JP2005127314A - 収束ピン冷却式翼形部 - Google Patents
収束ピン冷却式翼形部 Download PDFInfo
- Publication number
- JP2005127314A JP2005127314A JP2004241764A JP2004241764A JP2005127314A JP 2005127314 A JP2005127314 A JP 2005127314A JP 2004241764 A JP2004241764 A JP 2004241764A JP 2004241764 A JP2004241764 A JP 2004241764A JP 2005127314 A JP2005127314 A JP 2005127314A
- Authority
- JP
- Japan
- Prior art keywords
- circuit
- airfoil
- pins
- side wall
- cooling
- 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.)
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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
- F01D5/187—Convection 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
-
- 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
【解決手段】 タービン翼形部(12)は、前縁(22)及び後縁(24)間で翼弦方向にかつ根元(26)及び先端(28)間でスパンにわたって延びる正圧及び負圧側壁(18、20)を含む。隔壁(30)が、側壁間に間隔を置いて配置されて、該隔壁の両側に前縁及び後縁間で収束する2つの冷却回路(32、34)を画成する。ピンの配列(44、46)が、回路の吐出端において正圧側壁(18)から内向きに延びており、またピンは、収束する回路に適合するように長さが減少している。
【選択図】 図1
Description
12 翼形部
14 ダブテール
16 プラットフォーム
18 正圧側壁
20 負圧側壁
22 前縁
24 後縁
26 根元
28 先端
30 隔壁
32 第1の冷却回路
34 第2の冷却回路
36 第3の冷却回路
38 冷却空気
40 燃焼ガス
42 フィルム冷却孔
44 第1のピンの配列
46 第2のピンの配列
48 出口スロット
50 出口開口
52 ブリッジ
Claims (10)
- 翼弦方向に対向する前縁(22)及び後縁(24)において互いに結合されかつ根元(26)から先端(28)までスパンにわたって延びる横方向に間隔を置いて配置された正圧及び負圧側壁(18、20)と、
前記正圧及び負圧側壁(18、20)間に間隔を置いて配置された隔壁(30)であって、該隔壁(30)の両側に沿ってスパンにわたって延びかつ前記前縁及び後縁間で収束する第1及び第2の冷却回路(32、34)を前記側壁と共に画成する隔壁(30)と、を含み、
前記第1の回路が前記正圧側壁(18)に沿って配置され、また前記第2の回路が前記負圧側壁(20)に沿って配置されかつ前記第1の回路から後方に前記後縁(24)まで延び、
ピンの配列(44、46)が、前記第1及び第2の回路の1つの吐出端において前記正圧側壁(18)から内向きに延び、前記ピンは、前記前縁及び後縁間で収束する前記1つの回路に適合するように長さが減少している、
タービン翼形部。 - 前記第1の回路が、前記正圧側壁に沿ってスパン方向に延びる細長い第1の出口スロット(48)を含み、前記第2の回路が、前記後縁(24)に近接して終端する第2の出口開口(50)の列を含む、請求項1記載の翼形部。
- 前記ピンの配列(44)が、前記第1の回路(32)の第1の出口スロット(48)の上流で該第1の回路内に配置されて、該スロットに沿って連続フィルムの状態で冷却空気(38)を吐出するようになっている、請求項2記載の翼形部。
- 前記第2の回路(34)が、前記ピン配列(44)の位置において前記負圧側壁(20)を前記隔壁(30)に一体的に結合するブリッジ(52)を含む、請求項3記載の翼形部。
- 前記第2の回路(34)の第2の出口開口(50)の上流で該第2の回路内に配置された第2の前記ピンの配列(46)をさらに含む、請求項4記載の翼形部。
- 前記第2のピン配列(46)が、前記第1のピン配列(44)の下流に配置され、前記正圧及び負圧側壁(18、20)を互いに一体的に結合している、請求項5記載の翼形部。
- 前記第1の回路(32)が、前記第1のピンの配列(44)に向かって収束する共通入口を形成するようにスパンにわたって延びる単一のチャネルを含み、
前記第2の回路(32)が、前記第2の出口開口(50)を通して冷却空気を吐出する蛇行回路を画成するように前記負圧側壁(20)を前記隔壁に一体的に結合する複数のブリッジ(52)を含む、
請求項6記載の翼形部。 - 前記ピン(44、46)が、前記正圧側壁(18)に沿ってスパン方向にかつ翼弦方向に間隔を置いて配置されて該ピンの後ろに遠回りの流路を形成するようになっている、請求項6に記載の翼形部。
- 前記ピン(44、46)が、均一な間隔及び均一な形状を有する、請求項6記載の翼形部。
- 前記隔壁(30)が、前記前縁(22)の後方で前記負圧側壁(20)と一体形で始まり、前記後縁(24)の前方で前記正圧側壁(18)と一体形で終端している、請求項6記載の翼形部。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/692,700 US6981840B2 (en) | 2003-10-24 | 2003-10-24 | Converging pin cooled airfoil |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2005127314A true JP2005127314A (ja) | 2005-05-19 |
JP4576177B2 JP4576177B2 (ja) | 2010-11-04 |
Family
ID=34394576
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2004241764A Expired - Fee Related JP4576177B2 (ja) | 2003-10-24 | 2004-08-23 | 収束ピン冷却式翼形部 |
Country Status (4)
Country | Link |
---|---|
US (1) | US6981840B2 (ja) |
EP (1) | EP1526250A2 (ja) |
JP (1) | JP4576177B2 (ja) |
CA (1) | CA2477402C (ja) |
Cited By (4)
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JP2017115874A (ja) * | 2015-12-22 | 2017-06-29 | ゼネラル・エレクトリック・カンパニイ | 後縁冷却回路を備えたタービンエーロフォイル |
JP2018112182A (ja) * | 2016-10-26 | 2018-07-19 | ゼネラル・エレクトリック・カンパニイ | 後縁冷却回路を備えたターボ機械ブレード |
JP2020513091A (ja) * | 2017-04-10 | 2020-04-30 | サフラン | 改良された冷却回路を備えるブレード |
US11814965B2 (en) | 2021-11-10 | 2023-11-14 | General Electric Company | Turbomachine blade trailing edge cooling circuit with turn passage having set of obstructions |
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FR2893974B1 (fr) * | 2005-11-28 | 2011-03-18 | Snecma | Circuit de refroidissement central pour aube mobile de turbomachine |
US20100247328A1 (en) * | 2006-06-06 | 2010-09-30 | United Technologies Corporation | Microcircuit cooling for blades |
