WO1997025522A1 - Stationary blade for gas turbine - Google Patents

Stationary blade for gas turbine Download PDF

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Publication number
WO1997025522A1
WO1997025522A1 PCT/JP1996/003696 JP9603696W WO9725522A1 WO 1997025522 A1 WO1997025522 A1 WO 1997025522A1 JP 9603696 W JP9603696 W JP 9603696W WO 9725522 A1 WO9725522 A1 WO 9725522A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling
steam
gas turbine
cooled
shroud
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.)
Ceased
Application number
PCT/JP1996/003696
Other languages
English (en)
French (fr)
Inventor
Masaaki Matsuura
Kiyoshi Suenaga
Kazuo Uematsu
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Priority to US08/913,077 priority Critical patent/US5954475A/en
Priority to EP96942570A priority patent/EP0814234B1/en
Priority to CA002214826A priority patent/CA2214826C/en
Priority to DE69622160T priority patent/DE69622160T2/de
Publication of WO1997025522A1 publication Critical patent/WO1997025522A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • 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
    • F01D5/182—Transpiration 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • 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
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • 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
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the present invention relates to a gas turbine stationary blade capable of performing cooling with a simple configuration without pressure loss of cooling steam.
  • FIGS 3 and 4 show examples of conventional cooling structures for steam-cooled gas turbine vanes.
  • the cooling steam is supplied from the cooling steam inlet 5 of the outer shroud 3 as shown by the arrow, passes through the impingement plate 13 provided with a number of pores, and passes through the inward cooling passage 7 in the wing portion 2.
  • the outer shroud After cooling the inner shroud 4 a through the internal cooling passage 9 with fins provided in the inner shroud 4 a, the outer shroud passes through the outward passage 8 in the wing 2 again.
  • the conventional steam-cooled gas turbine vane of the conventional steam cooling has a complicated cooling passage shape of the inner shroud for flowing the cooling steam from the inward passage to the outward passage in the blade.
  • Technical difficulties and high costs In addition, the pressure loss when the cooling steam passes through the narrow part of the inner shroud becomes large, leading to a decrease in the efficiency of the gas turbine. Disclosure of the invention
  • An object of the present invention is to provide a gas turbine stationary blade capable of solving the above problems.
  • the gas turbine static g of the present invention is characterized in that the outer shroud and the blade are cooled by steam, and the inner shroud is cooled by air.
  • the outer shroud and the inner space are cooled by steam, and the inner shroud is cooled by air coming from another system, so that the shroud and the wing are cooled effectively.
  • the cooling steam changes its direction from the inward cooling passage to the outward cooling passage, and does not pass through the inner shroud. Can be achieved with low pressure loss and a simple return flow path.
  • FIG. 1 is a longitudinal sectional view of a gas turbine stationary blade according to an embodiment of the present invention.
  • FIG. 2 is a cross-sectional view taken along the line AA of FIG.
  • FIG. 3 is a longitudinal sectional view of a conventional steam-cooled gas turbine vane.
  • FIG. 4 is a sectional view taken along the line BB of FIG. BEST MODE FOR CARRYING OUT THE INVENTION
  • the cooling structure of the outer shroud 3 and the wing section 2 by steam in this embodiment is almost the same as that of the prior art shown in FIGS.
  • the supplied cooling steam cools the outer shroud 3 and the blade section 2 as described below, and then is discharged from the cooling steam outlet 6 to the outside of the blade to be completely recovered.
  • the inner shroud In section 4 the cooling steam passage is configured as a simple return type that simply changes its direction from the inward passage 7 in the wing portion 2 to the outward passage 8, and the inner shroud 4 has the shapes shown in Figs. 3 and 4. Is not provided, and the cooling steam is not introduced into the inner shaft 4.
  • the inner shroud 4 is cooled by supplying air partially extracted from the combustion air separately from the inner cooling air inlet 11 to the inner shroud 4 and passing through the impingement plate 10 provided with many pores to the inner surface of the shroud.
  • the spraying is performed by cooling the shroud metal.
  • a number of film cooling holes 12 are formed in the surface of the inner shroud 4, and the cooling air that has cooled the shroud metal of the inner shroud 4 blows out into the mainstream gas 1 through the cooling holes 12.
  • film cooling is performed in which the shroud surface of the inner shroud 4 is shielded with low-temperature air from high-temperature gas.
  • the present embodiment has the above configuration, a predetermined cooling effect is achieved in the inner shroud 4 with a very small amount of air. Further, the steam for cooling the wing portion 2 only flows through a simple return-type passage provided in the wing portion 2, so that the pressure loss of the steam flow is suppressed to a small level.
  • a steam-cooled vane that performs air cooling only on the inner shroud eliminates the complexity of the cooling structure and reduces the pressure loss of the cooling steam. Reduced. As a result, it is possible to prevent the efficiency of the gas turbine from lowering and to reduce the production cost without impairing the predetermined cooling effect.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

