JPH09264103A - Gas turbine stationary blade - Google Patents
Gas turbine stationary bladeInfo
- Publication number
- JPH09264103A JPH09264103A JP7390596A JP7390596A JPH09264103A JP H09264103 A JPH09264103 A JP H09264103A JP 7390596 A JP7390596 A JP 7390596A JP 7390596 A JP7390596 A JP 7390596A JP H09264103 A JPH09264103 A JP H09264103A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- passage
- gas turbine
- shroud
- air
- 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]
【発明の属する技術分野】本発明は翼内部を蒸気冷却方
式としたガスタービン静翼に於いて、静翼の内径側にロ
ータとの間の段間シールを有する構造のガスタービン静
翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine stationary blade in which the inside of the blade is of a steam cooling type and has a structure having an interstage seal with a rotor on the inner diameter side of the stationary blade.
【０００２】[0002]
【従来の技術】従来のガスタービン静翼では、翼の内部
を中空として通路を設け、その中に自分の圧縮機の吐出
空気或いは抽気を流し翼を冷却し、翼メタル温度を主流
ガス温度より低い或る許容温度に維持している。一方、
翼内部は、段間シールでエアカーテンを作るためのシー
ル用空気通路ともなっている。2. Description of the Related Art In a conventional gas turbine stationary blade, the inside of the blade is hollow to provide a passage in which air discharged from the compressor or bleed air is flowed to cool the blade, and the blade metal temperature is set lower than the mainstream gas temperature. It is maintained at some low allowable temperature. on the other hand,
The inside of the blade also serves as a sealing air passage for forming an air curtain with an interstage seal.
【０００３】また、蒸気冷却方式のガスタービン静翼で
は、従来の空気に代り翼内部に蒸気を循環させる。翼の
冷却に蒸気を用いるガスタービン静翼では、冷却に供し
た後の蒸気を主流ガス中に放出して回収しない形式も存
在するが、冷却に用いた蒸気を全量回収するのが好まし
い。Further, in a steam-cooling type gas turbine stationary blade, steam is circulated inside the blade instead of the conventional air. In a gas turbine stationary blade that uses steam for cooling the blade, there is a type in which the steam after cooling is released into the mainstream gas and is not recovered, but it is preferable to recover all the steam used for cooling.
【０００４】冷却に用いた蒸気を全量回収するために
は、内径側の段間シールにおいて低温ガスのカーテンを
作り主流ガスの洩れ込みを防ぐように、従来通り段間シ
ール用の空気を供給しなければならない。In order to recover the entire amount of steam used for cooling, air for interstage sealing is supplied as usual so that a curtain of low temperature gas is formed in the interstage seal on the inner diameter side to prevent mainstream gas from leaking. There must be.
【０００５】また、翼のトレイリングエッジは肉厚が薄
いので内部に所要面積を持った蒸気循環用通路を設ける
のが難しく、蒸気冷却方式にあっても翼壁内に翼内面か
ら主流中に貫通する穴を設けその穴に空気を流す方式を
採用することが考えられている。Further, since the trailing edge of the blade has a small wall thickness, it is difficult to provide a steam circulation passage having a required area inside. It is considered to employ a method of providing a through hole and flowing air through the hole.
【０００６】以上のように、蒸気冷却方式のガスタービ
ン静翼の翼部には、蒸気通路、トレイリングエッジ用空
気通路及び段間シール用空気通路を設けなければならな
い。As described above, the steam passage, the air passage for the trailing edge, and the air passage for the interstage seal must be provided in the blade portion of the gas turbine stationary blade.
【０００７】[0007]
【発明が解決しようとする課題】ガスタービン静翼にお
けるトレイリングエッジ冷却部は翼の出口側に直接開口
しているのに対して、段間シール用の空気は翼上流側の
圧力に対して若干正の圧力を保持しなければならないの
で、トレイリングエッジ冷却用の空気と段間シール用の
空気の両通路を共通にするのは難しい。While the trailing edge cooling section of the gas turbine stationary blade is directly open to the outlet side of the blade, the air for interstage sealing is against the pressure on the upstream side of the blade. Since it is necessary to maintain a slightly positive pressure, it is difficult to use both the trailing edge cooling air and the interstage sealing air passages in common.
