WO1998023851A1 - Turbine a gaz du type a recuperation du refrigerant - Google Patents
Turbine a gaz du type a recuperation du refrigerant Download PDFInfo
- Publication number
- WO1998023851A1 WO1998023851A1 PCT/JP1996/003503 JP9603503W WO9823851A1 WO 1998023851 A1 WO1998023851 A1 WO 1998023851A1 JP 9603503 W JP9603503 W JP 9603503W WO 9823851 A1 WO9823851 A1 WO 9823851A1
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- WO
- WIPO (PCT)
- Prior art keywords
- flow path
- rotor
- disk
- gas turbine
- spacer
- Prior art date
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Classifications
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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
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
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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
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
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- 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
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
Definitions
- the present invention relates to a gas turbine that cools a moving blade, and more particularly, to a closed cooling gas turbine that collects a refrigerant that cools a moving blade.
- the present invention refers to a gas turbine that heats a rotor shaft portion at the time of startup to relieve thermal stress.
- a center hole is provided at the center (axial center) of a disk or the like with respect to a gas turbine having a supply / recovery flow path of a refrigerant to a rotor blade in a disk or spacer constituting a rotor.
- a gas turbine with a solid disk, without any, is described. Disclosure of the invention
- the metal temperature distribution of the rotor and the thermal stress and thermal displacement acting on the rotor are affected by the flow of heat from the space inside the rotor and from the outer peripheral surface of the rotor.
- Japanese Patent Application Laid-Open No. 3-275946 does not consider any specific countermeasures against the above-mentioned effects on the rotor.
- an object of the present invention is to provide a gas turbine in which the operational reliability of the gas turbine is improved by suppressing the thermal stress acting on the central portion of the rotor.
- a first feature of the present invention is that a plurality of disks in which a plurality of blades driven by combustion gas are annularly arranged on an outer peripheral portion thereof and a spacer arranged between the disks are sequentially arranged in an axial direction.
- a disk having a solid structure wherein the disk is formed in a solid structure, and a region of the disk facing the swirler on the rotor axis side and an adjacent swirler are formed.
- a gap is formed between the discs, and a contact surface is formed in which both the disc-facing area of the disk facing the spur and the adjacent spur are in contact with each other.
- a third flow path for guiding a fluid to the gap is provided.
- the flow of heat into and out of the rotor member can be controlled, the thermal stress acting on the rotor member can be reduced, and the reliability of the rotor member at startup can be increased.
- a second feature of the present invention is that, in the axial direction, a plurality of disks in which a plurality of blades driven by combustion gas are arranged in an outer periphery in a ⁇ shape, and a spacer arranged between the disks are sequentially arranged in the axial direction.
- the rotor blades are arranged at the rotor blades, and the rotor blades have a flow path for introducing a cooling refrigerant and leading out the refrigerant heated by the combustion gas.
- a contact surface is formed between the disk and an adjacent sourcing device to make contact with both.
- FIG. 1 is a schematic diagram of a refrigerant recovery type gas turbine according to an embodiment of the present invention.
- FIG. 2 is a sectional view of a port of the refrigerant recovery type gas turbine according to one embodiment of the present invention.
- FIG. 3 is a sectional view of a port of the refrigerant recovery type gas turbine according to one embodiment of the present invention.
- FIG. 4 is a sectional view of a rotor of the refrigerant recovery type gas turbine according to one embodiment of the present invention.
- a gas turbine of a recovery type refrigerant can be applied.
- compressed air or compressed nitrogen can be used as the refrigerant.
- the recovery type refrigerant in the case of a gas turbine of a refrigerant recovery type, the recovery type refrigerant will be described as steam as an example. First, a description will be given with reference to FIG.
- the common configuration of the embodiment is as follows.
- the compressor port 3a of the compressor 1 and the turbine rotor 1a of the turbine 120 are connected by a distance piece 2a.
- the air 14a in the atmospheric state is pressurized by the moving and stationary blades in the compressor air flow path 5a on the outer periphery of the compressor rotor 3a.
- It has a combustor 4a to which the pressurized discharge air from the compressor 1 is supplied.
- the fuel 13a reacts with the compressed air to generate high-temperature and high-pressure combustion gas 15a.
- the combustion gas 15a passes through the moving blades 7a and the stationary blades 17a in the gas flow path 6a on the outer periphery of the turbine rotor 1a of the turbine 120 to generate power.
- a plurality of disks 12a having rotor blades 7a on the outer periphery are arranged in the axial direction via a spacer 11a.
- one set is shown as a representative example.
- the turbine rotor 1a and the spacer 11a on the side of the disk are in contact on the outer peripheral side, and the area including the center part on the center side from the contact surface is located between the adjacent spacer. A gap is formed.
