JPH10325301A - Cooling blade of gas turbine - Google Patents
Cooling blade of gas turbineInfo
- Publication number
- JPH10325301A JPH10325301A JP13845597A JP13845597A JPH10325301A JP H10325301 A JPH10325301 A JP H10325301A JP 13845597 A JP13845597 A JP 13845597A JP 13845597 A JP13845597 A JP 13845597A JP H10325301 A JPH10325301 A JP H10325301A
- Authority
- JP
- Japan
- Prior art keywords
- partition wall
- flow path
- cooling medium
- blade
- serpentine flow
- 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、火力発電などに適
用されるガスタービンの冷却翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine cooling blade applied to thermal power generation and the like.
【０００２】[0002]
【従来の技術】図２および図３は火力発電などに使用さ
れている従来のガスタービンの冷却動翼の説明図であ
る。図２において、本ガスタービンの冷却動翼はサーペ
ンタイン方式が採用されており、冷却媒体の空気、或い
は蒸気が翼根５１の冷却媒体の入口５２から翼根５１内
に入り、翼５３のサーペンタイン流路５４ａを矢印で示
す方向に流れて翼５３の前縁を冷却した後、翼頂部で仕
切壁５８に沿って反転（リターン）して翼５３の中央部
を冷却する。そして、翼台５５で再び仕切壁５８に沿っ
て反転し、最終のサーペンタイン流路５４ｂを通って翼
５３の後縁を冷却した後、翼根５１の冷却媒体の出口５
６から流出するようになっている。2. Description of the Related Art FIGS. 2 and 3 are explanatory views of a cooling blade of a conventional gas turbine used for thermal power generation or the like. In FIG. 2, the cooling blade of the present gas turbine employs a serpentine method, in which air or steam of the cooling medium enters the blade root 51 from the cooling medium inlet 52 of the blade root 51, and the serpentine flow of the blade 53. After flowing along the path 54a in the direction indicated by the arrow to cool the leading edge of the wing 53, the wing top is reversed (returned) along the partition wall 58 to cool the central part of the wing 53. Then, the blades 55 are again inverted along the partition wall 58 by the platform 55 to cool the trailing edge of the blade 53 through the final serpentine flow path 54b, and then the cooling medium outlet 5 of the blade root 51
6 to flow out.
【０００３】図３において、サーペンタイン流路５４
ａ，５４ｂにはサーペンタイン流路５４ａ，５４ｂに対
して水平に、或いは図に示すように外周側に傾斜した複
数列のタービュレータ５７が設けられており、タービュ
レータ５７の下流および上流には渦が発生し、この渦に
誘導されて冷却媒体の空気、或いは蒸気の流れが層流か
ら乱流に転じ、擾乱が発生する。これらの渦の端は流体
中で互いに繋がるか、或いは境界面で終わっており、流
れは個所Ａで流路壁に再付着するが、熱伝達率はタービ
ュレータ５７後流の渦域で急激に低下し、再付着以降で
上昇する。In FIG. 3, a serpentine channel 54
The turbulators 57 a and 54 b are provided with a plurality of rows of turbulators 57 that are inclined with respect to the serpentine flow paths 54 a and 54 b or on the outer peripheral side as shown in the figure, and vortices are generated downstream and upstream of the turbulator 57. Then, the flow of the cooling medium air or steam is changed from laminar to turbulent by being guided by the vortex, and disturbance is generated. The ends of these vortices are connected to each other in the fluid or terminate at the interface, and the flow reattaches to the channel wall at point A, but the heat transfer coefficient drops sharply in the vortex region downstream of the turbulator 57. And rises after reattachment.
