JPH08246805A - Stator blade for turbine - Google Patents
Stator blade for turbineInfo
- Publication number
- JPH08246805A JPH08246805A JP4699895A JP4699895A JPH08246805A JP H08246805 A JPH08246805 A JP H08246805A JP 4699895 A JP4699895 A JP 4699895A JP 4699895 A JP4699895 A JP 4699895A JP H08246805 A JPH08246805 A JP H08246805A
- Authority
- JP
- Japan
- Prior art keywords
- ring
- inner ring
- vane
- strength
- 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.)
- Granted
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、火力発電などに適用さ
れる蒸気タービンなどタービンの静翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a stationary blade of a turbine such as a steam turbine applied to thermal power generation.
【０００２】[0002]
【従来の技術】図４は火力発電などに使用されている従
来の蒸気タービンの静翼の説明図である。図において、
従来の蒸気タービンの静翼（仕切板を含む）８の前後に
は蒸気の圧力差があり、この圧力差を利用してノズル６
および翼部で仕事をするようになっている。この蒸気の
圧力差を有効に利用するために静翼８の内輪７内側にシ
ールリング９を装着して蒸気の漏洩を減らす工夫がなさ
れており、このために内輪７内側は自由支持構造になっ
ている。図における符号２は車室または翼環、４はロー
タ、５は静翼８の外輪である。2. Description of the Related Art FIG. 4 is an explanatory view of a vane of a conventional steam turbine used for thermal power generation or the like. In the figure,
There is a steam pressure difference before and after a conventional vane (including a partition plate) 8 of a steam turbine, and the nozzle 6 is utilized by utilizing this pressure difference.
And work on the wings. In order to effectively utilize this pressure difference of steam, a seal ring 9 is attached to the inner ring 7 of the stationary vane 8 to reduce steam leakage. Therefore, the inner ring 7 has a free support structure. ing. In the figure, reference numeral 2 is a vehicle compartment or blade ring, 4 is a rotor, and 5 is an outer ring of the stationary blade 8.
【０００３】[0003]
【発明が解決しようとする課題】上記のように、従来の
蒸気タービンの静翼においては内輪７内側は自由支持構
造になっているが、蒸気入口の高温、高圧化に伴って静
翼８前後の圧力差や温度などが増大し、特に初段近くの
静翼８はノズル６の強度、内輪７、外輪５の強度などが
不足して撓み量が増すなど設計的に厳しくなっている。
これらの強度不足に対しては高強度の材料を採用した
り、内輪７、外輪５の板厚を増加させるなどして対応し
ているが、内輪７内側の支持構造が自由支持構造になっ
ているために限界がある。As described above, in the conventional vane of the steam turbine, the inside of the inner ring 7 has a free support structure, but the vane 8 is located around the vane 8 due to the high temperature and high pressure of the steam inlet. The pressure difference, temperature, and the like increase, and the design of the stationary blades 8 near the first stage becomes severe because the strength of the nozzle 6, the strength of the inner ring 7, and the outer ring 5 are insufficient, and the amount of bending increases.
The lack of strength is dealt with by using high-strength materials or increasing the plate thickness of the inner ring 7 and the outer ring 5, but the support structure inside the inner ring 7 is a free support structure. There are limits because
【０００４】[0004]
【課題を解決するための手段】本発明に係るタービンの
静翼は上記課題の解決を目的にしており、ロータの外側
にシール材を介して静翼の内輪が装着されるタービンの
静翼において、上記ロータの外周にシール材を介してリ
ング状部材を嵌装し、上記リング状部材の外周に上記内
輪を嵌装して互いの接触面に刻設された凹凸を介して固
定した構成を特徴とする。SUMMARY OF THE INVENTION A turbine vane according to the present invention is intended to solve the above-mentioned problems. In a turbine vane in which an inner ring of the vane is mounted on the outer side of a rotor via a seal material. A configuration in which a ring-shaped member is fitted on the outer circumference of the rotor via a seal material, and the inner ring is fitted on the outer circumference of the ring-shaped member and fixed via concavities and convexities engraved on the mutual contact surfaces. Characterize.
【０００５】また、本発明に係るタービンの静翼は、ロ
ータの外側にシール材を介して静翼の内輪が装着される
タービンの静翼において、上記ロータの外周にシール材
を介してリング状部材を嵌装し、上記リング状部材の外
周に上記内輪を嵌装して互いの接触面に刻設された段差
を嵌め込んで固定した構成を特徴とする。Further, the turbine vane according to the present invention is a turbine vane in which an inner ring of the vane is mounted on the outside of the rotor via a seal material, and a ring shape is provided on the outer circumference of the rotor via the seal material. A member is fitted, the inner ring is fitted on the outer periphery of the ring-shaped member, and the steps formed on the contact surfaces of the members are fitted and fixed.
