WO2024142889A1 - 蒸気タービン - Google Patents

蒸気タービン Download PDF

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Publication number
WO2024142889A1
WO2024142889A1 PCT/JP2023/044271 JP2023044271W WO2024142889A1 WO 2024142889 A1 WO2024142889 A1 WO 2024142889A1 JP 2023044271 W JP2023044271 W JP 2023044271W WO 2024142889 A1 WO2024142889 A1 WO 2024142889A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
dimensional
axial direction
downstream
blades
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2023/044271
Other languages
English (en)
French (fr)
Japanese (ja)
Inventor
智晃 野上
智貴 大内
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Compressor Corp
Original Assignee
Mitsubishi Heavy Industries Compressor Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Compressor Corp filed Critical Mitsubishi Heavy Industries Compressor Corp
Priority to CN202380088594.3A priority Critical patent/CN120418523A/zh
Priority to DE112023004470.8T priority patent/DE112023004470T5/de
Publication of WO2024142889A1 publication Critical patent/WO2024142889A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • 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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines

Definitions

  • a steam turbine comprises a rotor (turbine rotor) disposed within a casing, a row of rotor blades provided radially outside the rotor, a diaphragm provided radially inside the casing, and a row of stator blades supported radially inside the diaphragm (see, for example, Patent Document 1).
  • the steam turbine of the present disclosure comprises a rotor shaft rotatable about an axis, a plurality of rotor blade rows fixed to the outside of the rotor shaft in a radial direction based on the axis and arranged at intervals in the axial direction along which the axis extends, a casing covering the rotor shaft and the plurality of rotor blade rows from the outside in the radial direction and having a main flow passage through which steam can flow, and a plurality of stator blade rows fixed to the inside of the casing in the radial direction and arranged on a first side in the axial direction with respect to each of the plurality of rotor blade rows, the plurality of rotor blade rows comprising a plurality of upper flow blade rows arranged in an upstream region of the main flow passage and a plurality of upper flow blade rows arranged in the upstream region of the main flow passage.
  • the upstream cascade having a plurality of parallel blades arranged at intervals in the circumferential direction around the axis
  • the downstream cascade having a plurality of three-dimensional blades arranged at intervals in the circumferential direction
  • the stator cascade having a plurality of stator blades arranged at intervals in the circumferential direction
  • the outer peripheral surface of the rotor shaft facing outward in the radial direction is formed in a cross section parallel to the axis in the region in which the three-dimensional blades are arranged in the downstream region, so that the diameter gradually increases parallel to the axis or radially outward toward the second side in the axial direction relative to the axis.
  • the steam turbine disclosed herein can improve efficiency while mixing parallel blades (impulse blades) and three-dimensional blades (reaction blades).
  • FIG. 1 is a schematic diagram showing an overall configuration of a steam turbine according to an embodiment of the present invention.
  • FIG. 2 is a cross-sectional view showing a row of rotor blades and a row of stator blades of the steam turbine.
  • FIG. 4 is a diagram showing a change in throat width in a stator blade row located on the second most side in the axial direction of the steam turbine.
  • 2 is a cross-sectional view showing a configuration around a diffuser provided in the steam turbine.
  • the steam turbine 1 of this embodiment has a rotor 20 that rotates about an axis Ar, a casing 10 that rotatably covers the rotor 20 , and a plurality of stator blade rows 41 .
  • the direction in which the axis Ar extends is referred to as the axial direction Da.
  • the first side of the axial direction Da is referred to as the upstream side (one side) Dau
  • the second side of the axial direction Da is referred to as the downstream side (the other side) Dad.
  • the radial direction of the rotor 20 based on the axis Ar is referred to simply as the radial direction Dr.
  • the side of this radial direction Dr that approaches the axis Ar is referred to as the inner side Dri of the radial direction Dr
  • the side of this radial direction Dr opposite the inner side Dri of the radial direction Dr is referred to as the outer side Dro of the radial direction Dr.
  • the circumferential direction of the rotor 20 centered on the axis Ar is referred to simply as the circumferential direction Dc.
  • the rotor 20 has a rotor shaft 21 and a number of rotor blade rows 31.
  • the rotor shaft 21 rotates about the axis Ar relative to the casing 10.
  • the rotor shaft 21 has a core portion 22 and multiple disk portions 23.
  • the core portion 22 is formed in a cylindrical shape centered on the axis Ar and extends in the axial direction Da.
  • the disk portions 23 extend from the core portion 22 to the outside Dro in the radial direction Dr.
  • the disk portions 23 are arranged at intervals from each other in the axial direction Da.
