WO2010001656A1 - ガスタービンの冷却空気供給構造およびガスタービン - Google Patents
ガスタービンの冷却空気供給構造およびガスタービン Download PDFInfo
- Publication number
- WO2010001656A1 WO2010001656A1 PCT/JP2009/057984 JP2009057984W WO2010001656A1 WO 2010001656 A1 WO2010001656 A1 WO 2010001656A1 JP 2009057984 W JP2009057984 W JP 2009057984W WO 2010001656 A1 WO2010001656 A1 WO 2010001656A1
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- Prior art keywords
- rotor
- turbine
- passage
- cooling air
- cavity
- 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
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and 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
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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
- F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
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- 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
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- 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
- F02C7/28—Arrangement of seals
Definitions
- the present invention relates to a cooling air supply structure for a gas turbine that supplies cooling air to turbine blades, and a gas turbine.
- the gas turbine is composed of a compressor, a combustor, and a turbine.
- the compressor compresses the air taken in from the air intake to produce high-temperature and high-pressure compressed air.
- the combustor generates high-temperature and high-pressure combustion gas by supplying fuel to the compressed air and burning it.
- the turbine is configured by alternately arranging a plurality of turbine stationary blades and turbine rotor blades in a casing, and the turbine rotor blades are driven by the combustion gas supplied to the exhaust passage to connect the generator. The rotor is rotated.
- the combustion gas that has driven the turbine is converted into a static pressure by the diffuser and then released to the atmosphere.
- the combustion gas acting on the plurality of turbine blades reaches 1500 ° C., and the turbine blades may be heated and damaged. Cooled by supplying to the moving blades.
- Some conventional gas turbines take out air from a compressor and supply this air as cooling air to turbine blades.
- Such a conventional gas turbine cooling air supply structure is provided with an introduction passage extending in the radial direction of the rotor inside the turbine vane.
- the introduction passage is connected to an external pipe connected to the compressor on the outer peripheral side of the turbine stationary blade, and is connected to the air passage on the inner peripheral side of the turbine stationary blade.
- the air passage is provided facing the rotor side and with the discharge port directed in the rotation direction of the rotor.
- a rotor cavity is provided on the rotor side in a space surrounded by the disk and the rotor radially inward from the stationary blade.
- the rotor cavity is formed with an opening for introducing moving blade cooling air toward the outer diameter direction of the rotor, and the turbine motion of the subsequent stage of the turbine stationary blade via a pressure increasing passage extending in the radial direction of the rotor. It is connected to a cooling passage provided inside the blade. Then, the cooling air led from the compressor to the introduction passage of the turbine vane through the external pipe is given a swirl flow by being discharged by the air passage with a velocity component in the same direction as the rotation of the rotor, and the rotor The air is fed into the cavity while the relative speed with respect to the peripheral speed is reduced, and is supplied to the cooling passage through the pressure increase passage.
- a seal member that prevents leakage of cooling air into the casing is provided between the inner peripheral side of the turbine stationary blade and the outer peripheral surface of the rotor (see, for example, Patent Documents 1 and 2).
- JP-T-2002-517652 gazette JP 2000-310127 A
- the opening of the cavity is formed on the outer peripheral surface of the rotor, and the discharge port of the air passage is provided on the inner peripheral side of the turbine vane facing the outer peripheral surface of the rotor. ing.
- the discharge port of the air passage is farther in the radial direction from the central axis that is the rotation center of the rotor than the connection port to the boosting passage in the cavity. For this reason, the rotation of the rotor causes the pressure at the position of the connection port of the pressure increase passage to be lower than the position of the discharge port of the air passage.
- the pressure acting on the seal member is increased and the differential pressure is increased, so that the cooling air leaks to the combustion gas side and the thermal efficiency of the gas turbine is reduced.
- the present invention has been made in view of the above, and provides a cooling air supply structure for a gas turbine and a gas turbine capable of reducing leakage of cooling air passing through the cavity to the combustion gas side. Objective.
- cooling air supply structure for a gas turbine of the present invention fuel is supplied to the compressed air compressed by the compressor and burned, and the generated combustion gas is supplied to the turbine casing of the turbine.
