member 80 aincluding the opening 71 ato a cylindrical main body member 80 b. The cylinder 80 is assembled, for example, as described below. The fuel nozzle part 60 penetrates through the opening 71 aof the lid member 80 a. Then, the burner housing 70 including the fuel nozzle part 60 is inserted into the main body member 80b. Thereafter, the lid member 80a is connected to the main body member 80b.Note that a mounting structure of the cylinder 80 is not limited thereto. The mounting structure of the cylinder 80 is not limited as long as the cylinder 80 has a structure surrounding the periphery of the burner 20 as illustrated in FIG. 2.An inner circumferential surface of the opening 82 on the downstream side of the cylinder 80 is in contact with an outer circumferential surface on the downstream end part of the transition piece 62.In addition, the pipe 42 is coupled to a side part of an upstream side of the cylinder 80. The pipe 42 penetrates the pipe 44 coupled to the side part of the upstream housing 71 and is coupled to the side part of the cylinder 80 as illustrated in FIG. 2. A part where the pipe 42 penetrates the inside of the pipe 44 has a double pipe structure.Note that the pipe 42 is inserted into the pipe 44 through an opening 44 aformed on the pipe 44, for example. At an opening part including the opening 44 a, the pipe 42 is connected to the pipe 44. In addition, the double-pipe structure of the pipe 42 and the pipe 44 is not limited to one location, but may be provided at a plurality of locations in a circumferential direction.Here, the flow of the carbon dioxide introduced from each of the pipe 42 and the pipe 44 will be explained.The carbon dioxide introduced from the pipe 42 into the cylinder 80 flows to a downstream side at an annular space between the combustion liner 61 and the cylinder 80. At this time, the carbon dioxide cools the combustor liner 61 and the transition piece 62.The carbon dioxide is introduced into the combustor liner 61 and the transition piece 62 from, for example, holes 63, 64 of a film cooling part (porous), dilution holes 65, etc. of the combustor liner 61 and the transition piece 62.As stated above, the entire amount of carbon dioxide introduced from the tube 42 is introduced into the combustor liner 61 and the transition piece 62. Note that the carbon dioxide introduced into the combustor liner 61 and the transition piece 62 is introduced into the turbine 25 together with the combustion gas generated by the combustion.Here, the temperature of the carbon dioxide introduced from the pipe 42 is about 700° C. This temperature of the carbon dioxide is lower as compared with a temperature of the combustion gas exposed to the combustor liner 61 and the transition piece 62. Accordingly, the combustor liner 61 and the transition piece 62 can be sufficiently cooled by this carbon dioxide. Moreover, since the temperature of the carbon dioxide is about 700° C., a combustion state is not impaired due to the carbon dioxide being introduced into the combustion liner 61.As previously stated, the carbon dioxide introduced from the tube 42 is introduced into the turbine 25 without flowing out to the combustor casing 70 from the cylinder 80 surrounding the periphery of the combustor 20.Meanwhile, the low-temperature carbon dioxide flowing through the pipe 44 is guided to the double pipe composed of the pipe 42 and the pipe 44. The carbon dioxide passed through the double tube flows through the tube 44 and is passed between the burner housing 70 and the cylinder 80. Specifically, the carbon dioxide that is supplied to the double pipe flows through an annular path between the pipe 42 and the pipe 44 and is supplied between the burner housing 70 and the cylinder 80.The carbon dioxide flowing between the pipe 42 and the pipe 44 cools the connection part between the pipe 42 and the pipe 44 and the pipe 42 entering the inside of the pipe 44. In addition, the low-temperature carbon dioxide flows on a periphery of the pipe 42, and therefore, heat transfer from the pipe 42 in which the high-temperature carbon dioxide flows to the burner housing 70 is suppressed.The carbon dioxide that is guided between the burner housing 70 and the cylinder 80 flows to the downstream side at an annular space between the burner housing 70 and the cylinder 80. At this time, the carbon dioxide cools the combustor casing 70 and the cylinder 80 and also is used for cooling, for example, vanes 85 and blades 86 of the turbine 25. The temperature of the burner housing 70 becomes 400° C. or less due to cooling, for example, as stated above.As described above, the burner housing 70 is cooled by the low-temperature carbon dioxide without being exposed to the high-temperature