JPH0960531A - Gas turbine - Google Patents
Gas turbineInfo
- Publication number
- JPH0960531A JPH0960531A JP21735395A JP21735395A JPH0960531A JP H0960531 A JPH0960531 A JP H0960531A JP 21735395 A JP21735395 A JP 21735395A JP 21735395 A JP21735395 A JP 21735395A JP H0960531 A JPH0960531 A JP H0960531A
- Authority
- JP
- Japan
- Prior art keywords
- cooling
- air
- cooling air
- cooled
- combustor plenum
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【本発明の属する技術分野】本発明は、コンバインドサ
イクルなどに適用されるガスタービンに関する。TECHNICAL FIELD The present invention relates to a gas turbine applied to a combined cycle and the like.
【０００２】[0002]
【従来の技術】図３は本出願人が特願平７−９０５８０
号により出願中のガスタービンの説明図である。図にお
いて、静翼を冷却する冷却用空気は冷却空気管１からガ
スタービンの車室内に供給され、一段、二段、三段の各
静翼を矢印方向に順次冷却した後、管２を通って車室外
に取り出される。車室外に取り出された高温の冷却用空
気は空気冷却器３に導入されて蒸気、或いはその他の流
体によって冷却された後、ブースターポンプ４によって
昇圧されて再び循環する。2. Description of the Related Art FIG. 3 shows a Japanese Patent Application No. 7-90580 filed by the present applicant.
It is explanatory drawing of the gas turbine currently applied for by the number. In the figure, cooling air for cooling the stationary vanes is supplied from the cooling air pipe 1 into the interior of the gas turbine, and the first, second, and third stationary vanes are sequentially cooled in the direction of the arrow and then passed through the pipe 2. Is taken out of the passenger compartment. The high temperature cooling air taken out of the passenger compartment is introduced into the air cooler 3 and cooled by steam or other fluid, and then boosted by the booster pump 4 and circulated again.
【０００３】また、動翼の冷却用空気は管５および二重
管６の一方側に導びかれ、車室内を矢印の方向に導入さ
れる。そして、中間軸カバー７内に入り、中間軸カバー
７とエアセパレータ８との間を通ってディスク９の細穴
から動翼内に入り動翼を冷却する。冷却した後、再びデ
ィスク９の細穴から出て次段、次々段の動翼を冷却した
後、矢印で示す方向にディスク９の内径を通り二重管６
の他方側を通って車室外に導びかれ、管１０を通って空
気冷却器３に入り冷却され、同様に循環する。Further, the cooling air for the moving blades is guided to one side of the pipe 5 and the double pipe 6 and introduced into the passenger compartment in the direction of the arrow. Then, it enters the intermediate shaft cover 7, passes between the intermediate shaft cover 7 and the air separator 8, and enters the moving blade through the small hole of the disk 9 to cool the moving blade. After cooling, it again comes out from the small holes of the disc 9 to cool the moving blades of the next stage and the next stage, and then passes through the inner diameter of the disc 9 in the direction shown by the arrow to form the double pipe 6.
Is guided to the outside of the vehicle through the other side of the air conditioner, enters the air cooler 3 through the pipe 10, is cooled, and is similarly circulated.
【０００４】このように、冷却用空気の流れは完全な閉
回路の中で行われるので、冷却用空気の消耗がなく、メ
イキャップ時にメイキャップライン１１から冷却用空気
を満たすのみでよい。As described above, since the flow of the cooling air is performed in a completely closed circuit, there is no consumption of the cooling air, and it suffices to fill the cooling air from the makeup line 11 at the time of makeup.
【０００５】[0005]
【発明が解決しようとする課題】上記のようなガスター
ビンにおいては、冷却用空気が完全な閉回路の中を循環
することにより冷却用空気の消耗がなくガスタービン翼
を冷却することができるが、さらに無駄なくガスタービ
ン翼の冷却効果も上げる必要がある。In the gas turbine as described above, the cooling air circulates in a completely closed circuit to cool the gas turbine blade without exhaustion of the cooling air. Moreover, it is necessary to increase the cooling effect of the gas turbine blade without waste.
