JP2009162224A - 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 - Google Patents
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 Download PDFInfo
- Publication number
- JP2009162224A JP2009162224A JP2008323256A JP2008323256A JP2009162224A JP 2009162224 A JP2009162224 A JP 2009162224A JP 2008323256 A JP2008323256 A JP 2008323256A JP 2008323256 A JP2008323256 A JP 2008323256A JP 2009162224 A JP2009162224 A JP 2009162224A
- Authority
- JP
- Japan
- Prior art keywords
- airfoil
- forming
- cooling
- hole
- diffusion
- 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.)
- Pending
Links
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H9/00—Machining specially adapted for treating particular metal objects or for obtaining special effects or results on metal objects
- B23H9/10—Working turbine blades or nozzles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/0093—Working by laser beam, e.g. welding, cutting or boring combined with mechanical machining or metal-working covered by other subclasses than B23K
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K26/00—Working by laser beam, e.g. welding, cutting or boring
- B23K26/36—Removing material
- B23K26/38—Removing material by boring or cutting
- B23K26/382—Removing material by boring or cutting by boring
- B23K26/389—Removing material by boring or cutting by boring of fluid openings, e.g. nozzles, jets
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K2101/00—Articles made by soldering, welding or cutting
- B23K2101/001—Turbines
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/06—Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components
-
- 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
- F05D2230/10—Manufacture by removing material
- F05D2230/12—Manufacture by removing material by spark erosion methods
-
- 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
- F05D2230/10—Manufacture by removing material
- F05D2230/13—Manufacture by removing material using lasers
-
- 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
-
- 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
- F23R2900/00018—Manufacturing combustion chamber liners or subparts
-
- 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
- F23R2900/03042—Film cooled combustion chamber walls or domes
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Optics & Photonics (AREA)
- Plasma & Fusion (AREA)
- Thermal Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
【解決手段】本方法は、加工物の第1の側面内にブラインド内向きテーパ移行開口部をレーザ形成する段階と、内向きテーパ移行開口部と連通したほぼ円筒形貫通孔を加工物の第2の対向する側面にEDM形成して、該加工物の第1及び第2の側面と連通した貫通冷却孔14を形成する段階とを含む。レーザ及びEDMの両方を使用することによって形成した冷却孔を有する翼形部10もまた、開示している。
【選択図】図3
Description
12 前縁
14 冷却孔
16 計量セクション
18 拡散セクション
20 前縁
22 冷却孔
24 計量セクション
26 拡散セクション
30 ロータブレード
32 翼形部
34 ダブテール
36 前縁
38 後縁
40 根元
42 先端
44 正圧側壁
46 負圧側壁
50 冷却回路
60 冷却孔
62 拡散セクション
64 計量セクション
F 冷却流体
Claims (9)
- 加工物内に冷却孔(14)を形成する方法であって、
前記加工物の第1の側面内にブラインド内向きテーパ移行開口部をレーザ形成する段階と、
前記内向きテーパ移行開口部と連通したほぼ円筒形貫通孔を前記加工物の第2の対向する側面にEDM形成して、該加工物の第1及び第2の側面と連通した貫通冷却孔(14)を形成する段階と、を含む、
方法。 - 前記加工物が、翼形部(10)を含み、
前記移行開口部を形成する段階が、前記冷却孔(14)の拡散セクション(18)を形成する段階を含み、
前記ほぼ円筒形貫通孔を形成する段階が、前記冷却孔(14)の計量セクション(24)を形成する段階を含む、
請求項1記載の方法。 - 軸方向に延びる空気力学的外表面曲率を有する前縁(36)及び軸方向に間隔を置いて配置された後縁(38)と、半径方向に延びるスパン軸線に沿って間隔を置いて配置された根元(40)及び先端(42)と、正圧側壁(44)及び横方向に間隔を置いて配置された負圧側壁(46)と、前記正圧側壁(44)及び負圧側壁(46)間に配置されてそれを冷却するために流体流を送るようになった冷却回路(50)とを有するタイプのタービン翼形部(10)内に複数の冷却孔(14)を形成する方法であって、
前記翼形部(10)の第1の側面内に複数のブラインド内向きテーパ拡散セクション(62)をレーザ形成する段階と、
