JP3040656B2 - Gas Turbine Blade Platform Cooling System - Google Patents
Gas Turbine Blade Platform Cooling SystemInfo
- Publication number
- JP3040656B2 JP3040656B2 JP6098444A JP9844494A JP3040656B2 JP 3040656 B2 JP3040656 B2 JP 3040656B2 JP 6098444 A JP6098444 A JP 6098444A JP 9844494 A JP9844494 A JP 9844494A JP 3040656 B2 JP3040656 B2 JP 3040656B2
- Authority
- JP
- Japan
- Prior art keywords
- platform
- gas turbine
- seal pin
- groove
- seal
- 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
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
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
-
- 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
【０００１】[0001]
【産業上の利用分野】本発明は、ガスタービン動翼のプ
ラットホームの冷却装置に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a cooling system for a gas turbine blade platform.
【０００２】[0002]
【従来の技術】図８は、代表的な従来のガスタービン中
空動翼の斜視断面図である。この従来のガスタービン中
空動翼では、翼根１１の底部から流入した冷却空気は矢
印の方向に流れて動翼を冷却する。即ち、前縁側１２Ａ
から流入した冷却空気は、フィン１３を有する曲りくね
った流路を流れて翼を冷却しチップシンニング１４が設
けられた翼頂部の穴Ａから流出して主ガス流れに合流す
る。また、後縁側１２Ｂから流入した冷却空気は、フィ
ン１３が設けられた冷却通路を矢印の方向に流れピンフ
ィン１５で翼後縁を冷却した後、穴又はスリットＢから
流出して主ガス流れに合流する。2. Description of the Related Art FIG. 8 is a perspective sectional view of a typical conventional gas turbine hollow rotor blade. In this conventional gas turbine hollow moving blade, the cooling air flowing from the bottom of the blade root 11 flows in the direction of the arrow to cool the moving blade. That is, the leading edge side 12A
Flows through the meandering flow path having the fins 13 to cool the blades, flows out of the holes A at the blade tops where the chip thinnings 14 are provided, and joins the main gas flow. The cooling air flowing in from the trailing edge side 12B flows through the cooling passage provided with the fins 13 in the direction of the arrow, cools the trailing edge of the blade with the pin fins 15, and then flows out of the holes or slits B to join the main gas flow. I do.
【０００３】このような高度な冷却構造をもつ動翼が、
円周方向に互いにプラットホーム１６を隣接させてディ
スク１７に植込まれている。[0003] A moving blade having such an advanced cooling structure is
The platforms 16 are implanted in the disk 17 circumferentially adjacent to each other.
【０００４】[0004]
【発明が解決しようとする課題】前記の従来のガスター
ビン中空動翼においては、翼根や翼に対して内部冷却を
行う高度な冷却構造をもってはいるが、冷却部位から突
出した形状となっている動翼プラットホームは殆んど無
冷却であり、冷却に対し充分な構造となってはいない。The above-mentioned conventional gas turbine hollow rotor blade has an advanced cooling structure for internally cooling the blade roots and blades, but has a shape protruding from the cooling portion. Some blade platforms are almost uncooled and are not well-structured for cooling.
【０００５】このため、今後更に高温化するガスタービ
ンに対応するために動翼プラットホームの冷却は必須項
目である。[0005] For this reason, cooling of the moving blade platform is an essential item in order to cope with a gas turbine whose temperature will be further increased in the future.
【０００６】本発明は、以上の問題点を解消するために
なされたものである。The present invention has been made to solve the above problems.
【０００７】[0007]
【課題を解決するための手段】本発明のガスタービン動
翼プラットホームの冷却装置は、次の手段を講じた。 （１） 円周方向に互いに隣接するガスタービン動翼の
プラットホームの間に隙間を設け、同隙間の一方のプラ
ットホームの端面に両側とも貫通しないシールピン溝を
設け、同シールピン溝に周方向に溝を設けた溝付きシー
ルピンを嵌入するとともに、同シールピンは他方のプラ
ットホームの端面に接するように配置したことを特徴と
する。 （２） 前記（１）のガスタービン動翼プラットホーム
の冷却装置において、円周方向に互いに隣接するガスタ
ービン動翼プラットホームの前記一方のプラットホーム
の端面に設けられた前記両側とも貫通しないシールピン
溝には同シールピン溝からプラットホーム上面に貫いた
複数の溝を設け、前記シールピン溝に前記溝付きシール
ピンに代えて丸棒ピンを嵌入したことを特徴とする。The gas turbine moving blade platform cooling apparatus of the present invention has the following features. (1) A gap is provided between the platforms of the gas turbine rotor blades that are adjacent to each other in the circumferential direction, and one of the platforms in the gap is provided .