【０００６】[0006]
【課題を解決するための手段】本発明に係るガスタービ
ンは上記課題の解決を目的にしており、燃焼器プレナム
から抽気されて冷却された冷却用空気を静翼内を順次通
して冷却した後に回収して上記燃焼器プレナムへ戻す第
一の閉回路と、上記燃焼器プレナムから抽気されて冷却
された冷却用空気を動翼内を順次通して冷却した後に回
収して上記燃焼器プレナムへ戻す第二の閉回路とを備え
た構成を特徴とする。即ち、本発明に係るガスタービン
においては、燃焼器プレナムから抽気されて冷却された
冷却用空気を第一の閉回路が静翼内を順次通して冷却し
た後に回収して燃焼器プレナムへ戻すとともに燃焼器プ
レナムから抽気されて冷却された冷却用空気を第二の閉
回路が動翼内を順次通して冷却した後に回収して燃焼器
プレナムへ戻すようになっており、冷却用空気を燃焼器
プレナムから抽気して燃焼器プレナムへ戻すことにより
ガスタービン翼の冷却効果が向上するとともに、冷却用
空気は閉回路内を循環するだけで冷却を終えた後に総て
回収されて燃焼器プレナムへ戻され僅かの消耗もない。
また、閉回路内に冷却用媒体をメイキャップする必要も
ない。SUMMARY OF THE INVENTION A gas turbine according to the present invention is intended to solve the above-mentioned problems, and after the cooling air extracted from the combustor plenum and cooled is sequentially passed through the vanes, the cooling air is cooled. A first closed circuit that recovers and returns to the combustor plenum, and cooling air that is extracted and cooled from the combustor plenum is sequentially passed through the moving blades to cool and then recovered and returned to the combustor plenum. And a configuration including a second closed circuit. That is, in the gas turbine according to the present invention, the cooling air extracted from the combustor plenum and cooled is recovered by returning to the combustor plenum after the first closed circuit sequentially cools the inside of the vanes. The second closed circuit sequentially cools the cooling air extracted from the combustor plenum and cooled, and then recovers it and returns it to the combustor plenum. By extracting air from the plenum and returning it to the combustor plenum, the cooling effect of the gas turbine blades is improved, and the cooling air is simply circulated in the closed circuit, and after cooling is completed, all is recovered and returned to the combustor plenum. There is no slight consumption.
Further, it is not necessary to make up the cooling medium in the closed circuit.
【０００７】また、本発明に係るガスタービンは、燃焼
器プレナムから抽気されて冷却された冷却用空気を静翼
内を順次通して冷却した後に回収して上記燃焼器プレナ
ム上流の圧縮機へ戻す第一の閉回路と、上記燃焼器プレ
ナムから抽気されて冷却された冷却用空気を動翼内を順
次通して冷却した後に回収して上記圧縮機へ戻す第二の
閉回路とを備えた構成を特徴とする。即ち、本発明に係
るガスタービンにおいては、燃焼器プレナムから抽気さ
れて冷却された冷却用空気を第一の閉回路が静翼内を順
次通して冷却した後に回収して燃焼器プレナム上流の圧
縮機へ戻すとともに燃焼器プレナムから抽気されて冷却
された冷却用空気を第二の閉回路が動翼内を順次通して
冷却した後に回収して圧縮機へ戻すようになっており、
冷却用空気を燃焼器プレナムから抽気して燃焼器プレナ
ム上流の圧縮機へ戻すことによりガスタービン翼の冷却
効果が向上するとともに、冷却用空気は閉回路内を循環
するだけで冷却を終えた後に総て回収されて圧縮機へ戻
され僅かの消耗もない。また、閉回路内に冷却用媒体を
メイキャップする必要もない。Further, in the gas turbine according to the present invention, the cooling air extracted from the combustor plenum and cooled is sequentially passed through the vanes to be cooled and then recovered and returned to the compressor upstream of the combustor plenum. A configuration including a first closed circuit and a second closed circuit in which cooling air extracted from the combustor plenum and cooled is sequentially passed through the moving blades to be cooled and then recovered and returned to the compressor. Is characterized by. That is, in the gas turbine according to the present invention, the first closed circuit sequentially cools the cooling air extracted and cooled from the combustor plenum, and then the recovered cooling air is recovered and compressed upstream of the combustor plenum. The second closed circuit sequentially cools the cooling air extracted and cooled from the combustor plenum while returning it to the compressor, and then recovers and returns it to the compressor.
The cooling effect of the gas turbine blades is improved by extracting the cooling air from the combustor plenum and returning it to the compressor upstream of the combustor plenum, and the cooling air circulates in the closed circuit only after cooling. All of them are collected and returned to the compressor without any slight consumption. Further, it is not necessary to make up the cooling medium in the closed circuit.
