JP5600449B2 - 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 - Google Patents
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 Download PDFInfo
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- JP5600449B2 JP5600449B2 JP2010049993A JP2010049993A JP5600449B2 JP 5600449 B2 JP5600449 B2 JP 5600449B2 JP 2010049993 A JP2010049993 A JP 2010049993A JP 2010049993 A JP2010049993 A JP 2010049993A JP 5600449 B2 JP5600449 B2 JP 5600449B2
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- film cooling
- airfoil
- insert
- holes
- turbine
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- 238000001816 cooling Methods 0.000 title claims description 242
- 239000000843 powder Substances 0.000 claims description 27
- 239000002245 particle Substances 0.000 claims description 6
- 239000000567 combustion gas Substances 0.000 description 19
- 229910052751 metal Inorganic materials 0.000 description 19
- 239000002184 metal Substances 0.000 description 19
- 238000012546 transfer Methods 0.000 description 17
- 239000012809 cooling fluid Substances 0.000 description 14
- 238000009792 diffusion process Methods 0.000 description 14
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 8
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- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 4
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 4
- 229910052782 aluminium Inorganic materials 0.000 description 4
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 4
- 238000002485 combustion reaction Methods 0.000 description 4
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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
- 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
- F05D2250/20—Three-dimensional
- F05D2250/25—Three-dimensional helical
-
- 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
- F05D2260/221—Improvement of heat transfer
-
- 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
-
- 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
Description
12 翼形部
14 プラットフォーム
16 ダブテール
17 凹状正圧側面
18 側壁
19 凸状負圧側面
20 前縁
21 翼形部表面
22 後縁
24 冷却回路
26 燃焼ガス
28 冷却流体
30 フィルム冷却孔
31 入口
32 縁部冷却孔
33 出口
34 第1の孔
36 第2の孔
38 内寄り表面
40 外寄り表面
42 第1の入口
44 第1の出口
46 第2の入口
48 第2の出口
50 中空静翼翼形部
52 外側燃焼ライナ
54 タービンシュラウド
56 タービン翼形部表面
100 フィルム冷却インサート
102 焼結粉末成形体
110 本体
112 近位端
114 遠位端
116 通路
117 テーパ導入部
118 ケーシング
119 外側表面
120 壁
121 内側表面
122 貫通孔通路
124 通路手段
126 リブ
128 横方向突出部
Claims (10)
- タービン翼形部(12)であって、
翼形部冷却回路(24)と翼形部表面(21)との間に延びるフィルム冷却孔を有する翼形部側壁(18)と、
翼形部表面(21)に近接して配置するよう構成された近位端(112)と遠位端(114)とを有する本体(110)を含み、フィルム冷却孔内に配置されたインサートと
を備えており、本体(110)が、フィルム冷却孔内に配置されたときに、遠位端(114)と近位端(112)との間に延びる通路(116)を画成するように構成されている、タービン翼形部(12)。 - 翼形部が、翼弦方向に対向する前縁及び後縁(20、22)で互いに接合され且つ第1の端部から第2の端部に翼長にわたって長手方向に延びた正圧側壁(17)と対向する負圧側壁(19)とを有するタービン動翼(10)又は静翼を備え、冷却回路(24)が、正圧側壁(17)又は負圧側壁(19)内に配置され、フィルム冷却孔が正圧側壁(17)、負圧側壁(19)、後縁(22)又は前縁(20)のうちのいずれかを貫通する、請求項1記載のタービン翼形部(12)。
- インサートが複数の通路を含む、請求項1記載のタービン翼形部(12)。
- インサートが、相互接続粒子の網状構造と相互接続の間隙スペースの対応する網状構造とを備えた多孔質構造を有する焼結粉末成形体を含み、相互接続の間隙スペースが複数の通路(116)を有する、請求項3記載のタービン翼形部(12)。
- 通路(116)が中心軸線を有し、軸線が非線形である、請求項1記載のタービン翼形部(12)。
- インサートが、長手方向に延びるリブ(126)を備え、通路(116)がリブ(126)によって画成される、請求項3記載のタービン翼形部(12)。
- 本体(110)が、内側及び外側表面(121、119)を有する略管状の構造体を含む、請求項1記載のタービン翼形部(12)。
- タービン翼形部(12)のフィルム冷却孔用インサートであって、該インサートが、フィルム冷却孔内に配置するよう構成された本体(110)を備え、本体(110)が、翼形部表面(21)に近接して配置されるよう構成された近位端(112)と、遠位端(114)とを有し、本体(110)がまた、フィルム冷却孔内に配置されたときに遠位端(114)と近位端(112)との間に延びる通路(116)を画成するように構成されるインサート。