- the disk is formed in a solid structure, and a gap is formed between a region of the disk facing the rotor on the rotor axis side and an adjacent spacer. Forming a contact surface where both the rotor and the adjacent outer surface of the disk facing the rotor are in contact with the outer peripheral region of the rotor; It has a center-side communication channel for guiding.
- a central portion including the central axis of the disk 12a has a solid structure, and is formed between the disk 12a and the spacer 11a.
- a third flow path separate from the steam supply flow path 8a and the steam recovery flow path 9a is provided inside the turbine rotor 1a so as to connect the gaps. It has a certain center side communication channel 10a.
- a center side communication channel 10a is provided so as to penetrate the disk 12a and the spacer 11a.
- a fluid is supplied from a part of the compressed air of the compressor 1 to the center side communication flow path 1 Oa, and the fluid is supplied to each gap formed between the disk 12a and the spacer 11a.
- the fluid exchanges heat with the components inside the turbine rotor 1a.
- the fluid after the heat exchange is discharged to, for example, the outer gas passage 6 a of the turbine 120.
- it may be discharged to other devices and members.
- thermal stress can be reduced. Therefore, the strength of the turbine rotor 1a can be secured even when a centrifugal force is applied in a state where the influence of the thermal stress is large.
- the thermal stress can be reduced as compared with the case where the flow path inside the rotor is only the steam supply flow path 8a and the steam recovery flow path 9a.
- thermal stress tends to increase in closed-cooled rotors.
- a large temperature difference occurs between the rotor outer side and the center.
- the outer periphery of the rotor has a higher temperature than the center of the rotor, the outer periphery of the rotor undergoes expansion displacement relative to the center of the rotor, the center of the rotor undergoes contraction displacement relative to the outer periphery of the rotor, and a radius occurs at the center of the rotor.
- the ripening stress of directional tension acts.
- the thermal stress of the radial tension and the centrifugal tensile stress due to the rotation are superimposed on each other, so that an excessive stress can be suppressed from being applied to the center of the rotor, and the strength of the turbine rotor 1a can be secured. .
- Another characteristic point is that a disk adjacent to the disk in a region on the outer peripheral side of the rotor is provided. And a supply flow for supplying the refrigerant for cooling the moving blades by penetrating the disk and the spacer in the area where the contact surface is formed in the axial direction of the rotor. A recovery channel for the refrigerant heated through the passage and the rotor blades is provided.
- the moving blade 7a is a steam cooling blade and a closed cooling blade that collects the cooled steam without discharging it to the gas flow path 6a.
- the contact surface with the disk may be provided with a supply port and a recovery port for the refrigerant.
- the turbine port 1a is provided with both a steam supply channel 8a for supplying steam to the rotor blades 7a and a steam recovery channel 9a for collecting steam. Both the steam supply passage 8a and the steam recovery passage 9a pass through the contact surface 16a in the axial direction of the rotor and pass through the disk 12a and the spacer 1ia. It is formed.
- the steam supply channel 8a and the steam recovery channel 9a are the inner peripheries of the through holes of the disc 12a and spacer 11a.
- Inner wall surface and contact surface 16a are the constituent elements. The separation of the two channels is made by the contact surface 16a. The coolant flows while contacting the inner wall surface.
- FIG. 2 shows a sectional view (turbine side sectional view) of a rotor of a refrigerant recovery type gas turbine of one embodiment, taking a four-stage turbine as an example. This shows the case of a closed steam-cooled gas turbine.
- the gas turbine rotor includes a compressor port 3a of the compressor 1 and a turbine port 1a of a turbine 120 connected via a distance piece 16.
- the compressor port 3a includes a compressor disk 2 provided with a compressor rotor blade 3 on an outer peripheral portion.
- the turbine rotor i a has a turbine section 100 and a stub shaft 17 connected thereto.
- the bin 100 is located at the first solid disk 8, the second solid disk 9, the third solid disk 10, the fourth solid disk 11, and the outer periphery thereof. It has a first-stage rotor blade 4, a second-stage rotor blade 5, a third-stage rotor blade 6, and a fourth-stage rotor blade 7. On the side of the disk, a hollow spacer 12 is located closest to the compressor 1 side. In addition, there are solid sensors 13, 14, 15. The stub shaft 17 is located on the side of the fourth-stage solid disk 11. The distant bead 16, turbine section 100, and stub shaft 17 are firmly connected by a plurality of stacking bolts 18 provided to penetrate the disk and spacer contact surfaces. .
- the disk has a solid structure in a region including an axis portion, and a spacer adjacent to the disks 8, 9, 10, 11 on the rotor axis side.
- a gap is formed between the discs 13, 14, and 15, and the discs 8 to 11 on the outer peripheral side of the rotor and the spacers 13, 14, 15 are in contact with each other.
- Contact surfaces 31 to 36 are formed, and the discs 8 to 11 further have a plurality of central communication channels (10a) 77, 81, 85 for guiding fluid to the gap. Things.
