WO2010001655A1 - ガスタービン及びガスタービンの運転方法 - Google Patents
ガスタービン及びガスタービンの運転方法 Download PDFInfo
- Publication number
- WO2010001655A1 WO2010001655A1 PCT/JP2009/057983 JP2009057983W WO2010001655A1 WO 2010001655 A1 WO2010001655 A1 WO 2010001655A1 JP 2009057983 W JP2009057983 W JP 2009057983W WO 2010001655 A1 WO2010001655 A1 WO 2010001655A1
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- Prior art keywords
- air
- gas turbine
- cooling air
- passage
- rotor
- Prior art date
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
- F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
- F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
- F02C7/16—Cooling of plants characterised by cooling medium
- F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/60—Shafts
- F05D2240/61—Hollow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
Definitions
- the present invention relates to a gas turbine and a gas turbine operating method, and more particularly, to a gas turbine for cooling a turbine-side moving blade and a gas turbine operating method.
- JP-A-61-2226502 Japanese Patent Publication No.59-41001 JP-A-11-117702
- the air compressed by the compressor through the central hole of the rotor flows from the compressor side to the turbine side through the internal passage and is supplied to the moving blade as cooling air. It is what is done.
- a part of air is extracted from a disk, which is a rotating member of the compressor, to a cavity located inside the compressor body, and is supplied to the moving blade side passage through the internal passage. For this reason, it is difficult to adjust the amount of extracted air during operation. For this reason, there is a possibility that cooling air having a flow rate higher than that required for cooling the moving blades during the maximum load operation of the gas turbine may be extracted from the compressor, and as a result, the thermal efficiency of the gas turbine may be reduced.
- Patent Document 2 is similar to the technique described in Patent Document 1 in that air is supplied from the compressor side to the moving blade side through the internal passage, and has the same problems.
- the technique described in Patent Document 3 supplies a cooling medium from the rotor shaft end on the turbine side, but is a system that presupposes recovery of the cooling medium, and is different from the purpose of the present application. .
- the amount of cooling air required for cooling the rotor blades varies depending on the load of the gas turbine.
- the gas turbine When the gas turbine is operating at a high load, it is necessary to supply high-pressure air to the moving blade side to ensure the necessary air amount and increase the cooling capacity.
- it In the case of low-load operation, it is necessary to reduce the amount of cooling air. Therefore, it is necessary to supply relatively low-pressure air, suppress unnecessary air consumption, and suppress a decrease in thermal efficiency of the gas turbine. is there.
- the above patent document does not disclose any means for adjusting the amount of air against such turbine load fluctuations.
- This invention is made
- the gas turbine is provided on a rotating member that rotates about the central axis as a rotational axis along the central axis of the rotor that is a rotational axis, and cooling air extends along the rotational axis of the rotor.
- An axial passage that flows in a direction, and is provided on the rotating member toward the outside from the center of the rotor, so that the cooling air is compressed, and one end communicates with the axial passage
- An air source having an end portion communicating with the outside of the rotating member, a radial passage that is a plurality of passages provided in the circumferential direction of the rotating member, and an air amount adjusting means, and one end portion taking in air
- an external passage whose other end communicates with the radial passage and into which the cooling air is introduced.
- a gas turbine operating method is provided on a rotating member that rotates about the central axis along the central axis of a rotor that is a rotating shaft, and cooling air is supplied to the rotor.
- An axial passage that flows in a direction along the rotation axis, and the rotation member is provided outward from the center of the rotor to compress the cooling air, and one end communicates with the axial passage.
- the other end portion communicates with the outside of the rotating member, and a radial passage that is a plurality of passages provided in the circumferential direction of the rotating member and one end portion communicates with an air source that takes in air.
- an external passage having a plurality of passages in which the cooling air is introduced and the other end communicating with the radial passage through a shaft end seal, and provided with switching means for switching the air source. Switch the air source in response to the down of the load.
- the operation method of the gas turbine according to the present invention it is possible to select an air source of cooling air according to the load of the gas turbine. Therefore, it is possible to adopt appropriate air according to the operation state, and the thermal efficiency of the entire gas turbine. Can be suppressed.
- FIG. 1 is an overall view of a gas turbine system according to a first embodiment.
- FIG. 2 is a schematic configuration diagram of the gas turbine 3 according to the first embodiment.
- FIG. 3 is a cross-sectional view schematically illustrating an example of a moving blade located at the rear stage of the gas turbine according to the first embodiment.
- FIG. 4 is a cross-sectional view schematically illustrating a passage through which cooling air flows.
- FIG. 5A is a cross-sectional view schematically illustrating the swirler according to the first embodiment by cutting along a plane including a central axis.
- 5B is a cross-sectional view schematically showing the swirler according to the first embodiment by cutting along a plane AA in FIG. 5A.
