JP2015511678A - タービン翼 - Google Patents
タービン翼 Download PDFInfo
- Publication number
- JP2015511678A JP2015511678A JP2015500931A JP2015500931A JP2015511678A JP 2015511678 A JP2015511678 A JP 2015511678A JP 2015500931 A JP2015500931 A JP 2015500931A JP 2015500931 A JP2015500931 A JP 2015500931A JP 2015511678 A JP2015511678 A JP 2015511678A
- Authority
- JP
- Japan
- Prior art keywords
- side wall
- wall
- pressure side
- suction side
- blade
- 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.)
- Granted
Links
- 239000012530 fluid Substances 0.000 claims abstract description 7
- 238000001816 cooling Methods 0.000 claims description 58
- 239000002826 coolant Substances 0.000 claims description 4
- 239000007789 gas Substances 0.000 description 22
- 239000000463 material Substances 0.000 description 13
- 230000035882 stress Effects 0.000 description 7
- 239000012528 membrane Substances 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 4
- 230000008602 contraction Effects 0.000 description 4
- 230000001052 transient effect Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000000930 thermomechanical effect Effects 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003779 heat-resistant material Substances 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 230000008646 thermal stress Effects 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
- 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
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2251/00—Material properties
- F05C2251/02—Elasticity
-
- 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
- F05D2250/70—Shape
- F05D2250/71—Shape curved
-
- 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
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/501—Elasticity
Abstract
Description
上で述べたタービン翼は、耐熱性の構成部材を成していて、特にガスタービン装置のタービン段において使用され、且つ静翼又は動翼の形態で、燃焼室から直接に流出する高温ガスに晒されている。
本開示の根底を成す課題は、流体回転機械用のタービン翼であって、翼板を備えており、該翼板は、凹状の圧力側壁と凸状の吸込み側壁とによって画成されており、これらの圧力側壁と吸込み側壁とは、翼板に配設可能な翼前縁の領域で結合されていて、翼前縁の長手方向延在部内に延在する中空室を包囲しており、該中空室は、翼前縁領域の圧力側壁及び吸込み側壁の内壁と、翼前縁に向かって長手方向に延在していて、吸込み側壁と圧力側壁の内壁を結合している中間壁とによって画成されているタービン翼を改良して、温度差に起因する翼前縁領域の疲労現象を減少させ、遂には完全に回避しようとするものであり、このようにして、激しく熱に暴露されるタービン翼の耐用年数を改良する点にある。
以下に、本発明の実施形態を図面につき詳しく説明する。
Claims (13)
- 流体回転機械用のタービン翼であって、翼板(4)を備えており、該翼板(4)は、凹状の圧力側壁(6)と凸状の吸込み側壁(7)とによって画成されており、これらの該圧力側壁(6)と該吸込み側壁(7)とは、前記翼板(4)に配設可能な翼前縁(5)の領域(B)で結合されていて、該翼前縁(5)の長手方向延在部内に延在する中空室(9)を包囲しており、該中空室(9)は、前記翼前縁(5)の領域の前記圧力側壁(6)及び前記吸込み側壁(7)の内壁と、前記翼前縁(5)に向かって長手方向に延在していて、前記吸込み側壁(7)と前記圧力側壁(6)の内壁を結合している中間壁(8)とによって画成されているものにおいて、
該中間壁(8)は、前記吸込み側壁(7)及び/又は前記圧力側壁(6)に対する接続領域において、該接続領域における前記中間壁(8)の弾性を高めるために、少なくとも部分的に穿孔部(16)を有していることを特徴とする、流体回転機械用のタービン翼。 - 前記穿孔部(16)は、1列の円筒状の孔(18)を有している、請求項1記載のタービン翼。
- 前記穿孔部は、1列の長孔(19)又はスリットを有しており、該長孔(19)又はスリットの長辺は、隣接する前記吸込み側壁(7)及び/又は前記圧力側壁(6)に対して平行に延びている、請求項1記載のタービン翼。
- 前記吸込み側壁(7)及び/又は前記圧力側壁(6)に対する前記中間壁(8)の接続領域は、凹溝(17)を有しており、前記穿孔部(16)は、少なくとも部分的に前記凹溝(17)を通って延びている、請求項1から3までのいずれか1項記載のタービン翼。
- 前記中間壁(8)は、前記中空室(9)とは反対の側に、前記吸込み側壁(7)及び前記圧力側壁(6)と共に少なくとも1つの別の中空室(10)を画成する壁面を有しており、前記中空室(9,10)は、内部に冷却媒体を導入可能な冷却通路である、請求項1から4までのいずれか1項記載のタービン翼。
- 前記穿孔部(16)の開口は、前記中間壁(8)の接続領域の前記吸込み側壁(7)若しくは前記圧力側壁(6)の表面に対して平行に形成されていて、運転中にこれらの開口を通って冷却空気が一方の中空室(10)から別の中空室(9)に流入し、各開口の流出流は、各前記吸込み側壁(7)若しくは前記圧力側壁(6)の内壁に対して接線方向に流出する、請求項5記載のタービン翼。
