JPH11223101A - Gas turbine moving blade - Google Patents
Gas turbine moving bladeInfo
- Publication number
- JPH11223101A JPH11223101A JP2330598A JP2330598A JPH11223101A JP H11223101 A JPH11223101 A JP H11223101A JP 2330598 A JP2330598 A JP 2330598A JP 2330598 A JP2330598 A JP 2330598A JP H11223101 A JPH11223101 A JP H11223101A
- Authority
- JP
- Japan
- Prior art keywords
- shroud
- cavity
- blade
- moving blade
- cooling
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- 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使用
されるガスタービン動翼に関し、特にシュラウドの冷却
構造を簡素化し、冷却性能を向上させるものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine blade used for thermal power generation and the like, and more particularly to a structure for simplifying a shroud cooling structure and improving a cooling performance.
【０００２】[0002]
【従来の技術】図７は従来の代表的なガスタービン動翼
を示し、（ａ）は動翼の縦断面図、（ｂ）はそのＥ−Ｅ
断面図である。図において、２１は動翼であり、２２は
その先端のシュラウド、２３はシュラウド２２に設けら
れたフィンである。２４は動翼２１内に穿設されたマル
チホール、２５は動翼２１内壁に設けられたピンフィ
ン、２６はリブであり空胴２９を支持するものである。
２７はハブ部、２８は翼根部であり、２９は前述の空胴
である。2. Description of the Related Art FIG. 7 shows a typical conventional gas turbine blade, in which (a) is a longitudinal sectional view of the blade, and (b) is an EE thereof.
It is sectional drawing. In the figure, 21 is a rotor blade, 22 is a shroud at its tip, and 23 is a fin provided on the shroud 22. 24 is a multi-hole formed in the moving blade 21, 25 is a pin fin provided on the inner wall of the moving blade 21, 26 is a rib for supporting the cavity 29.
27 is a hub portion, 28 is a blade root portion, and 29 is the aforementioned cavity.
【０００３】図８は図７におけるＦ−Ｆ断面図、図９は
図８におけるＧ−Ｇ断面図であり、両図において、シュ
ラウド２２内部には２つのキャビティ３０，３１が独立
に形成されており、キャビティ３０，３１にはそれぞれ
プラグ３２，３３が上面より挿入されて内部を密閉し、
動翼２１のマルチホール２４がキャビティ３０，３１に
それぞれ連通し、冷却空気を供給している。キャビティ
３０，３１にはそれぞれ両側に向かって複数の冷却穴３
４が連通し、冷却穴３４はそれぞれ両端面で開口し、冷
却空気を流出する構成である。FIG. 8 is a sectional view taken along line FF in FIG. 7, and FIG. 9 is a sectional view taken along line GG in FIG. 8. In both figures, two cavities 30, 31 are independently formed inside the shroud 22. The plugs 32 and 33 are inserted into the cavities 30 and 31 from the upper surface to seal the inside,
The multi-holes 24 of the moving blade 21 communicate with the cavities 30 and 31, respectively, and supply cooling air. Each of the cavities 30 and 31 has a plurality of cooling holes 3 toward both sides.
4, the cooling holes 34 are opened at both end surfaces, and the cooling air flows out.
【０００４】上記構成の動翼においては、冷却空気は矢
印で図示するように翼根部２８より空胴２９に流入し、
ピンフィン２５により熱伝達率を向上させて基部を冷却
してマルチホール２４を流れて先端部へ導かれる。先端
部からはシュラウド２２のキャビティ３０，３１に流入
し、キャビティ３０，３１から各冷却穴３４を通り、互
に対向するシュラウド２２の両端面へ流出し、シュラウ
ド全面を冷却している。In the rotor blade having the above structure, cooling air flows into the cavity 29 from the blade root portion 28 as shown by the arrow,
The heat transfer coefficient is improved by the pin fins 25 to cool the base and flow through the multi-hole 24 to be guided to the tip. From the tip end, it flows into the cavities 30, 31 of the shroud 22, passes through the cooling holes 34 from the cavities 30, 31, and flows out to both end surfaces of the shroud 22 facing each other, thereby cooling the entire shroud.