前記内向きテーパ拡散セクションすなわち内向きテーパ移行開口部と連通したほぼ円筒形貫通計量セクション(64)を前記翼形部(10)の第2の対向する側面にEDM形成して、該翼形部(10)の第1及び第2の側面と連通した貫通冷却孔(60)を形成する段階と、を含む、
方法。 - 前記移行開口部の内端部を前記円筒形貫通孔のEDM形成用のガイドとして使用する段階を含む、請求項1又は請求項3記載の方法。
- 前記移行開口部を形成する段階が、前記円筒形貫通孔を形成する段階の前に行われる、請求項1又は請求項3記載の方法。
- 前記移行開口部を形成する段階が、前記円筒形貫通孔を形成する段階の後に行われる、請求項1又は請求項3記載の方法。
- 翼形部(32)であって、
(a)軸方向に延びる外表面曲率を有する前縁(36)及び軸方向に間隔を置いて配置された後縁(38)と、
(b)半径方向に延びるスパン軸線に沿って間隔を置いて配置された根元(40)及び先端(42)と、
(c)正圧側壁(44)及び横方向に間隔を置いて配置された負圧側壁(46)と、
(d)前記正圧側壁(44)及び負圧側壁(46)間に配置されて該翼形部(32)を冷却するために流体流を送るようになった冷却回路(50)と、
(e)前記冷却回路(50)と流体連通状態で該翼形部(32)のスパン軸線に沿って前記前縁(36)内に形成された複数の冷却孔(60)と、を含み、
前記冷却孔(60)の少なくとも幾つかが、前記前縁(36)表面と連通した拡散セクション(62)を有し、
前記拡散セクション(62)が、前記前縁(36)の表面上に出口開口部を形成した対向壁を有し、
それぞれの円筒形計量セクション(64)が、該翼形部(32)の内部と前記拡散セクション(62)との間に配置されかつそれらと連通し、
前記拡散セクション(62)がレーザによって形成され、また前記円筒形計量セクション(64)がEDMによって形成される、
翼形部(32)。 - 該翼形部(32)が、ガスタービン翼形部(32)である、請求項7記載の翼形部(32)。
- 前記拡散セクション(62)の少なくとも幾つかが、前記外表面上にほぼ直線矩形出口開口部を形成した対向壁を有し、
前記拡散壁(62)の少なくとも幾つかが、前記冷却孔(60)に対して局所的な該翼形部(32)の外表面曲率にほぼ一致した凸面形曲率を有し、それによって前記出口開口部からの流体流が、前記冷却孔(60)に隣接する該翼形部(32)の外表面のランド部分に沿って均等に分散されかつ広げられ、
前記拡散セクション(62)が、前記前縁(36)の表面上に出口開口部を形成した対向壁を有し、
それぞれの円筒形計量セクション(64)が、前記翼形部(32)の内部と前記拡散セクション(62)との間に配置されかつそれらに連通しかつ前記前縁(36)の半径から逸れた長手方向軸線を定め、
前記拡散セクション(62)がレーザによって形成され、また前記円筒形計量セクション(64)がEDMによって形成される、
請求項7又は8記載の翼形部(32)。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/965,859 US20090169394A1 (en) | 2007-12-28 | 2007-12-28 | Method of forming cooling holes and turbine airfoil with hybrid-formed cooling holes |
Publications (1)
Publication Number | Publication Date |
---|---|
JP2009162224A true JP2009162224A (ja) | 2009-07-23 |
Family
ID=40473720
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2008323256A Pending JP2009162224A (ja) | 2007-12-28 | 2008-12-19 | 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 |
Country Status (3)
Country | Link |
---|---|
US (1) | US20090169394A1 (ja) |
EP (1) | EP2075410A3 (ja) |
JP (1) | JP2009162224A (ja) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2012137898A1 (ja) | 2011-04-07 | 2012-10-11 | 株式会社Ihi | タービン翼 |
US9278408B2 (en) | 2013-02-27 | 2016-03-08 | Honda Motor Co., Ltd. | Laser machining apparatus |
US9759069B2 (en) | 2011-12-15 | 2017-09-12 | Ihi Corporation | Turbine blade |
JP2017205866A (ja) * | 2016-05-03 | 2017-11-24 | ゼネラル・エレクトリック・カンパニイ | 液体誘導レーザ加工および放電加工の組み合わせ |
Families Citing this family (40)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102008016026A1 (de) * | 2008-03-28 | 2009-10-01 | Mtu Aero Engines Gmbh | Verfahren und Vorrichtung zum Vermessen wenigstens einer Bohrung in zumindest einer ersten Oberfläche eines Bauteils |
US8079810B2 (en) * | 2008-09-16 | 2011-12-20 | Siemens Energy, Inc. | Turbine airfoil cooling system with divergent film cooling hole |
US8371815B2 (en) * | 2010-03-17 | 2013-02-12 | General Electric Company | Apparatus for cooling an airfoil |
DE102010051638A1 (de) * | 2010-11-17 | 2012-05-24 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenbrennkammer mit einer Kühlluftzuführvorrichtung |
US8944141B2 (en) * | 2010-12-22 | 2015-02-03 | United Technologies Corporation | Drill to flow mini core |
US9052113B1 (en) * | 2011-06-06 | 2015-06-09 | General Electric Company | Combustor nozzle and method for modifying the combustor nozzle |
US8522558B1 (en) * | 2012-02-15 | 2013-09-03 | United Technologies Corporation | Multi-lobed cooling hole array |
US9598979B2 (en) | 2012-02-15 | 2017-03-21 | United Technologies Corporation | Manufacturing methods for multi-lobed cooling holes |
