JPS59226202A - Moving blade of turbine - Google Patents
Moving blade of turbineInfo
- Publication number
- JPS59226202A JPS59226202A JP9958883A JP9958883A JPS59226202A JP S59226202 A JPS59226202 A JP S59226202A JP 9958883 A JP9958883 A JP 9958883A JP 9958883 A JP9958883 A JP 9958883A JP S59226202 A JPS59226202 A JP S59226202A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- turbine
- steam
- wheel
- blade root
- 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.)
- Pending
Links
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
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/326—Locking of axial insertion type blades by other means
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【発明の詳細な説明】 ［発明の技術分野］ 本発明はタービン動翼に関する。[Detailed description of the invention] [Technical field of invention] The present invention relates to turbine rotor blades.
［発明の技術的背景コ
今１３、蒸気タービンの高効率化が省エネルギ一対策の
一環として広く要請され−Ｃいる。[Technical Background of the Invention] Nowadays, there is a widespread demand for higher efficiency of steam turbines as part of energy saving measures.
この要請に対応する方法として、第１に蒸気タービンを
人容最化する口とがあげられる。ざらに最近では原子力
用タービンをベースロード運用し、原子力用タービン以
外の大容缶事業用タービンにおいてもミドル火力運用さ
れる場合が多く、このようなタービンでは、部分負荷時
の高効率化の方法が必要とされている。The first method to meet this demand is to optimize the steam turbine for human capacity. In recent years, nuclear power turbines have been used for base load operation, and large-capacity commercial turbines other than nuclear power turbines have often been used for medium-fired power generation. is needed.
このような方法として、従来タービン発電（幾の負荷に
応じて、主蒸気圧力を下げる変圧運転の採用および調速
弁により部分噴射を行なう順次間ガバニング（ノズルガ
バニング）方式が採用されＣいる。As such a method, conventional turbine power generation (variable pressure operation that lowers the main steam pressure depending on the load) and a sequential governing (nozzle governing) system that performs partial injection using a speed regulating valve have been adopted.
そしてこのようなノズルガバニングを行なう人容母蒸気
タービンにおいては、特にバルブポイントにおいて部分
噴射のため初段羽根１枚あたりに過大な負荷がかかるこ
とになる。そのため、一般的に初段段落には羽根幅が大
きく、堅牢な翼素が使用されている。そしてこのような
翼素に対しては、通常ビンを介し゛Ｃ遠心力を支え、か
つ羽根有効部の遠心力が大きいため羽根植込部の遠心力
の軽減を図る意味でいわゆるアキシャルエントリー型の
植込部が採用されＣいる。In a human-carrier steam turbine that performs such nozzle governing, an excessive load is applied to each first-stage blade due to partial injection, particularly at the valve point. For this reason, the first stage generally uses strong blade elements with a wide blade width. For such blade elements, the so-called axial entry type is used to support the C centrifugal force through a bottle and to reduce the centrifugal force in the blade implanted part because the centrifugal force in the effective part of the blade is large. The implanted part is used.
第１図および第２図はこのようなアギシャルエントり一
定の植込部を備えたタービン動翼を示すもので、図にお
いて符号１はタービン羽根を示している。タービン羽根
１の外周にはシュラウド２、シスラウドカバー３おＪ：
びテノン４が順に配設されＣいる。ターどン羽根１の内
側にはソリッド部５が形成されてあり、このソリッド部
５の内側には一定間隔をおいて一対の羽根植込部６が形
成されている。この羽根植込部６はタービンホイール７
に形成されるホイール植込溝９に嵌合され、固定ピン１
０によりタービンホイール７に固定されている。FIGS. 1 and 2 show a turbine rotor blade having such an implanted portion having a constant agical entry, and in the figures, reference numeral 1 indicates a turbine blade. A shroud 2 and a shroud cover 3 are installed around the outer circumference of the turbine blade 1.
and tenon 4 are arranged in order. A solid portion 5 is formed inside the tardon blade 1, and a pair of blade embedded portions 6 are formed inside the solid portion 5 at a constant interval. This blade embedded part 6 is connected to the turbine wheel 7
The fixing pin 1 is fitted into the wheel installation groove 9 formed in the
0 to the turbine wheel 7.