【０００４】このようにサーペンタイン流路５４ａ，５
４ｂにタービュレータ５７を設けることにより、サーペ
ンタイン流路５４ａ，５４ｂを流れる冷却媒体の空気、
或いは蒸気に対する抵抗は増すが、冷却媒体の流れを強
制的に乱流に遷移させるとともに、冷却通路と交叉する
方向の二次流れを発生させ、サーペンタイン流路５４
ａ，５４ｂにおける熱伝達率を向上させて冷却効果を増
大させる。Thus, the serpentine flow paths 54a, 54
By providing the turbulator 57 in the 4b, the air of the cooling medium flowing through the serpentine channels 54a and 54b,
Alternatively, although the resistance to steam increases, the flow of the cooling medium is forcibly changed to a turbulent flow, and a secondary flow is generated in a direction intersecting with the cooling passage, so that the serpentine flow path 54
a, 54b to improve the heat transfer coefficient to increase the cooling effect.
【０００５】[0005]
【発明が解決しようとする課題】上記のように、従来の
ガスタービンの冷却動翼においては複数列のタービュレ
ータ５７がサーペンタイン流路５４ａ，５４ｂに対して
水平に、或いは外周側に傾斜して設けられており、この
ようにサーペンタイン流路５４ａ，５４ｂにタービュレ
ータ５７を設けることにより、サーペンタイン流路５４
ａ，５４ｂを流れる冷却媒体に対する抵抗が増す。As described above, in a conventional cooling blade of a gas turbine, a plurality of rows of turbulators 57 are provided horizontally with respect to the serpentine flow paths 54a and 54b, or inclined at the outer peripheral side. By providing the turbulator 57 in the serpentine flow passages 54a and 54b in this way, the serpentine flow passage 54a
a, the resistance to the cooling medium flowing through 54b is increased.
【０００６】また、冷却媒体の流れが翼頂部、或いは翼
台５５で反転した後に冷却媒体の流れに剥離が生じるた
め、サーペンタイン流路５４ａ，５４ｂにおけるＣ域に
比べてＢ域における熱伝達量が小さく、局所的に冷却性
能が衰えることにより冷却効果に大きな差を生じてい
る。Further, since the flow of the cooling medium is separated after the flow of the cooling medium is reversed at the blade top or the wing base 55, the heat transfer amount in the B region is smaller than that in the C region in the serpentine flow paths 54a and 54b. A small difference in the cooling effect is caused by the small and local deterioration of the cooling performance.
【０００７】[0007]
【課題を解決するための手段】本発明に係るガスタービ
ンの冷却翼は上記課題の解決を目的にしており、翼内部
に仕切壁によりＵ字状に仕切られて冷却媒体が流れるサ
ーペンタイン流路を備えたガスタービンの冷却翼におけ
る上記サーペンタイン流路の少なくとも上記仕切壁によ
り仕切られたＵターン部下流の内壁に冷却媒体の流れに
対して上記仕切壁側に傾斜した第一のタービュレータが
上記サーペンタイン流路の全幅にわたって設けられると
ともに、上記第一のタービュレータよりも短い第二のタ
ービュレータが上記第一のタービュレータと同様に傾斜
し上記仕切壁に当接して設けられている。SUMMARY OF THE INVENTION An object of the present invention is to provide a cooling blade for a gas turbine according to the present invention, in which a serpentine flow path in which a cooling medium flows is formed by being partitioned into a U-shape by a partition wall inside the blade. A first turbulator inclined to the partition wall side with respect to the flow of the cooling medium at least on the inner wall downstream of the U-turn section of the serpentine flow path in the cooling blade of the gas turbine provided with the partition wall by the partition wall is provided with the serpentine flow. A second turbulator, which is provided over the entire width of the road and is shorter than the first turbulator, is provided in contact with the partition wall inclining in the same manner as the first turbulator.
