JP2016008590A - Gas turbine facility - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a gas turbine facility capable of configuring a casing provided around a combustor out of an expensive material.SOLUTION: A gas turbine facility in an embodiment comprises: a combustor 20 provided in a combustor casing 70, and burning fuel and oxidant; a cylindrical body 80 separating a space between the combustor casing 70 and the combustor 20; and a turbine 25 revolving by flue gas discharged from the combustor 20. The gas turbine facility further comprises: a heat exchanger cooling the flue gas discharged from the turbine 25; a pipe 42 heating a part of the flue gas cooled by the heat exchanger through the heat exchanger and introducing the flue gas into a space between the combustor 20 and the cylindrical body 80; a pipe 44 introducing the other part of the flue gas cooled by the heat exchanger into a space between the combustor casing 70 and the cylindrical body 80; and a pipe discharging a remainder of the flue gas cooled by the heat exchanger to outside.

Description

  Embodiments described herein relate generally to gas turbine equipment.

  Increasing the efficiency of power plants is advancing due to demands such as carbon dioxide reduction and resource saving. Specifically, the working fluids of gas turbines and steam turbines are being actively heated and combined cycles are being promoted. Research and development is also underway for carbon dioxide recovery technology.

  FIG. 6 is a system diagram of a conventional gas turbine facility 300 that circulates a part of carbon dioxide generated in a combustor as a working fluid. FIG. 7 is a view schematically showing a longitudinal section of a combustor 313 provided in the conventional gas turbine equipment 300.

  As shown in FIG. 6, in the conventional gas turbine equipment 300, oxygen separated from an air separator (not shown) is introduced into a pipe 340. The oxygen is boosted by the compressor 310 and the flow rate is controlled by the flow rate adjustment valve 311. Oxygen that has passed through the flow rate adjusting valve 311 is heated by the heat exchanger 312 by receiving heat from combustion gas, which will be described later, and supplied to the combustor 313.

  The fuel is guided to the pipe 341 from a fuel supply source (not shown). The flow rate of the fuel is adjusted by the flow rate adjustment valve 314 and supplied to the combustor 313. This fuel is a hydrocarbon.

  In the combustor 313, as shown in FIG. 7, the oxygen supplied from the pipe 340 and the fuel supplied from the pipe 341 are introduced into the combustion region. Then, oxygen and fuel undergo a combustion reaction to generate combustion gas. The combustion gas contains carbon dioxide and water vapor. The flow rates of the fuel and oxygen are adjusted so as to obtain a stoichiometric mixture ratio (theoretical mixture ratio) in a state where they are completely mixed.

  Combustion gas generated by the combustor 313 is introduced into the turbine 315. As shown in FIG. 6, for example, a generator 319 is connected to the turbine 315. The combustion gas that has performed expansion work in the turbine 315 passes through the heat exchanger 312. At this time, heat is released, and oxygen flowing through the pipe 340 described above and carbon dioxide flowing through the pipe 343 described later are heated. The combustion gas that has passed through the heat exchanger 312 further passes through the heat exchanger 316. When passing through the heat exchanger 316, the water vapor in the combustion gas is condensed into water. Water is discharged outside through the pipe 342.

  The carbon dioxide separated from the water vapor is pressurized by a compressor 317 interposed in the pipe 343 and becomes a supercritical fluid. A part of the pressurized carbon dioxide is introduced into a pipe 344 branched from the pipe 343. The flow rate of the carbon dioxide introduced into the pipe 344 is adjusted by the flow rate adjustment valve 318 and extracted outside.

  On the other hand, the remainder of carbon dioxide flows through the pipe 343. The carbon dioxide is heated in the heat exchanger 312 and supplied into the combustor casing 350 that houses the combustor 313 as shown in FIG. The temperature of the carbon dioxide that has passed through the heat exchanger 312 is about 700 ° C. Here, the combustor casing 350 includes an upstream casing 351a and a downstream casing 351b.