【０００８】両空気通路を共通にして必要断面積を確保
しようとすると、トレイリングエッジ部分は翼厚が薄い
ので翼弦方向に長い通路としなければならず、そうする
と空気冷却を要する翼断面積が増え、更に冷却空気量を
増加しなければならなくなる。即ち、蒸気冷却の有効性
が減る。In order to secure a required cross-sectional area by using both air passages in common, the trailing edge portion has a small blade thickness, and therefore the passage must be long in the chord direction. The amount of cooling air must be increased and the amount of cooling air must be increased. That is, the effectiveness of steam cooling is reduced.
【０００９】本発明は、翼断面を中空として冷却蒸気を
流すようにしたガスタービン静翼において、トレイリン
グエッジ冷却用空気及び段間シール用空気の通路をそれ
ぞれ効果的に設けたガスタービン静翼を提供することを
課題としている。According to the present invention, in a gas turbine stationary blade having a hollow blade cross section for allowing cooling steam to flow, gas turbine stationary blades having trailing edge cooling air and interstage sealing air passages are effectively provided. The challenge is to provide.
【００１０】[0010]
【課題を解決するための手段】本発明は、前記課題を解
決するため、翼断面を中空とし、かつ、翼弦方向に複数
個の室に仕切りそれらの室を直列に接続して冷却蒸気通
路を形成したガスタービン静翼において、翼弦の中央部
の翼厚の大きい部分の一つの前記室を外側シュラウドの
外側から内側シュラウドの内径側に空気を流す段間シー
ル用空気通路とした構成を採用する。SUMMARY OF THE INVENTION In order to solve the above problems, the present invention provides a cooling steam passage in which a blade has a hollow cross section and is partitioned into a plurality of chambers in the chord direction to connect the chambers in series. In the gas turbine stationary blade having the structure described above, one of the chambers having a large blade thickness at the central portion of the chord is configured as an air passage for interstage sealing that allows air to flow from the outside of the outer shroud to the inner diameter side of the inner shroud. adopt.
【００１１】なお、本発明によるガスタービン静翼にお
いて、翼弦方向に仕切って形成した複数個の室を直列に
接続して冷却蒸気通路を形成させる上では、各室を更に
グループに分け、その各々を直列に接続して複数に分け
られた冷却蒸気通路としてもよい。In the gas turbine vane according to the present invention, in order to form a cooling steam passage by connecting a plurality of chambers formed by partitioning in the chord direction in series, each chamber is further divided into groups. Each may be connected in series to form a plurality of cooling steam passages.
【００１２】本発明によるガスタービン静翼において
は、前記した一つの室の一端をシュラウドに直接開口さ
せ、他端は冷却蒸気通路を接続する通路で蓋されると共
に翼形をシュラウドの外方に延長させその通路側面をシ
ュラウドの外側に開口させて前記段間シール用空気通路
とした構成とすることができる。In the gas turbine vane according to the present invention, one end of the above-mentioned one chamber is directly opened to the shroud, and the other end is covered with a passage connecting the cooling steam passage, and the airfoil is located outside the shroud. The air passage for the interstage sealing can be formed by extending and opening the side surface of the passage to the outside of the shroud.
【００１３】以上のように構成した本発明のガスタービ
ン静翼によれば、段間シール用空気通路は翼厚の大きい
部分に設けられるので、翼弦方向長さを短かくすること
が出来、蒸気冷却対象外の面積を最小にして段間シール
空気に対する通路を形成出来る。According to the gas turbine stationary blade of the present invention configured as described above, since the interstage sealing air passage is provided in a portion having a large blade thickness, the chord direction length can be shortened, It is possible to form the passage for the interstage sealing air by minimizing the area outside the steam cooling target.
【００１４】また、本発明のガスタービン静翼では、段
間シール用空気通路を前記したように構成することによ
って、段間シール用空気通路とトレイリングエッジのた
めの空気通路を分離出来るので、各空気通路に対して適
した空気圧力になるように通路面積を選択し、又はそこ
にオリフィスを設け供給空気を調整できる。Further, in the gas turbine vane of the present invention, the air passage for interstage sealing can be separated from the air passage for trailing edge by constructing the air passage for interstage sealing as described above. The passage area can be selected so that the air pressure is suitable for each air passage, or an orifice can be provided therein to adjust the supply air.
