JPH0421042B2 - - Google Patents
Info
- Publication number
- JPH0421042B2 JPH0421042B2 JP58105932A JP10593283A JPH0421042B2 JP H0421042 B2 JPH0421042 B2 JP H0421042B2 JP 58105932 A JP58105932 A JP 58105932A JP 10593283 A JP10593283 A JP 10593283A JP H0421042 B2 JPH0421042 B2 JP H0421042B2
- Authority
- JP
- Japan
- Prior art keywords
- blade body
- passage
- blade
- cooling fluid
- cavity
- 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.)
- Expired - Lifetime
Links
- 239000012809 cooling fluid Substances 0.000 claims description 32
- 238000001816 cooling Methods 0.000 claims description 14
- 239000007789 gas Substances 0.000 description 12
- 239000000567 combustion gas Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000005495 investment casting Methods 0.000 description 2
- 238000005192 partition Methods 0.000 description 2
- 238000005266 casting Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000011295 pitch Substances 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
【発明の詳細な説明】
〔発明の技術分野〕
本発明は、冷却構造を改良したガスタービンの
翼に関する。DETAILED DESCRIPTION OF THE INVENTION [Technical Field of the Invention] The present invention relates to a gas turbine blade having an improved cooling structure.
ガスタービンは、通常、１つの軸に圧縮機とタ
ービンとを連結し、圧縮機で圧縮された高圧空気
で燃焼器内の圧力を高め、この状態で燃焼器内に
燃料を噴射して燃焼させ、この燃焼によつて生じ
た高温、高圧のガスをタービンに導いて膨張させ
ることにより回転動力を得るように構成されてい
る。圧縮機は、通常、案内翼と回転翼とを軸方向
に交互に配列して構成され、また、タービンも動
翼と静翼とを軸方向に交互に配列して構成されて
いる。
A gas turbine usually has a compressor and a turbine connected to a single shaft, uses high-pressure air compressed by the compressor to increase the pressure in the combustor, and in this state fuel is injected into the combustor and combusted. The high-temperature, high-pressure gas produced by this combustion is guided to a turbine and expanded to obtain rotational power. Compressors are usually configured with guide vanes and rotor blades arranged alternately in the axial direction, and turbines are also configured with moving blades and stationary blades alternately arranged in the axial direction.
ところで、上記のようなガスタービンにおい
て、出力効率を高めるにはタービンの入口におけ
る燃焼ガスの温度を高めることが最も有効である
と云われている。しかし、タービンの入口ガス温
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特性等により制限される。
そこで、従来、翼本体の耐熱特性を向上させるた
めに翼本体を冷却流体によつて強制冷却するよう
にした翼が用いられている。すなわち、翼根部お
よび翼本体内に冷却流体の通路を形成し、この通
路内に翼根部側から冷却流体を導いて翼本体を内
側から対流冷却するとともに上記通路を通過した
冷却流体を翼本体の前縁部、後縁部および側縁部
から翼本体外へ流出させることによつて翼本体の
外面をフイルム冷却するようにした翼が用いられ
ている。 By the way, in the above gas turbine, it is said that the most effective way to increase the output efficiency is to increase the temperature of the combustion gas at the inlet of the turbine. However, the inlet gas temperature of the turbine is limited by the thermal stress resistance or high-temperature oxidation/corrosion characteristics of the materials forming the turbine blades.
Therefore, in the past, blades have been used in which the blade body is forcibly cooled with a cooling fluid in order to improve the heat resistance characteristics of the blade body. That is, a cooling fluid passage is formed in the blade root and the blade body, and the cooling fluid is guided into this passage from the blade root side to convection cool the blade body from the inside, and the cooling fluid that has passed through the passage is transferred to the blade body. A blade is used in which the outer surface of the blade body is film-cooled by allowing the film to flow out of the blade body from the leading edge, trailing edge, and side edge.