- a cooling air supply structure for a gas turbine that is provided in a gas turbine that obtains rotational power of the rotor and supplies cooling air to the turbine rotor blades of the turbine, provided in the interior of the turbine vane fixed in the turbine casing
- the turbine casing in a manner communicating with the introduction passage, an introduction passage communicating with the inside and outside of the turbine casing, a rotor cavity having a space provided on the rotor side and having an opening along a circumferential direction of the rotor, and the introduction passage.
- a cooling air outlet is provided at the inner periphery of the blade and faces the opening of the rotor cavity, and a swirler is provided at the outlet.
- a cooling passage and a pressure increasing passage communicating with the cooling cavity to the cooling passage, and a discharge port of the nozzle and a connection port of the rotor cavity to the pressure increasing passage are radially formed from the central axis of the rotor. It is characterized by being arranged with the same distance.
- the seal member is constituted by a brush seal.
- fuel is supplied to the compressed air compressed by the compressor and burned by the combustor, and the generated combustion gas is sent to the turbine casing of the turbine to rotate the rotor.
- an introduction passage provided inside a turbine stationary blade fixed in the turbine casing and communicating between the inside and the outside of the turbine casing, and provided on the rotor side along the circumferential direction of the rotor
- a rotor cavity that forms a space having an opening, and is provided in an inner peripheral portion of the turbine vane in a manner communicating with the introduction passage, and a cooling air discharge port is directed to the opening of the rotor cavity and is directed to the discharge port.
- the connection port to the boosting passage is arranged with a radial distance from the central axis of the rotor.
- the gas turbine of the present invention is characterized in that the seal member is constituted by a brush seal.
- the nozzle discharge port and the connection port of the pressure increasing passage are arranged at equal distances from the central axis of the rotor in the radial direction, the cooling immediately after being discharged from the nozzle discharge port It is possible to make the pressure of the air coincide with the pressure of the cooling air sent from the connection port to the pressure increasing passage.
- the differential pressure applied to the upstream seal member can be reduced, leakage of cooling air into the turbine casing can be prevented, and a reduction in heat exchange of the gas turbine can be suppressed.
- FIG. 1 is a schematic configuration diagram showing a gas turbine according to the present invention.
- FIG. 2 is a schematic configuration diagram showing the turbine internal structure of the embodiment of the gas turbine shown in FIG.
- FIG. 3 is a pressure change diagram of the cooling air of the gas turbine shown in FIG.
- FIG. 4 is a schematic configuration diagram showing a turbine internal structure of a conventional example in a gas turbine.
- the gas turbine cooling air supply structure and gas turbine supply the extracted air taken out from the intermediate stage of the compressor to the moving blade as cooling blade cooling air for the turbine through the turbine stationary blade.
- the gas turbine includes a compressor 1, a combustor 2, and a turbine 3.
- the compressor 1 has an air intake port 11 for taking in air, a plurality of compressor vanes 13 and compressor blades 14 are alternately arranged in a compressor casing 12, and a bleed manifold 15 is provided on the outside thereof. It has been.
- the combustor 2 supplies fuel to the compressed air compressed by the compressor 1 and ignites it with a burner to produce high-temperature and high-pressure combustion gas.
- a plurality of turbine stationary blades 32 and turbine rotor blades 33 are alternately arranged in a turbine casing 31.
- An exhaust chamber 34 having an exhaust diffuser 34 a continuous with the turbine 3 is provided on the rear side of the turbine casing 31. Further, the rotor 4 is disposed so as to penetrate through the center of the compressor 1, the combustor 2, the turbine 3, and the exhaust chamber 34.
- the rotor 4 has an end portion on the compressor 1 side supported by a bearing portion 41, while an end portion on the exhaust chamber 34 side is supported by a bearing portion 42, and is provided so as to be rotatable about its own central axis S. It has been.
- a plurality of disks (fixing members) are fixed to the rotor 4, the rotor blades 14 and 33 are connected to each other, and a drive shaft of a generator (not shown) is connected to the end on the exhaust chamber 34 side. ing.
- the air taken in from the air intake port 11 of the compressor 1 passes through the plurality of compressor stationary blades 13 and the compressor moving blades 14 and is compressed to become high-temperature and high-pressure compressed air, and the combustor 2
- the fuel is burned by supplying a predetermined fuel to the compressed air.