- FIG. 5C is a cross-sectional view schematically showing the swirler according to the first embodiment by cutting along the BB plane in FIG. 5B.
- FIG. 6A is a cross-sectional view schematically showing a first radial passage according to the first embodiment.
- 6B is a cross-sectional view schematically showing another first radial passage according to the first embodiment.
- FIG. 6C is a cross-sectional view schematically showing another first radial passage according to the first embodiment.
- FIG. 7 is an overall view of a gas turbine system according to the second embodiment.
- FIG. 1 is an overall view of a gas turbine system according to a first embodiment.
- FIG. 2 is a schematic configuration diagram of the gas turbine 3 according to the first embodiment.
- the combustion air supplied to the gas turbine 3 according to the present embodiment is introduced into the compressor 20 via an air filter 71.
- the combustion air compressed to a predetermined pressure by the compressor 20 is supplied to the combustor 30 and mixed with fuel and burned.
- Combustion gas generated in the combustor 30 is introduced into the turbine 10, and when flowing down the turbine side stationary blade 12 and the turbine side moving blade 13, thermal energy is converted into rotational energy of the rotor 50 in the turbine 10 to generate electric power. Removed from machine 80.
- the gas turbine 3 of the present embodiment includes a compressor 20, a combustor 30, a turbine 10, and an exhaust chamber 40 in order from the upstream side to the downstream side of the fluid flow. Consists of.
- the compressor 20 pressurizes the air and sends the pressurized air to the combustor 30.
- the combustor 30 supplies fuel to the air and burns it.
- the turbine 10 converts the energy of the combustion gas sent out from the combustor 30 into rotational energy.
- the compressor 20 includes an air inlet 21, a compressor housing 22, a compressor side stationary blade 23, a compressor side moving blade 24, and an extraction manifold 25.
- the air intake 21 serves as an air inlet for taking in the air introduced from the air filter 71 shown in FIG. 1 into the compressor housing 22.
- a plurality of compressor side stationary blades 23 and a plurality of compressor side moving blades 24 are provided alternately.
- the air compressed by the compressor 20 is guided to the vehicle compartment 36 of the combustor 30.
- the extraction manifold 25 is provided outside the compressor-side stationary blades 23 and has a role of temporarily storing compressed air extracted from the intermediate stage of the compressor 20 for cooling the turbine-side stationary blades.
- the extraction manifold 25 includes a compressor extraction port 26 for connection to external piping.
- the compressor bleed port 26 may be provided with a plurality of bleed ports.
- a low-pressure extraction port for low-pressure extraction extracted from the low-pressure side intermediate stage of the compressor or a high-pressure extraction port for high-pressure extraction extracted from the high-pressure side intermediate stage may be provided, and the extraction port may be changed as appropriate according to the operating conditions.
- the combustor 30 includes a housing 31, a combustor liner 32, and a transition piece 33.
- a vehicle compartment 36 is formed inside the housing 31.
- the combustor liner 32 is formed in a substantially cylindrical shape, and is provided inside the vehicle compartment 36 as a passage for combustion gas.
- a tail cylinder 33 is provided in the vehicle compartment 36 as a passage for combustion gas.
- the transition piece 33 is formed in a substantially cylindrical shape, and a combustion region 37 in which air and fuel are combusted is formed inside the transition piece 33.
- the tail tube 33 is connected to one end portion.
- a fuel nozzle 34 for injecting fuel into the combustor liner 32 is provided at the end of the combustor liner 32 opposite to the tail cylinder 33.
- a plurality of combustor liner air inlets 35 for introducing compressed air into the combustor liner 32 are formed on the outer peripheral surface of the combustor liner 32.
- the turbine 10 includes a turbine casing 11, a turbine side stationary blade 12, and a turbine side moving blade 13.
- the exhaust chamber 40 includes an exhaust diffuser 41 that is continuous with the turbine 10.
- the exhaust diffuser 41 converts the dynamic pressure of the combustion gas that has passed through the turbine 10, that is, the exhaust gas, into a static pressure.
- the gas turbine 3 has a rotor 50 as a rotating member.
- the rotor 50 is provided so as to penetrate through the center of the compressor 20, the combustor 30, the turbine 10, and the exhaust chamber 40.
- the rotor 50 is rotatably supported at the end on the compressor 20 side by a bearing 51 and is rotatably supported at the end on the exhaust chamber 40 side by a bearing 52.
- a plurality of disks 14 are fixed to the rotor 50.
- the compressor 14 blade 24 and the turbine blade 13 are connected to the disk 14.
- a drive shaft of a generator (not shown) is connected to the end of the rotor 50 on the compressor 20 side.
- the gas turbine 3 supplies the compressed air existing in the intermediate stage of the compressor 20 as a high pressure region to the axial passage 60 as cooling air.
