JP3631898B2 - Cooling structure of split ring in gas turbine - Google Patents

Cooling structure of split ring in gas turbine Download PDF

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Publication number
JP3631898B2
JP3631898B2 JP05044298A JP5044298A JP3631898B2 JP 3631898 B2 JP3631898 B2 JP 3631898B2 JP 05044298 A JP05044298 A JP 05044298A JP 5044298 A JP5044298 A JP 5044298A JP 3631898 B2 JP3631898 B2 JP 3631898B2
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Prior art keywords
cooling
cavity
split ring
upstream
downstream
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JP05044298A
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JPH11247621A (en
Inventor
康司 渡辺
潔 末永
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Priority to JP05044298A priority Critical patent/JP3631898B2/en
Priority to US09/256,102 priority patent/US6146091A/en
Priority to CA002263013A priority patent/CA2263013C/en
Priority to EP99104200A priority patent/EP0940562B1/en
Priority to EP04023188.8A priority patent/EP1500789B1/en
Priority to DE69933601T priority patent/DE69933601T2/en
Publication of JPH11247621A publication Critical patent/JPH11247621A/en
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Description

【０００１】
【発明の属する技術分野】
本発明は、ガスタービンにおいて動翼の半径方向外周側に配置された分割環の冷却構造に関するものである。
【０００２】
【従来の技術】
ガスタービンの全体的な構成は、図７に概略的に示すように、圧縮機１で空気を圧縮し、燃焼器２に燃料を投入して燃焼ガスを生成し、同燃焼ガスを主流ガスとしてタービン３に導入し、発電機４を回転させるようになっている。
【０００３】
この中タービン３は図８に一般的構成を示すように、交互に配列されたそれぞれ複数列の静翼５と動翼６とから成り立っており、動翼６の半径方向外周側は、高温ガスを動翼６と適正な隙間をもって下流側に送るために周方向に複数の分割数をもった分割環（リングセグメント又はチィプシールセグメント）１０で囲われた構造となっている。
【０００４】
そしてこの分割環１０は、燃焼器２から出る高温の主流ガス１５に耐え得る様な冷却構造となっているが、従来のガスタービンにおけるこの冷却構造を有した分割環１０の一例を図３及び図４により説明する。
【０００５】
圧縮機１から抽気した冷却媒体９、もしくは外部に設けた適宜の供給源から供給された冷却媒体９をインピンジメント冷却口１１を形成したインピンジメント冷却板１２を経てキャビティ１６に供給し、分割環１０に当接させて強制冷却した後、同分割環１０内に設けられた冷却通路１３を通して再度分割環１０を冷却し、分割環後部１４より主流ガス１５中に放出する様になっている。
【０００６】
なおここで冷却通路１３は、断面が円形、矩形、又は波状等の形状を選択してよく、同冷却通路１３は軸方向に伸びた複数の孔を周方向略平行に配列して構成されている。
【０００７】
【発明が解決しようとする課題】
しかしながら前記した従来のものにあっては、冷却媒体９は高温の主流ガス１５の逆流を防ぐため、キャビティ１６を主流ガス１５の圧力よりも高く保持する必要があり、そのために分割環外周側のキャビティ１６を軸方向上流側の主流ガス１５より相対的に高い圧力にして冷却媒体９を供給している。
【０００８】
他方、主流ガス１５は軸方向下流側では、前記軸方向上流側に比べて圧力が低下しているので、前記のように軸方向上流側の主流ガス１５との関連で圧力調整されたキャビティ１６内の冷却媒体９では過大な漏れを消費してしまい、タービン効率の低下を招くことになる。