しかしながら、上記のように、冷却流体を使つ
て翼本体を内外から冷却するようにした翼にあつ
ても次のような問題があつた。すなわち、翼根部
から導かれた冷却流体を翼本体内において分岐さ
せ、翼本体の前縁部、後縁部および側縁部から翼
本体外へ流出させるようにしているので必然的に
翼本体の先端部を冷却する冷却流体の量が少なく
なり、この結果、他の部分に較べて翼本体の先端
部の温度上昇が大きく、特に燃焼ガスが直接衝突
する先端部の前縁部は温度上昇が大きく、この温
度上昇に基いてガス温度が制限される問題があつ
た。 However, as described above, even with blades that use cooling fluid to cool the blade body from the inside and outside, the following problems still occur. In other words, since the cooling fluid led from the blade root is branched within the blade body and flowed out of the blade body from the leading edge, trailing edge, and side edge of the blade body, it is inevitable that the cooling fluid The amount of cooling fluid that cools the tip is reduced, and as a result, the temperature rise at the tip of the blade body is greater than in other parts, especially the leading edge of the tip where the combustion gas directly impinges. A major problem was that the gas temperature was limited based on this temperature rise.
本発明は、このような事情に鑑みてなされたも
ので、その目的とするところは、翼本体を全体に
亘つて良好に冷却でき、もつてガス温度の高温
化、すなわち出力効率の向上化に寄与できるガス
タービンの翼を提供することにある。
The present invention was made in view of the above circumstances, and its purpose is to be able to cool the entire blade body well, thereby increasing the gas temperature, that is, improving the output efficiency. The objective is to provide gas turbine blades that can contribute to the development of gas turbines.
本発明は、翼本体内に冷却流体の通路を直接形
成し、この通路に導かれた冷却流体で翼本体を内
部から冷却するとともに通路を通過した冷却流体
を翼本体外へ流出させて翼本体を外部からも冷却
できるようにしたガスタービンの翼において、翼
本体内の先端壁内に翼本体の最前縁部近傍からキ
ヤンバ線に沿つて翼本体の最後縁近傍まで形成さ
れた空洞と、通路内に導かれた冷却流体の一部を
少なくとも前記翼本体内の前縁部近傍から前記空
洞内に導く導入口と、この導入口から導かれた冷
却流体を空洞内を翼本体の前縁部からキヤンバ線
に沿つて翼本体の後縁部まで略全域にわたつて連
続的に通流させ、空洞内がほぼ均一な温度となる
ように冷却した後に翼本体外へ流出させる排出孔
と、
を具備してなることを特徴としている。
The present invention forms cooling fluid passages directly within the blade body, cools the blade body from the inside with the cooling fluid guided through the passage, and allows the cooling fluid that has passed through the passage to flow out of the blade body. In a gas turbine blade that can also be cooled from the outside, a cavity and a passage are formed in the tip wall of the blade body from near the leading edge of the blade body to near the rearmost edge of the blade body along the camber line. an inlet for introducing a portion of the cooling fluid into the cavity from at least the vicinity of the leading edge of the blade body; a discharge hole that allows the flow to flow continuously over almost the entire area from the camber line to the trailing edge of the blade body, cools the inside of the cavity to a substantially uniform temperature, and then flows out of the blade body; It is characterized by the following:
上記のように翼本体の先端壁内に空洞を設け、
この空洞内にも冷却流体を通流させるようにして
いるので、翼本体の先端部の冷却不足を解消する
ことができる。この場合、空洞への冷却流体の入
口および出口の径を所望に設定することによつて
空洞内での流速を十分高めることができ、この結
果、先端部を良好に冷却することが可能となる。
したがつて翼本体を内、外から冷却したことと相
俟つて翼本体全体を良好に冷却でき、ガス温度の
高温化に寄与できるものが得られる。
As mentioned above, a cavity is provided in the tip wall of the wing body,
Since the cooling fluid is allowed to flow through this cavity as well, it is possible to solve the problem of insufficient cooling of the tip of the blade body. In this case, by setting the diameters of the inlet and outlet of the cooling fluid to the cavity as desired, the flow velocity within the cavity can be sufficiently increased, and as a result, the tip can be cooled well. .
Therefore, in combination with the fact that the blade body is cooled from the inside and outside, the entire blade body can be cooled well, and it is possible to obtain something that can contribute to increasing the gas temperature.