- the gas turbine 3 includes a shaft end seal 67, an external passage 68, a cooler 69 as cooling air cooling means, and an air flow rate adjustment valve 70.
- the shaft end seal 67 is installed so as to cover the cooling air inlet 61 and communicates with the external passage 68. Thereby, the cooling air inlet 61 and the external passage 68 communicate with each other via the shaft end seal 67 as shown in FIG.
- the external passage 68 is connected to, for example, a compressor bleed port 26 provided in the bleed manifold 25 of the compressor 20.
- the cooler 69 is provided in the external passage 68.
- the temperature of the compressed air extracted from the compressor 20 is higher than the temperature in the atmosphere. Therefore, the cooler 69 cools the cooling air flowing inside the external passage 68.
- the air flow rate adjustment valve 70 is provided in the external passage 68 and adjusts the flow rate of the cooling air flowing inside the external passage 68.
- the flow rate of the cooling air extracted from the compressor 20 and flowing in the external passage 68 varies depending on the operating state of the gas turbine 3. Specifically, as the gas turbine operates at a higher load, the cooling air flowing in the external passage 68 increases.
- the cooling air extracted from the compressor 20 is supplied to the turbine 10 via the external passage 68.
- the flow rate of the cooling air is adjusted by the air flow rate adjustment valve 70 and cooled by the cooler 69.
- the cooling air cooled by the cooler 69 is introduced into the cooling air inlet 61 through the external passage 68 and the shaft end seal 67.
- the combustion gas that has passed through the final stage of the turbine is introduced from the exhaust chamber 40 to the exhaust heat recovery unit 42 to be recovered, and is discharged from the chimney 43 to the atmosphere.
- the turbine-side stationary blade 12 and the turbine-side moving blade 13 through which the high-temperature combustion gas passes are cooled with cooling air in order to suppress damage to the blade due to the high-temperature combustion gas.
- the cooling air is finally discharged into the combustion gas after cooling the turbine-side stationary blade 12 and the turbine-side moving blade 13.
- the air extracted from the compressor bleed port 26 is cooled to an appropriate temperature by the cooler 69.
- cooling water is used as the refrigerant.
- a relatively low temperature fluid such as a boiler working fluid of the exhaust heat recovery unit 42 in the system can also be used as the refrigerant of the cooler 69. In this case, the energy loss of the entire system is further reduced by heat recovery.
- the adjustment of the flow rate of the cooling air is performed by an air flow rate adjusting valve 70 that is an air flow rate adjusting means according to the load of the gas turbine. Further, the temperature of the cooling air is adjusted by adjusting the refrigerant flow rate of the cooler 69 or adjusting the amount of air that bypasses the cooler according to the load of the gas turbine.
- the air flow rate adjusting means includes a method of adjusting the flow rate of the cooling air by manual operation such as a manual valve or an orifice, in addition to the air flow rate adjustment valve 70 that can be controlled continuously.
- the gas turbine system 1 uses the gas turbine 3 including the compressor 20, the turbine 10, the combustor 30, and the exhaust chamber 40 illustrated in FIG. 2 and the cooling air disposed around the gas turbine 3 as the turbine.
- the gas turbine system 1 is configured such that the shaft end seal 67 and the external passage 68 can be removed, or the supply source of the cooling air can be switched between the atmosphere and the compressor 20, thereby The air source that is the supply source of the cooling air can also be changed depending on the operation status of the turbine 3.
- the gas turbine 3 has a function of cooling the turbine-side moving blade 13 with the cooling air.
- the cooling target is used for cooling the turbine side stationary blade 12 and other gas turbine components in addition to the turbine side moving blade 13.
- the last stage moving blade is cooled by the cooling air, but the moving blade to be cooled is not limited to this.
- FIG. 3 is a cross-sectional view schematically showing an example of a moving blade located at the rear stage of the gas turbine according to the first embodiment.
- the turbine-side moving blade 13 includes a base portion 131, a tip portion 132 that is a tip portion of the turbine-side moving blade 13, and a cooling passage 133 that is a hole.
- the turbine-side moving blade 13 is attached to the outer periphery of the disk 14 shown in FIG.
- the cooling passage 133 is formed in the base 131 so as to open into a hollow space.
- a plurality of cooling passages 133 are formed substantially linearly from the base portion 131 toward the tip portion 132.
- a plurality of cooling passages 133 are formed substantially linearly from the base portion 131 toward the tip portion 132, but the present embodiment is not limited to this.
- the cooling passage 133 may be provided, for example, in a curved shape (so-called serpentine flow path).
- the cooling air first flows into the cooling passage 133 from the base 131 side of the turbine rotor blade 13.
- the cooling air exchanges heat with the wall surface in the cooling passage 133.
- the cooling air flows through the cooling passage 133 to the tip portion 132 side of the turbine-side rotor blade 13. In this way, the cooling air flowing through the cooling passage 133 performs heat exchange with the turbine-side moving blade 13 to cool the turbine-side moving blade 13.
