JP4594685B2 - 涙滴形フィルム冷却式ブレード - Google Patents
涙滴形フィルム冷却式ブレード Download PDFInfo
- Publication number
- JP4594685B2 JP4594685B2 JP2004269423A JP2004269423A JP4594685B2 JP 4594685 B2 JP4594685 B2 JP 4594685B2 JP 2004269423 A JP2004269423 A JP 2004269423A JP 2004269423 A JP2004269423 A JP 2004269423A JP 4594685 B2 JP4594685 B2 JP 4594685B2
- Authority
- JP
- Japan
- Prior art keywords
- holes
- airfoil
- side wall
- along
- row
- 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 - Fee Related
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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
- F01D5/14—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
- F01D5/186—Film 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
- F01D5/187—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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
-
- 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)
Description
12 翼形部
14 支持ダブテール
16 プラットホーム
18 正圧側壁
20 負圧側壁
22 前縁
24 後縁
26 翼形部根元
28 翼形部先端
30 内部冷却回路
34 第1の流路
36 第2の流路
38 ブリッジ
40 インピンジメント開口
42 第1の拡散フィルム冷却孔
48 第2の拡散フィルム冷却孔
54 通常型のフィルム冷却孔
66 底孔
68 先端孔
Claims (6)
- タービンブレード(10)であって、
支持ダブテール(14)に一体形に接合された翼形部(12)を含み、
前記翼形部が、対向する前縁及び後縁(22、24)間で翼弦方向にかつスパンにわたって根元(26)から先端(28)まで延びる対向する正圧及び負圧側壁(18、20)と、内部冷却回路(30)と、前記翼形部正圧及び負圧側壁(18、20)の外部表面を被覆する断熱皮膜(58)とを含み、
前記冷却回路が、前記前縁(22)の直ぐ背後に配置され、次に前記正圧及び負圧側壁に一体形に接合されたブリッジ(38)によってそれから分離された第2の流路(36)が続く第1の流路(34)を含み、
前記ブリッジ(38)が、前記第2の流路(36)から第1の流路(34)内に前記前縁(22)の背後にインピンジメントする状態で空気を吐出するインピンジメント開口(40)の列を含み、
前記負圧側壁が、前記第1の流路(34)と流れ連通した状態で該負圧側壁を貫通して延びる第1の拡散フィルム冷却孔(42)の列を含み、前記第1の孔が、前記負圧側壁(20)の凸面形輪郭内にほぼ涙滴形出口(46)を形成する四辺形断面で該負圧側壁を複合傾斜角度で貫通して配置され、前記涙滴形出口が、前記断熱皮膜を貫通して延び、
前記翼形部先端(28)が、前記正圧及び負圧側壁(18、20)から外向きに延びてその間に陥凹先端底(64)を形成するスキーラリブを含み、
前記先端底(64)が、前記正圧及び負圧側壁(18、20)の両方に沿って前記スキーラリブの内部側に底孔(66)の列を含み、
前記正圧側壁(18)が、前記スキーラリブ(28)の下方で該正圧側壁に配置された先端孔(68)の軸方向列を含み、
前記第1の孔(42)が各々、前記第1の流路(34)から負圧側壁(20)を貫通して延び、次にそれから発散する前記涙滴形出口(46)が続く一様入口(44)を含み、
前記涙滴形出口(46)が、前記翼形部スパンに沿って前記第1の孔(42)の列に整列したほぼ直線状側辺部と、前記直線状側辺部から前縁(22)に向かって延びかつ前記凸面形輪郭に沿った円弧状側辺部によって互いに結合された2つの傾斜側辺部とを含み、
前記ブレードは、前記第1の孔(42)の列に隣接して前記負圧側壁(20)を貫通して延びる第2の拡散フィルム冷却孔(48)の列をさらに含み、前記第2の孔が、前記負圧側壁の凸面形輪郭内にほぼ涙滴形出口(52)を形成する四辺形断面で該負圧側壁を複合傾斜角度で貫通して配置されており、
前記第2の孔(48)が各々、前記第1の流路(34)から負圧側壁(20)を貫通して延び、次にそれから発散する前記涙滴形出口(52)が続く一様入口(50)を含み、
前記第2の孔の涙滴形出口(52)が、前記翼形部スパンに沿って前記第2の孔(48)の列に整列したほぼ直線状側辺部と、前記直線状側辺部から前縁(22)に向かって延びかつ前記凸面形輪郭に沿った円弧状側辺部によって互いに結合された2つの傾斜側辺部とを含み、
前記第2の孔(48)の列が、前記翼形部スパンに沿って前記第1の孔(42)の列と千鳥配列されており、
前記第1及び第2の孔(42、48)が、前記翼形部スパンに沿って重なり合い、前記翼形部負圧側壁(20)に沿って、前記各孔から吐出された連続して一列に並んだフィルム冷却空気をもたらし、
前記第1及び第2の孔(42、48)が、前記翼形部スパンに沿った約45度よりも大きいほぼ同じ外向き傾斜スパン方向角度を有し、前記出口(46、52)が対応する入口よりも前記先端により接近している
ことを特徴とする、ブレード。 - 前記第1及び第2の孔(42、48)が、前記負圧側壁に沿って約45度よりも大きい異なる傾斜翼弦方向角度を有し、前記出口(46、52)が、対応する入口よりも前記後縁により接近しており、
前記第1の孔(42)の列が、12個の孔から成り、
前記第2の孔(48)の列が、13個の孔から成る、
ことを特徴とする請求項1に記載のブレード。 - 前記断熱皮膜(58)がセラミック材料からなることを特徴とする請求項1又は2に記載のブレード。
- 前記正圧及び負圧側壁(18、20)が、金属基体(62)からなり、
前記断熱皮膜(58)は、プラチナアルミナイドを含むボンドコート(60)により前記金属基体(62)に付着されることを特徴とする請求項1乃至3のいずれか1項に記載のブレード。 - 前記底孔(66)は、前記正圧側壁(18)に沿って8個が配置され、前記負圧側壁(20)に沿って7個が配置されていることを特徴とする請求項1乃至4のいずれか1項に記載のブレード。
- 前記先端底(64)の後縁(24)側の後方端部において前記正圧及び負圧側壁(18、20)の中間に配置された底孔を更に含むことを特徴とする請求項5に記載のブレード。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/664,649 US7008186B2 (en) | 2003-09-17 | 2003-09-17 | Teardrop film cooled blade |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005090511A JP2005090511A (ja) | 2005-04-07 |
JP4594685B2 true JP4594685B2 (ja) | 2010-12-08 |
Family
ID=34194753