US20080031739A1 (en) * | 2006-08-01 | 2008-02-07 | United Technologies Corporation | Airfoil with customized convective cooling |
US7544044B1 (en) | 2006-08-11 | 2009-06-09 | Florida Turbine Technologies, Inc. | Turbine airfoil with pedestal and turbulators cooling |
US7549844B2 (en) * | 2006-08-24 | 2009-06-23 | Siemens Energy, Inc. | Turbine airfoil cooling system with bifurcated and recessed trailing edge exhaust channels |
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US7819629B2 (en) * | 2007-02-15 | 2010-10-26 | Siemens Energy, Inc. | Blade for a gas turbine |
US7762775B1 (en) | 2007-05-31 | 2010-07-27 | Florida Turbine Technologies, Inc. | Turbine airfoil with cooled thin trailing edge |
US7955053B1 (en) | 2007-09-21 | 2011-06-07 | Florida Turbine Technologies, Inc. | Turbine blade with serpentine cooling circuit |
US8292581B2 (en) * | 2008-01-09 | 2012-10-23 | Honeywell International Inc. | Air cooled turbine blades and methods of manufacturing |
US8167558B2 (en) | 2009-01-19 | 2012-05-01 | Siemens Energy, Inc. | Modular serpentine cooling systems for turbine engine components |
US8079813B2 (en) * | 2009-01-19 | 2011-12-20 | Siemens Energy, Inc. | Turbine blade with multiple trailing edge cooling slots |
US8061990B1 (en) * | 2009-03-13 | 2011-11-22 | Florida Turbine Technologies, Inc. | Turbine rotor blade with low cooling flow |
JP5709879B2 (ja) * | 2009-10-20 | 2015-04-30 | シーメンス エナジー インコーポレイテッド | ガスタービンエンジン |
US8894363B2 (en) | 2011-02-09 | 2014-11-25 | Siemens Energy, Inc. | Cooling module design and method for cooling components of a gas turbine system |
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US8714926B2 (en) | 2010-09-17 | 2014-05-06 | Siemens Energy, Inc. | Turbine component cooling channel mesh with intersection chambers |
US8961133B2 (en) | 2010-12-28 | 2015-02-24 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine and cooled airfoil |
US9017027B2 (en) | 2011-01-06 | 2015-04-28 | Siemens Energy, Inc. | Component having cooling channel with hourglass cross section |
US8764394B2 (en) | 2011-01-06 | 2014-07-01 | Siemens Energy, Inc. | Component cooling channel |
US20130052036A1 (en) * | 2011-08-30 | 2013-02-28 | General Electric Company | Pin-fin array |
US9249675B2 (en) | 2011-08-30 | 2016-02-02 | General Electric Company | Pin-fin array |
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US9970319B2 (en) | 2014-05-05 | 2018-05-15 | United Technologies Corporation | Reducing variation in cooling hole meter length |
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US10352181B2 (en) | 2014-11-26 | 2019-07-16 | Ansaldo Energia Ip Uk Limited | Leading edge cooling channel for airfoil |
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-
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- 2004-08-19 EP EP04255001A patent/EP1526250A2/en not_active Withdrawn
- 2004-08-23 JP JP2004241764A patent/JP4576177B2/ja not_active Expired - Fee Related
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Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2017115874A (ja) * | 2015-12-22 | 2017-06-29 | ゼネラル・エレクトリック・カンパニイ | 後縁冷却回路を備えたタービンエーロフォイル |
JP2018112182A (ja) * | 2016-10-26 | 2018-07-19 | ゼネラル・エレクトリック・カンパニイ | 後縁冷却回路を備えたターボ機械ブレード |
JP7175599B2 (ja) | 2016-10-26 | 2022-11-21 | ゼネラル・エレクトリック・カンパニイ | 後縁冷却回路を備えたターボ機械ブレード |
JP2020513091A (ja) * | 2017-04-10 | 2020-04-30 | サフラン | 改良された冷却回路を備えるブレード |
JP7130664B2 (ja) | 2017-04-10 | 2022-09-05 | サフラン | 改良された冷却回路を備えるブレード |
US11814965B2 (en) | 2021-11-10 | 2023-11-14 | General Electric Company | Turbomachine blade trailing edge cooling circuit with turn passage having set of obstructions |
Also Published As
Publication number | Publication date |
---|---|
JP4576177B2 (ja) | 2010-11-04 |
CA2477402A1 (en) | 2005-04-24 |
US6981840B2 (en) | 2006-01-03 |
US20050169752A1 (en) | 2005-08-04 |
CA2477402C (en) | 2009-07-14 |
EP1526250A2 (en) | 2005-04-27 |
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