JPH08505917A - 冷却可能なエアフォイル - Google Patents
冷却可能なエアフォイルInfo
- Publication number
- JPH08505917A JPH08505917A JP6513160A JP51316094A JPH08505917A JP H08505917 A JPH08505917 A JP H08505917A JP 6513160 A JP6513160 A JP 6513160A JP 51316094 A JP51316094 A JP 51316094A JP H08505917 A JPH08505917 A JP H08505917A
- Authority
- JP
- Japan
- Prior art keywords
- passage
- cooling air
- airfoil
- region
- rib
- 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
Classifications
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- 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
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- 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
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
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- 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
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
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- 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims (1)
- 【特許請求の範囲】 1.前縁と後縁とを有するエアフォイル部と、 前記エアフォイル部に冷却空気を供給する付根部と、 前記付根部からスパン方向に間隔を置かれて前記エアフォイル部内に配置され た翼端領域とを有する回転機器のための冷却可能なエアフォイルであって、前記 翼端領域は上流端と当該ブレードの外部と連通する下流端とを有するスパン方向 に延在する翼端通路を有しており、更に、 前記エアフォイル部は、 前記翼端領域へと外向きに延在する冷却空気のための第1通路の境界を形成す る吸い込み側壁及び圧力側壁と、 前記第1通路への熱の伝達を防ぐべく前記第1通路に近接する当該エアフォイ ル構造の外部をフィルム式に冷却するための手段と、 前記翼端領域へと外向きに延在する曲折した通路であって、前記第1通路の後 方に位置すると共に少なくとも前記第1通路の2倍の長さを有する該曲折通路と を有しており、 更に、 前記第1通路と前記曲折通路は、前記翼端通路の上流端に冷却空気を放出する ように前記翼端通路と連通しており、 動作状態に於いては、前記第1通路からの冷却空気の温度が前記曲折通路から の冷却空気の温度よりも低く、前記翼端通路に於いて混合冷却空気の温度が下が るようになっていることを特徴とするエアフォイル。 2.前記前縁との間に衝当空間を形成するように衝当板が前記前縁からスパン方 向に間隔を置いて配置されており、 この衝当板は前記第1通路の境界を形成すると共に、衝当孔を有しており、前 記第1通路と前記衝当空間とを連通させて前記前縁に冷却空気が衝当するように なっており、 更に、前記エアフォイルの側壁を貫通するフィルム式冷却用孔が、前記衝当空 間と当該ブレードの外側を連通させており、前記第1通路をフィルム式に冷却す るようになっていることを特徴とする請求項1に記載の冷却可能なエアフォイル 。 3.前記フィルム式冷却用孔が前記翼端通路から前記エアフォイル部の外側まで 延在しており、前記翼端通路の下流端が前記エアフォイル部の後縁領域と連通し ていることを特徴とする請求項2に記載の冷却可能なエアフォイル。 4.軸流回転機器のための冷却可能なロータブレードであって、 翼弦方向に延在する付根壁を有し当該ロータブレードをロータアセンブリに係 合する付根部と、 前記付根壁を通して冷却空気供給源と連通するように適合された第1ダクトと 、 前記付根壁を通して冷却空気供給源と連通するように適合された第2ダクトと 、 前記付根壁を通して冷却空気供給源と連通するように適合された第3ダクトと を備え、 更に、前記エアフォイル部は、 前縁と、 後縁と、 吸い込み側壁と、 前記前縁と後縁とに於いて前記吸い込み側壁との間に間隔をあけられて接合さ れ、そこにキャビティを形成する圧力側壁と、 前記吸い込み側壁と圧力側壁との間に翼弦方向に延在する壁を有する翼端領域 と、 前記翼端の壁へとスパン方向に延在すると共に、前記前縁との間に間隔があけ られており、前記キャビティを後方部と前記第1ダクトと連通する第1通路を含 む前方部とに分割する第1リブと、 スパン方向に延在すると共に、前記第1リブとの間に翼弦方向に間隔が置かれ て、前記キャビティの後方部を翼弦中央領域と前記第3ダクトと連通した後縁領 域とに分割すると同時に、前記翼端壁との間にスパン方向に間隔を置いて翼弦方 向に延在しそこに前記翼弦中央領域と連通する翼端通路を形成する第2リブと、 前記付根壁からスパン方向に延在して、当該ブレードの前記翼弦中央領域を前 記付根領域から前記翼端領域へと外向きに延在する第2通路と、前記翼端領域か ら前記付根領域へと内向きに延在する第3通路とに分割すると同時に、第1曲が り通路を形成するように前記第2リブの翼弦方向 延在部分との間にスパン方向に間隔が置かれている第3リブと、 前記第2リブの翼弦方向延在部分から前記付根領域へとスパン方向に延在して 第3通路の境界を形成すると共に、前記第1リブとの間に翼弦方向に間隔が置か れておりそこに外向きに延在しかつ前記翼端通路と連通する第4通路を形成し、 更に、前記付根壁との間にスパン方向に間隔が置かれてそこに前記第4通路を前 記第3通路に連通させる第2曲がり通路を形成する第4リブと、 当該エアフォイルの前記前方部内に前記翼端壁から前記付根壁へとスパン方向 に延在して前記第1通路の境界を形成すると共に、前記前縁との間に翼弦方向に 間隔が置かれてそこに衝当空間を形成する第5リブであって、前記第1通路と前 記前縁とを連通させる該リブを貫通する複数の衝当孔を有する該第5リブとを有 し、 更に、 当該エアフォイルを冷却すると共に作動媒体ガスから前記第1通路への熱の伝 達を防ぐように、複数のフィルム式冷却用孔が前記衝当空間から当該エアフォイ ルの外側へと前記前縁を貫通しており、 前記第2、第3及び第4通路によって前記翼弦領域内に曲折通路が形成される ように、前記第2通路は該第2通路へ冷却空気が供給されるように前記第2ダク トと連通し、この冷却空気は第3通路を内向きに、第4通路を外向きに 前記翼端通路へと流れることができ、 前記第1通路からの冷却空気と前記翼弦中央領域の前記曲折通路からの冷却空 気とを混合するように前記第1通路を前記翼端通路と連通させるため、前記翼端 領域に於いて開口が前記第1リブを貫通して延在していることを特徴とするロー タブレード。 