EP2230385A1 - Turbinenrotorschaufel - Google Patents

Turbinenrotorschaufel Download PDF

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Publication number
EP2230385A1
EP2230385A1 EP09701788A EP09701788A EP2230385A1 EP 2230385 A1 EP2230385 A1 EP 2230385A1 EP 09701788 A EP09701788 A EP 09701788A EP 09701788 A EP09701788 A EP 09701788A EP 2230385 A1 EP2230385 A1 EP 2230385A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine rotor
turbine
root
platform
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.)
Withdrawn
Application number
EP09701788A
Other languages
English (en)
French (fr)
Other versions
EP2230385A4 (de
Inventor
Naoto Tochitani
Shohei Danno
Shoki Yamashita
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 Ltd
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
Publication of EP2230385A1 publication Critical patent/EP2230385A1/de
Publication of EP2230385A4 publication Critical patent/EP2230385A4/de
Withdrawn legal-status Critical Current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
    • 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, and the like.
  • Patent Citation 1 Japanese Unexamined Patent Application, Publication No. 2006-283681
  • the present invention has been conceived in light of the circumstances described above, and an object thereof is to provide a turbine rotor blade with which the blade root of the final (last) turbine rotor blade can be slotted into the blade groove on the turbine disc easily and rapidly even if the plan-view shape of the shroud of the turbine rotor blade is complex.
  • a turbine rotor blade according to one aspect of the present invention is a turbine rotor blade provided with a blade root that is slotted into a blade groove formed on a circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, and a shroud that extends along the circumferential direction from an end of the blade portion; the turbine rotor blade has a cut-out portion that is cut out to a predetermined depth, either at the leading edge or the trailing edge of the blade root, along the lengthwise direction thereof, from the end of the blade root to an intermediate part of the shank.
  • the turbine rotor blade can be set between a normal blade and a normal blade that have been slotted into the blade grooves on the turbine disc to a predetermined depth (for example, 5 mm) merely by moving the end surface that is formed by the cut-out portion and that extends in the lengthwise direction in a plane that includes the end surfaces forming the circumferential portion of the turbine disc (in other words, moving radially inward from radially outward), when the blade root is slotted into the blade groove formed on the circumferential portion of the turbine disc to be assembled.
  • a predetermined depth for example, 5 mm
  • the blade root of the turbine rotor blade and the blade roots of the normal blades can be slotted (are capable of being slotted) into the blade grooves on the turbine disc easily and rapidly.
  • the turbine rotor according to one aspect of the present invention is provided with the turbine rotor blade with which, when the blade root is slotted into the blade groove formed on the circumferential portion of the turbine disc to be assembled, the end surface that is formed by the cut-out portion and that extends in the lengthwise direction can be moved in the plane that includes the end surfaces forming the circumferential portion of the turbine disc (in other words, moved radially inward from radially outward); therefore, simplification of the procedure for assembling the turbine rotor blade and the normal blades on the turbine disc can be achieved, a reduction in the time required for assembly can be achieved, and a reduction in production costs can be achieved.
  • a method for constructing the turbine rotor according to the above-mentioned aspect is a method for constructing a turbine rotor by slotting at least one turbine rotor blade provided with a blade root that is slotted into a blade groove formed on a circumferential portion of a turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade portion, a shank that connects the blade root and the platform, a shroud that extends along the circumferential direction from the end of the blade portion, and a cut-out portion that is cut out to a predetermined depth, either at the leading edge or the trailing edge of the blade root, along the lengthwise direction thereof from the end of the blade root to an intermediate part of the shank; and a plurality of normal blades provided with a blade root that is slotted into a blade groove formed on the circumferential portion of the turbine disc to hold the whole blade, a blade portion that is exposed to high-temperature gas, a platform that supports this blade
  • the turbine rotor blade can be set between the normal blade and the normal blade that have been slotted into the blade grooves on the turbine disc to a predetermined depth (for example, 5 mm) merely by moving the end surface that is formed by the cut-out portion and that extends in the lengthwise direction in the plane that includes the end surfaces forming the circumferential portion of the turbine disc (in other words, moving radially inward from radially outward), when the blade root is slotted into the blade groove formed on the circumferential portion of the turbine disc to be assembled.
  • a predetermined depth for example, 5 mm