- a predetermined through-hole for supplying a warm-up medium (fluid) to the cavity between the disks 8 to 11 and the spacers 13, 14, 15 is provided when the gas turbine is started. It is provided.
- a cavity is formed between the disk and the spacer.
- the cavities 78 are formed in the center of the first-stage solid disk 8 and the solid spacer 13. Similarly, let the cavities formed between each disc and the spacer be 80, 82, 84, 86, 88.
- the center side communication channel 10a for communicating the cavity is formed with holes 77, 79, 81 through the disks 8, 9, 10, 11 and the spacers 13, 14, 15, 15. , 83, 85, 87 are provided.
- the hole is provided in an area of the disk or the like where the contact surface is located, and is provided so as to pass through the supply channel or the recovery channel at the center side in the axial direction.
- a hole 77 is provided for communicating the inner space 62 with the cavity 78 and passing through the first solid disk 8 in the axial direction.
- a hole 79 is provided for communicating the cavity 78 with the cavity 80 and passing through the solid spacer 13 in the axial direction.
- a hole 81 that penetrates through the second-stage solid disk 9 in the axial direction and a solid spacer 14 that penetrates in the axial direction so as to communicate between the cavities in the center.
- a slit 89, a solid spacer 15 and a fourth stage solid formed radially on the contact surface 31 between the solid space 15 and the fourth stage solid disk 11 are provided.
- a donut-shaped cavity 90 formed by the disk 11 and a hole 91 connected from the cavity 90 to a gas flow path of the gas turbine are provided.
- the slit 89 is provided on the connection surface 31 at a position that does not intersect the supply holes 52, 53 and the recovery holes 24, 25.
- the flow paths from the cavities 62 to the cavities 90 are in series, and the entire amount of air flowing into the cavities 90 passes through the cavities 78, 80, 82, 84, 86, 88.
- a plurality of channels can be provided in parallel, and cavities 78, 80, 82, 84, 86, 88 can be allocated to the components of each channel provided in parallel.
- a part of the air in the compressor air passage 5a flows into the internal space 62 through the gap between the compressor disks 2.
- the air that has flowed into the internal space 62 passes through a slit extending radially outward from the hollow spacer 12, flows through the hole 77, and is supplied into the cavity 78.
- the air supplied to the cavities 78 flows through the center of the first-stage solid disk 8 and the first-stage solid space 13, the center of the disk 8 and the space 13 Part) warms up at startup. Heat is exchanged between the disc 8 and the center of the spacer 13 by the supplied compressed air. Compressed air passing through the center passes through cavity 7 9 to cavity 8 0 to go into.
- the cores of the first-stage solid disk 13 and the second-stage solid disk 9 are warmed at the time of startup.
- enter cavity 82 through hole 81 enter cavity 84 through hole 83, enter cavity 86 through hole 85, and enter cavity 8 through hole 87.
- the gas passes through the slit 89, passes through the cavity 90, and is discharged to the gas flow path 6a.
- the outer peripheral portions of the solid disks 8, 9, 10, 11 and solid rotors 13, 14 and 15 have high temperatures due to the heat input from the working gas of the gas turbine. Since the central part of the mouth is not easily heated, a large temperature difference occurs between the outer peripheral side of the rotor and the central part of the mouth.
- the outer peripheral portion of the rotor is hotter than the central portion of the rotor.
- the part is subjected to radial tensile thermal stress.
- the ripening stress of the radial tension and the centrifugal tensile stress of the rotation are superimposed, and a large stress may be applied to the center of the rotor. Therefore, by carrying out the present embodiment, the cavity at the center of the rotor formed by the solid disk and the solid spacer is formed.
- the central cooling channel 10a is independent of the supply channel and the recovery channel, and the air at an appropriate temperature and pressure is introduced into the same channel from the middle stage of the compressor to reduce the flow. The amount of heat flowing into and out of the heater member can be controlled.
- the central cooling channel 10a is independent of the supply channel and the recovery channel, a flow rate adjustment mechanism is provided in the central cooling channel 10a, and the It is conceivable to flow air of temperature and pressure. As a result, the air flowing through the central cooling passage 10a can be saved during steady operation, leading to an improvement in efficiency.
- center side communication flow path 10a is connected to the gas flow path of the gas turbine through the side surface of the fourth stage solid disk 11, and the air passing through the flow path flows to the disk side surface.
- seal air that prevents gas from entering the disk side can be supplemented by air that has passed through the central-side communication flow path 1 Oa, reducing the amount of seal air. .
- the holes provided in the discs 8, 9 and 10 are directly provided between the adjacent cavities by the holes provided in the discs 8, 9 and 10 in order to more effectively warm the center of the disc and the like. Provide at a position where they communicate. Specifically, for example, gaps 78, 80, 82, 84, 86, 88 are formed with adjacent spacers and the like on the center side of the contact surfaces 31 to 37 of the disk. The area is on the outer side of the center axis of the disk.