  • the disk portions 23 are arranged for each of the multiple rotor blade rows 31.
  • the rotor blade row 31 is fixed to the outside of the rotor shaft 21 in the radial direction Dr. Specifically, as shown in FIG. 2, the rotor blade row 31 is fixed to the outside Dro of the disk portion 23, which is the outer peripheral portion of the rotor shaft 21 in the radial direction Dr.
  • a plurality of rotor blade rows 31 are arranged at intervals in the axial direction Da of the rotor shaft 21. In the case of this embodiment, a total of seven rotor blade rows 31 are arranged, for example, from the rotor blade row 31A located at the most upstream side Dau in the axial direction Da to the rotor blade row 31G located at the most downstream side Dad in the axial direction Da.
  • Each rotor blade row 31 has a plurality of rotor blades 32 arranged in the circumferential direction Dc.
  • the plurality of rotor blades 32 are each attached to the disk portion 23.
  • Each rotor blade 32 has a platform 32a, a blade body 32b, and a shroud 32c.
  • the platform 32a is disposed on the outer side Dro of the disk portion 23 in the radial direction Dr.
  • the platform 32a extends in the circumferential direction Dc.
  • the platforms 32a of the multiple rotor blades 32 are aligned in the circumferential direction Dc to form a cylindrical shape centered on the axis Ar as a whole.
  • the blade body 32b extends from the platform 32a to the outside Dro in the radial direction Dr.
  • the blade body 32b is formed integrally with the platform 32a and the shroud 32c.
  • the blade body 32b is disposed in the main flow passage 15, which will be described later.
  • the blade body 32b has an airfoil-shaped cross section when viewed from the outside in the radial direction Dr.
  • the shroud 32c is connected to the end of the blade body 32b on the outer side Dro in the radial direction Dr. In other words, in the radial direction Dr, the shroud 32c is disposed on the opposite side of the blade body 32b from the platform 32a.
  • the shroud 32c extends in the circumferential direction Dc.
  • the shrouds 32c of the multiple rotor blades 32 are aligned in the circumferential direction Dc to form a cylindrical shape overall.
  • the casing 10 is formed to cover the rotor shaft 21 and the multiple moving blade rows 31 from the outside Dro in the radial direction Dr. Inside the casing 10, there are formed a nozzle chamber 11 into which steam S flows from the outside, a flow passage chamber 12 through which the steam S flows from the nozzle chamber 11, and an exhaust chamber 13 through which the steam S flowing from the flow passage chamber 12 is exhausted. Between the nozzle chamber 11 and the flow passage chamber 12, the moving blade row 31A and the stator blade row 41A of the first stage 50A on the most upstream side Dau are arranged among the multiple moving blade rows 31 and the stator blade row 41.
  • the inside of the casing 10 is divided into the nozzle chamber 11 and the flow passage chamber 12 by the moving blade row 31A and the stator blade row 41A on the most upstream side Dau.
  • the nozzle chamber 11, the flow passage chamber 12, and the exhaust chamber 13 form a main flow passage 15 through which high-pressure steam S flows.
  • the first stage 50A to the fourth stage 50D arranged on the upstream side Dau in the axial direction Da form the high-pressure stage 50x.
  • the fifth stage 50E to the seventh stage 50G (the three stages from the most downstream stage) arranged on the downstream side Dad in the axial direction Da relative to the high-pressure stage 50x form the low-pressure stage 50y.
  • the region in the main flow passage 15 where the high-pressure stage 50x is located is referred to as the upstream region P1.
  • the region located downstream Dad in the axial direction Da from the upstream region P1 where the low-pressure stage 50y is located is referred to as the downstream region P2.
  • the outer peripheral surface 21f of the rotor shaft 21 is the surface to which the rotor blades 32 and the stator blades 42 are connected.
  • the outer peripheral surface 21f of the rotor shaft 21 is the outer peripheral surface of the disk portion 23 that contacts the inner peripheral surface of the platform 32a, and the outer peripheral surface of the inner ring 46.
  • the lower flow cascade 31L unlike the upper flow cascade 31U, has a three-dimensional blade 37 as the blade main body 32b.
  • the three-dimensional blade 37 is formed so that the length in the radial direction Dr is longer than that of the parallel blade 35.
  • the three-dimensional blade 37 is curved three-dimensionally so that the blade surface (pressure surface) facing one side of the circumferential direction Dc and the blade surface (suction surface) facing the other side of the circumferential direction Dc are twisted as they progress in the blade height direction (radial direction Dr).
  • the blade cross section of the three-dimensional blade 37 is not constant in the blade height direction, and the shape and cross-sectional area change.
  • the three-dimensional blade 37 of the lower flow cascade 31L is a reaction blade with a reaction degree R of, for example, 45% to 60%.
  • the throat width at the three-dimensional blade tip portion 37s is formed to be smaller than the throat width at the three-dimensional blade base portion 37b and the throat width at the three-dimensional blade middle portion 37c in the radial direction Dr of the three-dimensional blade 37.
