JP2013245673A - マイクロチャネル冷却式プラットフォーム及びフィレットを有する部品並びにその製造方法 - Google Patents
マイクロチャネル冷却式プラットフォーム及びフィレットを有する部品並びにその製造方法 Download PDFInfo
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Images
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
- F01D5/187—Convection 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
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- 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
- F05D2260/204—Heat transfer, e.g. cooling by the use of microcircuits
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/4935—Heat exchanger or boiler making
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】部品は、外面112と内面116とを含む基材110を備える。内面は中空内部空間114を画成する。基材の外面は翼形部を形成する。基材の外面は、プラットフォーム92と、翼形部と各プラットフォームとの間に延在してそれらを一体につなぐフィレット94とをさらに画成する。外面は、少なくとも部分的に各フィレットに沿って延在する溝132を画成する。溝は中空内部空間と流体連通している。本部品は、基材の外面の少なくとも一部の上に設けられた皮膜150であって、溝の上に延在する構造皮膜を含む皮膜をさらに備えている。溝と構造皮膜とは一緒に各フィレットを冷却するためのチャネル130を画成する。
【選択図】図5
Description
さらに、フィレットが大きいと、鋳造収率に対する制約が減るので、鋳造コストが下がる。さらに、本発明で新たに可能となったフィレットサイズの増大によって、フィレット領域(一般に溶射プロセスの際のミクロ組織制御が難しい領域である。)でのセラミック皮膜のミクロ組織も改善される。さらに、上述のフィレット及び/又はプラットフォーム冷却は設計面で柔軟性に富み、フィレット/プラットフォームに冷却を事実上あらゆる配向で組み込むことができる。加えて、フィレット輪郭が大きくなることで、空力効率も向上すると予測される。
12 圧縮機
14 燃焼器
16 タービン
18 シャフト
20 燃料ノズル
24 基材(部品)の正圧側壁
26 基材(部品)の負圧側壁
28 部品の前縁
30 部品の後縁
32 冷却流路の入口部
34 冷却流路の中間部
36 冷却流路の出口部
52 表面法線
54 構造皮膜
90 翼形部
92 プラットフォーム
94 フィレット
96 シャンク
98 プラットフォーム端部
100 高温ガス経路部品
110 基材
112 基材の外面
114 中空内部空間
116 基材の内面
130 チャネル
132 溝
134 溝の底面
136 溝の開口(上面)
140 アクセス穴
144 透過性スロット
146 シャンクを貫通する通路
148 プラットフォームを貫通するアクセス穴
150 皮膜
160 研磨液ジェット
Claims (15)
- 外面と内面とを含む基材であって、内面が1以上の中空内部空間を画成しており、基材の外面が正圧側壁と負圧側壁とを画成していて正圧側壁と負圧側壁が部品の前縁及び後縁で一体となって部品の翼形部を形成しており、基材の外面がさらに、1以上のプラットフォームと、翼形部と各プラットフォームとの間に一体に延在してそれらを接続する1以上のフィレットとを画成しており、外面が、少なくとも部分的に各フィレットに沿って延在する1以上の溝を画成していて、各々の溝が各中空内部空間と流体連通している、基材と、
基材の外面の少なくとも一部の上に設けられた皮膜であって、皮膜が少なくとも構造皮膜を含んでいて、構造皮膜が1以上の溝の上に延在していて、1以上の溝と構造皮膜とが一緒に各フィレットを冷却するための1以上のチャネルを画成している、皮膜と
を備える部品。 - 当該部品がタービン動翼を含んでいて、前記基材がさらに、各中空内部空間と1以上の冷却流路との間に延在してそれらを流体連通せしめる1以上のアクセスチャネルを画成している、請求項1記載の部品。
- 冷却流路の少なくとも1つが各フィレットに沿って半径方向に延在する、請求項1記載の部品。
- 冷却流路の少なくとも1つが、各フィレットに沿って軸方向、長手方向又は軸方向と長手方向の両方向に延在する、請求項1記載の部品。
- 冷却流路の少なくとも1つが、各フィレットに沿って軸方向−半径方向に延在する、請求項1記載の部品。
- 各々の溝が開口を有しており、各々の溝がその開口で狭まっていてリエントラント形の溝をなしており、各々の冷却流路がリエントラント形冷却流路を含んでいる、請求項1記載の部品。
- 当該部品がタービン動翼を含んでいて、前記基材がさらに、
プラットフォームと一体につながるシャンクと、
シャンクを貫通して各中空内部空間とシャンクの外部領域とを流体連通せしめる1以上の通路と、
少なくとも部分的にプラットフォーム内に延在して冷却流路とシャンクの外部領域とを流体連通せしめる1以上のアクセス穴であって、各冷却流路の底面に通じる1以上のアクセス穴と
を画成しており、各々の冷却流路が各フィレットに沿って半径方向に延在する、請求項1記載の部品。 - 前記冷却流路が、各フィレットの上端部に出口を有する、請求項7記載の部品。
- 外面と内面とを含む基材であって、内面が1以上の中空内部空間を画成しており、基材の外面が正圧側壁と負圧側壁とを画成していて正圧側壁と負圧側壁が部品の前縁及び後縁で一体となって部品の翼形部を形成しており、基材の外面がさらに、1以上のプラットフォームと、翼形部と各プラットフォームとの間に一体に延在してそれらを接続する1以上のフィレットとを画成しており、外面が、少なくとも部分的に各プラットフォームに沿って延在する1以上の溝を画成していて、各々の溝が各中空内部空間と流体連通している、基材と、
基材の外面の少なくとも一部の上に設けられた皮膜であって、皮膜が少なくとも構造皮膜を含んでいて、構造皮膜が1以上の溝の上に延在していて、1以上の溝と構造皮膜とが一緒に各プラットフォームを冷却するための1以上のチャネルを画成している、皮膜と
を備える部品。 - 当該部品がタービン動翼を含んでいて、前記基材がさらに、各中空内部空間と1以上の冷却流路との間に延在してそれらを流体連通せしめる1以上のアクセスチャネルを画成しており、各々の溝が開口を有しており、各々の溝がその開口で狭まっていてリエントラント形の溝をなしており、各々の冷却流路がリエントラント形冷却流路を含んでいる、請求項9記載の部品。
- 冷却流路の少なくとも1つが、各プラットフォームに沿って軸方向、長手方向又は軸方向と長手方向の両方向に延在する、請求項9記載の部品。
- 前記冷却流路が、各プラットフォームの一端に出口を有する、請求項11記載の部品。