- This embodiment can also be applied to a gas turbine provided with a steam supply channel and a recovery channel for cooling blades.
- gaps 78 to 88 are formed between the disks 8 to 11 on the rotor axis side and the adjacent spacers 13, 14, 15, and Contact surface between the disc and the spreader on the outer peripheral side of the contact 31 to 37 are formed, and the cooling medium is passed through the disks 8 to 11 and the spacers 13, 14, 15 in the area where the contact surface is formed in the rotor axial direction.
- the supply flow paths 24 to 30 and the recovery flow paths 48 to 53 for the heated refrigerant are formed, respectively.
- the fourth-stage solid disk 11 and the stub shaft 17 are in contact on the outer peripheral side, and the area including the center on the center side is the cavity of the void formed by the disk 11 and the stub shaft 17. 2 1 is formed.
- a steam supply channel 8a (first channel) and a steam recovery channel 9a (second channel) are formed so as to penetrate each disk and spacer at each contact surface in the axial direction. You.
- Each of the flow passages has an inner peripheral surface (inner wall) of a through hole passing through each disk and the spacer and a contact surface thereof.
- the steam supply passage 8a includes supply holes 24, 25, 26, 27, 28, 29, 30 which are the through holes of the respective discs and the spacer.
- the vapor recovery passage 9a includes recovery holes 48, 49, 50, 51, 52, and 53, which are the through holes of the discs and the spacer.
- the supply hole and the recovery hole of the component are provided at the contact surface 31 between the fourth stage solid disk 11 and the solid spacer 15, the third stage solid disk 10 and the solid spacer 15.
- Contact surface 3 2 contact surface of the third stage solid disk 10 and solid sensor 14 3, contact surface of the second stage solid disk 9 and solid spacer 14 ,
- First The contact surface 35 of the second-stage solid disk 9 and the solid spacer 13 and the contact surface 36 of the first-stage solid disk 8 and the solid spacer 13 are connected.
- the first-stage solid disk 8 and the solid spacer 12 are connected to each other by a contact surface 37.
- the steam supply channel 8a and the steam recovery channel 9a are separated by the contact surface.
- the contact surface 22 between the stub shaft 17 and the fourth-stage solid disk 11 is connected radially from the cavity 21 to the supply holes 24 provided in the plurality of fourth-stage solid disks 11.
- the formed slit 23 is formed.
- the contact surface 37 communicates with the supply hole 30, and the steam flowing through the supply hole 30 is provided on the outer peripheral side so as to be radially connected to the cavity 39 formed in a donut shape.
- Uto 38 is provided.
- the flow path (23, 24, 25, 26, 27, 28, 29, 30, 38) from the slit 23 to the cavity 39 is in the circumferential direction. There are more than one. It is desirable that they are arranged at substantially equal intervals.
- the contact surface 34 communicates with the supply hole 27 or 28, and the steam flowing through the supply hole 27 or 28 is provided on the outer peripheral side, and is formed in a donut-shaped cavity 42 in the radial direction.
- a slit 41 is provided to contact
- the contact surface 33 is connected to the supply hole 26 or 27, and the steam flowing through the supply hole 26 or 27 is provided on the outer peripheral side, and the donut-shaped cavity 44 is provided in the radial direction.
- a slit 1 4 3 will be provided.
- the cavities 39 are provided with channels 40 for supplying steam to the first-stage solid moving blades 4 in the first-stage solid disks 8 by the number of the first-stage moving blades 4.
- the cavities 42 are provided with channels 43 for supplying steam to the second-stage solid moving blades 5 in the second-stage solid disks 9 by the number of the second-stage moving blades 5.
- the cavities 44 are provided with flow paths 45 for supplying steam to the third-stage solid moving blades 6 inside the third-stage solid disks 10 by the number of the three-stage moving blades 6. .
- the steam whose temperature has risen due to heat exchange in each of the moving blades flows from the first-stage moving blade 4 to a flow path 46 for recovering steam inside the first-stage solid disk 8.
- the flow channels 46 are connected to the cavity 47 formed in a donut shape on the contact surface 36 between the solid spacer 13 and the first-stage solid disk 8. .
- a flow path 54 for recovering steam is formed inside the second-stage solid disk 9 from the second-stage moving blade 5, and the flow path 54 is connected to the solid spacer 13.
- the cavity 55 is formed in a donut shape on the contact surface 35 of the second-stage solid disk 9.
- the passages 56 for recovering steam from the third-stage moving blades 6 are formed inside the third-stage solid disk 10 by the number of the moving blades.
- a contact 57 formed in a donut shape on the contact surface 32 between the solid spacer 15 and the third-stage solid disk 10 is communicated.
- the cavity 47 is communicated from the contact surface 36 to a recovery hole 48 that passes through the solid spacer 13 in the axial direction.