Seal pin grooves on both sides of the
Grooved seal with a circumferential groove in the seal pin groove
The seal pin is inserted into the other plug.
It is characterized by being arranged so as to be in contact with the end face of the platform . (2) In the cooling device for a gas turbine moving blade platform (1), the one of the platform of the gas turbine moving blade platform adjacent to each other in the circumferential direction
The seal pin groove provided on the end face of the seal which does not penetrate on both sides penetrates from the seal pin groove to the upper surface of the platform.
A plurality of grooves provided, characterized in that fitted to rod pin the place of the grooved seal pin on the seal pin grooves.
【０００８】[0008]
【作用】前記本発明は（１），（２）から構成され、次
の作用を奏する。 The present invention comprises (1) and (2).
Has the effect of
【０００９】前記本発明（１）においては、円周方向に
互いに隣接するガスタービン動翼プラットホームの隙間
の一方のプラットホームの端面に両側とも貫通しないシ
ールピン溝を設け、同シールピン溝に周方向に溝を設け
た溝付きシールピンを嵌入したことによって、プラット
ホーム下面の翼根間を流れるシール空気はプラットホー
ムの下面を冷却するとともに、隙間を通って溝付きシー
ルピンの溝部から主ガス流側に流出しプラットホームの
端面及び上面を冷却する。[0009] In the above invention (1), the clearance of the gas turbine moving blade platform adjacent to each other in a circle circumferential direction
A seal pin groove that does not penetrate both sides is provided on the end face of one of the platforms, and a seal pin with a groove provided in the circumferential direction in the seal pin groove is fitted. While cooling, it flows out from the groove of the grooved seal pin to the main gas flow side through the gap to cool the end face and the upper surface of the platform.
【００１０】また、前記本発明（２）では、前記本発明
（１）において、円周方向に互いに隣接するガスタービ
ン動翼プラットホームの前記一方のプラットホームの端
面に両側とも貫通しないシールピン溝を設けるとともに
同シールピン溝からプラットフォーム上面に貫いた複数
の溝を設け、前記シールピン溝に丸棒ピンを嵌入したこ
とによって、プラットホーム下面の翼根間を流れるシー
ル空気は隙間を通り、前記複数の溝から主ガス流側に流
出し、プラットホームの下面を冷却するとともに、プラ
ットフォームの端面及び上面を冷却する。Furthermore, the in invention (2), in the present invention (1), does not penetrate both sides on the end <br/> face of said one of the platform of the gas turbine moving blade platform adjacent to each other in the circumferential direction By providing a seal pin groove and providing a plurality of grooves penetrating from the seal pin groove to the upper surface of the platform, and inserting a round bar pin into the seal pin groove, seal air flowing between the blade roots on the lower surface of the platform passes through a gap, and The gas flows out from the groove toward the main gas flow side to cool the lower surface of the platform and to cool the end surface and the upper surface of the platform.
【００１１】[0011]
【実施例】本発明の第１の実施例を、図１ないし図４に
よって説明する。円周方向に互いに隣接するガスタービ
ン動翼１のプラットホーム２とプラットホーム２の間に
は、隙間Ｃが設けられている。前記隣接するガスタービ
ン動翼１の一方のプラットホーム２の端面には、両側と
も貫通しないシ−ルピン溝Ａが削成されていて、同シ−
ルピン溝Ａには、軸方向に間隔をおいて設けられた複数
の周方向の溝３ａを備えた断面円形の溝付きシ−ルピン
３が嵌入さられており、同溝付きシ−ルピン３は、図４
に示すように、一方のプラットホーム２のシ−ルピン溝
Ａと隣接するプラットホーム２の端部に接触するように
配置されている。なお、５はプラットホーム２の下面に
連設されている翼根である。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described with reference to FIGS. A gap C is provided between the platforms 2 of the gas turbine rotor blades 1 that are circumferentially adjacent to each other. Seal pin grooves A which are not penetrated on both sides are formed in the end surface of one platform 2 of the adjacent gas turbine blade 1.
