JP4800742B2 - ガスタービンエンジン部品 - Google Patents
ガスタービンエンジン部品 Download PDFInfo
- Publication number
- JP4800742B2 JP4800742B2 JP2005310643A JP2005310643A JP4800742B2 JP 4800742 B2 JP4800742 B2 JP 4800742B2 JP 2005310643 A JP2005310643 A JP 2005310643A JP 2005310643 A JP2005310643 A JP 2005310643A JP 4800742 B2 JP4800742 B2 JP 4800742B2
- Authority
- JP
- Japan
- Prior art keywords
- pores
- wall
- diameter
- tbc
- gas 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
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- 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
- F01D5/182—Transpiration cooling
- F01D5/183—Blade walls being porous
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- 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
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
50、100 支持壁
52、102 支持壁の外面
54、104 支持壁の内面
56、106 細孔
74、130 熱障壁被膜(TBC)
58、108 境膜冷却孔
110 細孔の排出側
112 細孔の入口側
114 境膜冷却孔の排出側
116 境膜冷却孔の入口側
120 境膜冷却孔の排出側の直径
122 境膜冷却孔の入口側の直径
126 細孔の排出側の直径
128 細孔の入口側の直径
Claims (8)
- ガスタービンエンジン部品(40)であって、
第1の表面(102)および反対側の第2の表面(104)を備える支持壁(100)と、
前記壁を通して延びる複数の細孔(106)と、
前記壁の第1の表面を覆って広がり、前記第1の表面で前記細孔を封止する熱障壁被膜(TBC)(130)と、
前記壁および前記TBCを通して延びる複数の境膜冷却孔(108)と、
を備え、
前記複数の境膜冷却孔および前記複数の細孔が前記壁および前記TBCを垂直に通して延びており、
前記複数の細孔(106)の各々は、前記第1の表面(102)において第1の直径(128)を有し且つ前記第2の表面(104)において第2の直径(126)を有し、
前記複数の細孔(106)の少なくとも1つは、前記第1の直径が前記第2の直径より小さいことを特徴とする、ガスタービンエンジン部品(40)。 - 前記孔(118)の各々が、前記第1の表面(102)において第3の直径(120)を有し、さらに前記孔(118)の各々が、前記第2の表面(104)において前記第3の直径より大きな第4の直径(122)を有することを特徴とする請求項1記載のガスタービンエンジン部品(40)。
- 前記複数の細孔(106)および前記複数の孔(118)が、前記壁の第2の表面(104)に沿って開いていることを特徴とする請求項1記載のガスタービンエンジン部品(40)。
- 前記複数の細孔(106)の各々が、そこを通して延びる中心線軸を含み、前記複数の孔(118)の各々が、そこを通して延びる中心線軸を含み、前記細孔の中心線軸の各々が前記孔の中心線軸の各々に対して平行であることを特徴とする請求項1記載のガスタービンエンジン部品(40)。
- 複数の平行な列の細孔と孔が前記壁に沿って第1の方向に延び、かつ複数の平行な列の細孔と孔が前記壁に沿って前記第1の方向に対して垂直な第2の方向に延びるように、前記複数の細孔(106)および前記複数の孔(118)が、前記壁(100)全体にわたって一様な格子パターンで間隔を開けて配置されていることを特徴とする請求項1記載のガスタービンエンジン部品(40)。
- 前記孔(118)が、前記壁(100)に沿って前記第1の方向に延びる前記平行な列の各々の中で全てのN番目の細孔(106)に取って代わり、前記孔が前記壁に沿って前記第2の方向に延びる前記平行な列の中で全てのN番目の細孔に取って代わっていることを特徴とする請求項5記載のガスタービンエンジン部品(40)。
- 前記複数の細孔(106)の各々が、約3ミルから6ミルまでの直径を有し、かつ前記孔(118)が約8ミルから20ミルまでの直径を有することを特徴とする請求項1記載のガスタービンエンジン部品(40)。
- 前記複数の細孔(106)および前記複数の孔(118)の少なくとも1つが、切頭円錐形を有することを特徴とする請求項1記載のガスタービンエンジン部品(40)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/984,292 | 2004-11-09 | ||
US10/984,292 US7186091B2 (en) | 2004-11-09 | 2004-11-09 | Methods and apparatus for cooling gas turbine engine components |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2006138624A JP2006138624A (ja) | 2006-06-01 |
JP4800742B2 true JP4800742B2 (ja) | 2011-10-26 |
Family
ID=35759126
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005310643A Expired - Fee Related JP4800742B2 (ja) | 2004-11-09 | 2005-10-26 | ガスタービンエンジン部品 |
Country Status (4)
Country | Link |
---|---|
US (1) | US7186091B2 (ja) |
EP (1) | EP1655454B1 (ja) |
JP (1) | JP4800742B2 (ja) |
CA (1) | CA2525283C (ja) |
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US7614235B2 (en) * | 2005-03-01 | 2009-11-10 | United Technologies Corporation | Combustor cooling hole pattern |
US8087447B2 (en) | 2006-10-30 | 2012-01-03 | United Technologies Corporation | Method for checking wall thickness of hollow core airfoil |
JP5474279B2 (ja) * | 2007-03-06 | 2014-04-16 | 株式会社Ihi | 冷却タービン翼 |
