JPH06185301A - Blade of turbine - Google Patents
Blade of turbineInfo
- Publication number
- JPH06185301A JPH06185301A JP20228793A JP20228793A JPH06185301A JP H06185301 A JPH06185301 A JP H06185301A JP 20228793 A JP20228793 A JP 20228793A JP 20228793 A JP20228793 A JP 20228793A JP H06185301 A JPH06185301 A JP H06185301A
- Authority
- JP
- Japan
- Prior art keywords
- blade
- cooling
- cooling fluid
- height direction
- main body
- 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
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、タービンの翼に係り、
特に工業用タービン・エンジンの第１段に使用されるよ
うな冷却を必要とするタービンの翼に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine blade,
In particular, it relates to turbine blades requiring cooling such as those used in the first stage of industrial turbine engines.
【０００２】[0002]
【従来の技術】タービン・エンジン等では、一般に、燃
焼するガスによって駆動されるタービン自身が、燃焼器
へ空気を供給する送風機又は圧縮機を駆動する、自力的
駆動方式が採用されている。かかるタービンの出力効率
を高めるために、最も有効な方法は、タービン入口にお
ける燃焼ガス温度を高めることであるが、上記温度はタ
ービンの翼を構成する材料の耐熱応力性あるいは高温酸
化・腐食等に耐える能力により制限される。2. Description of the Related Art In turbine engines and the like, generally, a self-driven system is adopted in which a turbine itself driven by burning gas drives a blower or a compressor which supplies air to a combustor. In order to increase the output efficiency of such a turbine, the most effective method is to raise the combustion gas temperature at the turbine inlet, but the above temperature may cause heat stress resistance or high temperature oxidation / corrosion of the material forming the blades of the turbine. Limited by your ability to withstand.
【０００３】そこで、従来は翼の内部に冷却流体を通流
させる流路を備えた対流式のタービンの翼が用いられて
いる。しかし、この対流式のタービンの翼にあっては、
所定のタービン入口ガス温度に対して、タービン翼の温
度を許容値以内に保つために使用する冷却流体の量が過
大であり、満足できるものではなかった。すなわち、冷
却流体の量が多いと、翼の温度は明らかに低下するが、
逆に、翼の空力損失が増大し、またタービン出力効率も
低下する。このため、少ない冷却流体で翼を良好に冷却
できるものの出現が望まれているのが実状である。Therefore, conventionally, a blade of a convection type turbine having a passage for allowing a cooling fluid to flow inside the blade has been used. However, in the blade of this convection type turbine,
For a given turbine inlet gas temperature, the amount of cooling fluid used to keep the temperature of the turbine blades within an allowable value is too large, which is not satisfactory. That is, if the amount of cooling fluid is large, the blade temperature will obviously decrease,
On the contrary, the aerodynamic loss of the blade increases and the turbine output efficiency also decreases. Therefore, in reality, it is desired to develop a blade that can cool the blade well with a small amount of cooling fluid.
【０００４】[0004]
【発明が解決しようとする課題】そこで本発明は、ター
ビン出力を低下させることのない量の冷却流体を使って
翼の各部を良好に冷却でき、また比較的安価に製造可能
なタービンの翼を提供することを目的としている。SUMMARY OF THE INVENTION Therefore, the present invention provides a turbine blade that can be satisfactorily cooled with a cooling fluid in an amount that does not reduce the turbine output, and that can be manufactured at a relatively low cost. It is intended to be provided.
【０００５】[0005]
【課題を解決するための手段】上記目的を達成するため
に、本発明は、翼根部の基端部に入口を有するとともに
上記入口から翼根部の内部および翼本体の内部を経由し
て翼外に通じる冷却流路を備え、上記入口を冷却流体供
給部に接続するようにしたタービンの翼において、翼前
縁部内に設けられ、主として冷却流体を前記翼根部の内
部および前記翼本体の内部に翼の高さ方向に沿って形成
された経路で導く流路および上記流路に案内された冷却
流体を上記翼本体の外部へ排出させる排出孔を備えてな
る第１の冷却流路と、この第１の冷却流路とは独立して
翼中間部内に設けられ、主として冷却流体を前記翼根部
の内部および前記翼本体の内部に翼の高さ方向に沿って
形成された経路で導いた後に上記翼本体の高さ方向先端
部近傍で上記翼本体の前縁部側回りにリターンさせて上
記翼本体の基端部近傍まで案内し、さらに上記基端部近
傍から上記翼本体の前縁部側回りにリターンさせて上記
翼本体の高さ方向先端部近傍まで案内する屈折流路およ
び上記屈折流路の少なくとも最下流領域に案内された冷
却流体を上記翼本体の外部へ排出させる排出孔を備えて
なる第２の冷却流路と、この第２の冷却流路および前記
第１の冷却流路とは独立に翼後縁部内に設けられ、主と
して冷却流体を前記翼根部の内部および前記翼本体の内
部に翼の高さ方向に沿って形成された経路で導く流路お
よび上記流路に案内された冷却流体を上記翼本体の後縁
から外部へ排出させる流路を備えてなる第３の冷却流路
とを設けたことを特徴としている。In order to achieve the above object, the present invention has an inlet at the base end portion of a blade root portion and an outside of the blade from the inlet through the inside of the blade root portion and the inside of the blade body. In a blade of a turbine, which is provided with a cooling flow path leading to a cooling fluid supply part, the cooling fluid is mainly provided inside the blade root part and inside the blade main body. A first cooling flow path having a flow path formed by a path formed along the height direction of the blade and a discharge hole for discharging the cooling fluid guided in the flow path to the outside of the blade main body; After being provided in the blade middle part independently of the first cooling flow path, after mainly guiding the cooling fluid through a path formed along the height direction of the blade inside the blade root and inside the blade body. In the vicinity of the height direction tip of the wing body, To the vicinity of the base end portion of the wing body, and then return to the vicinity of the base end portion of the wing body from the vicinity of the base end portion of the wing body to the tip in the height direction of the wing body. A second cooling flow passage having a refraction flow passage for guiding the vicinity of the blade and a discharge hole for discharging the cooling fluid guided at least in the most downstream region of the refraction flow passage to the outside of the blade body; Is provided in the blade trailing edge portion independently of the cooling passage and the first cooling passage, and a cooling fluid is mainly formed inside the blade root portion and inside the blade body along the height direction of the blade. And a third cooling flow path having a flow path for guiding the cooling fluid guided to the flow path to the outside from the trailing edge of the blade body.