carbon dioxide. The burner housing 70 is therefore made of, for example, Fe (iron)-based heat-resistant steel such as CrMoV steel, CrMo steel.As described above, according to the gas turbine apparatus 10 of the first embodiment, the cylinder 80 and the pipe 42 coupled to the cylinder 80 are included, and thereby the burner casing 70 is not exposed to the high-temperature carbon dioxide. In addition, the low-temperature carbon dioxide flows between the burner housing 70 and the cylinder 80, and thereby it is possible to suppress a temperature rise of the burner housing 70.The burner housing 70 can thereby consist, for example, of cost-effective Fe-based heat-resistant steel. Accordingly, it is possible to reduce the manufacturing cost of the gas turbine apparatus 10.Here, the structure of the combustor casing 70 in the gas turbine apparatus 10 of the first embodiment is not limited to the one described above. FIG. 3 is a view schematically illustrating a vertical section of the combustor 20 and the combustor casing 70 having another structure provided in the gas turbine apparatus 10 of the first embodiment.For example, when a working pressure in a gas turbine becomes high, as in a case where supercritical fluid carbon dioxide is used as part of a working fluid, it is preferable that, for example, a double casing structure of an outer casing and an inner casing is used. In FIG. 3, only an example in a case where the dual case structure is applied is illustrated.For example, as shown in FIG. 3, the burner housing 70 includes the upstream housing 71 on the upstream side and the downstream housing 72 on the downstream side. The downstream housing 72 includes an outer housing 90 and an inner housing 91 inside the outer housing 90 Moreover, a cylindrical sleeve 92 is provided on an inner periphery between the outer housing 90 and the inner housing 91 along a longitudinal direction of the burner 20.Between the sleeve 92 and the inner housing 91, for example, an annular seal ring 93 is installed. The provision of the seal ring 93 prevents the carbon dioxide from leaking between the outer casing 90 and the inner casing 91. Note that here, the outer casing 90 and the sleeve 92 are connected to a downstream end surface of the upstream casing 71.In a case where the above configuration is included, the low-temperature carbon dioxide that is guided between the burner housing 70 and the cylinder 80 flows to the downstream side between the cylinder 80 and the upstream housing 71, the sleeve 92, and the inner housing 91. At this time, the low temperature carbon dioxide cools the upstream housing 71, the cylinder 80, the sleeve 92, and the inner housing 91.Accordingly, the upstream housing 71, the sleeve 92, and the inner housing 91 may be made of, for example, the inexpensive Fe-based heat-resistant steel. Note that the outer case 90 provided on an outer circumferential side as the sleeve 92 and the inner case 91 may also be made of the low-cost Fe-based heat-resistant steel.(Second Embodiment)FIG. 4 is a system diagram of a gas turbine apparatus 11 of a second embodiment. FIG. 5 is a view schematically illustrating a vertical section of the combustor 20 and the combustor casing 70 provided in the gas turbine apparatus 11 of the second embodiment. Note that the same constituent elements as those of the gas turbine apparatus 10 of the first embodiment are denoted by the same reference numerals, and redundant descriptions have been omitted or simplified.As shown in FIG. 4, a portion of the carbon dioxide compressed by the compressor 28 flows through the pipe 42 and is heated in the heat exchanger 24. The carbon dioxide is then directed to an interior 100 which is divided by a cylinder 130. Note that the pipe 42 functions as a high temperature combustion gas supply pipe.Another portion of the compressed carbon dioxide is introduced into the pipe 44 which branches from the pipe 42. The tube 44 is coupled to the torch housing 70 and defines the interior 100. Note that the pipe 44 is coupled to a flow channel formed at a thick inner part of the burner housing 70 that forms the internal space 100. This will be described in detail later.Accordingly, the carbon dioxide introduced into the pipe 44 is introduced into the flow passage as a cooling medium. It should be noted that this flow passage communicates with an exterior 101 partitioned by the cylinder 130. Note that the pipe 44 functions as a supply pipe for low-temperature combustion gas.Next, a structure of the combustor casing 70 of the gas turbine apparatus 11 of the second embodiment will be described in detail.As shown in FIG. 5, the cylinder 130 partitioning a space is provided between the burner housing 70 and the burner 