JP2011137471A - Gas turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To inhibit the deterioration in output efficiency by cooling a combustor while inhibiting a pressure loss of compressed air. <P>SOLUTION: A gas turbine is constructed to obtain a rotary power by supplying fuel to compressed air compressed by a compressor 11 in the combustor 12, burning them and supplying the generated combustion gas to a turbine 13. The gas turbine includes a booster device 41 pressure-raising part of the compressed air compressed by the compressor 11, a combustor cooling device 42 cooling the combustor 12 with the compressed air pressure-raised by the booster device 41, a compressed air circulation line 46 supplying the compressed air cooling the combustor 12 to a casing of the combustor 12, and an exchanger 86 cooling the compressed air pressure-raised by the booster device 41 with the steam generated by an exhaust heat recovery boiler 84. <P>COPYRIGHT: (C)2011,JPO&INPIT

Description

  The present invention relates to a gas turbine that supplies fuel to compressed compressed air for combustion and supplies the generated combustion gas to a turbine to obtain rotational power.

  A general gas turbine is composed of a compressor, a combustor, and a turbine. The air taken in from the air intake port is compressed by the compressor to become high-temperature and high-pressure compressed air. Fuel is supplied to the compressed air and burned, and high-temperature, high-pressure combustion gas drives the turbine, and the generator connected to the turbine is driven.

  In such a gas turbine, when the combustion temperature in the combustor becomes high, nitrogen oxide (NOx) in the exhaust gas increases, and thus the combustor is provided with a cooling device. Conventional combustor cooling devices include steam cooling, air cooling, and recovery air cooling.

  The steam cooling type cooling device cools this combustor by supplying the steam generated in the exhaust heat recovery boiler to the cooling passage formed in the wall of the inner cylinder constituting the combustor. Steam is collected by a steam turbine, and air is not used for cooling, so that sufficient combustion air can be secured, low NOx can be achieved, and low temperature steam with low specific heat can be obtained. Since it is used, it can be applied to a gas turbine having a high cooling capacity and an extremely high temperature.

  The cooling device of the air cooling system cools the combustor by extracting a part of the compressed air compressed by the compressor from the passenger compartment and supplying this compressed air to the cooling passage formed in the wall of the inner cylinder. The air after cooling the combustor is ejected into the exhaust gas passage, and the combustor can be cooled with a simple structure. The recovery type air cooling system is provided with a flow sleeve on the outside of the combustor wall, and the compressed air compressed by the compressor flows from the passenger compartment air through the annular passage of the flow sleeve to cool the combustor. The air after being supplied is supplied to this combustor, and the air after cooling is recovered as combustion air, so that sufficient combustion air can be secured and NOx reduction can be achieved.

  In addition, there exists a thing described in the following patent document 1 as a cooling device of a gas turbine.

JP 2004-169484 A

  However, the various cooling devices in the gas turbine described above have problems as described below. In the cooling device of the steam cooling system, the combustor is cooled by the steam generated in the exhaust heat recovery boiler, so ancillary equipment such as steam piping for circulating the steam between the gas turbine and the exhaust heat recovery boiler is required. The structure becomes large and complicated. Further, in order to cool the gas turbine, the exhaust heat recovery boiler must be activated, and the operation control becomes complicated. In this case, the exhaust heat recovery boiler needs to be warmed up, so that the startup time is long. turn into. Furthermore, since the combustor is cooled with steam, there is a problem that the heat efficiency of the gas turbine is lost and the plant efficiency is lowered.

  In addition, in the air-cooling type cooling device, the combustor is cooled by a part of the compressed air compressed by the compressor, so that the combustion air decreases, the combustion temperature in the combustor rises, and the exhaust gas is exhausted. There is a problem that NOx in the gas increases. In an ultra-high temperature gas turbine, the passenger compartment temperature rises to a high temperature, so that an air-cooled cooling device has a low cooling capacity and is difficult to realize. Furthermore, in the recovery type air cooling system cooling device, the combustor is cooled by the compressed air compressed by the compressor, and the compressed air after cooling is supplied to the combustor, ensuring combustion air and reducing NOx. However, since the compressed air is recovered after the wall of the combustor is cooled, there is a problem that the pressure loss in the combustor is large and the turbine efficiency is lowered. Moreover, since it is necessary to provide a flow sleeve on the outer peripheral side of the inner cylinder in the combustor, the number of structural members increases and the structure becomes complicated.

  This invention solves the subject mentioned above, and it aims at providing the gas turbine which made it possible to suppress the fall of output efficiency by suppressing the pressure loss of compressed air and enabling it to cool a combustor. .

  In order to achieve the above object, the gas turbine according to the first aspect of the present invention is configured such that fuel is supplied to the compressed air compressed by the compressor by the combustor and burned, and the generated combustion gas is supplied to the turbine to rotate the power. In the gas turbine for obtaining the pressure, the pressure-increasing means for increasing the pressure of a part of the compressed air compressed by the compressor, the combustor cooling means for cooling the combustor by the compressed air pressurized by the pressure-increasing means, and cooling the combustor A first air supply means for supplying the compressed air to the combustor and a compressed air cooling means for cooling the compressed air boosted by the boosting means. The combustor cooling means is cooled by the compressed air cooling means. The combustor is cooled with compressed air, the exhaust gas discharged from the turbine is sent to a boiler to generate steam, the generated steam is sent to a steam turbine to generate power, and the cooled feed water is Provided the exhaust heat recovery means for heating back to Ira, the compressed air cooling unit is characterized in that for cooling the compressed air that is pressurized by the pressurizing unit with the steam generated in the boiler.

  In the gas turbine according to a second aspect of the present invention, the boosting means bleeds and pressurizes a part of the compressed air compressed by the compressor from the passenger compartment, while the first air supply means cools the combustor. The compressed air is returned to the passenger compartment.

  The gas turbine according to a third aspect of the present invention is characterized in that the combustor cooling means has a large number of cooling passages formed in a wall portion of an inner cylinder constituting the combustor.

  In the gas turbine according to a fourth aspect of the present invention, there is provided turbine cooling means for cooling the turbine with compressed air boosted by the pressure boosting means, and second air supply means for supplying compressed air having cooled the turbine to the combustor. It is characterized by that.

  According to the gas turbine of the first aspect of the present invention, the boosting means for boosting a part of the compressed air compressed by the compressor, the combustor cooling means for cooling the combustor with the compressed air boosted by the boosting means, and the combustion Since the first air supply means for supplying the compressed air having cooled the combustor to the combustor is provided, the compressed air compressed by the compressor is supplied to the combustor, and a part thereof is pressurized by the pressure increasing means and then burned. The combustor is cooled by the compressed air, and the combustor is cooled by the compressed air. The compressed air that has cooled the combustor is supplied to the combustor by the first air supply means, and the combustor supplies fuel to the compressed air. Then, the combustion gas generated is supplied to the turbine to obtain rotational power, and the compressed air compressed by the compressor is pressurized and then the combustor is cooled. Minimize Since the combustor can be properly cooled and the air cooled by the combustor is supplied to the combustor together with the compressed air compressed by the compressor, the combustion air does not decrease, and NOx due to an increase in the combustion temperature. An increase in discharge amount can be suppressed, and as a result, a decrease in output efficiency can be suppressed.