【０００６】[0006]
【作用】第１，第２，第３つの冷却流路は、翼内におい
て完全に独立している。このため、各冷却流路への冷却
流体供給圧力を一定とした場合、従来の翼のように１つ
あるいは２つの内部流路だけを設けたものに較べて冷却
流体の流速が増加する。この結果、対流による冷却効果
が向上し、結果的に冷却流体の供給圧力を低下でき、冷
却流体の量の減少化が可能となり、空力損失の減少化な
らびに効率の向上化に寄与できる。また、３つの冷却流
路が完全に独立しているので、各冷却流路内の圧力が互
いに干渉することがなく、各冷却通路に設定通りの冷却
流体を通流させることが可能となり、最少の流量で最大
の冷却効果を発揮させることが可能となる。また、第２
の冷却流路では、翼中間部領域内の後縁部から翼中間部
領域内の前縁部に向けて屈折しながら延びる流路構成と
なっているので、翼中間部領域内の後縁部を延びる流路
部分からフイルム冷却用の排出孔を介して翼中間部領域
の後縁部外面に冷却流体を噴出させてフイルム冷却する
ようにすると、翼の形状に起因する特性から翼中間部領
域の後縁部を良好に冷却できる。したがって、第２の冷
却流路を流れる冷却流体が第２の冷却流路の後流域に達
するまでに温度上昇してしまうのを防止でき、この結
果、少ない量の冷却流体で翼中間部領域の前縁部を良好
に冷却することが可能となる。The first, second, and third cooling channels are completely independent within the blade. For this reason, when the cooling fluid supply pressure to each cooling flow path is constant, the flow velocity of the cooling fluid increases as compared with a conventional blade provided with only one or two internal flow paths. As a result, the cooling effect by convection is improved, the supply pressure of the cooling fluid can be reduced as a result, the amount of the cooling fluid can be reduced, and the aerodynamic loss can be reduced and the efficiency can be improved. Further, since the three cooling channels are completely independent, the pressures in the respective cooling channels do not interfere with each other, and it is possible to allow the cooling fluid to flow through the respective cooling passages as set. It is possible to maximize the cooling effect at the flow rate of. Also, the second
In the cooling flow path of, since the flow path configuration extends while bending from the trailing edge portion in the blade middle area toward the leading edge portion in the blade middle area, the trailing edge portion in the blade middle area is formed. When the cooling fluid is jetted from the flow path portion extending through the exhaust hole for film cooling to the outer surface of the trailing edge portion of the blade intermediate portion area to cool the film. The trailing edge of the can be cooled well. Therefore, it is possible to prevent the temperature of the cooling fluid flowing through the second cooling passage from rising before reaching the wake region of the second cooling passage, and as a result, a small amount of the cooling fluid can be applied to the blade middle region. It is possible to cool the leading edge satisfactorily.
【０００７】[0007]
【実施例】図１は本発明をタービンの動翼に適用した一
実施例の外観を示すものである。すなわち、この動翼
は、大きく分けて、翼本体１と、この翼本体１を支持す
る翼根部２と、プラットホーム部３とから構成されてい
る。FIG. 1 shows the appearance of an embodiment in which the present invention is applied to a turbine rotor blade. That is, the moving blade is roughly divided into a blade body 1, a blade root portion 2 that supports the blade body 1, and a platform portion 3.
【０００８】翼本体１，翼根部２およびプラットホーム
部３は、翼本体１の先端壁Ｘ（図２参照）だけを残して
精密鋳造によって一体的に形成されたもので、先端壁Ｘ
は溶接あるいは拡散接合によって接合されている。The blade body 1, the blade root portion 2 and the platform portion 3 are integrally formed by precision casting, leaving only the tip wall X (see FIG. 2) of the blade body 1.