- the high-temperature and high-pressure combustion gas generated in the combustor 2 passes through the plurality of turbine stationary blades 32 and the turbine rotor blades 33 constituting the turbine 3 to rotationally drive the rotor 4. Electric power is generated by applying rotational power to the generator connected to.
- the exhaust gas that rotationally drives the rotor 4 is converted to static pressure by the exhaust diffuser 34a in the exhaust chamber 34 and then released to the atmosphere.
- an introduction passage 324 is provided in the turbine stationary blade 32.
- the introduction passage 324 is formed of a tubular body provided inside the stationary blade 321 so as to extend along the stationary blade 321 in the radial direction of the rotor 4 (direction of arrow A shown in FIG. 2).
- the introduction passage 324 introduces cooling air from the outside of the turbine casing 31 by communicating with the external pipe 5 outside the turbine casing 31.
- the introduction passage 324 passes through the inner shroud 322 of the stationary blade 321.
- a retaining ring 323 formed in an annular shape along the circumferential direction of the rotor 4 is provided on the inner peripheral portion of the turbine stationary blade 321.
- a stationary blade cavity 325 forming a space is formed inside the holding ring 323, and an end portion of the introduction passage 324 is disposed in the stationary blade cavity 325. That is, the stationary blade cavity 325 communicates with the introduction passage 324.
- the cooling air supplied to the stationary blade cavity 325 is on a plane parallel to the rotor center axis S from the tips of the plurality of nozzles 326 provided at the lower portion (inner side in the rotor radial direction) of the stationary blade cavity 325, In addition, a swirling flow is blown toward the rotor cavity 334 in a direction having a certain angle with respect to the rotor center axis S.
- the turbine rotor blade 33 fixed to the rotor 4 side includes a plurality of rotor blades 331.
- the moving blade 331 is attached in an annular shape along the outer peripheral surface of the disk (fixing member) 333.
- the adjacent disks 333 are stacked in the extending direction of the central axis S of the rotor 4 (in the direction of arrow B shown in FIG. 2) and fastened with a spindle bolt (not shown), so that the rotor 4 is integrated as a whole. Is forming.
- a plate-like arm portion 333a is projected from the disk 333 located on the downstream side toward the upstream side in the axial direction of the rotor 4 (left side as viewed from the front in FIG. 2).
- a seal portion 328 is provided between the inner peripheral end surface 323 a of the holding ring 323.
- the rotor cavity 334 is disposed on the inner side in the rotor radial direction from the arm portion 333a, and is formed by being surrounded by the plate-like arm portion 333b protruding from the mutually facing surfaces of the adjacent disks 333 and the arm portion 333a.
- These arm portions 333 a and 333 b are formed in an annular shape along the circumferential direction of the rotor 4.
- a seal portion 329 is provided in a gap between the arm portion 333 b protruding from the disk 333 located on the upstream side and the inner peripheral end surface 323 b of the holding ring 323, and the cooling air leaks to the upstream combustion chamber cavity 351. Is preventing.
- a seal member 335 closes between the opposing tips of the pair of arm portions 333 b protruding from the upstream and downstream disks 333.
- the space of the rotor cavity 334 including the facing surface of the adjacent disk 333 and having the opening 334 a facing the upstream side along the circumferential direction of the rotor 4 is annularly defined along the circumferential direction of the rotor 4. ing.
- a purge hole 323c for purging the cooling air in the stationary vane cavity 325 toward the upstream combustion chamber cavity 351 is formed in the lower wall surface of the holding ring 323 (the side closer to the center of the rotor 4). ing.
- the purge hole 323 c plays a role of preventing the combustion gas on the combustion gas (gas path) side from flowing backward to the upstream combustion chamber cavity 351 by continuously blowing out a small amount of cooling air.
- the downstream disk 333 forming the rotor cavities 334 is annularly arranged in a sectional view cut by a plane perpendicular to the rotor axial direction.
- a plurality of cooling passages 336 and pressure increase passages 337 are formed.
- the cooling passage 336 is formed along the extending direction of the central axis S of the rotor 4 inside the disk 333, and is disposed on the outer side in the radial direction of the rotor 4 with respect to the rotor cavity 334, and the moving blade 331 at the moving blade bottom 331a.