  According to the gas turbine of the first aspect of the present invention, the compressed air cooling means for cooling the compressed air boosted by the boosting means is provided, and the combustor cooling means is combusted by the compressed air cooled by the compressed air cooling means. Since the combustor is cooled, the compressed air can be cooled by the compressed air cooling means to lower the temperature, the combustor can be efficiently cooled, and the combustion temperature is lowered to reduce the NOx emission amount. Can do.

  According to the gas turbine of the first aspect of the present invention, the exhaust gas discharged from the turbine is sent to the boiler to generate steam, the generated steam is sent to the steam turbine to generate power, and the cooled feed water is supplied to the boiler. An exhaust heat recovery means is provided for returning to overheating and the compressed air cooling means cools the compressed air that has been boosted by the boosting means with the steam generated by the boiler, so that the steam of the exhaust heat recovery means serves as a refrigerant for cooling the compressed air. Can be used to efficiently cool the pressurized compressed air.

  According to the gas turbine of the second aspect of the present invention, the pressurizing means bleeds and pressurizes a part of the compressed air compressed by the compressor from the passenger compartment, while the first air supply means supplies the compressed air that has cooled the combustor. Since the air that has cooled the combustor is returned to the passenger compartment because it is returned to the passenger compartment, all of the compressed air compressed by the compressor is supplied to the combustor, and the combustion air does not decrease and combustion An increase in NOx emissions due to temperature rise can be suppressed.

  According to the gas turbine of the invention of claim 3, the combustor cooling means has a large number of cooling passages formed in the wall portion of the inner cylinder constituting the combustor, so that the compressed air is in the wall portion of the inner cylinder. Since the combustor is cooled by passing through a large number of cooling passages, the combustor can be efficiently cooled.

  According to the gas turbine of the fourth aspect of the present invention, the turbine cooling means for cooling the turbine with the compressed air pressurized by the pressure increasing means and the second air supply means for supplying the compressed air having cooled the turbine to the combustor are provided. Compressed air compressed by the compressor is supplied to the combustor, and a part of the compressed air is boosted by the boosting means and then sent to the combustor cooling means and the turbine cooling means. The combustor and turbine are cooled by the compressed air. The compressed air after cooling is supplied to the combustor by the first and second air supply means. In the combustor, fuel is supplied to the compressed air and burned, and the generated combustion gas is supplied to the turbine. Rotational power can be obtained, and the combustor and turbine can be properly cooled while minimizing the pressure loss of compressed air, and all the cooled air is supplied to the combustor. Because not the combustion air is reduced, it is possible to suppress an increase in NOx emissions due to an increase in combustion temperature, as a result, it is possible to suppress a decrease in power efficiency.

FIG. 1 is a schematic diagram illustrating a gas turbine according to a first embodiment of the present invention. FIG. 2 is a schematic configuration diagram illustrating a gas turbine according to the first embodiment. FIG. 3 is a schematic configuration diagram illustrating a combustor in the gas turbine according to the first embodiment. FIGS. 4-1 is the schematic showing the combustor cooling device in the gas turbine which concerns on Example 2 of this invention. FIG. 4-2 is a schematic diagram illustrating a modification of the combustor cooling device in the gas turbine of the second embodiment. FIG. 4-3 is a schematic diagram illustrating a modification of the combustor cooling device in the gas turbine of the second embodiment. FIGS. 4-4 is the schematic showing the modification of the combustor cooling device in the gas turbine of Example 2. FIGS. FIG. 5 is a schematic diagram illustrating a gas turbine according to a third embodiment of the present invention. FIG. 6 is a schematic diagram illustrating a gas turbine according to a fourth embodiment of the present invention. FIG. 7 is a schematic diagram illustrating a gas turbine according to a fifth embodiment of the present invention. FIG. 8 is a schematic diagram illustrating a gas turbine according to a sixth embodiment of the present invention. FIG. 9 is a schematic diagram illustrating a gas turbine according to a seventh embodiment of the present invention. FIG. 10 is a schematic diagram illustrating a gas turbine according to an eighth embodiment of the present invention.

  Exemplary embodiments of a gas turbine according to the present invention will be described below in detail with reference to the accompanying drawings. In addition, this invention is not limited by this Example.

  1 is a schematic diagram illustrating a gas turbine according to a first embodiment of the present invention, FIG. 2 is a schematic configuration diagram illustrating a gas turbine according to the first embodiment, and FIG. 3 illustrates a combustor in the gas turbine according to the first embodiment. It is a schematic block diagram.

  As shown in FIGS. 1 and 2, the gas turbine according to the first embodiment includes a compressor 11, a combustor 12, and a turbine 13, and a generator 14 is connected to the turbine 13. The compressor 11 has an air intake port 15 for taking in air, a plurality of stationary blades 17 and moving blades 18 are alternately arranged in a compressor casing 16, and a bleed manifold 19 is provided on the outside thereof. ing. The combustor 12 is combustible by supplying fuel to the compressed air compressed by the compressor 11 and igniting it with a burner. In the turbine 13, a plurality of stationary blades 21 and moving blades 22 are alternately arranged in a turbine casing 20.

  An exhaust chamber 23 is continuously provided in the turbine casing 20 of the turbine 13, and the exhaust chamber 23 has an exhaust diffuser 24 that is continuous with the turbine 13. A rotor (turbine shaft) 25 is positioned so as to pass through the center of the compressor 11, the combustor 12, the turbine 13, and the exhaust chamber 23, and the end on the compressor 11 side is freely rotatable by the bearing portion 26. On the other hand, the end portion on the exhaust chamber 23 side is rotatably supported by the bearing portion 27. A plurality of disk plates are fixed to the rotor 25, the rotor blades 18 and 22 are connected, and the drive shaft of the generator 14 is connected to the end on the exhaust chamber 23 side.

  Therefore, the air taken in from the air intake port 15 of the compressor 11 passes through the plurality of stationary blades 17 and the moving blades 18 and is compressed to become high-temperature and high-pressure compressed air. Combustion occurs when a predetermined fuel is supplied to the compressed air. The high-temperature and high-pressure combustion gas generated in the combustor 12 drives and rotates the rotor 25 by passing through the plurality of stationary blades 21 and the moving blades 22 constituting the turbine 13, and is connected to the rotor 25. While generating power by applying rotational power to the generator 14, the exhaust gas is converted into static pressure by the exhaust diffuser 24 in the exhaust chamber 23 and then released to the atmosphere.

  In the above-described combustor 12, as shown in FIG. 3, the combustor inner cylinder 32 is supported by the combustor outer cylinder 31, and the combustor tail cylinder 33 is connected to the tip of the combustor inner cylinder 32 to combust the combustor. A casing is constructed. In the combustor inner cylinder 32, a pilot nozzle 34 is disposed at the center thereof, and a plurality of premixing nozzles are disposed on the inner peripheral surface of the combustor inner cylinder 32 so as to surround the pilot nozzle 34 along the circumferential direction. 35 is disposed, and a pilot cone 36 is attached to the tip of the pilot nozzle 34.