  The carbon dioxide led into the upstream casing 351a flows toward the turbine 315 between the downstream casing 351b, the combustor liner 352, and the transition piece 353 (tail tube). In this way, carbon dioxide other than that discharged from the pipe 344 circulates in the system.

  As the carbon dioxide flows between the downstream casing 351b and the combustor liner 352 and transition piece 353, the carbon dioxide cools the combustor liner 352 and transition piece 353. Such cooling is performed by, for example, porous membrane cooling. As shown in FIG. 7, a part of the carbon dioxide is introduced into the combustor liner 352 and the transition piece 353 from the holes 354 and 356 of the porous film cooling unit, the dilution hole 355, and the like. The carbon dioxide is also used for cooling the stationary blade 360 and the moving blade 361 of the turbine 315.

  The carbon dioxide introduced into the combustor liner 352 or the transition piece 353 is introduced into the turbine 315 together with the combustion gas generated by the combustion.

  Here, since the upstream casing 351a and the downstream casing 351b are exposed to high-temperature carbon dioxide, they are made of an expensive Ni-based alloy.

JP 2000-337107 A

  As described above, in the conventional gas turbine facility 300, the upstream casing 351a and the downstream casing 351b that are exposed to high-temperature carbon dioxide must be made of an expensive Ni-based alloy. Therefore, the manufacturing cost of gas turbine equipment increases.

  The problem to be solved by the present invention is to provide a gas turbine facility in which a casing provided around a combustor can be made of an inexpensive material.

  The gas turbine equipment of the embodiment is provided in a casing, and combustors that burn fuel and oxidant, a cylinder that partitions a space between the casing and the combustors, and exhausted from the combustors. And a turbine rotated by combustion gas. Furthermore, the gas turbine equipment includes a heat exchanger that cools the combustion gas discharged from the turbine, and a part of the combustion gas cooled by the heat exchanger is heated through the heat exchanger, and the combustor A high-temperature combustion gas supply pipe that leads between the casing and the cylinder, and a high-temperature combustion gas supply pipe that leads the other part of the combustion gas cooled by the heat exchanger between the casing and the cylinder And a discharge pipe for discharging the remainder of the combustion gas cooled by the heat exchanger to the outside.

It is a distribution diagram of gas turbine equipment of a 1st embodiment. It is the figure which showed typically the longitudinal cross-section of the combustor and combustor casing which are provided in the gas turbine equipment of 1st Embodiment. It is the figure which showed typically the longitudinal cross-section of the combustor provided in the gas turbine equipment of 1st Embodiment, and the combustor casing of another structure. It is the figure which showed typically the longitudinal cross-section of the combustor and combustor casing which are provided in the gas turbine equipment of 2nd Embodiment. It is a figure which shows the AA cross section of FIG. It is a systematic diagram of the conventional gas turbine equipment which circulates a part of carbon dioxide produced | generated in the combustor as a working fluid. It is the figure which showed typically the longitudinal cross-section of the combustor provided in the conventional gas turbine equipment.

  Hereinafter, 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 facility 10 according to a first embodiment. As shown in FIG. 1, the gas turbine facility 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. I have.

  The pipe 40 is provided with a flow rate adjusting valve 21 that adjusts the flow rate of the fuel supplied to the combustor 20. Here, hydrocarbons such as methane and natural gas are used as the fuel. Further, as the fuel, for example, a coal gasification gas fuel containing carbon monoxide and hydrogen can be used.

  The pipe 41 is provided with a flow rate adjusting valve 22 that adjusts the flow rate of the oxidant supplied to the combustor 20. The pipe 41 is provided with a compressor 23 that boosts the oxidant. As the oxidant, oxygen separated from the atmosphere by an air separation device (not shown) is used. The oxidant flowing through the pipe 41 passes through the heat exchanger 24 described later, is heated, and is supplied to the combustor 20.

