JP4619135B2 - タービンブレードの冷却空気排出スロットに対する改善 - Google Patents
タービンブレードの冷却空気排出スロットに対する改善 Download PDFInfo
- Publication number
- JP4619135B2 JP4619135B2 JP2005004827A JP2005004827A JP4619135B2 JP 4619135 B2 JP4619135 B2 JP 4619135B2 JP 2005004827 A JP2005004827 A JP 2005004827A JP 2005004827 A JP2005004827 A JP 2005004827A JP 4619135 B2 JP4619135 B2 JP 4619135B2
- Authority
- JP
- Japan
- Prior art keywords
- blade
- wall
- discharge slot
- slot
- opening
- 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 claims description 36
- 230000008878 coupling Effects 0.000 claims description 30
- 238000010168 coupling process Methods 0.000 claims description 30
- 238000005859 coupling reaction Methods 0.000 claims description 30
- 210000002105 tongue Anatomy 0.000 claims description 11
- 230000000295 complement effect Effects 0.000 claims description 6
- 239000000919 ceramic Substances 0.000 description 6
- 239000007789 gas Substances 0.000 description 4
- 239000000567 combustion gas Substances 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000001627 detrimental effect Effects 0.000 description 1
- 230000003467 diminishing effect Effects 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
- B22C9/103—Multipart cores
-
- 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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
-
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/21—Manufacture essentially without removing material by casting
- F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
-
- 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
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- 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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
-
- 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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
12 基部
14 翼
14a 凹状面
14b 凸状面
16 ブレードベース
18 ブレード先端
20 前縁
22 後縁
24、52 底部プラットフォーム
26、58 底部結合ゾーン
28 キャビティ
30 排出スロット
30a 底部排出スロット
32、64 セットバック壁部
34 底壁部
36、60 末端壁部
38、62 開口部
40 底縁部
42 底肩部
50 ステータブレード
54 頂部プラットフォーム
56 頂部結合ゾーン
66 頂壁部
70 頂縁部
72 頂肩部
80 セラミックコア
82 主部
84 底部平坦舌部
86 第1の面
88 第2の面
90 第3の面
Claims (12)
- ターボ機械のタービンブレード(10、50)であって、
径方向にブレードベース(16)からブレード先端部(18)へ延び、かつ軸方向に前縁(20)から後縁(22)へ延びる翼(14)と、
底部結合ゾーン(26、52)によってブレードベース(16)に結合された少なくとも一つの底部プラットフォーム(24、52)と、
径方向にブレード先端部(18)からブレードベース(16)へ延びる少なくとも一つのキャビティ(28)、キャビティの径方向端部における少なくとも一つの空気入口開口部、および翼の後縁(22)に沿って配設された複数の排出スロット(30、30a、30b)からなる冷却回路とを有し、
前記タービンブレードが、ブレードベース(16)の付近に配置された底部排出スロット(30a)を有し、前記底部排出スロット(30a)が、
キャビティ(28)内に開口する開口部(38)が設けられた末端壁部(36)と、
セットバック壁部(32)と、
ブレードベース(16)の近傍に配置された底壁部(34)と、
セットバック壁部(32)と底壁部(34)との間に形成された底縁部(40)と、
底壁部(34)と底部結合ゾーン(26、58)との間に形成された底肩部(42)とを含み、
底部排出スロット(30a)の底縁部(40)および底部排出スロット(30a)の底肩部(42)の両方が、それぞれ実質的に丸められた形状の横断面を有し、それによって前記底部排出スロット(30a)の開口部(38)と底部結合ゾーン(26、58)との間のいかなる突出する角度をも回避することを特徴とする、ターボ機械のタービンブレード。 - 頂部結合ゾーン(56)によってブレード先端部(16)に結合された頂部プラットフォーム(54)をさらに含み、冷却回路は、ブレード先端部付近に配置された頂部排出スロット(30b)をさらに含み、かつ