すなわち、タービンホイール７には第３図に示すように
、羽根植込部６と同一形状に形成されたホイール植込溝
９が軸り向に治って形成されＣおり、羽根植込部６とタ
ービンホイール７とを跨いで軸方向に沿って形成された
貫通孔１１には、固定ピン１０が挿入されている。羽根
植込部６の蒸気流入側および流出側にはそれぞれスピル
ストリップインサート１２が配設され、これらのスピル
ストリップインサー１〜１２はタービンホイール７に形
成される凹溝１３に嵌合支持されている。また羽根植込
部６には、位置決め用のストッパ１４が形成されている
。That is, as shown in FIG. 3, the turbine wheel 7 is provided with a wheel installation groove 9 formed in the same shape as the blade installation part 6 and curved in the axial direction. A fixing pin 10 is inserted into a through hole 11 formed along the axial direction across the turbine wheel 7. Spill strip inserts 12 are provided on the steam inflow side and the steam outflow side of the blade implant 6, respectively, and these spill strip inserts 1 to 12 are fitted and supported in grooves 13 formed in the turbine wheel 7. . Further, a stopper 14 for positioning is formed in the blade implantation part 6.
以上のように構成されたタービン羽根ひは、タービン動
翼に作用する遠心力に対しでは、ターどン羽根１ば固定
ピン１０により支持され、また第２図に矢符Ａで示す蒸
気流によるスラスト力に対しては、タービン羽根１は羽
根植込部６の両側に配設されるスピルストリップインサ
ー１−１２により支持される。The turbine blades configured as described above are supported by the fixed pins 10 against the centrifugal force acting on the turbine rotor blades, and are supported by the steam flow shown by arrow A in FIG. For thrust forces, the turbine blade 1 is supported by spill strip inserters 1-12 arranged on both sides of the blade implant 6.
また、このようなタービン動翼では、スピルストリップ
インサート１２は高圧高温の蒸気から羽根植込部６ｉｕ
よびホイール植込溝９を保護する機能をも有している。In addition, in such a turbine rotor blade, the spill strip insert 12 protects the blade implant portion 6iu from high-pressure and high-temperature steam.
It also has the function of protecting the wheel installation groove 9.
「背景技術の問題点］
しかしながら、このように構成されたタービン動翼では
、羽根植込部６とスピルストリップインサート１２との
間に一般に軸方向に微少な間隙が存在し、スピルストリ
ップインサート１２はノズル出口からの蒸気噴射による
繰り返し荷重を羽根植込部６を介して受け、長期の使用
によりスピルストリップインサート１２が摩耗あるいは
破断するｄ−３それがある。"Problems with Background Art" However, in the turbine rotor blade configured in this way, there is generally a small gap in the axial direction between the blade embedded part 6 and the spill strip insert 12, and the spill strip insert 12 is There is a possibility that the spill strip insert 12 may wear out or break due to long-term use due to the repeated load applied by the steam injection from the nozzle outlet through the vane implant 6.
さらにこのようなタービン動翼では、スピルストリップ
インサート１２をタービンホイール７の一部を切欠いて
全周にわたり植込む必要があるため部品点数が非常に多
くなるという問題がある。Furthermore, in such a turbine rotor blade, it is necessary to cut out a part of the turbine wheel 7 and insert the spill strip insert 12 over the entire circumference, so there is a problem that the number of parts becomes extremely large.
特に１７１ｊ ；ホした蒸気タービンの高効率化の要求
に応え、主蒸気の蒸気条件を向上させた場合、Ｊ−なわ
ち人容伝超高圧高温タービンにおいては、超高圧化Ｊ５
よび大容量化による蒸気の励振力が一段と増加し、スピ
ルストリップインサート１２の植込みネック部に作用す
る振動応力が増大し、スピルストリップインサート１２
がこの植込みネック部にｉＪ”ｉいて破断するおそれが
生ず−る。In particular, when the steam conditions of the main steam are improved in response to the demand for higher efficiency of steam turbines, J-, that is, ultra-high pressure high-temperature turbines,
The excitation force of the steam increases further due to the increased capacity, and the vibration stress acting on the implantation neck of the spill strip insert 12 increases, causing the spill strip insert 12 to
There is a risk that the implant will break at the neck of the implant.