以下本発明の実施例を図面を参照しながら説明
する。
Embodiments of the present invention will be described below with reference to the drawings.
第１図は、本発明を適用した動翼をキヤンバ線
に沿つて切断して示す図である。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およびプラツトホーム部３と
で構成されている。翼本体１、翼根部２およびプ
ラツトホーム部３は、翼本体１の先端壁４を除い
て精密鋳造によつて一体的に形成されたもので、
鋳造後に、同じく精密鋳造等によつて形成された
上記先端壁４を溶接あるいは拡散接合等によつて
接合したものとなつている。 FIG. 1 is a diagram showing a rotor blade to which the present invention is applied, cut along a camber line. That is, this rotor blade can be roughly divided into a blade body 1 and a blade body 1.
It consists of a blade root part 2 and a platform part 3 that support the blade. The blade body 1, the blade root part 2, and the platform part 3 are integrally formed by precision casting, except for the tip wall 4 of the blade body 1.
After casting, the tip wall 4, which was also formed by precision casting, is joined by welding, diffusion bonding, or the like.
しかして、上記翼本体１および翼根部２の内部
には冷却流体の通路１１が形成されており、ま
た、先端壁４の内部には通路１１から分岐した冷
却流体の一部を通流させる通路１２が形成されて
いる。 A passage 11 for the cooling fluid is formed inside the blade body 1 and the blade root 2, and a passage branched from the passage 11 through which a part of the cooling fluid flows is formed inside the tip wall 4. 12 are formed.
上記通路１１は、翼根部２から翼本体１の先端
壁４まで高さ方向に延びた第１の通路１３と、こ
の通路１３と翼本体１１の前縁部外面との間に上
記第１の通路１３と平行に高さ方向に延びた第２
の通路１４と、上記第１の通路１３と翼本体１１
の後縁部外面との間に上記第１の通路１３と平行
に高さ方向に延びた第３の通路１５と、第１の通
路１３と第２の通路１４との間に存在する仕切壁
１６に高さ方向に複数設けられた小孔１７と、翼
本体１の前縁部外面と第２の通路１４との間に存
在する壁１８に高さ方向に複数設けられた小孔１
９と、前記第１の通路１３と第３の通路１５との
間に存在する仕切壁２０に高さ方向に複数設けら
れた小孔２１と、翼本体１の後縁部外面と第３の
通路１５との間に存在する壁２２に高さ方向に複
数設けられた小孔２３とで構成されている。 The passage 11 includes a first passage 13 extending in the height direction from the blade root 2 to the tip wall 4 of the blade body 1, and a first passage 13 between the passage 13 and the outer surface of the leading edge of the blade body 11. A second tube extending in the height direction parallel to the passage 13
passage 14, the first passage 13 and the wing body 11.
a third passage 15 extending in the height direction parallel to the first passage 13 between the rear edge outer surface and a partition wall existing between the first passage 13 and the second passage 14; A plurality of small holes 17 are provided in the height direction in the wall 18 between the leading edge outer surface of the blade body 1 and the second passage 14.
9, a plurality of small holes 21 provided in the height direction in the partition wall 20 existing between the first passage 13 and the third passage 15, and the outer surface of the trailing edge of the wing body 1 and the third It is composed of a plurality of small holes 23 provided in the height direction in the wall 22 existing between the passage 15 and the passage 15.
一方、通路１２は、先端壁４の内部にキヤンバ
線方向に延びる関係に形成された空洞２５と、前
記第２の通路１４と上記空洞２５内の前縁部側と
を連通させる導入口２６と、空洞２５の後縁部側
を翼本体外へ通じさせる排出口２７とで構成され
ている。 On the other hand, the passage 12 includes a cavity 25 formed inside the tip wall 4 extending in the camber line direction, and an introduction port 26 that communicates the second passage 14 with the front edge side of the cavity 25. , and a discharge port 27 that communicates the trailing edge side of the cavity 25 to the outside of the wing body.