【０００５】上記に説明の動翼においては、前述のよう
に、動翼２１の先端にはインテグラル状をなすシュラウ
ド２２が動翼２１と一体に形成されている。シュラウド
２２は動翼２１の先端から漏洩するガスを減少させると
ともに、シュラウド２２の端面を隣接するシュラウド２
２の端面に圧接させて一連のグループ翼を形成させるこ
とにより動翼２１の耐振動強度を向上させている。動翼
２１には回転軸方向と円周方向との２方向の振動が発生
するが、シュラウド２２の端面を斜めに形成することに
より両方向の振動が抑制される。また、シュラウド２２
には動翼２１の先端部から漏洩するガスを減少させるた
めとケーシング側との接触を防止するため、フィン２３
が削り出して設けられている。In the moving blade described above, an integral shroud 22 is formed integrally with the moving blade 21 at the tip of the moving blade 21 as described above. The shroud 22 reduces the gas leaking from the tip of the rotor blade 21, and reduces the end face of the shroud 22 to the adjacent shroud 2.
The vibration resistance of the rotor blade 21 is improved by forming a series of group blades by pressing against the end face of the rotor blade 2. Vibration in the rotating blade 21 is generated in two directions, that is, the rotation axis direction and the circumferential direction. By forming the end face of the shroud 22 obliquely, vibrations in both directions are suppressed. Also, shroud 22
In order to reduce gas leaking from the tip of the rotor blade 21 and to prevent contact with the casing side,
Is cut out and provided.
【０００６】[0006]
【発明が解決しようとする課題】前述のように、従来の
ガスタービン動翼においては、シュラウド２２の対向す
る両側の冷却穴３４より冷却空気が流出し、シュラウド
２２全体を冷却して温度を低下させるが、冷却空気の消
費の面からは、冷却空気が動翼２１のマルチホール２４
からキャビティ３０，３１に合流し、キャビティ３０，
３１から両側に分かれ互に対向する冷却穴３４に流れ、
それぞれ両側に流れる。従って、各キャビティから両側
へ複数の冷却穴３４が配置されており、各冷却穴３４の
抵抗のちがいにより、各冷却穴によって流量が異なり、
冷却空気が均等に流れず、均等な冷却空気の分配調整が
むずかしく、シュラウドの均一な冷却ができない状況に
ある。As described above, in the conventional gas turbine blade, cooling air flows out of the cooling holes 34 on both sides of the shroud 22 facing each other, and the entire shroud 22 is cooled to lower the temperature. However, from the viewpoint of cooling air consumption, the cooling air is
From the cavities 30, 31 and
31 flows into the cooling holes 34 which are divided into two sides and face each other,
Each flows on both sides. Therefore, a plurality of cooling holes 34 are arranged on both sides from each cavity, and the flow rate differs for each cooling hole due to the difference in resistance of each cooling hole 34.
The cooling air does not flow evenly, and it is difficult to control the uniform distribution of the cooling air, so that the shroud cannot be cooled uniformly.
【０００７】そこで本発明はガスタービン動翼のシュラ
ウドにおいて、シュラウドに設けた冷却穴に流入する冷
却空気の流量調整を容易とし、冷却効果が均一になるよ
うなシュラウドの構造とし、シュラウドの温度が均等に
低下するようなガスタービン動翼を提供することを課題
としてなされたものである。In view of the above, the present invention provides a shroud for a gas turbine blade in which the flow rate of cooling air flowing into a cooling hole provided in the shroud is easily adjusted, and the shroud is structured so that the cooling effect is uniform. It is an object of the present invention to provide a gas turbine blade that is uniformly reduced.
【０００８】[0008]
【課題を解決するための手段】本発明は前述の課題を解
決するために次の（１）乃至（３）の手段を提供する。The present invention provides the following means (1) to (3) to solve the above-mentioned problems.
【０００９】（１）翼先端にシュラウドを有し、同翼の
内部に基部から先端に向けて冷却通路を設けて冷却空気
を流して前記シュラウド内に導き、同シュラウドの周囲
より流出させるガスタービンの動翼において、前記シュ
ラウド内部には周囲を残して拡大キャビティを形成し、
同拡大キャビティは前記動翼の冷却通路に連通すると共
に、前記シュラウド内で対向する両側に伸び周辺におい
て下方に屈曲して同シュラウド下面に開口する複数の穴
に連通することを特徴とするガスタービン動翼。(1) A gas turbine having a shroud at the blade tip, providing a cooling passage inside the blade from the base to the tip, flowing cooling air into the shroud, and flowing out from around the shroud. In the rotor blade of the shroud, forming an enlarged cavity leaving a periphery inside the shroud,
The gas turbine is characterized in that the enlarged cavity communicates with a cooling passage of the rotor blade and extends to opposite sides in the shroud, is bent downward at the periphery, and communicates with a plurality of holes opened on the lower surface of the shroud. Bucket.