A grooved seal pin 3 having a circular cross section and having a plurality of circumferential grooves 3a provided at intervals in the axial direction is fitted into the lupine groove A. , FIG.
As shown in FIG. 2, the seal pin groove A of one of the platforms 2 is disposed so as to contact the end of the platform 2 adjacent to the seal pin groove A. Reference numeral 5 denotes a blade root continuously provided on the lower surface of the platform 2.
【００１２】本実施例では、翼根５の間を流れるシ−ル
空気は、図４中矢印で示すように、溝付きシ−ルピン３
の溝３ａと隙間Ｃを通り主ガス側に流出し、プラットホ
ーム２の下面とともに端面及び上面を冷却する。In this embodiment, the seal air flowing between the blade roots 5, as shown by arrows in FIG.
Through the groove 3a and the gap C to the main gas side to cool the end face and the upper face together with the lower face of the platform 2.
【００１３】本発明の第２の実施例を、図５ないし図７
によって説明する。円周方向に互いに隣接するガスター
ビン動翼１のプラットホーム２とプラットホーム２の間
には、隙間Ｃが設けられている。前記の隣接する動翼１
の一方のプラットホーム２の端面には、両側とも貫通し
ないシ−ルピン溝Ａが削成されるとともに、同シ−ルピ
ン溝Ａからプラットホーム２の上面に貫いた複数の溝Ｂ
が削成されている。そして丸棒形状のシ−ルピン４がシ
−ルピン溝に嵌入れられており、同シ−ルピン４は、図
７に示すように、一方のプラットホーム２のシ−ルピン
溝Ａと隣接するプラットホーム２の端部に接触するよう
に配置されている。なお、５はプラットホーム２の下面
に連設されている翼根である。FIGS. 5 to 7 show a second embodiment of the present invention.
It will be explained by. A gap C is provided between the platforms 2 of the gas turbine rotor blades 1 that are circumferentially adjacent to each other. Said adjacent bucket 1
In the end face of one of the platforms 2, a seal pin groove A which does not penetrate on both sides is formed, and a plurality of grooves B penetrating from the seal pin groove A to the upper surface of the platform 2 are formed.
Has been cut. A seal pin 4 in the form of a round bar is fitted in the seal pin groove, and the seal pin 4 is adjacent to the seal pin groove A of one of the platforms 2 as shown in FIG. Are arranged so as to come into contact with the ends of the. Reference numeral 5 denotes a blade root continuously provided on the lower surface of the platform 2.
【００１４】本実施例では、翼根５の間を流れるシ−ル
空気は、シ−ルピン溝Ａからプラットホーム２の上面に
貫通する複数の溝Ｂを通って主ガス側に流出しプラット
ホーム２の下面とともに端面及び上面を冷却する。In this embodiment, the seal air flowing between the blade roots 5 flows out from the seal pin groove A to the main gas side through a plurality of grooves B penetrating to the upper surface of the platform 2 and flows out of the platform 2. The end face and the upper face are cooled together with the lower face.
【００１５】前記第１及び第２の実施例においてはシ−
ルピン３，４を用いているが、本発明では、隙間Ｃの大
きさもしくは溝Ｂの数と大きさを適宜選定してシ−ルピ
ン３，４を省略することができる。In the first and second embodiments, the shield is
Although the lupines 3 and 4 are used, in the present invention, the size of the gap C or the number and size of the grooves B can be appropriately selected to omit the sealpins 3 and 4.
【００１６】[0016]
【発明の効果】本発明によれば、特許請求の範囲の請求
項１ないし２に記載した構成を具備することによって、
ガスタービン動翼プラットホームの下面、端面及び上面
をも冷却することができる。従って、より一層の高温化
にも対応できるとともにプラットホームの焼損事故も回
避できるなどガスタービンの信頼性向上に寄与する効果
は大きい。According to the present invention, by providing the structure according to claims 1 and 2 ,
The lower, end and upper surfaces of the gas turbine blade platform can also be cooled. Therefore, it is possible to cope with a higher temperature and to avoid a burnout accident of the platform.