  • the three-dimensional blade middle portion 37c is the region of the three-dimensional blade 37 sandwiched between the three-dimensional blade tip portion 37s and the three-dimensional blade base portion 37b in the radial direction Dr. More specifically, the three-dimensional blade middle portion 37c is a region of about 40% of the blade length Hb, including the central portion.
  • the throat width is the width of the flow passage at the position where the flow passage cross-sectional area is smallest among the flow passages formed between a pair of blade bodies (blade main body 32b and stator blade 42) in the circumferential direction Dc.
  • the number of stages of the upper flow blade row 31U having the parallel blades 35 is increased, it is possible to suppress the occurrence of a large step on the rotor shaft 21 in the region where the upper flow blade row 31U having the parallel blades 35 switches to the lower flow blade row 31L having the three-dimensional blades 37.
  • the number of stages of the upper flow blade row 31U can be increased while suppressing the structural impact on the rotor 20 and the casing 10. This allows for a mixture of parallel blades 35 and three-dimensional blades 37 while improving efficiency.
  • the throat width of the stator vane 42 is larger at the stator vane intermediate portion 42c than at the stator vane tip portion 42s and the stator vane base portion 42b.
  • the throat width becomes smaller from the stator vane intermediate portion 42c toward the stator vane tip portion 42s. Therefore, the radial flow, which is a flow in which the steam S spreads to the outside Dro in the radial direction Dr, is suppressed.
  • the throat width of the stator vane 42 becomes smaller from the stator vane intermediate portion 42c toward the stator vane base portion 42b. Therefore, the degree of reaction can be reduced, and the leakage flow of steam into the gap between the stator vane tip portion 42s and the outer circumferential surface 21f of the rotor can be suppressed.
  • the upstream flow wing row 31U has a plurality of parallel blades 35 arranged at intervals in the circumferential direction Dc around the axis Ar
  • the downstream flow wing row 31L has a plurality of three-dimensional blades 37 arranged at intervals in the circumferential direction Dc
  • the stator blade row 41 has a plurality of stator blades 42 arranged at intervals in the circumferential direction Dc
  • the outer peripheral surface 21f of the rotor shaft 21 facing the outside Dro in the radial direction Dr is formed in the area where the three-dimensional blades 37 are arranged in the downstream region P2, in a cross section parallel to the axis Ar, or toward the second side Dad in the axial direction Da relative to the axis Ar, so as to gradually expand in diameter toward the outside Dro in the radial direction Dr.
  • Such a steam turbine 1 includes an upper flow cascade 31U having parallel blades 35 and a lower flow cascade 31L having three-dimensional blades 37. Furthermore, in this embodiment, the outer peripheral surface 21f of the rotor shaft 21 is formed in a cross section parallel to the axis Ar, parallel to the axis Ar, or so as to gradually expand in diameter from the upstream side Dau in the axial direction Da to the downstream side Dad in the axial direction Da relative to the axis Ar. In other words, the outer peripheral surface 21f of the rotor shaft 21 is formed in the region where the three-dimensional blades 37 are arranged in the downstream region P2 so as not to shrink inward Dri in the radial direction Dr from the upstream side Dau in the axial direction Da to the downstream side Dad.
  • the steam turbine 1 according to the third aspect is the steam turbine 1 of (2), in which the downward flow blade row 31L located on the second most side Dad in the axial direction Da is configured so that the clearance in the radial direction Dr between the three-dimensional blade tip portion 37s and the casing 10 is 1.5 to 2.5% of the blade length in the radial direction Dr of the three-dimensional blade 37.
  • the guide member 71 guides the steam S flowing through the diffuser 70 over a long distance in the axial direction Da.
  • separation of the flow of the steam S can be suppressed on the outer side Dro in the radial direction Dr. Therefore, in the diffuser 70, separation of the steam S can be suppressed while reducing the flow velocity. Therefore, even when the flow velocity (average flow velocity) of the steam S flowing out from the rotor blade row 31G of the final stage is transonic, the occurrence of separation can be suppressed. Therefore, it is possible to efficiently recover the static pressure of the steam S in the diffuser 70.
  • the steam turbine 1 according to the seventh aspect is any one of the steam turbines 1 according to (1) to (6), in which the parallel blades 35 are impulse blades and the three-dimensional blades 37 are reaction blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
PCT/JP2023/044271 2022-12-27 2023-12-11 蒸気タービン Ceased WO2024142889A1 (ja)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN202380088594.3A CN120418523A (zh) 2022-12-27 2023-12-11 蒸汽轮机
DE112023004470.8T DE112023004470T5 (de) 2022-12-27 2023-12-11 Dampfturbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2022209756A JP2024093395A (ja) 2022-12-27 2022-12-27 蒸気タービン
JP2022-209756 2022-12-27