【００１０】（２）上記（１）の発明において、前記動
翼の冷却通路は翼全長にわたった一体の空胴からなり、
同空胴内壁には多数のピンフィンを設けたことを特徴と
するガスタービン動翼。(2) In the invention of the above (1), the cooling passage of the moving blade comprises an integral cavity extending over the entire length of the blade.
A gas turbine blade having a number of pin fins provided on an inner wall of the cavity.
【００１１】（３）上記（１）の発明において、前記動
翼の冷却通路は翼の基部側が一体の空胴と同空胴に設け
た多数のピンフィン、先端側が先端に向かう多数の細穴
からなることを特徴とするガスタービン動翼。(3) In the invention of the above (1), the cooling passage of the rotor blade is formed by an integral cavity on the base side of the blade, a number of pin fins provided in the cavity, and a number of small holes whose tip end faces the tip. A gas turbine rotor blade comprising:
【００１２】本発明の（１）においては、シュラウド内
に拡大キャビティを設けているのでシュラウド内部がほ
とんどこの拡大キャビティが占めることになり、シュラ
ウドの周辺には多数の穴が設けられる構成である。従っ
て、動翼の冷却通路から流入する冷却空気はこの拡大キ
ャビティ内を満たし、拡大キャビティの主要部を冷却す
る。一方、拡大キャビティの周辺の穴は拡大キャビティ
に連通し、冷却空気をシュラウド外へ流出するので、拡
大キャビティ内の冷却空気は中央部より周辺に向かって
流動し、シュラウドの主要部の冷却効果を高める。更
に、穴から流出する冷却空気はシュラウドの穴が下向き
に流出するのでシュラウドの周辺を効果的に冷却し、全
体が均一に冷却される。In (1) of the present invention, since the enlarged cavity is provided in the shroud, almost the inside of the shroud is occupied by the enlarged cavity, and a large number of holes are provided around the shroud. Therefore, the cooling air flowing from the cooling passage of the bucket fills the enlarged cavity and cools the main part of the enlarged cavity. On the other hand, the holes around the enlarged cavity communicate with the enlarged cavity and allow the cooling air to flow out of the shroud, so that the cooling air in the enlarged cavity flows from the center to the periphery, reducing the cooling effect of the main part of the shroud. Enhance. Further, the cooling air flowing out of the holes effectively cools the periphery of the shroud because the holes of the shroud flow downward, and the whole is uniformly cooled.
【００１３】本発明の（２）は上記（１）のシュラウド
が、動翼内部が全長にわたって一体の空胴と同空胴に設
けられたピンフィンで構成された翼先端に設けられ、
又、（２）の発明は上記（１）のシュラウドが、動翼内
部が従来例のように基部側が空胴とピンフィン、先端側
が多数の細穴からなる翼先端に設けられるので、どのよ
うな形式の冷却構造を有する動翼にも適用でき、動翼の
熱伝達率向上による冷却効果とシュラウド全体の均一な
冷却とにより動翼全体の冷却効果が高まるものである。According to a second aspect of the present invention, the shroud according to the first aspect is provided at a tip of a blade which is constituted by an integral cavity over the entire length of the rotor blade and a pin fin provided in the cavity.
In the invention of (2), the shroud of (1) is provided at the tip of the blade having a cavity and pin fins on the base side and a number of small holes on the tip side, as in the conventional example. The present invention can also be applied to a moving blade having a type of cooling structure. The cooling effect by improving the heat transfer coefficient of the moving blade and the uniform cooling of the entire shroud enhance the cooling effect of the whole moving blade.