明 細 書 ガスタービン静翼 技術分野
本発明は、 簡単な構成によって冷却蒸気の圧力損失なく冷却を行うこと ができるようにしたガスタービン静翼に関する。 背景技術
近年、 産業用ガスタービンのタービン入口ガス温度は高出力、 高効率を 図るために上昇し、 1 5 0 0 'Cにも達するものと予想されている。 このた め、 ガスタービン静翼の冷却は冷却効果の高い水蒸気を内部に流し行うこ とがある。 図 3及び図 4に従来の蒸気冷却のガスタービン静翼の冷却構造 例を示す。 冷却蒸気は、 矢印に示すように、 外側シュラウド 3の冷却蒸気 入口 5から供給され、 多数の細孔が設けられたインピンジメント板 1 3を 通って翼部 2内の内向き冷却通路 7を通って翼面を冷却し、 内側シュラウ ド 4 aに設けられたフィ ン付内部冷却通路 9を通って内側シュラウド 4 a を冷却した後、 再度翼部 2内の外向き通路 8を通り、 外側シュラウド 3の 冷却蒸気出口 6より薦外に排出され、 全量回収されるようになっている。 前記の従来の蒸気冷却のガスタービン静翼では、 図 3及び図 4に示すよ うに、翼部内の内向き通路から外向き通路へ冷却蒸気を流す内側シュラウ ドの冷却通路形状が複雑となり、 製作する上での技術的困難さ、 コスト高 につながる。 また、 冷却蒸気が内側シュラウ ドの狭あい部を通過する際の 圧力桟失が大となり、 ガスタービンの効率の低下につながる。 発明の開示
本発明は、 以上の問題点を解決することができるガスタービン静翼を提 供しょうとするものである。
本発明のガスタービン静 gは、 外側シュラウドと翼部は蒸気によって冷 却し、 内側シュラウ ドは空気によって冷却することを特徴とする。
本発明では、 外側シュラウドと ¾都を蒸気によって冷却し、 内側シユラ ウドは、 別系統からくる空気によって冷却しており、 シュラウドと翼部の 冷却が効果的に行われる。 また、 冷却蒸気は、 内向き冷却通路から外向き 冷却通路へ方向を変えて流れて内側シュラウ ド内を通ることがなく、 蒸気 が流れる冷却通路の形状は簡単となり、 萬部と外側シュラウドの冷却を低 い圧力損失と単純なリターンフロ一通路で達成することができる。 図面の簡単な説明
第 1図は本発明の実施の一形態に係るガスタービン静翼の縦断面図であ る。 第 2図は第 1図の A— A矢視断面図である。 第 3図は従来の蒸気冷却 ガスタービン静翼の縦断面図である。 第 4図は第 3図の B— B矢視断面図 である。 発明を実施するための最良の形態
本発明の実施の一形態を、 図 1及び図 2によって説明する。 本実施の形 態における外側シュラウ ド 3及び翼部 2の蒸気による冷却構造は、 図 3及 び図 4に示される従来技術におけるとほぼ同じであり、 冷却蒸気入口 5よ り外側シュラウ ド 3に供給された冷却蒸気は以下述べるように外側シュラ ゥ ド 3と翼部 2を冷却した上、 冷却蒸気出口 6より翼外に排出され、 全量 回収されるようになっている。 ただ、 本実施の形態では、 内側シュラウ ド 4の部分で冷却蒸気の通路は翼部 2内の内向き通路 7から外向き通路 8へ 単純に向き力く変わるのみの単純なリターン型に構成され、 内側シュラウド 4には図 3及び図 4に示されるフィン付内部通路 9が設けられておらず、 冷却蒸気は内側シユラゥド 4へは導入されないようになっている。
内側シュラウド 4の冷却は、 別途燃焼用空気から一部抽気した空気を、 内側の冷却空気入口 1 1から内側シュラウド 4へ供給し多数の細孔が設け られたィンビンジメント板 1 0を通してシュラウ ド内面に吹きつけてシュ ラウドメタルを冷却して行うようになっている。 また、 内側シュラウド 4 の面にはフィルム冷却孔 1 2が多数あけられており、 前記内側シュラウ ド 4のシユラウドメタルを冷却した冷却空気は、 冷却孔 1 2力、ら主流ガス 1 中に吹出し、 高温ガスから内側シュラウド 4のシュラウド面を低温の空気 でしゃへいするフィルム冷却を行うようになっている。
本実施の形態は、 以上の構成を具備しているので、 内側シュラウド 4で は、 極少量の空気により所定の冷却効果が達成される。 また、 翼部 2を冷 却する蒸気は、 翼部 2内に設けられた単純なリタ一ン型通路を流れるだけ となるので、 蒸気流の圧力損失カ嘬小に押さえられる。 産業上の利用可能性
本発明では、 特許請求の範囲に記載したように、 内側シュラウ ドのみを 空気冷却を行う蒸気冷却静翼を採用しているので、 冷却構造の複雑さが解 消され、 冷却蒸気の圧力損失が低減される。 これにより、 所定冷却効果を 損うことなく、 ガスタービンの効率の低下を防ぎ、 かつ、 製作コス トの低 减を図ることができる。