【０００６】また、本発明に係るタービンの静翼は、ロ
ータの外側にシール材を介して静翼の内輪が装着される
タービンの静翼において、上記ロータの外周にシール材
を介してリング状部材を嵌装し、上記リング状部材の外
周に上記内輪を嵌装して互いの接触面に挿入されたキー
状部材により固定した構成を特徴とする。Further, the turbine vane according to the present invention is a turbine vane in which an inner ring of the vane is mounted on the outside of the rotor via a seal material, and a ring shape is provided on the outer periphery of the rotor via the seal material. A member is fitted, and the inner ring is fitted on the outer periphery of the ring-shaped member and fixed by a key-shaped member inserted into the mutual contact surface.
【０００７】[0007]
【作用】即ち、本発明に係るタービンの静翼において
は、ロータの外側にシール材を介して静翼の内輪が装着
されるタービンの静翼におけるロータの外周にシール材
を介して嵌装されたリング状部材の外周に内輪が嵌装さ
れ互いの接触面に刻設された凹凸を介して固定されてお
り、タービンの静翼の内輪の支持構造を従来の自由支持
構造から固定支持構造とすることにより静翼前後の圧力
差に対する静翼のノズル、内輪、外輪などの強度が向上
して撓み量を従来の自由支持構造の場合に比べて大幅に
小さくすることができる。In other words, in the turbine vane according to the present invention, the inner ring of the vane is mounted on the outer side of the rotor via the seal material and is fitted on the outer periphery of the rotor of the turbine vane via the seal material. The inner ring is fitted around the outer periphery of the ring-shaped member and is fixed through the concavities and convexities engraved on the mutual contact surfaces, and the supporting structure of the inner ring of the turbine vane is changed from the conventional free supporting structure to the fixed supporting structure. By doing so, the strength of the nozzle, inner ring, outer ring, etc. of the stationary blade against the pressure difference between the front and rear of the stationary blade is improved, and the amount of deflection can be made significantly smaller than in the case of the conventional free support structure.
【０００８】また、本発明に係るタービンの静翼におい
ては、ロータの外側にシール材を介して静翼の内輪が装
着されるタービンの静翼におけるロータの外周にシール
材を介して嵌装されたリング状部材の外周に内輪が嵌装
され互いの接触面に刻設された段差を嵌め込んで固定さ
れており、タービンの静翼の内輪の支持構造を従来の自
由支持構造から固定支持構造とすることにより静翼前後
の圧力差に対する静翼のノズル、内輪、外輪などの強度
が向上して撓み量を従来の自由支持構造の場合に比べて
大幅に小さくすることができる。Further, in the turbine vane according to the present invention, the inner ring of the vane is mounted on the outer side of the rotor via the seal material and is fitted on the outer periphery of the rotor of the turbine vane via the seal material. The inner ring is fitted around the outer periphery of the ring-shaped member and fixed by inserting the step carved in the contact surfaces of the ring-shaped members from the conventional free support structure to the fixed support structure of the inner ring of the turbine vane. By doing so, the strength of the nozzle of the stationary blade, the inner ring, the outer ring and the like against the pressure difference before and after the stationary blade is improved, and the amount of deflection can be made significantly smaller than in the case of the conventional free support structure.
【０００９】また、本発明に係るタービンの静翼におい
ては、ロータの外側にシール材を介して静翼の内輪が装
着されるタービンの静翼におけるロータの外周にシール
材を介して嵌装されたリング状部材の外周に内輪が嵌装
され互いの接触面に挿入されたキー状部材により固定さ
れており、タービンの静翼の内輪の支持構造を従来の自
由支持構造から固定支持構造とすることにより静翼前後
の圧力差に対する静翼のノズル、内輪、外輪などの強度
が向上して撓み量を従来の自由支持構造の場合に比べて
大幅に小さくすることができる。Further, in the turbine vane according to the present invention, the inner ring of the vane is mounted on the outer side of the rotor via the seal material, and is fitted on the outer periphery of the rotor of the turbine vane of the turbine via the seal material. The inner ring is fitted around the outer periphery of the ring-shaped member and is fixed by the key-shaped member inserted into the contact surface of each other, and the supporting structure of the inner ring of the turbine vane is changed from the conventional free supporting structure to the fixed supporting structure. As a result, the strength of the nozzle of the stationary blade, the inner ring, the outer ring, and the like against the pressure difference before and after the stationary blade is improved, and the amount of bending can be significantly reduced as compared with the conventional free support structure.