20. The cylinder 130 is provided along the longitudinal direction of the burner 20 between the burner housing 70 and the burner 20.One end (upstream end) of the cylinder 130 is opened. Apart from this, the one end of the cylinder 130 includes, for example, an annular part 131 bent toward an outer circumferential surface. An outer circumferential side 131 aof the annular part 131 is bent toward an inner circumferential surface of the upstream housing 71, for example.The other end (downstream end) of the cylinder 130 is closed, and there is formed an opening 132 into which the downstream end of the transition piece 62 penetrates. An inner circumferential surface of the opening 132 on the downstream side of the cylinder 130 is in contact with an outer circumferential surface of the downstream end part of the transition piece 62.That is, the cylinder 130 divides the space between the burner housing 70 and the burner 20 into the internal space 100 and the external space 101. The internal space 100 is a space on the side of the combustor liner 61 (the fuel nozzle part 60) side partitioned by the cylinder 130. Note that the internal space 100 is also formed by a part of an inner surface of the upstream housing 71. The exterior 101 is a space on the side of the burner housing 70 divided by the cylinder 130.The opening 71 a, into which the fuel nozzle part 60 is inserted, is formed at the center of the one end of the upstream housing 71. Apart from this, a flow channel 110 communicating with the exterior 101 is formed at a thick inner part of the upstream housing 71.The flow passage 110 communicates with the pipe 44 through an opening 74 formed at an end surface 73 of the upstream housing 71. Outlets 111 of the flow channel 110 are opened to the exterior 101. These outlets 111 are formed of, for example, slits or a plurality of holes, etc. Note that a part of the upstream housing 71 in which the flow passage 110 is included functions as a flow passage forming part 78.Here, the thick inner part of the upstream housing 71 is a thick part between an inner surface and an outer surface of the upstream housing 71.Moreover, the pipe 42 is coupled to the upstream side side side part of the upstream housing 71. The tube 42 communicates with the interior 100. That is, a location where the pipe 42 is coupled is located on the upstream side relative to a location where the annular part 131 of the cylinder 130 is connected to the inner circumferential surface of the upstream housing 71. Apart from this, the tube 42 is coupled, for example, by penetrating into the flow channel forming part 78.A structure of the flow passage 110 at the thick inner part of the upstream housing 71 is not limited to the above-mentioned structure. A structure capable of cooling the upstream housing 71 facing the internal space 100 and to which the pipe 42 is coupled by the low-temperature carbon dioxide flowing through the flow channel 110 may be used as the structure of the flow channel 110. Moreover, a structure that conducts the carbon dioxide flowing through the flow channel 110 to the exterior 101 may be used as the structure of the flow channel 110.Here, the upstream housing 71 is formed by connecting two cylindrical structures, for example, an inner structure 75 and an outer structure 76, as illustrated in FIG. 5. Specifically, the upstream housing 71 is formed as described below, for example.At a part constituting the opening 71 aat which the fuel nozzle part 60 is inserted, an annular ring 77 is sandwiched between the inner structure 75 and the outer structure 76 and welded from an inner surface side of the opening 71 a. At a part constituting each outlet 111 of the flow passage 110, an annular ring is sandwiched between the inner structure 75 and the outer structure 76 and welded from an inner surface side of the upstream housing 71. Slits, bores, etc. are formed on each annular ring constituting the outlet 111.Therefore, a gap is formed between the inner structure 75 and the outer structure 76 at a predetermined interval. That is, the flow channel 110 is formed at the thick inner part of the upstream housing 71.Subsequently, a through hole is processed for inserting the pipe 42. Then, the pipe 42 is inserted into the through hole and is welded from, for example, an inside of the upstream housing 71 and an outside of the upstream housing 71.Note that a method of forming the flow passage 110 at the thick inner part of the upstream housing 71 is not limited to the above-mentioned method. That is, other methods may be used as long as it is a method capable of forming the flow channel 110 at the thick inner part of the upstream housing 71.Here, the flow of the carbon dioxide introduced from each of