  The fuel and oxidant guided to the combustor 20 cause a combustion reaction in the combustion region and become combustion gas. Here, in the gas turbine facility 10, it is preferable that surplus oxidant (oxygen) and fuel do not remain in the combustion gas discharged from the combustor 20. Therefore, the flow rates of the fuel and the oxidant are adjusted to be, for example, a stoichiometric mixture ratio (equivalent ratio 1). In addition, the equivalent ratio here is an equivalent ratio (equivalent ratio in overall) when it is assumed that the fuel and oxygen are uniformly mixed.

  The gas turbine facility 10 includes a turbine 25 that is rotated by combustion gas discharged from the combustor 20. For example, a generator 26 is connected to the turbine 25. The combustion gas discharged from the combustor 20 here is a combustion product generated by the fuel and the oxidant, and is supplied to the combustor 20 and discharged from the combustor 20 together with the combustion product, which will be described later. It contains carbon dioxide (combustion gas from which water vapor has been removed).

  The combustion gas discharged from the turbine 25 is guided to the pipe 42 and is cooled by passing through the heat exchanger 24. At this time, the oxidant flowing through the pipe 41 and the carbon dioxide flowing through the pipe 42 described later are heated by heat radiation from the combustion gas.

  The combustion gas that has passed through the heat exchanger 24 further passes through the heat exchanger 27. When the combustion gas passes through the heat exchanger 27, water vapor contained in the combustion gas is removed. In addition, the water vapor | steam in combustion gas is condensed by passing the heat exchanger 27, and turns into water. For example, water is discharged to the outside through the pipe 43.

  Here, as described above, when the flow rates of the fuel and the oxidant are adjusted so as to have a stoichiometric mixing ratio (equivalent ratio 1), the component of the combustion gas from which water vapor has been removed (dry combustion gas) is almost equal to dioxide. Carbon. The combustion gas from which water vapor has been removed may contain, for example, a trace amount of carbon monoxide of 0.2% or less. Hereinafter, the combustion gas from which water vapor has been removed is simply referred to as carbon dioxide.

  Carbon dioxide is pressurized by the compressor 28 interposed in the pipe 42 and becomes a supercritical fluid. A part of the pressurized carbon dioxide flows through the pipe 42 and is heated in the heat exchanger 24. The carbon dioxide is introduced into a combustor casing 70 that houses the combustor 20 and will be described later. The temperature of the carbon dioxide that has passed through the heat exchanger 24 is about 700 ° C. The pipe 42 that guides the high-temperature carbon dioxide to the combustor casing 70 functions as a high-temperature combustion gas supply pipe.

  Another part of the pressurized carbon dioxide is introduced into a pipe 44 branched from the pipe 42. The flow rate of the carbon dioxide introduced into the pipe 44 is adjusted by the flow rate adjusting valve 29 and is introduced into the combustor casing 70 as a cooling medium. The temperature of carbon dioxide led into the combustor casing 70 by the pipe 44 is about 400 ° C. The pipe 44 functions as a low-temperature combustion gas supply pipe.

  On the other hand, the remainder of the pressurized carbon dioxide is introduced into the pipe 45 branched from the pipe 42. The flow rate of the carbon dioxide introduced into the pipe 45 is adjusted by the flow rate adjusting valve 30 and is discharged to the outside. The pipe 45 functions as a discharge pipe. The carbon dioxide discharged to the outside can be used, for example, for EOR (Enhanced Oil Recovery) employed at oil mining sites.

  Next, the structure of the combustor casing 70 of the gas turbine equipment 10 of the first embodiment and the flow of carbon dioxide in the combustor casing 70 will be described.

  FIG. 2 is a diagram schematically showing a longitudinal section of the combustor 20 and the combustor casing 70 provided in the gas turbine equipment 10 of the first embodiment.

  As shown in FIG. 2, the combustor 20 includes a fuel nozzle portion 60, a combustor liner 61, and a transition piece 62 (tail tube). The fuel nozzle unit 60 ejects the fuel supplied from the pipe 40 and the oxidant supplied from the pipe 41 into the combustor liner 61. For example, fuel is ejected from the center, and oxidant is ejected from the surroundings. The combustor 20 is accommodated in the combustor casing 70.