【００１０】[0010]
【実施例】図１は本発明の一実施例に係る蒸気タービン
の静翼の説明図、図２および図３はそれぞれその応用例
に係る蒸気タービンの静翼の説明図である。図におい
て、これら実施例に係る蒸気タービンの静翼は火力発電
などに使用される蒸気タービンの静翼で、図における符
号２は車室または翼環、３はダミー環、４はロータ、
５，６，７はそれぞれ静翼８の外輪、ノズル、内輪、９
はシールリング、１０はねじ、ピンなどのキー部材であ
る。DESCRIPTION OF THE PREFERRED EMBODIMENTS FIG. 1 is an explanatory view of a steam turbine vane according to an embodiment of the present invention, and FIGS. 2 and 3 are explanatory views of a steam turbine vane according to its application. In the drawings, the stationary blades of the steam turbines according to these examples are stationary blades of the steam turbine used for thermal power generation, etc., in the drawing, reference numeral 2 is a casing or blade ring, 3 is a dummy ring, 4 is a rotor,
5, 6 and 7 are the outer ring, nozzle, inner ring, and 9 of the vane 8, respectively.
Is a seal ring, and 10 is a key member such as a screw or a pin.
【００１１】図１において、蒸気タービンの静翼（仕切
板を含む）８の前後には蒸気の圧力差があり、この圧力
差を利用してノズル６および翼部で仕事をするようにな
っている。この蒸気の圧力差を有効に利用するために静
翼８の内輪７内側にシールリング９を装着して蒸気の漏
洩を減らす工夫がなされている。本静翼においては、図
に示すようにロータ４の外周にダミー環３が嵌装され、
ロータ４とダミー環３との間にシールリング９が装着さ
れている。そして、静翼８の内輪７内側に凹部が、また
ダミー環３外側に凸部がそれぞれ設けられており、凹部
に凸部を嵌め込むことにより内輪７とダミー環３とを固
定して静翼８を支持するようになっている。In FIG. 1, there is a steam pressure difference before and after a stationary blade (including a partition plate) 8 of the steam turbine, and the nozzle 6 and the blade portion are made to work by utilizing this pressure difference. There is. In order to effectively use this steam pressure difference, a seal ring 9 is attached to the inside of the inner ring 7 of the stationary blade 8 to reduce steam leakage. In the stationary vane, the dummy ring 3 is fitted on the outer periphery of the rotor 4 as shown in the figure,
A seal ring 9 is mounted between the rotor 4 and the dummy ring 3. Further, a concave portion is provided inside the inner ring 7 of the vane 8 and a convex portion is provided outside the dummy ring 3, respectively. By fitting the convex portion into the concave portion, the inner ring 7 and the dummy ring 3 are fixed, and the vane blade is fixed. It is designed to support 8.
【００１２】なお、図２に示すように内輪７内側とダミ
ー環３外側とをそれぞれＬ字状に切欠いて段差を設け、
互いの段差を嵌め込むことにより内輪７とダミー環３と
を固定して静翼８を支持するようにしてもよい。また、
図３に示すようにねじ、ピンなどのキー部材１０を内輪
７内側とダミー環３外側との嵌合面に刻設したキー溝内
に嵌入することにより内輪７とダミー環３とを固定して
静翼８を支持するようにしてもよい。As shown in FIG. 2, the inside of the inner ring 7 and the outside of the dummy ring 3 are each cut out in an L shape to form a step,
The inner ring 7 and the dummy ring 3 may be fixed by fitting the steps to each other to support the vanes 8. Also,
As shown in FIG. 3, the inner ring 7 and the dummy ring 3 are fixed by fitting the key member 10 such as a screw or a pin into the key groove formed in the fitting surface between the inner ring 7 inner side and the dummy ring 3 outer side. You may make it support the stationary blade 8.
【００１３】このように静翼８の内輪７内側の支持構造
を従来の自由支持構造から固定支持構造とすることによ
り、静翼８前後の圧力差に対するノズル６、内輪７、外
輪５などの強度が向上して撓み量を従来の自由支持構造
の場合と比べ大幅に小さくすることができる。By changing the supporting structure inside the inner ring 7 of the stationary blade 8 from the conventional free supporting structure to the fixed supporting structure as described above, the strength of the nozzle 6, the inner ring 7, the outer ring 5 and the like against the pressure difference across the stationary blade 8. And the amount of bending can be significantly reduced as compared with the conventional free supporting structure.
