JP4856417B2 - タービン壁 - Google Patents
タービン壁 Download PDFInfo
- Publication number
- JP4856417B2 JP4856417B2 JP2005320293A JP2005320293A JP4856417B2 JP 4856417 B2 JP4856417 B2 JP 4856417B2 JP 2005320293 A JP2005320293 A JP 2005320293A JP 2005320293 A JP2005320293 A JP 2005320293A JP 4856417 B2 JP4856417 B2 JP 4856417B2
- Authority
- JP
- Japan
- Prior art keywords
- holes
- hole
- film cooling
- outlet
- turbine
- 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
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
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
- 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
-
- 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 プラットフォーム
16 ダブテール
18 側壁
20 前縁
22 後縁
26 燃焼ガス
28 冷却空気
30 フィルム冷却孔
32 後縁冷却孔
34、36 多形フィルム冷却孔
50 ベーン
52 ライナ
54 シュラウド
Claims (8)
- タービン壁(18)であって、
タービンの半径方向スパンに沿って延びる列の形態で配置された複数の円筒形の第1のフィルム冷却孔(34)と、
前記第1の孔(34)の列と一直線上に配置され且つ該第1の孔(34)と交互に配置された、該第1の孔(34)とは異なる形状を有する複数の発散拡散形の第2のフィルム冷却孔(36)と、
を含み、
前記第1の孔(34)の第1の出口(44)が、前記第2の孔(36)の第2の出口(48)から上流又は下流方向にその一部がオフセットすることを特徴とする、タービン壁(18)。 - 前記第1及び第2の孔(34、36)が、該壁(18)の対向する内側及び外側面(38、40)間で該壁を傾斜して貫通しており、前記内側面(38)上に対応する第1及び第2の入口(42、46)を有し、前記第1及び第2の出口(44、48)は、前記外側面(40)上に配置されていることを特徴とする請求項1記載のタービン壁。
- 前記第2の入口(46)が円筒形であり、また前記第2の出口(48)が、それから後方に発散することを特徴とする請求項2記載のタービン壁。
- 前記第1及び第2の孔(34、36)が、前記タービンの軸方向及び半径方向の両方向に対して傾斜して該壁を貫通することを特徴とする請求項3記載のタービン壁。
- 前記第2の出口(48)が、前記外側面(40)に対して異なる傾斜角度を形成する複数の非対称な流路壁を有することを特徴とする請求項4記載のタービン壁。
- 前記第1及び第2の孔(34、36)が、一対一で交互になっていることを特徴とする請求項3記載のタービン壁。
- 前記第1及び第2の孔(34、36)が、それぞれ一対二で交互になっていることを特徴とする請求項3記載のタービン壁。
- 前記第1及び第2の孔(34、36)が、それぞれ二対一で交互になっていることを特徴とする請求項3記載のタービン壁。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/991,805 | 2004-11-18 | ||
US10/991,805 US7186085B2 (en) | 2004-11-18 | 2004-11-18 | Multiform film cooling holes |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2006144785A JP2006144785A (ja) | 2006-06-08 |
JP4856417B2 true JP4856417B2 (ja) | 2012-01-18 |
Family
ID=35999588
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005320293A Expired - Fee Related JP4856417B2 (ja) | 2004-11-18 | 2005-11-04 | タービン壁 |
Country Status (5)
Country | Link |
---|---|
US (1) | US7186085B2 (ja) |
EP (1) | EP1662091B1 (ja) |
JP (1) | JP4856417B2 (ja) |
CA (1) | CA2526717C (ja) |
DE (1) | DE602005006362T2 (ja) |
Families Citing this family (80)
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US7220934B2 (en) * | 2005-06-07 | 2007-05-22 | United Technologies Corporation | Method of producing cooling holes in highly contoured airfoils |
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US8057182B2 (en) * | 2008-11-21 | 2011-11-15 | General Electric Company | Metered cooling slots for turbine blades |
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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 |
US8371814B2 (en) * | 2009-06-24 | 2013-02-12 | Honeywell International Inc. | Turbine engine components |
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US8529193B2 (en) * | 2009-11-25 | 2013-09-10 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
US20110150665A1 (en) * | 2009-12-22 | 2011-06-23 | Nissan Technical Center North America, Inc. | Fan assembly |
CN102667068A (zh) * | 2009-12-30 | 2012-09-12 | 西门子公司 | 用于转换能量的涡轮机及其操作方法 |
US8628293B2 (en) | 2010-06-17 | 2014-01-14 | Honeywell International Inc. | Gas turbine engine components with cooling hole trenches |
US8568085B2 (en) | 2010-07-19 | 2013-10-29 | Pratt & Whitney Canada Corp | High pressure turbine vane cooling hole distrubution |
US8684691B2 (en) | 2011-05-03 | 2014-04-01 | Siemens Energy, Inc. | Turbine blade with chamfered squealer tip and convective cooling holes |
RU2473813C1 (ru) * | 2011-07-29 | 2013-01-27 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Сопловой аппарат турбомашины с конвективно-пленочным охлаждением |
JP5632812B2 (ja) * | 2011-10-03 | 2014-11-26 | 三菱日立パワーシステムズ株式会社 | ガスタービン翼 |
US8944750B2 (en) | 2011-12-22 | 2015-02-03 | Pratt & Whitney Canada Corp. | High pressure turbine vane cooling hole distribution |
US9138804B2 (en) * | 2012-01-11 | 2015-09-22 | United Technologies Corporation | Core for a casting process |
US8584470B2 (en) | 2012-02-15 | 2013-11-19 | United Technologies Corporation | Tri-lobed cooling hole and method of manufacture |
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2004
- 2004-11-18 US US10/991,805 patent/US7186085B2/en not_active Expired - Fee Related
-
2005
- 2005-11-04 JP JP2005320293A patent/JP4856417B2/ja not_active Expired - Fee Related
- 2005-11-10 CA CA2526717A patent/CA2526717C/en not_active Expired - Fee Related
- 2005-11-14 DE DE602005006362T patent/DE602005006362T2/de active Active
- 2005-11-14 EP EP05256999A patent/EP1662091B1/en not_active Not-in-force
Also Published As
Publication number | Publication date |
---|---|
CA2526717C (en) | 2013-01-08 |
DE602005006362T2 (de) | 2009-06-10 |
US20060104807A1 (en) | 2006-05-18 |
CA2526717A1 (en) | 2006-05-18 |
EP1662091A3 (en) | 2006-06-07 |
EP1662091B1 (en) | 2008-04-30 |
US7186085B2 (en) | 2007-03-06 |
JP2006144785A (ja) | 2006-06-08 |
EP1662091A2 (en) | 2006-05-31 |
DE602005006362D1 (de) | 2008-06-12 |
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