EP2151545A2 - Aube de turbine et structure de fixation correspondante - Google Patents

Aube de turbine et structure de fixation correspondante Download PDF

Info

Publication number: EP2151545A2
Authority: EP; European Patent Office
Prior art keywords: blade; turbine rotor; base portion; leading edge; blade base
Prior art date: 2008-08-07
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.): Granted

Application number

EP09167300A

Other languages

German (de)

English (en)

Other versions

EP2151545A3 (fr

EP2151545B1 (fr

Inventor

Yasushi Hayasaka

Hajime Toriya

Katsuhiro Murakami

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 Power Ltd

Original Assignee

Hitachi 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.)

2008-08-07

Filing date

2009-08-05

Publication date

2010-02-10

2009-08-05 Application filed by Hitachi Ltd filed Critical Hitachi Ltd

2010-02-10 Publication of EP2151545A2 publication Critical patent/EP2151545A2/fr

2012-12-19 Publication of EP2151545A3 publication Critical patent/EP2151545A3/fr

2017-06-07 Application granted granted Critical

2017-06-07 Publication of EP2151545B1 publication Critical patent/EP2151545B1/fr

Status Not-in-force legal-status Critical Current

2029-08-05 Anticipated expiration legal-status Critical

Images

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
- F01D5/12—Blades
- F01D5/14—Form or construction
- 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
- F01D5/3053—Fixing blades to rotors; Blade roots ; Blade spacers by means of pins
- 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
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- 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
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/312—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being parallel to each other
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