- FIG. 4 is a cross-sectional view schematically illustrating a passage through which cooling air flows.
- the gas turbine 3 according to the present embodiment includes an axial passage 60, a cooling air inlet 61, a swirler 62 as a swirling means, a first radial passage 63, and a cavity 64. And a second radial passage 65.
- the axial passage 60 is formed in a cylindrical shape along the central axis RL of the rotor 50 on the exhaust chamber 40 side.
- the axial passage 60 is formed such that the central axis RL of the rotor 50 and the central axis of the axial passage 60 coincide.
- the cooling air inlet 61 which is one end of the axial passage 60 communicates with the external passage 68 shown in FIG.
- the cooling air inlet 61 is provided, for example, in a bell mouth shape at the end 50a of the rotor 50 on the exhaust chamber 40 side.
- the bell mouth shape is a tapered shape with a substantially bell-shaped curvature, and the diameter is larger toward the upstream side of the cooling air flow, and the diameter becomes smaller toward the downstream side of the cooling air flow. It is formed small. Thereby, the cooling air inlet 61 can introduce the cooling air from the external passage 68 to the axial passage 60 more efficiently.
- FIG. 5A is a cross-sectional view schematically showing the swirler according to the first embodiment cut along a plane including the central axis.
- 5B is a cross-sectional view schematically showing the swirler according to the first embodiment by cutting along a plane AA in FIG. 5A.
- 5C is a cross-sectional view schematically showing the swirler according to the first embodiment by cutting along the BB plane in FIG. 5B.
- the swirler 62 shown in FIGS. 5A, 5B, and 5C is provided at the end of the axial passage 60 opposite to the cooling air inlet 61 shown in FIG.
- the swirler 62 is a rotating member that is fixed to the rotor 50 and rotates together with the rotor 50.
- the swirler 62 includes a guide plate 62a. As the swirler 62 rotates, the guide plate 62 a turns the cooling air inside the axial passage 60 in the rotation direction of the rotor 50. That is, the swirler 62 causes the cooling air to flow in the rotational direction of the rotor 50 with a velocity component.
- the swirler 62 may be provided in the cooling air inlet 61 that is the other end of the axial passage 60.
- the swirler 62 is preferably provided in the vicinity of the first radial passage 63.
- an axial passage 60 that rotates and an external passage 68 having a stationary structure are connected to the end of the external passage 68 that communicates with the cooling air inlet 61 to leak cooling air.
- a shaft end seal 67 is provided for introduction to the turbine 10 side.
- the shaft end seal 67 is a tight seal between rotation and stationary, and has a seal structure composed of a combination of a labyrinth seal 67a and a brush seal 67b.
- the shaft end seal 67 suppresses cooling air from leaking from the connection portion to the outside.
- the shaft end seal 67 may be configured as a seal structure by, for example, a leaf seal or other seal material instead of the brush seal.
- FIG. 6A is a cross-sectional view schematically showing a first radial passage according to the first embodiment.
- 6B is a cross-sectional view schematically showing another first radial passage according to the first embodiment.
- FIG. 6C is a cross-sectional view schematically showing another first radial passage according to the first embodiment.
- 6A to 6C show a case of a cross-sectional view on a plane orthogonal to the central axis RL of the rotor 50.
- first radial passages 63 are formed in the rotor 50 from the center of the rotor 50 toward the outside.
- the first radial passage 63 is formed, for example, as a radial hole from the center of the axial passage 60.
- the first radial passage 63 has a cooling air introduction side opening 63a and a cooling air discharge side opening 63b.
- the cooling air introduction side opening 63 a opens in the axial passage 60.
- the cooling air discharge side opening 63b opens into the cavity 64 shown in FIG.
- the first radial passage 63 is formed radially from the center of the axial passage 60.
- the present embodiment is not limited to this.
- the first radial passage 63 may be formed in a curved shape.
- the virtual extension line of the first radial passage 63 does not necessarily pass through the center of the axial passage 60.
- the cavity 64 is formed in the rotor 50 in the vicinity of the disk 14 as a rotating member to which the turbine-side rotor blade 13 is attached.
- the disk 14 is a rotating member that rotates with the rotor 50 about the central axis RL.
- the cavity 64 temporarily stores the cooling air supplied from the first radial passage 63 and supplies the cooling air to the second radial passage 65 that opens to the cavity 64.
- the first radial passage 63 and the second radial passage 65 communicate with each other through the cavity 64, but the present embodiment is not limited to this.
- the first radial passage 63 and the second radial passage 65 may be communicated by a tubular passage without providing the cavity 64 in the middle.
- a plurality of second radial passages 65 are provided on the disk 14 from the center of the disk 14 toward the outside.