5.第6リブが前記第2通路内にスパン方向に置かれて、前記第2通路のスパン 方向延在部分に於いて前記側壁間の高さHに対する幅Wの比が1.0以下(W/ H≦1.0)となるサブ通路を形成していることを特徴とする請求項4に記載の ロータブレード。 6.第6リブが、前記第1曲がり通路内へと延在してサブ通路を形成しており、 前記曲がり通路に於いて前記サブ通路の各々の前記側壁間の高さHに対する幅W の比が1.5以下(W/H≦1.5)となっていることを特徴とする請求項4に 記載のロータブレード。 7.前記第6リブが前記第1曲がり通路内へと延在してサブ通路を形成しており 、前記曲がり通路に於いて前記サブ通路の各々の前記側壁間の高さHに対する幅 Wの比が1.5以下(W/H≦1.5)となっていることを特徴とする請求項5 に記載のロータブレード。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US07/982,820 | 1992-11-30 | ||
US07/982,820 US5403159A (en) | 1992-11-30 | 1992-11-30 | Coolable airfoil structure |
PCT/US1993/010714 WO1994012766A1 (en) | 1992-11-30 | 1993-11-04 | Coolable airfoil structure |
Publications (2)
Publication Number | Publication Date |
---|---|
JPH08505917A true JPH08505917A (ja) | 1996-06-25 |
JP3337219B2 JP3337219B2 (ja) | 2002-10-21 |
Family
ID=25529536
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP51316094A Expired - Fee Related JP3337219B2 (ja) | 1992-11-30 | 1993-11-04 | 冷却可能なエアフォイル |
Country Status (5)
Country | Link |
---|---|
US (1) | US5403159A (ja) |
EP (1) | EP0670953B1 (ja) |
JP (1) | JP3337219B2 (ja) |
DE (1) | DE69320203T2 (ja) |
WO (1) | WO1994012766A1 (ja) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2000291406A (ja) * | 1999-03-05 | 2000-10-17 | General Electric Co <Ge> | 多重衝突翼冷却 |
JP2007263112A (ja) * | 2006-03-28 | 2007-10-11 | United Technol Corp <Utc> | 冷却通路およびタービンエンジン構成要素 |
JP2016503850A (ja) * | 2012-12-14 | 2016-02-08 | シーメンス アクティエンゲゼルシャフト | サーペンタイン冷却回路及びアキシアル方向先端部冷却回路が組み込まれたタービンブレード |
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-
1993
- 1993-11-04 DE DE69320203T patent/DE69320203T2/de not_active Expired - Lifetime
- 1993-11-04 WO PCT/US1993/010714 patent/WO1994012766A1/en active IP Right Grant
- 1993-11-04 JP JP51316094A patent/JP3337219B2/ja not_active Expired - Fee Related
- 1993-11-04 EP EP94904376A patent/EP0670953B1/en not_active Expired - Lifetime
Cited By (3)
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JP2000291406A (ja) * | 1999-03-05 | 2000-10-17 | General Electric Co <Ge> | 多重衝突翼冷却 |
JP2007263112A (ja) * | 2006-03-28 | 2007-10-11 | United Technol Corp <Utc> | 冷却通路およびタービンエンジン構成要素 |
JP2016503850A (ja) * | 2012-12-14 | 2016-02-08 | シーメンス アクティエンゲゼルシャフト | サーペンタイン冷却回路及びアキシアル方向先端部冷却回路が組み込まれたタービンブレード |
Also Published As
Publication number | Publication date |
---|---|
WO1994012766A1 (en) | 1994-06-09 |
US5403159A (en) | 1995-04-04 |
EP0670953A1 (en) | 1995-09-13 |
DE69320203T2 (de) | 1999-04-29 |
DE69320203D1 (de) | 1998-09-10 |
EP0670953B1 (en) | 1998-08-05 |
JP3337219B2 (ja) | 2002-10-21 |
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