Are joined by welding or diffusion bonding.
【０００９】翼本体１内と翼根部２内とには、図２およ
び図３に示すように翼本体１の高さ方向に延びる３つの
冷却流体系統１１，１２，１３が仕切壁１４，１５によ
って形成されており、これら冷却流体系統１１，１２，
１３の翼根部２内に位置する端部は、図示しない回転軸
に設けられた冷却流体供給路に接続されている。In the blade body 1 and the blade root portion 2, as shown in FIGS. 2 and 3, three cooling fluid systems 11, 12, 13 extending in the height direction of the blade body 1 are provided as partition walls 14, 15. Are formed by these cooling fluid systems 11, 12,
An end portion of the blade 13 located inside the blade root portion 2 is connected to a cooling fluid supply passage provided on a rotating shaft (not shown).
【００１０】仕切壁１４は、翼本体１の根本部近傍にお
いて２つの分岐壁１４ａ，１４ｂに分岐し、これら分岐
壁１４ａ，１４ｂは前述した先端壁Ｘの内面近くまで延
びている。そして、分岐壁１４ａ，１４ｂ間には、この
分岐壁１４ａ，１４ｂの間にＵ字形の流路１６を構成す
る壁１７が設けられている。The partition wall 14 branches into two branch walls 14a and 14b in the vicinity of the root of the blade main body 1, and these branch walls 14a and 14b extend close to the inner surface of the tip wall X described above. Further, between the branch walls 14a and 14b, a wall 17 that constitutes a U-shaped flow path 16 is provided between the branch walls 14a and 14b.
【００１１】前記第１の冷却系統１１は、翼根部２から
翼本体１の先端部近傍まで延びるように仕切壁１４と前
縁部Ｆの近傍に設けられた仕切壁１８とによって形成さ
れた直線状の流路１９と、仕切壁１８と前縁部Ｆの外面
との間に形成された空洞２０と、仕切壁１８に複数設け
られた小孔２１と、空洞２０と前縁部Ｆの外面との間に
存在する壁２２に複数設けられたフィルム冷却用の排出
孔２３とで構成されている。The first cooling system 11 is a straight line formed by a partition wall 14 extending from the blade root 2 to the vicinity of the tip of the blade body 1 and a partition wall 18 provided in the vicinity of the front edge F. -Shaped channel 19, a cavity 20 formed between the partition wall 18 and the outer surface of the front edge portion F, a plurality of small holes 21 provided in the partition wall 18, and an outer surface of the cavity 20 and the front edge portion F. And a plurality of discharge holes 23 for cooling the film provided on the wall 22 existing between.
【００１２】したがって、この第１の冷却系統１１に供
給された冷却流体は、翼根部２から流入し、流路１９を
翼高さ方向に流れ、先端壁Ｘ付近に達するが、その間
に、仕切壁１８に設けられた複数の小孔２１から空洞２
０内に噴射流入し、さらに、壁２２に設けられた複数の
排出孔２３を通過して、翼外部に流出する。なお、図中
２４は流路１９の翼背側の内面および翼腹側の内面の両
者にそれぞれ突設され、対流冷却効果を増進させるため
の攪拌ストリップを示している。Therefore, the cooling fluid supplied to the first cooling system 11 flows in from the blade root portion 2, flows in the flow passage 19 in the blade height direction, and reaches the vicinity of the tip wall X. Cavity 2 from a plurality of small holes 21 provided in the wall 18
Injected into 0, further passes through a plurality of discharge holes 23 provided in the wall 22, and flows out to the outside of the blade. In the figure, reference numeral 24 denotes a stirring strip projecting on both the inner surface of the flow passage 19 on the blade back side and the inner surface of the blade ventral side to enhance the convection cooling effect.
【００１３】この第１の冷却系統１１の冷却性能は、主
に、流路１９における対流冷却効果、冷却流体が流路１
９から小孔２１を通過し壁２２の内面に噴流として衝突
することによるインピンジ冷却効果、排出孔２３の内面
の対流冷却効果および上記排出孔２３を介して翼外に吹
出した冷却流体が翼外表面、すなわち前縁部Ｆならびに
この前縁部Ｆの背側，腹側に沿って流れることによるフ
ィルム冷却効果の相乗効果で与えられる。The cooling performance of the first cooling system 11 is mainly due to the convection cooling effect in the flow passage 19 and the cooling fluid flowing in the flow passage 1.
9 through the small holes 21 and impinging on the inner surface of the wall 22 as a jet flow, the impingement cooling effect, the convection cooling effect on the inner surface of the discharge hole 23, and the cooling fluid blown out of the blade through the discharge hole 23 It is given by the synergistic effect of the film cooling effect by flowing along the surface, that is, the front edge portion F and the back side and the ventral side of the front edge portion F.
【００１４】前記第２の冷却系統１２は、仕切壁１４と
１５との間に形成され翼根部２から翼本体１の先端壁Ｘ
の近傍まで延びた後、前記Ｕ字形の流路に通じた屈折流
路３１と、この屈折流路３１を構成する翼本体１の腹側
の壁に複数設けられた排出孔３２（図３参照）とを主体
にして構成されている。The second cooling system 12 is formed between the partition walls 14 and 15 and extends from the blade root portion 2 to the tip wall X of the blade body 1.
, And a plurality of discharge holes 32 provided in the ventral wall of the blade body 1 forming the refraction channel 31 (see FIG. 3). ) And is mainly composed.
【００１５】したがって、この第２の冷却系統１２に導
かれた冷却流体は、仕切壁１４と１５との間を翼根部か
ら翼本体１の先端部へ向けて流れた後、前縁部側回りに
１８０度リターンして分岐壁１４ｂと壁１７との間を流
れ、その後、翼本体１の根本部分において再び前縁部側
回りに１８０度リターンして分岐壁１４ａと壁１７との
間を翼先端部付近まで流れる。この間に、この屈折流路
３１を構成する翼本体１の腹側の壁に設けられた排出孔
３２から翼外へと流れる。なお、図中３３は第１の冷却
系統１１と同様に設けられた攪拌ストリップを示し、ま
た３４は先端壁Ｘに設けられた排出孔を示している。Therefore, the cooling fluid guided to the second cooling system 12 flows between the partition walls 14 and 15 from the blade root portion toward the tip portion of the blade body 1, and then rotates around the leading edge side. 180 degrees to flow between the branch wall 14b and the wall 17, and then return again 180 degrees around the front edge portion at the root portion of the wing body 1 to return the wing between the branch wall 14a and the wall 17. It flows to near the tip. During this time, the air flows out of the blade through the discharge hole 32 provided in the ventral wall of the blade main body 1 forming the refraction channel 31. In the figure, 33 indicates a stirring strip provided similarly to the first cooling system 11, and 34 indicates a discharge hole provided in the tip wall X.
【００１６】この第２の冷却系統１２の冷却性能は、屈
折流路３１での対流冷却効果、排出孔３２，３４内での
対流冷却効果、排出孔３２，３４から吹出した冷却流体
が翼の腹側外面および先端部外面に沿って流れることに
よるフィルム冷却効果によって与えられる。The cooling performance of the second cooling system 12 is such that the convection cooling effect in the refraction channel 31, the convection cooling effect in the discharge holes 32 and 34, and the cooling fluid blown out from the discharge holes 32 and 34 are the blades. It is provided by the film cooling effect by flowing along the ventral outer surface and the tip outer surface.
【００１７】なお、屈折流路３１は途中の複数個所にお
いて、排出孔３２から冷却流体を翼外へ排出しているの
下流に向かうにしたがって通過する冷却流体の量が徐々
に減少し、対流冷却効果が低下する虞れがあるので、こ
の実施例では、下流に向かうにしたがって通路断面積を
減少させ、これによって流速をほぼ一定に保つようにし
ている。また流路の圧力損失を少なくするという観点か
ら２つのリターン部はなめらかな曲率で変化する曲率路
に形成されている。At a plurality of locations along the refraction channel 31, the cooling fluid is discharged from the discharge holes 32 to the outside of the blade, and the amount of the cooling fluid passing therethrough gradually decreases, and convection cooling is performed. Since the effect may be reduced, in this embodiment, the passage cross-sectional area is reduced toward the downstream side, thereby keeping the flow velocity substantially constant. Further, from the viewpoint of reducing the pressure loss of the flow path, the two return parts are formed in a curvature path that changes with a smooth curvature.
【００１８】前記第３の冷却系統１３は、翼の後縁部側
を冷却するためのもので、仕切壁１５と翼本体１の後縁
部側に設けられた仕切壁４１との間に翼根部２から翼本
体１の先端壁Ｘの近辺に至るまで延びる流路４２と、仕
切壁４１と翼本体１の後縁部Ｒとの間に形成された空洞
４３と、仕切壁４１に設けられた複数の小孔４４と、空
洞４３と後縁部Ｒとの間に存在する壁４５に設けられた
複数の排出孔４６とで構成されている。The third cooling system 13 is for cooling the trailing edge side of the blade, and is provided between the partition wall 15 and the partition wall 41 provided on the trailing edge side of the blade body 1. The flow passage 42 extending from the root portion 2 to the vicinity of the tip wall X of the blade body 1, a cavity 43 formed between the partition wall 41 and the trailing edge R of the blade body 1, and the partition wall 41 are provided. It is composed of a plurality of small holes 44 and a plurality of discharge holes 46 provided in the wall 45 existing between the cavity 43 and the rear edge portion R.
【００１９】したがって、この第３の冷却系統１３に導
かれた冷却流体は、翼根部２から流路４２内を翼本体１
の先端部側へと流れた後、小孔４４を通って空洞４３内
に流れ込み、次に排出孔４６を通って翼外へと流れる。
なお、図中４７は、攪拌ストリップを示している。Therefore, the cooling fluid guided to the third cooling system 13 flows from the blade root portion 2 through the flow passage 42 into the blade main body 1.
After flowing to the tip side of the blade, it flows into the cavity 43 through the small hole 44, and then to the outside of the blade through the discharge hole 46.
In the figure, 47 indicates a stirring strip.