the present invention relates to a turbine rotor blade for a turbine such as a steam turbine or a gas turbine.
the present invention also relates to a fixation structure of such a turbine rotor blade.
a blade base portion (blade implant portion) of a turbine rotor blade for a steam turbine, gas turbine, or the like is variously shaped.
the turbine rotor blade is engaged with a blade groove to be mounted on a turbine rotor, the blade groove being complementarily shaped relative to the blade base portion.
An object of the present invention is to provide a turbine rotor blade that is highly manufacturable and capable of reducing the stress caused by centrifugal force.
a turbine rotor blade comprising: a vane portion having a blade leading edge positioned upstream in the distribution direction of working fluid and a blade trailing edge positioned downstream of the blade leading edge; and/or a blade base portion which is extended unidirectionally on a base side of the vane portion and engaged with a blade groove formed in the outer circumference of a turbine rotor; wherein an end of the blade base portion at the side of the blade leading edge is positioned to be different in the circumferential direction of the turbine rotor from an end of the blade base portion at the side of the blade trailing edge.
the present invention enables the blade groove to efficiently support the centrifugal load on the turbine rotor blade through the blade base portion, thereby making it possible to reduce the stress on the blade groove with ease.
FIG. 1 is a front view taken in an axial direction of a turbine rotor to illustrate a turbine rotor blade according to an embodiment of the present invention.
FIG. 2 is a perspective view of the turbine rotor blade.
a radial direction of a turbine rotor, a circumferential direction of a turbine rotor, and an axial direction of a turbine rotor are defined as indicated in these figures.
Turbine rotor blades 40a and 40b shown in FIGS. 1 and 2 are used with a steam turbine.
the turbine rotor blades 40a and 40b each include: a vane portion 3; a shroud 1 which is provided on the leading end of the vane portion 3 (the outer end portion in the radial direction of the turbine rotor); a seal (fin seal) 1a which is provided on the outer circumference of the shroud 1; blade base portion 5 (5a, 5b, and 5c, 5d) which engages with blade groove 6 (6a, 6b, and 6c, 6d) provided on the outer circumference of a turbine rotor 8; and a platform 4 which is provided between the vane portion 3 and the blade base portion 5.
the blade base portion 5 is extended unidirectionally on a base side of the vane portion 3 (on the inner end of the vane portion 3 in the radial direction of the turbine rotor), and inserted into the blade groove 6 along the extension direction of the blade base portion 5.
the extension direction of the blade base portion 5 will now be described with reference to FIG. 3 .
FIG. 3 is a view taken in the direction of arrow B in FIG. 1 .
Like elements in FIGS. 1 to 3 are designated by the same reference numerals and will not be redundantly described (the same is also true for the subsequent drawings).
the vane portion 3 includes a blade leading edge 21 which is positioned upstream in the distribution direction of working fluid, and a blade trailing edge 22 which is positioned downstream of the blade leading edge 21.
the turbine rotor 8 rotates downward in FIG. 3 .
an end (leading edge side end) 51a (51b) of the blade base portion 5a (5b) at the side of the blade leading edge 21 is positioned to be different in the circumferential direction of the turbine rotor from an end (trailing edge side end) 52a (52b) of the blade base portion 5a (5b) at the side of the blade trailing edge 22.
the blade base portions 5a and 5b are not extended in parallel with the rotation axis of the turbine rotor 8 (the axial direction C of the turbine rotor), but extended in a direction that is inclined at an angle of D (see FIG. 3 ) from the axial direction C of the turbine rotor.
the blade grooves 6a and 6b are provided in the outer circumference of the turbine rotor 8 and arranged in a direction (an axial direction of a groove) that is inclined at an angle of D from the axial direction of the turbine rotor, as is the case with the blade base portions 5a and 5b.
a direction an axial direction of a groove
the blade base portion 5 and blade groove 6 are positioned as described above, they are longer than those when they are positioned in parallel with the axial direction C of the turbine rotor. Therefore, the contact area between the blade base portion 5 and blade groove 6 can be increased.
the vane portion 3 is configured so that the position of the blade trailing edge 22 in the circumferential direction of the turbine rotor is displaced in the rotational direction of the turbine rotor with respect to that of the blade leading edge 21 in the circumferential direction of the turbine rotor, and the degree of reaction of the vane portion 3 is several tens of percent.
the blade base portion 5 should preferably be configured in accordance with the shape of the vane portion 3 so that the position of the trailing edge side end portion 52 (52a, 52b) in the circumferential direction of the turbine rotor is displaced in the rotational direction of the turbine rotor (downward in FIG.
the blade base portion 5 is configured as described above, the overlap between the vane portion 3 and the blade base portion 5 can be increased. This makes it possible to effectively support the vane portion 3 even when centrifugal force is applied to a turbine rotor blade 40a, 40b during an operation. It is also preferred that the blade base portion 5 be provided along the direction G of the blade chord length, that is, the direction of a line joining the blade leading edge 21 to the blade trailing edge 22, as shown in FIG. 3 .
the blade base portion 5 should preferably be configured so that the angle D formed between the blade base portion 5 and the axial direction C of the turbine rotor is equal to the angle formed between the direction G of the blade chord length and the axial direction C of the turbine rotor. The reason is that such a configuration makes it possible to further increase the overlap and efficiently position the blade base portion 5 relative to the vane portion 3.
the turbine rotor blade 40a of this embodiment includes the two blade base portions 5a and 5b.
the two blade base portions 5a and 5b are dovetail-shaped type, and are molded integral with the vane portion 3, the platform 4, and the shroud 1.
the number of blade base portions 5 is larger than that of vane portions 3 for one turbine rotor blade 40a, 40b as described above, it is possible to reduce the stress that arises due to steam force acting on the turbine rotor blades 40a, 40b during a steam turbine operation.
the blade base portions 5a, 5b are projected inward in the radial direction of the turbine rotor from the platform 4.
the directions of their projections are parallel to each other.
the centerline 41a (41c) of the blade base portion 5a (5c) is parallel to the centerline 41b (41d) of the blade base portion 5b (5d).
a blade hook portion 7 is projected toward each side in the circumferential direction of the turbine rotor from the leading ends of the blade base portion 5.
the blade hook portion 7 is engaged with a groove hook portion 13 which is projected in the circumferential direction of the turbine rotor from the blade groove 6.
Such an engagement structure fastens the turbine rotor blades 40a and 40b to the turbine rotor 8.