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2004269423A Expired - Fee Related JP4594685B2 (ja) | 2003-09-17 | 2004-09-16 | 涙滴形フィルム冷却式ブレード |
Country Status (4)
Country | Link |
---|---|
US (1) | US7008186B2 (ja) |
EP (1) | EP1517003B1 (ja) |
JP (1) | JP4594685B2 (ja) |
CA (1) | CA2480989C (ja) |
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JP4931507B2 (ja) | 2005-07-26 | 2012-05-16 | スネクマ | 壁内に形成された冷却流路 |
US7452186B2 (en) * | 2005-08-16 | 2008-11-18 | United Technologies Corporation | Turbine blade including revised trailing edge cooling |
US7249934B2 (en) * | 2005-08-31 | 2007-07-31 | General Electric Company | Pattern cooled turbine airfoil |
US7625178B2 (en) * | 2006-08-30 | 2009-12-01 | Honeywell International Inc. | High effectiveness cooled turbine blade |
US7563073B1 (en) | 2006-10-10 | 2009-07-21 | Florida Turbine Technologies, Inc. | Turbine blade with film cooling slot |
JP4941891B2 (ja) | 2006-11-13 | 2012-05-30 | 株式会社Ihi | フィルム冷却構造 |
US7704048B2 (en) * | 2006-12-15 | 2010-04-27 | Siemens Energy, Inc. | Turbine airfoil with controlled area cooling arrangement |
US7704046B1 (en) * | 2007-05-24 | 2010-04-27 | Florida Turbine Technologies, Inc. | Turbine blade with serpentine cooling circuit |
US20090000754A1 (en) | 2007-06-27 | 2009-01-01 | United Technologies Corporation | Investment casting cores and methods |
US8292581B2 (en) * | 2008-01-09 | 2012-10-23 | Honeywell International Inc. | Air cooled turbine blades and methods of manufacturing |
US8087892B1 (en) * | 2008-02-22 | 2012-01-03 | Florida Turbine Technologies, Inc. | Turbine blade with dual serpentine flow circuits |
US8052378B2 (en) * | 2009-03-18 | 2011-11-08 | General Electric Company | Film-cooling augmentation device and turbine airfoil incorporating the same |
US20100239409A1 (en) * | 2009-03-18 | 2010-09-23 | General Electric Company | Method of Using and Reconstructing a Film-Cooling Augmentation Device for a Turbine Airfoil |
US8118553B2 (en) * | 2009-03-20 | 2012-02-21 | Siemens Energy, Inc. | Turbine airfoil cooling system with dual serpentine cooling chambers |
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US8529193B2 (en) * | 2009-11-25 | 2013-09-10 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
US8628293B2 (en) | 2010-06-17 | 2014-01-14 | Honeywell International Inc. | Gas turbine engine components with cooling hole trenches |
FR2961552B1 (fr) * | 2010-06-21 | 2014-01-31 | Snecma | Aube de turbine a cavite de bord d'attaque refroidie par impact |
US8568085B2 (en) | 2010-07-19 | 2013-10-29 | Pratt & Whitney Canada Corp | High pressure turbine vane cooling hole distrubution |
US8944141B2 (en) * | 2010-12-22 | 2015-02-03 | United Technologies Corporation | Drill to flow mini core |
US8733694B2 (en) * | 2011-01-06 | 2014-05-27 | Jay M. Francisco | Arrangement for maintaining flow to an air inlet of an auxiliary power unit assembly |
US8944750B2 (en) | 2011-12-22 | 2015-02-03 | Pratt & Whitney Canada Corp. | High pressure turbine vane cooling hole distribution |
US9328617B2 (en) | 2012-03-20 | 2016-05-03 | United Technologies Corporation | Trailing edge or tip flag antiflow separation |
US9650900B2 (en) | 2012-05-07 | 2017-05-16 | Honeywell International Inc. | Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations |
CA2875028A1 (en) | 2012-06-13 | 2013-12-19 | General Electric Company | Gas turbine engine wall |
US9267381B2 (en) | 2012-09-28 | 2016-02-23 | Honeywell International Inc. | Cooled turbine airfoil structures |