【０００８】[0008]
【発明の実施の形態】図１は本発明の実施の一形態に係
るガスタービン翼の説明図、図２は本発明の実施の他の
形態に係るガスタービン翼の説明図である。図におい
て、これらガスタービン翼はコンバインドサイクルに使
用されるガスタービンにおけるガスタービン翼で、冷却
用空気が供給されて内部を冷却した後に回収されて循環
するようになっている。1 is an explanatory view of a gas turbine blade according to an embodiment of the present invention, and FIG. 2 is an explanatory view of a gas turbine blade according to another embodiment of the present invention. In the figure, these gas turbine blades are gas turbine blades in a gas turbine used in a combined cycle, and are supplied with cooling air to cool the inside, and then are recovered and circulated.
【０００９】図１において、本実施の形態に係るガスタ
ービン翼は図に示すように動翼および静翼を冷却する冷
却用空気が燃焼器プレナム１から冷却空気管２によって
機外に取り出され、空気冷却器３に導入されて蒸気、或
いはその他の流体によって冷却されるようになってい
る。Referring to FIG. 1, in the gas turbine blade according to this embodiment, as shown in the figure, cooling air for cooling the moving blades and the stationary blades is taken out of the combustor plenum 1 by a cooling air pipe 2. It is introduced into the air cooler 3 and cooled by steam or another fluid.
【００１０】静翼を冷却する冷却用空気は、冷却空気管
４からガスタービン車室内に供給され、一段、二段、三
段の各静翼内の閉回路を矢印で示す方向に順次通って冷
却した後、管５を通って車室外に取り出される。そし
て、車室外に取り出された高温の冷却用空気はブースタ
ー６で加圧された後、再び燃焼器プレナム１へ戻され
る。Cooling air for cooling the vanes is supplied from the cooling air pipe 4 into the gas turbine casing, and sequentially passes through a closed circuit in each of the first, second, and third vanes in the direction indicated by the arrow. After cooling, it is taken out of the passenger compartment through the pipe 5. Then, the high temperature cooling air taken out of the vehicle compartment is pressurized by the booster 6 and then returned to the combustor plenum 1.
【００１１】動翼を冷却する冷却用空気は、冷却空気管
７および二重管８の一方側に導びかれ、車室内に矢印で
示す方向に導入される。そして、中間軸カバー９の内側
を通ってディスク１０の細穴から動翼内の閉回路に入り
動翼を冷却する。ここで、一部の冷却用空気はディスク
穴１１をバイパスして次段、次々段の冷却効果を上げる
ために供せられる。そして、冷却後にディスク１０の内
径を通り、さらに二重管８の他方側を通って車室外に導
かれ、管１２を通ってブースター６で加圧された後、再
び燃焼器プレナム１へ戻される。The cooling air for cooling the moving blades is guided to one side of the cooling air pipe 7 and the double pipe 8 and introduced into the vehicle compartment in the direction indicated by the arrow. Then, it passes through the inside of the intermediate shaft cover 9 and enters a closed circuit inside the moving blade from the small hole of the disk 10 to cool the moving blade. Here, a part of the cooling air bypasses the disk hole 11 and is provided to enhance the cooling effect of the next stage and the next stage. Then, after cooling, it passes through the inner diameter of the disk 10, passes through the other side of the double pipe 8, is guided to the outside of the vehicle compartment, is pressurized by the booster 6 through the pipe 12, and is then returned to the combustor plenum 1 again. .
【００１２】このように、本ガスタービン翼においては
動翼および静翼内の冷却用空気の通路を翼内を循環する
閉回路とし、燃焼器プレナム１から抽出した圧縮空気を
冷却器により蒸気タービンから抽出した蒸気を媒体とし
て冷却し、この圧縮空気で動翼および静翼を冷却した
後、冷却を終えた冷却用空気をブースター６で加圧して
再び燃焼器プレナム１へ戻すようにしており、冷却用空
気は完全な閉回路の中を循環するので冷却を終えた冷却
用空気が総て回収されて少しの消耗もない。また、閉回
路内に冷却媒体をメイキャップする必要もない。これら
により、コンバインドサイクルにおける熱効率および性
能が向上する。As described above, in the gas turbine blade of the present invention, the passage of the cooling air in the moving blade and the stationary blade is a closed circuit for circulating the inside of the blade, and the compressed air extracted from the combustor plenum 1 is cooled by the steam turbine. After cooling the steam extracted from the medium as a medium and cooling the moving blades and the stationary blades with this compressed air, the cooled cooling air is pressurized by the booster 6 and returned to the combustor plenum 1 again. Since the cooling air circulates in a completely closed circuit, all the cooling air that has finished cooling is collected and is not consumed at all. Further, it is not necessary to make up the cooling medium in the closed circuit. These improve thermal efficiency and performance in the combined cycle.