- 前記中間壁(8)は、前記吸込み側壁(7)から前記圧力側壁(6)までの延在部又は前記圧力側壁(6)から前記吸込み側壁(7)までの延在部に、直線的な壁延在部とは異なる、湾曲して形成された少なくとも1つの壁区分を有しており、該少なくとも1つの湾曲した壁区分は、前記吸込み側壁(7)から前記圧力側壁(6)までの前記中間壁(8)の延在方向又は前記圧力側壁(6)から前記吸込み側壁(7)までの前記中間壁(8)の延在方向に、湾曲に起因する弾性を有するように形成されている、請求項1から6までのいずれか1項記載のタービン翼。
- 前記少なくとも1つの湾曲して形成された壁区分は、前記翼前縁(5)を断面した横断面で見てV字形又はU字形に形成されている、請求項7記載のタービン翼。
- 前記V字形又はU字形に形成された前記中間壁(8)の横断面の底部は、少なくとも部分的に穿孔部(16)を有しており、該穿孔部(16)は、弾性を高めるために、前記接続領域の穿孔部に対して平行に延びている、請求項8記載のタービン翼。
- 前記V字形又はU字形に形成された壁区分の凸状の壁面は、前記翼前縁(5)において結合されていて、前記中空室(9)を画成する前記吸込み側壁(7)及び前記圧力側壁(6)に対して概ね平行に形成され且つ配置されている、請求項7から9までのいずれか1項記載のタービン翼。
- 前記中間壁(8)に、前記翼前縁(5)において結合された前記吸込み側壁(7)及び前記圧力側壁(6)の衝突冷却用の通流通路(15)が設けられている、請求項7から10までのいずれか1項記載のタービン翼。
- 前記中間壁(8)内に配置された通流通路は、該通流通路に配設可能な通流通路長手方向延在部に基づき規定される通流方向に関して、少なくとも3つのグループに分けることができ、第1グループの通流通路(15a)は、前記吸込み側壁(7)に対して方向付けられた通流方向を有しており、第2グループの通流通路(15b)は、前記翼前縁(5)に対して方向付けられた通流方向を有しており、第3グループの通流通路(15c)は、前記圧力側壁(6)に対して方向付けられた通流方向を有している、請求項7から11までのいずれか1項記載のタービン翼。
- 当該タービン翼は、ガスタービン装置のタービン段の静翼又は動翼である、請求項1から12までのいずれか1項記載のタービン翼。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12160893 | 2012-03-22 | ||
EP12160893.9 | 2012-03-22 | ||
PCT/EP2013/055965 WO2013139926A1 (de) | 2012-03-22 | 2013-03-21 | Turbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2015511678A true JP2015511678A (ja) | 2015-04-20 |
JP6169161B2 JP6169161B2 (ja) | 2017-07-26 |
Family
ID=48049957
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2015500931A Expired - Fee Related JP6169161B2 (ja) | 2012-03-22 | 2013-03-21 | タービン翼 |
Country Status (6)
Country | Link |
---|---|
US (1) | US9932836B2 (ja) |
EP (1) | EP2828484B1 (ja) |
JP (1) | JP6169161B2 (ja) |
CN (1) | CN104204412B (ja) |
CA (1) | CA2867960A1 (ja) |
WO (1) | WO2013139926A1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2017078414A (ja) * | 2015-10-15 | 2017-04-27 | ゼネラル・エレクトリック・カンパニイ | タービンブレード |
JP2017145824A (ja) * | 2016-02-16 | 2017-08-24 | ゼネラル・エレクトリック・カンパニイ | 交差穴を有する翼形部 |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CA2867960A1 (en) * | 2012-03-22 | 2013-09-26 | Alstom Technology Ltd. | Turbine blade |
US9296039B2 (en) | 2012-04-24 | 2016-03-29 | United Technologies Corporation | Gas turbine engine airfoil impingement cooling |
US9995149B2 (en) * | 2013-12-30 | 2018-06-12 | General Electric Company | Structural configurations and cooling circuits in turbine blades |
EP2933435A1 (de) | 2014-04-15 | 2015-10-21 | Siemens Aktiengesellschaft | Turbinenschaufel und zugehörige Turbine |
EP3000970B1 (en) * | 2014-09-26 | 2019-06-12 | Ansaldo Energia Switzerland AG | Cooling scheme for the leading edge of a turbine blade of a gas turbine |
EP3199760A1 (de) * | 2016-01-29 | 2017-08-02 | Siemens Aktiengesellschaft | Turbinenschaufel mit einem drosselelement |
US20190017392A1 (en) * | 2017-07-13 | 2019-01-17 | General Electric Company | Turbomachine impingement cooling insert |
US10626733B2 (en) * | 2017-10-03 | 2020-04-21 | United Technologies Corporation | Airfoil having internal hybrid cooling cavities |
US10626734B2 (en) | 2017-10-03 | 2020-04-21 | United Technologies Corporation | Airfoil having internal hybrid cooling cavities |
