WO2009090908A1 - Pale de rotor de turbine - Google Patents

Pale de rotor de turbine Download PDF

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Publication number
WO2009090908A1
WO2009090908A1 PCT/JP2009/050160 JP2009050160W WO2009090908A1 WO 2009090908 A1 WO2009090908 A1 WO 2009090908A1 JP 2009050160 W JP2009050160 W JP 2009050160W WO 2009090908 A1 WO2009090908 A1 WO 2009090908A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
turbine
root
platform
turbine rotor
Prior art date
Application number
PCT/JP2009/050160
Other languages
English (en)
Japanese (ja)
Inventor
Naoto Tochitani
Shohei Danno
Shoki Yamashita
Original Assignee
Mitsubishi Heavy Industries, Ltd.
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, Ltd. filed Critical Mitsubishi Heavy Industries, Ltd.
Priority to EP09701788A priority Critical patent/EP2230385A4/fr
Priority to JP2009550004A priority patent/JP4939613B2/ja
Priority to US12/673,494 priority patent/US20110217175A1/en
Priority to CN200980000565.7A priority patent/CN101743380B/zh
Publication of WO2009090908A1 publication Critical patent/WO2009090908A1/fr
Priority to ZA2010/01031A priority patent/ZA201001031B/en

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the present invention relates to a turbine rotor blade applied to a gas turbine, a steam turbine or the like.
  • a platform As a turbine rotor blade applied to a gas turbine, a steam turbine, etc., a blade root embedded in a blade groove formed in a peripheral portion of a turbine disk to hold the entire blade, a blade portion exposed to high temperature gas, A platform is known that includes a platform that supports the wing, a shank that connects the blade root and the platform, and a shroud extending in the circumferential direction from the tip of the wing (see, for example, Patent Document 1). . JP 2006-283681 A
  • the present invention has been made in view of the above circumstances, and even if the shape of the shroud of the turbine blade is complicated in plan view, the blade root of the turbine blade is used as the blade root of the final (last) turbine blade.
  • An object of the present invention is to provide a turbine rotor blade that can be embedded easily and quickly.
  • a turbine rotor blade includes a blade root that is embedded in a blade groove formed in a peripheral portion of a turbine disk to hold the entire blade, a blade portion that is exposed to high-temperature gas, and a blade portion that includes the blade root.
  • a turbine rotor blade comprising a supporting platform, a shank connecting the blade root and the platform, and a shroud extending from the tip of the blade portion along the circumferential direction, on the leading edge side or the trailing edge side of the blade root, Along the length direction, there is a notch cut out at a predetermined depth from the tip of the blade root to the middle of the shank.
  • the end surface extending in the length direction formed by the notch portion is A predetermined depth (e.g., 5 mm) with respect to the blade groove of the turbine disk is simply moved in a plane including the end surface forming the peripheral edge of the disk (i.e., moved from the radially outer side to the radially inner side). ) Can be set between the regular wing and the regular wing embedded.
  • At least the final (last) blade to be embedded in the turbine disk is the turbine according to the above aspect.
  • the blade roots of these turbine blades and the blade roots of the regular blades can be easily and quickly embedded (embedded) in the blade grooves of the turbine disk.
  • the end surface extending in the length direction formed by the notch portion is set to Turbine blades that can be moved in a plane including the end faces forming the part (that is, moved radially outward to radially inward), so that the turbine blades and the regular blades are attached to the turbine disk.
  • the assembly work process can be simplified, the work time required for the assembly work can be shortened, and the manufacturing cost can be reduced.
  • the method of manufacturing a turbine rotor according to the above aspect includes a blade root that is embedded in a blade groove formed in a peripheral portion of a turbine disk to hold the entire blade, a blade portion that is exposed to high-temperature gas, and supports the blade portion.