【００１４】従来の蒸気タービンの静翼においては内輪
内側は自由支持構造になっているが、蒸気入口の高温、
高圧化に伴って静翼前後の圧力差や温度などが増大し、
特に初段近くの静翼はノズルの強度、内輪、外輪の強度
などが不足して撓み量が増すなど設計的に厳しくなって
いる。これらの強度不足に対しては高強度の材料を採用
したり、内輪、外輪の板厚を増加させるなどして対応し
ているが、内輪内側の支持構造が自由支持構造になって
いるために限界がある。これに対し、上述の各蒸気ター
ビンの静翼においては内輪７内側をダミー環３に固定し
て静翼８を支持する構造にしており、ノズル６、内輪
７、外輪５などの強度を向上させて撓み量を大幅に減少
させることができる。この内輪７の支持構造の強度計算
例では従来の自由支持構造の場合の強度をベースとする
と、固定支持構造ではノズル６の強度が８０％、外輪５
の強度が８０％、内輪７の強度が４０％それぞれ向上し
て撓み量が１０％以下となる。従来の蒸気タービンの静
翼のように内輪７内側の支持構造が自由支持構造では蒸
気条件、前後圧力差、温度などによってはノズル６の強
度、内輪７、外輪５の強度、撓み量などの許容値を満足
させるためには高強度材料を採用したり、内輪７、外輪
５の板厚を増加させることにより軸方向のスパンが必要
以上に延びたりするが、上述のように内輪７内側が固定
支持構造の場合は静翼８の強度が向上して撓み量が従来
の自由支持構造の場合に比べて大幅に減少するので、高
強度材料の採用や内輪７、外輪５の板厚の増加などを回
避することができて軸方向のスパンを必要以上に延ばす
ことなく蒸気入口の高温、高圧化に対応することがで
き、コンパクトな構造の蒸気タービンが得られる。In the conventional vane of a steam turbine, the inside of the inner ring has a free support structure, but the high temperature of the steam inlet,
As the pressure increases, the pressure difference before and after the stationary blade and temperature increase,
In particular, the stator vanes near the first stage are stricter in terms of design because the strength of the nozzle, the strength of the inner ring, and the outer ring are insufficient and the amount of bending increases. We cope with these lack of strength by adopting high-strength materials and increasing the plate thickness of the inner ring and outer ring, but because the support structure inside the inner ring is a free support structure. There is a limit. On the other hand, in the above vane of each steam turbine, the inside of the inner ring 7 is fixed to the dummy ring 3 to support the vane 8, and the strength of the nozzle 6, the inner ring 7, the outer ring 5, etc. is improved. Therefore, the amount of bending can be greatly reduced. In this strength calculation example of the support structure of the inner ring 7, the strength of the nozzle 6 is 80% in the fixed support structure and the strength of the outer ring 5 is based on the strength of the conventional free support structure.
The strength of the inner ring 7 is improved by 80% and the strength of the inner ring 7 is improved by 40%, and the amount of bending is reduced to 10% or less. When the support structure inside the inner ring 7 is a free support structure such as the stationary blade of a conventional steam turbine, the strength of the nozzle 6, the strength of the inner ring 7 and the outer ring 5, and the amount of bending may be allowed depending on the steam conditions, the pressure difference between the front and rear, the temperature, etc. In order to satisfy the value, a high-strength material is used, or the axial thickness is increased by increasing the plate thickness of the inner ring 7 and the outer ring 5, but the inner ring 7 is fixed inside as described above. In the case of the support structure, the strength of the stationary blades 8 is improved and the amount of deflection is significantly reduced compared to the conventional free support structure. Therefore, the use of high strength materials, the increase of the plate thickness of the inner ring 7 and the outer ring 5, etc. It is possible to avoid high temperature and high pressure at the steam inlet without unnecessarily extending the span in the axial direction, and a steam turbine having a compact structure can be obtained.
【００１５】[0015]
【発明の効果】本発明に係るタービンの静翼は前記のよ
うに構成されており、静翼の強度が向上するので、高強
度材料の採用、内輪、外輪の板厚の増加などを回避して
軸方向のスパンを必要以上に延ばすことなく蒸気入口の
高温、高圧化に対応することができる。The turbine vane according to the present invention is constructed as described above, and since the strength of the vane is improved, it is possible to avoid the use of high-strength materials and the increase in the thickness of the inner and outer rings. It is possible to cope with high temperature and high pressure at the steam inlet without extending the axial span unnecessarily.