【０００８】このように、本発明に係るガスタービンの
冷却翼においては、サーペンタイン流路におけるＵター
ン部下流に内周の仕切壁側に傾斜を有しサーペンタイン
流路幅の全幅にわたるように配設された第一のタービュ
レータと、この第一のタービュレータと同様に傾斜し仕
切壁に当接して配設され第一のタービュレータよりも短
い第二のタービュレータとが設けられており、特に剥離
を生じ易いサーペンタイン流路のＵターン部下流に内周
側に傾斜した第一のタービュレータをサーペンタイン流
路の全幅にわたって配設したことによって冷却媒体の流
れがＵターンした後にサーペンタイン流路の仕切壁側
（内周側）に案内され、仕切壁の内周側における冷却媒
体の流れの剥離が生じ難くなる。As described above, in the cooling blade of the gas turbine according to the present invention, the serpentine flow path is disposed downstream of the U-turn portion on the inner peripheral partition wall side so as to extend over the entire width of the serpentine flow path. The first turbulator, and a second turbulator which is disposed in such a manner as to be inclined and abutted on the partition wall and is shorter than the first turbulator, similarly to the first turbulator, is provided, and in particular, the peeling easily occurs. By disposing a first turbulator inclined to the inner peripheral side downstream of the U-turn part of the serpentine flow path over the entire width of the serpentine flow path, the flow of the cooling medium makes a U-turn, so that the partition wall side of the serpentine flow path (inner circumference) Side), and the separation of the flow of the cooling medium on the inner peripheral side of the partition wall hardly occurs.
【０００９】また、特に剥離を生じ易いサーペンタイン
流路のＵターン部下流に短い第二のタービュレータを内
周側に傾斜させ仕切壁に当接して配設したことによって
冷却媒体の流れがＵターンした後にサーペンタイン流路
の仕切壁側（内周側）に案内され、サーペンタイン流路
における冷却媒体の流れに対する抵抗を増すことなく、
仕切壁の内周側における冷却媒体の流れの剥離がより一
層生じ難くなる。In addition, the flow of the cooling medium is U-turned by arranging a short second turbulator at the downstream side of the U-turn portion of the serpentine flow passage, which is liable to cause separation, inclining inward and abutting against the partition wall. Later, it is guided to the partition wall side (inner peripheral side) of the serpentine flow path, without increasing the resistance to the flow of the cooling medium in the serpentine flow path,
Separation of the flow of the cooling medium on the inner peripheral side of the partition wall is more unlikely to occur.
【００１０】[0010]
【発明の実施の形態】図１は本発明の実施の一形態に係
るガスタービンの冷却動翼の説明図である。図におい
て、本実施の形態に係るガスタービンの冷却動翼は火力
発電などに使用されるガスタービンの冷却動翼で、サー
ペンタイン流路にタービュレータを配列する場合の配列
方向やタービュレータの構造などを改良している。図に
おける符号１はサーペンタイン流路、２は仕切壁、３は
サーペンタイン流路の全幅にわたるタービュレータ、４
はサーペンタイン流路幅の半分程度の短いタービュレー
タ（案内用突起）、５はガスタービンの翼である。FIG. 1 is an explanatory view of a cooling blade of a gas turbine according to an embodiment of the present invention. In the figure, the cooling blade of the gas turbine according to the present embodiment is a cooling blade of a gas turbine used for thermal power generation and the like, and the arrangement direction and the structure of the turbulator are improved when turbulators are arranged in a serpentine flow path. doing. In the figure, reference numeral 1 denotes a serpentine flow path, 2 denotes a partition wall, 3 denotes a turbulator extending over the entire width of the serpentine flow path, 4
Is a turbulator (guide protrusion) that is about half the serpentine flow path width, and 5 is a gas turbine blade.
【００１１】本ガスタービンの冷却動翼は図に示すよう
にサーペンタイン方式が採用されており、従来例のガス
タービンの冷却動翼と同様に冷却媒体の空気、或いは蒸
気が翼根の冷却媒体の入口から翼根内に入り、翼５のサ
ーペンタイン流路１を矢印で示す方向に流れて翼５の前
縁を冷却した後、翼頂部で仕切壁２に沿って反転（リタ
ーン）して翼５の中央部を冷却する。そして、翼台で再
び仕切壁２に沿って反転し、最終のサーペンタイン流路
１を通って翼５の後縁を冷却した後、翼根の冷却媒体の
出口から流出するようになっている。As shown in the figure, the cooling blade of the gas turbine employs a serpentine system, and the air or steam of the cooling medium is used as the cooling blade of the blade root similarly to the cooling blade of the conventional gas turbine. After entering the blade root from the inlet and flowing through the serpentine flow path 1 of the blade 5 in the direction shown by the arrow to cool the leading edge of the blade 5, the blade 5 is reversed (returned) along the partition wall 2 at the blade top to return to the blade 5. Cool the center of the. Then, the blade is again inverted along the partition wall 2 by the platform, and after cooling the trailing edge of the blade 5 through the final serpentine flow path 1, flows out from the outlet of the cooling medium of the blade root.
