WO2009090908A1 - タービン動翼 - Google Patents
タービン動翼 Download PDFInfo
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- 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
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- WIPO (PCT)
- Prior art keywords
- blade
- turbine
- root
- platform
- turbine rotor
- Prior art date
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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
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- 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.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
また、タービン動翼の長さ(翼高さ)が、例えば、200mm以下と短い(低い)場合(より詳しくは、L(翼高さ)/D(コード長)が1/3以上の場合)には、最終(最後)のタービン動翼の翼根をタービンディスクの翼溝に埋め込むことができないといった問題点もあった。
本発明の一態様に係るタービン動翼は、タービンディスクの周縁部に形成された翼溝に埋め込まれて翼全体を保持する翼根と、高温ガスに曝される翼部と、この翼部を支持するプラットホームと、翼根とプラットホームとを連結するシャンクと、翼部の先端から周方向に沿って延びるシュラウドとを備えたタービン動翼であって、前記翼根の前縁側または後縁側に、その長さ方向に沿って、前記翼根の先端から前記シャンクの途中まで所定の深さで切り欠かれた切欠部を有している。
すなわち、タービン動翼および正規翼のシュラウドの平面視形状が複雑なものであっても(シュラウドの平面視形状に関係なく)、少なくとも最終(最後)にタービンディスクに埋め込む翼を上記態様に係るタービン動翼とすることで、これらタービン動翼の翼根および正規翼の翼根をタービンディスクの翼溝に容易、かつ、迅速に埋め込む(埋め込んでいく)ことができる。
すなわち、タービン動翼および正規翼のシュラウドの平面視形状が複雑なものであっても(シュラウドの平面視形状に関係なく)、少なくとも最終(最後)にタービンディスクに埋め込む翼を本発明の一態様に係るタービン動翼とすることで、これらタービン動翼の翼根および正規翼の翼根をタービンディスクの翼溝に容易、かつ、迅速に埋め込む(埋め込んでいく)ことができる。
これにより、タービン動翼および正規翼をタービンディスクに組み付ける作業工程の簡略化を図ることができるとともに、組み付け作業に要する作業時間の短縮化を図ることができて、製造コストの低減化を図ることができる。
2 タービンディスク
2a 翼溝
3 翼根
4 翼部
5 プラットホーム
6 シャンク
7 シュラウド
8 切欠部
11 正規翼
13 翼根
20 タービンロータ
図1Aは本実施形態に係るタービン動翼を示す側面図であり、図1Bは本実施形態に係るタービン動翼を示す平面図である。図2は本実施形態に係るタービン動翼を正面側から見た斜視図である。
そして、タービン動翼1を正規翼11と正規翼11との間にセットしたら、図6に示すように、タービン翼1および正規翼11全体をタービンディスク2の軸方向に沿って移動させ、タービン翼1および正規翼11の翼根3,13全体が、タービンディスク2の周縁部に形成された翼溝2aに埋め込まれるようにする。
なお、図3A、図3Bおよび図4中の符号4,5,6,7はそれぞれ、翼部、プラットホーム、シャンク、シュラウドであり、その説明は図1A、図1Bおよび図2を用いて既に説明したので、ここではその説明を省略する。
図5および図6中の符号20は、少なくとも一枚のタービン動翼1と、複数枚の正規翼11と、タービンディスク2とを備えてなるタービンロータを示している。
すなわち、タービン動翼1および正規翼11のシュラウド7の平面視形状が複雑なものであっても(平面視形状に関係なく)、少なくとも最終(最後)にタービンディスク2に埋め込む翼を本実施形態に係るタービン動翼1とすることで、これらタービン動翼1の翼根3および正規翼11の翼根13をタービンディスク2の翼溝2aに容易、かつ、迅速に埋め込む(埋め込んでいく)ことができる。
本発明は上述した実施形態に限定されるものではなく、本発明の技術的思想を逸脱しない範囲で、適宜必要に応じて変形実施、変更実施することができる。
Claims (3)
- タービンディスクの周縁部に形成された翼溝に埋め込まれて翼全体を保持する翼根と、高温ガスに曝される翼部と、この翼部を支持するプラットホームと、翼根とプラットホームとを連結するシャンクと、翼部の先端から周方向に沿って延びるシュラウドとを備えたタービン動翼であって、
前記翼根の前縁側または後縁側に、その長さ方向に沿って、前記翼根の先端から前記シャンクの途中まで所定の深さで切り欠かれた切欠部を有しているタービン動翼。 - 少なくとも一枚の請求項1に記載のタービン動翼と、
タービンディスクの周縁部に形成された翼溝に埋め込まれて翼全体を保持する翼根と、高温ガスに曝される翼部と、この翼部を支持するプラットホームと、翼根とプラットホームとを連結するシャンクと、翼部の先端から周方向に沿って延びるシュラウドとを備えた複数枚の正規翼と、
前記タービンディスクとを備えているタービンロータ。 - タービンディスクの周縁部に形成された翼溝に埋め込まれて翼全体を保持する翼根と、高温ガスに曝される翼部と、この翼部を支持するプラットホームと、翼根とプラットホームとを連結するシャンクと、翼部の先端から周方向に沿って延びるシュラウドと、前記翼根の前縁側または後縁側に、その長さ方向に沿って、前記翼根の先端から前記シャンクの途中まで所定の深さで切り欠かれた切欠部とを備えた少なくとも一枚のタービン動翼と、
タービンディスクの周縁部に形成された翼溝に埋め込まれて翼全体を保持する翼根と、高温ガスに曝される翼部と、この翼部を支持するプラットホームと、翼根とプラットホームとを連結するシャンクと、翼部の先端から周方向に沿って延びるシュラウドとを備えた複数枚の正規翼とを、前記タービンディスクにそれぞれ埋め込んでタービンロータを完成させるタービンロータの製造方法であって、