キャビティ(28)内に開口する開口部(62)が設けられた末端壁部(60)と、
セットバック壁部(64)と、
ブレード先端部の近傍に配置された頂壁部(66)と、
セットバック壁部(64)と頂壁部(66)の間に形成された頂縁部(70)と、
頂壁部(66)と頂部結合ゾーン(56)との間に形成された頂肩部(72)とを有し、
頂部排出スロット(30b)の頂縁部(70)および頂部排出スロット(30b)の頂肩部(72)が、それぞれ実質的に丸められた形状の横断面を有し、それによって前記頂部排出スロット(30b)の開口部(62)と頂部結合ゾーン(70)との間のいかなる突出する角度をも回避することを特徴とする、請求項1に記載のブレード(50)。 - 縁部(40、70)および肩部(42、72)の横断面の丸められた形状が、各々軸方向に、排出スロット(30a、30b)の開口部(38、62)と翼の後縁(22)との間で出口平面(P)へと延びることを特徴とする、請求項1または2に記載のブレード。
- 縁部(40、70)および肩部(42、72)の横断面の丸められた形状が、各々排出スロット(30a、30b)の開口部(38、62)から、出口平面(P)へと増大する曲率半径を有することを特徴とする、請求項3に記載のブレード。
- 出口平面(P)において、縁部(40、70)および肩部(42、72)の横断面の丸められた形状の曲率半径は、排出スロット(30a、30b)のセットバック壁部(32、64)が、結合ゾーン(26、58、70)と一致するようにすることを特徴とする、請求項4に記載のブレード。
- ターボ機械の高圧タービンにおける可動ブレード(10)からなることを特徴とする、請求項1に記載のブレード。
- 底部排出スロット(30a)のセットバック壁部(32)が、ブレード先端(18)に向かって傾斜していることを特徴とする、請求項6に記載のブレード。
- 底部排出スロット(30a)の末端壁部(36)における開口部(38)は、本質的に、底部結合ゾーン(26)に形成されることを特徴とする、請求項6または7に記載のブレード。
- ターボ機械の高圧タービンのステータノズルブレード(50)からなることを特徴とする、請求項2に記載のブレード。
- ブレードの冷却キャビティのために空間を確保すべく構成された主部(82)を含み、前記主部(82)には、ブレードの冷却回路の排出スロットのために対応する数の空間を確保すべく構成された複数の終端平坦舌部(84)が設けられている、請求項1から9のいずれか一項に記載のブレードを得るためのコアであって、コアの主部(82)が、底部排出スロットのために確保された空間に底部平坦舌部(84a)をさらに含み、前記平坦舌部の形状は前記底部排出スロットに対して相補的であることを特徴とするコア。
- 請求項6から8のいずれか一項に記載の、複数の可動ブレード(10)を有することを特徴とする、ターボ機械の高圧タービン。
- 請求項9に記載の複数のブレードを有することを特徴とする、ターボ機械ノズル。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0400289A FR2864990B1 (fr) | 2004-01-14 | 2004-01-14 | Perfectionnements apportes aux fentes d'evacuation de l'air de refroidissement d'aubes de turbine haute-pression |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2005201273A JP2005201273A (ja) | 2005-07-28 |
JP2005201273A5 JP2005201273A5 (ja) | 2007-12-27 |
JP4619135B2 true JP4619135B2 (ja) | 2011-01-26 |
Family
ID=34610765
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2005004827A Active JP4619135B2 (ja) | 2004-01-14 | 2005-01-12 | タービンブレードの冷却空気排出スロットに対する改善 |
Country Status (9)
Country | Link |
---|---|
US (1) | US7278827B2 (ja) |
EP (1) | EP1555390B1 (ja) |
JP (1) | JP4619135B2 (ja) |
CA (1) | CA2493094C (ja) |
DE (1) | DE602004003331T2 (ja) |
ES (1) | ES2276254T3 (ja) |
FR (1) | FR2864990B1 (ja) |
RU (1) | RU2294438C2 (ja) |
UA (1) | UA84846C2 (ja) |
Families Citing this family (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7575414B2 (en) * | 2005-04-01 | 2009-08-18 | General Electric Company | Turbine nozzle with trailing edge convection and film cooling |
US7503749B2 (en) * | 2005-04-01 | 2009-03-17 | General Electric Company | Turbine nozzle with trailing edge convection and film cooling |
US7371048B2 (en) * | 2005-05-27 | 2008-05-13 | United Technologies Corporation | Turbine blade trailing edge construction |
FR2899269A1 (fr) * | 2006-03-30 | 2007-10-05 | Snecma Sa | Aube de redresseur optimisee, secteur de redresseurs, etage de compression, compresseur et turbomachine comportant une telle aube |