- a cavity side opening 65a that is an opening provided at one end portion opens to the cavity 64
- a moving blade side opening 65b that is an opening provided at the other end portion is provided to the turbine side moving blade 13.
- the cooling passage 133 is opened.
- the cooling air existing inside the axial passage 60 is swirled in the rotational direction of the rotor 50 by the swirler 62 that rotates together with the rotor 50 when the gas turbine 3 operates and the rotor 50 rotates.
- the cooling air is introduced into the first radial passage 63 through the cooling air introduction side opening 63 a provided in the vicinity of the swirler 62.
- the cooling air introduced into the first radial passage 63 is boosted by a pumping effect similar to that of the centrifugal compressor as the first radial passage 63 rotates about the central axis RL.
- a cooling air flow AF02 shown by an arrow in the figure flows from the axial passage 60 into the cooling air introduction side opening 63a and flows from the radial center side to the radial outer side.
- the cooling air flowing in the first radial passage 63 is introduced into the cavity 64 through the cooling air discharge side opening 63b.
- the cooling air flowing inside the cavity 64 is introduced into the second radial passage 65 that opens to the cavity 64 via the cavity-side opening 65a.
- the cooling air introduced into the second radial passage 65 is boosted by the pumping effect similar to that of the centrifugal compressor as the second radial passage 65 rotates about the central axis RL.
- a cooling air flow AF03 illustrated by arrows in the figure flows from the radial center side of the disk 14 to the radial outer side.
- the cooling air flowing inside the second radial passage 65 is introduced into the cooling passage 133 through the moving blade side opening 65b.
- the cooling air flowing inside the cooling passage 133 is boosted by a pumping effect similar to that of the centrifugal compressor as the cooling passage 133 rotates about the central axis RL.
- a cooling air flow AF04 illustrated by an arrow in the drawing flows from the base 131 side toward the tip portion 132 shown in FIG.
- the cooling air that reaches the tip portion 132 is discharged from the cooling air discharge port 136 into the combustion gas.
- the starting point of the first radial passage 63 arranged in the radial direction is arranged in the vicinity of the center of the rotor 50, and the second radial passage 65 and the cooling passage 133 shown in FIG. Since they are arranged in order, the pumping action works effectively.
- the gas turbine 3 has a pressure loss generated when the pumping force acting on the cooling air flows from the external passage 68 through the axial passage 60, the first radial passage 63, and the second radial passage 65. It overcomes a part of the driving force for guiding the cooling air to the tip of the turbine side rotor blade 13.
- the pumping action works effectively on the cooling air flowing through the cooling passage 133, and the pressure of the cooling air required for the air source can be further reduced.
- the pumping action works effectively even with the pressure of the air source similar to the atmospheric air, and the turbine-side rotor blades 13 to be cooled are Cooling air can be supplied to the tip.
- the gas turbine system 1 described above is provided along the central axis RL of the rotor 50 that is a rotating shaft and is provided in the rotor 50 with the axial passage 60 communicating with the external passage 68 from the center of the rotor 50 toward the outside.
- the air for cooling is compressed, and the first radial passage 63 communicating with the axial passage 60 and one end thereof are communicated with the first radial passage 63 via the cavity 64, and the other end is communicated.
- the gas turbine system 1 is different from the gas turbine shown in the conventional example, and is configured to include the air flow rate adjustment valve 70 and the cooler in the external passage 68 separately from the gas turbine 3. Even inside, it is possible to adjust the air amount and air temperature.
- FIG. 7 is an overall view of a gas turbine system according to the second embodiment.
- a case where a plurality of air sources of cooling air are provided in order to cool the rear turbine blade 13 supplied to the turbine 10 will be described.
- the gas turbine system 2 includes a compressor high-pressure extraction port 27, a compressor low-pressure extraction port 28, and an air introduction port 29 as air sources.
- the gas turbine system 2 includes external passages 68 from respective air sources to shaft end seals 67 provided at the shaft ends of the rotor 50 of the turbine 10.
- Compressor high-pressure bleed port 27 and compressor low-pressure bleed port 28 can extract compressed air from an intermediate stage of the compressor. If necessary, the compressor high-pressure bleed port 27 and the compressor low-pressure bleed port 28 may be provided with three or more bleed ports, not limited to two.
- the gas turbine system 2 bleeds high-pressure air from a compressor high-pressure bleed port 27 located on the downstream side of the compressed air flow close to the outlet side of the air flow of the compressor 20.
- the low-pressure air having a pressure lower than that of the high-pressure air is extracted from the compressor low-pressure extraction port 28 located on the upstream side.
- an air filter 71 is connected from the air inlet 29 as shown in FIG.
- the atmospheric air can be introduced directly through.
- the flow rate of air introduced from the air introduction port 29 is adjusted by an air flow rate adjusting valve 70 that is an air amount adjusting means.
