JP3697705B2 - Gas turbine high pressure turbine stationary blade fixing device - Google Patents
Gas turbine high pressure turbine stationary blade fixing device Download PDFInfo
- Publication number
- JP3697705B2 JP3697705B2 JP15611995A JP15611995A JP3697705B2 JP 3697705 B2 JP3697705 B2 JP 3697705B2 JP 15611995 A JP15611995 A JP 15611995A JP 15611995 A JP15611995 A JP 15611995A JP 3697705 B2 JP3697705 B2 JP 3697705B2
- Authority
- JP
- Japan
- Prior art keywords
- pin
- gas turbine
- head
- stationary blade
- pressure 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 - Lifetime
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- Turbine Rotor Nozzle Sealing (AREA)
Description
【0001】
【産業上の利用分野】
本発明は、ガスタービン高圧タービン静翼の固定装置に関するものである。
【0002】
【従来の技術】
従来のこの種の静翼の固定装置は、たとえば、図2に示すような構成からなっている。
図2において、11はガスタービン高圧タービン静翼、12は該静翼11を取付けているインナーバンド、12aは該インナーバンド12の内側フランジ、13はアウターバンド、14は内側固定部材、15は締結ボルト、16はそのナット(通常はシャンクナット)、17はラビリンスシールシュラウド、18は動翼、19はロータである。
【0003】
すなわち、インナーバンド12の内側フランジ12aを内側固定部材14の溝部に嵌入して前記ボルト15とナット16で締結している。
【0004】
【発明が解決しようとする課題】
しかしながら、従来のこの種の静翼の固定装置は、図2に示したように、内側フランジ12aと内側固定部材14とはボルト15とナット16による締結であるため、前記内側フランジ12aとロータ19の間に比較的大きなスペースを必要とし、全体としての軸方向の長さが長くなり、また矢印20から21で示す冷却空気が通る際、ボルト15の頭部またはナット16の存在により、冷却空気がかくはんされて風損を生じて発熱するなどして、冷却効果が悪くなるという問題点があった。
【0005】
本発明は、このような問題点を解決しようとするものである。すなわち、本発明は、軸方向の長さが短く、かつ、冷却空気の風損が少く、発熱が抑制されて冷却効果が向上するガスタービン高圧タービン静翼の固定装置を提供することを目的とするものである。
【0006】
【課題を解決するための手段】
上記目的を達成するため、本発明は、ガスタービン高圧タービン静翼を取付けているインナーバンドの内側フランジを内側固定部材に固定した頭部の薄いピンと、延長部が前記ピンの頭部外面全体に接するように延びて該ピンの抜け止めをしているラビリンスシールシュラウドとからなるものとした。
【0007】
【作用】
本発明によれば、ガスタービン高圧タービン静翼を取付けているインナーバンドの内側フランジを内側固定部材に固定した頭部の薄いピンと、延長部が前記ピンの頭部に接して該ピンの抜け止めをしているラビリンスシールシュラウドとからなるので、従来のボルトナット締結に比較して頭部の薄いピンによるため、軸方向の長さが短くなり、かつ、ピンの頭のつくる凹凸をラビリンスシールシュラウドが覆い、流路が平坦となることで冷却空気の風損も微少なものとなり、発熱が抑制される。
【0008】
【実施例】
図1は本発明の一実施例を示した断面側面図である。
図1において、1はガスタービン高圧タービン静翼、2は該静翼1を取付けているインナーバンド、2aは該インナーバンド2の内側フランジ、3はアウターバンド、4は内側固定部材、5はピン、5aは該ピン5の頭部、5bは該ピン5の先部、6はラビリンスシールシュラウド、6aは該シュラウド6の延長部、7は動翼、8はロータである。
【0009】
すなわち、ガスタービン高圧タービン静翼1を取付けているインナーバンド2の内側フランジ2aを内側固定部材4の溝部に嵌入して該フランジ2aと該固定部材4のピン孔にピン5を挿通し、該シュラウド6の延長部6aをピン5の頭部5aに圧接させてピン5の抜け止めをする。
【0010】
図1に示すように構成されたガスタービン高圧タービン静翼の固定装置においては、インナーバンド2の内側フランジ2aとロータ8の間に広いスペースを必要としなくなって軸方向の長さが短くなるため、内側フランジ2aを可及的にエンジンの後方に寄せることができる。また矢印9から10で示すように流れる冷却空気の流路にボルト頭部やナットなどの流れをかくはんさせるものがないため、風損による発熱もない。
【0011】
【発明の効果】
以上説明したように、本発明によれば、ガスタービン高圧タービン静翼を取付けているインナーバンドの内側フランジを内側固定部材に固定した頭部の薄いピンと、延長部が前記ピンの頭部に接して該ピンの抜け止めをしているラビリンスシールシュラウドとからなるので、インナーバンドの内側フランジとロータの間に広いスペースを必要としなくなって軸方向の長さが短くなるため、該内側フランジを可及的にエンジンの後方に寄せることができて、インナーバンドの冷却が容易となる。また冷却空気の流路にボルト頭部やナットなどの流れをかくはんさせる凹凸物がないため、風損による発熱を抑制できる。
【図面の簡単な説明】
【図1】本発明の一実施例を示した断面側面図である。
【図2】従来の技術の一例を示した断面側面図である。
【符号の説明】
1 ガスタービン高圧タービン静翼
2 インナーバンド
2a 内側フランジ
4 内側固定部材
5 ピン
5a 頭部
6 ラビリンスシールシュラウド
6a 延長部[0001]
[Industrial application fields]
The present invention relates to a fixing device for a gas turbine high-pressure turbine stationary blade.
