CN101743380B - Turbine rotor blade - Google Patents
Turbine rotor blade Download PDFInfo
- Publication number
- CN101743380B CN101743380B CN200980000565.7A CN200980000565A CN101743380B CN 101743380 B CN101743380 B CN 101743380B CN 200980000565 A CN200980000565 A CN 200980000565A CN 101743380 B CN101743380 B CN 101743380B
- Authority
- CN
- China
- Prior art keywords
- blade
- turbine rotor
- blade root
- leaf
- turbine
- 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.)
- Expired - Fee Related
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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
- F01D5/30—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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Even if the shape of a shroud of a turbine rotor blade in plan view is complicated, a blade root of the final (last) turbine rotor blade can be easily and quickly embedded into a blade groove of a turbine disc. A turbine rotor blade (1) comprising a blade root (3) which is embedded in a blade groove formed at the peripheral edge of a turbine disc and holds the entire blade, a blade portion (4) which is exposed to high-temperature gas, a platform (5) which supports the blade portion (4), a shank (6) which couples the blade root (3) and the platform (5), and a shroud (7) which extends along a circumferential direction from the end of the blade portion (4) includes a cutout portion (8) which is cut to a predetermined depth from the end of the blade root (3) to the midpoint of the shank (6) on the front edge side or rear edge side of the blade root (3) along the lengthwise direction thereof.
Description
Technical field
The present invention relates to a kind of turbine rotor blade that is applicable to gas turbine or steam turbine etc.
Background technique
As the turbine rotor blade that is applicable to gas turbine or steam turbine etc., the known blade root that has in the leaf groove of imbedding on the peripheral portion that is formed on the turbine disk and keep blade integral, the leaf section that is exposed to high-temperature gas, the platform that supports this leaf section, the petiole that links blade root and platform, the scheme (for example, with reference to patent documentation 1) from the front end of leaf section along the guard shield of circumferential extension.
Patent documentation 1: TOHKEMY 2006-283681 communique
But, in recent years, require further to reduce the leakage loss (gas leakage) of the front end of leaf section, improve turbine efficiency, and require further to reduce the vibration of the front end of leaf section, reduce the blade volume of leaf section.Therefore, complex-shapedization during the overlooking of guard shield, as in the past by the blade root of turbine rotor blade one by one in the method in the buried groove of the leaf to the turbine disk, exist when finally the blade root of the turbine rotor blade of (finally) is imbedded in the leaf groove of the turbine disk, the final guard shield of the turbine rotor blade of (finally), interfere with the guard shield of the turbine rotor blade that is positioned at adjacent both sides, exist and be difficult to the blade root of the turbine rotor blade of final (finally) is imbedded to the problem in the leaf groove of the turbine disk.
In addition, also exist when the length (blade height) of turbine rotor blade for example in the situation for 200mm following short (low) (in more detail, L (blade height)/D (chord length) be in the situation 1/3 or more), the final blade root of the turbine rotor blade of (finally) can not be imbedded to the problem in the leaf groove of the turbine disk.
Summary of the invention
The present invention researches and develops in view of the above problems, its purpose is to provide a kind of turbine rotor blade, even complex-shaped during the overlooking of the guard shield of turbine rotor blade, also can be easily and the blade root of turbine rotor blade that promptly will final (finally) be embedded in the leaf groove of the turbine disk.
The present invention, in order to address the above problem, adopt following structure and method.
The turbine rotor blade of a mode of the present invention, have: imbed in the leaf groove on the peripheral portion that is formed on the turbine disk and keep the blade root of blade integral, the leaf section that is exposed to high-temperature gas, the platform that supports this leaf section, the petiole that links blade root and platform, the guard shield from the front end of leaf section along circumferential extension, wherein, have in front edge side or the trailing edge side of described blade root and cut the cut midway to described petiole from the front end of described blade root with the degree of depth of regulation along its length.
Turbine rotor blade according to an embodiment of the present invention, in the time of in blade root being imbedded to the leaf groove be assembled on the peripheral portion that is formed at the turbine disk, only by the end face extended along its length that will be formed by cut, move (from the radial direction outside towards the radial direction medial movement) in the plane of the end face that forms peripheral portion that comprises the turbine disk, for example imbed, between the rule blade and rule blade of prescribed depth (5mm) and be arranged on respect to the leaf groove of the turbine disk.