【００２０】この第３の冷却系統１３の冷却性能は、流
路４２での対流冷却効果、小孔４４を通過した冷却流体
が噴流となって壁４５の内面に衝突することによるイン
ピンジ冷却効果および排出孔４６の内面における対流冷
却効果によって与えられる。The cooling performance of the third cooling system 13 includes the convective cooling effect in the flow path 42, the impingement cooling effect due to the cooling fluid passing through the small holes 44 forming a jet and colliding with the inner surface of the wall 45. It is provided by the convective cooling effect on the inner surface of the discharge hole 46.
【００２１】一方、第１，第２，第３の冷却系統１１，
１２，１３の翼根部２に位置する冷却流体導入口には、
各冷却系統１１，１２，１３に流入する冷却流体の流量
を細かに調整するオリフィスプレート５１が着脱自在に
設けられている。On the other hand, the first, second and third cooling systems 11,
The cooling fluid introduction ports located at blade roots 2 of 12 and 13 are
An orifice plate 51 for finely adjusting the flow rate of the cooling fluid flowing into each cooling system 11, 12, 13 is provided detachably.
【００２２】これは次のような理由に基づく。すなわ
ち、上記構成の翼は、翼の内部から外部へ冷却流体を吹
出す、いわゆるフィルム冷却用の排出孔を多用している
ため、少ない流量で冷却効果を得るには各冷却系統間の
流量配分を厳密に行なう必要がある。この配分を行なう
手段として、製造加工時の精度を上げることも考えられ
るが、上記精度を上げることは実際問題として困難であ
る。そこで、この実施例では、流量調整機構、つまりオ
リフィスプレート５１を付加して製作後に流量配分を適
正値に保つようにしているのである。This is based on the following reasons. That is, since the blade having the above-mentioned structure uses a large number of discharge holes for so-called film cooling, which blows out the cooling fluid from the inside of the blade to the outside, in order to obtain the cooling effect with a small flow rate, the flow rate distribution between the cooling systems Must be done strictly. As a means for carrying out this distribution, it may be possible to increase the precision during the manufacturing process, but it is actually difficult to raise the precision. Therefore, in this embodiment, a flow rate adjusting mechanism, that is, an orifice plate 51 is added to maintain the flow rate distribution at an appropriate value after manufacturing.
【００２３】このように、タービンの翼の内部を複数の
細長い流路に区切り、内部を通過する冷却流体の速度を
上昇させて対流冷却効果を高めると同時に、フィルム冷
却用の排出孔を多数配置し、フィルム冷却の重ね合わさ
れた効果をも併用しているので少ない量の冷却流体で冷
却性能を飛躍的に向上させることができる。また、第２
の冷却系統１２では、翼中間部領域内の後縁部から翼中
間部領域内の前縁部に向けて屈折しながら延びる流路構
成となっているので、屈折流路３１の翼中間部領域内の
後縁部を延びる部分から排出孔３２を介して翼中間部領
域の後縁部外面に冷却流体を噴出させてフイルム冷却す
るようにすると、翼の形状に起因する特性から翼中間部
領域の後縁部を良好に冷却できる。すなわち、翼中間部
領域の後縁部外面で腹側に沿って流れる燃焼ガスの流速
は通常、極めて速い。したがって、この腹側部分に冷却
流体を噴出させてフイルム冷却を行うと、翼とフイルム
との間の温度境界層を薄くでき、翼からフイルムへ熱伝
達率を大きくできる。すなわち、この腹側部分を良好に
冷却できる。一方、翼中間部領域の後縁部外面で背側に
沿って流れる燃焼ガスは翼の形状の影響を受けて乱流化
する。したがって、この背側部分に冷却流体を噴出させ
てフイルム冷却を行うと、やはり翼とフイルムとの間の
温度境界層を薄くでき、翼からフイルムへの熱伝達率を
大きくできる。すなわち、この背側部分を良好に冷却で
きる。このため、第２の冷却系統１２を流れる冷却流体
が第２の冷却系統１２の後流域に達するまでに温度上昇
してしまうのを防止でき、この結果、冷却流体の量を増
すことなく翼中間部領域の前縁部も良好に冷却すること
が可能となる。As described above, the inside of the blade of the turbine is divided into a plurality of elongated flow paths, the speed of the cooling fluid passing through the inside is increased to enhance the convection cooling effect, and at the same time, a large number of discharge holes for film cooling are arranged. However, since the combined effect of film cooling is also used, the cooling performance can be dramatically improved with a small amount of cooling fluid. Also, the second
Since the cooling system 12 has a flow path configuration that extends while refracting from the trailing edge portion in the blade intermediate portion area toward the leading edge portion in the blade intermediate portion area, the blade intermediate portion area of the refraction flow passage 31 is formed. When the cooling fluid is jetted from the portion extending the inner trailing edge portion to the outer surface of the trailing edge portion of the blade intermediate portion through the discharge hole 32 to cool the film, the blade intermediate portion area is formed due to the characteristic of the blade. The trailing edge of the can be cooled well. That is, the flow velocity of the combustion gas flowing along the ventral side on the outer surface of the trailing edge portion of the blade middle region is usually extremely high. Therefore, when the cooling fluid is jetted to the ventral side portion to cool the film, the temperature boundary layer between the blade and the film can be thinned and the heat transfer coefficient from the blade to the film can be increased. That is, this ventral portion can be cooled well. On the other hand, the combustion gas flowing along the back side at the outer surface of the trailing edge of the blade middle region is turbulent due to the influence of the shape of the blade. Therefore, when the cooling fluid is jetted to the back side portion to cool the film, the temperature boundary layer between the blade and the film can be thinned and the heat transfer coefficient from the blade to the film can be increased. That is, this back portion can be cooled well. Therefore, it is possible to prevent the temperature of the cooling fluid flowing through the second cooling system 12 from rising until it reaches the wake region of the second cooling system 12, and as a result, the amount of the cooling fluid is not increased and the blade intermediate portion is increased. It is also possible to cool the leading edge of the partial region satisfactorily.