【００１５】[0015]
【発明の実施の形態】以下、本発明の実施の一形態によ
るガスタービン静翼について図１〜図３を用いて具体的
に説明する。このガスタービン静翼は翼形１の断面が中
空となっていて、かつ、仕切り２’によって翼弦方向に
複数個の室２、２、…に仕切られている。各室２を蛇行
状に直列に接続して冷却蒸気通路を形成し、そこに冷却
蒸気を流す翼となっている。BEST MODE FOR CARRYING OUT THE INVENTION Hereinafter, a gas turbine vane according to an embodiment of the present invention will be specifically described with reference to FIGS. In this gas turbine stationary blade, the airfoil 1 has a hollow cross section, and is partitioned into a plurality of chambers 2, 2, ... In the chord direction by a partition 2 '. The respective chambers 2 are connected in a meandering manner in series to form a cooling steam passage, which is a blade for flowing the cooling steam.
【００１６】また、翼厚の最も大きい翼弦の中央部分で
蒸気の上向と下向又は下向と上向き通路の間に段間シー
ル用空気通路３が設けられている。Further, an air passage 3 for interstage sealing is provided between the upward passage and the downward passage of the steam or the downward passage and the upward passage in the central portion of the chord having the largest blade thickness.
【００１７】シール用空気通路３の一端（下端）は直接
シュラウド面４に開口するが、他端（上端）はシール用
空気通路３を挟む両側の蒸気通路６，７によって蓋をさ
れた構造となっている。従って、この上端側は翼形１が
シュラウド５の上面に延長された構成となっていて側面
８に開口されている。One end (lower end) of the sealing air passage 3 is directly opened to the shroud surface 4, while the other end (upper end) is covered by the steam passages 6 and 7 on both sides of the sealing air passage 3. Has become. Therefore, on the upper end side, the airfoil 1 is extended to the upper surface of the shroud 5 and opened to the side surface 8.
【００１８】冷却用蒸気通路６，７及び段間シール用空
気通路３における蒸気及び空気の流れは図中に矢印で示
すとおりである。また、静翼のトレイリングエッジに
は、図１に示すようにトレイリングエッジ冷却用の空気
通路が形成されており、矢印で示すように流れる空気に
よって冷却される。The flow of steam and air in the cooling steam passages 6 and 7 and the interstage sealing air passage 3 is shown by arrows in the figure. Further, an air passage for cooling the trailing edge is formed in the trailing edge of the stationary blade as shown in FIG. 1, and is cooled by the air flowing as shown by the arrow.
【００１９】以上、本発明を図示した実施形態に基づい
て具体的に説明したが、本発明がこれらの実施形態に限
定されず特許請求の範囲に示す本発明の範囲内で、その
具体的構造、構成に種々の変更を加えてよいことはいう
までもない。The present invention has been specifically described above based on the illustrated embodiments, but the present invention is not limited to these embodiments and within the scope of the present invention as set forth in the claims, the specific structure thereof Needless to say, various modifications may be added to the configuration.
【００２０】例えば、上記実施形態では翼弦方向に複数
個に仕切って形成した室２を直列に接続して一つの冷却
蒸気通路を構成するようにしているが、各室２を更にそ
れぞれ複数個のグループに仕切り、その各々を直列に接
続して複数の冷却蒸気通路を形成してもよい。For example, in the above embodiment, the plurality of chambers 2 formed by partitioning in the chord direction are connected in series to form one cooling steam passage. May be divided into groups, and each of them may be connected in series to form a plurality of cooling steam passages.
【００２１】[0021]
【発明の効果】以上説明したように、本発明のガスター
ビン静翼によれば、冷却蒸気通路、段間シール用空気通
路、及び肉厚が薄く内部に蒸気循環通路を設け難いトレ
イリングエッジにトレイリングエッジ用空気通路をそれ
ぞれ設けることが可能となる。As described above, according to the gas turbine stationary blade of the present invention, the cooling steam passage, the interstage sealing air passage, and the trailing edge where the thickness is thin and it is difficult to provide the steam circulation passage inside the trailing edge. It is possible to provide each trailing edge air passage.
【００２２】このようにして、本発明のガスタービン静
翼では、翼内に形成した通路にそれぞれの目的の流体を
それぞれに適した圧力で供給することが出来るのでその
供給制御が容易になる。In this way, in the gas turbine stationary blade of the present invention, the respective target fluids can be supplied to the passages formed in the blade at pressures suitable for the respective passages, so that the supply control becomes easy.