【００１２】また、本ガスタービンの冷却動翼において
は図に示すように、サーペンタイン流路１には仕切壁２
によってリターン部が形成されており、仕切壁２側（内
周側）に下がるように傾斜したタービュレータ３がサー
ペンタイン流路１の全幅にわたって配設されている。そ
して、このサーペンタイン流路１の全幅にわたるタービ
ュレータ３とタービュレータ３との間に、サーペンタイ
ン流路１流路幅の半分程度の短いタービュレータ４が同
様に仕切壁２側（内周側）に下がるように傾斜し仕切壁
２に当接して配設されている。As shown in the drawing, the cooling blade of the gas turbine has a partition wall 2 in the serpentine flow path 1.
A turbulator 3 inclined so as to descend toward the partition wall 2 (inner peripheral side) is provided over the entire width of the serpentine flow path 1. Then, between the turbulator 3 and the turbulator 3 over the entire width of the serpentine flow path 1, the turbulator 4 as short as about half the width of the serpentine flow path 1 is similarly lowered to the partition wall 2 side (inner peripheral side). It is inclined and disposed in contact with the partition wall 2.
【００１３】このようにサーペンタイサーペンタイン流
路１に複数列のタービュレータ３を設けることにより、
タービュレータ３の下流および上流に渦が発生し、この
渦に誘導されて冷却媒体の空気、或いは蒸気の流れを層
流から強制的に乱流に遷移させて擾乱を発生させるとと
もに、冷却通路と交叉する方向の二次流れを発生させ、
サーペンタイン流路１における熱伝達率を向上させて冷
却効果を増大させる。また、本ガスタービンの冷却翼に
おいてはサーペンタイン流路１のリターン部にタービュ
レータ３がサーペンタイン流路１の内周側に下がるよう
に傾斜を有しサーペンタイン流路１流路幅の全幅にわた
るように配列され、このタービュレータ３とタービュレ
ータ３との間に内周側に下がるように傾斜を有しサーペ
ンタイン流路１流路幅の半分程度の短いタービュレータ
４が仕切壁２に当接して配列されており、従来のサーペ
ンタイン流路においては冷却媒体の流れがサーペンタイ
ン流路１のリターン部で外周側に案内されてしまうため
に仕切壁２近傍の内周側で剥離が生じて著しく伝熱性能
が損われるが、本ガスタービンの冷却翼においては内周
側に下がるように傾斜したタービュレータ３がサーペン
タイン流路１の全幅にわたって配列されていることによ
り、このタービュレータ３によって冷却媒体の流れが仕
切壁２側に案内され、仕切壁２の内周側における冷却媒
体の流れの剥離が生じ難くなって伝熱性能が向上すると
ともに剥離が生じ易いリターン後の仕切壁２部分の伝熱
性能が向上する。また、サーペンタイン流路１の全幅に
わたるタービュレータ３とタービュレータ３との間に同
様に内周側に下がるように傾斜しサーペンタイン流路１
の全幅にはわたらない短いタービュレータ４が配列され
ていることにより、この短いタービュレータ４によって
冷却媒体の流れが仕切壁２側に案内され、サーペンタイ
ン流路１における冷却媒体の流れに対する抵抗を増すこ
となく、仕切壁２の内周側における冷却媒体の流れの剥
離がより一層生じ難くなり、伝熱性能が向上するととも
に剥離が生じ易いリターン後の仕切壁２部分の伝熱性能
が向上する。By providing a plurality of rows of turbulators 3 in the serpentine serpentine flow path 1 as described above,
Vortices are generated downstream and upstream of the turbulator 3, and are induced by the vortices to forcibly transition the flow of the air or steam of the cooling medium from laminar flow to turbulent flow to generate turbulence and cross the cooling passage. A secondary flow in the direction of
The heat transfer coefficient in the serpentine flow path 1 is improved to increase the cooling effect. Further, in the cooling blade of the present gas turbine, the turbulators 3 are inclined at the return portion of the serpentine flow path 1 so as to descend to the inner peripheral side of the serpentine flow path 1 and are arranged so as to cover the entire width of the serpentine flow path 1. A turbulator 4 having a slope and being about half the width of the serpentine flow path 1 and having a slope descending to the inner peripheral side between the turbulators 3 and 3 is arranged in contact with the partition wall 2, In the conventional serpentine flow path, since the flow of the cooling medium is guided to the outer peripheral side at the return portion of the serpentine flow path 1, separation occurs on the inner peripheral side near the partition