  The combustor casing 70 is provided along the longitudinal direction of the combustor 20 (left-right direction in FIG. 2) so as to surround the combustor 20. The combustor casing 70 is divided into two in the longitudinal direction of the combustor 20, for example. The combustor casing 70 includes, for example, an upstream casing 71 on the upstream side and a downstream casing 72 on the downstream side. The combustor casing 70 functions as a casing.

  The upstream casing 71 is configured by a cylindrical body such as a cylinder with one end (upstream side) closed and the other end (downstream side) opened, for example. At the center of one end, an opening 71a for inserting the fuel nozzle portion 60 is formed. As shown in FIG. 2, a pipe 42 and a pipe 44 are connected to the upstream casing 71. For example, the pipe 42 is connected to the upstream casing 71 on the upstream side of the pipe 44. In addition, the connection part of the piping 42 and the piping 44, and the upstream casing 71 is not restricted to one place, You may own two or more in the circumferential direction.

  The downstream casing 72 is configured by a cylindrical body having both ends opened. One end of the downstream casing 72 is connected to the upstream casing 71, and the other end is connected to a casing surrounding the turbine 25, for example.

  As shown in FIG. 2, a cylinder 80 that partitions this space is provided between the combustor casing 70 and the combustor 20. The cylinder 80 is provided between the combustor casing 70 and the combustor 20 along the longitudinal direction of the combustor 20. That is, the cylinder 80 divides the space between the combustor casing 70 and the combustor 20 into an inner diameter side and an outer diameter side.

  The upstream end 80a of the cylindrical body 80 is connected to the inner peripheral surface of the upstream casing 71 on the downstream side of the position where the pipe 42 is connected and on the upstream side of the position where the pipe 44 is connected. Yes. On the other hand, the downstream end portion 80 b of the cylindrical body 80 is connected to the outer peripheral surface of the downstream end portion of the transition piece 62.

  That is, the cylinder body 80 is provided so that low-temperature carbon dioxide introduced from the pipe 44 flows between the combustor casing 70 and the cylinder body 80. The cylinder 80 is provided so that high-temperature carbon dioxide introduced from the pipe 42 flows between the combustor 20 and the cylinder 80. Thereby, the carbon dioxide introduced from the pipe 42 and the carbon dioxide introduced from the pipe 44 can be separated and flowed.

  Carbon dioxide introduced from the piping 42 flows while cooling 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 the combustor liner 61 and the transition piece 62, for example, through the holes 63 and 64 of the porous film cooling unit and the dilution hole 65. As described above, the entire amount of carbon dioxide introduced from the pipe 42 is introduced into the combustor liner 61 and the transition piece 62. 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 carbon dioxide introduced from the pipe 42 is about 700 ° C. The temperature of the carbon dioxide is lower than the temperature of the combustion gas to which the combustor liner 61 and the transition piece 62 are exposed. Therefore, the combustor liner 61 and the transition piece 62 can be sufficiently cooled. Furthermore, since the temperature of carbon dioxide is about 700 ° C., even if carbon dioxide is introduced into the combustor liner 61, the combustion reaction is not deteriorated.

  On the other hand, carbon dioxide introduced from the pipe 44 flows while cooling a part of the upstream casing 71, the downstream casing 72, and the cylindrical body 80. The carbon dioxide is also used for cooling the stationary blades 85 and the moving blades 86 of the turbine 25, for example. In this case, the temperature of the downstream casing 72 is, for example, 400 ° C. or less.

  In the combustor casing 70 having such a configuration, the upstream casing 71 has a portion exposed to high-temperature carbon dioxide. Therefore, the upstream casing 71 is made of, for example, a Ni (nickel) based alloy. On the other hand, the downstream casing 72 is cooled by low temperature carbon dioxide without being exposed to high temperature carbon dioxide. Therefore, the downstream casing 72 is made of Fe (iron) based heat resistant steel such as CrMoV steel or CrMo steel.

