JP3697705B2 - Gas turbine high pressure turbine stationary blade fixing device - Google Patents

Gas turbine high pressure turbine stationary blade fixing device Download PDF

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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
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Japan
Prior art keywords
pin
gas turbine
head
stationary blade
pressure turbine
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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
Application number
JP15611995A
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Japanese (ja)
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JPH094407A (en
Inventor
正純 林
Original Assignee
石川島播磨重工業株式会社
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Priority to JP15611995A priority Critical patent/JP3697705B2/en
Publication of JPH094407A publication Critical patent/JPH094407A/en
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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 stationary blade 11 is attached, 12a is an inner flange of the inner band 12, 13 is an outer band, 14 is an inner fixing member, and 15 is a fastening member. Bolts 16 are nuts (usually shank nuts), 17 are labyrinth seal shrouds, 18 are moving blades, and 19 is a rotor.
[0003]
That is, the inner flange 12 a of the inner band 12 is fitted into the groove portion of the inner fixing member 14 and fastened by the bolt 15 and the nut 16.
[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 inner fixing member 14 are fastened by bolts 15 and nuts 16. A relatively large space is required between them, the overall axial length is increased, and when the cooling air indicated by arrows 20 to 21 passes, the presence of the head of the bolt 15 or the nut 16 causes the cooling air. There is a problem that the cooling effect is deteriorated by being stirred and generating windage and generating heat.
[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 inner band 2, 3 is an outer band, 4 is an inner fixing member, and 5 is a pin. 5a is the head of the pin 5, 5b is the tip of the pin 5, 6 is a labyrinth seal shroud, 6a is an extension of the shroud 6, 7 is a moving blade, and 8 is a rotor.
[0009]
That is, the inner flange 2a of the inner band 2 to which the gas turbine high-pressure turbine stationary blade 1 is attached is fitted into the groove portion of the inner fixing member 4, and the pin 5 is inserted into the pin hole of the flange 2a and the fixing member 4, The extension 6 a of the shroud 6 is pressed against the head 5 a of the pin 5 to prevent the pin 5 from coming off.
[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 inner band 2 and the rotor 8, and the axial length is shortened. The inner flange 2a can be moved toward the rear of the engine as much as possible. In addition, since there is nothing that stirs the flow of bolt heads and nuts in the flow path of the cooling air flowing as shown by arrows 9 to 10, there is no heat generation due to windage.
[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 stationary blade 2 Inner band 2a Inner flange 4 Inner fixing member 5 Pin 5a Head 6 Labyrinth seal shroud 6a Extension part

Claims (3)

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 extending so as to contact the entire outer surface of the head to prevent the pin from coming off. A gas turbine high pressure turbine stationary blade fixing device comprising a labyrinth seal shroud. 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り、
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 . 前記ラビリンスシールシュラウドは、軸方向に下流側から上流側へ移動させるだけで、前記延長部が前記ピンの頭部に接触して該ピンを抜け止めするように装着されることを特徴とする請求項１又は２に記載のガスタービン高圧タービン静翼の固定装置。The labyrinth seal shroud is mounted such that the extension portion contacts the head of the pin and prevents the pin from coming off only by moving the labyrinth seal shroud from the downstream side to the upstream side in the axial direction. Item 3. The fixing device for a gas turbine high-pressure turbine stationary blade according to Item 1 or 2.
JP15611995A 1995-06-22 1995-06-22 Gas turbine high pressure turbine stationary blade fixing device Expired - Lifetime JP3697705B2 (en)

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

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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.

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