the pipe 42 and the pipe 44 will be explained.The carbon dioxide introduced from the pipe 42 to the internal space 100 flows to a downstream side at an annular space between the combustion liner 61 and the cylinder 130. At this time, the carbon dioxide cools the combustor liner 61 and the transition piece 62.The carbon dioxide is introduced into the combustor liner 61 and the transition piece 62 as described in the first embodiment. At this time, the combustor liner 61 and the transition piece 62 are cooled. Note that the entire amount of the carbon dioxide introduced from the pipe 42 is introduced into the combustor liner 61 and the transition piece 62.As explained above, the carbon dioxide introduced from the pipe 42 flows out not toward the burner housing 70 side but the cylinder 130.Meanwhile, the low-temperature carbon dioxide flowing through the pipe 44 is guided to the flow channel 110 through the opening 74 of the upstream housing 71. The carbon dioxide guided to the flow channel 110 flows to the outlets 111 while propagating in the flow channel 110. At this time, the carbon dioxide cools the upstream housing 71.Besides, the carbon dioxide flowing through the flow passage 110 also flows at a periphery of the pipe 42 entering the flow passage forming part 78. Accordingly, suppressed heat transfer occurs from the pipe 42 where the high-temperature carbon dioxide flows to the upstream housing 71.The carbon dioxide guided from the outlets 111 to the exterior 101 flows to the downstream side at an annular space between the burner housing 70 and the cylinder 130. At this time, the carbon dioxide cools the burner housing 70 and the cylinder 130. In addition, this carbon dioxide is also used to cool, for example, the vanes 85 and the blades 86 of the turbine 25. The temperature of the burner housing 70 (the upstream housing 71 and the downstream housing 72) becomes 400° C. or less due to the cooling, for example, as stated above.The low-temperature carbon dioxide flows through the flow channel 110, and thereby it is possible to suppress a temperature rise of the upstream housing 71 exposed to the high-temperature carbon dioxide. In addition, the burner housing 70 facing the exterior 101 is cooled by the low-temperature carbon dioxide without being exposed to the high-temperature carbon dioxide. The burner housing 70 is therefore made of, for example, Fe (iron)-based heat-resistant steel such as CrMoV steel, CrMo steel.As stated above, according to the gas turbine apparatus 11 of the second embodiment, the flow channel 110 is included, and therefore the temperature rise on the upstream casing 71 exposed to the high-temperature carbon dioxide can be suppressed. Apart from this, the cylinder 130 is included, and thereby the burner housing 70 facing the exterior 101 is not exposed to the high temperature carbon dioxide. Apart from this, the low-temperature carbon dioxide flows on the exterior 101, and thereby the temperature rise of the burner housing 70 can be suppressed.It is therefore possible for the burner housing 70 to be constructed from, for example, inexpensive Fe (iron)-based heat-resistant steel. It is therefore possible to reduce the manufacturing cost of the gas turbine apparatus 11.Here, the structure of the flow channel 110 is not limited to the above-mentioned structure. FIG. 6 is a cross section corresponding to an A-A cross section of FIG. 5, and is a view showing a part of another flow passage 110 in the combustor casing 70 of the gas turbine apparatus 11 of the second embodiment. FIG. 7 is a cross section corresponding to a B-B cross section of FIG. 5, and is a view showing a part of another flow passage 110 in the combustor casing 70 of the gas turbine apparatus 11 of the second embodiment.As shown in FIGS. 6 and 7, a plurality of flow channel walls 120, 121, 122 may be provided on the flow channel 110. The flow channel walls 120, 121, 122 are each formed of, for example, a plate-shaped rib or the like. The height of the flow channel walls 120, 121, 122 corresponds in each case to a distance between the inner structure 75 and the outer structure 76.The flow channel wall 120 divides a space between the inner structure 75 and the outer structure 76 into, for example, a concentric plurality of flow channels as shown in FIG. 6. The flow channel 110 is divided into a left half side and a right half side by the flow channel wall 121 provided in a diametrical direction, for example.Meanwhile, a plurality of flow channel walls 122 are provided at a predetermined interval in the flow channel 110 at a side part as shown in FIG. 7. Gaps of the flow channel walls 122 provided in a circumferential direction as stated above are provided in a plurality of