a contact area between the blade hook portion 7 and groove hook portion 13 is provided with a pinhole 9a which is extended in the axial direction of the turbine rotor through the blade hook portion 7 and groove hook portion 13.
a fixing pin 9b is inserted in the axial direction of the turbine rotor into the pinhole 9a.
the fixing pin 9b is inserted into the pinhole 9a after the blade base portion 5 is implanted in the blade groove 6 to accurately fasten the turbine rotor blades 40a and 40b in the circumferential direction of the turbine rotor and in the radial direction of the turbine rotor.
FIG. 4 is a view that is taken in the same direction as in FIG. 3 to present a comparative example of the turbine rotor blade according to the present embodiment.
the turbine rotor blade 90 shown in FIG. 4 includes blade base portions 91a and 91b which are extended in the same direction as the axial direction C of the turbine rotor. Further, the turbine rotor has blade grooves 92a and 92b which are provided in the same direction as the blade base portions 91a and 91b.
the lengths of the blade base portions 91a and 91b are decreased to reduce the area that supports the load on the turbine rotor blade 90. Therefore, when the turbine rotor blade 90 described above is used, increased stress is imposed on the blade base portions 91a, 91b and blade grooves 92a, 92b.
the employed turbine rotor blade 90 includes a vane portion 93 having a high degree of reaction
its platform 94 may not stay quadrilateral, as shown in FIG. 4 , while providing adequate clearance to an adjacent turbine rotor blade. Therefore, the blade base portion 91b has to terminate at a point (91e) before the end of the platform 94 on the side of the blade trailing edge 22. As a result, the blade base portion 91b is shorter than the platform 94. Decreasing the length of the blade base portion 91b in this manner not only increases the stress imposed on the blade base portion 91b but also produces a gap 92e in the blade groove 92b. This further increases the imposed stress.
the turbine rotor blade according to the present embodiment includes the blade base portion 5 which is formed so that the position of the leading edge side end portion 51 is different from that of the trailing edge side end portion 52 in the circumferential direction.
the blade base portion 5 is formed as described above, the portion can be made longer than when it is formed in parallel with the axial direction C of the turbine rotor. Therefore, the contact area between the blade groove 6 and blade base portion 5 can be increased. As this increases an area that supports the load on the turbine rotor blade portion 40, the stress imposed on the blade base portion 5 and blade groove 6 decreases, making it easy to enhance the structural reliability of the blade base portion 5 and blade groove 6.
the blade base portion 5 should preferably be configured in accordance with the shape of the vane portion 3 so that the position of the trailing edge side end portion 52 in the circumferential direction of the turbine rotor is displaced in the rotational direction of the turbine rotor with respect to that of the leading edge side end portion 51 in the circumferential direction of the turbine rotor.
Configuring the blade base portion 5 as described above makes it possible to increase the overlap between the vane portion 3 and blade base portion 5. Consequently, the centrifugal force applied to the turbine rotor blade portion 40 can be effectively shared by the blade base portion 5 and blade groove 6. As a result, the structural reliability of the blade base portion 5 and blade groove 6 can be further enhanced.
the blade base portion 5 should preferably be configured so that the angle D formed between the blade base portion 5 and the axial direction C of the turbine rotor is equal to the angle formed between the direction G of the blade chord length and the axial direction C of the turbine rotor.
Configuring the blade base portion 5 as described above makes it possible to not only further increase the overlap between the vane portion 3 and blade base portion 5, but also dispose the blade base portion 5 efficiently in relation to the vane portion 3. Consequently, the structural reliability can be further enhanced.
the present invention produces a striking effect particularly when the vane portion has a high degree of reaction (e.g., several tens of percent) and its blade chord length direction G is oblique to the axial direction of the turbine rotor.
the present embodiment has been described on the assumption that the blade base portion 5 is dovetail-shaped.
the present invention can be applied to a turbine rotor blade as far as an engagement structure is employed to couple the blade base portion to the blade groove.
a typical turbine rotor blade of this type includes blade base portion that is shaped like an inverted Christmas tree. More specifically, the width of this blade base portion increases outward in the radial direction of the turbine rotor with a plurality of convexes projected toward both sides in the width direction.
the inverted-Christmas-tree-shaped blade base portion is extended in the above-described direction, the area of contact with the blade groove can be unprecedentedly large as implied earlier. This makes it possible to reduce the stress resulting from centrifugal load.
the blade base portion 5 has the following features which contribute toward stress reduction. Such stress reduction features will be described below with reference to FIGS. 5A and 5B .
FIGS. 5A and 5B schematically illustrate the blade base portions of the turbine rotor blade according to the present embodiment and of a conventional turbine rotor blade.
FIG. 5A is a schematic diagram illustrating the blade base portion 5 according to the present embodiment and their vicinity.
FIG. 5B is a schematic diagram illustrating the blade base portion of a conventional turbine rotor blade and their vicinity.
the centerline 41a of the dovetail 5a is parallel to the centerline 41b of the dovetail 5b. Further, the distance E between the dovetail 5a and dovetail 5b is maintained constant.
the dovetails 50a and 50b of the conventional example are disposed so that their centerlines 42a and 42b respectively radiate from the center 43 of the turbine rotor 8. In other words, the distance between the dovetail 50a and dovetail 50b decreases with closing to the center 43, and equals F (F ⁇ E) at their leading ends.
the stress imposed on the dovetails and blade grooves in the area between the dovetails generally increases with a decrease in the distance between the dovetails.
the distance E between the dovetails can be longer than the conventional distance F. Therefore, the stress imposed on the dovetails 5a, 5b and blade groove 6 can be reduced. This makes it possible to further reduce the stress in addition to the stress reduction effect based on the direction in which the blade base portion 5 is extended.
the present invention has been described with reference to the turbine rotor blade having the vane portion 3 which is configured so that the positions of the blade leading edge 21 and blade trailing edge 22 in the circumferential direction are different from each other.
the stress resulting from centrifugal load can also be reduced even when the present invention is applied to a turbine rotor blade having a vane portion which is configured so that the positions of the blade leading edge and blade trailing edge in the circumferential direction are equal to each other.
the present invention has been described with reference to a case where the present invention is applied to a steam turbine, the present invention is also applicable to a gas turbine.