wall 2 and heat transfer performance is significantly impaired. In the cooling blades of the present gas turbine, turbulators 3 inclined so as to descend to the inner peripheral side are arranged over the entire width of the serpentine flow path 1. As a result, the flow of the cooling medium is guided toward the partition wall 2 by the turbulator 3, and the separation of the flow of the cooling medium on the inner peripheral side of the partition wall 2 hardly occurs, so that the heat transfer performance is improved and the separation occurs. The heat transfer performance of the partition wall 2 after return is improved. Similarly, the serpentine flow path 1 is inclined between the turbulators 3 over the entire width of the serpentine flow path 1 so as to descend to the inner peripheral side.
Are arranged so that the flow of the cooling medium is guided toward the partition wall 2 without increasing the resistance to the flow of the cooling medium in the serpentine flow path 1. In addition, the separation of the flow of the cooling medium on the inner peripheral side of the partition wall 2 is more unlikely to occur, and the heat transfer performance is improved, and the heat transfer performance of the part of the partition wall 2 after the return where the separation easily occurs is improved.
【００１４】従来のガスタービンの冷却動翼において
は、複数列のタービュレータがサーペンタイン流路に対
して水平に、或いは外周側に傾斜して設けられており、
このようにサーペンタイン流路にタービュレータを設け
ることにより、サーペンタイン流路を流れる冷却媒体に
対する抵抗が増す。また、冷却媒体の流れが翼頂部、或
いは翼台で反転した後に冷却媒体の流れに剥離が生じる
ため、局所的に冷却性能が衰えることにより冷却効果に
大きな差を生じている。なお、このような現象は既に様
々な文献などで報告されている。In a conventional cooling blade of a gas turbine, a plurality of rows of turbulators are provided horizontally with respect to a serpentine flow path or inclined at an outer peripheral side.
By providing the turbulator in the serpentine flow path as described above, resistance to the cooling medium flowing through the serpentine flow path is increased. In addition, since the flow of the cooling medium is separated after the flow of the cooling medium is reversed at the blade top or the platform, the cooling performance is locally deteriorated, so that the cooling effect has a large difference. Such a phenomenon has already been reported in various documents.
【００１５】これに対し、本ガスタービンの冷却動翼に
おいては、このような問題点を解消するためにサーペン
タイン流路１のリターン部に内周側に下がる傾斜を有し
サーペンタイン流路１の全幅にわたるようにタービュレ
ータ３を配列するとともに、このタービュレータ３とタ
ービュレータ３との間に内周側に下がる傾斜を有しサー
ペンタイン流路１流路幅の半分程度の短いタービュレー
タ４を仕切壁２に当接して配列している。On the other hand, in the cooling blade of the present gas turbine, in order to solve such a problem, the return portion of the serpentine flow path 1 has a slope which is inclined toward the inner peripheral side and has a full width of the serpentine flow path 1. The turbulators 3 are arranged so as to extend over the turbulators 3, and the turbulators 4 having a slope which is inclined downward to the inner peripheral side between the turbulators 3 and the turbulators 3 and which are about half the width of the serpentine flow path 1 are brought into contact with the partition wall 2. They are arranged.