Complex-shaped during the overlooking of the guard shield of turbine rotor blade and rule blade even (shape independently when overlooking), make at least final (finally) imbed the turbine rotor blade of the blade employing present embodiment of the turbine disk, the blade root of the blade root of these turbine rotor blades and rule blade easily and promptly can be imbedded in the leaf groove of (bury to) turbine disk.
The turbine rotor of one embodiment of the present invention, owing to having while being assembled on the leaf groove of blade root being imbedded on the peripheral portion that is formed on the turbine disk, the end face extended along its length that can be formed by cut moves the turbine rotor blade of (from the radial direction outside towards the radial direction medial movement) in the plane of the end face that forms peripheral portion that contains the turbine disk, so can realize turbine rotor blade and rule blade are assembled in the simplification of the flow chart in the turbine disk, and can realize the shortening of the activity duration that assembling operation is required, thereby can realize the reduction of manufacture cost.
The manufacture method of the turbine rotor of above-mentioned mode of execution, at least a slice turbine rotor blade and multi-disc rule blade are imbedded respectively in the turbine disk, thereby complete turbine rotor, described at least a slice turbine rotor blade: have in the leaf groove of imbedding on the peripheral portion that is formed on the turbine disk and the blade root that keeps blade integral, be exposed to the leaf section of high-temperature gas, support the platform of this leaf section, the petiole that links blade root and platform, guard shield from the front end of leaf section along circumferential extension, front edge side or trailing edge side described blade root are cut the cut midway to described petiole from the front end of described blade root with the degree of depth of regulation along its length, described rule blade has: imbed in the leaf groove on the peripheral portion that is formed on the turbine disk and the blade root that keeps blade integral, be exposed to the leaf section of high-temperature gas, support the platform of this leaf section, the petiole that links blade root and platform, guard shield from the front end of leaf section along circumferential extension, wherein, there is the stage as described below: by described turbine rotor blade from the radial direction outside towards the radial direction medial movement between rule blade, this rule blade refers to that its blade root imbeds the rule blade to prescribed depth with respect to the leaf groove of the described turbine disk, at described turbine rotor blade after between rule blade, described turbine rotor blade and rule blade are moved on the axial direction of described turbine rotor, the blade root of described turbine rotor blade and rule blade is imbedded in the leaf groove of the described turbine disk.
Manufacture method according to the turbine rotor of above-mentioned mode of execution, in the time of in blade root being imbedded to the leaf groove be assembled on the peripheral portion that is formed at the turbine disk, only by the end face extended along its length that will be formed by cut, move (from the radial direction outside towards the radial direction medial movement) in the plane of the end face that forms peripheral portion that comprises the turbine disk, for example imbed, between the rule blade and rule blade of prescribed depth (5mm) and be arranged on respect to the leaf groove of the turbine disk.
Complex-shaped during the overlooking of the guard shield of turbine rotor blade and rule blade even (shape independently when overlooking), make at least final (finally) imbed the turbine rotor blade of the blade employing present embodiment of the turbine disk, the blade root of the blade root of these turbine rotor blades and rule blade easily and promptly can be imbedded in the leaf groove of (bury to) turbine disk.
Thus, can realize turbine rotor blade and rule blade are assembled in to the simplification of the flow chart in the turbine disk, and can realize the shortening of the activity duration that assembling operation is required, can realize the reduction of manufacture cost.
According to turbine rotor blade of the present invention, though complex-shaped during the overlooking of guard shield that can play turbine rotor blade, also can be easily and the blade root of turbine rotor blade that promptly will final (finally) be embedded to the effect in the leaf groove of the turbine disk.
The accompanying drawing explanation
Figure 1A means the profile of the turbine rotor blade of one embodiment of the present invention.
Figure 1B means the plan view of the turbine rotor blade of one embodiment of the present invention.
Fig. 2 is the stereogram that the turbine rotor blade shown in Figure 1A and Figure 1B is observed from face side.
Fig. 3 A means does not have Figure 1A, the profile of the rule blade of the cut shown in Figure 1B and Fig. 2.
Fig. 3 B means does not have Figure 1A, the plan view of the rule blade of the cut shown in Figure 1B and Fig. 2.
Fig. 4 means the stereogram that the rule blade shown in Fig. 3 A and Fig. 3 B is observed from face side.
Fig. 5 is the stereogram to the assembling sequence of the turbine disk for explanation.
Fig. 6 is the stereogram to the assembling sequence of the turbine disk for explanation.