- the cavity 55 is communicated from the contact surface 35 to a recovery hole 48 that penetrates the solid sensor 13 in the axial direction.
- the cavity 57 is communicated from the contact surface 32 to a recovery hole 52 which penetrates through the solid spacer 15 in the axial direction.
- the recovery hole 52 is connected to the recovery channel 59 by a channel 58.
- the flow path for supplying and recovering the refrigerant to the moving blades provided on the outer periphery of each disk is thus separated into the supply side and the recovery side.
- the steam guided to 21 passes through the slit 23 and reaches the supply hole 24 passing through the fourth-stage solid disk 11 in the axial direction from the contact surface 22.
- the steam that has passed through the supply holes 25, the supply holes 26, the supply holes 27, the supply holes 28, the supply holes 29, and the supply holes 30 is led to the cavity 39 through the slit 38.
- the steam supplied to the cavities 21 is distributed to the respective supply holes, and the steam is supplied in parallel to the cavities 39.
- the steam from the cavity 39 is supplied into the moving blades by being supplied to the supply port of each first-stage moving blade 4 via the flow path 40.
- the steam having passed through the supply hole 27 goes to the supply hole 28, while being guided to the cavity 42 through the slit 41.
- the steam from the cavity 42 is supplied to the second-stage bucket 5 via the flow path 43.
- the steam having passed through the supply hole 26 is directed to the supply hole 27 while being guided to the cavity 44 through the slit 144.
- the steam from the cavities 44 is supplied to the third-stage buckets 6 via the flow passages 45.
- the steam that has cooled the first-stage moving blade 4 and raised in temperature is guided to the cavity 47 via the flow path 46 and reaches the recovery hole 48. Further, the steam that has cooled the second-stage bucket 5 and raised in temperature is led to the cavity 55 through the flow path 54 and merges into the recovery hole 48. Further, the steam whose temperature has risen by cooling the third-stage moving blade 6 is guided to the cavity 57 via the flow path 56, and joins the recovery hole 52.
- the steam that has reached the recovery hole 53 passes through a center-facing flow path 58 provided inside the stub shaft 17, and from a flow path 59 formed by the stub shaft 17 and the separation pipe 19, to the rotor. Collected outside.
- Flow paths 48, 49, 50, 51, 52, 53, from the cavities 47, 55, 57 to the flow path 59 formed by the stub shaft 17 and the separation pipe 19. 5 8 exist in the circumferential direction However, they are arranged so as to be uniform in the circumferential direction and do not intersect with the supply flow paths 41 and 144, and the steam is collected in parallel.
- the steam supply port to the rotor is the internal flow path 20 of the separation pipe 19, and the recovery port is the external flow path 59 of the separation pipe 19, but the supply port and the recovery port are reversed.
- the flow can be in the opposite direction.
- a steam recovery flow path is arranged between the adjacent steam supply flow paths and on the outer peripheral side of the supply flow path in a certain area of the contact surface.
- the steam recovery channel is arranged between adjacent steam supply channels and on the center side of the supply channel, the steam recovery channel is arranged to support the stub shaft 17. For unsupported bearing metal, etc., a more stable temperature can be achieved.
- the supply holes for the purpose of supplying steam passing through the disks and spacers in the axial direction from within the contact surfaces of the solid disks and spacers are formed as supply channels for the supply and recovery channels.
- the first flow path of 4, 25, 26, 27, 28, 29, 30 and recovery holes 48, 49, 50, 51, 52, 5 for the purpose of steam recovery 3 are provided on the disk, spacer contact surfaces 31, 32, 33, 34, 35, 36 are separated by In other words, since separate parts such as a separation pipe and a connecting pipe are not required for separating the first flow path and the second flow path, the accessory parts fall off or are damaged by the action of centrifugal force and thermal stress due to high-speed rotation.
- the disk of the present embodiment must have a wider contact surface as compared with the case where one of the flow paths for supplying and recovering the refrigerant penetrates the contact surfaces 31 to 37. Must.
- a contact surface is formed between the disks 8 to 11 and the spacers 13, 14, 15 to make contact with each other, and an outer peripheral side of a region where the contact surface is formed Through the disk and spacer in the axial direction of the rotor to guide a fluid at a lower temperature than the combustion gas flowing in the gas turbine (110a) 65, 66, 67 , 68, 69, 70, 71, 72, 73, 74, 75, etc.
- An outer channel 110a which is a fourth channel different from the supply channel and the recovery channel, is provided in the mouth.
- the outer flow path 110a includes, as a component, a cavity formed between a hole penetrating the outer peripheral side of a contact area with an adjacent spacer and an adjacent spacer in each disk. .
- a donut-shaped cavity 65 formed by a distance steel 16, a first-stage solid disk 8, and a hollow spacer 12 is provided on the outer peripheral side from the contact surface.
- a donut-shaped cavity 67 formed by the first-stage solid disk 8 and solid space 13 is provided.