  • the turbine rotor blade according to the one aspect of the present invention at least as the final (last) blade to be slotted into the turbine disc, the blade root of the turbine rotor blade and the blade roots of the normal blades can be slotted (are capable of being slotted) into the blade grooves on the turbine disc easily and rapidly. Accordingly, simplification of the procedure for assembling the turbine rotor blade and the normal blades on the turbine disc can be achieved, a reduction in the time required for assembly can be achieved, and a reduction in production costs can be achieved.
  • the turbine rotor blade according to the present invention affords an advantage in that it is possible to easily and rapidly slot the blade root of the final (last) turbine rotor blade into the blade groove on the turbine disc, even if the plan-view shape of the shroud of the turbine rotor blade is complex.
  • FIG. 1A is a side view showing the turbine rotor blade according to this embodiment
  • FIG. 1B is a plan view showing the turbine rotor blade according to this embodiment
  • FIG. 2 is a perspective view of the turbine rotor blade according to this embodiment viewed from the front side.
  • the turbine rotor blade 1 is applied to a gas turbine provided with, for example, a compression unit (not shown) that compresses combustion air, a combustion unit (not shown) that combusts fuel by injecting the fuel into the high-pressure air sent from this compression unit, generating high-temperature combustion gas, and a turbine unit (not shown) that is located downstream of this combustion unit and is driven by the combustion gas discharged from the combustion unit.
  • a compression unit not shown
  • a combustion unit that combusts fuel by injecting the fuel into the high-pressure air sent from this compression unit, generating high-temperature combustion gas
  • a turbine unit not shown
  • the turbine rotor blade 1 is provided with a Christmas tree-shaped blade root (bottom) 3 that is slotted into a blade groove 2a (see FIGS. 5 and 6 ) formed on the circumferential portion of a turbine disc 2 (see FIGS.
  • the turbine rotor blade 1 has, either at the leading edge or the trailing edge of the blade root 3, a cut-out portion 8 that is cut out uniformly (to a predetermined depth (for example, 5 mm)) along the lengthwise direction (vertical direction in FIGS. 1A and 2 ) of the turbine rotor blade 1 from the end (lower end) of the blade root 3 to an intermediate part of the shank 6.
  • An end surface 8a that is formed by this cut-out portion 8 and extends in the lengthwise direction (vertical direction in FIGS.
  • the cut-out portion 8 of the turbine rotor blade 1 is formed so that, in a state where the blade root 13 of a turbine blade 11 without the cut-out portion 8 (hereinafter referred to as "normal blade"), such as those shown in FIGS. 3A, 3B , and 4 , is slotted into the blade groove 2a on the turbine disc 2 to a predetermined depth (for example, 5 mm), as shown in FIG. 5 , the turbine rotor blade 1 can be set between a normal blade 11 and a normal blade 11 by moving the end surface 8a that is formed by the cut-out portion 8 and that extends in the lengthwise direction in a plane that includes the end surfaces 2b forming the circumferential portion of the turbine disc 2. Then, as shown in FIG.
  • FIGS. 3A, 3B , and 4 reference signs 4, 5, 6, and 7 are a blade portion, a platform, a shank, and a shroud, respectively, and because descriptions thereof have been described using FIGS. 1A, 1B , and 2 , the descriptions thereof will be omitted here.
  • the reference sign 20 in FIGS. 5 and 6 indicates a turbine rotor that is provided with at least one turbine rotor blade 1, a plurality of normal blades 11, and the turbine disc 2.
  • the thus-configured turbine rotor blade 1 can be set between the normal blade 11 and the normal blade 11 that have been slotted into the blade grooves 2a on the turbine disc 2 to a predetermined depth (for example, 5 mm) merely by moving the end surface 8a that is formed by the cut-out portion 8 and that extends in the lengthwise direction in the plane that includes the end surfaces 2b forming the circumferential portion of the turbine disc 2 (in other words, moving radially inward from radially outward), when the blade root 3 is slotted into the blade groove 2a formed on the circumferential portion of the turbine disc 2 to be assembled.
  • a predetermined depth for example, 5 mm
  • the turbine rotor 20 is provided with the turbine rotor blade 1 with which, when the blade roots 3 and 13 are slotted into the blade grooves 2a formed on the circumferential portion of the turbine disc 2 to be assembled, the end surface 8a that is formed by the cut-out portion 8 of the turbine rotor blade 1 and extends in the lengthwise direction can be moved in the plane that includes the end surfaces 2b forming the circumferential portion of the turbine disc 2 (in other words, moved radially inward from radially outward); therefore, simplification of the procedure for assembling the turbine rotor blade 1 and the normal blades 11 on the turbine disc 2 can be achieved, a reduction in the time required for assembly can be achieved, and a reduction in production costs can be achieved.
  • the present invention is not only applicable to a gas turbine, but may also be applied to a steam turbine or a fluid rotary machine having other similar configurations.
  • the present invention is not limited to the embodiments described above; various modifications and alterations are permissible as required, so long as they do not depart 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)
EP09701788A 2008-01-16 2009-01-08 Turbinenrotorschaufel Withdrawn EP2230385A4 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2008006895 2008-01-16
PCT/JP2009/050160 WO2009090908A1 (ja) 2008-01-16 2009-01-08 タービン動翼

