JP2006242187A - タービンのエーロフォイル - Google Patents
タービンのエーロフォイル Download PDFInfo
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- JP2006242187A JP2006242187A JP2006052423A JP2006052423A JP2006242187A JP 2006242187 A JP2006242187 A JP 2006242187A JP 2006052423 A JP2006052423 A JP 2006052423A JP 2006052423 A JP2006052423 A JP 2006052423A JP 2006242187 A JP2006242187 A JP 2006242187A
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- JP
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- Prior art keywords
- airfoil
- cooling
- turbine
- turbine airfoil
- downstream
- 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
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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
- F01D5/186—Film cooling
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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
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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
- F05D2200/00—Mathematical features
- F05D2200/20—Special functions
- F05D2200/24—Special functions exponential
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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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
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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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/26—Three-dimensional paraboloid
-
- 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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/29—Three-dimensional machined; miscellaneous
- F05D2250/292—Three-dimensional machined; miscellaneous tapered
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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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- 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】複数の冷却孔(50)が、冷却回路(40)と流体連通するようにエーロフォイル(22)の外部表面に形成され、複数の冷却孔(50)の少なくともいくつかは、冷却回路(40)の下流に絞り部分(58)と、ディフューザ部分(51)とを有する。ディフューザ部分(51)の両側壁(53、54)および頂壁と底壁(55、56)のいずれか一方が、広がりが強化され、付着性が強化され、より乱流になりにくい冷却回路(40)からの冷却膜の流れを、それぞれの冷却孔(50)近傍のエーロフォイル(22)の下流表面に実現するための、ベル形の構造を有する。
【選択図】図4
Description
22 エーロフォイル
24 ダブテール
26 前縁部
28 後縁部
30 翼根部
32 翼端
34 正圧側の壁
36 負圧側の壁
40 冷却回路
50 冷却孔
51 ディフューザ部分
52 出口開口
53 側壁
54 側壁
55 頂壁
56 底壁
58 絞り部分
60 ツール
61 絞り部分
62 ディフューザ部分
64 湾曲した壁
65 湾曲した壁
70 冷却孔
71 ディフューザ部分
72 絞り部分
80 冷却孔
81 ディフューザ部分
82 絞り部分
Claims (10)
- 湾曲を画定する外部表面を有するタービンエーロフォイル(22)であって、このタービンエーロフォイル(22)は、
(a)軸方向に延びる空気力学的外部表面の湾曲を有する前縁部(26)および軸方向に隔置された後縁部(28)と、
(b)翼根部(30)、並びに径方向に延びる翼幅軸に沿って隔置された翼端(32)と、
(c)正圧側の壁(34)、並びに側方に隔置された負圧側の壁(36)と、
(d)前記正圧側の壁(34)と前記負圧側の壁(36)の間に配置された、エーロフォイル(22)を冷却するために流体流(F)を送るための冷却回路(40)と、
(e)前記冷却回路(40)と流体連通するように、前記エーロフォイル(22)の前記外部表面に形成された複数の冷却孔(50)とを有し、
前記複数の冷却孔(50)の少なくともいくつかは、
(i)前記冷却回路(40)の下流位置の絞り部分(58)と、
(ii)前記絞り部分(58)の下流かつ前記エーロフォイル(22)の前記外部表面の上流に設けられたディフューザ部分(51)であって、前記外部表面上に冷却膜を出すための出口開口(52)を画成する、頂壁(55)と底壁(56)と両側壁(53、54)とを有し、
このタービンエーロフォイル(22)は、さらに、
(f)前記ディフューザ部分(51)の少なくとも、前記両側壁(53、54)と、前記頂壁および底壁(55、56)のいずれか一方は、下流で広がったベル形の構造を有することにより、前記冷却回路(40)からの前記冷却膜の流れが、それぞれの冷却孔(50)近傍の前記エーロフォイル(22)の下流表面において、広がりを強化され、付着性が強化され、より乱流になりにくくされたことを特徴とするタービンエーロフォイル(22)。 - 前記絞り部分(58)が、そこを通る流体流の方向に垂直な一定の断面を有することを特徴とする請求項1記載のタービンエーロフォイル(22)。
- 前記絞り部分(58)が、そこを通る流体流の方向に垂直な、円形、楕円形および矩形からなるグループから選択された、一定の断面を有することを特徴とする請求項1記載のタービンエーロフォイル(22)。
- 前記冷却孔(50)が、前記エーロフォイル(22)の前記負圧側の壁(36)に形成されることを特徴とする請求項1記載のタービンエーロフォイル(22)。