- a slit 64 provided radially on the contact surface between the distant piece 16 and the hollow spacer 12 is connected to the cavity 65.
- a part of the air in the compressor air passage 5a flows into the internal space 62 through the slit 61 between the compressor disks 2.
- the compressed air in the internal space 62 is supplied into the cavity 65 through a slit 64 extending radially outward between the distance piece 16 and the hollow spacer 12. Thereafter, it is supplied to the cavity 67 through the hole 66.
- an outer flow path is provided as a fourth flow path flowing through the cavities 65, 67, 69, 71, 73, 75 on the outer peripheral side of the mouth formed by the disc and the spacer. Since the compressor air is flowing there, heat input from the gas turbine gas channel to the center of the turbine rotor 1a can be cut off. Also, the side cavities 65, 67, of the first, second, and third solid disks, Since 69, 71, 73, and 75 have the same air temperature atmosphere, it is possible to suppress asymmetric thermal deformation due to the temperature difference between both sides of the disk. That is, the tilt displacement of the rotor blade located on the outer periphery of the disk is also reduced, and the tip clearance of the rotor blade can be reduced accordingly.
- the outer passage 110a is configured to be connected to the gas passage of the gas turbine through the side surface of the third-stage solid disk 10 so that the air passing through the outer passage 110a Gas can be prevented from entering the side. That is, part of the seal air that prevents gas from entering the disk side surface can be supplemented by the air that has passed through the outer flow passage 110a, and the amount of seal air can be reduced.
- This embodiment is more effective when applied together with the third and fourth embodiments.
- it can also be applied to gas turbines that have a hollow disk with a hole at the center (axis) of the disk.
- the third embodiment can basically have the same basic configuration as the configuration in FIG.
- the main difference from the embodiment shown in FIG. 2 is that the third moving blade 6 that is the second moving blade from the rear is an air-cooled moving blade,
- a channel 201 is provided inside the third-stage solid disk 10 so as to communicate the cavity 73 with the air supply port of the third-stage bucket 6.
- the solid spacer 15 is penetrated in the axial direction so as to connect the cavity 75 formed between the third stage rotor blade 10 and the solid spacer 15 to the cavity 90.
- a hole 203 is provided.
- a flow path 202 is provided inside the third-stage solid disk 10 so as to communicate the cavity 75 with the air supply port of the third-stage moving blade 6.
- the first is that the air branched from the compressor air flow path 5a is, first, from the internal space 62, the slit 64, the cavity 65,? It passes through L 66, cavity 67, hole 68, cavity 69, hole 70, cavity 71, hole 72 and reaches cavity 73. Second, from the internal space 62, the holes 77, cavities 78, holes 79, cavities 80, holes 81, cavities 82, holes 83, cavities 84, holes 85, cavities are provided. 8 6,? 87, cavities 88, slits 89, cavities 90, and from cavities 90 to cavities 75 through holes 203 passing through solid spacers 15 in the axial direction. Reach.
- the air that has reached the cavity 3 and the cavity 75 passes through the channels 201, 202 formed inside the third-stage solid disk 10 by the number of the third-stage rotor blades, and passes through the third passage. It is used as cooling air for the stage rotor blade 6, and the air after the next cooling is discharged from the third stage rotor blade 6 into the gas flow path.
- the gas released from the third-stage moving blade 6 into the gas flow path lowers the gas temperature, and the amount of power recovered by the fourth-stage moving blade 7 downstream therefrom is reduced.In other words, the plant thermal efficiency decreases. It is conceivable, however, that the number of steam cooling blades is reduced, so the required amount of cooling steam is also reduced, and the steam supply equipment can be made smaller. That is, equipment costs can be reduced.
- the total amount of air passing through the third and fourth flow paths is 6 is used for cooling, but if the required amount of air passing through the third and fourth flow paths is equal to or greater than the cooling amount of the third-stage moving blade 6, the surplus is used for the third-stage solid disk 10 , 4th-stage solid disk 11 Can be used for sealing air on one side.
- the cavities 78, 80, 82, 84, 86, 88 and the steam supply passages 24 to 30 or the recovery passages 48 to 53 for cooling the blades are provided.
- the steam flowing through the supply channel is introduced into the cavity, or the steam introduced into the cavity is introduced into the steam recovery channel.
- the center side communication channel 10a connects the cavities 78, 80, 82, 84, 86, 88 with the steam supply channel 8a or the steam recovery channel 9a. It is provided to be. A part of the cooling medium of the rotor blade from the steam supply channel 8a is supplied to the cavity, and then the medium in the cavity flows so as to join the steam recovery channel 9a.
- a steam supply flow path for steam supply (first flow path) 8 Provided in the contact surface 33 toward the center in the radial direction for flowing steam from the supply hole 29, which is a component of 8a, to the cavity 78 The provided slit 103 is provided.