【０００９】
さらには、冷却通路１３内の冷却媒体９は、冷却による熱交換により軸方向下流側に進むにつれ自身が昇温されてゆき、分割環下流側では相当な温度上昇をするため、冷却性能が低下する。
【００１０】
本発明は従来のものにおける前記した不具合点を解消し、ガスタービンの分割環における冷却効率の向上を図るようにした冷却構造を提供することを課題とするものである。
【００１１】
【課題を解決するための手段】
本発明は前記した課題を解決すべくなされたもので、分割環とその外周に配置したインピンジメント冷却板との間を周方向に延びる圧力隔板により軸方向で区画し、それぞれ異なる圧力に調整した上流側キャビティと下流側キャビティを設け、前記上流側キャビティの内部は冷却通路を経て動翼先端部の上流側半分の範囲に開口し、下流側キャビティの内部は他の冷却通路を経て軸方向と平行状に延びて動翼の後流に開口したガスタービンにおける分割環の冷却構造を提供するものである。
【００１２】
即ち本発明によれば、圧力隔板により軸方向で区画した上流側キャビティと下流側キャビティは、それぞれ異なる圧力に調整されるので、軸方向上流と下流で圧力の異なる主流ガスに対して個々に、かつ適切に対応し、上流側では主流ガスの逆流防止を行い、また下流側では隙間からのもれ空気を最小として効率の向上を図る様にしたものである。
【００１４】
しかも前記上流側キャビティの内部は冷却通路を経て動翼先端部の上流側半分の範囲に開口し、下流側キャビティの内部は他の冷却通路を経て軸方向と平行状に延びて動翼の後流に開口することにより軸方向に異なる位置で動翼先端側に開放しているので、各キャビティを出てから動翼先端側に向けて開放されるまでの分割環冷却孔の距離は短縮され、特に前記上流側キャビティからの冷却通路では冷却媒体が温まらないうちに動翼先端に開放されるので、動翼の冷却効果を高め、また、下流側キャビティからの他の冷却通路では軸方向に平行状に延びて冷却媒体を案内することにより分割環の冷却効果を高めるものである。
【００１５】
【発明の実施の形態】
本発明の実施の一形態について図１、図２に基づいて説明する。
なお前記した従来のものと同一の部分については図面中に同一の符号を付して示し、重複する説明は出来るだけ省略して本実施の形態に固有の点について重点的に説明する。
【００１６】
１０は分割環で、動翼先端との隙間をシールするように動翼先端に近接して配置されており、図１および図２では周方向で複数に分割されたものの中一つを代表として抜き出して示している。
【００１７】
１２はインピンジメント冷却板で、分割環１０に対して適当な間隔を離して分割環１０の外周側に同心状に配列される様に遮熱環１９で支持されており、板面に多数設けられたインピンジメント冷却口１１を経て前記分割環１０との間冷却媒体を受け入れるキャビティを形成している。
【００１８】
１８は前記分割環１０の表面に周方向に延びて設けられた溝で、同溝１８には頂面をインピンジメント冷却板１２と当接した圧力隔板１７が嵌められ、前記分割環１０とインピンジメント冷却板１２との間に形成されるキャビティを上流側キャビティ１６ａと下流側キャビティ１６ｂとに区画している。
【００１９】
なお、圧力隔板１７は前記分割環１０及びインピンジメント冷却板１２と同様に、円周方向で複数に分割して構成されてもよく、その場合には周方向の接合部は微小の隙間を残して端面を接合し、微小の漏れが有ってもよいが、図４に示す様に端部接合面を互いに断面方向に切り込んで重ね接合し、密封度を向上することもできる。
【００２０】
また、圧力隔板１７の内周側は前記したように溝１８と嵌合し、これに対向する外周側は図３に示すように逆Ｌ字型としているが、同圧力隔板１７はこの形状に限定されるものではなく、Ｔ字型等その他の形状を選択してもよいことは勿論である。
【００２１】
前記上流側キャビティ１６ａの内部は、冷却通路１３ａを経て動翼６先端部の上流側半分の範囲に開口し、また、下流側キャビティ１６ｂの内部は冷却通路１３ｂを経て軸方向とほぼ平行に延びて動翼６の後流に開口しているので、冷却通路１３ａ及び１３ｂそれぞれの距離は分割環１０及び動翼６先端の軸方向長さに対して十分に短いものとなる。
【００２３】
また、上流側キャビティ１６ａと下流側キャビティ１６ｂそれぞれのインピンジメント冷却板１２には、多数のインピンジメント冷却口１１が設けられているが、前記上流側キャビティ１６ａに開口するインピンジメント冷却口１１と下流側キャビティ１６ｂに開口するインピンジメント冷却口１１とは、その開口径の大きさ、形状、開口数を互いに相違しており、上流側キャビティ１６ａ内は下流側キャビティ１６ｂより高い圧力であり、かつ同上流側キャビティ１６ａ内圧力は上流側主流ガス１５ａを上回り、また下流側キャビティ１６ｂ内圧力は下流側主流ガス１５ｂを上回るように調整されている。
【００２４】