１−）で明の目的］
本発明はかかる従来の事情に対処してなされたちのＣ゛
、タービン羽根に作用するスラスト力を確実に支持づ゛
ることのできるタービン動翼を提供しようとするもので
ある。1-)] The present invention has been made in response to the above-mentioned conventional circumstances.It is an object of the present invention to provide a turbine rotor blade that can reliably support the thrust force acting on the turbine blade. It is something.
Ｕ発明の概要コ
すなわち本発明は、タービンホイールの外周に軸方向に
沿って凹溝を形成し、この凹溝にタービン羽根の羽根植
込部を嵌合してなるタービン動翼において、前記タービ
ンホイールの蒸気下流側に前記羽根植込部の蒸気下流側
への移動をトｌ止するホイール植込部ストッパを前記タ
ービンホイールと一体に形成し、前記羽根植込部の蒸気
上流側にこの羽根植込部の蒸気下流側への移動を阻止す
るストッパを形成したことを特徴とリーるタービン動翼
である。U Summary of the Invention In other words, the present invention provides a turbine rotor blade in which a groove is formed along the axial direction on the outer periphery of a turbine wheel, and a blade embedded part of a turbine blade is fitted into the groove. A wheel implant stopper is formed integrally with the turbine wheel to stop the movement of the blade implant toward the steam downstream side on the steam downstream side of the wheel, and the blade is installed on the steam upstream side of the blade implant. This turbine rotor blade is characterized in that a stopper is formed to prevent the implanted portion from moving downstream of the steam.
［発明の実施例］
以下本発明の詳細を図面に示Ｊ−実施例につぃＣ説明す
る。[Embodiments of the Invention] Details of the present invention will be described below with reference to embodiments shown in the drawings.
第４図は本発明の一実施例のタービン動翼を示すもので
、図にｄ３いて符号１５はタービン羽根を示しており、
このタービン羽根１５の外側にはシュラウ］く１６、シ
ュラウドカバー１７およびテノン１８が配設されている
。FIG. 4 shows a turbine rotor blade according to an embodiment of the present invention, and d3 in the figure and reference numeral 15 indicate a turbine blade.
A shroud 16, a shroud cover 17, and a tenon 18 are disposed outside the turbine blade 15.
タービン羽根１５の内側には、第５図に示すように、ソ
リッド部１９が配設され、このソリッド部１９の下面に
は軸方向に並行に一対の羽根植込部２Ｑが形成されでい
る。そして羽根植込部２０の蒸気流入側にはソリッド部
１９に垂直に羽根植込部棚部２１が形成されている。な
お羽根植込部２０の下面には位置決めストッパー２２が
形成されＣいる。As shown in FIG. 5, a solid portion 19 is disposed inside the turbine blade 15, and a pair of blade embedded portions 2Q are formed on the lower surface of the solid portion 19 in parallel in the axial direction. On the steam inflow side of the vane implantation section 20, a vane implantation section shelf section 21 is formed perpendicularly to the solid section 19. Note that a positioning stopper 22 is formed on the lower surface of the blade implantation part 20.