【図１】本発明の第１の実施例の斜視図である。FIG. 1 is a perspective view of a first embodiment of the present invention.
【図２】図１のＸ矢視図である。FIG. 2 is a view as viewed from an arrow X in FIG. 1;
【図３】同実施例に用いられる溝付きシ−ルピンの斜視
図である。FIG. 3 is a perspective view of a grooved seal pin used in the embodiment.
【図４】図２のＹ−Ｙ断面図である。FIG. 4 is a sectional view taken along line YY of FIG. 2;
【図５】本発明の第２の実施例の斜視図である。FIG. 5 is a perspective view of a second embodiment of the present invention.
【図６】図５のＸ矢視図である。6 is a view as viewed in the direction of the arrow X in FIG. 5;
【図７】図６のＹ−Ｙ断面図である。FIG. 7 is a sectional view taken along line YY of FIG. 6;
【図８】代表的な従来のガスタービン中空動翼の斜視図
である。FIG. 8 is a perspective view of a typical conventional gas turbine hollow rotor blade.
１ ガスタービン動翼 ２ プラットホーム ３ 溝付きシ−ルピン ３ａ 溝 ４ シ−ルピン ５ 翼根 Ａ シ−ルピン溝 Ｂ 溝 Ｃ 隙間 DESCRIPTION OF SYMBOLS 1 Gas turbine rotor blade 2 Platform 3 Seal pin with groove 3a groove 4 Seal pin 5 Blade root A Seal pin groove B groove C Clearance
───────────────────────────────────────────────────── フロントページの続き (58)調査した分野(Int.Cl.7，ＤＢ名) F01D 5/18 F01D 5/08 ──────────────────────────────────────────────────続 き Continued on the front page (58) Field surveyed (Int.Cl. 7 , DB name) F01D 5/18 F01D 5/08
Claims (2)
動翼のプラットホームの間に隙間を設け、同隙間の一方
のプラットホームの端面に両側とも貫通しないシールピ
ン溝を設け、同シールピン溝に周方向に溝を設けた溝付
きシールピンを嵌入するとともに、同シールピンは他方
のプラットホームの端面に接するように配置したことを
特徴とするガスタービン動翼プラットホームの冷却装
置。A gap is provided between platforms of gas turbine blades circumferentially adjacent to each other, and one of the gaps is provided .
Seals that do not penetrate both sides of the platform
With a groove in the seal pin groove and a groove in the circumferential direction.
And the other seal pin is inserted
A cooling system for a gas turbine blade platform, wherein the cooling device is arranged so as to be in contact with an end surface of the platform .
動翼プラットホームの前記一方のプラットホームの端面
に設けられた前記両側とも貫通しないシールピン溝には
同シールピン溝からプラットホーム上面に貫いた複数の
溝を設け、前記シールピン溝に前記溝付きシールピンに
代えて丸棒ピンを嵌入したことを特徴とする請求項１に
記載のガスタービン動翼プラットホームの冷却装置。Wherein the seal pin grooves the either side does not penetrate provided on an end face of said one of the platform of the gas turbine moving blade platform adjacent to each other in the circumferential direction
A plurality of seal pins penetrated from the seal
A groove provided on the grooved seal pin on the seal pin grooves
The cooling device for a gas turbine blade platform according to claim 1, wherein a round bar pin is inserted instead .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6098444A JP3040656B2 (en) | 1994-05-12 | 1994-05-12 | Gas Turbine Blade Platform Cooling System |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP6098444A JP3040656B2 (en) | 1994-05-12 | 1994-05-12 | Gas Turbine Blade Platform Cooling System |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH07305602A JPH07305602A (en) | 1995-11-21 |
| JP3040656B2 true JP3040656B2 (en) | 2000-05-15 |
Family
ID=14219926
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP6098444A Expired - Lifetime JP3040656B2 (en) | 1994-05-12 | 1994-05-12 | Gas Turbine Blade Platform Cooling System |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3040656B2 (en) |
Families Citing this family (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10274003A (en) * | 1997-03-31 | 1998-10-13 | Mitsubishi Heavy Ind Ltd | Seal device for gas turbine |
| US6984112B2 (en) * | 2003-10-31 | 2006-01-10 | General Electric Company | Methods and apparatus for cooling gas turbine rotor blades |
| US6939107B2 (en) * | 2003-11-19 | 2005-09-06 | United Technologies Corporation | Spanwisely variable density pedestal array |
| US7189063B2 (en) * | 2004-09-02 | 2007-03-13 | General Electric Company | Methods and apparatus for cooling gas turbine engine rotor assemblies |