US10704398B2 (en) * | 2017-10-03 | 2020-07-07 | Raytheon Technologies Corporation | Airfoil having internal hybrid cooling cavities |
US20190101009A1 (en) * | 2017-10-03 | 2019-04-04 | United Technologies Corporation | Airfoil having internal hybrid cooling cavities |
US10633980B2 (en) * | 2017-10-03 | 2020-04-28 | United Technologies Coproration | Airfoil having internal hybrid cooling cavities |
US10563519B2 (en) * | 2018-02-19 | 2020-02-18 | General Electric Company | Engine component with cooling hole |
US11391161B2 (en) * | 2018-07-19 | 2022-07-19 | General Electric Company | Component for a turbine engine with a cooling hole |
KR102161765B1 (ko) * | 2019-02-22 | 2020-10-05 | 두산중공업 주식회사 | 터빈용 에어포일, 이를 포함하는 터빈 |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0475658A1 (en) * | 1990-09-06 | 1992-03-18 | General Electric Company | Turbine blade airfoil with serial impingement cooling through internal cavity-forming ribs |
US6206638B1 (en) * | 1999-02-12 | 2001-03-27 | General Electric Company | Low cost airfoil cooling circuit with sidewall impingement cooling chambers |
US20010016162A1 (en) * | 2000-01-13 | 2001-08-23 | Ewald Lutum | Cooled blade for a gas turbine |
US20040096313A1 (en) * | 2002-11-12 | 2004-05-20 | Harvey Neil W. | Turbine components |
US6837683B2 (en) * | 2001-11-21 | 2005-01-04 | Rolls-Royce Plc | Gas turbine engine aerofoil |
US20050111981A1 (en) * | 2003-07-11 | 2005-05-26 | Peter Davison | Turbine blade with impingement cooling |
EP1605138A2 (en) * | 2004-05-27 | 2005-12-14 | United Technologies Corporation | Cooled rotor blade with leading edge impingement cooling |
FR2918105A1 (fr) * | 2007-06-27 | 2009-01-02 | Snecma Sa | Aube refroidie de turbomachine comprenant des trous de refroidissement a distance d'impact variable. |
US20090074575A1 (en) * | 2007-01-11 | 2009-03-19 | United Technologies Corporation | Cooling circuit flow path for a turbine section airfoil |
US7520725B1 (en) * | 2006-08-11 | 2009-04-21 | Florida Turbine Technologies, Inc. | Turbine airfoil with near-wall leading edge multi-holes cooling |
US20100303635A1 (en) * | 2009-06-01 | 2010-12-02 | Rolls-Royce Plc | Cooling arrangements |
Family Cites Families (40)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3191908A (en) * | 1961-05-02 | 1965-06-29 | Rolls Royce | Blades for fluid flow machines |
JPS59200001A (ja) * | 1983-04-28 | 1984-11-13 | Toshiba Corp | ガスタ−ビン翼 |
FR2659689B1 (fr) * | 1990-03-14 | 1992-06-05 | Snecma | Circuit de refroidissement interne d'une aube directrice de turbine. |
US5813835A (en) * | 1991-08-19 | 1998-09-29 | The United States Of America As Represented By The Secretary Of The Air Force | Air-cooled turbine blade |
US5246340A (en) * | 1991-11-19 | 1993-09-21 | Allied-Signal Inc. | Internally cooled airfoil |
US5690472A (en) * | 1992-02-03 | 1997-11-25 | General Electric Company | Internal cooling of turbine airfoil wall using mesh cooling hole arrangement |
FR2689176B1 (fr) * | 1992-03-25 | 1995-07-13 | Snecma | Aube refrigeree de turbo-machine. |
US5660524A (en) | 1992-07-13 | 1997-08-26 | General Electric Company | Airfoil blade having a serpentine cooling circuit and impingement cooling |