- 前記ディフューザ部分(51)の前記出口開口(52)が、径方向に延びる縦の高さ寸法と、横方向に延びる幅寸法を規定することを特徴とする請求項1記載のタービンエーロフォイル(22)。
- 前記底壁(56)が、前記ディフューザ部分(51)の前記出口開口(52)の下流に、ベル形の湾曲を有することを特徴とする請求項1記載のタービンエーロフォイル(22)。
- 前記ベル形のディフューザ底壁(56)が、前記絞り部分(58)の円筒形の壁に比べて、0〜30度の角度に方向付けられたことを特徴とする請求項6記載のタービンエーロフォイル(22)。
- 前記冷却孔(50)よる前記前縁部(26)の表面積被覆率が、約35パーセントであることを特徴とする請求項1記載のタービンエーロフォイル(22)。
- 各出口開口(52)の前記面積が、約0.12mm2〜約0.65mm2であることを特徴とする請求項1記載のタービンエーロフォイル(22)。
- 前記出口開口(52)の前記面積が、約0.45mm2であることを特徴とする請求項1記載のタービンエーロフォイル(22)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/069,869 | 2005-03-01 | ||
US11/069,869 US7374401B2 (en) | 2005-03-01 | 2005-03-01 | Bell-shaped fan cooling holes for turbine airfoil |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2006242187A true JP2006242187A (ja) | 2006-09-14 |
JP4794317B2 JP4794317B2 (ja) | 2011-10-19 |
Family
ID=36102192
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2006052423A Expired - Fee Related JP4794317B2 (ja) | 2005-03-01 | 2006-02-28 | タービンのエーロフォイル |
Country Status (4)
Country | Link |
---|---|
US (1) | US7374401B2 (ja) |
EP (1) | EP1698757B1 (ja) |
JP (1) | JP4794317B2 (ja) |
CA (1) | CA2536859C (ja) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2009162224A (ja) * | 2007-12-28 | 2009-07-23 | General Electric Co <Ge> | 冷却孔を形成する方法及びハイブリッド形成冷却孔を有するタービン翼形部 |
JP2012072767A (ja) * | 2010-09-29 | 2012-04-12 | General Electric Co <Ge> | タービン翼およびタービン翼を冷却するための方法 |
WO2012137898A1 (ja) * | 2011-04-07 | 2012-10-11 | 株式会社Ihi | タービン翼 |
KR20190036202A (ko) * | 2017-09-27 | 2019-04-04 | 두산중공업 주식회사 | 가스 터빈 블레이드 |
WO2020246289A1 (ja) * | 2019-06-07 | 2020-12-10 | 株式会社Ihi | フィルム冷却構造及びガスタービンエンジン用タービン翼 |
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CN111022127B (zh) * | 2019-11-29 | 2021-12-03 | 大连理工大学 | 一种涡轮叶片尾缘曲线式排气劈缝结构 |
US11746661B2 (en) * | 2021-06-24 | 2023-09-05 | Doosan Enerbility Co., Ltd. | Turbine blade and turbine including the same |
WO2023211485A2 (en) * | 2021-10-22 | 2023-11-02 | Raytheon Technologies Corporation | Gas turbine engine article with cooling holes for mitigating recession |
CN114985852A (zh) * | 2022-06-30 | 2022-09-02 | 贵州安吉华元科技发展有限公司 | 一种航空发动机叶片异形气膜孔加工方法 |
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Cited By (10)
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JP2009162224A (ja) * | 2007-12-28 | 2009-07-23 | General Electric Co <Ge> | 冷却孔を形成する方法及びハイブリッド形成冷却孔を有するタービン翼形部 |
JP2012072767A (ja) * | 2010-09-29 | 2012-04-12 | General Electric Co <Ge> | タービン翼およびタービン翼を冷却するための方法 |
WO2012137898A1 (ja) * | 2011-04-07 | 2012-10-11 | 株式会社Ihi | タービン翼 |
JP2012219702A (ja) * | 2011-04-07 | 2012-11-12 | Society Of Japanese Aerospace Co | タービン翼 |
KR20190036202A (ko) * | 2017-09-27 | 2019-04-04 | 두산중공업 주식회사 | 가스 터빈 블레이드 |
KR102000835B1 (ko) * | 2017-09-27 | 2019-07-16 | 두산중공업 주식회사 | 가스 터빈 블레이드 |
WO2020246289A1 (ja) * | 2019-06-07 | 2020-12-10 | 株式会社Ihi | フィルム冷却構造及びガスタービンエンジン用タービン翼 |
JPWO2020246289A1 (ja) * | 2019-06-07 | 2020-12-10 | ||
JP7248112B2 (ja) | 2019-06-07 | 2023-03-29 | 株式会社Ihi | フィルム冷却構造及びガスタービンエンジン用タービン翼 |
US11732591B2 (en) | 2019-06-07 | 2023-08-22 | Ihi Corporation | Film cooling structure and turbine blade for gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
JP4794317B2 (ja) | 2011-10-19 |
CA2536859C (en) | 2014-09-16 |
EP1698757A2 (en) | 2006-09-06 |
US7374401B2 (en) | 2008-05-20 |
EP1698757A3 (en) | 2011-10-19 |
EP1698757B1 (en) | 2015-10-14 |
US20080031738A1 (en) | 2008-02-07 |
CA2536859A1 (en) | 2006-09-01 |
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