FR2899270A1 (fr) * | 2006-03-30 | 2007-10-05 | Snecma Sa | Aube de redresseur a amenagement de forme localise, secteur de redresseurs, etage de compression, compresseur et turbomachine comportant une telle aube |
FR2924156B1 (fr) * | 2007-11-26 | 2014-02-14 | Snecma | Aube de turbomachine |
DE102008035271B4 (de) | 2008-07-29 | 2023-06-29 | Genady Maslov | Verfahren und Einrichtung zur Verarbeitung von Abgasen (Dieselmotor) |
DE202008010121U1 (de) | 2008-07-29 | 2009-05-14 | Koltun, Mykhaylo | Einrichtung zur Durchführung des Abgasreinigungsverfahrens (Dieselmotor) |
DE202008010119U1 (de) | 2008-07-29 | 2009-05-07 | Koltun, Mykhaylo | Einrichtung zur Reinigung von Abgasen der Turbostrahltriebwerke |
CH699601A1 (de) * | 2008-09-30 | 2010-03-31 | Alstom Technology Ltd | Schaufel für eine gasturbine. |
US8113784B2 (en) * | 2009-03-20 | 2012-02-14 | Hamilton Sundstrand Corporation | Coolable airfoil attachment section |
US8632297B2 (en) * | 2010-09-29 | 2014-01-21 | General Electric Company | Turbine airfoil and method for cooling a turbine airfoil |
EP2639004B1 (de) * | 2012-03-15 | 2016-05-11 | MTU Aero Engines GmbH | Schaufelkranzsegment mit Ringraumbegrenzungsfläche mit einem welligen Höhenprofil sowie Verfahren zur Herstellung desselben |
US9175569B2 (en) * | 2012-03-30 | 2015-11-03 | General Electric Company | Turbine airfoil trailing edge cooling slots |
US20130302177A1 (en) * | 2012-05-08 | 2013-11-14 | Robert Frederick Bergholz, JR. | Turbine airfoil trailing edge bifurcated cooling holes |
US20130302176A1 (en) * | 2012-05-08 | 2013-11-14 | Robert Frederick Bergholz, JR. | Turbine airfoil trailing edge cooling slot |
US20130302179A1 (en) * | 2012-05-09 | 2013-11-14 | Robert Frederick Bergholz, JR. | Turbine airfoil trailing edge cooling hole plug and slot |
EP2941543B1 (en) | 2013-03-13 | 2017-03-22 | Rolls-Royce Corporation | Trenched cooling hole arrangement for a ceramic matrix composite vane |
DE102013213416B4 (de) * | 2013-07-09 | 2017-11-09 | MTU Aero Engines AG | Schaufel für eine Gasturbomaschine |
US9995166B2 (en) * | 2014-11-21 | 2018-06-12 | General Electric Company | Turbomachine including a vane and method of assembling such turbomachine |
US20160208626A1 (en) * | 2015-01-19 | 2016-07-21 | United Technologies Corporation | Integrally bladed rotor with pressure side thickness on blade trailing edge |
US10196904B2 (en) | 2016-01-24 | 2019-02-05 | Rolls-Royce North American Technologies Inc. | Turbine endwall and tip cooling for dual wall airfoils |
US10240462B2 (en) | 2016-01-29 | 2019-03-26 | General Electric Company | End wall contour for an axial flow turbine stage |
EP3954882B1 (en) * | 2016-03-30 | 2023-05-03 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Variable geometry turbocharger |
FR3108364B1 (fr) | 2020-03-18 | 2022-03-11 | Safran Aircraft Engines | Aube de turbine comportant des nervures entre des sorties de refroidissement avec des orifices de refroidissement |