- Kit 104 A slot provided in the contact surface 33 facing the center in the radial direction for collecting steam from the cavities 78 to the supply holes 122, which is a component of the steam recovery channel 9a for steam recovery. Kit 104 is provided.
- slit 105 The steam flowing into the tee 80 is provided so as to be recovered through the slit 106.
- the slit 107, the slit 108, the slit 109, the slit 110, the slit 111, the slit 112, the slit 113, the slit 113 G 1 1 4 will be provided.
- Part of the steam flowing through the supply hole 29 is supplied to the cavity 78 through the slit 103.
- the supplied steam exchanges heat near the center of the first solid disk 8 and the first slit 13.
- the steam can heat the disk and spacer. Thereafter, it is collected in the collection holes 122 through the slit 104.
- the disk portion near the center can be opened, the temperature difference between the outer peripheral side of the mouth and the center portion is reduced, and the thermal stress of the center portion in the radial direction is suppressed. In addition, it is possible to prevent asymmetrical thermal deformation and thermal stress from occurring at the center of the disk.
- the gas turbine which improved the operational reliability of a gas turbine by suppressing the thermal stress which acts on a rotor center part can be provided.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/JP1996/003503 WO1998023851A1 (fr) | 1996-11-29 | 1996-11-29 | Turbine a gaz du type a recuperation du refrigerant |
DE69632837T DE69632837T2 (de) | 1996-11-29 | 1996-11-29 | Gasturbine bei der das kühlmittel wiederverwendet wird |
EP96940152A EP0965726B1 (en) | 1996-11-29 | 1996-11-29 | Refrigerant recovery type gas turbine |
JP52645598A JP3634871B2 (ja) | 1996-11-29 | 1996-11-29 | ガスタービン |
US09/308,981 US6393829B2 (en) | 1996-11-29 | 1996-11-29 | Coolant recovery type gas turbine |
US10/782,966 US7028487B2 (en) | 1996-11-29 | 2004-02-23 | Coolant recovery type gas turbine |
US10/782,961 US7028486B2 (en) | 1996-11-29 | 2004-02-23 | Coolant recovery type gas turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/JP1996/003503 WO1998023851A1 (fr) | 1996-11-29 | 1996-11-29 | Turbine a gaz du type a recuperation du refrigerant |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/754,383 Division US6370866B2 (en) | 1996-11-29 | 2001-01-05 | Coolant recovery type gas turbine |
Related Child Applications (4)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09308981 A-371-Of-International | 1996-11-29 | ||
US09/308,981 A-371-Of-International US6393829B2 (en) | 1996-11-29 | 1996-11-29 | Coolant recovery type gas turbine |
US09/754,383 Division US6370866B2 (en) | 1996-11-29 | 2001-01-05 | Coolant recovery type gas turbine |
US10/082,062 Division US6568191B2 (en) | 1996-11-29 | 2002-02-26 | Coolant recovery type gas turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1998023851A1 true WO1998023851A1 (fr) | 1998-06-04 |
Family
ID=14154172
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP1996/003503 WO1998023851A1 (fr) | 1996-11-29 | 1996-11-29 | Turbine a gaz du type a recuperation du refrigerant |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP0965726B1 (ja) |
JP (1) | JP3634871B2 (ja) |
DE (1) | DE69632837T2 (ja) |
WO (1) | WO1998023851A1 (ja) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0909878A3 (en) * | 1997-10-17 | 2000-07-19 | Hitachi, Ltd. | Gas turbine |
JP2000282802A (ja) * | 1998-12-22 | 2000-10-10 | General Electric Co <Ge> | 熱媒体によるタービンロータ部品間の熱的不整合の調整 |
US6568192B2 (en) * | 1999-11-05 | 2003-05-27 | Hitachi, Ltd. | Gas turbine, gas turbine apparatus, and refrigerant collection method for gas turbine moving blades |
US6831144B2 (en) | 1999-08-24 | 2004-12-14 | Kuraray Co., Ltd. | Anionic polymerization process, and process for producing a polymer by the anionic polymerization process |
JP2021134705A (ja) * | 2020-02-26 | 2021-09-13 | 東芝エネルギーシステムズ株式会社 | タービン |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6053701A (en) * | 1997-01-23 | 2000-04-25 | Mitsubishi Heavy Industries, Ltd. | Gas turbine rotor for steam cooling |