【００１４】[0014]
【発明の実施の形態】以下、本発明の実施の形態につい
て図面に基づいて具体的に説明する。図１は本発明の実
施の第１形態に係るガスタービン動翼の縦断面図であ
る。図において１は動翼であり、２はその先端のシュラ
ウド、３は翼根部である。４はリブであり、内部空胴１
０内を製造時に形成し、この空胴１０を支持するための
ものであり、本発明にとっては特に必要としないもので
ある。５は内部空胴１０内の両壁面に固定されて形成さ
れた多数のピンフィンである。１０は前述の動翼１内に
形成された内部空胴である。Embodiments of the present invention will be specifically described below with reference to the drawings. FIG. 1 is a longitudinal sectional view of a gas turbine bucket according to a first embodiment of the present invention. In the figure, 1 is a moving blade, 2 is a shroud at the tip, and 3 is a blade root. Reference numeral 4 denotes a rib, and the internal cavity 1
0 is formed at the time of manufacture to support the cavity 10, and is not particularly required for the present invention. Reference numeral 5 denotes a number of pin fins fixed to both wall surfaces inside the internal cavity 10. Reference numeral 10 denotes an internal cavity formed in the rotor blade 1 described above.
【００１５】このように本実施の第１形態の動翼は内部
を全長にわたり内部空胴１０とし、多数のピンフィン５
を設けた構造として内部の冷却空気の流通と対流を良く
し、冷却効果を高めるようにし、更に次に述べるように
先端のシュラウドの冷却にも特徴を持たせたものであ
る。As described above, the rotor blade of the first embodiment of the present invention has an internal cavity 10 over its entire length, and a large number of pin fins 5.
The structure is provided with a structure to improve the flow and convection of the cooling air inside, to enhance the cooling effect, and to also provide a feature in cooling the shroud at the tip as described below.
【００１６】図２は図１におけるＡ−Ａ断面図であり、
図３は図１におけるＢ−Ｂ断面図である。両図におい
て、シュラウド２内部には拡大キャビティ６が設けら
れ、シュラウドの周囲を残し、内部を空胴に形成してい
る。FIG. 2 is a sectional view taken along the line AA in FIG.
FIG. 3 is a sectional view taken along line BB in FIG. In both figures, an enlarged cavity 6 is provided inside the shroud 2, and the inside is formed as a cavity, leaving the periphery of the shroud.
【００１７】図４は図３におけるＣ−Ｃ断面図であり、
拡大キャビティ６は動翼１内の内部空胴１０と連通して
おり、冷却空気３０が導かれる。シュラウド２の周囲に
は図３に示すように拡大キャビティ６と連通する多数の
穴７が下向きに設けられており、拡大キャビティ６内の
冷却空気を下向きに流出する。FIG. 4 is a sectional view taken along the line CC in FIG.
The enlarged cavity 6 communicates with the internal cavity 10 in the bucket 1, and the cooling air 30 is guided. A large number of holes 7 communicating with the enlarged cavity 6 are provided downward around the shroud 2 as shown in FIG. 3, and the cooling air in the enlarged cavity 6 flows out downward.
【００１８】上記構成の実施の第１形態の動翼において
冷却空気３０が翼根部３より翼内部へ流入し、内部空胴
１０内の多数のピンフィン５により乱流となって熱伝達
を良好にし、先端部へ流れる過程で翼を冷却し、シュラ
ウド２内へ流入する。In the rotor blade of the first embodiment having the above-described structure, cooling air 30 flows into the blade from the blade root 3 and becomes turbulent due to a large number of pin fins 5 in the internal cavity 10 to improve heat transfer. In the process of flowing to the tip, the blade cools and flows into the shroud 2.
【００１９】シュラウド２に流入した冷却空気は拡大キ
ャビティ６内を満たし、所定の圧力以上になると、その
周囲の穴７より下向きに流出し、拡大キャビティ６内で
冷却空気が中央部の内部空胴１０との接続部から周辺に
向かって流れを作り、拡大キャビティ６の上，下面を一
様に冷却する。The cooling air that has flowed into the shroud 2 fills the inside of the enlarged cavity 6 and, when the pressure exceeds a predetermined pressure, flows downward through a hole 7 around the same. A flow is created from the connection portion with 10 to the periphery, and the upper and lower surfaces of the enlarged cavity 6 are uniformly cooled.