Description of reference numerals
1 turbine rotor blade
2 turbine disks
2a leaf groove
3 blade roots
4 leaf sections
5 platforms
6 petioles
7 guard shields
8 cut
11 rule blades
13 blade roots
20 turbine rotors
Embodiment
Below, with reference to Figure 1A, Figure 1B and Fig. 2, a mode of execution of turbine rotor blade of the present invention is described.
Figure 1A means the profile of the turbine rotor blade of one embodiment of the present invention, and Figure 1B means the plan view of the turbine rotor blade of one embodiment of the present invention, and Fig. 2 is the stereogram that the related turbine rotor blade of present embodiment is observed from face side.
The turbine rotor blade 1 of present embodiment for example is applicable to have the press part (not shown) of air for compression and combustion, to burner oil the high-pressure air of sending here from this press part and make its burning, produce high-temperature combustion gas burning section (not shown), be positioned at the downstream side of this burning section, by the gas turbine of the turbine portion (not shown) of the combustion gases drive flowed out from burning section.
As shown in Figure 1A, Figure 1B and Fig. 2, turbine rotor blade 1 have in the leaf groove 2a (with reference to Fig. 5 and Fig. 6) imbedded on the peripheral portion that is formed on the turbine disk 2 (with reference to Fig. 5 and Fig. 6) and keep (supporting) turbine rotor blade 1 integral body Xmas-tree blade root (foundation) 3, be exposed to leaf section 4 in high-temperature gas, support this leaf section 4 platform 5, link the petiole 6 of blade root 3 and platform 5, from the front end (tip) of leaf section 4 along circumferential extension, prevent the guard shield 7 of leakage loss (Leakage Gas) of the front end of the resonance of turbine rotor blade 1 reduction leaf section 4.
In addition, the turbine rotor blade 1 of present embodiment, as shown in Figure 1A and Fig. 2, there is in the front edge side of blade root 3 or trailing edge side the front end (lower end) along the length direction (being above-below direction in Figure 1A and Fig. 2) of turbine rotor blade 1 from blade root 3 to the cut 8 that similarly (for example, with the degree of depth (5mm) of regulation) cuts of petiole 6 midway.The end face 8a that (in Figure 1A and the Fig. 2 for above-below direction) along its length formed by this cut 8 extends when being assembled on the turbine disk 2 at turbine rotor blade 1 with the peripheral portion that is formed on the turbine disk 2 on the mode of end face 2b almost parallel form, extend to petiole 6 midway.
; the cut 8 of turbine rotor blade 1; can for example imbed, to the state of prescribed depth (5mm) by the leaf groove 2a with respect to the turbine disk 2 shown in Fig. 5 the blade root 13 of shown in Fig. 3 A, Fig. 3 B and Fig. 4, turbine blade that do not there is cut 8 (below be called " rule blade ") 11; move in the plane of the end face 2b that forms peripheral portion that will comprise the turbine disk 2 at the end face 8a extended along its length formed by cut 8, and turbine rotor blade 1 is arranged between rule blade 11 and rule blade 11 simultaneously and form.
And, after turbine rotor blade 1 being arranged between rule blade 11 and rule blade 11, as shown in Figure 6, make turbine blade 1 and rule blade 11 integral body along the moving axially of the turbine disk 2, blade root 3,13 integral body of turbine blade 1 and rule blade 11 are imbedded in the leaf groove 2a on the peripheral portion that is formed on the turbine disk 2.
In addition, the reference character 4,5,6,7 of Fig. 3 A, Fig. 3 B and Fig. 4 is respectively leaf section, platform, leaf section, guard shield, and it illustrates owing to using Figure 1A, Figure 1B and Fig. 2 to carry out explanation, so omit in this its explanation.
The reference character 20 of Fig. 5 and Fig. 6 means to have at least a slice turbine rotor blade 1, multi-disc rule blade 11 and the turbine disk 2 and the turbine rotor that forms.
In the turbine rotor blade 1 formed like this, in the time of in blade root 3 being imbedded to the leaf groove 2a be assembled on the peripheral portion that is formed at the turbine disk 2, can be only by the end face 8a extended along its length that will be formed by cut 8, move (from the radial direction outside towards the radial direction medial movement) in the plane of the end face 2b that forms peripheral portion that comprises the turbine disk 2, and the leaf groove 2a be arranged on respect to the turbine disk 2 for example imbeds, between the rule blade 11 and rule blade 11 of prescribed depth (5mm).