本実施の形態は前記の様に構成されているので、冷却媒体９はインピンジメント冷却板１２のインピンジメント穴１１を通過し、上流側キャビティ１６ａ及び下流側キャビティ１６ｂを形成する分割環１０をインピンジメント冷却したのち軸方向に延びた複数列の分割環冷却通路１３ａ及び１３ｂを通過することにより、分割環１０を再度冷却し、最終的に主流ガス１５中に放出される。
【００２５】
そしてこの分割環冷却構造を構成した上流側キャビティ１６ａ及び下流側キャビティ１６ｂ内に供給される冷却媒体９の圧力が、インピンジメント冷却口１１の開口径の大きさ、形状、開口数等を調整することにより、前記した様に上流側キャビティ１６ａでは上流側燃焼ガス１５ａの圧力より相対的に若干高くし、また下流側キャビティ１６ｂでは、圧力の低下した下流側燃焼ガス１５ｂ圧力よりわずかに高く維持した状態で設定することが可能となったことにより、分割環１０の上流側キャビティ１６ａでは主流燃焼ガス１５ａの逆流の懸念がなく、また、下流側キャビティ１６ｂでは各部隙間からのもれ空気を最小限にとどめることができる。
【００２６】
なお、上流側キャビティ１６ａ及び下流側キャビティ１６ｂ内から、分割環１０の板厚を貫通して設けられた冷却通路１３ａ及び１３ｂを通して冷却媒体９を案内することにより、分割環１０を冷却し、かつ、この冷却媒体９をタービン動翼６先端に向けて吹き出すことによってタービン動翼６の冷却効果も望めるものである。
【００２７】
以上、本発明を図示の実施の形態について説明したが、本発明はかかる実施の形態に限定されず、本発明の範囲内でその具体的構造に種々の変更を加えてよいことはいうまでもない。
【００２８】
たとえば、前記実施の形態においては、インピンジメント冷却板１２と分割環１０との間には、単数の隔壁１７を配設し、上流側キャビティ１６ａと下流側キャビティ１６ｂに区画したものを示したが、複数の隔壁１７で区画して多数のキャビティを形成してよいことは勿論である。
【００２９】
【発明の効果】
以上本発明によれば、分割環とその外周に配置したインピンジメント冷却板との間を周方向に延びる圧力隔板により軸方向で区画し、それぞれ異なる圧力に調整した上流側キャビティと下流側キャビティを設けてガスタービンにおける分割環の冷却構造を構成しているので、圧力隔板により軸方向上流と下流で区画された各キャビティは、それぞれ異なる圧力に調整されて圧力の異なる主流ガスに対して個々に、かつ適切に対応可能となり、上流側では主流ガスの逆流防止を行い、また下流側では隙間からのもれ空気を最小としてガスタービンの効率を一段と向上することができたものである。
【００３０】
しかも本発明によれば、前記上流側キャビティの内部は冷却通路を経て動翼先端部の上流側半分の範囲に開口し、下流側キャビティの内部は他の冷却通路を経て軸方向と平行状に延びて動翼の後流に開口することにより軸方向に異なる位置で動翼先端側に開放してガスタービンにおける分割環の冷却構造を構成しているので、上流側及び下流側の各キャビティから軸方向に異なる位置で動翼先端側に開放する分割環冷却孔は、各キャビティを出てから動翼先端側に向けて開放されるまでの分割環冷却孔の距離は短縮され、特に前記上流側キャビティからの冷却通路では冷却媒体が温まらないうちに動翼先端側に開放されるので、動翼先端部をフィルム冷却し、また、下流側キャビティからの他の冷却通路では軸方向に平行状に延びて冷却媒体を案内することにより分割環を十分に冷却して、併せてガスタービン冷却効率を一段と向上することができたものである。
【図面の簡単な説明】
【図１】本発明の実施の一形態に係るガスタービンにおける分割環の冷却構造を一部破断して示す斜視図である。
【図２】本実施形態の分割環の冷却構造の側面断面図である。
【図３】本実施形態の分割環の冷却構造の要部である圧力隔板によるキャビティ分割を示す説明図である。
【図４】図３に示す圧力隔板の分割部の接合状態を示す説明図である。
【図５】従来のガスタービンにおける分割環の冷却構造を一部破断して示す斜視図である。
【図６】従来の分割環の冷却構造の側面断面図である。
【図７】ガスタービンの全体的な構成を概略的に示す説明図である。
【図８】タービン部の一般的構成を概略的に示す説明図である。
【符号の説明】
１ 圧縮機
２ 燃焼器
３ タービン
４ 発電機
５ 静翼
６ 動翼
９ 冷却媒体
１０ 分割環
１１ インピンジメント冷却口
１２ インピンジメント冷却板
１３ 冷却通路
１４ 分割環後部
１３ａ 冷却通路
１３ｂ 冷却通路
１５ 主流ガス
１５ａ 上流側主流ガス
１５ｂ 下流側主流ガス
１６ キャビティ
１６ａ 上流側キャビティ
１６ｂ 下流側キャビティ
１７ 圧力隔板
１８ 溝
１９ 遮熱環[0001]
BACKGROUND OF THE INVENTION
The present invention relates to a cooling structure for a split ring disposed on a radially outer peripheral side of a moving blade in a gas turbine.