US5382133A (en) * | 1993-10-15 | 1995-01-17 | United Technologies Corporation | High coverage shaped diffuser film hole for thin walls |
US5688104A (en) * | 1993-11-24 | 1997-11-18 | United Technologies Corporation | Airfoil having expanded wall portions to accommodate film cooling holes |
DE19617556A1 (de) * | 1996-05-02 | 1997-11-06 | Asea Brown Boveri | Thermisch belastete Schaufel für eine Strömungsmaschine |
EP0954679B1 (en) | 1996-06-28 | 2003-01-22 | United Technologies Corporation | Coolable airfoil for a gas turbine engine |
JP3781832B2 (ja) | 1996-08-29 | 2006-05-31 | 株式会社東芝 | ガスタービン |
DE19738065A1 (de) | 1997-09-01 | 1999-03-04 | Asea Brown Boveri | Turbinenschaufel einer Gasturbine |
US6099251A (en) * | 1998-07-06 | 2000-08-08 | United Technologies Corporation | Coolable airfoil for a gas turbine engine |
JP4315599B2 (ja) | 1998-08-31 | 2009-08-19 | シーメンス アクチエンゲゼルシヤフト | タービン翼 |
US6290463B1 (en) * | 1999-09-30 | 2001-09-18 | General Electric Company | Slotted impingement cooling of airfoil leading edge |
US6431832B1 (en) | 2000-10-12 | 2002-08-13 | Solar Turbines Incorporated | Gas turbine engine airfoils with improved cooling |
GB0025012D0 (en) | 2000-10-12 | 2000-11-29 | Rolls Royce Plc | Cooling of gas turbine engine aerofoils |
JP2002242607A (ja) * | 2001-02-20 | 2002-08-28 | Mitsubishi Heavy Ind Ltd | ガスタービン冷却翼 |
US6672836B2 (en) * | 2001-12-11 | 2004-01-06 | United Technologies Corporation | Coolable rotor blade for an industrial gas turbine engine |
US6732502B2 (en) * | 2002-03-01 | 2004-05-11 | General Electric Company | Counter rotating aircraft gas turbine engine with high overall pressure ratio compressor |
GB0418914D0 (en) | 2004-08-25 | 2004-09-29 | Rolls Royce Plc | Turbine component |
US7374403B2 (en) * | 2005-04-07 | 2008-05-20 | General Electric Company | Low solidity turbofan |
US7534089B2 (en) * | 2006-07-18 | 2009-05-19 | Siemens Energy, Inc. | Turbine airfoil with near wall multi-serpentine cooling channels |
DE502006003548D1 (de) | 2006-08-23 | 2009-06-04 | Siemens Ag | Beschichtete Turbinenschaufel |
US7815417B2 (en) * | 2006-09-01 | 2010-10-19 | United Technologies Corporation | Guide vane for a gas turbine engine |
EP2074322B1 (en) * | 2006-10-12 | 2013-01-16 | United Technologies Corporation | Turbofan engine |
US7625180B1 (en) * | 2006-11-16 | 2009-12-01 | Florida Turbine Technologies, Inc. | Turbine blade with near-wall multi-metering and diffusion cooling circuit |
US8844265B2 (en) * | 2007-08-01 | 2014-09-30 | United Technologies Corporation | Turbine section of high bypass turbofan |
EP2107215B1 (en) * | 2008-03-31 | 2013-10-23 | Alstom Technology Ltd | Gas turbine airfoil |
US8807477B2 (en) * | 2008-06-02 | 2014-08-19 | United Technologies Corporation | Gas turbine engine compressor arrangement |
GB0810986D0 (en) | 2008-06-17 | 2008-07-23 | Rolls Royce Plc | A Cooling arrangement |
US8152468B2 (en) * | 2009-03-13 | 2012-04-10 | United Technologies Corporation | Divoted airfoil baffle having aimed cooling holes |
US8961111B2 (en) * | 2012-01-03 | 2015-02-24 | General Electric Company | Turbine and method for separating particulates from a fluid |
US20130192256A1 (en) * | 2012-01-31 | 2013-08-01 | Gabriel L. Suciu | Geared turbofan engine with counter-rotating shafts |