- the pressure increasing passage 337 extends in the radial direction of the rotor 4 and communicates with the cooling passage 336 on the downstream side of the pressure increasing passage 337.
- the upstream side of the pressure increasing passage 337 communicates with the rotor cavity 334 via the connection port 337a. Therefore, the cooling air in the rotor cavity 334 is introduced from the connection port 337a of the pressure increasing passage 337 into the pressure increasing passage 337 formed in the disk 333, flows in the cooling passage 336, and flows from the blade bottom 331a to the moving blade 331. Then, after cooling the inner wall and the like of the moving blade 331, it is discharged into the combustion gas.
- the nozzle 326 disposed on the inner side in the radial direction of the retaining ring 323 of the turbine stationary blade 321 is disposed to face the opening 334 a of the rotor cavity 334.
- the nozzle 326 has a plurality of discharge ports 326 a along the circumferential direction of the rotor 4, and the discharge ports 326 a are provided in parallel to the rotor axis toward the opening 334 a of the rotor cavity 334.
- a swirler 327 is provided at the discharge port 326 a of the nozzle 326. The swirler 327 guides the cooling air toward the rotation direction of the rotor 4 and gives a swirl flow to the cooling air so that the cooling air easily moves to the rotor cavity 334 side.
- the nozzle 326 provided with the swirler 327 is annularly arranged around the central axis S of the rotor 4 so that the cooling air is blown at a certain angle in the rotation direction of the rotor 4 with respect to the central axis S of the rotor 4. .
- the discharge port 326 a of the nozzle 326 is within the range of the inlet cross section of the opening 334 a of the rotor cavity 334, and the discharge port 326 a of the nozzle 326 and the connection port 337 a of the pressure increase passage 337 have a radius from the central axis S of the rotor 4. They are arranged with the same distance in the direction.
- the type of the nozzle 326 may be either a tubular nozzle or a wing type nozzle.
- the seal portion 328 is provided between the inner peripheral end surface 323a of the retaining ring 323 of the turbine stationary blade 321 and the outer peripheral surface of the arm portion 333a. Further, a seal portion 329 is disposed between the arm portion 333 b protruding from the upstream disk 333 and the inner peripheral end surface 323 b of the holding ring 323. The presence of these seal portions 328 and 329 prevents the cooling air from leaking into the downstream combustion chamber cavity 352 and the upstream combustion chamber cavity 351, thereby avoiding a decrease in the thermal efficiency of the gas turbine.
- the seal portion 328 is composed of a brush seal 328a and a labyrinth seal 328b, and the seal portion 329 is composed of a brush seal, but is not limited to this type.
- a leaf seal may be used instead of the brush seal, and other seal types may be used.
- cooling air supply structure configured in this way, a part of the compressed air compressed by the compressor 1 is extracted from the extraction manifold 15 of the compressor casing 12 by the external pipe 5, and this compressed air is used as cooling air for turbine static It is fed into the introduction passage 324 of the blade 321.
- the cooling air is discharged from the discharge port 326 a of the nozzle 326 through the stationary blade cavity 325.
- the cooling air discharged from the nozzle 326 is discharged with the same tangential speed component as the rotation direction of the rotor 4, thereby reducing the relative speed difference with the rotor 4.
- connection port 337a By matching the speed component of the discharged cooling air in the rotor rotation direction with the peripheral speed at the connection port 337a, pressure loss is suppressed when the cooling air is introduced from the connection port 337a to the pressure increase passage 337. it can.
- the cooling air sent into the rotor cavity 334 is pressurized by the pumping action of the centrifugal force in the pressure increasing passage 337, supplied to the cooling passage 336, and released from the blade bottom 331a to the turbine blade 331. In this way, the turbine blade 33 is cooled by the cooling air supplied to the turbine blade 33.
- the pressure change is displayed on the downstream side of the pressure increase passage 337 (P3), in the cooling passage 336 (P4), and the moving blade
- the combustion gas (P5) in the vicinity of 331, the upstream side of the seal part 329 (P6), and the downstream side of the seal part 329 (P7: upstream side combustion cavity 351) were targeted.
- a change in pressure can be calculated from the principle of a free vortex that rotates and flows. At other locations, the pressure change is calculated from the pressure loss of the fluid.