- the air introduced from the atmosphere introduction port 29 has a relatively low atmospheric temperature, it is not necessary to be cooled by the cooler 69.
- the compressor bleed port may be provided with only one compressor bleed port without providing the compressor high pressure bleed port 27 and the compressor low pressure bleed port 28.
- the air source basically supplies cooling air to the turbine 10 using any one air source. That is, the gas turbine 3 does not introduce cooling air into the turbine 10 from a plurality of air sources at the same time.
- the air source is switched by a switching valve 72 provided in each external passage 68.
- the gas turbine 3 When switching the air source that is the supply source of the cooling air, the gas turbine 3 may be temporarily stopped and switched, or may be gradually switched during the operation of the gas turbine 3.
- the compressor high pressure extraction port 27 having the highest extraction pressure at the air source is selected. If the compressor high-pressure extraction port 27 is selected and air cooled to an appropriate temperature by the cooler 69 is supplied to the turbine 10, the gas turbine 3 can supply the maximum amount of cooling air to the turbine-side moving blade 13. . Thereby, the gas turbine 3 can obtain the maximum cooling effect.
- the gas turbine 3 When the load of the gas turbine 3 is small, the gas turbine 3 introduces cooling air from the air introduction port 29.
- the gas turbine 3 requires the cooler 69 when the compressor high-pressure bleed port 27 and the compressor low-pressure bleed port 28 are used as the air source.
- the air introduction port 29 is used as the air source, the gas turbine 3 is used. do not need. Therefore, the gas turbine 3 loses the corresponding heat loss, and the overall thermal efficiency of the gas turbine 3 is improved.
- the air inlet 29 is used as an air source, it is a low-pressure air source, so that the air flow rate that can be introduced into the turbine 10 is limited by the loss of pressure in the passage through which the cooling air flows.
- cooling air may be extracted from the compressor low-pressure extraction port 28.
- the required amount of air is smaller than when the gas turbine 3 is 100% loaded, and when the required amount of air is larger than when the load is small and the air inlet 29 is used as the air source, the gas turbine 3 is compressed. Cooling air is introduced into the turbine 10 from the machine low-pressure extraction port 28.
- the pressure of the cooling air introduced into the turbine 10 may be lower than that of the compressor high-pressure bleed port 27 used when the gas turbine 3 is operated at 100% load. Energy loss at 20 can be reduced.
- the gas turbine 3 includes a manual valve, an orifice and the like in addition to the air flow rate adjusting valve 70 as an air amount adjusting means.
- the air source switching means may be one that can be switched manually instead of the switching valve 72 that can be switched remotely.
- the gas turbine 3 has been described as including the swirler 62, the present embodiment is not limited to this.
- the gas turbine 3 may not include the swirler 62.
- the swirler 62 it is possible to reduce pressure loss when cooling air is introduced from the axial passage 60 to the first radial passage 63. Therefore, the gas turbine 3 can suppress the deterioration of cooling performance more suitably.
- the cooling air is cooled from the low-pressure air source by the pressure increased by the pumping action in the passage secured longer in the radial direction than the conventional gas turbine.
- the temperature of the air extracted from the compressor extraction port is increased because the air is compressed by the compressor. Therefore, the air extracted from the compressor extraction port can be cooled by the cooling air cooling means. Thereby, the said gas turbine can cool the cooling object more.
- the air source can be an air inlet that opens to the atmosphere, so that cooling air can be supplied from the atmosphere to the object to be cooled.
- the gas turbine which concerns on this invention can take in air from an atmospheric inlet, without extracting the cooling air from the compressor side like the conventional gas turbine. Therefore, since the gas turbine according to the present invention does not require high-pressure air as an air source for cooling air, an improvement in thermal efficiency can be expected.
- the cooling air before the cooling air reaches the radial passage, the cooling air is swirled in the same rotational direction as the radial passage in which the swirl applying means rotates. Thereby, the cooling air is efficiently introduced from the axial passage into the radial passage. Therefore, the gas turbine according to the present invention can suppress a decrease in thermal efficiency.
- path is comprised from several external channel
- the gas turbine and the gas turbine operating method according to the present embodiment are useful for cooling the moving blades on the turbine side, and are particularly suitable for gas turbines that can suppress a decrease in thermal efficiency.