[0002]
[Prior art]
A conventional stationary blade fixing device of this type has a structure as shown in FIG. 2, for example.
In FIG. 2, 11 is a gas turbine high-pressure turbine stationary blade, 12 is an inner band to which the
[0003]
That is, the inner flange 12 a of the
[0004]
[Problems to be solved by the invention]
However, in this type of conventional stationary blade fixing device, as shown in FIG. 2, the inner flange 12 a and the
[0005]
The present invention is intended to solve such problems. That is, an object of the present invention is to provide a gas turbine high-pressure turbine stationary blade fixing device that has a short axial length, has a small air loss of cooling air, suppresses heat generation, and improves a cooling effect. To do.
[0006]
[Means for Solving the Problems]
In order to achieve the above-mentioned object, the present invention provides a thin pin on the head in which the inner flange of the inner band to which the gas turbine high-pressure turbine stationary blade is attached is fixed to the inner fixing member, and an extension part on the entire outer surface of the head of the pin. The labyrinth seal shroud extends so as to contact and prevents the pin from coming off.
[0007]
[Action]
According to the present invention, the thin pin of the head in which the inner flange of the inner band to which the gas turbine high-pressure turbine stationary blade is attached is fixed to the inner fixing member, and the extension is in contact with the head of the pin and the pin is prevented from coming off. The labyrinth seal shroud is made of a pin with a thin head compared to the conventional bolt and nut fastening, so the axial length is shortened and the irregularities created by the pin head are reduced. Since the flow path is flat and the flow path is flat, the air loss of the cooling air is also small, and heat generation is suppressed.
[0008]
【Example】
FIG. 1 is a sectional side view showing an embodiment of the present invention.
In FIG. 1, 1 is a gas turbine high-pressure turbine stationary blade, 2 is an inner band to which the stationary blade 1 is attached, 2a is an inner flange of the
[0009]
That is, the inner flange 2a of the
[0010]
In the gas turbine high-pressure turbine stationary blade fixing device configured as shown in FIG. 1, a large space is not required between the inner flange 2a of the
[0011]
【The invention's effect】
As described above, according to the present invention, the thin pin of the head in which the inner flange of the inner band to which the gas turbine high-pressure turbine stationary blade is attached is fixed to the inner fixing member, and the extension portion are in contact with the head of the pin. Since the labyrinth seal shroud prevents the pin from coming off, a large space is not required between the inner flange of the inner band and the rotor, and the axial length is shortened. As a result, the inner band can be moved to the rear of the engine and cooling of the inner band is facilitated. In addition, since there are no irregularities that stir the flow of bolt heads and nuts in the cooling air flow path, heat generation due to windage can be suppressed.
[Brief description of the drawings]
FIG. 1 is a sectional side view showing an embodiment of the present invention.
FIG. 2 is a cross-sectional side view showing an example of a conventional technique.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Gas turbine high pressure turbine
Claims (3)
前記ラビリンスシールシュラウドは周方向に隙間なく連続的に延びて一体をなす単一部材であることを特徴とする、ガスタービン高圧タービン静翼の固定装置。A thin pin on the head with the inner flange of the inner band to which the gas turbine high-pressure turbine stator blade is attached fixed to the inner fixing member, and an extension portion so as to contact the head of the pin to prevent the pin from coming off. The labyrinth seal shroud
The labyrinth seal shroud is a single member that continuously extends in the circumferential direction without gaps and is integrated into a single member .
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP15611995A JP3697705B2 (en) | 1995-06-22 | 1995-06-22 | Gas turbine high pressure turbine stationary blade fixing device |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP15611995A JP3697705B2 (en) | 1995-06-22 | 1995-06-22 | Gas turbine high pressure turbine stationary blade fixing device |
Publications (2)
Publication Number | Publication Date |
---|---|
JPH094407A JPH094407A (en) | 1997-01-07 |
JP3697705B2 true JP3697705B2 (en) | 2005-09-21 |
Family
ID=15620741
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP15611995A Expired - Lifetime JP3697705B2 (en) | 1995-06-22 | 1995-06-22 | Gas turbine high pressure turbine stationary blade fixing device |
Country Status (1)
Country | Link |
---|---|
JP (1) | JP3697705B2 (en) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3048017B1 (en) * | 2016-02-24 | 2019-05-31 | Safran Aircraft Engines | AIRCRAFT TURBOMACHINE COMPRESSOR RECTIFIER, COMPRISING STRIPPED AIR-LIFTING ORIFICES ACCORDING TO THE CIRCUMFERENTIAL DIRECTION |
FR3091311B1 (en) * | 2018-12-31 | 2021-04-09 | Safran Aircraft Engines | Turbine distributor, turbomachine turbine equipped with this distributor and turbomachine equipped with this turbine. |
-
1995
- 1995-06-22 JP JP15611995A patent/JP3697705B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
JPH094407A (en) | 1997-01-07 |
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