| US7090466B2 (en) * | 2004-09-14 | 2006-08-15 | General Electric Company | Methods and apparatus for assembling gas turbine engine rotor assemblies |
| US7163376B2 (en) * | 2004-11-24 | 2007-01-16 | General Electric Company | Controlled leakage pin and vibration damper for active cooling and purge of bucket slash faces |
| JP2006214367A (en) * | 2005-02-04 | 2006-08-17 | Mitsubishi Heavy Ind Ltd | Moving blade member |
| FR2963381B1 (en) * | 2010-07-27 | 2015-04-10 | Snecma | INTER-AUB SEALING FOR A TURBINE OR TURBOMACHINE COMPRESSOR WHEEL |
| US8876479B2 (en) * | 2011-03-15 | 2014-11-04 | United Technologies Corporation | Damper pin |
| US9879548B2 (en) * | 2015-05-14 | 2018-01-30 | General Electric Company | Turbine blade damper system having pin with slots |
| US20170067347A1 (en) * | 2015-09-03 | 2017-03-09 | General Electric Company | Slotted damper pin for a turbine blade |
| EP3438410B1 (en) | 2017-08-01 | 2021-09-29 | General Electric Company | Sealing system for a rotary machine |
| JP6985197B2 (en) * | 2018-03-28 | 2021-12-22 | 三菱重工業株式会社 | Rotating machine |
-
1994
- 1994-05-12 JP JP6098444A patent/JP3040656B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH07305602A (en) | 1995-11-21 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP3040656B2 (en) | Gas Turbine Blade Platform Cooling System | |
| KR100567693B1 (en) | Turbine blade with platform cooling | |
| US6179556B1 (en) | Turbine blade tip with offset squealer | |
| EP1600605B1 (en) | Cooled rotor blade | |
| KR100653816B1 (en) | Hollow airfoil for a gas turbine engine | |
| JP4713423B2 (en) | Oblique tip hole turbine blade | |
| EP1840330B1 (en) | Turbulator arrangement for passageways | |
| CA2381474C (en) | Gas turbine cooled blade | |
| EP1790822B1 (en) | Microcircuit cooling for blades | |
| US6350102B1 (en) | Shroud leakage flow discouragers | |
| JPH09151705A (en) | Shroud for rotor assembly | |
| EP1391581A1 (en) | Gas turbine moving blade | |
| EP1605138B1 (en) | Cooled rotor blade with leading edge impingement cooling | |
| JP3510467B2 (en) | Gas turbine blades | |
| JPH08232601A (en) | Sealing device of clearance between adjacent bland of rotor assembly for gas turbine engine | |
| EP1790824B1 (en) | A cooling arrangement | |
| US9562437B2 (en) | Turbine blade airfoils including film cooling systems, and methods for forming an improved film cooled airfoil of a turbine blade | |
| JP3188105B2 (en) | Gas turbine blades | |
| JP3040660B2 (en) | Gas Turbine Blade Platform Cooling Mechanism | |
| US20030082050A1 (en) | Device for sealing turbomachines | |
| CA2287577A1 (en) | Gas turbine cooled moving blade | |
| JP3095633B2 (en) | Cooling system for high temperature part of gas turbine | |
| JP3416184B2 (en) | Cooling structure at the tip of a gas turbine air-cooled rotor blade | |
| JPH0463901A (en) | Gas turbine cooling blade | |
| JPH0882201A (en) | Gas turbine moving blade and manufacture thereof |
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: 20000201 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20080303 Year of fee payment: 8 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090303 Year of fee payment: 9 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100303 Year of fee payment: 10 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110303 Year of fee payment: 11 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20110303 Year of fee payment: 11 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120303 Year of fee payment: 12 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20130303 Year of fee payment: 13 |
|
| FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20140303 Year of fee payment: 14 |
|
| EXPY | Cancellation because of completion of term |