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Abstract
Description
図1は、実施形態1に係るガスタービンシステムの全体図である。図2は、実施形態1に係るガスタービン3の概略構成図である。図1及び図2に示すように、本実施形態に係るガスタービン3に供給される燃焼用空気は、空気フィルタ71を介して圧縮機20に導入される。圧縮機20によって、所定圧力に圧縮された燃焼用空気は、燃焼器30に供給され、燃料と混合されて燃焼される。燃焼器30で発生した燃焼ガスは、タービン10に導入され、タービン側静翼12、タービン側動翼13を流下する際に熱エネルギーがタービン10におけるロータ50の回転エネルギーに変換されて電力として発電機80から取り出される。
図4に示すように、冷却用空気導入口61に連通する外部通路68の端部には、回転駆動する軸方向通路60と静止構造の外部通路68とを接続して、冷却用空気を洩れなくタービン10側へ導入するための軸端シール67が設けられる。
上述のように、第1径方向通路63、第2径方向通路65、冷却通路133を冷却用空気が流れる際、冷却用空気には遠心力によるポンピング作用が働く。本実施形態では、径方向に配置された第1径方向通路63の始点がロータ50中心近傍に配置され、第2径方向通路65、タービン側動翼13内の図3に示す冷却通路133が順番に配置されているので、ポンピング作用が有効に働く。
図7は、実施形態2に係るガスタービンシステムの全体図である。実施形態2では、タービン10に供給される後方段のタービン側動翼13を冷却するため、冷却用空気の空気源が複数個所供えられる場合を示す。
3 ガスタービン
10 タービン
11 タービン車室
12 タービン側静翼
13 タービン側動翼
14 ディスク
20 圧縮機
21 空気取入口
22 圧縮機筐体
23 圧縮機側静翼
24 圧縮機側動翼
25 抽気マニホールド
26 圧縮機抽気口
27 圧縮機高圧抽気口
28 圧縮機低圧抽気口
29 大気導入口
30 燃焼器
31 ハウジング
32 燃焼器ライナ
33 尾筒
34 燃料ノズル
35 燃焼器ライナ空気取入口
36 車室
37 燃焼領域
40 排気室
41 排気ディフューザ
42 排熱回収部
43 煙突
50 ロータ
51 軸受
52 軸受
60 軸方向通路
61 冷却用空気導入口
62 スワラ
62a ガイド板
63 第1径方向通路
63a 冷却用空気導入側開口
63b 冷却用空気排出側開口
64 キャビティ
65 第2径方向通路
65a キャビティ側開口
65b 動翼側開口
67 軸端シール
67a ラビリンスシール
67b ブラシシール
68 外部通路
69 冷却器
70 空気流量調節弁
71 空気フィルタ
72 切替弁
80 発電機
131 基部
132 チップ部
133 冷却通路
136 冷却用空気排出口
AF02 冷却用空気流
AF03 冷却用空気流
AF04 冷却用空気流
RL 中心軸
Claims (7)
- 回転軸であるロータの中心軸に沿って前記中心軸を回転軸として回転する回転部材に設けられると共に冷却用空気が前記ロータの回転軸に沿う方向に流動する軸方向通路と、
前記回転部材に前記ロータの中心から外側に向かって設けられることで前記冷却用空気を圧縮すると共に、一方の端部が前記軸方向通路に連通し、他方の端部が前記回転部材の外部に連通し、前記回転部材の周方向に向かって複数本設けられる通路である径方向通路と、
空気量調整手段を備え、一方の端部が空気を取り入れる空気源に連通し、他方の端部が前記径方向通路に連通して前記冷却用空気が導入される外部通路と、
を備えることを特徴とするガスタービン。 - 前記空気源は、空気を圧縮する圧縮機に設けられる圧縮機抽気口であることを特徴とする請求項1に記載のガスタービン。
- 前記外部通路に設けられると共に、前記冷却用空気を冷却する冷却用空気冷却手段を備えることを特徴とする請求項2に記載のガスタービン。
- 前記空気源が大気に開口する大気導入口であることを特徴とする請求項1に記載のガスタービン。
- 前記軸方向通路に設けられて、前記軸方向通路を流動する前記冷却用空気に対して前記ロータの回転方向の旋回を与えるスワール付与手段を備えることを特徴とする請求項1に記載のガスタービン。
- 前記外部通路が、複数の外部通路から構成され、前記空気源を切り替える切替手段を備えることを特徴とする請求項1に記載のガスタービン。
- 回転軸であるロータの中心軸に沿って前記中心軸を回転軸として回転する回転部材に設けられると共に冷却用空気が前記ロータの回転軸に沿う方向に流動する軸方向通路と、
前記回転部材に前記ロータの中心から外側に向かって設けられることで前記冷却用空気を圧縮すると共に、一方の端部が前記軸方向通路に連通し、他方の端部が前記回転部材の外部に連通し、前記回転部材の周方向に向かって複数本設けられる通路である径方向通路と、
一方の端部が空気を取り入れる空気源に連通して前記冷却用空気が導入され、他方の端部が前記径方向通路に軸端シールを介して連通する複数の通路から構成され、前記空気源を切り替える切替手段を備える外部通路と、
を備えるガスタービンの負荷に応じて前記空気源を切り替えることを特徴とするガスタービンの運転方法。
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JP2010518955A JP4981970B2 (ja) | 2008-06-30 | 2009-04-22 | ガスタービン |
KR1020137031824A KR20140013061A (ko) | 2008-06-30 | 2009-04-22 | 가스 터빈 및 가스 터빈의 운전 방법 |
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US9650953B2 (en) | 2011-09-12 | 2017-05-16 | Ansaldo Energia Ip Uk Limited | Gas turbine |
JP2013060948A (ja) * | 2011-09-12 | 2013-04-04 | Alstom Technology Ltd | ガスタービン |