【図１】図１は本発明の一実施例に係る蒸気タービンの
静翼の正面図である。FIG. 1 is a front view of a vane of a steam turbine according to an embodiment of the present invention.
【図２】図２はその応用例に係る蒸気タービンの静翼の
要部詳細図である。FIG. 2 is a detailed view of a main part of a vane of a steam turbine according to the application example.
【図３】図３（ａ）は他の応用例に係る蒸気タービンの
静翼の要部詳細図、同図（ｂ）は同図（ａ）におけるＢ
−Ｂ矢視図である。FIG. 3 (a) is a detailed view of a main part of a vane of a steam turbine according to another application example, and FIG. 3 (b) is a B in FIG. 3 (a).
FIG.
【図４】図４は従来の蒸気タービンの静翼の正面図であ
る。FIG. 4 is a front view of a vane of a conventional steam turbine.
２ 車室または翼環 ３ ダミー環 ４ ロータ ５ 外輪 ６ ノズル ７ 内輪 ８ 静翼 ９ シールリング １０ ねじ、ピンなどのキー部材 2 Cabin or blade ring 3 Dummy ring 4 Rotor 5 Outer ring 6 Nozzle 7 Inner ring 8 Stator blade 9 Seal ring 10 Key members such as screws and pins
Claims (3)
内輪が装着されるタービンの静翼において、上記ロータ
の外周にシール材を介してリング状部材を嵌装し、上記
リング状部材の外周に上記内輪を嵌装して互いの接触面
に刻設された凹凸を介して固定したことを特徴とするタ
ービンの静翼。1. In a turbine vane in which an inner ring of a vane is mounted on the outside of a rotor via a seal material, a ring-shaped member is fitted on the outer periphery of the rotor via the seal material, and the ring-shaped member is mounted. A turbine vane characterized in that the inner ring is fitted around the outer periphery of and fixed via concavities and convexities engraved on the mutual contact surfaces.
内輪が装着されるタービンの静翼において、上記ロータ
の外周にシール材を介してリング状部材を嵌装し、上記
リング状部材の外周に上記内輪を嵌装して互いの接触面
に刻設された段差を嵌め込んで固定したことを特徴とす
るタービンの静翼。2. In a turbine vane in which an inner ring of a vane is mounted on the outer side of a rotor via a seal material, a ring-shaped member is fitted on the outer periphery of the rotor via a seal material, and the ring-shaped member is mounted. A turbine vane, characterized in that the inner ring is fitted on the outer periphery of and the steps formed on the contact surfaces of the inner ring are fitted and fixed.
内輪が装着されるタービンの静翼において、上記ロータ
の外周にシール材を介してリング状部材を嵌装し、上記
リング状部材の外周に上記内輪を嵌装して互いの接触面
に挿入されたキー状部材により固定したことを特徴とす
るタービンの静翼。3. In a turbine vane in which an inner ring of a vane is mounted on the outer side of a rotor via a seal material, a ring-shaped member is fitted on the outer periphery of the rotor via the seal material, and the ring-shaped member is mounted. A turbine vane characterized in that the inner ring is fitted around the outer periphery of and fixed by a key-shaped member inserted into the mutual contact surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4699895A JP2961063B2 (en) | 1995-03-07 | 1995-03-07 | Turbine vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4699895A JP2961063B2 (en) | 1995-03-07 | 1995-03-07 | Turbine vane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH08246805A true JPH08246805A (en) | 1996-09-24 |
| JP2961063B2 JP2961063B2 (en) | 1999-10-12 |
Family
ID=12762869
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4699895A Expired - Fee Related JP2961063B2 (en) | 1995-03-07 | 1995-03-07 | Turbine vane |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2961063B2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2017172453A (en) * | 2016-03-23 | 2017-09-28 | 株式会社東芝 | Steam turbine |
| JP2019049218A (en) * | 2017-09-08 | 2019-03-28 | 三菱日立パワーシステムズ株式会社 | Seal device of steam turbine and steam turbine having the seal device |
-
1995
- 1995-03-07 JP JP4699895A patent/JP2961063B2/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2017172453A (en) * | 2016-03-23 | 2017-09-28 | 株式会社東芝 | Steam turbine |
| JP2019049218A (en) * | 2017-09-08 | 2019-03-28 | 三菱日立パワーシステムズ株式会社 | Seal device of steam turbine and steam turbine having the seal device |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2961063B2 (en) | 1999-10-12 |
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