前記タービンディスクの翼溝に対して、その翼根が所定の深さまで埋め込まれた正規翼間に、前記タービン動翼を半径方向外側から半径方向内側に向かって移動させて、正規翼間に位置させた後に、これらタービン動翼および正規翼を前記タービンロータの軸線方向に移動させて、これらタービン動翼および正規翼の翼根を、前記タービンディスクの翼溝に埋め込む段階を備えているタービンロータの製造方法。
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
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 |
EP09701788A EP2230385A4 (en) | 2008-01-16 | 2009-01-08 | ROTOR BLADE OF TURBINE |
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 |
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WO2009090908A1 true WO2009090908A1 (ja) | 2009-07-23 |
Family
ID=40885299
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2009/050160 WO2009090908A1 (ja) | 2008-01-16 | 2009-01-08 | タービン動翼 |
Country Status (7)
Country | Link |
---|---|
US (1) | US20110217175A1 (ja) |
EP (1) | EP2230385A4 (ja) |
JP (1) | JP4939613B2 (ja) |
CN (1) | CN101743380B (ja) |
RU (1) | RU2010104753A (ja) |
WO (1) | WO2009090908A1 (ja) |
ZA (1) | ZA201001031B (ja) |
Cited By (1)
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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 |
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EP2551460A1 (de) * | 2011-07-29 | 2013-01-30 | Siemens Aktiengesellschaft | Schaufelverband |
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 |
FR3143683A1 (fr) * | 2022-12-16 | 2024-06-21 | Safran Aircraft Engines | Systeme propulsif aeronautique |
FR3143676A1 (fr) * | 2022-12-16 | 2024-06-21 | Safran Aircraft Engines | système PROPULSIF AERONAUTIQUE |
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2009
- 2009-01-08 EP EP09701788A patent/EP2230385A4/en not_active Withdrawn
- 2009-01-08 WO PCT/JP2009/050160 patent/WO2009090908A1/ja active Application Filing
- 2009-01-08 US US12/673,494 patent/US20110217175A1/en not_active Abandoned
- 2009-01-08 JP JP2009550004A patent/JP4939613B2/ja not_active Expired - Fee Related
- 2009-01-08 RU RU2010104753/06A patent/RU2010104753A/ru not_active Application Discontinuation
- 2009-01-08 CN CN200980000565.7A patent/CN101743380B/zh not_active Expired - Fee Related
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2010
- 2010-02-11 ZA ZA2010/01031A patent/ZA201001031B/en unknown
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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)
Publication number | Priority date | Publication date | Assignee | Title |
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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 |
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RU2010104753A (ru) | 2012-02-27 |
EP2230385A1 (en) | 2010-09-22 |
JPWO2009090908A1 (ja) | 2011-05-26 |
JP4939613B2 (ja) | 2012-05-30 |
CN101743380B (zh) | 2014-01-01 |
CN101743380A (zh) | 2010-06-16 |
ZA201001031B (en) | 2011-08-31 |
US20110217175A1 (en) | 2011-09-08 |
EP2230385A4 (en) | 2011-03-16 |
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