【００２０】穴７より流出する冷却空気は下向きとなっ
ているので、冷却がしにくいシュラウド２の周端部が効
果的に冷却されて、拡大キャビティ６により、中央部
を、穴６によって周端部を主に冷却し、シュラウド２が
全面にわたって均一に冷却されることになる。Since the cooling air flowing out of the hole 7 is directed downward, the peripheral end of the shroud 2 which is difficult to cool is effectively cooled. The main part is cooled, and the shroud 2 is uniformly cooled over the entire surface.
【００２１】図５，図６は本発明の実施の第２形態に係
るガスタービン動翼を示し、図５はシュラウドの断面
図、図６はそのＤ−Ｄ断面図である。この実施の第２形
態における動翼は従来例で説明した図７で示す動翼であ
り、図５は図７における断面Ｆ−Ｆ（図９）に相当する
図である。従って、動翼の都合は図７と同じであるので
説明は省略し、図５，図６に基づいて説明する。FIGS. 5 and 6 show a gas turbine rotor blade according to a second embodiment of the present invention. FIG. 5 is a sectional view of a shroud, and FIG. 6 is a sectional view taken along line DD of FIG. The moving blade in the second embodiment is the moving blade shown in FIG. 7 described in the conventional example, and FIG. 5 is a view corresponding to a cross section FF (FIG. 9) in FIG. Therefore, the convenience of the moving blade is the same as that of FIG. 7, and the description is omitted, and the description will be made based on FIGS.
【００２２】図５において、シュラウド２、拡大キャビ
ティ６、穴７の配置は図３に示す実施の第１形態と同じ
であり、拡大キャビティ６は動翼のマルチホール２４に
連通している。その他の構造は図３に示す実施の第１形
態と同じである。5, the arrangement of the shroud 2, the enlarged cavity 6, and the hole 7 is the same as that of the first embodiment shown in FIG. 3, and the enlarged cavity 6 communicates with the multihole 24 of the rotor blade. Other structures are the same as those of the first embodiment shown in FIG.
【００２３】上記の実施の第２形態の動翼において、従
来例でも説明したように冷却空気３０は動翼の基部より
翼内部に流入し、ピンフィン２５により対流を促進して
基部側を冷却し、マルチホール２４を通って先端部を冷
却し、その後シュラウド２内に流入する。シュラウド２
には多数のマルチホール２４と拡大シュラウド６とが連
通しているので、冷却空気は拡大キャビティ６内を満た
し、所定の圧力以上となるとシュラウド２周辺の穴７よ
り下向きに流出し、実施の第１形態と同様にシュラウド
２全面及び周辺を均一に冷却することができる。In the moving blade of the second embodiment, as described in the conventional example, the cooling air 30 flows into the inside of the blade from the base of the moving blade and promotes convection by the pin fins 25 to cool the base side. , Cools the tip through the multi-hole 24, and then flows into the shroud 2. Shroud 2
Since the multi-hole 24 and the enlarged shroud 6 communicate with each other, the cooling air fills the enlarged cavity 6 and flows downward from the hole 7 around the shroud 2 when the pressure exceeds a predetermined pressure. As in the first embodiment, the entire surface and the periphery of the shroud 2 can be uniformly cooled.
【００２４】[0024]
【発明の効果】本発明の（１）のガスタービン動翼は、
翼先端にシュラウドを有し、同翼の内部に基部から先端
に向けて冷却通路を設けて冷却空気を流して前記シュラ
ウド内に導き、同シュラウドの周囲より流出させるガス
タービンの動翼において、前記シュラウド内部には周囲
を残して拡大キャビティを形成し、同拡大キャビティは
前記動翼の冷却通路に連通すると共に、前記シュラウド
内で対向する両側に伸び周辺において下方に屈曲して同
シュラウド下面に開口する複数の穴に連通することを特
徴としている。このような構成により、拡大キャビティ
でシュラウドの主要部を冷却し、周辺の穴より流出する
冷却空気によりシュラウドの周囲を冷却するので、シュ
ラウド全面にわたって均一に冷却することができる。The gas turbine rotor blade (1) of the present invention has the following features.