  Therefore, when high-temperature and high-pressure compressed air flows from the compressor casing 16 in the compressor 11 into the combustor 12, the compressed air is mixed with the fuel injected from the main fuel rods in each premixing nozzle 35. The swirl flow of the premixed gas flows into the combustor inner cylinder 32. On the other hand, in the pilot nozzle 34, the compressed air is mixed with the fuel injected from the pilot fuel rods, and this air-fuel mixture is ignited and burned by a not-shown type fire and becomes combustion gas in the combustor inner cylinder 32. Erupts. Then, a part of the combustion gas is injected into the combustor inner cylinder 32 so as to diffuse to the surroundings with a flame, so that it flows from each premix nozzle 35 into the combustor inner cylinder 32 and the combustor tail cylinder 33. It is ignited by the premixed gas and burns.

  In the gas turbine of the present embodiment configured as described above, as shown in FIG. 1, a booster (for example, a compressor or a blower) that extracts and pressurizes a part of the compressed air compressed by the compressor 11 from the passenger compartment. ) 41 and a combustor cooling device 42 that cools the combustor 12 with the compressed air pressurized by the pressure increasing device 41, and the compressed air that has cooled the combustor 12 is supplied to the combustor 12.

  That is, the compressed air supply line 43 connected from the compressor 11 to the combustor 12 is branched in the middle to form a compressed air branch line 44, and is connected to the booster 41. The combustor cooling device 42 is, for example, a large number of cooling passages formed in the wall of the inner cylinder constituting the combustor 12, and the booster 41 is connected to the combustor cooling device 42 by the cooling air supply line 45. Has been. The combustor cooling device 42 is connected by a compressed air supply line 43 and a compressed air circulation line (first air supply means) 46, and the compressed air that has cooled the combustor 12 passes through the compressed air supply line 43. It is supplied to the combustor 12. In this case, the compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 to be supplied to the compartment of the combustor 12.

  Further, a fuel supply line 47 that supplies fuel to the combustor 12 is connected to the combustor 12. Further, the combustor 12 is connected to the turbine 13 by a combustion gas discharge line 48.

  Therefore, in the compressor 11, the taken-in air passes through the plurality of stationary blades 17 and the moving blades 18 and is compressed to become high-temperature / high-pressure compressed air and flows to the compressed air supply line 43. A part of the compressed air flowing through the compressed air supply line 43, that is, compressed air extracted from the passenger compartment is branched into the compressed air branch line 44 and supplied to the booster 41, where the pressure is further increased. The compressed air boosted by the booster 41 is supplied to the combustor cooling device 42 through the cooling air supply line 45, and is cooled by flowing in the wall of the inner cylinder constituting the combustor 12, for example. The compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 through the compressed air circulation line 46. Therefore, the entire amount of compressed air compressed by the compressor 11 is supplied to the combustor 12 through the compressed air supply line 43.

  Then, in the combustor 12, the compressed air supplied from the compressed air supply line 43 is combusted by supplying predetermined fuel from the fuel supply line 47. The high-temperature and high-pressure combustion gas generated in the combustor 12 is sent to the turbine 13 through the combustion gas discharge line 48 and passes through the plurality of stationary blades 21 and the moving blades 22 so that the rotor 25 is driven and rotated. Electricity is generated by driving the generator 14 connected to the rotor 25.

  As described above, in the gas turbine according to the first embodiment, the combustor 12 supplies fuel to the compressed air compressed by the compressor 11 and burns, and the generated combustion gas is supplied to the turbine 13 to generate rotational power. A booster 41 configured to boost a part of the compressed air compressed by the compressor 11, a combustor cooling device 42 for cooling the combustor 12 by the compressed air boosted by the booster 41, and a combustor A compressed air circulation line 46 is provided for supplying compressed air having cooled 12 to the passenger compartment of the combustor 12.

  Therefore, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and a part of the compressed air is boosted by the booster 41 and then sent to the combustor cooling device 42. The combustor 12 is cooled by the compressed air. Then, the compressed air that has cooled the combustor 12 is supplied to the combustor 12 through the compressed air circulation line 46. In the combustor 12, fuel is supplied to the compressed air and burned, and the generated combustion gas is converted into the turbine 13. To obtain rotational power. At this time, since the combustor 12 is cooled after increasing the pressure of a part of the compressed air compressed by the compressor 11, only this part of the compressed air becomes a pressure loss, and the pressure loss of the compressed air is minimized. Thus, the combustor 12 can be properly cooled. Further, since the air that has cooled the combustor 12 is returned to the compressed air supply line 43, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and the combustion air is not reduced. It is possible to suppress an increase in the NOx emission amount due to the increase in the amount of NOx. As a result, a decrease in turbine output efficiency can be suppressed.

  Further, in the gas turbine of this embodiment, the booster 41 extracts a part of the compressed air compressed by the compressor 11 from the passenger compartment to increase the pressure, while the compressed air that has cooled the combustor 12 is compressed into the compressed air circulation line. Since the entire amount of air that has cooled the combustor 12 is returned to the passenger compartment by returning to the passenger compartment of the compressor 11 by 46, the compressed air compressed by the compressor 11 can be efficiently supplied to the combustor 12. The combustion air does not decrease, and an increase in NOx emission due to an increase in combustion temperature can be suppressed.

  4-1 is a schematic diagram illustrating a combustor cooling device in a gas turbine according to a second embodiment of the present invention, and FIGS. 4-2 to 4-4 are modifications of the combustor cooling device in the gas turbine according to the second embodiment. It is the schematic showing an example. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine of the second embodiment, as shown in FIG. 4A, the combustor cooling device 51 is a large number of cooling passages formed in the wall portion of the inner cylinder 52 constituting the combustor 12. More specifically, in this combustor cooling device 51, a large number of cooling passages 53 are formed in the wall portion of the inner cylinder 52 along the longitudinal direction (flow direction of combustion gas). Further, a ring-shaped header 54 is fixed to an outer peripheral portion of the inner cylinder 52 in the longitudinal direction, and a cooling air supply pipe 55 as a cooling air supply line is connected to the header 54. . A large number of cooling passages 53 communicate with the cooling air supply pipe 55 through the header 54, and each end opens to the vehicle compartment 56.

  Therefore, when a part of the compressed air compressed by the compressor is supplied to the header 54 through the cooling air supply pipe 55, the compressed air passes through the cooling passages 53 of the combustor cooling device 51, thereby combustor. The compressed air that has cooled the combustor 12 is discharged to the vehicle compartment 56 and collected. Therefore, the entire amount of compressed air compressed by the compressor can be supplied to the combustor 12 through the casing 56.