第６図は前述した羽根植込部２０を挿入支持するタービ
ンホイール２３の外周部を示すもので、図において符号
２４は羽根植込部２０８嵌合するホイール植込溝を示し
でいる。このホイール植込）６２４はタービンホイール
２３の外周に沿って軸方向に一定間隔をおいて形成され
ており、タービンホイール２３の蒸気下流側端にはター
ビンホイール２３の側面に沿ってホイール植込部ストッ
パ２５が形成されている。ターじンホイール２３の熱気
上流側には第５図に示した羽根植込部棚部２１を嵌合ず
−る段部２６が形成されている。そし−Ｃホイール植込
溝２４および羽根植込部２０に跨って固定ビン２７を挿
入する挿入孔２８がそれぞれ穿設されている。また、ホ
イール植込溝２４の底部の蒸気流入側には位置決めスト
ッパー２２を収容する溝２９が形成され−Ｃいる。FIG. 6 shows the outer periphery of the turbine wheel 23 into which the blade implant 20 described above is inserted and supported, and in the figure, reference numeral 24 indicates a wheel installation groove into which the blade implant 208 is fitted. The wheel implants 624 are formed along the outer circumference of the turbine wheel 23 at regular intervals in the axial direction, and a wheel implant portion 624 is formed along the side surface of the turbine wheel 23 at the steam downstream end of the turbine wheel 23. A stopper 25 is formed. A stepped portion 26 is formed on the hot air upstream side of the turbine wheel 23, into which the blade-embedded shelf portion 21 shown in FIG. 5 is fitted. Insertion holes 28 are formed across the C-wheel installation groove 24 and the blade installation section 20, respectively, into which the fixed pin 27 is inserted. Further, a groove 29 for accommodating the positioning stopper 22 is formed at the bottom of the wheel installation groove 24 on the steam inflow side.
以上のように構成されたタービン動翼では、羽根植込部
２０がタービンホイール２３のホイール植込溝２４上流
側からホイール植込部ス１−ツバ２５に当接するまで挿
入され、この後、羽根植込部２０およびホイール植込溝
２４を跨いで形成されるビン挿入孔２８に第７図に示す
ように、固定ビン２７がそれぞれ挿入され、この後、固
定ビン２７を羽根植込部棚部２１にかしめることにより
組立が行なわれる。In the turbine rotor blade configured as described above, the blade embedding portion 20 is inserted from the upstream side of the wheel embedding groove 24 of the turbine wheel 23 until it comes into contact with the wheel embedding portion slot 25, and then the blade As shown in FIG. 7, the fixed bins 27 are respectively inserted into the bottle insertion holes 28 formed across the implantation part 20 and the wheel implantation groove 24, and then the fixed bins 27 are inserted into the blade implantation part shelf. Assembly is performed by caulking at 21.
そして、以上のように構成されたタービン動翼では、タ
ービン羽根１５に作用する遠心力は従来と同様に固定ピ
ン２７により支持され、一方、タービン羽根１５に作用
するスラスト力はホイール植込部ストッパ２５および羽
根植込部棚部２１により支持される。従って高効率化の
ためにタービンを大容量化しかつ蒸気条件を超高圧化す
ることによる蒸気の励振力増に対しても振動応力上信頼
性の高いタービン動翼を捉供することができる。In the turbine rotor blade configured as described above, the centrifugal force acting on the turbine blade 15 is supported by the fixed pin 27 as in the conventional case, while the thrust force acting on the turbine blade 15 is supported by the wheel embedded part stopper. 25 and the blade implant shelf 21 . Therefore, it is possible to provide a turbine rotor blade that is highly reliable in terms of vibration stress even when the excitation force of steam is increased by increasing the capacity of the turbine and increasing the steam condition to an ultra-high pressure in order to improve efficiency.
また従来のようにスピルストリップインサート１２を使
用しないため、部品点数を大幅に削減することができる
。Further, since the spill strip insert 12 is not used as in the conventional case, the number of parts can be significantly reduced.
［発明の効果］
以上述へたように本発明のタービン動翼によれば、蒸気
流によりタービンホイールに生ずるスラスト力を従来の
スピルストリップイン′Ｉ＋ −１〜を使用することな
く確実に支持することができる。[Effects of the Invention] As described above, according to the turbine rotor blade of the present invention, the thrust force generated on the turbine wheel by the steam flow can be reliably supported without using the conventional spill strip in'I+ -1~. be able to.