  • At least one turbine blade provided with a notch cut out at a predetermined depth from the tip of the root to the middle of the shank, and the entire blade embedded in a blade groove formed at the peripheral edge of the turbine disk
  • a blade root that holds the blade, a blade that is exposed to high-temperature gas, a platform that supports the blade, a shank that connects the blade root and the platform, and a shura that extends from the tip of the blade along the circumferential direction.
  • the turbine blades and the normal blades are connected to the turbine rotor.
  • the turbine blades and the blade roots of the normal blades are embedded in the blade grooves of the turbine disk by moving in the axial direction.
  • the end surface extending in the length direction formed by the notch portion is used as the turbine disk.
  • a predetermined depth (for example, 5 mm) with respect to the blade groove of the turbine disk is simply moved in a plane including an end surface forming the peripheral edge of the turbine disk (that is, moved from the radially outer side toward the radially inner side). It can be set between a regular wing and a regular wing embedded.
  • At least the final (last) blade to be embedded in the turbine disk is one aspect of the present invention.
  • the turbine blade according to the above the blade roots of these turbine blades and the blade roots of the regular blades can be easily and quickly embedded (embedded) in the blade grooves of the turbine disk.
  • the blade root of the final (final) turbine blade can be easily formed in the blade groove of the turbine disk, and The effect is that it can be embedded quickly.
  • FIG. 1A is a side view showing a turbine blade according to this embodiment
  • FIG. 1B is a plan view showing the turbine blade according to this embodiment
  • FIG. 2 is a perspective view of the turbine rotor blade according to the present embodiment as viewed from the front side.
  • the turbine rotor blade 1 includes, for example, a compression unit (not shown) that compresses combustion air, and injects and burns fuel into high-pressure air sent from the compression unit to perform high-temperature combustion.
  • the present invention is applied to a gas turbine including a combustion section (not shown) that generates gas and a turbine section (not shown) that is located on the downstream side of the combustion section and is driven by the combustion gas exiting the combustion section. Is.
  • the turbine rotor blade 1 is embedded in a blade groove 2a (see FIGS. 5 and 6) formed in a peripheral portion of a turbine disk 2 (see FIGS. 5 and 6).
  • a Christmas tree-type blade root (base) 3 that holds (supports) the entire turbine rotor blade 1, a blade portion 4 that is exposed to high-temperature gas, a platform 5 that supports the blade portion 4, and a blade root 3 and the shanks 6 that connect the platform 5 and the tip (tip) of the blade 4 extend along the circumferential direction to prevent resonance of the turbine rotor blade 1 and leak loss (gas leakage) at the tip of the blade 4. ) Is provided.
  • the turbine rotor blade 1 As shown in FIGS. 1A and 2, the turbine rotor blade 1 according to the present embodiment is arranged on the front edge side or the rear edge side of the blade root 3 in the longitudinal direction of the turbine rotor blade 1 (up and down in FIGS. 1A and 2).
  • the cutout 8 is cut out uniformly (with a predetermined depth (for example, 5 mm)) from the tip (lower end) of the blade root 3 to the middle of the shank 6 along the direction.
  • An end face 8a formed by the notch 8 and extending in the length direction (vertical direction in FIGS. 1A and 2) is formed at the peripheral edge of the turbine disk 2 when the turbine rotor blade 1 is assembled to the turbine disk 2. It is formed so as to be substantially parallel to the end face 2 b and extends partway through the shank 6.