  Further, in the modification of the gas turbine of the second embodiment, as shown in FIG. 4B, the combustor cooling device 61 includes a large number of cooling passages formed in the wall portion of the inner cylinder 52 constituting the combustor 12. A plurality of cooling passages 53 are formed in the wall portion of the inner cylinder 52, and a ring-shaped header 54 is fixed to the outer peripheral portion of the inner cylinder 52, and a cooling air supply pipe 55 is connected to the header 54. Yes. The multiple cooling passages 53 communicate with the cooling air supply pipe 55 through the header 54, and one end portion opens into the vehicle compartment 56, while the other end portion opens into the inner cylinder 52.

  Therefore, when a part of the compressed air compressed by the compressor is supplied to the header 54 through the cooling air supply pipe 55, the compressed air passes through the cooling passages 53 of the combustor cooling device 61 to be combustor. The compressed air that has cooled the combustor 12 is discharged to the vehicle compartment 56 and collected, and merged with the combustion gas in the inner cylinder 52. Therefore, the compressed air compressed by the compressor can be supplied to the combustor 12 through the casing 56, and the compressed air is supplied to the downstream side in the inner cylinder 52, so that the tail cylinder and the first stationary blade can be removed. Can be cooled.

  Further, in the modified example of the gas turbine of the second embodiment, as shown in FIG. 4C, the combustor cooling device 62 includes a large number of cooling passages formed in the wall portion of the inner cylinder 52 constituting the combustor 12. A plurality of cooling passages 53 are formed in the wall portion of the inner cylinder 52, and two ring-shaped headers 54 are fixed to the outer peripheral portion of the inner cylinder 52, and a cooling air supply pipe 55 is provided in each header 54. It is connected. A large number of cooling passages 53 communicate with the cooling air supply pipe 55 through the header 54, and end portions and intermediate portions open to the vehicle compartment 56.

  Accordingly, when a part of the compressed air compressed by the compressor is supplied to the header 54 through the cooling air supply pipe 55, the compressed air passes through the cooling passages 53 of the combustor cooling device 62, thereby causing the combustor. The compressed air that has cooled the combustor 12 is discharged to the vehicle compartment 56 and collected, and merged with the combustion gas in the inner cylinder 52. Therefore, the compressed air compressed by the compressor can be supplied to the combustor 12 through the casing 56, and the compressed air is supplied to the downstream side in the inner cylinder 52, so that the tail cylinder and the first stationary blade can be removed. Can be cooled.

  In the modification of the gas turbine of the second embodiment, as shown in FIG. 4-4, the combustor cooling device 63 includes a large number of cooling passages formed in the wall portion of the inner cylinder 52 constituting the combustor 12. A plurality of cooling passages 53 are formed in the wall portion of the inner cylinder 52, and a ring-shaped header 54 corresponding to the downstream end portion of the outer periphery of the inner cylinder 52 in the flow direction of the combustion gas is fixed. A cooling air supply pipe 55 is connected to the header 54. The numerous cooling passages 53 communicate with the cooling air supply pipe 55 through the header 54, and the upstream end portion in the flow direction of the combustion gas opens into the vehicle compartment 56.

  Accordingly, when a part of the compressed air compressed by the compressor is supplied to the header 54 through the cooling air supply pipe 55, the compressed air passes through the cooling passages 53 of the combustor cooling device 62, thereby causing the combustor. The compressed air that has cooled the combustor 12 is discharged to the vehicle compartment 56 and collected. For this reason, the compressed air can be efficiently cooled by flowing and cooling from the downstream side in the flow direction of the combustion gas to the upstream side.

  As described above, in the gas turbine according to the second embodiment, the combustor cooling devices 51, 61, 62, and 63 that cool the combustor 12 with the compressed air obtained by boosting a part of the compressed air compressed by the compressor are provided. As the combustor cooling devices 51, 61, 62 and 63, a large number of cooling passages 53 are provided in the wall portion of the inner cylinder 52 constituting the combustor 12.

  Therefore, when a part of the compressed air compressed by the compressor is supplied to the header 54 through the cooling air supply pipe 55, the compressed air cools the combustor 12 by passing through each cooling passage 53. The combustor 12 can be efficiently cooled with a simple configuration.

  FIG. 5 is a schematic diagram illustrating a gas turbine according to a third embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine of the third embodiment, as shown in FIG. 5, the compressor 11 is connected to the combustor 12 via the compressed air supply line 43 and is also compressed air branched off in the middle of the compressed air supply line 43. The booster 41 is connected to the booster 41 via a line 44, and the booster 41 is connected to the combustor cooler 42 via a cooling air supply line 45. The cooling air supply line 45 includes a water supply line 71. The water supply device 71 is connected to the water supply line 71. The combustor cooling device 42 is connected to a compressed air supply line 43 via a compressed air circulation line 46. Further, a fuel supply line 47 is connected to the combustor 12, and the combustor 12 is connected to the turbine 13 through a combustion gas discharge line 48.

  Therefore, the compressor 11 compresses air to generate high-temperature and high-pressure compressed air and flows to the compressed air supply line 43. A part of the compressed air flowing through the compressed air supply line 43 branches to the compressed air branch line 44 and is supplied to the booster 41, where the pressure is further increased and then flows to the cooling air supply line 45. On the other hand, the water injection device 72 injects a predetermined amount of moisture into the water supply line 71, and the moisture is added from the water supply line 71 to the compressed air flowing through the cooling air supply line 45, thereby compressing the compressed air. The cooled compressed air is supplied to the combustor cooling device 42 to cool the combustor 12. The compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 through the compressed air circulation line 46. Therefore, the entire amount of compressed air compressed by the compressor 11 is supplied to the combustor 12 through the compressed air supply line 43.

  Then, in the combustor 12, the compressed air supplied from the compressed air supply line 43 is combusted by supplying predetermined fuel from the fuel supply line 47. The high-temperature and high-pressure combustion gas generated in the combustor 12 is sent to the turbine 13 through the combustion gas discharge line 48 and passes through the plurality of stationary blades 21 and the moving blades 22 so that the rotor 25 is driven and rotated. Electricity is generated by driving the generator 14 connected to the rotor 25.

  As described above, in the gas turbine of the third embodiment, the booster 41 that boosts a part of the compressed air compressed by the compressor 11 and the combustion that cools the combustor 12 with the compressed air boosted by the booster 41. A cooler 42, a compressed air circulation line 46 that supplies compressed air that has cooled the combustor 12 to the passenger compartment of the combustor 12, and a water injection device 72 that adds moisture to the compressed air that has been pressurized by the booster 41. A water supply line 71 having

  Accordingly, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and a part of the compressed air is boosted by the booster 41, cooled by the water injection device 72, and then sent to the combustor cooling device 42. The combustor 12 is cooled by the compressed air, and the compressed air that has cooled the combustor 12 is supplied to the combustor 12 by the compressed air circulation line 46. In the combustor 12, fuel is supplied to the compressed air and burned. Then, the generated combustion gas is supplied to the turbine 13 to obtain rotational power. At this time, since a part of the compressed air compressed by the compressor 11 is pressurized and cooled before the combustor 12 is cooled, only this part of the compressed air becomes a pressure loss, and the pressure loss of the compressed air is minimized. Therefore, the combustor 12 can be appropriately cooled. Further, since the air that has cooled the combustor 12 is returned to the compressed air supply line 43, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and the combustion air is not reduced. It is possible to suppress an increase in the NOx emission amount due to the increase in the amount of NOx. Further, since the compressed air is pressurized and cooled and then supplied to the combustor cooling device 42, the temperature of the compressed air can be lowered, the combustor 12 can be cooled efficiently, and the low-temperature compressed air can be cooled. Is supplied into the combustor 12, so that the combustion temperature can be lowered and the NOx emission amount can be reduced.