  Moreover, the part exposed to high temperature carbon dioxide decreases in the upstream casing 71 by making the connection part of the piping 42 and the piping 44 into the upstream part of the upstream casing 71, and the part exposed to cold carbon dioxide Will increase. In this case, similarly to the downstream casing 72, the upstream casing 71 can be made of Fe-based heat resistant steel.

  As described above, according to the gas turbine equipment 10 of the first embodiment, high-temperature carbon dioxide and low-temperature carbon dioxide can be introduced into the combustor casing 70 surrounding the combustor 20. In addition, by providing the cylinder 80, low-temperature carbon dioxide can flow between the combustor casing 70 and the cylinder 80, and high-temperature carbon dioxide can flow between the combustor 20 and the cylinder 80. . Thereby, at least a part of the combustor casing 70 can be made of, for example, inexpensive Fe-based heat-resistant steel. Therefore, the manufacturing cost of the gas turbine equipment 10 can be reduced.

  Here, the configuration of the combustor casing 70 in the gas turbine equipment 10 of the first embodiment is not limited to the above. FIG. 3 is a diagram schematically showing a longitudinal section of the combustor 20 provided in the gas turbine equipment 10 of the first embodiment and a combustor casing 70 of another configuration.

  For example, when the operating pressure of the gas turbine becomes high as in the case where carbon dioxide, which is a supercritical fluid, is used as a part of the working fluid, it is preferable to employ, for example, a double casing structure of an outer casing and an inner casing. . FIG. 3 shows an example when such a double casing structure is adopted.

  As shown in FIG. 3, the combustor casing 70 includes an upstream casing 71 on the upstream side and a downstream casing 72 on the downstream side. The downstream casing 72 includes an outer casing 90 and an inner casing 91 inside thereof. Further, a cylindrical sleeve 92 is provided along the longitudinal direction of the combustor 20 on the inner periphery between the outer casing 90 and the inner casing 91. Further, for example, an annular seal ring 93 is fitted between the sleeve 92 and the inner casing 91. By providing the seal ring 93, leakage of carbon dioxide from between the outer casing 90 and the inner casing 91 is prevented. Here, the outer casing 90 and the sleeve 92 are connected to the downstream end face of the upstream casing 71.

  When such a configuration is provided, the low-temperature carbon dioxide introduced from the pipe 44 flows while cooling a part of the upstream casing 71, the outer casing 90, the inner casing 91, the sleeve 92, and the cylindrical body 80. Therefore, the outer casing 90, the inner casing 91, the sleeve 92, and the cylinder 80 can be made of, for example, inexpensive Fe-based heat resistant steel.

(Second Embodiment)
FIG. 4 is a diagram schematically showing a longitudinal section of the combustor 20 and the combustor casing 70 provided in the gas turbine equipment 10 of the second embodiment. FIG. 5 is a diagram schematically showing an AA cross section of FIG. 4. In addition, the same code | symbol is attached | subjected to the same component of the gas turbine equipment 10 of 1st Embodiment, and the overlapping description is abbreviate | omitted or simplified. Moreover, the system diagram of the gas turbine equipment 10 of the second embodiment is the same as the system diagram of the gas turbine equipment 10 of the first embodiment.

  As shown in FIG. 4, the combustor casing 70 is provided along the longitudinal direction of the combustor 20 (the left-right direction in FIG. 4) so as to surround the combustor 20. The combustor casing 70 is divided into two in the longitudinal direction of the combustor 20, for example. The combustor casing 70 includes, for example, an upstream casing 71 on the upstream side and a downstream casing 72 on the downstream side. The combustor casing 70 functions as a casing.

  As shown in FIG. 4, the upstream casing 71 is connected to a pipe 42 for introducing high-temperature carbon dioxide and a pipe 44 for introducing low-temperature carbon dioxide. For example, the pipe 44 is connected to the upstream casing 71 on the upstream side of the pipe 42.

  As shown in FIGS. 4 and 5, a double-pipe cylinder 100 having an internal space 103 is provided between the combustor casing 70 and the combustor 20. The cylinder 100 is provided between the combustor casing 70 and the combustor 20 along the longitudinal direction of the combustor 20. The cylindrical body 100 is a passage that guides the high-temperature carbon dioxide guided by the pipe 42 into the combustor liner 61 through the dilution hole 65, for example.