第１図は従来のタービン動翼の側面図、第２図は第１図
のＩＩ −ＩＩ線に沿う縦ｌＮ７ｉ面図、第３図は第１
図にボすタービン動翼のホイール植込溝を示す外１ｉλ
図、第４図は本発明の一実施例のタービン動ψメを示す
縦断面図、第５図は第４図に示す羽根植込部近傍を示す
外観図、第６図は第４図に示すホイール植込溝近傍を示
す外観図、第７図は第４図の側面を矢符１３方向から見
た側面図である。
１５・・・・・・・・・・・・タービン羽根１９・・・
・・・・・・・・・ソリッド部２０・・・・・・川・・
・羽根植込βＢ２１・・・・・・・・・・・・羽根植込
部棚部２３・・・・ｔ・・・・・・・タービンホイール
２４・・・・・・・・・・・・ホイール植込溝２５・・
・・・・・・・・・・ホイール植込部ストッパ２７・・
・・・・・・・・・・固定ビン代理人弁理士 則
３Ｊｉ 憲 佑（ばか１名）
第１図
第２図
第３図
第４図Fig. 1 is a side view of a conventional turbine rotor blade, Fig. 2 is a vertical lN7i plane view taken along line II-II in Fig. 1, and Fig. 3 is a side view of a conventional turbine rotor blade.
The figure shows the wheel installation groove of the turbine rotor blade.
4 is a vertical sectional view showing the turbine mechanism of an embodiment of the present invention, FIG. 5 is an external view showing the vicinity of the blade implantation part shown in FIG. 4, and FIG. 6 is the same as FIG. 7 is a side view of the side surface of FIG. 4 viewed from the direction of arrow 13. FIG. 15... Turbine blade 19...
......Solid part 20...River...
・Blade implantation βB21...Blade implantation shelf section 23...t...Turbine wheel 24...・Wheel implant groove 25...
.......Wheel implant stopper 27...
・・・・・・・・・・Fixed Bin Agent Patent Attorney Rules
3Ji Kensuke (1 idiot) Figure 1 Figure 2 Figure 3 Figure 4
Claims (1)
形成し、この凹溝にタービン羽根の羽根植込部を嵌合し
てなるタービン動翼におい−Ｃ１前記タービンホイール
の蒸気下流側に前記羽根植込部の蒸気下流側への移動を
阻止するホイール植込部スＩ〜ツバを前記タービンホイ
ールと一体に形成し、前記羽根植込部の蒸気上流側にこ
の羽根植込部の蒸気下流側への移動を阻止するストッパ
を形成したことを特徴とするタービン切要。(1) A turbine rotor blade in which a groove is formed along the axial direction on the outer periphery of the turbine wheel, and the blade implantation part of the turbine blade is fitted into the groove - C1 on the steam downstream side of the turbine wheel. A wheel implantation part I to a collar that prevents steam movement of the blade implantation part to the downstream side is formed integrally with the turbine wheel, and the steam of the blade implantation part is formed on the steam upstream side of the blade implantation part. A turbine cutout characterized in that a stopper is formed to prevent movement toward the downstream side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9958883A JPS59226202A (en) | 1983-06-06 | 1983-06-06 | Moving blade of turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP9958883A JPS59226202A (en) | 1983-06-06 | 1983-06-06 | Moving blade of turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS59226202A true JPS59226202A (en) | 1984-12-19 |
Family
ID=14251248
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP9958883A Pending JPS59226202A (en) | 1983-06-06 | 1983-06-06 | Moving blade of turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS59226202A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4767274A (en) * | 1986-12-29 | 1988-08-30 | United Technologies Corporation | Multiple lug blade to disk attachment |
| EP0321825A2 (en) * | 1987-12-19 | 1989-06-28 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Axially traversed row of rotor blades for compressors or turbines |
| US5067877A (en) * | 1990-09-11 | 1991-11-26 | United Technologies Corporation | Fan blade axial retention device |
| US5368444A (en) * | 1993-08-30 | 1994-11-29 | General Electric Company | Anti-fretting blade retention means |
| EP1830037A2 (en) * | 2006-03-02 | 2007-09-05 | Hitachi, Ltd. | Steam turbine blade |
| JP2008144624A (en) * | 2006-12-07 | 2008-06-26 | Ihi Corp | Turbine moving blade fixing structure |