  FIG. 6 is a schematic diagram illustrating a gas turbine according to a fourth embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine according to the fourth embodiment, as shown in FIG. 6, the compressor 11 is connected to the combustor 12 via the compressed air supply line 43 and is also branched in the middle of the compressed air supply line 43. The booster 41 is connected to the booster 41 via a line 44, and the booster 41 is connected to the combustor cooler 42 via a cooling air supply line 45. The cooling air supply line 45 is provided with a heat exchanger (compressed air cooling means) 81 for cooling the compressed air boosted by the booster 41, and the combustor cooling device 42 is cooled by the heat exchanger 81. The combustor 12 is cooled with the compressed air. In the exchanger 81, heat is exchanged between the compressed air by introducing the compressed air flowing through the cooling air supply line 45 and the compressed air flowing through the compressed air supply line 43. That is, the compressed air that has been compressed by the compressor 11 and then pressurized by the booster 41 and then flows to the cooling air supply line 45 is higher in temperature and pressure than the compressed air that is compressed by the compressor 11 and flows to the compressed air supply line 43. Therefore, the compressed air boosted by the booster 41 passes through the exchanger 81 and is cooled by the compressed air compressed by the compressor 11. The combustor cooling device 42 is connected to a compressed air supply line 43 via a compressed air circulation line 46. Further, a fuel supply line 47 is connected to the combustor 12, and the combustor 12 is connected to the turbine 13 through a combustion gas discharge line 48.

  Therefore, the compressor 11 compresses air to generate high-temperature and high-pressure compressed air and flows to the compressed air supply line 43. A part of the compressed air flowing through the compressed air supply line 43 branches to the compressed air branch line 44 and is supplied to the booster 41, where the pressure is further increased and then flows to the cooling air supply line 45. Then, the compressed air compressed by the compressor 11 is introduced into the heat exchanger 81 through the compressed air supply line 43, and the compressed air pressurized by the pressure increasing device 41 is supplied from the cooling air supply line 45 to the heat exchanger 81. In this heat exchanger 81, heat is exchanged between both compressed air, and the compressed air boosted by the booster 41 is cooled by the exchanger 81 and then the combustor cooling device 42. To cool the combustor 12. The compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 through the compressed air circulation line 46. Therefore, the entire amount of compressed air compressed by the compressor 11 is supplied to the combustor 12 through the compressed air supply line 43.

  Then, in the combustor 12, the compressed air supplied from the compressed air supply line 43 is combusted by supplying predetermined fuel from the fuel supply line 47. The high-temperature and high-pressure combustion gas generated in the combustor 12 is sent to the turbine 13 through the combustion gas discharge line 48 and passes through the plurality of stationary blades 21 and the moving blades 22 so that the rotor 25 is driven and rotated. Electricity is generated by driving the generator 14 connected to the rotor 25.

  As described above, in the gas turbine of the fourth embodiment, the booster 41 that boosts a part of the compressed air compressed by the compressor 11 and the combustion that cools the combustor 12 by the compressed air boosted by the booster 41. By the compressor cooling device 42, the compressed air circulation line 46 for supplying the compressed air that has cooled the combustor 12 to the passenger compartment of the combustor 12, and the compressed air compressed by the compressor 11 by the compressed air that has been pressurized by the booster 41 An exchanger 81 for cooling is provided.

  Accordingly, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and a part of the compressed air is boosted by the booster 41, cooled by the heat exchanger 81, and then sent to the combustor cooler 42. The combustor 12 is cooled by the compressed air, and the compressed air that has cooled the combustor 12 is supplied to the combustor 12 by the compressed air circulation line 46. In the combustor 12, fuel is supplied to the compressed air and burned. Then, the generated combustion gas is supplied to the turbine 13 to obtain rotational power. At this time, since a part of the compressed air compressed by the compressor 11 is pressurized and cooled before the combustor 12 is cooled, only this part of the compressed air becomes a pressure loss, and the pressure loss of the compressed air is minimized. Therefore, the combustor 12 can be appropriately cooled. Further, since the air that has cooled the combustor 12 is returned to the compressed air supply line 43, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and the combustion air is not reduced. It is possible to suppress an increase in the NOx emission amount due to the increase in the amount of NOx. Further, since the compressed air is pressurized and cooled and then supplied to the combustor cooling device 42, the temperature of the compressed air can be lowered, the combustor 12 can be cooled efficiently, and the low-temperature compressed air can be cooled. Is supplied into the combustor 12, so that the combustion temperature can be lowered and the NOx emission amount can be reduced.

  FIG. 7 is a schematic diagram illustrating a gas turbine according to a fifth embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine of the fifth embodiment, as shown in FIG. 7, the compressor 11 is connected to the combustor 12 via the compressed air supply line 43 and is also branched in the middle of the compressed air supply line 43. The booster 41 is connected to the booster 41 via a line 44, and the booster 41 is connected to the combustor cooler 42 via a cooling air supply line 45. The cooling air supply line 45 is provided with a heat exchanger (compressed air cooling means) 82 for cooling the compressed air boosted by the booster 41, and the combustor cooling device 42 is cooled by the heat exchanger 82. The combustor 12 is cooled with the compressed air. In the exchanger 82, heat is exchanged between the compressed air and the fuel by introducing the compressed air flowing through the cooling air supply line 45 and the fuel flowing through the fuel supply line 47. That is, since the compressed air that has been compressed by the compressor 11 and then pressurized by the booster 41 and then flows to the cooling air supply line 45 is hotter and higher than the fuel that flows to the fuel supply line 47, this compressed air is By passing through the exchanger 82, it is cooled by the fuel. The combustor cooling device 42 is connected to a compressed air supply line 43 via a compressed air circulation line 46. Further, a fuel supply line 47 is connected to the combustor 12, and the combustor 12 is connected to the turbine 13 through a combustion gas discharge line 48.

  Therefore, the compressor 11 compresses air to generate high-temperature and high-pressure compressed air and flows to the compressed air supply line 43. A part of the compressed air flowing through the compressed air supply line 43 branches to the compressed air branch line 44 and is supplied to the booster 41, where the pressure is further increased and then flows to the cooling air supply line 45. Then, the compressed air boosted by the booster 41 is introduced into the heat exchanger 81 through the cooling air supply line 45, and the fuel is introduced into the heat exchanger 82 through the fuel supply line 47, In this heat exchanger 82, heat is exchanged between the compressed air and the fuel, and the compressed air boosted by the booster 41 is cooled by the exchanger 82 and then supplied to the combustor cooler 42 for combustion. While the combustor 12 is cooled, the fuel is heated by the exchanger 82 and then supplied to the combustor 12. The compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 through the compressed air circulation line 46. Therefore, the entire amount of compressed air compressed by the compressor 11 is supplied to the combustor 12 through the compressed air supply line 43.