Complex-shaped during the overlooking of the guard shield 7 of turbine rotor blade 1 and rule blade 11 even (shape independently when overlooking), make at least final (finally) imbed the turbine rotor blade 1 of the blade employing present embodiment of the turbine disk 2, the blade root 13 of the blade root of these turbine rotor blades 13 and rule blade 11 easily and promptly can be imbedded in the leaf groove 2a of (bury to) turbine disk 2.
The present invention not only can be applicable to gas turbine, also can be applicable to steam turbine, other have the fluid rotary machine of same structure.
The present invention is not limited to above-mentioned mode of execution, and in the scope that does not break away from technical conceive of the present invention, suitable distortion is implemented, changed and implement as required.
Claims (3)
1. a turbine rotor blade, it has: imbed in the leaf groove on the peripheral portion that is formed on the turbine disk and keep the blade root of blade integral, the leaf section that is exposed to high-temperature gas, the platform that supports this leaf section, the petiole that links blade root and platform, the guard shield from the front end of leaf section along circumferential extension, it is characterized in that
Described turbine rotor blade has cut and by this cut (8) forms and front edge side from from described blade root (13) to described petiole (6) or trailing edge side are extended along its length the first end face (8a), this cut the front edge side of described blade root or the front end of trailing edge side along its length direction from described blade root with the degree of depth of regulation cut to described petiole midway
When described the first end face (8a) is assembled on the described turbine disk (2) according at described turbine rotor blade (11), imbedding described leaf groove (2a), with second end face (2b) of the formation peripheral portion of the described turbine disk (2), compares with the mode of this second end face almost parallel and cut formation.
2. a turbine rotor is characterized in that having:
A slice turbine rotor blade claimed in claim 1 at least;
The multi-disc rule blade, this rule blade has: imbed in the leaf groove on the peripheral portion that is formed on the turbine disk and keep the blade root of blade integral, the leaf section that is exposed to high-temperature gas, the platform that supports this leaf section, the petiole that links blade root and platform, the guard shield from the front end of leaf section along circumferential extension;
The described turbine disk.
3. the manufacture method of a turbine rotor,
At least a slice turbine rotor blade and multi-disc rule blade are imbedded respectively in the turbine disk, thereby complete turbine rotor,
Described at least a slice turbine rotor blade has: imbed in the leaf groove on the peripheral portion that is formed on the described turbine disk and the blade root that keeps blade integral, be exposed to the leaf section of high-temperature gas, support the platform of this leaf section, the petiole that links blade root and platform, guard shield from the front end of leaf section along circumferential extension, front edge side or the front end of trailing edge side along its length direction from described blade root described blade root cut the cut midway to described petiole with the degree of depth of regulation, by the first end face (8a) that this cut (8) forms and front edge side from from described blade root (13) to described petiole (6) or trailing edge side are extended along its length,
Described rule blade has: imbed in the leaf groove on the peripheral portion that is formed on the described turbine disk and keep the blade root of blade integral, the leaf section that is exposed to high-temperature gas, the platform that supports this leaf section, the petiole that links blade root and platform, the guard shield from the front end of leaf section along circumferential extension
The manufacture method of described turbine rotor is characterised in that,
There is the stage as described below: by described turbine rotor blade from the radial direction outside towards the radial direction medial movement between rule blade, this rule blade refers to that its blade root imbeds the rule blade to prescribed depth with respect to the leaf groove of the described turbine disk, after described turbine rotor blade is between rule blade, described turbine rotor blade and rule blade are moved on the axial direction of described turbine rotor, the blade root of described turbine rotor blade and rule blade is imbedded in the leaf groove of the described turbine disk