  Specifically, at one end of the cylindrical body 100, only a portion communicating with the pipe 42 is opened, and the other portion is closed. For example, a communication pipe 101 that connects the opening of the cylinder 100 and the pipe 42 is provided on one end side of the cylinder 100. Note that the communication pipe 101 is not limited to one place, and a plurality of communication pipes 101 may be provided in the circumferential direction.

  On the other hand, the other end of the cylindrical body 100 is opened only at a portion communicating with the dilution hole 65, and the other portion is closed. For example, a communication tube 102 that connects the opening of the cylinder 100 and the dilution hole 65 is provided on the other end side of the cylinder 100. For example, as shown in FIG. 5, a plurality of communication pipes 102 are provided in the circumferential direction.

  Carbon dioxide introduced from the pipe 42 passes through the communication pipe 101 and is guided to the internal space 103 of the cylindrical body 100. The carbon dioxide flows through the internal space 103 of the cylinder 100, passes through the communication pipe 102, and is introduced into the combustor liner 61 from the dilution hole 65. In this way, the entire amount of carbon dioxide introduced from the pipe 42 is introduced into the combustor liner 61 from the dilution hole 65. Therefore, the upstream casing 71 and the downstream casing 72 are not exposed to high-temperature carbon dioxide.

  In addition, since the temperature of the carbon dioxide introduced from the piping 42 is about 700 ° C., even if it is introduced into the combustor liner 61, the combustion reaction is not deteriorated. The carbon dioxide introduced into the combustor liner 61 is introduced into the turbine 25 together with the combustion gas generated by the combustion.

  On the other hand, the carbon dioxide introduced from the pipe 44 flows while cooling the upstream casing 71, the downstream casing 72, the cylindrical body 100, the combustor liner 61, and the transition piece 62. The temperature of the upstream casing 71 and the downstream casing 72 is, for example, 400 ° C. or less. And the carbon dioxide which cooled the combustor liner 61 and the transition piece 62 is used also for cooling of the stationary blade 85 of the turbine 25, and the moving blade 86, for example.

  When low-temperature carbon dioxide introduced from the piping 44 flows around the combustor 20 as described above, the combustor liner 61 and the transition piece 62 are configured to guide carbon dioxide, such as a porous film cooling unit, to the inside. Is not prepared. That is, the combustor liner 61 and the transition piece 62 are cooled by low temperature carbon dioxide flowing on the outer surface. Thus, since low temperature carbon dioxide is not introduced into the combustor liner 61, an optimal combustion reaction is maintained.

  For example, as shown in FIG. 4, a guide 110 may be provided on the outer periphery of the transition piece 62 so that carbon dioxide flows along the outer peripheral surface of the transition piece 62.

  In the combustor casing 70 having such a configuration, the upstream casing 71 and the downstream casing 72 are cooled by the low temperature carbon dioxide without being exposed to the high temperature carbon dioxide. Therefore, the upstream casing 71 and the downstream casing 72 are made of Fe-based heat-resistant steel such as CrMoV steel or CrMo steel, for example.

  As described above, according to the gas turbine equipment 10 of the second embodiment, the provision of the cylinder 100 separates the high-temperature carbon dioxide and the low-temperature carbon dioxide introduced into the combustor casing 70. Can be shed. This can prevent the combustor casing 70 from being exposed to high-temperature carbon dioxide. Therefore, the combustor casing 70 can be made of, for example, inexpensive Fe-based heat-resistant steel.

  In addition, the cylinder 100 in the above-described second embodiment can be applied instead of the cylinder 80 shown in FIG. 3 in the first embodiment.

  Here, in the gas turbine equipment 10 of the above-described embodiment, an example in which oxygen as an oxidizer is supplied to the combustor 20 via the pipe 41 is shown, but the configuration is not limited thereto. For example, a configuration may be adopted in which part of the carbon dioxide boosted by the compressor 28 is supplied into the pipe 41.

