JP5723134B2 - トレンチの長さに沿った方向を向いた孔を有する浅いトレンチを使用した膜冷却を改良するための構造及び方法 - Google Patents
トレンチの長さに沿った方向を向いた孔を有する浅いトレンチを使用した膜冷却を改良するための構造及び方法 Download PDFInfo
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- JP5723134B2 JP5723134B2 JP2010234132A JP2010234132A JP5723134B2 JP 5723134 B2 JP5723134 B2 JP 5723134B2 JP 2010234132 A JP2010234132 A JP 2010234132A JP 2010234132 A JP2010234132 A JP 2010234132A JP 5723134 B2 JP5723134 B2 JP 5723134B2
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- JP
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- Prior art keywords
- trench
- width
- membrane
- aerodynamic component
- airfoil
- 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.)
- Active
Links
- 238000001816 cooling Methods 0.000 title description 78
- 238000000034 method Methods 0.000 title description 9
- 239000012528 membrane Substances 0.000 claims description 46
- 239000000758 substrate Substances 0.000 claims description 13
- 239000012790 adhesive layer Substances 0.000 claims description 10
- 239000012720 thermal barrier coating Substances 0.000 claims description 9
- 239000000463 material Substances 0.000 claims description 7
- 239000002826 coolant Substances 0.000 description 20
- 239000007789 gas Substances 0.000 description 11
- 230000000694 effects Effects 0.000 description 10
- 239000012530 fluid Substances 0.000 description 6
- 239000010410 layer Substances 0.000 description 5
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000000903 blocking effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000002156 mixing Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 238000003491 array Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 238000003892 spreading Methods 0.000 description 1
Images
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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
所望の位置で長さ方向を有する少なくとも1つの浅いトレンチを有するタービンエーロフォイルを構成するステップと、
それぞれのトレンチ内に複数の膜冷却孔を形成するステップであって、各膜冷却孔が、実質的に対応するトレンチの長さ方向を向いた中心軸を有し、その結果、これらの複数の膜冷却孔から流出した膜ジェットが、対応するトレンチの長さ方向に対して実質的に平行に、対応するトレンチ内へ流入する、ステップと
を含む。
12 膜冷却孔
14 浅いトレンチ
16 浅いトレンチの側壁
18 膜冷却孔12の中心軸
30 熱ガス
32 膜冷却材流
40 エーロフォイル部品
42 膜冷却孔
44 膜冷却孔42の中心軸
46 浅いトレンチ14の長さ方向
50 シャワーヘッド膜冷却領域
60 基材
62 基材60の熱い表面
64 基材60のより冷たい表面
70 基材60の接着層
72 基材60の遮熱コーティング
73 コーティングされた表面
76 膜冷却孔42の平均のど直径
80 トレンチ14の底面
Claims (10)
- 少なくとも1つのトレンチを備えるタービンエーロフォイルであって、
各トレンチが、複数の膜孔を含み、
前記複数の膜孔が、各トレンチ内に配置され、対応するトレンチの長さ方向に沿って位置し、実質的に対応するトレンチの長さ方向で、ある角度をなして、対応するエーロフォイル基材を貫通し、
前記トレンチの深さが、対応する膜孔の平均のど直径よりも小さく、
前記タービンエーロフォイルはさらに、
前記対応するエーロフォイル基材の表面に接着された接着層と、
前記接着層の反対面に付着させた、上を覆う遮熱コーティングと、
を備え、
前記トレンチが、前記接着層及び前記上を覆う遮熱コーティングを貫通し、さらに、各膜孔が、前記エーロフォイル基材を貫通する、
タービンエーロフォイル。 - それぞれの膜孔の中心軸とその対応するトレンチの底面との間の角度が、約15度から約50度である、請求項1に記載のタービンエーロフォイル。
- 各トレンチが、トレンチの幅を画定する方向と同じ方向に測定した対応する膜孔の最大出口幅に実質的に等しい幅を含む、請求項1または2に記載のタービンエーロフォイル。
- 各トレンチが、対応する膜孔の最大出口フットプリント幅の約1.0から約1.5倍の幅を含む、請求項1から3のいずれかに記載のタービンエーロフォイル。
- 各トレンチが実質的に長方形であり、前記トレンチの底面に対して約70度から約90度の角度を有する側壁を備える、請求項1から4のいずれかに記載のタービンエーロフォイル。
- 長さ及び幅を有する少なくとも1つのトレンチを備える膜冷却式の空力構成部品であって、
各トレンチが、前記トレンチの長さ方向に沿って中に配置された複数の膜孔を備え、
各膜孔が、実質的に対応するトレンチの長さ方向で、ある角度をなして、前記空力構成部品を貫通し、