【図１】本発明の実施の一形態に係るガスタービン静翼
の図で、図２のＢ−Ｂ線に沿う立断面図。1 is a view of a gas turbine vane according to an embodiment of the present invention, and is a vertical cross-sectional view taken along the line BB of FIG.
【図２】図１のＣ−Ｃ線に沿うガスタービン静翼の平断
面図。FIG. 2 is a plan sectional view of a gas turbine stationary blade taken along the line CC of FIG.
【図３】図２のＡ−Ａ線に沿うガスタービン静翼の立断
面図。3 is a vertical cross-sectional view of the gas turbine stationary blade taken along the line AA of FIG.
１ 翼形 ２ 室 ３ シール用空気通路 ４，５ シュラウド ６，７ 蒸気通路 1 Airfoil 2 Chamber 3 Sealing air passage 4,5 Shroud 6,7 Steam passage
Claims (2)
数個の室に仕切りそれらの室を直列に接続して冷却蒸気
通路を形成すると共に、翼弦の中央部の翼厚の大きい部
分の一つの前記室を外側シュラウドの外側から内側シュ
ラウドの内径側に空気を流す段間シール用空気通路とし
たことを特徴とするガスタービン静翼。1. A cooling blade having a hollow blade cross section and partitioning into a plurality of chambers in the chord direction in series to form a cooling steam passage and having a large blade thickness at the central portion of the chord. A gas turbine stationary blade, wherein one of the chambers of the portion is an air passage for interstage sealing that allows air to flow from the outside of the outer shroud to the inner diameter side of the inner shroud.
開口させ、他端は前記冷却蒸気通路を接続する通路で蓋
されると共に翼形をシュラウドの外方に延長させその通
路側面をシュラウドの外側に開口させて前記段間シール
用空気通路とした請求項１記載のガスタービン静翼。2. One end of the one chamber is directly opened to the shroud, the other end is covered with a passage connecting the cooling steam passage, and the airfoil is extended to the outside of the shroud, and the passage side surface of the shroud is formed. The gas turbine stationary blade according to claim 1, wherein the gas turbine stationary blade is opened to the outside to form the interstage sealing air passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP07390596A JP3150610B2 (en) | 1996-03-28 | 1996-03-28 | Gas turbine vane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP07390596A JP3150610B2 (en) | 1996-03-28 | 1996-03-28 | Gas turbine vane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH09264103A true JPH09264103A (en) | 1997-10-07 |
| JP3150610B2 JP3150610B2 (en) | 2001-03-26 |
Family
ID=13531681
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP07390596A Expired - Fee Related JP3150610B2 (en) | 1996-03-28 | 1996-03-28 | Gas turbine vane |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3150610B2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1999036675A1 (en) * | 1996-07-19 | 1999-07-22 | Mitsubishi Heavy Industries, Ltd. | Stationary blade of gas turbine |
| DE19926949A1 (en) * | 1999-06-14 | 2000-12-21 | Abb Alstom Power Ch Ag | Cooling arrangement for blades of gas turbine etc. has blades combined into groups with connected flow channels to form continuous coolant channel for cooling steam |
| US6315518B1 (en) | 1998-01-20 | 2001-11-13 | Mitsubishi Heavy Industries, Ltd. | Stationary blade of gas turbine |
-
1996
- 1996-03-28 JP JP07390596A patent/JP3150610B2/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1999036675A1 (en) * | 1996-07-19 | 1999-07-22 | Mitsubishi Heavy Industries, Ltd. | Stationary blade of gas turbine |
| US6315518B1 (en) | 1998-01-20 | 2001-11-13 | Mitsubishi Heavy Industries, Ltd. | Stationary blade of gas turbine |
| DE19880989C2 (en) * | 1998-01-20 | 2002-01-24 | Mitsubishi Heavy Ind Ltd | Stationary blade of a gas turbine |
| DE19926949A1 (en) * | 1999-06-14 | 2000-12-21 | Abb Alstom Power Ch Ag | Cooling arrangement for blades of gas turbine etc. has blades combined into groups with connected flow channels to form continuous coolant channel for cooling steam |
| US6422811B1 (en) | 1999-06-14 | 2002-07-23 | Alstom (Switzerland) Ltd | Cooling arrangement for blades of a gas turbine |
| DE19926949B4 (en) * | 1999-06-14 | 2011-01-05 | Alstom | Cooling arrangement for blades of a gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3150610B2 (en) | 2001-03-26 |
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