このような構成であると、通路１１の第１の通
路１３に、図中実線矢印で示すように冷却流体を
導入すると、この冷却流体は、第１の通路１３内
を翼本体１の先端方向へと流れ、この間に翼本体
１の中央部分を対流冷却によつて内側から冷却す
る。そして、第１の通路１３内の冷却流体は、第
２図にも示すように、次に２つの流れに分岐さ
れ、一方においては小孔１７から壁１８の内面に
向けて噴射され、壁１８をインピンジ冷却した
後、一部が小孔１９から噴出して翼本体１の周面
に冷却流体の膜を形成するフイルム冷却に供さ
れ、また残りが前縁部近傍に設けられた導入口２
６を介して空洞２５内に流れ込む。また、他方に
おいては小孔２１から壁２２の内面に向けて噴射
され、壁２２をインピンジ冷却し、続いて小孔２
３から噴出し、小孔２３内を通る間に壁２２を対
流冷却する。そして、空洞２５内の前縁側に流れ
込んだ冷却流体は、最初に温度上昇の大きい前縁
側を冷却した後、空洞２５内を燃焼ガスの圧力の
高い前縁側からガスの圧力の低い後縁側へとスム
ーズに流れ、その間に対流冷却によつて先端壁４
を冷却した後、排出口２７を介して翼本体外へと
流出する。したがつて、翼本体１は、その中央
部、前縁部、後縁部および先端壁４の全てが、冷
却流体による対流冷却、インピンジ冷却あるいは
フイルム冷却によつて冷却されることになり、従
来の翼のように局部的に非常に高温になるところ
がないので、結局、前述した効果が得られる。 With such a configuration, when the cooling fluid is introduced into the first passage 13 of the passage 11 as shown by the solid line arrow in the figure, the cooling fluid flows inside the first passage 13 toward the tip of the blade body 1. During this time, the central portion of the blade body 1 is cooled from the inside by convection cooling. The cooling fluid in the first passage 13 is then branched into two streams, as shown in FIG. After being impinged cooled, a portion is ejected from the small hole 19 and used for film cooling to form a film of cooling fluid on the circumferential surface of the blade body 1, and the rest is provided through the inlet 2 provided near the leading edge.
6 into the cavity 25. On the other hand, the water is injected from the small hole 21 toward the inner surface of the wall 22, impingement-cooling the wall 22, and then
3 and cools the wall 22 by convection while passing through the small hole 23. The cooling fluid flowing into the leading edge side of the cavity 25 first cools the leading edge side where the temperature rise is large, and then flows inside the cavity 25 from the leading edge side where the combustion gas pressure is high to the trailing edge side where the gas pressure is low. It flows smoothly, during which the tip wall 4 is cooled by convection cooling.
After being cooled, it flows out of the blade body through the outlet 27. Therefore, the center, leading edge, trailing edge, and tip wall 4 of the blade body 1 are all cooled by convection cooling, impingement cooling, or film cooling using a cooling fluid, which is different from conventional methods. Since there is no place where the temperature locally becomes extremely high as in the case of the blade, the above-mentioned effect can be obtained.
ここで、対流による熱伝達を表わすヌツセルト
数Nuは、一般に、
Nu∝RemPrn
の形で表現される。但し、Reはレイノルズ数、
Prはプラントル数を示し、ｍ、ｎは定数を示し
ている。レイノルズ数Reは流体の流速が速い程
大きい。したがつて、導入口２６および排出口２
７の径を選択すれば、空洞２５内の冷却流体の流
速を速めることができ、これによつて先端壁４を
良好に冷却できる。このことは、第２の通路１４
の先端側位置（流量の少ない位置）から空洞２５
内に冷却流体を送り込むようにしても空洞２５内
の流体制御によつて良好に冷却できることを意味
している。 Here, the Nutsselt number Nu, which represents heat transfer by convection, is generally expressed in the form Nu∝Re m Pr n . However, Re is the Reynolds number,
Pr represents Prandtl's number, and m and n represent constants. The Reynolds number Re increases as the flow velocity of the fluid increases. Therefore, the inlet 26 and the outlet 2
If a diameter of 7 is selected, the flow velocity of the cooling fluid in the cavity 25 can be increased, thereby allowing the tip wall 4 to be cooled well. This means that the second passage 14
from the tip side position (position with low flow rate) to the cavity 25
This means that even if cooling fluid is sent into the cavity 25, good cooling can be achieved by controlling the fluid inside the cavity 25.