- Expression 1 is an expression showing a relative pressure change at the comparison position 2 with respect to the reference position 1.
- connection port 337a shows the change in pressure at the connection port 337a (comparison position P2) located at the downstream end of the cooling air flow in the rotor cavity 334, with the pressure at the discharge port 326a (reference position P1) as the reference pressure. Indicated. Further, the pressure in the rotor cavity 334 (connection port 337a (P2)) is indicated as a reference pressure.
- the horizontal axis displays each target position, and the vertical axis indicates the pressure.
- the solid line indicates the case of the present invention, and the dotted line indicates the case of the conventional example.
- the position of the connection port 337 a of the pressure increasing passage 337 in the rotor cavity 334 is smaller than the position of the nozzle discharge port 326 a by the distance from the rotation center of the rotor 4 ( The inner side of the rotor radial direction).
- the structure shown in FIG. 4 is basically the same as the structure shown in FIG. 2, except that the shape of the nozzle 326, the discharge direction of the discharge port 326a, and the relative position of the discharge port 326a and the rotor cavity 334 are different. This is different from the case of the present invention shown in FIG. Therefore, the same reference numerals are used in FIGS. 2 and 4 for the configuration of each common part, and detailed description thereof is omitted.
- the distances from the rotor rotation center of the discharge port 326a (P1) and the connection port 337a (P2) of the nozzle 326 are set to be the same.
- the pressure is the same according to Equation 1, and as shown by the solid line in FIG. 3, there is almost no pressure change from the discharge port 326a (P1) to the connection port 337a (P2), and the pressure is almost constant.
- the discharge port 326a (P1) has a longer distance from the rotor rotation center than the connection port 337a (P2).
- the pressure of P2) is lower than the discharge port 326a (P1). This is shown in FIG.
- the pressure in the rotor cavity 334 is considered to be the same pressure at any place as long as the distance from the center of rotation does not change, and there is no problem.
- the cooling air that has flowed into the pressure increase passage 337 from the connection port 337a is pressurized in the pressure increase passage 337. That is, the pressure increasing passage 337 is a flow path radially disposed in the disk 333, and the cooling air flowing in from the connection port 337a (P2) receives a centrifugal force and is boosted by its pumping action. Further, when the cooling air flows in the cooling passage 336 and flows into the moving blade 331 from the moving blade blade bottom 331a, the pressure is slightly reduced due to pressure loss. The cooling air supplied into the moving blade 331 is discharged into the combustion gas (P5) after cooling the inside of the moving blade 331.
- the pressure in the rotor cavity 334 is uniquely determined from the pressure on the combustion gas side (P5) at the end of the rotor blade 331 from which the cooling air is discharged. That is, the pressure of the rotor cavity 334 can be calculated by adding the pressure loss of the cooling air passage to the pressure of the combustion gas flow.
- the pressure of the combustion gas (P5) in the vicinity of the moving blade 331 is lower than the downstream side (P7) of the seal portion 329 because the combustion gas passes through the stationary blade 321 and the moving blade 331 and a pressure loss occurs.
- the same concept can be applied to the present invention and the conventional example. Therefore, the pressure change from the connection port 337a (P2) of the pressure increasing passage 337 to the combustion gas side (P5) in the vicinity of the moving blade 331 through the moving blade 331, as shown by the solid line in FIG. Same pressure change.
- the pressure in the vicinity of the discharge port 326a of the nozzle 326 is different between the present invention and the conventional example, and leakage of cooling air to the combustion gas side becomes a problem.
- the discharge port 326a (P1) of the nozzle 326 and the rotor cavity 334 are at the same distance from the rotation center of the rotor 4, and no differential pressure is generated between them.
- the rotation radius r is different as described above, a pressure difference is generated. That is, since the position of the seal portion 329 is close to the discharge port 326a of the nozzle 326, in the conventional example, the pressure in the discharge port 326a (P1) is higher than the pressure in the rotor cavity 334 (connection port 337a (P2)).
- the pressure of the discharge port 326a (P1) of the nozzle 326 is relatively higher than that in the rotor cavity 334 (connection port 337a (P2)).