前記トレンチの深さが、対応する膜孔の平均のど直径よりも小さく、
前記空力構成部品はさらに、
空力構成部品基材と、
前記空力構成部品基材の表面に接着された接着層と、
前記接着層の反対面に付着させた、上を覆う遮熱コーティングと、
をさらに備え、
前記トレンチが、前記接着層及び前記上を覆う遮熱コーティングを貫通し、さらに、各膜孔が、前記空力構成部品基材を貫通した、
膜冷却式空力構成部品。 - 前記トレンチがさらに、前記空力構成部品基材に部分的に陥入した、請求項6に記載の膜冷却式空力構成部品。
- 各トレンチが、トレンチの幅を画定する方向と同じ方向に測定した対応する膜孔の最大出口幅に実質的に等しい幅を含む、請求項6または7に記載の膜冷却式空力構成部品。
- 各トレンチが、対応する膜孔の最大出口フットプリント幅の約1.0から約1.5倍の幅を含む、請求項6から8のいずれかに記載の膜冷却式空力構成部品。
- 各トレンチが実質的に長方形であり、前記トレンチの底面に対して約70度から約90度の角度を有する側壁を備える、請求項6から9のいずれかに記載の膜冷却式空力構成部品。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/604,460 | 2009-10-23 | ||
US12/604,460 US20110097188A1 (en) | 2009-10-23 | 2009-10-23 | Structure and method for improving film cooling using shallow trench with holes oriented along length of trench |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2011089519A JP2011089519A (ja) | 2011-05-06 |
JP5723134B2 true JP5723134B2 (ja) | 2015-05-27 |
Family
ID=43796944
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2010234132A Active JP5723134B2 (ja) | 2009-10-23 | 2010-10-19 | トレンチの長さに沿った方向を向いた孔を有する浅いトレンチを使用した膜冷却を改良するための構造及び方法 |
Country Status (5)
Country | Link |
---|---|
US (1) | US20110097188A1 (ja) |
JP (1) | JP5723134B2 (ja) |
CN (1) | CN102042042B (ja) |
CH (1) | CH702110B1 (ja) |
DE (1) | DE102010038131A1 (ja) |
Families Citing this family (32)
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US20090246011A1 (en) * | 2008-03-25 | 2009-10-01 | General Electric Company | Film cooling of turbine components |
US8371814B2 (en) * | 2009-06-24 | 2013-02-12 | Honeywell International Inc. | Turbine engine components |
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 |
US9028207B2 (en) * | 2010-09-23 | 2015-05-12 | Siemens Energy, Inc. | Cooled component wall in a turbine engine |
US8777571B1 (en) * | 2011-12-10 | 2014-07-15 | Florida Turbine Technologies, Inc. | Turbine airfoil with curved diffusion film cooling slot |
US8870535B2 (en) * | 2012-01-13 | 2014-10-28 | General Electric Company | Airfoil |
US8870536B2 (en) * | 2012-01-13 | 2014-10-28 | General Electric Company | Airfoil |
US9429027B2 (en) * | 2012-04-05 | 2016-08-30 | United Technologies Corporation | Turbine airfoil tip shelf and squealer pocket cooling |
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 |
US9080451B2 (en) * | 2012-06-28 | 2015-07-14 | General Electric Company | Airfoil |
US9273561B2 (en) | 2012-08-03 | 2016-03-01 | General Electric Company | Cooling structures for turbine rotor blade tips |
DE102013109116A1 (de) * | 2012-08-27 | 2014-03-27 | General Electric Company (N.D.Ges.D. Staates New York) | Bauteil mit Kühlkanälen und Verfahren zur Herstellung |
US10113433B2 (en) | 2012-10-04 | 2018-10-30 | Honeywell International Inc. | Gas turbine engine components with lateral and forward sweep film cooling holes |
US9617859B2 (en) | 2012-10-05 | 2017-04-11 | General Electric Company | Turbine components with passive cooling pathways |
US20150202683A1 (en) * | 2012-10-12 | 2015-07-23 | General Electric Company | Method of making surface cooling channels on a component using lithographic molding techniques |