A blade of a gas turbine having a shroud at a blade tip, providing a cooling passage from a base to a tip inside the blade, flowing cooling air into the shroud, and flowing out from around the shroud. An enlarged cavity is formed inside the shroud while leaving a periphery, and the enlarged cavity communicates with the cooling passage of the blade, extends on both sides facing the inside of the shroud, bends downward at the periphery, and opens to the lower surface of the shroud. It is characterized in that it communicates with a plurality of holes. With such a configuration, the main portion of the shroud is cooled by the enlarged cavity, and the periphery of the shroud is cooled by the cooling air flowing out from the peripheral holes, so that the entire shroud can be uniformly cooled.
【００２５】本発明の（２）は、上記（１）の発明にお
いて、前記動翼の冷却通路は翼全長にわたった一体の空
胴からなり、同空胴内壁には多数のピンフィンを設けた
ことを特徴としている。又、（３）の発明は、上記
（１）の発明において、前記動翼の冷却通路は翼の基部
側が一体の空胴と同空胴に設けた多数のピンフィン、先
端側が先端に向かう多数の細穴からなることを特徴とし
ている。このような構成により、（１）のシュラウドが
各種の冷却構造を有する動翼の先端にも適用でき、動翼
の冷却効果とシュラウドの均一な冷却効果との相乗効果
により動翼全体を効果的に冷却することができる。According to a second aspect of the present invention, in the first aspect of the present invention, the cooling passage of the rotor blade includes an integral cavity extending over the entire length of the blade, and a number of pin fins are provided on the inner wall of the cavity. It is characterized by: According to a third aspect of the present invention, in the first aspect of the present invention, the cooling passage of the rotor blade has a cavity in which a base portion of the blade is an integral cavity, a large number of pin fins provided in the cavity, and a large number of pin fins whose leading end faces the distal end. It is characterized by a small hole. With such a configuration, the shroud of (1) can be applied to the tip of a moving blade having various cooling structures, and the entire moving blade can be effectively controlled by a synergistic effect of a cooling effect of the moving blade and a uniform cooling effect of the shroud. Can be cooled.
【図１】本発明の実施の第１形態に係るガスタービン動
翼の縦断面図である。FIG. 1 is a longitudinal sectional view of a gas turbine bucket according to a first embodiment of the present invention.
【図２】図１におけるＡ−Ａ断面図である。FIG. 2 is a sectional view taken along line AA in FIG.
【図３】図１におけるＢ−Ｂ断面図である。FIG. 3 is a sectional view taken along line BB in FIG.
【図４】図３におけるＣ−Ｃ断面図である。FIG. 4 is a sectional view taken along the line CC in FIG. 3;
【図５】本発明の実施の第２形態に係るガスタービン動
翼のシュラウドの断面図である。FIG. 5 is a sectional view of a shroud of a gas turbine rotor blade according to a second embodiment of the present invention.
【図６】図５におけるＤ−Ｄ断面図である。FIG. 6 is a sectional view taken along line DD in FIG. 5;
【図７】従来のガスタービン動翼を示し、（ａ）は縦断
面図、（ｂ）は（ａ）におけるＥ−Ｅ断面図である。7A and 7B show a conventional gas turbine blade, wherein FIG. 7A is a longitudinal sectional view, and FIG. 7B is an EE sectional view in FIG.
【図８】図７におけるＦ−Ｆ断面図である。FIG. 8 is a sectional view taken along line FF in FIG. 7;
【図９】図８におけるＧ−Ｇ断面図である。FIG. 9 is a sectional view taken along line GG in FIG.
１，２１ 動翼 ２ シュラウド ３ 翼根部 ４ リブ ５ ピンフィン ６ 拡大キャビテイ ７ 穴 １０ 内部空洞 ２４ マルチホール ３０ 冷却空気 1, 21 bucket 2 shroud 3 blade root 4 rib 5 pin fin 6 enlarged cavity 7 hole 10 internal cavity 24 multi-hole 30 cooling air
───────────────────────────────────────────────────── フロントページの続き (72)発明者 富田 康意 兵庫県高砂市荒井町新浜２丁目１番１号 三菱重工業株式会社高砂製作所内 ────────────────────────────────────────────────── ─── Continued on the front page (72) Inventor Yasushi Tomita 2-1-1 Shinhama, Arai-machi, Takasago City, Hyogo Prefecture Inside the Mitsubishi Heavy Industries, Ltd. Takasago Machinery Works
Claims (3)
に基部から先端に向けて冷却通路を設けて冷却空気を流
して前記シュラウド内に導き、同シュラウドの周囲より
流出させるガスタービンの動翼において、前記シュラウ
ド内部には周囲を残して拡大キャビティを形成し、同拡
大キャビティは前記動翼の冷却通路に連通すると共に、
前記シュラウド内で対向する両側に伸び周辺において下
方に屈曲して同シュラウド下面に開口する複数の穴に連
通することを特徴とするガスタービン動翼。1. A gas turbine having a shroud at a blade tip, a cooling passage provided inside the blade from a base to a tip, and flowing cooling air into the shroud to flow out from around the shroud. In the rotor blade, an enlarged cavity is formed inside the shroud leaving a periphery, and the enlarged cavity communicates with a cooling passage of the rotor blade,
A gas turbine rotor blade which extends to opposite sides in the shroud, bends downward at the periphery, and communicates with a plurality of holes opened on the lower surface of the shroud.