WO2013125074A1 (ja) * | 2012-02-23 | 2013-08-29 | 三菱重工業株式会社 | ガスタービン |
JPWO2013125074A1 (ja) * | 2012-02-23 | 2015-07-30 | 三菱日立パワーシステムズ株式会社 | ガスタービン |
DE112012005939B4 (de) * | 2012-02-23 | 2021-02-25 | Mitsubishi Power, Ltd. | Gasturbine |
US9371737B2 (en) | 2012-02-23 | 2016-06-21 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine |
WO2014050163A1 (ja) * | 2012-09-27 | 2014-04-03 | 三菱重工業株式会社 | ガスタービン冷却系統の制御方法、この方法を実行する制御装置、これを備えているガスタービン設備 |
JP2014070510A (ja) * | 2012-09-27 | 2014-04-21 | Mitsubishi Heavy Ind Ltd | ガスタービン冷却系統の制御方法、この方法を実行する制御装置、これを備えているガスタービン設備 |
US10465563B2 (en) | 2012-09-27 | 2019-11-05 | Mitsubishi Hitachi Power Systems, Ltd. | Method for controlling cooling system of gas turbine, control device performing the same, and gas turbine plant comprising the control device |
US9797259B2 (en) | 2014-03-07 | 2017-10-24 | Siemens Energy, Inc. | Turbine airfoil cooling system with cooling systems using high and low pressure cooling fluids |
JP2017518452A (ja) * | 2014-03-07 | 2017-07-06 | シーメンス エナジー インコーポレイテッド | 高圧及び低圧の冷却流体を用いる冷却システムを備えたタービン翼 |
KR101965986B1 (ko) * | 2014-08-29 | 2019-04-04 | 미츠비시 히타치 파워 시스템즈 가부시키가이샤 | 가스 터빈 |
CN106574556A (zh) * | 2014-08-29 | 2017-04-19 | 三菱日立电力***株式会社 | 燃气轮机 |
KR20170031196A (ko) * | 2014-08-29 | 2017-03-20 | 미츠비시 히타치 파워 시스템즈 가부시키가이샤 | 가스 터빈 |
CN106574556B (zh) * | 2014-08-29 | 2019-03-29 | 三菱日立电力***株式会社 | 燃气轮机 |
JP2016050494A (ja) * | 2014-08-29 | 2016-04-11 | 三菱日立パワーシステムズ株式会社 | ガスタービン |
WO2016031475A1 (ja) * | 2014-08-29 | 2016-03-03 | 三菱日立パワーシステムズ株式会社 | ガスタービン |
US11248466B2 (en) | 2014-08-29 | 2022-02-15 | Mitsubishi Power, Ltd. | Gas turbine |
JP2015155703A (ja) * | 2015-06-03 | 2015-08-27 | 三菱重工業株式会社 | ガスタービン及びガスタービン冷却方法 |
KR102202368B1 (ko) * | 2020-09-16 | 2021-01-13 | 서울대학교산학협력단 | 밀폐성과 작동성을 향상시킨 가스 터빈 엔진 |
KR102206447B1 (ko) * | 2020-10-08 | 2021-01-22 | 서울대학교산학협력단 | 유동 안정성과 냉각 효율을 향상시킨 가스 터빈 엔진 |
Also Published As
Publication number | Publication date |
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KR101370731B1 (ko) | 2014-03-06 |
CN103758578B (zh) | 2015-12-09 |
KR20140013061A (ko) | 2014-02-04 |
JP2012067767A (ja) | 2012-04-05 |
US8079802B2 (en) | 2011-12-20 |
KR20110022641A (ko) | 2011-03-07 |
US20090324386A1 (en) | 2009-12-31 |
CN102076940A (zh) | 2011-05-25 |
JP5524248B2 (ja) | 2014-06-18 |
JPWO2010001655A1 (ja) | 2011-12-15 |
EP2309109A1 (en) | 2011-04-13 |
JP2012067766A (ja) | 2012-04-05 |
JP2012067765A (ja) | 2012-04-05 |
EP2309109B1 (en) | 2017-04-19 |
JP5571106B2 (ja) | 2014-08-13 |
CN102076940B (zh) | 2014-12-31 |
JP4981970B2 (ja) | 2012-07-25 |
EP2309109A4 (en) | 2015-05-20 |
CN103758578A (zh) | 2014-04-30 |
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