US9062556B2 (en) | 2012-09-28 | 2015-06-23 | Pratt & Whitney Canada Corp. | High pressure turbine blade cooling hole distribution |
US9121289B2 (en) | 2012-09-28 | 2015-09-01 | Pratt & Whitney Canada Corp. | High pressure turbine blade cooling hole distribution |
US10113433B2 (en) | 2012-10-04 | 2018-10-30 | Honeywell International Inc. | Gas turbine engine components with lateral and forward sweep film cooling holes |
US9482101B2 (en) | 2012-11-28 | 2016-11-01 | United Technologies Corporation | Trailing edge and tip cooling |
US10125614B2 (en) | 2014-04-17 | 2018-11-13 | United Technologies Corporation | Cooling hole arrangement for engine component |
US9581029B2 (en) | 2014-09-24 | 2017-02-28 | Pratt & Whitney Canada Corp. | High pressure turbine blade cooling hole distribution |
GB201417587D0 (en) | 2014-10-06 | 2014-11-19 | Rolls Royce Plc | A cooked component |
US20160298462A1 (en) * | 2015-04-09 | 2016-10-13 | United Technologies Corporation | Cooling passages for a gas turbine engine component |
US10107108B2 (en) * | 2015-04-29 | 2018-10-23 | General Electric Company | Rotor blade having a flared tip |
GB201508795D0 (en) * | 2015-05-22 | 2015-07-01 | Rolls Royce Plc | Cooling of turbine blades |
US10047613B2 (en) | 2015-08-31 | 2018-08-14 | General Electric Company | Gas turbine components having non-uniformly applied coating and methods of assembling the same |
US11021965B2 (en) | 2016-05-19 | 2021-06-01 | Honeywell International Inc. | Engine components with cooling holes having tailored metering and diffuser portions |
US20180058224A1 (en) * | 2016-08-23 | 2018-03-01 | United Technologies Corporation | Gas turbine blade with tip cooling |
US11021963B2 (en) * | 2019-05-03 | 2021-06-01 | Raytheon Technologies Corporation | Monolithic body including an internal passage with a generally teardrop shaped cross-sectional geometry |
US11840940B2 (en) * | 2021-03-09 | 2023-12-12 | Mechanical Dynamics And Analysis Llc | Turbine blade tip cooling hole supply plenum |
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JP2003232204A (ja) * | 2002-01-11 | 2003-08-22 | General Electric Co <Ge> | クロスオーバ冷却式の翼形部後縁 |
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2003
- 2003-09-17 US US10/664,649 patent/US7008186B2/en not_active Expired - Lifetime
-
2004
- 2004-09-09 CA CA002480989A patent/CA2480989C/en not_active Expired - Fee Related
- 2004-09-16 EP EP04255629.0A patent/EP1517003B1/en not_active Expired - Fee Related
- 2004-09-16 JP JP2004269423A patent/JP4594685B2/ja not_active Expired - Fee Related
Patent Citations (5)
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JPH1054203A (ja) * | 1996-05-28 | 1998-02-24 | Toshiba Corp | 構造要素 |
JP2000230402A (ja) * | 1999-02-08 | 2000-08-22 | Toshiba Corp | 温度制御構造を有する流体機器、同機器を適用したガスタービン、ガスタービン用燃焼器および冷凍サイクル装置 |
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JP2002364303A (ja) * | 2001-05-17 | 2002-12-18 | General Electric Co <Ge> | ガスタービンエンジンのブレード、システム及びブレードの変更方法 |
JP2003232204A (ja) * | 2002-01-11 | 2003-08-22 | General Electric Co <Ge> | クロスオーバ冷却式の翼形部後縁 |
Also Published As
Publication number | Publication date |
---|---|
CA2480989C (en) | 2009-10-20 |
EP1517003A3 (en) | 2012-07-11 |
US7008186B2 (en) | 2006-03-07 |
EP1517003A2 (en) | 2005-03-23 |
EP1517003B1 (en) | 2016-03-16 |
JP2005090511A (ja) | 2005-04-07 |
US20050232768A1 (en) | 2005-10-20 |
CA2480989A1 (en) | 2005-03-17 |
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