一体の空胴からなり、同空胴内壁には多数のピンフィン
を設けたことを特徴とする請求項１記載のガスタービン
動翼。2. The gas turbine rotor blade according to claim 1, wherein the cooling passage of the rotor blade comprises an integral cavity extending over the entire length of the blade, and a plurality of pin fins are provided on the inner wall of the cavity. .
の空胴と同空胴に設けた多数のピンフィン、先端側が先
端に向かう多数の細穴からなることを特徴とする請求項
１記載のガスタービン動翼。3. The cooling passage of the rotor blade comprises a cavity on the base side of the blade, a number of pin fins provided in the cavity, and a number of narrow holes on the tip side toward the tip. A gas turbine blade as described.
Priority Applications (7)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP02330598A JP3426948B2 (en) | 1998-02-04 | 1998-02-04 | Gas turbine blade |
| DE69931088T DE69931088T2 (en) | 1998-02-04 | 1999-02-01 | Gas turbine rotor blade |
| EP03025023.7A EP1391581B1 (en) | 1998-02-04 | 1999-02-01 | Gas turbine moving blade |
| EP09178798.6A EP2157280B1 (en) | 1998-02-04 | 1999-02-01 | Gas turbine rotor blade |
| EP99102032A EP0935052B1 (en) | 1998-02-04 | 1999-02-01 | Gas turbine rotor blade |
| US09/243,821 US6152695A (en) | 1998-02-04 | 1999-02-03 | Gas turbine moving blade |
| CA002261107A CA2261107C (en) | 1998-02-04 | 1999-02-03 | Gas turbine moving blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP02330598A JP3426948B2 (en) | 1998-02-04 | 1998-02-04 | Gas turbine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH11223101A true JPH11223101A (en) | 1999-08-17 |
| JP3426948B2 JP3426948B2 (en) | 2003-07-14 |
Family
ID=12106903
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP02330598A Expired - Lifetime JP3426948B2 (en) | 1998-02-04 | 1998-02-04 | Gas turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3426948B2 (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009168014A (en) * | 2008-01-10 | 2009-07-30 | General Electric Co <Ge> | Turbine blade tip shroud |
| JP2013117227A (en) * | 2011-12-01 | 2013-06-13 | General Electric Co <Ge> | Cooled turbine blade and method for cooling turbine blade |
| JP2013194733A (en) * | 2012-03-15 | 2013-09-30 | General Electric Co <Ge> | Turbo-machine blade for improving stiffness to weight ratio |
| US20170114648A1 (en) * | 2015-10-27 | 2017-04-27 | General Electric Company | Turbine bucket having cooling passageway |
| JP2017210959A (en) * | 2016-05-24 | 2017-11-30 | ゼネラル・エレクトリック・カンパニイ | Cooling passage for gas turbine rotor blade |
| US9885243B2 (en) | 2015-10-27 | 2018-02-06 | General Electric Company | Turbine bucket having outlet path in shroud |
| US10508554B2 (en) | 2015-10-27 | 2019-12-17 | General Electric Company | Turbine bucket having outlet path in shroud |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140023497A1 (en) * | 2012-07-19 | 2014-01-23 | General Electric Company | Cooled turbine blade tip shroud with film/purge holes |
-
1998
- 1998-02-04 JP JP02330598A patent/JP3426948B2/en not_active Expired - Lifetime
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009168014A (en) * | 2008-01-10 | 2009-07-30 | General Electric Co <Ge> | Turbine blade tip shroud |
| JP2013117227A (en) * | 2011-12-01 | 2013-06-13 | General Electric Co <Ge> | Cooled turbine blade and method for cooling turbine blade |
| JP2013194733A (en) * | 2012-03-15 | 2013-09-30 | General Electric Co <Ge> | Turbo-machine blade for improving stiffness to weight ratio |
| US20170114648A1 (en) * | 2015-10-27 | 2017-04-27 | General Electric Company | Turbine bucket having cooling passageway |
| US9885243B2 (en) | 2015-10-27 | 2018-02-06 | General Electric Company | Turbine bucket having outlet path in shroud |