FR3108363B1 (fr) | 2020-03-18 | 2022-03-11 | Safran Aircraft Engines | Aube de turbine comportant trois types d’orifices de refroidissement du bord de fuite |
DE102020207646A1 (de) | 2020-06-22 | 2021-12-23 | Siemens Aktiengesellschaft | Turbinenschaufel und Verfahren zum Bearbeiten einer solchen |
CN112343666B (zh) * | 2020-12-14 | 2021-08-24 | 北京航空航天大学 | 一种应用于涡轮叶片尾缘半劈缝的波纹型肋导流结构 |
CN113236370B (zh) * | 2021-05-25 | 2023-04-25 | 杭州汽轮动力集团有限公司 | 一种燃气轮机涡轮高压动叶片的冷却结构 |
US20230151737A1 (en) * | 2021-11-18 | 2023-05-18 | Raytheon Technologies Corporation | Airfoil with axial cooling slot having diverging ramp |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2001098903A (ja) * | 1998-08-05 | 2001-04-10 | Soc Natl Etud Constr Mot Aviat <Snecma> | 後縁を改良したタービンの冷却羽根 |
JP2003193804A (ja) * | 2001-12-10 | 2003-07-09 | Snecma Moteurs | 高圧タービンブレードの後縁の高温状態の改良 |
JP2003201805A (ja) * | 2001-12-12 | 2003-07-18 | General Electric Co <Ge> | ガスタービンエンジンのタービンノズル用の翼形部及びその製作方法 |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP3316418B2 (ja) * | 1997-06-12 | 2002-08-19 | 三菱重工業株式会社 | ガスタービン冷却動翼 |
US6062817A (en) * | 1998-11-06 | 2000-05-16 | General Electric Company | Apparatus and methods for cooling slot step elimination |
DE19860788A1 (de) * | 1998-12-30 | 2000-07-06 | Abb Alstom Power Ch Ag | Kühlbare Schaufel für eine Gasturbine |
CA2334071C (en) * | 2000-02-23 | 2005-05-24 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade |
FR2835015B1 (fr) * | 2002-01-23 | 2005-02-18 | Snecma Moteurs | Aube mobile de turbine haute pression munie d'un bord de fuite au comportement thermique ameliore |
-
2004
- 2004-01-14 FR FR0400289A patent/FR2864990B1/fr not_active Expired - Fee Related
- 2004-12-20 EP EP04293046A patent/EP1555390B1/fr active Active
- 2004-12-20 ES ES04293046T patent/ES2276254T3/es active Active
- 2004-12-20 DE DE602004003331T patent/DE602004003331T2/de active Active
-
2005
- 2005-01-11 US US11/032,012 patent/US7278827B2/en active Active
- 2005-01-12 JP JP2005004827A patent/JP4619135B2/ja active Active
- 2005-01-13 RU RU2005100467/06A patent/RU2294438C2/ru active
- 2005-01-13 UA UAA200500303A patent/UA84846C2/ru unknown
- 2005-01-14 CA CA2493094A patent/CA2493094C/fr active Active
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2001098903A (ja) * | 1998-08-05 | 2001-04-10 | Soc Natl Etud Constr Mot Aviat <Snecma> | 後縁を改良したタービンの冷却羽根 |
JP2003193804A (ja) * | 2001-12-10 | 2003-07-09 | Snecma Moteurs | 高圧タービンブレードの後縁の高温状態の改良 |
JP2003201805A (ja) * | 2001-12-12 | 2003-07-18 | General Electric Co <Ge> | ガスタービンエンジンのタービンノズル用の翼形部及びその製作方法 |
Also Published As
Publication number | Publication date |
---|---|
EP1555390A1 (fr) | 2005-07-20 |
FR2864990B1 (fr) | 2008-02-22 |
ES2276254T3 (es) | 2007-06-16 |
DE602004003331T2 (de) | 2007-06-21 |
US20050249593A1 (en) | 2005-11-10 |
RU2294438C2 (ru) | 2007-02-27 |
FR2864990A1 (fr) | 2005-07-15 |