JP2008309051A (ja) * | 2007-06-14 | 2008-12-25 | Ihi Corp | タービンシュラウドの冷却構造 |
US8376706B2 (en) * | 2007-09-28 | 2013-02-19 | General Electric Company | Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method |
US8241001B2 (en) * | 2008-09-04 | 2012-08-14 | Siemens Energy, Inc. | Stationary turbine component with laminated skin |
US8387397B2 (en) * | 2009-01-27 | 2013-03-05 | General Electric Company | Flow conditioner for use in gas turbine component in which combustion occurs |
US8986002B2 (en) * | 2009-02-26 | 2015-03-24 | 8 Rivers Capital, Llc | Apparatus for combusting a fuel at high pressure and high temperature, and associated system |
US9068743B2 (en) * | 2009-02-26 | 2015-06-30 | 8 Rivers Capital, LLC & Palmer Labs, LLC | Apparatus for combusting a fuel at high pressure and high temperature, and associated system |
MX345743B (es) * | 2009-02-26 | 2017-02-14 | 8 Rivers Capital Llc | Aparato y método para efectuar la combustión de un combustible a alta presión y alta temperatura, y sistema y dispositivo asociados. |
EP2230455B1 (en) * | 2009-03-16 | 2012-04-18 | Alstom Technology Ltd | Burner for a gas turbine and method for locally cooling a hot gases flow passing through a burner |
US8371814B2 (en) * | 2009-06-24 | 2013-02-12 | Honeywell International Inc. | Turbine engine components |
US8852720B2 (en) | 2009-07-17 | 2014-10-07 | Rolls-Royce Corporation | Substrate features for mitigating stress |
US20110110772A1 (en) * | 2009-11-11 | 2011-05-12 | Arrell Douglas J | Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same |
US8529193B2 (en) * | 2009-11-25 | 2013-09-10 | Honeywell International Inc. | Gas turbine engine components with improved film cooling |
US9341118B2 (en) * | 2009-12-29 | 2016-05-17 | Rolls-Royce Corporation | Various layered gas turbine engine component constructions |
JP5767248B2 (ja) | 2010-01-11 | 2015-08-19 | ロールス−ロイス コーポレイション | 環境障壁コーティングに加わる熱又は機械的応力を軽減するための特徴体 |
EP2354453B1 (en) * | 2010-02-02 | 2018-03-28 | Siemens Aktiengesellschaft | Turbine engine component for adaptive cooling |
US8651805B2 (en) * | 2010-04-22 | 2014-02-18 | General Electric Company | Hot gas path component cooling system |
US8628293B2 (en) | 2010-06-17 | 2014-01-14 | Honeywell International Inc. | Gas turbine engine components with cooling hole trenches |
US8869889B2 (en) | 2010-09-21 | 2014-10-28 | Palmer Labs, Llc | Method of using carbon dioxide in recovery of formation deposits |
US8387245B2 (en) * | 2010-11-10 | 2013-03-05 | General Electric Company | Components with re-entrant shaped cooling channels and methods of manufacture |
US8753071B2 (en) | 2010-12-22 | 2014-06-17 | General Electric Company | Cooling channel systems for high-temperature components covered by coatings, and related processes |
US20120243995A1 (en) * | 2011-03-21 | 2012-09-27 | General Electric Company | Components with cooling channels formed in coating and methods of manufacture |
US20120295061A1 (en) * | 2011-05-18 | 2012-11-22 | General Electric Company | Components with precision surface channels and hybrid machining method |
US8997495B2 (en) | 2011-06-24 | 2015-04-07 | United Technologies Corporation | Strain tolerant combustor panel for gas turbine engine |
US9206696B2 (en) | 2011-08-16 | 2015-12-08 | General Electric Company | Components with cooling channels and methods of manufacture |