- the upstream side (P6) of the seal portion 329 in the vicinity also shows substantially the same pressure. Therefore, a relatively large differential pressure is generated between the upstream combustion gas cavity 351 (P7) and the upstream side (P6) of the seal portion 329, and the cooling air may leak through the seal portion 329.
- the discharge port 326a (P1) of the nozzle 326 and the connection port 337a (P2) to the pressure increase passage 337 of the rotor cavity 334 are provided.
- the cooling air at the nozzle 326 is adjusted so that the speed component in the rotor rotation direction of the cooling air immediately after being discharged from the discharge port 326a (P1) of the nozzle 326 matches the peripheral speed of the connection port 337a (P2). Is selected, the pressure loss of the cooling air at the connection port 337a (P2) can be minimized. As a result, the pressure change of the cooling air from the rotor cavity 334 to the rotor blade 331 can be stabilized, and the reliability of the cooling performance can be improved.
- the cooling air in the stationary vane cavity 325 is purged to the upstream combustion chamber cavity 351 little by little via the purge hole 323c provided in the holding ring 323, and is discharged from the combustion gas (gas path) side. Prevents backflow of combustion gas.
- the differential pressure at the seal portion 329 pressure difference between the upstream combustion chamber cavity 351 (P7) and the upstream side (P6) of the seal portion 329) is large as in the prior art, the seal portion 329
- the cooling air in the rotor cavity 334 leaks from the seal portion 329 to the upstream combustion chamber cavity 351, and the amount of cooling air supplied to the moving blades decreases. The rotor blades cannot be cooled sufficiently.
- the discharge port 326a (P1) of the nozzle 326 and the connection port 337a (P2) to the pressure increase passage 337 of the rotor cavity 334 are arranged in the radial direction from the central axis S of the rotor 4. Therefore, the differential pressure is not generated between the upstream combustion chamber cavity 351 (P7) and the upstream side (P6) of the seal portion 329, and the pressures can be made substantially the same.
- the present invention it is possible to minimize the leakage of the cooling air amount to the combustion gas side, to stably supply the cooling air to the moving blade, and to prevent the thermal efficiency of the gas turbine from being lowered.
- the cooling air supply structure of the gas turbine may be applied to the turbine blades 33 of all stages of the turbine 3, but for the turbine blades 33 of a predetermined stage to be cooled. It may be applied.
- the nozzle outlet and the connection port of the pressure increasing passage are arranged at equal distances from the central axis of the rotor in the radial direction, immediately after being discharged from the nozzle outlet. It is possible to make the pressure of the cooling air coincide with the pressure of the cooling air sent from the connection port to the pressure increasing passage. As a result, since the differential pressure applied to the upstream seal member can be reduced, leakage of cooling air into the turbine casing can be prevented, and a reduction in heat exchange of the gas turbine can be suppressed.
- the cooling air supply structure for a gas turbine and the gas turbine according to the present invention are useful for supplying cooling air to a turbine rotor blade, and in particular, when supplying cooling air to a rotor blade, It is suitable for providing a device that suppresses air leakage.