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 |
US9561555B2 (en) | 2012-12-28 | 2017-02-07 | United Technologies Corporation | Non-line of sight electro discharge machined part |
US10041356B2 (en) * | 2014-08-15 | 2018-08-07 | United Technologies Corporation | Showerhead hole scheme apparatus and system |
US20160245094A1 (en) * | 2015-02-24 | 2016-08-25 | General Electric Company | Engine component |
US10208602B2 (en) * | 2015-04-27 | 2019-02-19 | United Technologies Corporation | Asymmetric diffuser opening for film cooling holes |
US10077667B2 (en) * | 2015-05-08 | 2018-09-18 | United Technologies Corporation | Turbine airfoil film cooling holes |
US9915151B2 (en) * | 2015-05-26 | 2018-03-13 | Rolls-Royce Corporation | CMC airfoil with cooling channels |
CA2933884A1 (en) * | 2015-06-30 | 2016-12-30 | Rolls-Royce Corporation | Combustor tile |
GB201521862D0 (en) * | 2015-12-11 | 2016-01-27 | Rolls Royce Plc | Cooling arrangement |
US11021965B2 (en) | 2016-05-19 | 2021-06-01 | Honeywell International Inc. | Engine components with cooling holes having tailored metering and diffuser portions |
US20180128177A1 (en) * | 2016-11-07 | 2018-05-10 | General Electric Company | Method for forming a hole in an engine component |
US10589370B2 (en) * | 2017-05-08 | 2020-03-17 | General Electric Company | Automatic blocked hole identification |
US10641102B2 (en) * | 2017-09-01 | 2020-05-05 | United Technologies Corporation | Turbine vane cluster including enhanced vane cooling |
US10933481B2 (en) | 2018-01-05 | 2021-03-02 | General Electric Company | Method of forming cooling passage for turbine component with cap element |
US10612391B2 (en) | 2018-01-05 | 2020-04-07 | General Electric Company | Two portion cooling passage for airfoil |
WO2019162464A1 (en) | 2018-02-23 | 2019-08-29 | Avonisys Ag | A method of machining a bore extending from an outer wall of a workpiece with liquid-jet guided laser beam |
US10767492B2 (en) * | 2018-12-18 | 2020-09-08 | General Electric Company | Turbine engine airfoil |
CN209324436U (zh) * | 2019-02-14 | 2019-08-30 | 高晟钧 | 一种航空发动机涡轮叶片 |
CN109973154B (zh) * | 2019-04-02 | 2019-12-06 | 高晟钧 | 一种带有冷却结构的航空发动机涡轮叶片 |
GB2600584B (en) * | 2019-07-23 | 2024-03-06 | Coflow Jet Llc | Fluid systems and methods that address flow separation |
US20210060709A1 (en) * | 2019-08-26 | 2021-03-04 | United Technologies Corporation | Laser rough drill and full edm finish for shaped cooling holes |
CN110524072B (zh) * | 2019-08-30 | 2020-12-25 | 中国航发动力股份有限公司 | 一种导向叶片气膜孔复合加工方法 |
CN112922677A (zh) * | 2021-05-11 | 2021-06-08 | 成都中科翼能科技有限公司 | 一种用于涡轮叶片前缘冷却的组合结构气膜孔 |
US11913119B2 (en) * | 2021-08-13 | 2024-02-27 | Rtx Corporation | Forming cooling aperture(s) in a turbine engine component |
US11732590B2 (en) | 2021-08-13 | 2023-08-22 | Raytheon Technologies Corporation | Transition section for accommodating mismatch between other sections of a cooling aperture in a turbine engine component |
US11898465B2 (en) | 2021-08-13 | 2024-02-13 | Rtx Corporation | Forming lined cooling aperture(s) in a turbine engine component |
US11813706B2 (en) | 2021-08-13 | 2023-11-14 | Rtx Corporation | Methods for forming cooling apertures in a turbine engine component |
US11603769B2 (en) | 2021-08-13 | 2023-03-14 | Raytheon Technologies Corporation | Forming lined cooling aperture(s) in a turbine engine component |