  In this case, a new pipe branched from the pipe 42 on the downstream side of the compressor 28 is provided. Referring to FIG. 1, this branched pipe is connected to the pipe 41 between the flow rate adjustment valve 22 and the heat exchanger 24, for example. That is, a mixed gas composed of an oxidant and carbon dioxide is introduced to the combustor 20. This mixed gas is heated by passing through the heat exchanger 24.

  Even in such a configuration, the same operational effects as the operational effects in the gas turbine equipment 10 of the above-described embodiment can be obtained.

  According to the embodiment described above, the casing provided around the combustor can be made of an inexpensive material.

  Although several embodiments of the present invention have been described, these embodiments are presented by way of example and are not intended to limit the scope of the invention. These novel embodiments can be implemented in various other forms, and various omissions, replacements, and changes can be made without departing from the scope of the invention. These embodiments and modifications thereof are included in the scope and gist of the invention, and are included in the invention described in the claims and the equivalents thereof.

  DESCRIPTION OF SYMBOLS 10 ... Gas turbine equipment, 20 ... Combustor, 21, 22, 29, 30 ... Flow control valve, 23, 28 ... Compressor, 24, 27 ... Heat exchanger, 25 ... Turbine, 26 ... Generator, 40, 41 , 42, 43, 44, 45 ... piping, 60 ... fuel nozzle, 61 ... combustor liner, 62 ... transition piece, 63, 64 ... hole, 65 ... dilution hole, 70 ... combustor casing, 71 ... upstream casing 72 ... downstream casing, 80, 100 ... cylindrical body, 80a, 80b ... end, 85 ... stationary blade, 86 ... moving blade, 90 ... outer casing, 91 ... inner casing, 92 ... sleeve, 93 ... seal ring, 101, 102 ... Communication pipe, 103 ... Internal space, 110 ... Guide.

Claims (6)

A combustor provided in the casing for burning fuel and oxidant;
A cylinder that separates the space between the casing and the combustor;
A turbine rotated by combustion gas discharged from the combustor;
A heat exchanger for cooling the combustion gas discharged from the turbine;
A high-temperature combustion gas supply pipe for heating a part of the combustion gas cooled by the heat exchanger through the heat exchanger and leading between the combustor and the cylinder;
A low-temperature combustion gas supply pipe for guiding another part of the combustion gas cooled by the heat exchanger between the casing and the cylindrical body;
A gas turbine facility comprising: a discharge pipe for discharging the remaining portion of the combustion gas cooled by the heat exchanger to the outside. The casing is composed of an upstream casing and a downstream casing,
The gas turbine equipment according to claim 1, wherein the high-temperature combustion gas supply pipe and the low-temperature combustion gas supply pipe are connected to the upstream casing.   The gas turbine equipment according to claim 2, wherein the high-temperature combustion gas supply pipe is connected to the upstream casing on the upstream side of the low-temperature combustion gas supply pipe. A combustor provided in the casing for burning fuel and oxidant;
A turbine rotated by combustion gas discharged from the combustor;
A heat exchanger for cooling the combustion gas discharged from the turbine;
A high-temperature combustion gas supply pipe for heating a part of the combustion gas cooled by the heat exchanger through the heat exchanger and leading to the combustor;
A passage that is provided between the casing and the combustor in a longitudinal direction and guides the combustion gas guided by the high-temperature combustion gas supply pipe into the combustor;
A low-temperature combustion gas supply pipe for guiding another part of the combustion gas cooled by the heat exchanger between the casing and the combustor;
A gas turbine facility comprising: a discharge pipe for discharging the remaining portion of the combustion gas cooled by the heat exchanger to the outside.   The gas turbine equipment according to claim 4, wherein an end portion on the downstream side of the passage communicates with a dilution hole of the combustor. The casing is composed of an upstream casing and a downstream casing,
The gas turbine equipment according to claim 4 or 5, wherein the high-temperature combustion gas supply pipe and the low-temperature combustion gas supply pipe are connected to the upstream casing.

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