| US10156145B2 (en) * | 2015-10-27 | 2018-12-18 | General Electric Company | Turbine bucket having cooling passageway |
| US10508554B2 (en) | 2015-10-27 | 2019-12-17 | General Electric Company | Turbine bucket having outlet path in shroud |
| US11078797B2 (en) | 2015-10-27 | 2021-08-03 | General Electric Company | Turbine bucket having outlet path in shroud |
| JP2017210959A (en) * | 2016-05-24 | 2017-11-30 | ゼネラル・エレクトリック・カンパニイ | Cooling passage for gas turbine rotor blade |
Also Published As
| Publication number | Publication date |
|---|---|
| JP3426948B2 (en) | 2003-07-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2157280B1 (en) | Gas turbine rotor blade | |
| JP4713423B2 (en) | Oblique tip hole turbine blade | |
| JP3367697B2 (en) | Blades for turbines | |
| JP5848019B2 (en) | Turbine bucket with radial cooling holes | |
| JP3632003B2 (en) | Gas turbine split ring | |
| JP4902157B2 (en) | Turbine blade with a groove at the tip | |
| US8864438B1 (en) | Flow control insert in cooling passage for turbine vane | |
| CN101749053B (en) | hollow channel | |
| JP3510467B2 (en) | Gas turbine blades | |
| JP2010509532A (en) | Turbine blade | |
| US8267659B2 (en) | Turbine blade | |
| CA2480393C (en) | Impingement cooling of gas turbine blades or vanes | |
| US20080019834A1 (en) | Cooling fan for rotating machine | |
| JPH112101A (en) | Gas turbine cooling moving blade | |
| JPH09273401A (en) | Turbine cooling device | |
| US5779447A (en) | Turbine rotor | |
| JPH11223101A (en) | Gas turbine moving blade | |
| JPH0828303A (en) | Moving blade of gas turbine | |
| JPS6380004A (en) | Gas turbine stator blade | |
| JP5524137B2 (en) | Gas turbine blade | |
| US20150184525A1 (en) | Structural configurations and cooling circuits in turbine blades | |
| JPH11229808A (en) | Gas turbine rotor blade | |
| JPH11223102A (en) | Gas turbine moving blade | |
| JP3546134B2 (en) | Gas turbine blade | |
| JP3403051B2 (en) | Gas turbine blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20030415 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20080509 Year of fee payment: 5 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090509 Year of fee payment: 6 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090509 Year of fee payment: 6 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100509 Year of fee payment: 7 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110509 Year of fee payment: 8 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120509 Year of fee payment: 9 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20130509 Year of fee payment: 10 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20140509 Year of fee payment: 11 |
|
| S531 | Written request for registration of change of domicile |
Free format text: JAPANESE INTERMEDIATE CODE: R313531 |
|
| S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313111 |
|
| R360 | Written notification for declining of transfer of rights |
Free format text: JAPANESE INTERMEDIATE CODE: R360 |
|
| R370 | Written measure of declining of transfer procedure |
Free format text: JAPANESE INTERMEDIATE CODE: R370 |
|
| R370 | Written measure of declining of transfer procedure |
Free format text: JAPANESE INTERMEDIATE CODE: R370 |
|
| S111 | Request for change of ownership or part of ownership |
Free format text: JAPANESE INTERMEDIATE CODE: R313111 |
|
| R350 | Written notification of registration of transfer |
Free format text: JAPANESE INTERMEDIATE CODE: R350 |
|
| R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
| EXPY | Cancellation because of completion of term |