【００１３】図２において、本実施の形態に係るガスタ
ービン翼は図に示すように動翼および静翼を冷却する冷
却用空気が燃焼器プレナム１から冷却空気管２によって
機外に取り出され、空気冷却器３に導入されて蒸気、或
いはその他の流体によって冷却されるようになってい
る。Referring to FIG. 2, in the gas turbine blade according to the present embodiment, as shown in the figure, cooling air for cooling the moving blades and the stationary blades is taken out of the combustor plenum 1 by a cooling air pipe 2. It is introduced into the air cooler 3 and cooled by steam or another fluid.
【００１４】静翼を冷却する冷却用空気は、冷却空気管
４からガスタービン車室内に供給され、一段、二段、三
段の各静翼内の閉回路を矢印で示す方向に順次通って冷
却した後、管５を通って車室外に取り出される。そし
て、車室外に取り出された高温の冷却用空気はブースタ
ー６で加圧された後、圧縮機１３の中間段へ戻される。Cooling air for cooling the vanes is supplied from the cooling air pipe 4 into the gas turbine casing, and sequentially passes through a closed circuit in each of the first, second, and third vanes in the direction indicated by the arrow. After cooling, it is taken out of the passenger compartment through the pipe 5. Then, the high temperature cooling air taken out of the vehicle compartment is pressurized by the booster 6 and then returned to the intermediate stage of the compressor 13.
【００１５】動翼を冷却する冷却空気は、冷却空気管７
および二重管８の一方側に導びかれ、車室内を矢印で示
す方向に導入される。そして、中間軸カバー９の内側を
通ってディスク１０の細穴から動翼内の閉回路に入り動
翼を冷却する。ここで、一部の冷却用空気はディスク穴
１１をバイパスして次段、次々段の冷却効果を上げるた
めに供せられる。そして、冷却後にディスク１０の内径
を通り、さらに二重管８の他方側を通って車室外に導び
かれ、管１２を通ってブースター６で加圧された後、圧
縮機１３の中間段へ戻される。The cooling air for cooling the moving blade is the cooling air pipe 7
And is guided to one side of the double pipe 8 and introduced into the vehicle interior in the direction indicated by the arrow. Then, it passes through the inside of the intermediate shaft cover 9 and enters a closed circuit inside the moving blade from the small hole of the disk 10 to cool the moving blade. Here, a part of the cooling air bypasses the disk hole 11 and is provided to enhance the cooling effect of the next stage and the next stage. Then, after cooling, it passes through the inner diameter of the disk 10, passes through the other side of the double pipe 8, is guided to the outside of the vehicle compartment, and is pressurized by the booster 6 through the pipe 12, and then to the intermediate stage of the compressor 13. Will be returned.
【００１６】このように、動翼および静翼の冷却用空気
は燃焼器プレナム１から機外に取り出されて空気冷却器
３で冷却され、動翼および静翼を冷却して再び機外に取
り出される過程は上記の実施の形態に係るガスタービン
翼と同じであるが、本ガスタービン翼においては機外に
取り出された動翼および静翼を冷却後の高温空気はブー
スター６によって加圧された後、圧縮機１３の中間段へ
返されて圧縮機１３によって昇圧され、燃焼器プレナム
１へ導入されるようにしており、これにより上記の実施
の形態に係るガスタービン翼と同様の作用および効果を
得ることができる。In this way, the cooling air for the moving blades and the stationary blades is taken out of the machine from the combustor plenum 1 and cooled in the air cooler 3, and the moving blades and the stationary blades are cooled and taken out again. The process is the same as that of the gas turbine blade according to the above-described embodiment, but in this gas turbine blade, the hot air after cooling the moving blades and the stationary blades taken out of the machine is pressurized by the booster 6. After that, the compressor 13 is returned to the intermediate stage of the compressor 13 to be boosted by the compressor 13 and introduced into the combustor plenum 1, whereby the same operation and effect as those of the gas turbine blade according to the above-described embodiment are performed. Can be obtained.