US11673200B2 (en) | 2021-08-13 | 2023-06-13 | Raytheon Technologies Corporation | Forming cooling aperture(s) using electrical discharge machining |
US11542831B1 (en) | 2021-08-13 | 2023-01-03 | Raytheon Technologies Corporation | Energy beam positioning during formation of a cooling aperture |
US20230193772A1 (en) * | 2021-12-21 | 2023-06-22 | Raytheon Technologies Corporation | Fabrication of cooling holes using laser machining and ultrasonic machining |
Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS63192902A (ja) * | 1986-11-13 | 1988-08-10 | クロマロイガスタービンコーポレイション | 分散された冷却孔を有する翼及びその加工する方法とその装置 |
US4818834A (en) * | 1988-03-21 | 1989-04-04 | Raycon Corporation | Process for drilling chamfered holes |
JPH0968001A (ja) * | 1995-08-31 | 1997-03-11 | Ishikawajima Harima Heavy Ind Co Ltd | 画像処理によるガスタービンブレードへの冷却孔の形成方法 |
JPH09144504A (ja) * | 1995-11-22 | 1997-06-03 | Ishikawajima Harima Heavy Ind Co Ltd | タービン冷却翼とその加工方法 |
JPH1089005A (ja) * | 1996-09-18 | 1998-04-07 | Toshiba Corp | 高温部材冷却装置 |
US6914214B2 (en) * | 2001-10-30 | 2005-07-05 | Rolls-Royce Plc | Method of forming a shaped hole |
JP2006207586A (ja) * | 2005-01-28 | 2006-08-10 | General Electric Co <Ge> | タービン翼形部の高効率ファン冷却孔 |
JP2006242187A (ja) * | 2005-03-01 | 2006-09-14 | General Electric Co <Ge> | タービンのエーロフォイル |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4808785A (en) * | 1986-11-13 | 1989-02-28 | Chromalloy Gas Turbine Corporation | Method and apparatus for making diffused cooling holes in an airfoil |
US5683600A (en) | 1993-03-17 | 1997-11-04 | General Electric Company | Gas turbine engine component with compound cooling holes and method for making the same |
US5486093A (en) | 1993-09-08 | 1996-01-23 | United Technologies Corporation | Leading edge cooling of turbine airfoils |
US5609779A (en) * | 1996-05-15 | 1997-03-11 | General Electric Company | Laser drilling of non-circular apertures |
US6287075B1 (en) | 1997-10-22 | 2001-09-11 | General Electric Company | Spanwise fan diffusion hole airfoil |
JP4450887B2 (ja) | 1999-05-20 | 2010-04-14 | 株式会社ティラド | 熱交換器 |
US6362446B1 (en) * | 1999-08-02 | 2002-03-26 | General Electric Company | Method for drilling hollow components |
US6326576B1 (en) * | 1999-09-22 | 2001-12-04 | General Electric Company | Method and apparatus for electrical discharge machining |
US6420677B1 (en) * | 2000-12-20 | 2002-07-16 | Chromalloy Gas Turbine Corporation | Laser machining cooling holes in gas turbine components |
GB2395157B (en) * | 2002-11-15 | 2005-09-07 | Rolls Royce Plc | Laser driliing shaped holes |
US6680454B1 (en) * | 2002-12-27 | 2004-01-20 | General Electric Company | Electromachining with perforated electrodes |
US7041933B2 (en) * | 2003-04-14 | 2006-05-09 | Meyer Tool, Inc. | Complex hole shaping |
US6897401B2 (en) * | 2003-07-31 | 2005-05-24 | United Technologies Corporation | Non-separating diffuser for holes produced by a two step process |
-
2007
- 2007-12-28 US US11/965,859 patent/US20090169394A1/en not_active Abandoned
-
2008
- 2008-12-17 EP EP08171897.5A patent/EP2075410A3/en not_active Withdrawn
- 2008-12-19 JP JP2008323256A patent/JP2009162224A/ja active Pending
Patent Citations (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS63192902A (ja) * | 1986-11-13 | 1988-08-10 | クロマロイガスタービンコーポレイション | 分散された冷却孔を有する翼及びその加工する方法とその装置 |
US4818834A (en) * | 1988-03-21 | 1989-04-04 | Raycon Corporation | Process for drilling chamfered holes |
JPH0968001A (ja) * | 1995-08-31 | 1997-03-11 | Ishikawajima Harima Heavy Ind Co Ltd | 画像処理によるガスタービンブレードへの冷却孔の形成方法 |