DE10208085A1 (de) * | 2002-02-25 | 2003-09-04 | Alstom Switzerland Ltd | Rotor für eine thermische Turbomaschine |
EP1577493A1 (de) * | 2004-03-17 | 2005-09-21 | Siemens Aktiengesellschaft | Strömungsmaschine und Rotor für eine Strömungsmaschine |
US8137067B2 (en) * | 2008-11-05 | 2012-03-20 | General Electric Company | Turbine with interrupted purge flow |
RU2539404C2 (ru) * | 2010-11-29 | 2015-01-20 | Альстом Текнолоджи Лтд | Осевая газовая турбина |
US9334753B2 (en) * | 2011-10-12 | 2016-05-10 | General Electric Company | Control system and methods for controlling the operation of power generation systems |
US8997498B2 (en) * | 2011-10-12 | 2015-04-07 | General Electric Company | System for use in controlling the operation of power generation systems |
DE102013005431B4 (de) * | 2013-03-28 | 2022-12-08 | Man Energy Solutions Se | Axialströmungsmaschine |
KR101744411B1 (ko) * | 2015-10-15 | 2017-06-20 | 두산중공업 주식회사 | 가스터빈의 냉각장치 |
EP3205817A1 (en) * | 2016-02-09 | 2017-08-16 | Ansaldo Energia Switzerland AG | Fluid cooled rotor for a gas turbine |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS648504U (ja) * | 1987-07-03 | 1989-01-18 | ||
JPH03275946A (ja) | 1990-03-26 | 1991-12-06 | Toshiba Corp | ガスタービン |
JPH0814064A (ja) * | 1994-06-24 | 1996-01-16 | Hitachi Ltd | ガスタービン及びその段落装置 |
JPH08277725A (ja) * | 1995-04-06 | 1996-10-22 | Hitachi Ltd | ガスタービン |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6053701A (en) * | 1997-01-23 | 2000-04-25 | Mitsubishi Heavy Industries, Ltd. | Gas turbine rotor for steam cooling |
-
1996
- 1996-11-29 WO PCT/JP1996/003503 patent/WO1998023851A1/ja active IP Right Grant
- 1996-11-29 EP EP96940152A patent/EP0965726B1/en not_active Expired - Lifetime
- 1996-11-29 DE DE69632837T patent/DE69632837T2/de not_active Expired - Fee Related
- 1996-11-29 JP JP52645598A patent/JP3634871B2/ja not_active Expired - Lifetime
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS648504U (ja) * | 1987-07-03 | 1989-01-18 | ||
JPH03275946A (ja) | 1990-03-26 | 1991-12-06 | Toshiba Corp | ガスタービン |
JPH0814064A (ja) * | 1994-06-24 | 1996-01-16 | Hitachi Ltd | ガスタービン及びその段落装置 |
JPH08277725A (ja) * | 1995-04-06 | 1996-10-22 | Hitachi Ltd | ガスタービン |
Non-Patent Citations (1)
Title |
---|
See also references of EP0965726A4 * |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0909878A3 (en) * | 1997-10-17 | 2000-07-19 | Hitachi, Ltd. | Gas turbine |
US6185924B1 (en) | 1997-10-17 | 2001-02-13 | Hitachi, Ltd. | Gas turbine with turbine blade cooling |
EP1329590A2 (en) * | 1997-10-17 | 2003-07-23 | Hitachi, Ltd. | Coolant recirculation type gas turbine |
EP1329590A3 (en) * | 1997-10-17 | 2003-07-30 | Hitachi, Ltd. | Coolant recirculation type gas turbine |
EP1428984A2 (en) * | 1997-10-17 | 2004-06-16 | Hitachi, Ltd. | Air-cooled gas turbine |
EP1428984A3 (en) * | 1997-10-17 | 2004-06-23 | Hitachi, Ltd. | Air-cooled gas turbine |
JP2000282802A (ja) * | 1998-12-22 | 2000-10-10 | General Electric Co <Ge> | 熱媒体によるタービンロータ部品間の熱的不整合の調整 |
JP4592854B2 (ja) * | 1998-12-22 | 2010-12-08 | ゼネラル・エレクトリック・カンパニイ | 熱媒体によるタービンロータ部品間の熱的不整合の調整 |
US6831144B2 (en) | 1999-08-24 | 2004-12-14 | Kuraray Co., Ltd. | Anionic polymerization process, and process for producing a polymer by the anionic polymerization process |
US6568192B2 (en) * | 1999-11-05 | 2003-05-27 | Hitachi, Ltd. | Gas turbine, gas turbine apparatus, and refrigerant collection method for gas turbine moving blades |
US6877324B2 (en) | 1999-11-05 | 2005-04-12 | Hitachi, Ltd. | Gas turbine, gas turbine apparatus, and refrigerant collection method for gas turbine moving blades |
JP2021134705A (ja) * | 2020-02-26 | 2021-09-13 | 東芝エネルギーシステムズ株式会社 | タービン |
Also Published As
Publication number | Publication date |
---|---|
DE69632837D1 (de) | 2004-08-05 |
EP0965726A1 (en) | 1999-12-22 |
DE69632837T2 (de) | 2005-07-07 |
EP0965726B1 (en) | 2004-06-30 |
JP3634871B2 (ja) | 2005-03-30 |
EP0965726A4 (en) | 2001-10-17 |
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