Publications (1)

Publication Number Publication Date
WO2024142889A1 true WO2024142889A1 (ja) 2024-07-04

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ID=91717580

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PCT/JP2023/044271 Ceased WO2024142889A1 (ja) 2022-12-27 2023-12-11 蒸気タービン

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JP (1) JP2024093395A (https=)
CN (1) CN120418523A (https=)
DE (1) DE112023004470T5 (https=)
WO (1) WO2024142889A1 (https=)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07208107A (ja) * 1994-01-14 1995-08-08 Mitsubishi Heavy Ind Ltd 反動型蒸気タービン
JPH08109803A (ja) * 1994-10-13 1996-04-30 Toshiba Corp タービンノズル、タービン動翼及びタービン段落
US20100303604A1 (en) * 2009-05-27 2010-12-02 Dresser-Rand Company System and method to reduce acoustic signature using profiled stage design
WO2016135832A1 (ja) * 2015-02-23 2016-09-01 三菱重工コンプレッサ株式会社 蒸気タービン
JP2020090952A (ja) * 2018-12-07 2020-06-11 三菱重工コンプレッサ株式会社 蒸気タービン翼及び蒸気タービン
JP2022048602A (ja) * 2020-09-15 2022-03-28 三菱重工コンプレッサ株式会社 蒸気タービン

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07208107A (ja) * 1994-01-14 1995-08-08 Mitsubishi Heavy Ind Ltd 反動型蒸気タービン
JPH08109803A (ja) * 1994-10-13 1996-04-30 Toshiba Corp タービンノズル、タービン動翼及びタービン段落
US20100303604A1 (en) * 2009-05-27 2010-12-02 Dresser-Rand Company System and method to reduce acoustic signature using profiled stage design
WO2016135832A1 (ja) * 2015-02-23 2016-09-01 三菱重工コンプレッサ株式会社 蒸気タービン
JP2020090952A (ja) * 2018-12-07 2020-06-11 三菱重工コンプレッサ株式会社 蒸気タービン翼及び蒸気タービン
JP2022048602A (ja) * 2020-09-15 2022-03-28 三菱重工コンプレッサ株式会社 蒸気タービン

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Publication number Publication date
CN120418523A (zh) 2025-08-01
JP2024093395A (ja) 2024-07-09
DE112023004470T5 (de) 2025-08-07

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