US10655473B2 (en) | 2012-12-13 | 2020-05-19 | United Technologies Corporation | Gas turbine engine turbine blade leading edge tip trench cooling |
US9719357B2 (en) | 2013-03-13 | 2017-08-01 | Rolls-Royce Corporation | Trenched cooling hole arrangement for a ceramic matrix composite vane |
CA2916025A1 (en) * | 2013-07-03 | 2015-04-02 | General Electric Company | Trench cooling of airfoil structures |
CN103452595A (zh) * | 2013-09-25 | 2013-12-18 | 青岛科技大学 | 一种提高冷却效率的新型气膜孔 |
US9441488B1 (en) | 2013-11-07 | 2016-09-13 | United States Of America As Represented By The Secretary Of The Air Force | Film cooling holes for gas turbine airfoils |
US9784123B2 (en) | 2014-01-10 | 2017-10-10 | Genearl Electric Company | Turbine components with bi-material adaptive cooling pathways |
EP2998512A1 (en) * | 2014-09-17 | 2016-03-23 | United Technologies Corporation | Film cooled components and corresponding operating method |
US11021965B2 (en) | 2016-05-19 | 2021-06-01 | Honeywell International Inc. | Engine components with cooling holes having tailored metering and diffuser portions |
KR101853550B1 (ko) * | 2016-08-22 | 2018-04-30 | 두산중공업 주식회사 | 가스 터빈 블레이드 |
US10760430B2 (en) | 2017-05-31 | 2020-09-01 | General Electric Company | Adaptively opening backup cooling pathway |
US11041389B2 (en) | 2017-05-31 | 2021-06-22 | General Electric Company | Adaptive cover for cooling pathway by additive manufacture |
US10704399B2 (en) | 2017-05-31 | 2020-07-07 | General Electric Company | Adaptively opening cooling pathway |
US10927680B2 (en) | 2017-05-31 | 2021-02-23 | General Electric Company | Adaptive cover for cooling pathway by additive manufacture |
US10570747B2 (en) * | 2017-10-02 | 2020-02-25 | DOOSAN Heavy Industries Construction Co., LTD | Enhanced film cooling system |
US10731474B2 (en) * | 2018-03-02 | 2020-08-04 | Raytheon Technologies Corporation | Airfoil with varying wall thickness |
CN108843404B (zh) | 2018-08-10 | 2023-02-24 | 中国科学院宁波材料技术与工程研究所 | 一种具有复合异型槽气膜冷却结构的涡轮叶片及其制备方法 |
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US7553534B2 (en) * | 2006-08-29 | 2009-06-30 | General Electric Company | Film cooled slotted wall and method of making the same |
US20090246011A1 (en) * | 2008-03-25 | 2009-10-01 | General Electric Company | Film cooling of turbine components |
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-
2009
- 2009-10-23 US US12/604,460 patent/US20110097188A1/en not_active Abandoned
-
2010
- 2010-10-12 DE DE102010038131A patent/DE102010038131A1/de not_active Ceased
- 2010-10-19 JP JP2010234132A patent/JP5723134B2/ja active Active
- 2010-10-19 CH CH01707/10A patent/CH702110B1/de not_active IP Right Cessation
- 2010-10-22 CN CN201010533889.1A patent/CN102042042B/zh active Active
Also Published As
Publication number | Publication date |
---|---|
CN102042042B (zh) | 2015-08-12 |
DE102010038131A1 (de) | 2011-04-28 |
CN102042042A (zh) | 2011-05-04 |
JP2011089519A (ja) | 2011-05-06 |
US20110097188A1 (en) | 2011-04-28 |
CH702110B1 (de) | 2015-11-13 |
CH702110A2 (de) | 2011-04-29 |
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