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。たとえば、第３図ａ，ｂに示すよう
に空洞２５の内面にキヤンバ線と交差するように
凸部３１を設け、この凸部３１で通流する冷却流
体を積極的に撹拌させることによつて対流冷却効
果を向上させるようにしてもよい。また、第４図
ａ，ｂに示すように、第１の通路１３および第３
の通路１５からも孔３２，３３を介して空洞２５
内に冷却流体を送り込むようにしてもよい。この
場合、孔３２，３３の径および配設ピツチの選択
によつて孔３２，３３から噴出する冷却流体でキ
ヤンバ線に沿つた所望のインピンジ冷却特性を発
揮させることができる。また、第１の通路１３の
存在によつて翼本体１の腹側に形成された壁にフ
イルム冷却用の小孔を設けるようにしてもよい。 Note that the present invention is not limited to the embodiments described above. For example, as shown in FIGS. 3a and 3b, a convex portion 31 is provided on the inner surface of the cavity 25 so as to intersect with the camber line, and the cooling fluid flowing through the convex portion 31 is actively stirred. The convection cooling effect may be improved. In addition, as shown in FIGS. 4a and 4b, the first passage 13 and the third
The passage 15 also passes through the holes 32 and 33 to the cavity 25.
Cooling fluid may also be pumped into the interior. In this case, by selecting the diameters and arrangement pitches of the holes 32, 33, the cooling fluid ejected from the holes 32, 33 can exhibit desired impingement cooling characteristics along the camber line. Furthermore, due to the presence of the first passage 13, a small hole for cooling the film may be provided in the wall formed on the ventral side of the blade body 1.
第１図は本発明の一実施例に係る翼をキヤンバ
線に沿つて切断した縦断面図、第２図は同翼を第
１図におけるＡ−Ａ線に沿つて切断し矢印方向に
みた図、第３図ａは本発明の別の実施例に係る翼
を局部的に取り出して示す縦断面図、同図ｂは同
翼をａにおけるＢ−Ｂ線に沿つて切断し矢印方向
にみた図、第４図ａは本発明のさらに別の実施例
に係る翼を局部的に取り出して示す縦断面図、同
図ｂは同翼をａにおけるＣ−Ｃ線に沿つて切断し
矢印方向にみた図である。
１…翼本体、２…翼根部、４…先端壁、１１…
通路、２５…空洞、２６…導入口、２７…排出
口。
FIG. 1 is a longitudinal cross-sectional view of a wing according to an embodiment of the present invention taken along a camber line, and FIG. 2 is a view of the same wing taken along line A-A in FIG. 1 and viewed in the direction of the arrow. , FIG. 3a is a vertical cross-sectional view partially taken out of a blade according to another embodiment of the present invention, and FIG. 3b is a view of the same blade cut along line B-B in a and viewed in the direction of the arrow , FIG. 4a is a longitudinal cross-sectional view showing a partially taken out blade according to yet another embodiment of the present invention, and FIG. It is a diagram. 1...Blade body, 2...Blade root, 4...Tip wall, 11...
Passage, 25...Cavity, 26...Inlet, 27...Outlet.