| EP2045444A1 (en) * | 2007-10-01 | 2009-04-08 | ALSTOM Technology Ltd | Rotor blade, method for producing a rotor blade, and compressor with such a rotor blade |
| US20100329872A1 (en) * | 2009-06-30 | 2010-12-30 | Donald Joseph Kasperski | Method and apparatus for assembling rotating machines |
| CN102758652A (en) * | 2011-04-26 | 2012-10-31 | 通用电气公司 | Adaptor assembly for coupling turbine blades to rotor disks |
| JP2013256938A (en) * | 2012-06-12 | 2013-12-26 | General Electric Co <Ge> | Blade attachment assembly |
| CN104912603A (en) * | 2015-04-03 | 2015-09-16 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combined blade root |
-
1983
- 1983-06-06 JP JP9958883A patent/JPS59226202A/en active Pending
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4767274A (en) * | 1986-12-29 | 1988-08-30 | United Technologies Corporation | Multiple lug blade to disk attachment |
| EP0321825A2 (en) * | 1987-12-19 | 1989-06-28 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Axially traversed row of rotor blades for compressors or turbines |
| JPH01193005A (en) * | 1987-12-19 | 1989-08-03 | Mtu Motoren & Turbinen Union Muenchen Gmbh | Axial flow rotor blade structure for compressor or turbine |
| US5067877A (en) * | 1990-09-11 | 1991-11-26 | United Technologies Corporation | Fan blade axial retention device |
| US5368444A (en) * | 1993-08-30 | 1994-11-29 | General Electric Company | Anti-fretting blade retention means |
| EP1830037A3 (en) * | 2006-03-02 | 2012-11-14 | Hitachi, Ltd. | Steam turbine blade |
| EP1830037A2 (en) * | 2006-03-02 | 2007-09-05 | Hitachi, Ltd. | Steam turbine blade |
| US7798779B2 (en) * | 2006-03-02 | 2010-09-21 | Hitachi, Ltd. | Steam turbine blade, and steam turbine and steam turbine power plant using the blade |
| JP2008144624A (en) * | 2006-12-07 | 2008-06-26 | Ihi Corp | Turbine moving blade fixing structure |
| US8257047B2 (en) | 2007-10-01 | 2012-09-04 | Alstom Technology Ltd. | Rotor blade, method for producing a rotor blade, and compressor with a rotor blade |
| EP2045444A1 (en) * | 2007-10-01 | 2009-04-08 | ALSTOM Technology Ltd | Rotor blade, method for producing a rotor blade, and compressor with such a rotor blade |
| CN101936191A (en) * | 2009-06-30 | 2011-01-05 | 通用电气公司 | Method and apparatus for assembling rotating machines |
| US8251668B2 (en) * | 2009-06-30 | 2012-08-28 | General Electric Company | Method and apparatus for assembling rotating machines |
| US20100329872A1 (en) * | 2009-06-30 | 2010-12-30 | Donald Joseph Kasperski | Method and apparatus for assembling rotating machines |
| CN102758652A (en) * | 2011-04-26 | 2012-10-31 | 通用电气公司 | Adaptor assembly for coupling turbine blades to rotor disks |
| US20120275920A1 (en) * | 2011-04-26 | 2012-11-01 | General Electric Company | Adaptor assembly for coupling turbine blades to rotor disks |
| US8740573B2 (en) * | 2011-04-26 | 2014-06-03 | General Electric Company | Adaptor assembly for coupling turbine blades to rotor disks |
| CN102758652B (en) * | 2011-04-26 | 2016-03-16 | 通用电气公司 | For turbine bucket being connected to the adapter assembly of rotor disk |
| JP2013256938A (en) * | 2012-06-12 | 2013-12-26 | General Electric Co <Ge> | Blade attachment assembly |
| US10215036B2 (en) | 2012-06-12 | 2019-02-26 | General Electric Company | Blade attachment assembly |
| CN104912603A (en) * | 2015-04-03 | 2015-09-16 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Combined blade root |
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