【００１６】このように、特に剥離を生じ易いサーペン
タイン流路１のリターン部に、タービュレータ３を内周
側に下がる傾斜でサーペンタイン流路１の全幅にわたる
ように配列したことにより、仕切壁２に沿って反転した
冷却媒体の流れがサーペンタイン流路１の仕切壁２側
（内周側）に案内されてサーペンタイン流路のＵターン
部下流に剥離が生じ難くなり、伝熱性能の不均一が解消
されて伝熱性能が向上する。As described above, the turbulators 3 are arranged on the return portion of the serpentine flow path 1 where the peeling is particularly likely to occur, so as to extend over the entire width of the serpentine flow path 1 with an inclination descending toward the inner peripheral side. The reversed flow of the cooling medium is guided to the partition wall 2 side (inner peripheral side) of the serpentine flow path 1, so that separation is less likely to occur downstream of the U-turn portion of the serpentine flow path, and uneven heat transfer performance is eliminated. The heat transfer performance is improved.
【００１７】また、特に剥離を生じ易いサーペンタイン
流路１のリターン部に、サーペンタイン流路１全幅の半
分程度の短いタービュレータ４を内周側に下がる傾斜で
仕切壁２に当接して配列したことにより、仕切壁２に沿
って反転した冷却媒体の流れがサーペンタイン流路１の
仕切壁２側（内周側）に案内され、サーペンタイン流路
１における冷却媒体の流れに対する抵抗を増すことな
く、サーペンタイン流路１のＵターン部下流に剥離がよ
り一層生じ難くなり、サーペンタイン流路１の仕切壁２
によるＵターン部下流における伝熱性能の不均一が解消
されて伝熱性能が向上する。In addition, a turbulator 4 having a length of about half of the entire width of the serpentine flow path 1 is arranged at the return portion of the serpentine flow path 1 where the separation is liable to occur, in contact with the partition wall 2 at an inclination falling to the inner peripheral side. The flow of the cooling medium reversed along the partition wall 2 is guided to the partition wall 2 side (inner peripheral side) of the serpentine flow path 1, and the flow of the serpentine flow is increased without increasing the resistance to the flow of the cooling medium in the serpentine flow path 1. Separation is more unlikely to occur downstream of the U-turn portion of the path 1, and the partition wall 2 of the serpentine flow path 1
As a result, the unevenness of the heat transfer performance downstream of the U-turn portion is eliminated, and the heat transfer performance is improved.
【００１８】これらにより、特に剥離が生じ易いリター
ン部における伝熱性能の不均一が解消されてサーペンタ
イン流路１の全領域でより一層均一な伝熱性能が得ら
れ、ガスタービンの翼５における冷却性能が向上する。Thus, unevenness of the heat transfer performance in the return portion where the peeling is particularly likely to be eliminated, and more uniform heat transfer performance can be obtained in the entire area of the serpentine flow path 1, and cooling in the gas turbine blades 5 can be achieved. Performance is improved.
【００１９】[0019]
【発明の効果】本発明に係るガスタービンの冷却翼は前
記のように構成されており、サーペンタイン流路におけ
る冷却媒体の流れに対する抵抗を増すことなく、仕切壁
の内周側における冷却媒体の流れの剥離がより一層生じ
難くなるので、サーペンタイン流路における伝熱性能の
不均一が解消されてサーペンタイン流路の全領域で均一
な伝熱性能が得られ、これによりガスタービンの冷却翼
における冷却性能が向上する。The cooling blade of the gas turbine according to the present invention is constructed as described above, and the flow of the cooling medium on the inner peripheral side of the partition wall is increased without increasing the resistance to the flow of the cooling medium in the serpentine flow path. Since it is more difficult for peeling to occur, uneven heat transfer performance in the serpentine flow path is eliminated, and uniform heat transfer performance is obtained in the entire area of the serpentine flow path. Is improved.