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

EP09167300.4A 2008-08-07 2009-08-05 Aube de turbine et structure de fixation correspondante Not-in-force EP2151545B1 (fr)

Applications Claiming Priority (1)

Application Number	Priority Date	Filing Date	Title
JP2008204234A JP5090287B2 (ja)	2008-08-07	2008-08-07	タービン動翼とその固定構造

Publications (3)

Publication Number	Publication Date
EP2151545A2 true EP2151545A2 (fr)	2010-02-10
EP2151545A3 EP2151545A3 (fr)	2012-12-19
EP2151545B1 EP2151545B1 (fr)	2017-06-07

Family

ID=41066619

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP09167300.4A Not-in-force EP2151545B1 (fr)	2008-08-07	2009-08-05	Aube de turbine et structure de fixation correspondante

Country Status (5)

Country	Link
US (1)	US20100111701A1 (fr)
EP (1)	EP2151545B1 (fr)
JP (1)	JP5090287B2 (fr)
KR (1)	KR101561305B1 (fr)
CA (1)	CA2674175C (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP3293362A4 (fr) *	2015-08-21	2018-06-20	Mitsubishi Heavy Industries Compressor Corporation	Turbine à vapeur

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US10145574B2 (en) *	2009-12-10	2018-12-04	Component Hardware Group, Inc.	Vent port for a refrigerated cabinet
JP5017392B2 (ja)	2010-02-24	2012-09-05	クラリオン株式会社	位置推定装置および位置推定方法
CN115229325B (zh) *	2022-09-08	2024-04-09	中车大连机车研究所有限公司	一种用于涡轮摩擦焊再制造的装置

Citations (1)

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JP2005195021A (ja)	2004-01-06	2005-07-21	General Electric Co <Ge>	高温蒸気タービン用の低重量コントロール段

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US5425622A (en) *	1993-12-23	1995-06-20	United Technologies Corporation	Turbine blade attachment means
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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
JP2007231868A (ja) *	2006-03-02	2007-09-13	Hitachi Ltd	蒸気タービン動翼およびそれを用いた蒸気タービン並びに蒸気タービン発電プラント
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2008
- 2008-08-07 JP JP2008204234A patent/JP5090287B2/ja not_active Expired - Fee Related
2009
- 2009-07-29 CA CA2674175A patent/CA2674175C/fr not_active Expired - Fee Related
- 2009-07-30 US US12/512,102 patent/US20100111701A1/en not_active Abandoned
- 2009-08-05 EP EP09167300.4A patent/EP2151545B1/fr not_active Not-in-force
- 2009-08-06 KR KR1020090072195A patent/KR101561305B1/ko not_active Expired - Fee Related

Patent Citations (1)

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Publication number	Priority date	Publication date	Assignee	Title
JP2005195021A (ja)	2004-01-06	2005-07-21	General Electric Co <Ge>	高温蒸気タービン用の低重量コントロール段

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
EP3293362A4 (fr) *	2015-08-21	2018-06-20	Mitsubishi Heavy Industries Compressor Corporation	Turbine à vapeur
US10550697B2 (en)	2015-08-21	2020-02-04	Mitsubishi Heavy Industries Compressor Corporation	Steam turbine

Also Published As

Publication number	Publication date
EP2151545A3 (fr)	2012-12-19
KR101561305B1 (ko)	2015-10-16
JP5090287B2 (ja)	2012-12-05
CA2674175C (fr)	2013-07-23
CA2674175A1 (fr)	2010-02-07
KR20100019348A (ko)	2010-02-18
JP2010038104A (ja)	2010-02-18
EP2151545B1 (fr)	2017-06-07
US20100111701A1 (en)	2010-05-06

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JP2007064221A (ja)	2007-03-15	静翼輪郭の最適化
JP2003522872A (ja)	2003-07-29	タービン翼配置構造
CN101776011B (zh)	2015-04-29	涡轮翼型件同步
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EP2151545B1 (fr)	2017-06-07	Aube de turbine et structure de fixation correspondante
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US20100061860A1 (en)	2010-03-11	Steam turbine rotating blade for a low pressure section of a steam turbine engine
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JP5916060B2 (ja)	2016-05-11	先端間隙制御システムで使用するタービンブレード先端シュラウド
JPH10184305A (ja)	1998-07-14	シュラウド動翼を有するタービン
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EP2863017A1 (fr)	2015-04-22	Turbine avec moyens de fixation de godet
US7367778B2 (en)	2008-05-06	Rotor end piece
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JP2021504628A (ja)	2021-02-15	ターボ機械のロータブレード及びロータブレードの製造方法
US8052393B2 (en)	2011-11-08	Steam turbine rotating blade for a low pressure section of a steam turbine engine

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