CA2867960A1 (en) * | 2012-03-22 | 2013-09-26 | Alstom Technology Ltd. | Turbine blade |
US9296039B2 (en) * | 2012-04-24 | 2016-03-29 | United Technologies Corporation | Gas turbine engine airfoil impingement cooling |
US8678743B1 (en) * | 2013-02-04 | 2014-03-25 | United Technologies Corporation | Method for setting a gear ratio of a fan drive gear system of a gas turbine engine |
EP3000970B1 (en) * | 2014-09-26 | 2019-06-12 | Ansaldo Energia Switzerland AG | Cooling scheme for the leading edge of a turbine blade of a gas turbine |
-
2013
- 2013-03-21 CA CA2867960A patent/CA2867960A1/en not_active Abandoned
- 2013-03-21 JP JP2015500931A patent/JP6169161B2/ja not_active Expired - Fee Related
- 2013-03-21 EP EP13714573.6A patent/EP2828484B1/de active Active
- 2013-03-21 CN CN201380015613.6A patent/CN104204412B/zh active Active
- 2013-03-21 WO PCT/EP2013/055965 patent/WO2013139926A1/de active Application Filing
-
2014
- 2014-09-19 US US14/490,813 patent/US9932836B2/en not_active Expired - Fee Related
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0475658A1 (en) * | 1990-09-06 | 1992-03-18 | General Electric Company | Turbine blade airfoil with serial impingement cooling through internal cavity-forming ribs |
US6206638B1 (en) * | 1999-02-12 | 2001-03-27 | General Electric Company | Low cost airfoil cooling circuit with sidewall impingement cooling chambers |
US20010016162A1 (en) * | 2000-01-13 | 2001-08-23 | Ewald Lutum | Cooled blade for a gas turbine |
US6837683B2 (en) * | 2001-11-21 | 2005-01-04 | Rolls-Royce Plc | Gas turbine engine aerofoil |
US20040096313A1 (en) * | 2002-11-12 | 2004-05-20 | Harvey Neil W. | Turbine components |
US20050111981A1 (en) * | 2003-07-11 | 2005-05-26 | Peter Davison | Turbine blade with impingement cooling |
EP1605138A2 (en) * | 2004-05-27 | 2005-12-14 | United Technologies Corporation | Cooled rotor blade with leading edge impingement cooling |
US7520725B1 (en) * | 2006-08-11 | 2009-04-21 | Florida Turbine Technologies, Inc. | Turbine airfoil with near-wall leading edge multi-holes cooling |
US20090074575A1 (en) * | 2007-01-11 | 2009-03-19 | United Technologies Corporation | Cooling circuit flow path for a turbine section airfoil |
FR2918105A1 (fr) * | 2007-06-27 | 2009-01-02 | Snecma Sa | Aube refroidie de turbomachine comprenant des trous de refroidissement a distance d'impact variable. |
US20100303635A1 (en) * | 2009-06-01 | 2010-12-02 | Rolls-Royce Plc | Cooling arrangements |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2017078414A (ja) * | 2015-10-15 | 2017-04-27 | ゼネラル・エレクトリック・カンパニイ | タービンブレード |
JP2017145824A (ja) * | 2016-02-16 | 2017-08-24 | ゼネラル・エレクトリック・カンパニイ | 交差穴を有する翼形部 |
Also Published As
Publication number | Publication date |
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JP6169161B2 (ja) | 2017-07-26 |
CN104204412A (zh) | 2014-12-10 |
EP2828484A1 (de) | 2015-01-28 |
EP2828484B1 (de) | 2019-05-08 |
WO2013139926A1 (de) | 2013-09-26 |
CN104204412B (zh) | 2016-09-28 |
US9932836B2 (en) | 2018-04-03 |
CA2867960A1 (en) | 2013-09-26 |
US20150004001A1 (en) | 2015-01-01 |
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