【図１】図１は本発明の実施の一形態に係るガスタービ
ンの冷却動翼におけるタービュレータの模式図である。FIG. 1 is a schematic diagram of a turbulator in a cooling blade of a gas turbine according to an embodiment of the present invention.
【図２】図２は従来のガスタービンの冷却動翼の斜視図
である。FIG. 2 is a perspective view of a cooling blade of a conventional gas turbine.
【図３】図３（ａ）はそのタービュレータの断面図、同
図（ｂ）はその作用説明図、同図（ｃ）はその模式図で
ある。3A is a cross-sectional view of the turbulator, FIG. 3B is an explanatory view of its operation, and FIG. 3C is a schematic view thereof.
１ サーペンタイン流路 ２ 仕切壁 ３ サーペンタイン流路の全幅にわたるタービュレータ ４ 短いタービュレータ（案内用突起） ５ 翼 DESCRIPTION OF SYMBOLS 1 Serpentine flow path 2 Partition wall 3 Turbulator over the full width of serpentine flow path 4 Short turbulator (guide protrusion) 5 Wing
Claims (1)
て冷却媒体が流れるサーペンタイン流路を備えたガスタ
ービンの冷却翼において、上記サーペンタイン流路の少
なくとも上記仕切壁により仕切られたＵターン部下流の
内壁に冷却媒体の流れに対して上記仕切壁側に傾斜し上
記サーペンタイン流路の全幅にわたって設けられた第一
のタービュレータと、該第一のタービュレータよりも短
く上記第一のタービュレータと同様に傾斜し上記仕切壁
に当接して設けられた第二のタービュレータとを備えた
ことを特徴とするガスタービンの冷却翼。In a cooling blade of a gas turbine provided with a serpentine flow path through which a cooling medium flows by being partitioned in a U-shape by a partition wall inside a blade, a U-turn partitioned by at least the partition wall of the serpentine flow path. A first turbulator which is inclined toward the partition wall side with respect to the flow of the cooling medium on the inner wall downstream of the part and is provided over the entire width of the serpentine flow path, similar to the first turbulator which is shorter than the first turbulator and shorter than the first turbulator. And a second turbulator provided so as to be inclined and abutted on the partition wall.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP13845597A JP3790328B2 (en) | 1997-05-28 | 1997-05-28 | Gas turbine cooling blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP13845597A JP3790328B2 (en) | 1997-05-28 | 1997-05-28 | Gas turbine cooling blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH10325301A true JPH10325301A (en) | 1998-12-08 |
| JP3790328B2 JP3790328B2 (en) | 2006-06-28 |
Family
ID=15222423
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP13845597A Expired - Lifetime JP3790328B2 (en) | 1997-05-28 | 1997-05-28 | Gas turbine cooling blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3790328B2 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001234702A (en) * | 1999-12-18 | 2001-08-31 | General Electric Co <Ge> | Coriolis turbulator moving blade |
| US8556583B2 (en) | 2007-08-30 | 2013-10-15 | Mitsubishi Heavy Industries, Ltd. | Blade cooling structure of gas turbine |
| KR101405014B1 (en) * | 2012-07-25 | 2014-06-10 | 연세대학교 산학협력단 | Cooling pipe |
-
1997
- 1997-05-28 JP JP13845597A patent/JP3790328B2/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001234702A (en) * | 1999-12-18 | 2001-08-31 | General Electric Co <Ge> | Coriolis turbulator moving blade |
| US8556583B2 (en) | 2007-08-30 | 2013-10-15 | Mitsubishi Heavy Industries, Ltd. | Blade cooling structure of gas turbine |
| KR101405014B1 (en) * | 2012-07-25 | 2014-06-10 | 연세대학교 산학협력단 | Cooling pipe |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3790328B2 (en) | 2006-06-28 |
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