JPH09144504A (ja) * | 1995-11-22 | 1997-06-03 | Ishikawajima Harima Heavy Ind Co Ltd | タービン冷却翼とその加工方法 |
JPH1089005A (ja) * | 1996-09-18 | 1998-04-07 | Toshiba Corp | 高温部材冷却装置 |
US6914214B2 (en) * | 2001-10-30 | 2005-07-05 | Rolls-Royce Plc | Method of forming a shaped hole |
JP2006207586A (ja) * | 2005-01-28 | 2006-08-10 | General Electric Co <Ge> | タービン翼形部の高効率ファン冷却孔 |
JP2006242187A (ja) * | 2005-03-01 | 2006-09-14 | General Electric Co <Ge> | タービンのエーロフォイル |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2012137898A1 (ja) | 2011-04-07 | 2012-10-11 | 株式会社Ihi | タービン翼 |
US9759069B2 (en) | 2011-12-15 | 2017-09-12 | Ihi Corporation | Turbine blade |
US9278408B2 (en) | 2013-02-27 | 2016-03-08 | Honda Motor Co., Ltd. | Laser machining apparatus |
US10155288B2 (en) | 2013-02-27 | 2018-12-18 | Honda Motor Co., Ltd. | Laser machining apparatus |
JP2017205866A (ja) * | 2016-05-03 | 2017-11-24 | ゼネラル・エレクトリック・カンパニイ | 液体誘導レーザ加工および放電加工の組み合わせ |
US11065715B2 (en) | 2016-05-03 | 2021-07-20 | General Electric Company | Combined liquid guided laser and electrical discharge machining |
Also Published As
Publication number | Publication date |
---|---|
EP2075410A2 (en) | 2009-07-01 |
EP2075410A3 (en) | 2013-05-29 |
US20090169394A1 (en) | 2009-07-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP2009162224A (ja) | 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 | |
JP4815223B2 (ja) | タービン翼形部の高効率ファン冷却孔 | |
US11371386B2 (en) | Manufacturing methods for multi-lobed cooling holes | |
JP3719466B2 (ja) | 非円形開口のレーザー加工 | |
US8858175B2 (en) | Film hole trench | |
US8993923B2 (en) | System and method for manufacturing an airfoil | |
JP6001862B2 (ja) | タービン部品用の湾曲冷却通路 | |
US8969760B2 (en) | System and method for manufacturing an airfoil | |
US6554571B1 (en) | Curved turbulator configuration for airfoils and method and electrode for machining the configuration | |
JP4688758B2 (ja) | パターン冷却式タービン翼形部 | |
US5374162A (en) | Airfoil having coolable leading edge region | |
US7431561B2 (en) | Method and apparatus for cooling gas turbine rotor blades | |
US20100068032A1 (en) | Turbine Airfoil Cooling System with Diffusion Film Cooling Hole | |
US5511946A (en) | Cooled airfoil tip corner | |
JP2010216471A (ja) | フィルム冷却増強装置及びこれを組み込んだタービン翼形部 | |
JP2005351277A (ja) | ガスタービンロータブレードを冷却するための方法及び装置 | |
JP2010112374A (ja) | シュラウド冷却に関連する方法及び装置 | |
JP2008057537A (ja) | タービンエンジンで使用するノズルセグメントを製作するためのノズルシングレット及びガスタービンエンジン | |
EP2527597A2 (en) | Turbine blade with curved film cooling passages | |
US11053803B2 (en) | Airfoils and core assemblies for gas turbine engines and methods of manufacture | |
US8007237B2 (en) | Cooled airfoil component | |
EP3453831A2 (en) | Airfoil having end wall contoured pedestals | |
JP2022501539A (ja) | 冷却式翼形部および製造方法 | |
US11041395B2 (en) | Airfoils and core assemblies for gas turbine engines and methods of manufacture | |
US20190017383A1 (en) | Gas turbine disc |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
RD04 | Notification of resignation of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7424 Effective date: 20110217 |
|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20111212 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20121015 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20121023 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20130121 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20130124 |
|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20130625 |