steps in a longitudinal direction of the flow channel 110 (longitudinal direction of the burner 20). For example, a position of the flow channel between the flow channel walls 122 in the circumferential direction is shifted with respect to a position of the flow channel of an adjacent column in the circumferential direction. It is therefore possible to prevent the carbon dioxide from flowing more linearly in the longitudinal direction without spreading in the circumferential direction.In the flow passage 110 having the above-mentioned structure, the carbon dioxide introduced from the opening 74 of the upstream housing 71 into the flow passage 110 flows from an inner side toward an outer side while flowing between the flow passages on the left half side and the right half side in the circumferential direction, as shown in FIG. 6.The carbon dioxide flowing into an outer peripheral flow channel rotates in the longitudinal direction (the longitudinal direction of the burner 20) and flows to the outlet 111. At this time, the carbon dioxide flows in the longitudinal direction while spreading at a gap between the flow channel walls 122 in the circumferential direction, as shown in FIG. 7. The carbon dioxide then flows out from the outlets 111 to the exterior 101.As mentioned above, the flow channel walls 120, 121, 122 are provided, and thereby the carbon dioxide can be securely passed through the flow channel 110. Apart from this, the carbon dioxide flows into the flow channel between the flow channel walls 120, 121, and thereby a flow velocity increases compared to a case where the flow channel walls 120, 121 are not provided. It is thereby possible to improve the heat transfer. It is thereby possible to securely cool the upstream housing 71.Note that an arrangement structure of the flow passage walls 120, 121, 122 is not limited to the above-mentioned structure. A structure that guides the carbon dioxide that is guided into the flow channel 110 through the entire flow channel 110 may serve as the arrangement structure for the flow channel walls 120, 121, 122.Moreover, when the flow channel walls 122 are included, a through hole penetrating from the outer structure 76 through the flow channel walls 122 into the inner structure 75 may be formed in FIG. 7. In this case, the pipe 42 is connected to a side surface of the outer structure 76 so as to communicate with the through hole.Note that the flow passage 110 and the cylinder 130 in the second embodiment are capable of being applied to the dual housing structure as shown in FIG. 3.Here, in each of the gas turbine apparatuses 10, 11 of the above-mentioned embodiments, an example in which oxygen, which is the oxidizing agent, is supplied to the combustor 20 through the pipe 41 is illustrated, but the configuration is not limited thereto. For example, they may have a structure in which a part of the carbon dioxide compressed by the compressor 28 is supplied to the pipe 41.In this case, a new branch pipe from the pipe 42 is provided on the downstream side of the compressor 28. Referring to FIG. 1, this branched pipe is coupled to the pipe 41 between the flow control valve 22 and the heat exchanger 24, for example. That is, mixed gas consisting of the oxidizing agent and the carbon dioxide is supplied to the burner 20. Note that the mixed gas is heated by flowing through the heat exchanger 24.Also in the aforementioned structure, an operation and an operation similar to the operation and the operation in the gas turbine apparatuses 10, 11 of the above-described embodiments can be achieved.According to the embodiments described above, it is possible that the housing provided around the burner is made of cost-effective materials.While certain embodiments have been described, these embodiments are exemplary only and are not intended to limit the scope of the inventions. The novel embodiments described herein may, in fact, be embodied in a variety of other forms; moreover, various omissions, substitutions and changes in the form of the embodiments described herein may be made without departing from the spirit of the invention. The accompanying claims and their equivalents are intended to cover such embodiments or modifications as fall within the spirit of the invention.EXPLANATION OF REFERENCE NUMERALS10, 11 .. Gas turbine Installation, 20,... Burners 21, 22, 29, 30... Flow control valve, 23... Compressor, 24... Heat Exchanger, 25... Turbine, 26... Generator, 27... Cooler, 28... Compressors 40, 41, 42, 43, 44, 45... Tube 44a, 74, 81, 82... Aperture 60... Fuel nozzle member 61... Combustion Chamber Insert, 62... Transition piece, 63, 64... Bore 65... Dilution well, 70... Burner Casing, 71... Upstream Casing, 71a, 71b, 132... Opening, 72... Downstream Housing, 73... End Surface, 75... Internal structure, 76... Outer structure, 77... annular ring, 78... Flow channel forming part, 80, 130... Cylinder 80a... Lid member, 80b... Main body member, 85... Guide vane, 86... Moving blade, 90... Outer casing, 91... Inner Housing, 92... Sleeve 93... Sealing ring, 100... Inner space, 101... Exterior, 110... Flow channel, 111... Outlet, 120, 121, 122... Flow channel wall, 131... Annular part, 131a... Outer circumferential surface