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- General Engineering & Computer Science (AREA)
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Abstract
Description
(数1)P2/P1={1+〔(k-1)/k〕}×〔(r2×Vθ2)2/2RT1〕×〔(1/r1)2-(1/r2)2〕(k/1-k)
11 空気取入口
12 圧縮機ケーシング
13 圧縮機静翼
14 圧縮機動翼
15 抽気マニホールド
2 燃焼器
3 タービン
31 タービンケーシング
32 タービン静翼
321 静翼
322 内側シュラウド
323 保持環
324 導入通路
325 静翼キャビティ
326 ノズル
327 スワラー
328 シール部
328a ブラシシール(シール部材)
328b ラビリンスシール
329 シール部
33 タービン動翼
331 動翼
331a 動翼翼底
332 プラネットホーム
333 ディスク(固定部材)
333a,333b アーム部
334 ロータキャビティ
334a 開口
335 シール部材
336 冷却通路
337 昇圧通路
337a 接続口
34 排気室
34a 排気ディフューザ
351 上流側燃焼室キャビティ
352 下流側燃焼室キャビティ
4 ロータ
41,42 軸受部
5 外部配管
51 外部クーラ
S 中心軸線
Claims (4)
- 圧縮機で圧縮した圧縮空気に燃焼器で燃料を供給して燃焼させ、発生した燃焼ガスをタービンのタービンケーシングに送ってロータの回転動力を得るガスタービンに設けられ、前記タービンのタービン動翼に冷却空気を供給するガスタービンの冷却空気供給構造において、
前記タービンケーシング内に固定されたタービン静翼の内部に設けられて前記タービンケーシングの内外を連通する導入通路と、
前記ロータ側に設けられて該ロータの周方向に沿う開口を有した空間を成すロータキャビティと、
前記導入通路に連通する態様で前記タービン静翼の内周部に設けられて前記ロータキャビティの開口に冷却空気の吐出口を向け、かつ前記吐出口にスワラーを有したノズルと、
前記タービン静翼と前記ロータ側との間に設けられたシール部材と、
前記ロータに固定されて該ロータと共に回転し、かつ前記タービン動翼を固定する固定部材の内部に設けられた冷却通路と、
前記冷却通路に前記ロータキャビティを連通する昇圧通路と
を備え、前記ノズルの吐出口と前記ロータキャビティの前記昇圧通路への接続口とを、前記ロータの中心軸線から半径方向への距離を揃えて配置したことを特徴とするガスタービンの冷却空気供給構造。 - 前記シール部材がブラシシールから構成されていることを特徴とする請求項1に記載のガスタービンの冷却空気供給構造。
- 圧縮機で圧縮した圧縮空気に燃焼器で燃料を供給して燃焼させ、発生した燃焼ガスをタービンのタービンケーシングに送ってロータの回転動力を得るガスタービンにおいて、
前記タービンケーシング内に固定されたタービン静翼の内部に設けられて前記タービンケーシングの内外を連通する導入通路と、
前記ロータ側に設けられて該ロータの周方向に沿う開口を有した空間を成すロータキャビティと、
前記導入通路に連通する態様で前記タービン静翼の内周部に設けられて前記ロータキャビティの開口に冷却空気の吐出口を向け、かつ前記吐出口にスワラーを有したノズルと、
前記タービン静翼と前記ロータ側との間に設けられたシール部材と、
前記ロータに固定されて該ロータと共に回転し、かつ前記タービン動翼を固定する固定部材の内部に設けられた冷却通路と、
前記冷却通路に前記ロータキャビティを連通する昇圧通路と
を備え、前記ノズルの吐出口と前記ロータキャビティの前記昇圧通路への接続口とを、前記ロータの中心軸線から半径方向への距離を揃えて配置したことを特徴とするガスタービン。 - 前記シール部材がブラシシールから構成されていることを特徴とする請求項3に記載のガスタービン。
Priority Applications (3)
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EP09773234.1A EP2325459B1 (en) | 2008-06-30 | 2009-04-22 | Cooling air supply structure of gas turbine and gas turbine |
CN200980124186.9A CN102076939B (zh) | 2008-06-30 | 2009-04-22 | 燃气轮机的冷却空气供给构造和燃气轮机 |
JP2010518956A JPWO2010001656A1 (ja) | 2008-06-30 | 2009-04-22 | ガスタービンの冷却空気供給構造およびガスタービン |
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US12/164,793 US8079803B2 (en) | 2008-06-30 | 2008-06-30 | Gas turbine and cooling air supply structure thereof |
US12/164,793 | 2008-06-30 |
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WO2010001656A1 true WO2010001656A1 (ja) | 2010-01-07 |
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US (1) | US8079803B2 (ja) |
EP (1) | EP2325459B1 (ja) |
JP (1) | JPWO2010001656A1 (ja) |
KR (1) | KR20110021933A (ja) |
CN (1) | CN102076939B (ja) |
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US20090324388A1 (en) | 2009-12-31 |
US8079803B2 (en) | 2011-12-20 |
EP2325459A1 (en) | 2011-05-25 |
JPWO2010001656A1 (ja) | 2011-12-15 |
CN102076939B (zh) | 2014-04-02 |
CN102076939A (zh) | 2011-05-25 |
EP2325459B1 (en) | 2016-04-20 |
KR20110021933A (ko) | 2011-03-04 |
EP2325459A4 (en) | 2015-01-28 |
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