  • the notch 8 of the turbine rotor blade 1 is a blade root 13 of a turbine blade (hereinafter referred to as “regular blade”) 11 that does not have the notch 8 as shown in FIGS. 3A, 3B and 4. 5, the end face 8a extending in the length direction formed by the notch 8 is embedded in the blade groove 2a of the turbine disk 2 up to a predetermined depth (for example, 5 mm).
  • the turbine rotor blade 1 is formed so as to be set between the normal blade 11 and the normal blade 11 while being moved in a plane including the end surface 2 b forming the peripheral edge of the turbine disk 2.
  • FIG. 5 and FIG. 6 indicate a turbine rotor including at least one turbine blade 1, a plurality of regular blades 11, and a turbine disk 2.
  • the turbine rotor blade 1 configured as described above has an end face 8a extending in the length direction formed by the notch 8 when the blade root 3 is embedded in the blade groove 2a formed in the peripheral edge of the turbine disk 2 and assembled. Is moved in a plane including the end face 2b that forms the peripheral edge of the turbine disk 2 (that is, moved from the radially outer side toward the radially inner side), with respect to the blade groove 2a of the turbine disk 2. Can be set between the regular blade 11 and the regular blade 11 embedded to a depth of 5 mm (for example, 5 mm).
  • the shroud 7 of the turbine rotor blade 1 and the regular blade 11 has a complicated plan view shape (regardless of the plan view shape), at least the blades embedded in the turbine disk 2 at the end (final) are used in this embodiment. Therefore, the blade root 3 of the turbine blade 1 and the blade root 13 of the regular blade 11 can be easily and quickly embedded (embedded) in the blade groove 2a of the turbine disk 2. Can do.
  • the blade roots 3 and 13 are formed by the notches 8 of the turbine rotor blade 1 when the blade roots 3 and 13 are embedded and assembled in the blade groove 2a formed at the peripheral edge of the turbine disk 2.
  • a turbine blade 1 capable of moving an end face 8a extending in a length direction in a plane including an end face 2b that forms a peripheral edge of the turbine disk 2 (that is, moving from a radially outer side toward a radially inner side). Therefore, the work process for assembling the turbine blade 1 and the regular blade 11 to the turbine disk 2 can be simplified, and the work time required for the assembling work can be shortened. Can be reduced.
  • the present invention can be applied not only to a gas turbine but also to a steam turbine and other fluid rotary machines having a similar configuration.
  • the present invention is not limited to the above-described embodiment, and can be appropriately modified and changed as necessary without departing from the technical idea of the present invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Même si la forme d'un anneau de renforcement d'une pale de rotor de turbine en vue en plan est complexe, une emplanture de la (dernière) pale finale de rotor de turbine peut être enfoncée facilement et rapidement à l'intérieur d'une rainure de pale d'un disque de turbine. Une pale de rotor de turbine (1) comprenant une emplanture de pale (3) qui est enfoncée dans une rainure de pale formée sur le bord périphérique d'un disque de turbine et maintient toute la pale, une partie de pale (4) qui est exposée à un gaz à haute température, une plateforme (5) qui porte la partie de pale (4), une tige (6) couplant l'emplanture (3) et la plateforme (5), et un anneau de renforcement (7) s'étendant le long d'une direction circonférentielle, depuis l'extrémité de la partie de pale (4) comporte une partie découpée (8) coupée jusqu'à une profondeur prédéterminée de l'extrémité de l'emplanture (3) jusqu'au centre de la tige (6) sur le côté de bord avant ou le côté de bord arrière de l'emplanture de pale (3) le long de la direction longitudinale de celle-ci.
PCT/JP2009/050160 2008-01-16 2009-01-08 Pale de rotor de turbine WO2009090908A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP09701788A EP2230385A4 (fr) 2008-01-16 2009-01-08 Pale de rotor de turbine
JP2009550004A JP4939613B2 (ja) 2008-01-16 2009-01-08 タービン動翼
US12/673,494 US20110217175A1 (en) 2008-01-16 2009-01-08 Turbine rotor blade
CN200980000565.7A CN101743380B (zh) 2008-01-16 2009-01-08 涡轮动叶
ZA2010/01031A ZA201001031B (en) 2008-01-16 2010-02-11 Turbine rotor blade