【００２４】なお、本発明は、上述した実施例に限定さ
れるものではない。すなわち、第２の冷却系統１２の屈
折流路３１におけるリターン部に図５に示すようにガイ
ド６１を設けることによって、この部分での流動抵抗を
減少させるようにしてもよい。また、第３の冷却系統１
３において、翼後縁部Ｒの両面の冷却を強化するために
流路４２および空洞４３と翼外とを連通させるフィルム
冷却用の排出孔を設けてもよい。さらに、最後縁部の流
路形状としては、図６(a) ，(b) に示すようにスリット
状流路７１としてもよいし、また図７(a) ，(b) に示す
ように空洞４３内に熱交換面を増加させるためにピンフ
ィン７２を設けるようにしてもよい。さらに、各冷却系
統において、翼本体１の先端壁Ｘにフィルム冷却用の排
出孔を設けてもよい。The present invention is not limited to the above embodiment. That is, the flow resistance in this portion may be reduced by providing the guide 61 as shown in FIG. 5 in the return portion of the refraction channel 31 of the second cooling system 12. Also, the third cooling system 1
In order to enhance the cooling of both surfaces of the blade trailing edge portion R, a discharge hole for film cooling may be provided that connects the flow passage 42 and the cavity 43 to the outside of the blade. Further, the flow path shape of the last edge may be a slit-like flow path 71 as shown in FIGS. 6 (a) and 6 (b), or a cavity as shown in FIGS. 7 (a) and 7 (b). A pin fin 72 may be provided in the portion 43 to increase the heat exchange surface. Further, in each cooling system, a discharge hole for film cooling may be provided in the tip wall X of the blade body 1.
【００２５】[0025]
【発明の効果】以上説明したように、本発明によれば、
独立した３つの冷却流路を設けているので、各冷却流路
への冷却流体供給圧力を一定とした場合、従来の翼のよ
うに１つあるいは２つの内部流路だけを設けたものに較
べて冷却流体の流速を増加させることができる。この結
果、対流による冷却効果を向上させることができ、結果
的に冷却流体の供給圧力を低下でき、冷却流体の量の減
少化を図れ、空力損失の減少化ならびに効率の向上化を
図ることができる。また、３つの冷却流路を完全に独立
させているので、各冷却流路内の圧力が互いに干渉する
ことがなく、各冷却通路に設定通りの冷却流体を通流さ
せることが可能となり、最少の流量で最大の冷却効果を
発揮させることが可能となる。また、第２の冷却流路で
は、翼中間部領域内の後縁部から翼中間部領域内の前縁
部に向けて屈折しながら延びる流路構成となっているの
で、翼中間部領域内の後縁部を延びる流路部分からフイ
ルム冷却用の排出孔を介して翼中間部領域の後縁部外面
に冷却流体を噴出させてフイルム冷却するようにする
と、翼の形状に起因する特性から翼中間部領域の後縁部
を良好に冷却できる。したがって、第２の冷却流路を流
れる冷却流体が第２の冷却流路の後流域に達するまでに
温度上昇してしまうのを防止でき、この結果、少ない量
の冷却流体で翼中間部領域の前縁部も良好に冷却するこ
とができる。As described above, according to the present invention,
Since three independent cooling channels are provided, when the cooling fluid supply pressure to each cooling channel is constant, compared to a conventional blade that has only one or two internal channels. The flow velocity of the cooling fluid can be increased. As a result, the cooling effect by convection can be improved, the supply pressure of the cooling fluid can be reduced as a result, the amount of the cooling fluid can be reduced, the aerodynamic loss can be reduced, and the efficiency can be improved. it can. Further, since the three cooling flow paths are completely independent, the pressures in the respective cooling flow paths do not interfere with each other, and it is possible to allow the cooling fluid to flow through the respective cooling paths according to the setting. It is possible to maximize the cooling effect at the flow rate of. Further, in the second cooling flow passage, since the flow passage structure extends from the trailing edge portion in the blade intermediate portion area toward the leading edge portion in the blade intermediate portion area while refracting, in the blade intermediate portion area. If the cooling fluid is jetted from the flow path portion extending through the trailing edge portion to the outer surface of the trailing edge portion of the blade middle area through the film cooling discharge hole to cool the film, the characteristics due to the shape of the blade will result. The trailing edge of the blade middle region can be cooled well. Therefore, it is possible to prevent the temperature of the cooling fluid flowing through the second cooling passage from rising before reaching the wake region of the second cooling passage, and as a result, a small amount of the cooling fluid can be applied to the blade middle region. The leading edge can also be cooled well.