Claims

A gas turbine apparatus (10) comprising: a casing (70; 71, 72); a burner (20) provided in the casing (70) to combust fuel and oxidant, the burner (20) having a fuel nozzle part (60), a combustor liner (61), and a transition piece (62), the fuel nozzle part (60) being provided at an upstream end portion of the combustor liner (61), the transition piece (62) being connected to a downstream end portion of the combustor liner (61); a cylinder (80) surrounding a periphery of the burner (20) to form a first annular space and a second annular space, the cylinder (80) having a lid member (80a) at an upstream end, the lid member (80a) being penetrated by the fuel nozzle part (60), the lid member (80a) closing the upstream end of the cylinder (80), a downstream end of the cylinder (80) being connected to an outer peripheral surface of the transition piece (62), the downstream end of the cylinder (80) being closed, the first annular space being formed between the cylinder (80) and the burner (20), the second annular space being formed between the housing (70) and the cylinder (80); a turbine (25) rotated by combustion gas from the burner (20) and discharging it; a heat exchanger (24) cooling the combustion gas discharged from the turbine (25) to form a cooled combustion gas and heating a part of the cooled combustion gas; a first combustion gas supply pipe (42) penetrating the housing (70) and the cylinder (80) for guiding the part of the cooled combustion gas heated in the heat exchanger (24) into the first annular space, and a second combustion gas supply pipe (44) surrounding the first combustion gas supply pipe (42) guiding another part of the cooled combustion gas cooled in the heat exchanger (24) to the second annular space, wherein a temperature of the other part of the cooled combustion gas cooled in the heat exchanger (24) guided by the second combustion gas supply pipe (44) is lower than a temperature of the part of the cooled combustion gas heated in the heat exchanger (24) guided by the first combustion gas supply pipe (42).The gas turbine apparatus according to claim 1, wherein the first combustion gas supply pipe (42) penetrates inside the second combustion gas supply pipe (44), the first combustion gas supply pipe (42) and the second combustion gas supply pipe (44) form a double pipe structure, the second combustion gas supply pipe (44) is coupled to the casing (70), and the other part of the cooled combustion gas flowing through the second combustion gas supply pipe (44) flows between the first combustion gas supply pipe (42) and the second combustion gas supply pipe (44) to be guided to the second annular space.A gas turbine apparatus (11) comprising: a casing (70; 71, 72); a burner (20) provided in the casing (70) to combust fuel and oxidant; a cylinder (130) provided in a longitudinal direction between the casing (70) and the burner (20), the cylinder (130) dividing a space between the casing (70) and the burner (20) into an exterior space (101) and an interior space (100); a turbine (25) rotated by combustion gas from the burner (20) and discharging it; a heat exchanger (24) cooling the combustion gas discharged from the turbine (25) to form a cooled combustion gas and heating a part of the cooled combustion gas; a first combustion gas supply pipe (42) that supplies the part of the cooled combustion gas heated in the heat exchanger (24) to the interior space (100); a flow channel (110) formed in a casing wall having an inner surface and an outer surface, the flow channel (110) being formed between the inner surface and the outer surface of the casing wall, the flow channel (110) being formed along the inner surface and the outer surface of the casing wall, the flow channel (110) communicating with the exterior space (101); and a second combustion gas supply pipe (44) that supplies another part of the cooled combustion gas cooled in the heat exchanger (24) to the flow channel (110).The gas turbine apparatus according to claim 3, wherein the first combustion gas supply pipe (42) is coupled to the casing (70) in which the flow channel (110) is included by penetrating into a flow channel forming part (78).

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