Described the first end face (8a) is compared the mode of cutting with this second end face almost parallel ground according to second end face (2b) of the formation peripheral portion with the described turbine disk (2) and is imbedded.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2008006895 | 2008-01-16 | ||
| JP006895/2008 | 2008-01-16 | ||
| PCT/JP2009/050160 WO2009090908A1 (en) | 2008-01-16 | 2009-01-08 | Turbine rotor blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101743380A CN101743380A (en) | 2010-06-16 |
| CN101743380B true CN101743380B (en) | 2014-01-01 |
Family
ID=40885299
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200980000565.7A Expired - Fee Related CN101743380B (en) | 2008-01-16 | 2009-01-08 | Turbine rotor blade |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US20110217175A1 (en) |
| EP (1) | EP2230385A4 (en) |
| JP (1) | JP4939613B2 (en) |
| CN (1) | CN101743380B (en) |
| RU (1) | RU2010104753A (en) |
| WO (1) | WO2009090908A1 (en) |
| ZA (1) | ZA201001031B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2551460A1 (en) * | 2011-07-29 | 2013-01-30 | Siemens Aktiengesellschaft | Blade group |
| 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 (en) * | 2021-11-30 | 2023-06-07 | 두산에너빌리티 주식회사 | Turbine blade, turbine and gas turbine including the same |
| FR3143683A1 (en) * | 2022-12-16 | 2024-06-21 | Safran Aircraft Engines | AERONAUTICAL PROPULSIVE SYSTEM |
| FR3143676A1 (en) * | 2022-12-16 | 2024-06-21 | Safran Aircraft Engines | AERONAUTICAL PROPULSIVE system |
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| US3748060A (en) * | 1971-09-14 | 1973-07-24 | Westinghouse Electric Corp | Sideplate for turbine blade |
| CN1144877A (en) * | 1995-06-02 | 1997-03-12 | Abb管理有限公司 | Working vane assembly method and equipment |
| 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 |
| US6061886A (en) * | 1997-07-11 | 2000-05-16 | Honda Giken Kogyo Kabushiki Kaisha | Turbine blade fitting apparatus and fitting method |
| CN1749535A (en) * | 2004-09-16 | 2006-03-22 | 株式会社日立制作所 | Turbine blade and turbine device |
| CN1840860A (en) * | 2005-04-01 | 2006-10-04 | 株式会社日立制作所 | Steam turbine blade, steam turbine rotor, steam turbine with those blades and rotors, and power plant with the turbines |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US1720729A (en) * | 1928-03-29 | 1929-07-16 | Westinghouse Electric & Mfg Co | Blade fastening |
| 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 |
| 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 (en) * | 1985-06-28 | 1987-01-08 | Bbc Brown Boveri & Cie | Blade lock for rim-straddling blades of turboengines |
| 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 (en) * | 1996-09-26 | 2005-08-10 | 株式会社東芝 | Turbine blade and its assembly method |
| JP3805485B2 (en) * | 1997-07-11 | 2006-08-02 | 本田技研工業株式会社 | Turbine blade assembly equipment |
| 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 |
-
2009
- 2009-01-08 EP EP09701788A patent/EP2230385A4/en not_active Withdrawn
- 2009-01-08 WO PCT/JP2009/050160 patent/WO2009090908A1/en active Application Filing
- 2009-01-08 US US12/673,494 patent/US20110217175A1/en not_active Abandoned
- 2009-01-08 JP JP2009550004A patent/JP4939613B2/en not_active Expired - Fee Related
- 2009-01-08 RU RU2010104753/06A patent/RU2010104753A/en not_active Application Discontinuation
- 2009-01-08 CN CN200980000565.7A patent/CN101743380B/en not_active Expired - Fee Related
-
2010
- 2010-02-11 ZA ZA2010/01031A patent/ZA201001031B/en unknown
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3748060A (en) * | 1971-09-14 | 1973-07-24 | Westinghouse Electric Corp | Sideplate for turbine blade |
| CN1144877A (en) * | 1995-06-02 | 1997-03-12 | Abb管理有限公司 | Working vane assembly method and equipment |
| 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 |
| CN1749535A (en) * | 2004-09-16 | 2006-03-22 | 株式会社日立制作所 | Turbine blade and turbine device |
| CN1840860A (en) * | 2005-04-01 | 2006-10-04 | 株式会社日立制作所 | Steam turbine blade, steam turbine rotor, steam turbine with those blades and rotors, and power plant with the turbines |
Non-Patent Citations (1)
| Title |
|---|
| JP昭55-78103A 1980.06.12 |
Also Published As
| Publication number | Publication date |
|---|---|
| RU2010104753A (en) | 2012-02-27 |
| WO2009090908A1 (en) | 2009-07-23 |
| EP2230385A1 (en) | 2010-09-22 |
| JPWO2009090908A1 (en) | 2011-05-26 |
| JP4939613B2 (en) | 2012-05-30 |
| CN101743380A (en) | 2010-06-16 |
| ZA201001031B (en) | 2011-08-31 |
| US20110217175A1 (en) | 2011-09-08 |
| EP2230385A4 (en) | 2011-03-16 |
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