【図１】本発明の一実施例に係るタービンの翼の外観図FIG. 1 is an external view of a turbine blade according to an embodiment of the present invention.
【図２】図１におけるＰ−Ｐ線に沿って切断し矢印方向
に見た断面図FIG. 2 is a cross-sectional view taken along the line P-P in FIG. 1 and viewed in the direction of the arrow.
【図３】図１におけるＱ−Ｑ線に沿って切断し矢印方向
に見た断面図3 is a cross-sectional view taken along the line QQ in FIG. 1 and viewed in the direction of the arrow.
【図４】図１におけるＳ−Ｓ線に沿って切断し矢印方向
に見た局部的な断面図FIG. 4 is a local cross-sectional view taken along line S-S in FIG. 1 and viewed in the direction of the arrow.
【図５】本発明に係るタービンの翼の変形例を局部的に
示す断面図FIG. 5 is a cross-sectional view locally showing a modified example of a turbine blade according to the present invention.
【図６】(a) は本発明の別の実施例における要部の縦断
面図で(b) は同要部の横断面図FIG. 6 (a) is a longitudinal sectional view of an essential part in another embodiment of the present invention, and FIG. 6 (b) is a lateral sectional view of the same part.
【図７】(a) は本発明のさらに別の実施例における要部
の縦断面図で(b) は同要部の横断面図FIG. 7 (a) is a vertical cross-sectional view of a main part in yet another embodiment of the present invention, and (b) is a cross-sectional view of the main part.
１…翼本体 ２…翼根部 ３…プラットホーム部 １１…第１の冷
却系統 １２…第２の冷却系統 １３…第３の冷
却系統DESCRIPTION OF SYMBOLS 1 ... Blade main body 2 ... Blade root part 3 ... Platform part 11 ... 1st cooling system 12 ... 2nd cooling system 13 ... 3rd cooling system
フロントページの続き (72)発明者 大友 文雄 神奈川県川崎市幸区小向東芝町１番地 株 式会社東芝総合研究所内Front page continuation (72) Inventor Fumio Otomo 1 Komukai Toshiba-cho, Sachi-ku, Kawasaki-shi, Kanagawa Stock company Toshiba Research Institute
Claims (4)
記入口から翼根部の内部および翼本体の内部を経由して
翼外に通じる冷却流路を備え、上記入口を冷却流体供給
部に接続するようにしたタービンの翼において、 翼前縁部内に設けられ、主として冷却流体を前記翼根部
の内部および前記翼本体の内部に翼の高さ方向に沿って
形成された経路で導く流路および上記流路に案内された
冷却流体を上記翼本体の外部へ排出させる排出孔を備え
てなる第１の冷却流路と、 この第１の冷却流路とは独立して翼中間部内に設けら
れ、主として冷却流体を前記翼根部の内部および前記翼
本体の内部に翼の高さ方向に沿って形成された経路で導
いた後に上記翼本体の高さ方向先端部近傍で上記翼本体
の前縁部側回りにリターンさせて上記翼本体の基端部近
傍まで案内し、さらに上記基端部近傍から上記翼本体の
前縁部側回りにリターンさせて上記翼本体の高さ方向先
端部近傍まで案内する屈折流路および上記屈折流路の少
なくとも最下流領域に案内された冷却流体を上記翼本体
の外部へ排出させる排出孔を備えてなる第２の冷却流路
と、 この第２の冷却流路および前記第１の冷却流路とは独立
に翼後縁部内に設けられ、主として冷却流体を前記翼根
部の内部および前記翼本体の内部に翼の高さ方向に沿っ
て形成された経路で導く流路および上記流路に案内され
た冷却流体を上記翼本体の後縁から外部へ排出させる流
路を備えてなる第３の冷却流路とを具備してなることを
特徴とするタービンの翼。1. A cooling fluid passage having an inlet at a base end portion of a blade root and communicating from the inlet to the outside of the blade via the inside of the blade root portion and the inside of the blade main body, and the inlet to a cooling fluid supply portion. In a turbine blade configured to be connected, a flow path that is provided in a blade leading edge and mainly guides a cooling fluid to the inside of the blade root portion and the inside of the blade main body through a path formed along the height direction of the blade. And a first cooling flow passage having a discharge hole for discharging the cooling fluid guided to the flow passage to the outside of the blade main body, and the first cooling flow passage is provided in the blade intermediate portion independently of the first cooling flow passage. The cooling fluid is mainly guided inside the blade root portion and the inside of the blade main body by a path formed along the height direction of the blade, and then in front of the blade main body in the vicinity of the height direction tip of the blade main body. Return to the periphery of the rim to allow the base end of the wing body At least the most downstream of the refraction channel and the refraction channel that guides to the vicinity and further returns from the vicinity of the base end portion to the vicinity of the front edge portion of the blade body and guides to the vicinity of the tip end in the height direction of the blade body A second cooling flow path having a discharge hole for discharging the cooling fluid guided to the region to the outside of the blade body, and the second cooling flow path and the first cooling flow path independently of each other. A cooling fluid is provided in the trailing edge portion, which mainly guides the cooling fluid through the passage formed along the height direction of the blade inside the blade root portion and inside the blade body. A blade for a turbine, comprising: a third cooling flow path having a flow path for discharging the air from the trailing edge of the blade body.