  Then, in the combustor 12, combustion is performed by supplying a predetermined fuel heated from the fuel supply line 47 to the compressed air supplied from the compressed air supply line 43. The high-temperature and high-pressure combustion gas generated in the combustor 12 is sent to the turbine 13 through the combustion gas discharge line 48 and passes through the plurality of stationary blades 21 and the moving blades 22 so that the rotor 25 is driven and rotated. Electricity is generated by driving the generator 14 connected to the rotor 25.

  As described above, in the gas turbine according to the fifth embodiment, the booster 41 that boosts a part of the compressed air compressed by the compressor 11 and the combustion that cools the combustor 12 by the compressed air boosted by the booster 41. Cooling by the cooler 42, the compressed air circulation line 46 that supplies the compressed air that has cooled the combustor 12 to the passenger compartment of the combustor 12, and the fuel that is supplied by the booster 41 to the combustor 12 Is provided.

  Accordingly, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and a part of the compressed air is boosted by the booster 41, cooled by the heat exchanger 82, and then sent to the combustor cooler 42. The combustor 12 is cooled by the compressed air, and the compressed air that has cooled the combustor 12 is supplied to the combustor 12 by the compressed air circulation line 46. In the combustor 12, fuel is supplied to the compressed air and burned. Then, the generated combustion gas is supplied to the turbine 13 to obtain rotational power. At this time, since a part of the compressed air compressed by the compressor 11 is pressurized and cooled before the combustor 12 is cooled, only this part of the compressed air becomes a pressure loss, and the pressure loss of the compressed air is minimized. Therefore, the combustor 12 can be appropriately cooled. Further, since the air that has cooled the combustor 12 is returned to the compressed air supply line 43, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and the combustion air is not reduced. It is possible to suppress an increase in the NOx emission amount due to the increase in the amount of NOx. Further, since the compressed air is pressurized and cooled and then supplied to the combustor cooling device 42, the temperature of the compressed air can be lowered, the combustor 12 can be cooled efficiently, and the low-temperature compressed air can be cooled. Is supplied into the combustor 12, so that the combustion temperature can be lowered and the NOx emission amount can be reduced. In addition, since the fuel is heated and then supplied to the combustor 12, atomization of the fuel spray is promoted, the combustion efficiency can be improved and the emission of harmful substances can be reduced, and the turbine output can be reduced. Can be improved.

  FIG. 8 is a schematic diagram illustrating a gas turbine according to a sixth embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  Although not shown, the gas turbine of the sixth embodiment is applied to a combined power generation system. In this combined power generation system, exhaust gas discharged from a gas turbine is sent to an exhaust heat recovery boiler, where steam is generated by high-temperature and high-pressure exhaust gas, and the steam turbine is driven by this steam to generate power by a generator. Here, after the steam supplied to the steam turbine is condensed by a condenser, it is returned to an exhaust heat recovery boiler as water supply by a pump and superheated.

  In the gas turbine according to the sixth embodiment applied to this combined power generation system, as shown in FIG. 8, the compressor 11 is connected to the combustor 12 via the compressed air supply line 43 and the compressed air supply line 43. The booster 41 is connected to a booster 41 via a compressed air branch line 44 that branches in the middle of the engine. The booster 41 is connected to a combustor cooler 42 via a cooling air supply line 45. The cooling air supply line 45 is provided with a heat exchanger (compressed air cooling means) 83 for cooling the compressed air boosted by the booster 41, and the combustor cooling device 42 is cooled by the heat exchanger 83. The combustor 12 is cooled with the compressed air. In this exchanger 83, the compressed air flowing through the cooling air supply line 45 and the feed water flowing through the feed water line 85 connected to the exhaust heat recovery boiler (exhaust heat recovery means) 84 are introduced, whereby the compressed air and the feed water are mixed. Heat exchange takes place between them. That is, the compressed air that has been compressed by the compressor 11 and then pressurized by the pressure increasing device 41 and then flows to the cooling air supply line 45 is more condensed than the water that is condensed by the condenser and then flows to the water supply line 85 after driving the steam turbine. Because of the high temperature and high pressure, the compressed air boosted by the pressure booster 41 passes through the exchanger 83 and is cooled by the feed water returned to the exhaust heat recovery boiler 84. The combustor cooling device 42 is connected to a compressed air supply line 43 via a compressed air circulation line 46. Further, a fuel supply line 47 is connected to the combustor 12, and the combustor 12 is connected to the turbine 13 through a combustion gas discharge line 48.

  Therefore, the compressor 11 compresses air to generate high-temperature and high-pressure compressed air and flows to the compressed air supply line 43. A part of the compressed air flowing through the compressed air supply line 43 branches to the compressed air branch line 44 and is supplied to the booster 41, where the pressure is further increased and then flows to the cooling air supply line 45. Then, the compressed air boosted by the booster 41 is introduced into the heat exchanger 83 through the cooling air supply line 45, and the feed water condensed by the condenser after driving the steam turbine passes through the feed water line 85. In this heat exchanger 83, heat exchange is performed between the compressed air and the feed water, and the compressed air boosted by the booster 41 is cooled by the exchanger 83. Then, it is supplied to the combustor cooling device 42 to cool the combustor 12. The compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 through the compressed air circulation line 46. Therefore, the entire amount of compressed air compressed by the compressor 11 is supplied to the combustor 12 through the compressed air supply line 43.

  Then, in the combustor 12, the compressed air supplied from the compressed air supply line 43 is combusted by supplying predetermined fuel from the fuel supply line 47. The high-temperature and high-pressure combustion gas generated in the combustor 12 is sent to the turbine 13 through the combustion gas discharge line 48 and passes through the plurality of stationary blades 21 and the moving blades 22 so that the rotor 25 is driven and rotated. Electricity is generated by driving the generator 14 connected to the rotor 25.

  As described above, in the gas turbine of the sixth embodiment, the booster 41 that boosts a part of the compressed air compressed by the compressor 11 and the combustion that cools the combustor 12 by the compressed air boosted by the booster 41. The cooler 42, the compressed air circulation line 46 that supplies the compressed air that has cooled the combustor 12 to the vehicle compartment of the combustor 12, and the compressed water that has been pressurized by the booster 41 is returned to the exhaust heat recovery boiler 84. And an exchanger 83 for cooling.