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2008006895 2008-01-16
JP2008-006895 2008-01-16

Publications (1)

Publication Number Publication Date
WO2009090908A1 true WO2009090908A1 (fr) 2009-07-23

Family

ID=40885299

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2009/050160 WO2009090908A1 (fr) 2008-01-16 2009-01-08 Pale de rotor de turbine

Country Status (7)

Country Link
US (1) US20110217175A1 (fr)
EP (1) EP2230385A4 (fr)
JP (1) JP4939613B2 (fr)
CN (1) CN101743380B (fr)
RU (1) RU2010104753A (fr)
WO (1) WO2009090908A1 (fr)
ZA (1) ZA201001031B (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111058899A (zh) * 2018-10-17 2020-04-24 普拉特 - 惠特尼加拿大公司 具有转子盘唇缘的转子组件

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2551460A1 (fr) * 2011-07-29 2013-01-30 Siemens Aktiengesellschaft Groupe d'aubes
US10309232B2 (en) * 2012-02-29 2019-06-04 United Technologies Corporation Gas turbine engine with stage dependent material selection for blades and disk
US10648354B2 (en) * 2016-12-02 2020-05-12 Honeywell International Inc. Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing
KR20230081267A (ko) * 2021-11-30 2023-06-07 두산에너빌리티 주식회사 터빈 블레이드, 이를 포함하는 터빈 및 가스터빈
FR3143676A1 (fr) * 2022-12-16 2024-06-21 Safran Aircraft Engines système PROPULSIF AERONAUTIQUE
FR3143683A1 (fr) * 2022-12-16 2024-06-21 Safran Aircraft Engines Systeme propulsif aeronautique

Citations (3)

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Publication number Priority date Publication date Assignee Title
JPS4837530A (fr) * 1971-09-14 1973-06-02
JPS5578103A (en) * 1978-12-08 1980-06-12 Hitachi Ltd Method of implanting movable turbine blade
JPH1136806A (ja) * 1997-07-11 1999-02-09 Honda Motor Co Ltd タービンブレード組付け装置

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US2974924A (en) * 1956-12-05 1961-03-14 Gen Electric Turbine bucket retaining means and sealing assembly
US3501249A (en) * 1968-06-24 1970-03-17 Westinghouse Electric Corp Side plates for turbine blades
US4533298A (en) * 1982-12-02 1985-08-06 Westinghouse Electric Corp. Turbine blade with integral shroud
DE3528640A1 (de) * 1985-06-28 1987-01-08 Bbc Brown Boveri & Cie Schaufelschloss fuer reiterfusschaufeln von turbomaschinen
US4702673A (en) * 1985-10-18 1987-10-27 General Electric Company Method for assembly of tangential entry dovetailed bucket assemblies on a turbomachine bucket wheel
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JP3682131B2 (ja) * 1996-09-26 2005-08-10 株式会社東芝 タービン動翼及びその組立方法
US6061886A (en) * 1997-07-11 2000-05-16 Honda Giken Kogyo Kabushiki Kaisha Turbine blade fitting apparatus and fitting method
US6030178A (en) * 1998-09-14 2000-02-29 General Electric Co. Axial entry dovetail segment for securing a closure bucket to a turbine wheel and methods of installation
US7353588B2 (en) * 2003-06-20 2008-04-08 General Electric Company Installation tool for assembling a rotor blade of a gas turbine engine fan assembly
JP4335771B2 (ja) * 2004-09-16 2009-09-30 株式会社日立製作所 タービン動翼及びタービン設備
JP4869616B2 (ja) * 2005-04-01 2012-02-08 株式会社日立製作所 蒸気タービン動翼と蒸気タービンロータ及びそれを用いた蒸気タービン並びにその発電プラント

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS4837530A (fr) * 1971-09-14 1973-06-02
JPS5578103A (en) * 1978-12-08 1980-06-12 Hitachi Ltd Method of implanting movable turbine blade
JPH1136806A (ja) * 1997-07-11 1999-02-09 Honda Motor Co Ltd タービンブレード組付け装置

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111058899A (zh) * 2018-10-17 2020-04-24 普拉特 - 惠特尼加拿大公司 具有转子盘唇缘的转子组件

Also Published As

Publication number Publication date
ZA201001031B (en) 2011-08-31
RU2010104753A (ru) 2012-02-27
EP2230385A1 (fr) 2010-09-22
EP2230385A4 (fr) 2011-03-16
JPWO2009090908A1 (ja) 2011-05-26
CN101743380B (zh) 2014-01-01
US20110217175A1 (en) 2011-09-08
JP4939613B2 (ja) 2012-05-30
CN101743380A (zh) 2010-06-16

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