は、各流路に流入する冷却流体の流量を調整する流量調
整機構が設けられてなることを特徴とする請求項１に記
載のタービンの翼。2. A flow rate adjusting mechanism for adjusting a flow rate of a cooling fluid flowing into each of the first, second, and third cooling flow paths is provided. The turbine blade according to Item 1.
翼本体の高さ方向先端部外面に沿って冷却流体を翼外へ
排出させる排出孔を備えてなることを特徴とする請求項
１に記載のタービンの翼。3. The first, second, and third cooling passages are provided with discharge holes for discharging the cooling fluid to the outside of the blade along the outer surface of the tip portion in the height direction of the blade body. The blade of the turbine according to claim 1.
本体の高さ方向に案内する部分と、この部分と上記翼本
体の前縁部外面との間に形成された空洞と、この空洞と
上記部分とを仕切る仕切壁に設けられ上記部分によって
案内された冷却流体を上記翼本体の前縁部外面と上記空
洞との間に存在する壁部の内面に向けて噴射させる複数
の小孔とを備えてなることを特徴とする請求項１に記載
のタービンの翼。4. The first cooling flow passage includes a portion for guiding a cooling fluid in a height direction of the blade body, and a cavity formed between this portion and an outer surface of a front edge portion of the blade body. A plurality of cooling fluids, which are provided on a partition wall that divides the cavity from the cavity and are guided by the section, toward the inner surface of the wall portion existing between the outer surface of the leading edge of the blade body and the cavity. The blade of the turbine according to claim 1, further comprising:
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5202287A JP2645209B2 (en) | 1993-08-16 | 1993-08-16 | Turbine wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5202287A JP2645209B2 (en) | 1993-08-16 | 1993-08-16 | Turbine wing |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5350882A Division JPS58170801A (en) | 1982-03-31 | 1982-03-31 | Blade for turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH06185301A true JPH06185301A (en) | 1994-07-05 |
| JP2645209B2 JP2645209B2 (en) | 1997-08-25 |
Family
ID=16455044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5202287A Expired - Lifetime JP2645209B2 (en) | 1993-08-16 | 1993-08-16 | Turbine wing |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2645209B2 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001073707A (en) * | 1999-05-14 | 2001-03-21 | General Electric Co <Ge> | Rear-edge cooling passage causing partial turbulence for gas turbine nozzle |
| JP2008128234A (en) * | 2006-11-20 | 2008-06-05 | General Electric Co <Ge> | Double feeding serpentine cooled blade |
| JP2014001633A (en) * | 2012-06-15 | 2014-01-09 | Hitachi Ltd | Gas turbine moving blade, gas turbine, and gas turbine moving blade adjusting method |
| WO2019102556A1 (en) * | 2017-11-22 | 2019-05-31 | 東芝エネルギーシステムズ株式会社 | Turbine blade and turbine |
| CN114017133A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Cooled variable-geometry low-pressure turbine guide vane |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50129707U (en) * | 1974-04-10 | 1975-10-24 | ||
| GB1514613A (en) * | 1976-04-08 | 1978-06-14 | Rolls Royce | Blade or vane for a gas turbine engine |
-
1993
- 1993-08-16 JP JP5202287A patent/JP2645209B2/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS50129707U (en) * | 1974-04-10 | 1975-10-24 | ||
| GB1514613A (en) * | 1976-04-08 | 1978-06-14 | Rolls Royce | Blade or vane for a gas turbine engine |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001073707A (en) * | 1999-05-14 | 2001-03-21 | General Electric Co <Ge> | Rear-edge cooling passage causing partial turbulence for gas turbine nozzle |
| JP2008128234A (en) * | 2006-11-20 | 2008-06-05 | General Electric Co <Ge> | Double feeding serpentine cooled blade |
| JP2014001633A (en) * | 2012-06-15 | 2014-01-09 | Hitachi Ltd | Gas turbine moving blade, gas turbine, and gas turbine moving blade adjusting method |
| WO2019102556A1 (en) * | 2017-11-22 | 2019-05-31 | 東芝エネルギーシステムズ株式会社 | Turbine blade and turbine |
| CN114017133A (en) * | 2021-11-12 | 2022-02-08 | 中国航发沈阳发动机研究所 | Cooled variable-geometry low-pressure turbine guide vane |
| CN114017133B (en) * | 2021-11-12 | 2023-07-07 | 中国航发沈阳发动机研究所 | Cooled variable geometry low pressure turbine guide vane |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2645209B2 (en) | 1997-08-25 |
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