【００１７】特願平７−９０５８０号により出願中のガ
スタービンにおいては、冷却用空気が完全な閉回路の中
を循環することにより冷却用空気の消耗がなくガスター
ビン翼を冷却することができるが、さらに無駄なくガス
タービン翼の冷却効果も上げる必要がある。これに対
し、上述の各ガスタービン翼においては静翼および動翼
内に空気冷却を行う閉回路が形成されており、冷却用空
気はこの閉回路内を循環して静翼および動翼を冷却する
だけで回収され、燃焼器プレナム１、或いは圧縮機１３
の中間段へ戻されるために消耗しない。従って、コンバ
インドサイクルにおける熱効率および性能が向上する。In the gas turbine applied for by Japanese Patent Application No. 7-90580, the cooling air circulates in a completely closed circuit to cool the gas turbine blade without exhaustion of the cooling air. However, it is necessary to further improve the cooling effect of the gas turbine blade without waste. On the other hand, in each of the gas turbine blades described above, a closed circuit for cooling air is formed in the stationary blade and the moving blade, and the cooling air circulates in the closed circuit to cool the stationary blade and the moving blade. It is recovered simply by burning the combustor plenum 1 or the compressor 13
Since it is returned to the middle stage of, it is not consumed. Therefore, the thermal efficiency and performance in the combined cycle are improved.
【００１８】[0018]
【発明の効果】本発明に係るガスタービンは前記のよう
に構成されており、冷却用空気は冷却を終えた後に総て
回収されて燃焼器プレナムまたは圧縮機へ戻され僅かの
消耗もないので、コンバインドサイクルにおける熱効率
および性能が向上する。The gas turbine according to the present invention is constructed as described above, and since the cooling air is completely recovered after being cooled and returned to the combustor plenum or the compressor, there is no slight consumption. , The thermal efficiency and performance in the combined cycle are improved.
【図１】図１は本発明の実施の一形態に係るガスタービ
ン翼の断面図である。FIG. 1 is a cross-sectional view of a gas turbine blade according to an embodiment of the present invention.
【図２】図２は本発明の実施の他の形態に係るガスター
ビン翼の断面図である。FIG. 2 is a sectional view of a gas turbine blade according to another embodiment of the present invention.
【図３】図３は出願中のガスタービン翼の断面図であ
る。FIG. 3 is a cross-sectional view of the pending gas turbine blade.
１ 燃焼器プレナム ２ 冷却空気管 ３ 空気冷却器 ４ 冷却空気管 ５ 管 ６ ブースター ７ 冷却空気管 ８ 二重管 ９ 中間軸カバー １０ ディスク １１ ディスク穴 １２ 管 １３ 圧縮機 1 Combustor Plenum 2 Cooling Air Pipe 3 Air Cooler 4 Cooling Air Pipe 5 Pipe 6 Booster 7 Cooling Air Pipe 8 Double Pipe 9 Intermediate Shaft Cover 10 Disc 11 Disc Hole 12 Pipe 13 Compressor
Claims (2)
た冷却用空気を静翼内を順次通して冷却した後に回収し
て上記燃焼器プレナムへ戻す第一の閉回路と、上記燃焼
器プレナムから抽気されて冷却された冷却用空気を動翼
内を順次通して冷却した後に回収して上記燃焼器プレナ
ムへ戻す第二の閉回路とを備えたことを特徴とするガス
タービン。1. A first closed circuit for returning the cooling air extracted from the combustor plenum and cooled to the combustor plenum after the cooling air is sequentially passed through the vanes to be cooled and is returned from the combustor plenum. A second closed circuit, comprising: a second closed circuit in which cooling air that has been extracted and cooled is sequentially passed through the moving blades to be cooled, and then recovered and returned to the combustor plenum.
た冷却用空気を静翼内を順次通して冷却した後に回収し
て上記燃焼器プレナム上流の圧縮機へ戻す第一の閉回路
と、上記燃焼器プレナムから抽気されて冷却された冷却
用空気を動翼内を順次通して冷却した後に回収して上記
圧縮機へ戻す第二の閉回路とを備えたことを特徴とする
ガスタービン。2. A first closed circuit, in which cooling air extracted from a combustor plenum and cooled is sequentially passed through the vanes to be cooled and then recovered and returned to a compressor upstream of the combustor plenum. A second closed circuit, comprising: a second closed circuit in which cooling air extracted from the combustor plenum and cooled is sequentially passed through the moving blades to be cooled and then recovered and returned to the compressor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21735395A JP3197190B2 (en) | 1995-08-25 | 1995-08-25 | gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP21735395A JP3197190B2 (en) | 1995-08-25 | 1995-08-25 | gas turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0960531A true JPH0960531A (en) | 1997-03-04 |
| JP3197190B2 JP3197190B2 (en) | 2001-08-13 |
Family
ID=16702850
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP21735395A Expired - Fee Related JP3197190B2 (en) | 1995-08-25 | 1995-08-25 | gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3197190B2 (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998058158A1 (en) * | 1997-06-19 | 1998-12-23 | Mitsubishi Heavy Industries, Ltd. | Device for sealing gas turbine stator blades |
| JPH11270353A (en) * | 1998-03-25 | 1999-10-05 | Hitachi Ltd | Gas turbine and stationary blade of gas turbine |
| US6065282A (en) * | 1997-10-29 | 2000-05-23 | Mitsubishi Heavy Industries, Ltd. | System for cooling blades in a gas turbine |
| EP1283338A1 (en) * | 2001-08-09 | 2003-02-12 | Siemens Aktiengesellschaft | Gas turbine and method for operating a gas turbine |
| US6860109B2 (en) | 1999-05-19 | 2005-03-01 | Mitsubishi Heavy Industries, Ltd. | Turbine equipment |
| JP2009275705A (en) * | 2008-05-16 | 2009-11-26 | General Electric Co <Ge> | Cooling circuit used in turbine bucket cooling |
| JP2014020331A (en) * | 2012-07-20 | 2014-02-03 | Toshiba Corp | Turbine |
| CN104420887A (en) * | 2013-08-30 | 2015-03-18 | 哈尔滨汽轮机厂有限责任公司 | Turbine motor of gas turbine |
| JP2016500790A (en) * | 2012-11-07 | 2016-01-14 | シーメンス アクティエンゲゼルシャフト | Air injection system for cooling a rotor of a gas turbine engine and method for cooling such a rotor |
| US9255490B2 (en) | 2008-10-08 | 2016-02-09 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and operating method thereof |
-
1995
- 1995-08-25 JP JP21735395A patent/JP3197190B2/en not_active Expired - Fee Related
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6217279B1 (en) | 1997-06-19 | 2001-04-17 | Mitsubishi Heavy Industries, Ltd. | Device for sealing gas turbine stator blades |
| WO1998058158A1 (en) * | 1997-06-19 | 1998-12-23 | Mitsubishi Heavy Industries, Ltd. | Device for sealing gas turbine stator blades |
| US6065282A (en) * | 1997-10-29 | 2000-05-23 | Mitsubishi Heavy Industries, Ltd. | System for cooling blades in a gas turbine |
| JPH11270353A (en) * | 1998-03-25 | 1999-10-05 | Hitachi Ltd | Gas turbine and stationary blade of gas turbine |
| US6860109B2 (en) | 1999-05-19 | 2005-03-01 | Mitsubishi Heavy Industries, Ltd. | Turbine equipment |
| EP1283338A1 (en) * | 2001-08-09 | 2003-02-12 | Siemens Aktiengesellschaft | Gas turbine and method for operating a gas turbine |
| US6786694B2 (en) | 2001-08-09 | 2004-09-07 | Siemens Aktiengesellschaft | Gas turbine and method of operating a gas turbine |
| JP2009275705A (en) * | 2008-05-16 | 2009-11-26 | General Electric Co <Ge> | Cooling circuit used in turbine bucket cooling |
| US9951644B2 (en) | 2008-10-08 | 2018-04-24 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and operating method thereof |
| US10309245B2 (en) | 2008-10-08 | 2019-06-04 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and operating method thereof |
| US10247030B2 (en) | 2008-10-08 | 2019-04-02 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and operating method thereof |
| US9255490B2 (en) | 2008-10-08 | 2016-02-09 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and operating method thereof |
| JP2014020331A (en) * | 2012-07-20 | 2014-02-03 | Toshiba Corp | Turbine |
| US9399949B2 (en) | 2012-07-20 | 2016-07-26 | Kabushiki Kaisha Toshiba | Turbine |
| JP2016500790A (en) * | 2012-11-07 | 2016-01-14 | シーメンス アクティエンゲゼルシャフト | Air injection system for cooling a rotor of a gas turbine engine and method for cooling such a rotor |
| CN104420887B (en) * | 2013-08-30 | 2016-06-15 | 哈尔滨汽轮机厂有限责任公司 | A kind of turbine of gas turbine |
| CN104420887A (en) * | 2013-08-30 | 2015-03-18 | 哈尔滨汽轮机厂有限责任公司 | Turbine motor of gas turbine |
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| Publication number | Publication date |
|---|---|
| JP3197190B2 (en) | 2001-08-13 |
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