Claims

請 求 の 範 囲
1 . 外側シュラウドと翼部は蒸気によって冷却し、 内側シュラウドは空 気によって冷却することを特徴とするガスタービン静¾。
2 . 翼部内に設けられ外側シュラウドの冷却蒸気入口から冷却蒸気が供 袷される内向き冷却通路、 及び翼部内に設けられ前記内向き冷却通路から の冷却蒸気の方向を変え内側シュラウドを通ることなく冷却蒸気を外側シ ュラウドの冷却蒸気出口へ導く外向き冷却通路を備えたことを特徴とする 請求項 1に記載のガスタービン静翼。
PCT/JP1996/003696 1996-01-08 1996-12-19 Stationary blade for gas turbine Ceased WO1997025522A1 (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US08/913,077 US5954475A (en) 1996-01-08 1996-12-19 Gas turbine stationary blade
EP96942570A EP0814234B1 (en) 1996-01-08 1996-12-19 Stationary blade for gas turbine
CA002214826A CA2214826C (en) 1996-01-08 1996-12-19 Gas turbine stationary blade
DE69622160T DE69622160T2 (de) 1996-01-08 1996-12-19 Leitschaufel für eine gasturbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP8000749A JP2971386B2 (ja) 1996-01-08 1996-01-08 ガスタービン静翼
JP8/749 1996-01-08

Publications (1)

Publication Number Publication Date
WO1997025522A1 true WO1997025522A1 (en) 1997-07-17

Family

ID=11482354

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP1996/003696 Ceased WO1997025522A1 (en) 1996-01-08 1996-12-19 Stationary blade for gas turbine

Country Status (8)