  Therefore, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and a part of the compressed air is boosted by the booster 41, cooled by the heat exchanger 83, and then sent to the combustor cooling device 42. The combustor 12 is cooled by the compressed air, and the compressed air that has cooled the combustor 12 is supplied to the combustor 12 by the compressed air circulation line 46. In the combustor 12, fuel is supplied to the compressed air and burned. Then, the generated combustion gas is supplied to the turbine 13 to obtain rotational power. At this time, since a part of the compressed air compressed by the compressor 11 is pressurized and cooled before the combustor 12 is cooled, only this part of the compressed air becomes a pressure loss, and the pressure loss of the compressed air is minimized. Therefore, the combustor 12 can be appropriately cooled. Further, since the air that has cooled the combustor 12 is returned to the compressed air supply line 43, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and the combustion air is not reduced. It is possible to suppress an increase in the NOx emission amount due to the increase in the amount of NOx. Further, since the compressed air is pressurized and cooled and then supplied to the combustor cooling device 42, the temperature of the compressed air can be lowered, the combustor 12 can be cooled efficiently, and the low-temperature compressed air can be cooled. Is supplied into the combustor 12, so that the combustion temperature can be lowered and the NOx emission amount can be reduced.

  FIG. 9 is a schematic diagram illustrating a gas turbine according to a seventh embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  Although the gas turbine of Example 7 is not illustrated, it is applied to the combined power generation system. In this combined power generation system, exhaust gas discharged from a gas turbine is sent to an exhaust heat recovery boiler, where steam is generated by high-temperature and high-pressure exhaust gas, and the steam turbine is driven by this steam to generate power by a generator. Here, after the steam supplied to the steam turbine is condensed by a condenser, it is returned to an exhaust heat recovery boiler as water supply by a pump and superheated.

  In the gas turbine according to the seventh embodiment applied to this combined power generation system, as shown in FIG. 9, the compressor 11 is connected to the combustor 12 via the compressed air supply line 43 and the compressed air supply line 43. The booster 41 is connected to a booster 41 via a compressed air branch line 44 that branches in the middle of the engine. The booster 41 is connected to a combustor cooler 42 via a cooling air supply line 45. Further, the cooling air supply line 45 is provided with a heat exchanger (compressed air cooling means) 86 for cooling the compressed air boosted by the booster 41, and the combustor cooling device 42 is cooled by the heat exchanger 86. The combustor 12 is cooled with the compressed air. In the exchanger 86, heat is exchanged between the compressed air and the steam by introducing the compressed air flowing through the cooling air supply line 45 and the steam flowing through the steam supply line 87 connected to the exhaust heat recovery boiler 84. Done. That is, the compressed air that has been compressed by the compressor 11 and then pressurized by the booster 41 and then flows to the cooling air supply line 45 is higher in temperature and pressure than the steam that is generated by the exhaust heat recovery boiler 84 and flows to the steam supply line 87. Therefore, the compressed air boosted by the booster 41 passes through the exchanger 86 and is cooled by the steam generated by the exhaust heat recovery boiler 84. The combustor cooling device 42 is connected to a compressed air supply line 43 via a compressed air circulation line 46. Further, a fuel supply line 47 is connected to the combustor 12, and the combustor 12 is connected to the turbine 13 through a combustion gas discharge line 48.

  Therefore, the compressor 11 compresses air to generate high-temperature and high-pressure compressed air and flows to the compressed air supply line 43. A part of the compressed air flowing through the compressed air supply line 43 branches to the compressed air branch line 44 and is supplied to the booster 41, where the pressure is further increased and then flows to the cooling air supply line 45. Then, the compressed air boosted by the booster 41 is introduced into the heat exchanger 86 through the cooling air supply line 45, and the steam generated in the exhaust heat recovery boiler 84 is heat-exchanged through the steam supply line 87. In this heat exchanger 86, heat is exchanged between the compressed air and steam, and the compressed air boosted by the booster 41 is cooled by the exchanger 86 and then combusted. Is supplied to the combustor cooling device 42 to cool the combustor 12. The compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 through the compressed air circulation line 46. Therefore, the entire amount of compressed air compressed by the compressor 11 is supplied to the combustor 12 through the compressed air supply line 43.

  Then, in the combustor 12, the compressed air supplied from the compressed air supply line 43 is combusted by supplying predetermined fuel from the fuel supply line 47. The high-temperature and high-pressure combustion gas generated in the combustor 12 is sent to the turbine 13 through the combustion gas discharge line 48 and passes through the plurality of stationary blades 21 and the moving blades 22 so that the rotor 25 is driven and rotated. Electricity is generated by driving the generator 14 connected to the rotor 25.

  As described above, in the gas turbine according to the seventh embodiment, the booster 41 that boosts a part of the compressed air compressed by the compressor 11 and the combustion that cools the combustor 12 by the compressed air boosted by the booster 41. The compressor cooler 42, the compressed air circulation line 46 that supplies the compressed air that has cooled the combustor 12 to the passenger compartment of the combustor 12, and the compressed air that has been pressurized by the booster 41 are generated by the exhaust heat recovery boiler 84. And an exchanger 86 that is cooled by steam.

  Accordingly, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and a part of the compressed air is pressurized by the booster 41, cooled by the heat exchanger 86, and then sent to the combustor cooler 42. The combustor 12 is cooled by the compressed air, and the compressed air that has cooled the combustor 12 is supplied to the combustor 12 by the compressed air circulation line 46. In the combustor 12, fuel is supplied to the compressed air and burned. Then, the generated combustion gas is supplied to the turbine 13 to obtain rotational power. At this time, since a part of the compressed air compressed by the compressor 11 is pressurized and cooled before the combustor 12 is cooled, only this part of the compressed air becomes a pressure loss, and the pressure loss of the compressed air is minimized. Therefore, the combustor 12 can be appropriately cooled. Further, since the air that has cooled the combustor 12 is returned to the compressed air supply line 43, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and the combustion air is not reduced. It is possible to suppress an increase in the NOx emission amount due to the increase in the amount of NOx. Further, since the compressed air is pressurized and cooled and then supplied to the combustor cooling device 42, the temperature of the compressed air can be lowered, the combustor 12 can be cooled efficiently, and the low-temperature compressed air can be cooled. Is supplied into the combustor 12, so that the combustion temperature can be lowered and the NOx emission amount can be reduced.

  FIG. 10 is a schematic diagram illustrating a gas turbine according to an eighth embodiment of the present invention. In addition, the same code | symbol is attached | subjected to the member which has the same function as what was demonstrated in the Example mentioned above, and the overlapping description is abbreviate | omitted.