CA2493094A1 (fr) | 2006-07-14 |
RU2005100467A (ru) | 2006-06-20 |
CA2493094C (fr) | 2011-10-11 |
EP1555390B1 (fr) | 2006-11-22 |
JP2005201273A (ja) | 2005-07-28 |
UA84846C2 (ru) | 2008-12-10 |
US7278827B2 (en) | 2007-10-09 |
DE602004003331D1 (de) | 2007-01-04 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4619135B2 (ja) | タービンブレードの冷却空気排出スロットに対する改善 | |
US7270515B2 (en) | Turbine airfoil trailing edge cooling system with segmented impingement ribs | |
JP4663479B2 (ja) | ガスタービンロータブレード | |
US7413407B2 (en) | Turbine blade cooling system with bifurcated mid-chord cooling chamber | |
US7686580B2 (en) | Turbine element | |
US7766606B2 (en) | Turbine airfoil cooling system with platform cooling channels with diffusion slots | |
JP4879267B2 (ja) | ガスタービンにおける冷却形タービン翼とそのタービン翼の利用 | |
US6602052B2 (en) | Airfoil tip squealer cooling construction | |
US7927072B2 (en) | Hollow rotor blade for the turbine of a gas turbine engine | |
US7351035B2 (en) | Hollow rotor blade for the turbine of a gas turbine engine, the blade being fitted with a “bathtub” | |
US11389860B2 (en) | Hollow turbine blade with reduced cooling air extraction | |
US7549843B2 (en) | Turbine airfoil cooling system with axial flowing serpentine cooling chambers | |
US20150132139A1 (en) | Foundry core assembly for manufacturing a turbomachine blade, associated method of manufacturing a blade and associated blade | |
US9631499B2 (en) | Turbine airfoil cooling system for bow vane | |
EP2107215A1 (en) | Gas turbine airfoil | |
US20170292386A1 (en) | Wrapped serpentine passages for turbine blade cooling | |
JPS58172407A (ja) | ガスタ−ビン機構用の軸流タ−ビン翼 | |
US6599092B1 (en) | Methods and apparatus for cooling gas turbine nozzles | |
KR20060044734A (ko) | 냉각식 터빈 에어포일 | |
JP2003214108A (ja) | 改善された温度特性を有する後縁を備えた高圧タービンのための動翼 | |
US7137784B2 (en) | Thermally loaded component | |
US6830431B2 (en) | High-temperature behavior of the trailing edge of a high pressure turbine blade | |
US20150184518A1 (en) | Turbine airfoil cooling system with nonlinear trailing edge exit slots | |
CN106715833A (zh) | 在冷却空间之间具有内部连接肋的被冷却的涡轮叶片、肋具有用于减小热应力的预定断裂点 | |
EP3533532A1 (en) | A core for an investment casting process |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20071114 |
|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20071114 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20100413 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20100712 |
|
TRDD | Decision of grant or rejection written | ||
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20101005 |
|
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20101026 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20131105 Year of fee payment: 3 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 4619135 Country of ref document: JP Free format text: JAPANESE INTERMEDIATE CODE: R150 Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |