JPH08240102A - Steam cooling blade for gas turbine - Google Patents
Steam cooling blade for gas turbineInfo
- Publication number
- JPH08240102A JPH08240102A JP4304395A JP4304395A JPH08240102A JP H08240102 A JPH08240102 A JP H08240102A JP 4304395 A JP4304395 A JP 4304395A JP 4304395 A JP4304395 A JP 4304395A JP H08240102 A JPH08240102 A JP H08240102A
- Authority
- JP
- Japan
- Prior art keywords
- steam
- blade
- cooling
- gas turbine
- blade tip
- 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.)
- Pending
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は、翼端部を効果的に冷却
することができるようにしたガスタービンの蒸気冷却翼
に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine steam cooling blade capable of effectively cooling a blade tip.
【０００２】[0002]
【従来の技術】高温ガスタービンと蒸気タービンのコン
バインプラントでは、ガスタービンの翼の冷却媒体とし
て蒸気を用いることが可能である。この場合、ガスター
ビンの翼の冷却に用いられた蒸気は、再び蒸気タービン
系に回収する必要があり、ガスタービンの翼の冷却は、
以下説明するように翼の内部に設けられた細管を流れる
蒸気による対流冷却を採用している。In high temperature gas turbine and steam turbine combiner implants, it is possible to use steam as a cooling medium for the blades of the gas turbine. In this case, the steam used for cooling the blades of the gas turbine needs to be recovered again in the steam turbine system, and the cooling of the blades of the gas turbine is
As described below, convection cooling by steam flowing through a thin tube provided inside the blade is adopted.
【０００３】即ち、図４及び図５に示すように、蒸気冷
却翼１内部の翼面近くに翼根部から翼端部６へ向う複数
の冷却用の細管２が設けられている。前記細管２の複数
のものは翼端部６付近で蒸気冷却翼１内に翼端部近くか
ら翼根部へ向って設けられた蒸気回収管４に合流してお
り、図５中、矢印で示すように細管２内を翼根部から翼
端部６へ向って流れた蒸気８は、翼端部６付近で翼端内
壁面５に沿って流れた上蒸気回収管４内に合流し、矢印
に示すように翼根部へ向って流れて回収されるようにな
っている。前記細管２内を流れる蒸気８によって蒸気冷
却翼１が対流冷却される。That is, as shown in FIGS. 4 and 5, a plurality of cooling thin tubes 2 extending from the blade root to the blade tip 6 are provided near the blade surface inside the steam cooling blade 1. A plurality of the thin tubes 2 are joined to a steam recovery pipe 4 provided in the steam cooling blade 1 near the blade tip 6 from the vicinity of the blade tip toward the blade root, as shown by an arrow in FIG. Thus, the steam 8 that has flowed in the narrow tube 2 from the blade root toward the blade tip 6 merges into the upper steam recovery pipe 4 that has flowed along the blade inner wall surface 5 near the blade tip 6, and the arrow 8 As shown, it flows toward the root of the blade and is collected. The steam cooling vanes 1 are convectively cooled by the steam 8 flowing in the narrow tubes 2.
【０００４】[0004]
【発明が解決しようとする課題】前記図４及び図５に示
す従来のタービンの蒸気冷却翼では、翼端部６は、図５
中矢印Ａに示すように腹側（高圧側）から背側（低圧
側）へ流れる高温ガスにさらされるため、この部分の冷
却を強化する必要がある。In the conventional steam cooling blade of the turbine shown in FIGS. 4 and 5, the blade tip portion 6 has the structure shown in FIG.
As shown by the middle arrow A, since it is exposed to the hot gas flowing from the ventral side (high pressure side) to the back side (low pressure side), it is necessary to strengthen the cooling of this portion.
【０００５】本発明は、以上の点に鑑みて、翼端部の冷
却を効果的に行うことができるようにしたガスタービン
の蒸気冷却翼を提供しようとするものである。In view of the above points, the present invention is to provide a gas turbine steam cooling blade capable of effectively cooling the blade tip portion.
【０００６】[0006]
（１）本発明のガスタービンの蒸気冷却翼は、翼内部に
配置され内部を蒸気が流れる冷却用の細管を、更に細い
複数の細管に分岐し、蒸気を翼端内面壁に噴流衝突さ
せ、該翼端内面壁を冷却することを特徴とする。(1) In the steam cooling blade of the gas turbine of the present invention, a cooling thin tube arranged inside the blade for cooling steam is branched into a plurality of thinner thin tubes, and the steam is jet-collised against the inner wall of the blade tip. The inner wall of the blade tip is cooled.
【０００７】（２）前記（１）のガスタービンの蒸気冷
却翼において、蒸気噴流が衝突する翼端内面壁を、粗面
としたことを特徴とする。(2) In the steam cooling blade of the gas turbine of (1), the inner wall of the blade tip against which the steam jet collides is a rough surface.
【０００８】[0008]
【作用】前記（１）の本発明では、内部を蒸気が流れる
冷却用の細管が更に細い複数の細管に分岐されており、
この更に細い複数の分岐された細管内を流れる蒸気は噴
流となって翼端内面壁に噴流衝突する。従って、翼端内
面壁は蒸気によって噴流冷却され、従来の細管の対流冷
却より熱伝達率が向上し、翼端部の冷却を効果的に行う
ことができる。In the present invention of (1) above, the cooling thin tube through which the steam flows is branched into a plurality of thin tubes.
The steam flowing in the plurality of further narrowed narrow tubes forms a jet flow and collides with the inner wall of the blade tip. Therefore, the inner wall of the blade tip is jet-cooled by the steam, the heat transfer coefficient is improved as compared with the conventional convection cooling of the thin tube, and the blade tip can be effectively cooled.
【０００９】前記（２）の本発明では、蒸気の噴流が衝
突する翼内面壁を粗面としているので、噴流冷却の熱伝
達率を更に高め、より冷却を強化することができる。In the present invention (2), since the inner wall of the blade against which the jet of steam collides is a rough surface, the heat transfer coefficient of jet cooling can be further increased and the cooling can be further strengthened.
【００１０】[0010]
【実施例】本発明の一実施例を、図１ないし図３によっ
て説明する。本実施例は、図４及び図５に示されるガス
タービンの蒸気冷却翼を以下説明するように改良したも
のであり、図１ないし図３において図４及び図５と同一
の部分には同一の符号を付し、その説明を省略する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS. In this embodiment, the steam cooling blades of the gas turbine shown in FIGS. 4 and 5 are improved as described below. In FIGS. 1 to 3, the same parts as those in FIGS. 4 and 5 are the same. The reference numerals are given and the description thereof is omitted.
【００１１】即ち、翼の後縁寄りの翼の厚みの小さい部
分以外にある各冷却用の細管２は、翼端部６の付近で更
に細い複数の細管３に分岐しており、細管２内を流れる
蒸気８は前記更に細い細管３より翼端内面壁５に噴流７
となって衝突した上蒸気回収管４に回収されるようにな
っている。That is, each of the cooling thin tubes 2 other than the small-thickness portion of the blade near the trailing edge of the blade branches into a plurality of thinner thin tubes 3 in the vicinity of the blade end portion 6, and inside the thin tube 2. The steam 8 flowing through the jet stream 7 is jetted to the inner wall 5 of the blade tip from the thin tube 3
Then, it collides and is recovered by the vapor recovery pipe 4.
【００１２】また、翼端内面壁５の表面は、図３（ａ）
に示すように複数の半球状のくぼみ５ａ又は図３（ｂ）
に示すように複数の半球状の凸起５ｂが形成された粗面
となっている。The surface of the wing tip inner surface wall 5 is shown in FIG.
A plurality of hemispherical depressions 5a as shown in FIG.
As shown in FIG. 5, it is a rough surface on which a plurality of hemispherical protrusions 5b are formed.
【００１３】本実施例では、細管２内を流れた蒸気８は
前記更に細い細管３より翼端内面壁５へ向って蒸気の噴
流７となって流れ、これが翼端内面壁５に衝突する。こ
れによって、蒸気冷却翼１の翼端部６が噴射冷却されて
同翼端部６の冷却を効果的に行うことができる。In this embodiment, the steam 8 flowing in the narrow tube 2 flows from the thinner tube 3 toward the inner wall 5 of the blade tip to form a jet 7 of steam, which collides with the inner wall 5 of the blade tip. As a result, the blade tip 6 of the steam cooling blade 1 is jet-cooled and the blade tip 6 can be effectively cooled.
【００１４】また、蒸気の噴流７が衝突する翼端内面壁
５は、図３（ａ）又は図３（ｂ）に示すように粗面とな
っているので、蒸気の噴流７による冷却の熱伝達率を高
めることができる。Since the inner wall 5 of the blade tip against which the steam jet 7 collides has a rough surface as shown in FIG. 3A or FIG. 3B, the heat of cooling by the steam jet 7 is generated. The transmission rate can be increased.
【００１５】なお、前記実施例では、翼端内面壁５が粗
面となっているが、これを平滑面にしてもよい。Although the inner wall 5 of the blade tip is a rough surface in the above embodiment, it may be a smooth surface.
【００１６】[0016]
【発明の効果】本発明により、蒸気を冷却媒体としたガ
スタービンの蒸気冷却翼の翼端部の冷却性能を強化する
ことができる。このため、本発明では、ガスタービンを
より高温で運転することが可能となり、ガスタービンの
熱効率の向上に寄与することができる。According to the present invention, the cooling performance of the blade tip portion of the steam cooling blade of a gas turbine using steam as a cooling medium can be enhanced. Therefore, in the present invention, the gas turbine can be operated at a higher temperature, which can contribute to the improvement of the thermal efficiency of the gas turbine.
【図１】本発明の一実施例の断面図である。FIG. 1 is a sectional view of an embodiment of the present invention.
【図２】図１のＡ−Ａ矢視断面図である。FIG. 2 is a sectional view taken along the line AA of FIG.
【図３】同実施例の翼端内面壁の部分の拡大断面図であ
る。FIG. 3 is an enlarged cross-sectional view of a portion of a blade tip inner surface wall of the embodiment.
【図４】従来のガスタービンの蒸気冷却翼の断面図であ
る。FIG. 4 is a sectional view of a steam cooling blade of a conventional gas turbine.
【図５】図４のＢ−Ｂ矢視断面図である。FIG. 5 is a sectional view taken along the line BB of FIG. 4;
１ 蒸気冷却翼 ２ 細管 ３ 更に細い細管 ４ 蒸気回収管 ５ 翼端内面壁 ５ａ 半球状のくぼみ ５ｂ 半球状の突起 ６ 翼端部 ７ 噴流 ８ 蒸気 1 steam cooling blade 2 thin tube 3 thinner tube 4 steam recovery tube 5 inner wall of blade tip 5a hemispherical depression 5b hemispherical protrusion 6 blade tip 7 jet 8 steam
Claims (2)
却用の細管を、更に細い複数の細管に分岐し、蒸気を翼
端内面壁に噴流衝突させ、該翼端内面壁を冷却すること
を特徴とするガスタービンの蒸気冷却翼。1. A cooling thin tube, which is arranged inside a blade and through which steam flows, is branched into a plurality of thin tubes, and the steam jet collides with the inner wall of the blade tip to cool the inner wall of the blade tip. A steam cooling blade for a gas turbine.
したことを特徴とする請求項１に記載のガスタービンの
蒸気冷却翼。2. The steam cooling blade for a gas turbine according to claim 1, wherein the inner wall of the blade tip against which the steam jet collides is a rough surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4304395A JPH08240102A (en) | 1995-03-02 | 1995-03-02 | Steam cooling blade for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4304395A JPH08240102A (en) | 1995-03-02 | 1995-03-02 | Steam cooling blade for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH08240102A true JPH08240102A (en) | 1996-09-17 |
Family
ID=12652881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4304395A Pending JPH08240102A (en) | 1995-03-02 | 1995-03-02 | Steam cooling blade for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH08240102A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998055735A1 (en) * | 1997-06-06 | 1998-12-10 | Mitsubishi Heavy Industries, Ltd. | Gas turbine blade |
| JP2001090501A (en) * | 1999-09-24 | 2001-04-03 | General Electric Co <Ge> | Gas turbine bucket having impingement cooled platform |
| JP2001232444A (en) * | 2000-01-10 | 2001-08-28 | General Electric Co <Ge> | Casting having high heat transfer surface, and mold and pattern for forming the same |
| JP2002517673A (en) * | 1998-06-08 | 2002-06-18 | ソウラー タービンズ インコーポレイテッド | Combustor for low exhaust gas turbine engine |
| EP1734228A2 (en) | 2005-06-16 | 2006-12-20 | General Electric Company | Turbine bucket tip cap |
| JP2017078422A (en) * | 2015-10-19 | 2017-04-27 | ゼネラル・エレクトリック・カンパニイ | Article and method of cooling article |
-
1995
- 1995-03-02 JP JP4304395A patent/JPH08240102A/en active Pending
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO1998055735A1 (en) * | 1997-06-06 | 1998-12-10 | Mitsubishi Heavy Industries, Ltd. | Gas turbine blade |
| US6257830B1 (en) | 1997-06-06 | 2001-07-10 | Mitsubishi Heavy Industries, Ltd. | Gas turbine blade |
| JP2002517673A (en) * | 1998-06-08 | 2002-06-18 | ソウラー タービンズ インコーポレイテッド | Combustor for low exhaust gas turbine engine |
| JP2001090501A (en) * | 1999-09-24 | 2001-04-03 | General Electric Co <Ge> | Gas turbine bucket having impingement cooled platform |
| JP4571277B2 (en) * | 1999-09-24 | 2010-10-27 | ゼネラル・エレクトリック・カンパニイ | Gas turbine blade with impingement cooling platform |
| JP2001232444A (en) * | 2000-01-10 | 2001-08-28 | General Electric Co <Ge> | Casting having high heat transfer surface, and mold and pattern for forming the same |
| JP2006348938A (en) * | 2005-06-16 | 2006-12-28 | General Electric Co <Ge> | Turbine bucket tip cap |
| EP1734228A3 (en) * | 2005-06-16 | 2007-06-27 | General Electric Company | Turbine bucket tip cap |
| EP1734228A2 (en) | 2005-06-16 | 2006-12-20 | General Electric Company | Turbine bucket tip cap |
| US7837440B2 (en) | 2005-06-16 | 2010-11-23 | General Electric Company | Turbine bucket tip cap |
| CN103790641A (en) * | 2005-06-16 | 2014-05-14 | 通用电气公司 | Turbine bucket tip cap |
| CN103790641B (en) * | 2005-06-16 | 2015-11-04 | 通用电气公司 | Turbine blade tip shroud |
| JP2017078422A (en) * | 2015-10-19 | 2017-04-27 | ゼネラル・エレクトリック・カンパニイ | Article and method of cooling article |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR100553295B1 (en) | Turbine Blade with Multi-Pass Cooling and Cooling Air Addition | |
| JPH09203301A (en) | Steam cooled blade | |
| JP4546760B2 (en) | Turbine blade with integrated bridge | |
| US5370499A (en) | Film cooling of turbine airfoil wall using mesh cooling hole arrangement | |
| JP4108427B2 (en) | Blade with inclined tip shelf | |
| EP0416542B1 (en) | Turbine blade | |
| US6099251A (en) | Coolable airfoil for a gas turbine engine | |
| US9151173B2 (en) | Use of multi-faceted impingement openings for increasing heat transfer characteristics on gas turbine components | |
| JP2009162119A (en) | Turbine blade cooling structure | |
| EP1728970B1 (en) | Turbine blade cooling system | |
| JPH0370084B2 (en) | ||
| JP2007138942A (en) | Gas turbine bucket which keeps front platform edge is cooled down and method of cooling down the same | |
| JP2004308658A (en) | Method for cooling aerofoil and its device | |
| JP2001073704A (en) | Cooling tip of rotor blade | |
| JPH10252404A (en) | Gas turbine moving blade | |
| JP2005299638A (en) | Thermal shield turbine airfoil | |
| BR102015032771A2 (en) | engine component | |
| JP2002235502A5 (en) | ||
| US20190101011A1 (en) | Turbine airfoil with internal cooling channels having flow splitter feature | |
| JPH0112921B2 (en) | ||
| JPH08240102A (en) | Steam cooling blade for gas turbine | |
| JPH05312002A (en) | Gas turbine blade | |
| JPH05163959A (en) | Turbine stationary blade | |
| JPH11173105A (en) | Moving blade of gas turbine | |
| JPH09303106A (en) | Gas turbine cooling blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20030715 |