Claims (1)
の通路に導かれた冷却流体で翼本体を内部から冷
却するとともに前記通路を通過した冷却流体を翼
本体外へ流出させて前記翼本体を外部からも冷却
できるようにしたガスタービンの翼において、 前記翼本体内の先端壁内に前記翼本体の最前縁
部近傍からキヤンバ線に沿つて前記翼本体の最後
縁近傍まで形成された空洞と、 前記通路内に導かれた冷却流体の一部を少なく
とも前記翼本体内の前縁部近傍から前記空洞内に
導く導入口と、 この導入口から導かれた冷却流体を前記空洞内
を前記翼本体の前縁部からキヤンバ線に沿つて前
記翼本体の後縁部まで略全域にわたつて連続的に
通流させ、前記空洞内がほぼ均一な温度となるよ
うに冷却した後に前記翼本体外へ流出させる排出
孔と、 を具備してなることを特徴とするガスタービンの
翼。 ２ 前記空洞は、内面に凸部が形成されたもので
あることを特徴とする特許請求の範囲第１項記載
のガスタービンの翼。[Claims] 1. A cooling fluid passage is formed directly within the blade body, and the cooling fluid guided through the passage cools the blade body from within, and the cooling fluid that has passed through the passage flows out of the blade body. In the blade of a gas turbine, the blade body can be cooled from the outside by cooling the blade body from the vicinity of the leading edge of the blade body along the camber line to the vicinity of the rearmost edge of the blade body within the tip wall of the blade body. an inlet for introducing a portion of the cooling fluid introduced into the passage into the cavity from at least the vicinity of the leading edge in the blade body; and an inlet for introducing the cooling fluid introduced from the inlet into the cavity. The inside of the cavity is cooled so that the inside of the cavity has a substantially uniform temperature by flowing continuously over substantially the entire area from the leading edge of the wing main body to the trailing edge of the wing main body along the camber line. A gas turbine blade, comprising: a discharge hole that allows the air to flow out of the blade body after the air is removed. 2. The gas turbine blade according to claim 1, wherein the cavity has a convex portion formed on its inner surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10593283A JPS59231102A (en) | 1983-06-15 | 1983-06-15 | Gas turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10593283A JPS59231102A (en) | 1983-06-15 | 1983-06-15 | Gas turbine blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS59231102A JPS59231102A (en) | 1984-12-25 |
| JPH0421042B2 true JPH0421042B2 (en) | 1992-04-08 |
Family
ID=14420621
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10593283A Granted JPS59231102A (en) | 1983-06-15 | 1983-06-15 | Gas turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS59231102A (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5720431A (en) * | 1988-08-24 | 1998-02-24 | United Technologies Corporation | Cooled blades for a gas turbine engine |
| US5975851A (en) * | 1997-12-17 | 1999-11-02 | United Technologies Corporation | Turbine blade with trailing edge root section cooling |
| DE50309922D1 (en) * | 2003-07-29 | 2008-07-10 | Siemens Ag | Chilled turbine blade |
| US7413403B2 (en) * | 2005-12-22 | 2008-08-19 | United Technologies Corporation | Turbine blade tip cooling |
| EP2426316A1 (en) * | 2010-09-03 | 2012-03-07 | Siemens Aktiengesellschaft | Turbine blade |
| DE102013224998A1 (en) * | 2013-12-05 | 2015-06-11 | Rolls-Royce Deutschland Ltd & Co Kg | Turbine rotor blade of a gas turbine and method for cooling a blade tip of a turbine rotor blade of a gas turbine |
| US9835087B2 (en) * | 2014-09-03 | 2017-12-05 | General Electric Company | Turbine bucket |
| US10508554B2 (en) | 2015-10-27 | 2019-12-17 | 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 |
| US9885243B2 (en) | 2015-10-27 | 2018-02-06 | General Electric Company | Turbine bucket having outlet path in shroud |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS4865313A (en) * | 1971-12-14 | 1973-09-08 | ||
| JPS5114519A (en) * | 1974-07-25 | 1976-02-05 | Mitsui Shipbuilding Eng | REIKYAKUTAABINDOYOKU |
| JPS5465209A (en) * | 1977-10-08 | 1979-05-25 | Rolls Royce | Cooling type rotor blade |
| JPS57173506A (en) * | 1981-03-20 | 1982-10-25 | Gen Electric | Leading end cap having replaceable moving blade |
-
1983
- 1983-06-15 JP JP10593283A patent/JPS59231102A/en active Granted
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS4865313A (en) * | 1971-12-14 | 1973-09-08 | ||
| JPS5114519A (en) * | 1974-07-25 | 1976-02-05 | Mitsui Shipbuilding Eng | REIKYAKUTAABINDOYOKU |
| JPS5465209A (en) * | 1977-10-08 | 1979-05-25 | Rolls Royce | Cooling type rotor blade |
| JPS57173506A (en) * | 1981-03-20 | 1982-10-25 | Gen Electric | Leading end cap having replaceable moving blade |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS59231102A (en) | 1984-12-25 |
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