Publications (2)

Publication Number Publication Date
EP2230385A1 true EP2230385A1 (de) 2010-09-22
EP2230385A4 EP2230385A4 (de) 2011-03-16

Family

ID=40885299

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09701788A Withdrawn EP2230385A4 (de) 2008-01-16 2009-01-08 Turbinenrotorschaufel

Country Status (7)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2551460A1 (de) * 2011-07-29 2013-01-30 Siemens Aktiengesellschaft Schaufelverband

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US10704400B2 (en) * 2018-10-17 2020-07-07 Pratt & Whitney Canada Corp. Rotor assembly with rotor disc lip
KR20230081267A (ko) * 2021-11-30 2023-06-07 두산에너빌리티 주식회사 터빈 블레이드, 이를 포함하는 터빈 및 가스터빈

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1720729A (en) * 1928-03-29 1929-07-16 Westinghouse Electric & Mfg Co Blade fastening
EP0745756A1 (de) * 1995-06-02 1996-12-04 ABB Management AG Vorrichtung und Verfahren zur Montage von Laufschaufeln
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
US20060177314A1 (en) * 2004-09-16 2006-08-10 Yutaka Yamashita Turbine rotor blade and turbine
JP2006283681A (ja) * 2005-04-01 2006-10-19 Hitachi Ltd 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

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US3748060A (en) * 1971-09-14 1973-07-24 Westinghouse Electric Corp Sideplate for turbine blade
JPS5578103A (en) * 1978-12-08 1980-06-12 Hitachi Ltd Method of implanting movable turbine blade
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
US5509784A (en) * 1994-07-27 1996-04-23 General Electric Co. Turbine bucket and wheel assembly with integral bucket shroud
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
JP3805485B2 (ja) * 1997-07-11 2006-08-02 本田技研工業株式会社 タービンブレード組付け装置
US6061886A (en) * 1997-07-11 2000-05-16 Honda Giken Kogyo Kabushiki Kaisha Turbine blade fitting apparatus and fitting method
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

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1720729A (en) * 1928-03-29 1929-07-16 Westinghouse Electric & Mfg Co Blade fastening
EP0745756A1 (de) * 1995-06-02 1996-12-04 ABB Management AG Vorrichtung und Verfahren zur Montage von Laufschaufeln
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
US20060177314A1 (en) * 2004-09-16 2006-08-10 Yutaka Yamashita Turbine rotor blade and turbine
JP2006283681A (ja) * 2005-04-01 2006-10-19 Hitachi Ltd 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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2009090908A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2551460A1 (de) * 2011-07-29 2013-01-30 Siemens Aktiengesellschaft Schaufelverband

Also Published As

Publication number Publication date
CN101743380B (zh) 2014-01-01
EP2230385A4 (de) 2011-03-16
CN101743380A (zh) 2010-06-16
JPWO2009090908A1 (ja) 2011-05-26
JP4939613B2 (ja) 2012-05-30
ZA201001031B (en) 2011-08-31
RU2010104753A (ru) 2012-02-27
US20110217175A1 (en) 2011-09-08
WO2009090908A1 (ja) 2009-07-23

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