US20130078418A1 (en) * | 2011-09-23 | 2013-03-28 | General Electric Company | Components with cooling channels and methods of manufacture |
US20130101761A1 (en) * | 2011-10-21 | 2013-04-25 | General Electric Company | Components with laser cladding and methods of manufacture |
US9249670B2 (en) * | 2011-12-15 | 2016-02-02 | General Electric Company | Components with microchannel 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 |
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 |
US9200521B2 (en) * | 2012-10-30 | 2015-12-01 | General Electric Company | Components with micro cooled coating layer and methods of manufacture |
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US9664111B2 (en) | 2012-12-19 | 2017-05-30 | United Technologies Corporation | Closure of cooling holes with a filing agent |
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US10934853B2 (en) | 2014-07-03 | 2021-03-02 | Rolls-Royce Corporation | Damage tolerant cooling of high temperature mechanical system component including a coating |
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US20170122109A1 (en) * | 2015-10-29 | 2017-05-04 | General Electric Company | Component for a gas turbine engine |
US10598026B2 (en) | 2016-05-12 | 2020-03-24 | General Electric Company | Engine component wall with a cooling circuit |
US11021965B2 (en) | 2016-05-19 | 2021-06-01 | Honeywell International Inc. | Engine components with cooling holes having tailored metering and diffuser portions |
DE102016219424A1 (de) * | 2016-10-06 | 2018-04-12 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammeranordnung einer Gasturbine sowie Fluggasturbine |
BR112019018466A2 (pt) | 2017-03-07 | 2020-04-14 | 8 Rivers Capital Llc | sistema e método para a operação de um combustor de combustível flexível para uma turbina de gás |
US10859264B2 (en) | 2017-03-07 | 2020-12-08 | 8 Rivers Capital, Llc | System and method for combustion of non-gaseous fuels and derivatives thereof |
US11047240B2 (en) | 2017-05-11 | 2021-06-29 | General Electric Company | CMC components having microchannels and methods for forming microchannels in CMC components |
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 |
US10760430B2 (en) | 2017-05-31 | 2020-09-01 | General Electric Company | Adaptively opening backup cooling pathway |
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US6761956B2 (en) | 2001-12-20 | 2004-07-13 | General Electric Company | Ventilated thermal barrier coating |
US6663919B2 (en) | 2002-03-01 | 2003-12-16 | General Electric Company | Process of removing a coating deposit from a through-hole in a component and component processed thereby |
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2004
- 2004-11-09 US US10/984,292 patent/US7186091B2/en not_active Expired - Fee Related
-
2005
- 2005-10-26 JP JP2005310643A patent/JP4800742B2/ja not_active Expired - Fee Related
- 2005-11-03 EP EP05256817A patent/EP1655454B1/en not_active Expired - Fee Related
- 2005-11-03 CA CA2525283A patent/CA2525283C/en not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
US20060099080A1 (en) | 2006-05-11 |
EP1655454B1 (en) | 2011-06-15 |
JP2006138624A (ja) | 2006-06-01 |
EP1655454A1 (en) | 2006-05-10 |
CA2525283A1 (en) | 2006-05-09 |
US7186091B2 (en) | 2007-03-06 |
CA2525283C (en) | 2013-03-12 |
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