  In the gas turbine of the eighth embodiment, as shown in FIG. 10, the compressor 11 is connected to the combustor 12 via the compressed air supply line 43 and is also compressed air branched off in the middle of the compressed air supply line 43. The booster 41 is connected via a line 44. The booster 41 is connected to the combustor cooling device 42 via the first cooling air supply line 45 and is connected to the turbine cooling device (second cooling air supply line 91 branched from the first cooling air supply line 45). Turbine cooling means) 92. The turbine cooling device 92 is, for example, a large number of cooling passages formed in one stage of the stationary blades of a number of stages fixed to the rotor shaft of the turbine 13, and low-temperature compressed air is contained in the cooling passage. Is used to cool the turbine 13. The cooling air supply line 45 is provided with a heat exchanger 82 for cooling the compressed air boosted by the booster 41, and each of the cooling devices 42 and 92 burns with the compressed air cooled by the heat exchanger 82. The vessel 12 and the turbine 13 are cooled. In the exchanger 82, heat is exchanged between the compressed air and the fuel by introducing the compressed air flowing through the cooling air supply line 45 and the fuel flowing through the fuel supply line 47, and the compressed air is cooled by the fuel. Is done. The combustor cooling device 42 is connected to the compressed air supply line 43 via the first compressed air circulation line 46, and the turbine cooling device 92 is a second compressed air circulation line (second air supply means) 93. It is connected to the compressed air supply line 43 via Further, a fuel supply line 47 is connected to the combustor 12, and the combustor 12 is connected to the turbine 13 through a combustion gas discharge line 48.

  Therefore, the compressor 11 compresses air to generate high-temperature and high-pressure compressed air and flows to the compressed air supply line 43. A part of the compressed air flowing through the compressed air supply line 43 branches to the compressed air branch line 44 and is supplied to the booster 41, where the pressure is further increased and then flows to the cooling air supply line 45. Then, the compressed air boosted by the booster 41 is introduced into the heat exchanger 81 through the cooling air supply line 45, and the fuel is introduced into the heat exchanger 82 through the fuel supply line 47, In the heat exchanger 82, heat exchange is performed between the compressed air and the fuel, and the compressed air boosted by the booster 41 is cooled by the exchanger 82.

  The compressed air cooled by the heat exchanger 82 is supplied to the combustor cooling device 42 to cool the combustor 12 and supplied to the turbine cooling device 92 to cool the turbine 13, while the fuel is supplied to the exchanger 82. And then supplied to the combustor 12. The compressed air that has cooled the combustor 12 is returned to the compressed air supply line 43 through the compressed air circulation line 46. Therefore, the entire amount of compressed air compressed by the compressor 11 is supplied to the combustor 12 through the compressed air supply line 43.

  Then, in the combustor 12, combustion is performed by supplying a predetermined fuel heated from the fuel supply line 47 to the compressed air supplied from the compressed air supply line 43. The high-temperature and high-pressure combustion gas generated in the combustor 12 is sent to the turbine 13 through the combustion gas discharge line 48 and passes through the plurality of stationary blades 21 and the moving blades 22 so that the rotor 25 is driven and rotated. Electricity is generated by driving the generator 14 connected to the rotor 25.

  As described above, in the gas turbine of the eighth embodiment, the booster 41 that boosts a part of the compressed air compressed by the compressor 11 and the combustion that cools the combustor 12 by the compressed air boosted by the booster 41. The cooler 42, the first compressed air circulation line 46 that supplies the compressed air that has cooled the combustor 12 to the passenger compartment of the combustor 12, and the fuel that supplies the compressed air pressurized by the booster 41 to the combustor 12. , A turbine cooling device 92 that cools the turbine 13 with compressed air pressurized by the pressure increasing device 41, and a second compressed air circulation line 93 that supplies the compressed air that has cooled the turbine 13 to the combustor 12. Is provided.

  Accordingly, the compressed air compressed by the compressor 11 is supplied to the combustor 12, and a part of the compressed air is boosted by the booster 41 and cooled by the heat exchanger 82, and then the combustor cooler 42 and the turbine cooler 92. The combustor 12 and the turbine 13 are cooled by the compressed air, and the compressed air that has cooled the combustor 12 and the turbine 13 is supplied to the combustor 12 by the compressed air circulation lines 46 and 93. Then, fuel is supplied to the compressed air and burned, and the generated combustion gas is supplied to the turbine 13 to obtain rotational power. At this time, since a part of the compressed air compressed by the compressor 11 is pressurized and cooled, and then the combustor 12 and the turbine 13 are cooled, only this part of the compressed air becomes a pressure loss, and the pressure loss of the compressed air Thus, the combustor 12 can be properly cooled. Moreover, since the air which cooled the combustor 12 and the turbine 13 is returned to the compressed air supply line 43, the compressed air compressed with the compressor 11 will be supplied to the combustor 12, and combustion air will not decrease. Further, it is possible to suppress an increase in NOx emission due to an increase in combustion temperature. Further, since the compressed air is pressurized and cooled and then supplied to the cooling devices 42 and 92, the temperature of the compressed air can be lowered, the combustor 12 and the turbine 13 can be efficiently cooled, By supplying low-temperature compressed air into the combustor 12, the combustion temperature can be lowered and the NOx emission amount can be reduced. In addition, since the fuel is heated and then supplied to the combustor 12, atomization of the fuel spray is promoted, the combustion efficiency can be improved and the emission of harmful substances can be reduced, and the turbine output can be reduced. Can be improved.

11 Compressor 12 Combustor 13 Turbine 14 Generator 41 Booster (Pressure Booster)
42, 51, 61, 62, 63 Combustor cooling device (combustor cooling means)
43 Compressed air supply line 44 Compressed air branch line 45 Cooling air supply line, first cooling air supply line 46 Compressed air circulation line, first compressed air circulation line (first air supply means)
47 Fuel supply line 48 Discharge line 53 Cooling passage 71 Water supply line 72 Water injection device (moisture addition means)
81, 82, 83, 86 Heat exchanger (compressed air cooling means)
84 Waste heat recovery boiler (waste heat recovery means)
85 Water supply line 87 Steam supply line 91 Second cooling air supply line 92 Turbine cooling device (turbine cooling means)
93 Second compressed air circulation line (second air supply means)

Claims (4)

In a gas turbine that obtains rotational power by supplying fuel to compressed air compressed by a compressor and burning it with a combustor and supplying the generated combustion gas to the turbine, a part of the compressed air compressed by the compressor is Pressurizing means for boosting, combustor cooling means for cooling the combustor with compressed air boosted by the boosting means, first air supply means for supplying the combustor with compressed air that has cooled the combustor, A compressed air cooling means for cooling the compressed air boosted by the boosting means is provided;
The combustor cooling means cools the combustor with the compressed air cooled by the compressed air cooling means,
The exhaust gas discharged from the turbine is sent to a boiler to generate steam, the generated steam is sent to a steam turbine to generate electricity, and the exhaust water recovery means for returning the cooled feed water to the boiler and overheating is provided, The compressed air cooling means cools the compressed air boosted by the boosting means with steam generated by a boiler.   2. The gas turbine according to claim 1, wherein the pressurizing unit bleeds and pressurizes a part of the compressed air compressed by the compressor from a passenger compartment, while the first air supply unit cools the combustor. A gas turbine, wherein the compressed air is returned to the passenger compartment.   3. The gas turbine according to claim 1, wherein the combustor cooling means includes a plurality of cooling passages formed in a wall portion of an inner cylinder constituting the combustor.   4. The gas turbine according to claim 1, wherein turbine cooling means for cooling the turbine with compressed air pressurized by the pressure increasing means, and compressed air that has cooled the turbine are supplied to the combustor. 5. A gas turbine comprising a second air supply means.

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