Country Link
US (1) US5954475A (ja)
EP (1) EP0814234B1 (ja)
JP (1) JP2971386B2 (ja)
KR (1) KR100264182B1 (ja)
CN (1) CN1081289C (ja)
CA (1) CA2214826C (ja)
DE (1) DE69622160T2 (ja)
WO (1) WO1997025522A1 (ja)

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JPH1037704A (ja) * 1996-07-19 1998-02-10 Mitsubishi Heavy Ind Ltd ガスタービンの静翼
JP3316405B2 (ja) * 1997-02-04 2002-08-19 三菱重工業株式会社 ガスタービン冷却静翼
JP3316415B2 (ja) * 1997-05-01 2002-08-19 三菱重工業株式会社 ガスタービン冷却静翼
US6315518B1 (en) 1998-01-20 2001-11-13 Mitsubishi Heavy Industries, Ltd. Stationary blade of gas turbine
US6176678B1 (en) * 1998-11-06 2001-01-23 General Electric Company Apparatus and methods for turbine blade cooling
EP1101901A1 (de) * 1999-11-16 2001-05-23 Siemens Aktiengesellschaft Turbinenschaufel sowie Verfahren zur Herstellung einer Turbinenschaufel
US6413040B1 (en) * 2000-06-13 2002-07-02 General Electric Company Support pedestals for interconnecting a cover and nozzle band wall in a gas turbine nozzle segment
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US8011881B1 (en) * 2008-01-21 2011-09-06 Florida Turbine Technologies, Inc. Turbine vane with serpentine cooling
EP2093381A1 (en) * 2008-02-25 2009-08-26 Siemens Aktiengesellschaft Turbine blade or vane with cooled platform
US8096772B2 (en) * 2009-03-20 2012-01-17 Siemens Energy, Inc. Turbine vane for a gas turbine engine having serpentine cooling channels within the inner endwall
US8734108B1 (en) * 2011-11-22 2014-05-27 Florida Turbine Technologies, Inc. Turbine blade with impingement cooling cavities and platform cooling channels connected in series
US8905714B2 (en) * 2011-12-30 2014-12-09 General Electric Company Turbine rotor blade platform cooling
EP2626519A1 (en) 2012-02-09 2013-08-14 Siemens Aktiengesellschaft Turbine assembly, corresponding impingement cooling tube and gas turbine engine
CN103306742B (zh) * 2012-03-13 2015-10-28 马重芳 冷却燃气轮机叶片的方法
US9151164B2 (en) * 2012-03-21 2015-10-06 Pratt & Whitney Canada Corp. Dual-use of cooling air for turbine vane and method
US20140064942A1 (en) * 2012-08-31 2014-03-06 General Electric Company Turbine rotor blade platform cooling
US9194237B2 (en) * 2012-09-10 2015-11-24 General Electric Company Serpentine cooling of nozzle endwall
US9771816B2 (en) 2014-05-07 2017-09-26 General Electric Company Blade cooling circuit feed duct, exhaust duct, and related cooling structure
US9638045B2 (en) * 2014-05-28 2017-05-02 General Electric Company Cooling structure for stationary blade
US9909436B2 (en) 2015-07-16 2018-03-06 General Electric Company Cooling structure for stationary blade
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JPH04311604A (ja) * 1991-04-11 1992-11-04 Toshiba Corp タービン静翼
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JPH0828205A (ja) * 1994-07-20 1996-01-30 Hitachi Ltd ガスタービン静翼

Also Published As

Publication number Publication date
CN1177994A (zh) 1998-04-01
CN1081289C (zh) 2002-03-20
JP2971386B2 (ja) 1999-11-02
EP0814234A1 (en) 1997-12-29
CA2214826C (en) 2000-09-12
DE69622160T2 (de) 2003-01-23
JPH09189203A (ja) 1997-07-22
DE69622160D1 (de) 2002-08-08
CA2214826A1 (en) 1997-07-17
KR100264182B1 (ko) 2000-08-16
US5954475A (en) 1999-09-21
EP0814234B1 (en) 2002-07-03
KR19980702822A (ko) 1998-08-05
EP0814234A4 (en) 1999-03-24

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