- 冷却流路の少なくとも1つが、各フィレットに沿って半径方向に延在し、次いで各プラットフォームに沿って軸方向、長手方向又は軸方向と長手方向の両方向に延在する、請求項11記載の部品。
- 当該部品がタービン動翼を含んでいて、前記基材がさらに、
プラットフォームと一体につながるシャンクと、
シャンクを貫通して各中空内部空間とシャンクの外部領域とを流体連通せしめる1以上の通路と、
少なくとも部分的にプラットフォーム内に延在して冷却流路とシャンクの外部領域とを流体連通せしめる1以上のアクセス穴であって、各冷却流路の底面に通じる1以上のアクセス穴と
を画成しており、各々の冷却流路が各プラットフォームに沿って軸方向、長手方向又は軸方向と長手方向の両方向に延在する、請求項9記載の部品。 - 当該部品がタービン動翼を含んでいて、前記基材がさらに、
プラットフォームと一体につながるシャンクと、
少なくとも部分的にプラットフォーム内に延在して各中空内部空間と各冷却流路とを流体連通せしめる1以上のアクセス穴と
を画成しており、冷却流路が、各プラットフォームに沿って軸方向、長手方向又は軸方向と長手方向の両方向に延在する、請求項9記載の部品。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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US13/478,517 | 2012-05-23 | ||
US13/478,517 US9243503B2 (en) | 2012-05-23 | 2012-05-23 | Components with microchannel cooled platforms and fillets and methods of manufacture |
Publications (3)
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JP2013245673A true JP2013245673A (ja) | 2013-12-09 |
JP2013245673A5 JP2013245673A5 (ja) | 2016-07-07 |
JP6192982B2 JP6192982B2 (ja) | 2017-09-06 |
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Country Status (4)
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US (1) | US9243503B2 (ja) |
EP (1) | EP2666965B1 (ja) |
JP (1) | JP6192982B2 (ja) |
RU (1) | RU2013123029A (ja) |
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US8673397B2 (en) | 2010-11-10 | 2014-03-18 | General Electric Company | Methods of fabricating and coating a component |
US8387245B2 (en) * | 2010-11-10 | 2013-03-05 | General Electric Company | Components with re-entrant shaped cooling channels and methods of manufacture |
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 |
US9238265B2 (en) | 2012-09-27 | 2016-01-19 | General Electric Company | Backstrike protection during machining of cooling features |
US9156114B2 (en) | 2012-11-13 | 2015-10-13 | General Electric Company | Method for manufacturing turbine nozzle having non-linear cooling conduit |
US9200534B2 (en) * | 2012-11-13 | 2015-12-01 | General Electric Company | Turbine nozzle having non-linear cooling conduit |
US10612392B2 (en) * | 2014-12-18 | 2020-04-07 | United Technologies Corporation | Gas turbine engine component with conformal fillet cooling path |
US10344597B2 (en) * | 2015-08-17 | 2019-07-09 | United Technologies Corporation | Cupped contour for gas turbine engine blade assembly |
US10267161B2 (en) * | 2015-12-07 | 2019-04-23 | General Electric Company | Gas turbine engine with fillet film holes |
US10227876B2 (en) | 2015-12-07 | 2019-03-12 | General Electric Company | Fillet optimization for turbine airfoil |
US10247009B2 (en) * | 2016-05-24 | 2019-04-02 | General Electric Company | Cooling passage for gas turbine system rotor blade |
US20220205364A1 (en) * | 2020-12-30 | 2022-06-30 | General Electric Company | Cooling circuit having a bypass conduit for a turbomachine component |
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EP2666965B1 (en) | 2015-07-08 |
JP6192982B2 (ja) | 2017-09-06 |
RU2013123029A (ru) | 2014-11-27 |
CN103422907A (zh) | 2013-12-04 |
US20130312941A1 (en) | 2013-11-28 |
US9243503B2 (en) | 2016-01-26 |
EP2666965A1 (en) | 2013-11-27 |
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