[0002]
[Prior art]
As shown schematically in FIG. 7, the overall configuration of the gas turbine is that air is compressed by a compressor 1, fuel is injected into the combustor 2 to generate combustion gas, and the combustion gas is used as a mainstream gas. It introduce | transduces into the turbine 3, and the generator 4 is rotated.
[0003]
As shown in FIG. 8, the turbine 3 is composed of a plurality of rows of stationary blades 5 and moving blades 6 arranged alternately, and the outer peripheral side of the moving blade 6 in the radial direction is a hot gas. In order to send the rotor blade 6 to the downstream side with an appropriate gap, the structure is surrounded by a split ring (ring segment or chip seal segment) 10 having a plurality of split numbers in the circumferential direction.
[0004]
The split ring 10 has a cooling structure that can withstand the high-temperature mainstream gas 15 coming out of the combustor 2. An example of the split ring 10 having this cooling structure in a conventional gas turbine is shown in FIGS. This will be described with reference to FIG.
[0005]
The cooling medium 9 extracted from the compressor 1 or the cooling medium 9 supplied from an appropriate supply source provided outside is supplied to the cavity 16 through the impingement cooling plate 12 in which the impingement cooling port 11 is formed, and the divided ring. Then, the ring 10 is cooled again through a cooling passage 13 provided in the split ring 10, and discharged from the rear part 14 of the split ring into the mainstream gas 15.
[0006]
Here, the cooling passage 13 may have a circular, rectangular, or wavy cross section, and the cooling passage 13 is configured by arranging a plurality of axially extending holes in a substantially parallel circumferential direction. Yes.
[0007]
[Problems to be solved by the invention]
However, in the above-described conventional one, the cooling medium 9 needs to keep the cavity 16 higher than the pressure of the mainstream gas 15 in order to prevent the backflow of the high-temperature mainstream gas 15. The cooling medium 9 is supplied with the cavity 16 at a pressure relatively higher than that of the mainstream gas 15 on the upstream side in the axial direction.
[0008]
On the other hand, since the pressure of the mainstream gas 15 is lower on the downstream side in the axial direction than on the upstream side in the axial direction, the cavity 16 whose pressure is adjusted in relation to the mainstream gas 15 on the upstream side in the axial direction as described above. The inner cooling medium 9 consumes excessive leakage, leading to a decrease in turbine efficiency.
[0009]
Further, the cooling medium 9 in the cooling passage 13 is heated up as it goes downstream in the axial direction due to heat exchange by cooling, and the cooling performance decreases because the temperature rises considerably on the downstream side of the split ring. To do.
[0010]
SUMMARY OF THE INVENTION An object of the present invention is to provide a cooling structure that eliminates the above-described disadvantages of the prior art and improves the cooling efficiency of a split ring of a gas turbine.
[0011]
[Means for Solving the Problems]
The present invention has been made to solve the above-described problems, and is divided between the split ring and the impingement cooling plate disposed on the outer periphery thereof in the axial direction by a pressure partition plate extending in the circumferential direction, and adjusted to different pressures. The upstream cavity and the downstream cavity are provided , the inside of the upstream cavity opens through the cooling passage to the upstream half of the rotor blade tip, and the inside of the downstream cavity passes through the other cooling passage in the axial direction. The cooling structure of the split ring in the gas turbine that extends in parallel with the gas turbine and opens to the wake of the rotor blade is provided.
[0012]
That is, according to the present invention, the upstream cavity and the downstream cavity partitioned in the axial direction by the pressure separator are adjusted to different pressures, respectively, so that the mainstream gas having different pressures upstream and downstream in the axial direction can be individually controlled. In addition, the mainstream gas is prevented from flowing backward on the upstream side, and the leakage air from the gap is minimized on the downstream side to improve efficiency.
[0014]
In addition, the interior of the upstream cavity opens through the cooling passage to the upstream half of the blade tip, and the interior of the downstream cavity extends in parallel to the axial direction through the other cooling passage to the rear of the blade. Since it opens to the blade tip side at different positions in the axial direction by opening in the flow, the distance of the split ring cooling hole from the exit from each cavity to the blade tip side is shortened Especially, in the cooling passage from the upstream cavity, the cooling medium is released to the tip of the rotor blade before it warms up, so that the cooling effect of the rotor blade is enhanced , and in the other cooling passage from the downstream cavity, it is axially a shall enhance the cooling effect of the split ring by guiding a cooling medium extends in parallel form.
[0015]
DETAILED DESCRIPTION OF THE INVENTION
An embodiment of the present invention will be described with reference to FIGS.
Note that the same parts as those of the above-described conventional one are denoted by the same reference numerals in the drawings, and redundant description will be omitted as much as possible, and points unique to the present embodiment will be mainly described.
[0016]
Reference numeral 10 denotes a split ring, which is arranged close to the tip of the rotor blade so as to seal a gap with the tip of the rotor blade. In FIGS. 1 and 2, one of the parts divided in the circumferential direction is representative. Shown extracted.
[0017]
Reference numeral 12 denotes an impingement cooling plate, which is supported by a heat shield ring 19 so as to be concentrically arranged on the outer peripheral side of the split ring 10 at an appropriate interval with respect to the split ring 10, and is provided in a large number on the plate surface. A cavity for receiving a cooling medium is formed between the split ring 10 and the impingement cooling port 11.
[0018]
Reference numeral 18 denotes a groove provided on the surface of the split ring 10 so as to extend in the circumferential direction. A pressure separator plate 17 whose top surface is in contact with the impingement cooling plate 12 is fitted into the groove 18. A cavity formed between the impingement cooling plate 12 is divided into an upstream cavity 16a and a downstream cavity 16b.
[0019]
In addition, the pressure separator 17 may be divided into a plurality of parts in the circumferential direction, like the split ring 10 and the impingement cooling plate 12, and in this case, the circumferential joint has a small gap. The end faces may be joined to leave a minute leak, but the end joint faces may be cut into each other in the cross-sectional direction as shown in FIG.
[0020]
Further, as described above, the inner peripheral side of the pressure separator 17 is fitted with the groove 18, and the outer peripheral side facing this is an inverted L shape as shown in FIG. Of course, the shape is not limited, and other shapes such as a T-shape may be selected.
[0021]
The inside of the upstream cavity 16a opens to the range of the upstream half of the tip of the moving blade 6 through the cooling passage 13a, and the inside of the downstream cavity 16b extends almost parallel to the axial direction through the cooling passage 13b. Therefore, the distance between the cooling passages 13a and 13b is sufficiently shorter than the axial lengths of the split ring 10 and the tip of the moving blade 6.
[0023]
The impingement cooling plate 12 of each of the upstream cavity 16a and the downstream cavity 16b is provided with a large number of impingement cooling ports 11, but the impingement cooling port 11 opening to the upstream cavity 16a and the downstream The impingement cooling port 11 that opens to the side cavity 16b is different from each other in the size, shape, and numerical aperture of the opening diameter. The pressure in the upstream cavity 16a is higher than that in the downstream cavity 16b. The pressure in the upstream cavity 16a is adjusted to exceed the upstream mainstream gas 15a, and the pressure in the downstream cavity 16b is adjusted to exceed the downstream mainstream gas 15b.
[0024]
Since the present embodiment is configured as described above, the cooling medium 9 passes through the impingement hole 11 of the impingement cooling plate 12, and the split ring 10 that forms the upstream cavity 16a and the downstream cavity 16b is impinged. After being cooled, the split ring 10 is cooled again by passing through a plurality of rows of split ring cooling passages 13 a and 13 b extending in the axial direction, and finally discharged into the mainstream gas 15.
[0025]
The pressure of the cooling medium 9 supplied into the upstream cavity 16a and the downstream cavity 16b constituting the split ring cooling structure adjusts the size, shape, numerical aperture, etc. of the opening diameter of the impingement cooling port 11. Thus, as described above, the pressure in the upstream cavity 16a is relatively slightly higher than the pressure of the upstream combustion gas 15a, and the pressure in the downstream cavity 16b is slightly higher than the pressure of the downstream combustion gas 15b in which the pressure has decreased. As a result, the upstream cavity 16a of the split ring 10 has no fear of backflow of the mainstream combustion gas 15a, and the downstream cavity 16b minimizes leakage air from the gaps between the respective parts. It can be kept in.
[0026]
The cooling ring 9 is cooled by guiding the cooling medium 9 from the upstream cavity 16a and the downstream cavity 16b through the cooling passages 13a and 13b provided through the plate thickness of the split ring 10, and The cooling effect of the turbine blade 6 can also be expected by blowing this cooling medium 9 toward the tip of the turbine blade 6.
[0027]
Although the present invention has been described with reference to the illustrated embodiment, the present invention is not limited to this embodiment, and it goes without saying that various modifications may be made to the specific structure within the scope of the present invention. Absent.
[0028]
For example, in the above-described embodiment, a single partition wall 17 is disposed between the impingement cooling plate 12 and the split ring 10 and divided into an upstream cavity 16a and a downstream cavity 16b. Of course, a plurality of cavities may be formed by partitioning with a plurality of partition walls 17.
[0029]
【The invention's effect】
As described above, according to the present invention, the upstream cavity and the downstream cavity that are divided in the axial direction by the pressure partition plate extending in the circumferential direction between the split ring and the impingement cooling plate disposed on the outer periphery thereof, and adjusted to different pressures, respectively. Since the cooling structure of the split ring in the gas turbine is configured, the cavities partitioned upstream and downstream in the axial direction by the pressure separators are adjusted to different pressures so that the mainstream gas having different pressures is adjusted. It was possible to deal with each individually and appropriately, and the upstream side prevented the backflow of the mainstream gas, and the downstream side was able to further improve the efficiency of the gas turbine by minimizing the leaked air from the gap.
[0030]
In addition , according to the present invention, the interior of the upstream cavity opens through the cooling passage to the upstream half of the blade tip, and the interior of the downstream cavity passes through the other cooling passage and is parallel to the axial direction. Since it extends to open to the wake of the rotor blade and opens to the tip of the rotor blade at different positions in the axial direction, it forms a cooling structure for the split ring in the gas turbine. ring segment cooling hole opened to blade tip side at different positions in the axial direction, the distance ring segment cooling hole from exiting the respective cavity until the opened toward the rotor blade tip side is shortened, especially the upstream In the cooling passage from the side cavity, the cooling medium is released to the tip of the rotor blade before it warms up, so the tip of the rotor blade is film cooled, and in the other cooling passage from the downstream cavity, it is parallel to the axial direction. Extending into the cooling medium Sufficiently cool the split ring by the guide to one in which it was possible to further improve the gas turbine cooling efficiency together.
[Brief description of the drawings]
FIG. 1 is a partially cutaway perspective view showing a cooling structure for a split ring in a gas turbine according to an embodiment of the present invention.
FIG. 2 is a side sectional view of a cooling structure of a split ring according to the present embodiment.
FIG. 3 is an explanatory view showing cavity division by a pressure separator, which is a main part of the cooling structure of the split ring of the present embodiment.
4 is an explanatory view showing a joining state of a divided portion of the pressure diaphragm shown in FIG. 3; FIG.
FIG. 5 is a perspective view showing a cooling structure of a split ring in a conventional gas turbine with a part broken away.
FIG. 6 is a side sectional view of a conventional cooling structure for a split ring.
FIG. 7 is an explanatory diagram schematically showing an overall configuration of a gas turbine.
FIG. 8 is an explanatory diagram schematically showing a general configuration of a turbine section.
[Explanation of symbols]
DESCRIPTION OF SYMBOLS 1 Compressor 2 Combustor 3 Turbine 4 Generator 5 Stator blade 6 Rotor blade 9 Cooling medium 10 Split ring 11 Impingement cooling port 12 Impingement cooling plate 13 Cooling passage 14 Split ring rear portion 13a Cooling passage 13b Cooling passage 15 Main flow gas 15a Upstream side mainstream gas 15b Downstream side mainstream gas 16 Cavity 16a Upstream side cavity 16b Downstream side cavity 17 Pressure separator 18 Groove 19 Heat shield ring

Claims (1)

分割環とその外周に配置したインピンジメント冷却板との間を周方向に延びる圧力隔板により軸方向で区画し、それぞれ異なる圧力に調整した上流側キャビティと下流側キャビティを設け、前記上流側キャビティの内部は冷却通路を経て動翼先端部の上流側半分の範囲に開口し、下流側キャビティの内部は他の冷却通路を経て軸方向と平行状に延びて動翼の後流に開口したことを特徴とするガスタービンにおける分割環の冷却構造。An upstream cavity and a downstream cavity that are divided in the axial direction by a pressure partition plate extending in the circumferential direction between the split ring and an impingement cooling plate disposed on the outer periphery thereof, and adjusted to different pressures are provided , and the upstream cavity The inside of the cavities opens through the cooling passage to the upstream half of the blade tip, and the interior of the downstream cavities extends parallel to the axial direction through the other cooling passage and opens to the wake of the blade . A cooling structure for a split ring in a gas turbine.
JP05044298A 1998-03-03 1998-03-03 Cooling structure of split ring in gas turbine Expired - Fee Related JP3631898B2 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
JP05044298A JP3631898B2 (en) 1998-03-03 1998-03-03 Cooling structure of split ring in gas turbine
US09/256,102 US6146091A (en) 1998-03-03 1999-02-24 Gas turbine cooling structure
CA002263013A CA2263013C (en) 1998-03-03 1999-02-25 Gas turbine
EP99104200A EP0940562B1 (en) 1998-03-03 1999-03-02 Gas turbine
EP04023188.8A EP1500789B1 (en) 1998-03-03 1999-03-02 Impingement cooled ring segment of a gas turbine
DE69933601T DE69933601T2 (en) 1998-03-03 1999-03-02 gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP05044298A JP3631898B2 (en) 1998-03-03 1998-03-03 Cooling structure of split ring in gas turbine

Publications (2)

Publication Number Publication Date
JPH11247621A JPH11247621A (en) 1999-09-14
JP3631898B2 true JP3631898B2 (en) 2005-03-23

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001221065A (en) * 2000-02-10 2001-08-17 General Electric Co <Ge> Impingement cooling of gas turbine shroud
FR2832178B1 (en) * 2001-11-15 2004-07-09 Snecma Moteurs COOLING DEVICE FOR GAS TURBINE RINGS
US7033138B2 (en) 2002-09-06 2006-04-25 Mitsubishi Heavy Industries, Ltd. Ring segment of gas turbine
EP1471210A1 (en) * 2003-04-24 2004-10-27 Siemens Aktiengesellschaft Turbine component with impingement cooling plate
FR2857406B1 (en) * 2003-07-10 2005-09-30 Snecma Moteurs COOLING THE TURBINE RINGS
GB0403198D0 (en) * 2004-02-13 2004-03-17 Rolls Royce Plc Casing arrangement
EP1990507B1 (en) * 2006-03-02 2015-04-15 IHI Corporation Impingement cooling structure
EP2239419A1 (en) * 2009-03-31 2010-10-13 Siemens Aktiengesellschaft Axial turbo engine rotor with sealing disc
US8292573B2 (en) * 2009-04-21 2012-10-23 General Electric Company Flange cooled turbine nozzle
JP2011208624A (en) * 2010-03-31 2011-10-20 Hitachi Ltd Cooling structure for high-temperature member
US9453429B2 (en) * 2013-03-11 2016-09-27 General Electric Company Flow sleeve for thermal control of a double-wall turbine shell and related method
JP6775428B2 (en) * 2017-01-12 2020-10-28 三菱パワー株式会社 Split ring surface side member, split ring support side member, split ring, rest side member unit and method

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