- 本体(110)が、複数の通路(116)を含む、請求項8記載のインサート。
- 本体(110)が、相互接続粒子の網状構造と相互接続の間隙スペースの対応する網状構造とを備えた多孔質構造を有する焼結粉末成形体を含み、相互接続の間隙スペースが複数の通路(116)を有する、請求項9記載のインサート。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/406,277 US8052378B2 (en) | 2009-03-18 | 2009-03-18 | Film-cooling augmentation device and turbine airfoil incorporating the same |
US12/406,277 | 2009-03-18 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2010216471A JP2010216471A (ja) | 2010-09-30 |
JP5600449B2 true JP5600449B2 (ja) | 2014-10-01 |
Family
ID=42167367
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2010049993A Active JP5600449B2 (ja) | 2009-03-18 | 2010-03-08 | 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 |
Country Status (4)
Country | Link |
---|---|
US (1) | US8052378B2 (ja) |
EP (1) | EP2230384B1 (ja) |
JP (1) | JP5600449B2 (ja) |
CN (1) | CN101852099B (ja) |
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US10927680B2 (en) * | 2017-05-31 | 2021-02-23 | General Electric Company | Adaptive cover for cooling pathway by additive manufacture |
US10830072B2 (en) * | 2017-07-24 | 2020-11-10 | General Electric Company | Turbomachine airfoil |
KR102000835B1 (ko) * | 2017-09-27 | 2019-07-16 | 두산중공업 주식회사 | 가스 터빈 블레이드 |
US10626734B2 (en) | 2017-10-03 | 2020-04-21 | United Technologies Corporation | Airfoil having internal hybrid cooling cavities |
US10626733B2 (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 |
US10633980B2 (en) | 2017-10-03 | 2020-04-28 | United Technologies Coproration | Airfoil having internal hybrid cooling cavities |
US10717101B2 (en) | 2018-02-16 | 2020-07-21 | General Electric Company | Method for making cooling assembly for a turbomachine part |
US10551327B2 (en) * | 2018-04-11 | 2020-02-04 | General Electric Company | Cooling hole inspection system |
US11391161B2 (en) * | 2018-07-19 | 2022-07-19 | General Electric Company | Component for a turbine engine with a cooling hole |
US10774653B2 (en) | 2018-12-11 | 2020-09-15 | Raytheon Technologies Corporation | Composite gas turbine engine component with lattice structure |
KR102162970B1 (ko) * | 2019-02-21 | 2020-10-07 | 두산중공업 주식회사 | 터빈용 에어포일, 이를 포함하는 터빈 |
US11486578B2 (en) | 2020-05-26 | 2022-11-01 | Raytheon Technologies Corporation | Multi-walled structure for a gas turbine engine |
US11603765B1 (en) * | 2021-07-16 | 2023-03-14 | Raytheon Technologies Corporation | Airfoil assembly with fiber-reinforced composite rings and toothed exit slot |
US11859512B2 (en) * | 2022-03-31 | 2024-01-02 | General Electric Company | Cooling passage exit opening cross-sectional area reduction for turbine system component |
Family Cites Families (40)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4545197A (en) * | 1978-10-26 | 1985-10-08 | Rice Ivan G | Process for directing a combustion gas stream onto rotatable blades of a gas turbine |
US4835958A (en) * | 1978-10-26 | 1989-06-06 | Rice Ivan G | Process for directing a combustion gas stream onto rotatable blades of a gas turbine |
US5405242A (en) * | 1990-07-09 | 1995-04-11 | United Technologies Corporation | Cooled vane |
US5660524A (en) | 1992-07-13 | 1997-08-26 | General Electric Company | Airfoil blade having a serpentine cooling circuit and impingement cooling |
JPH07279612A (ja) * | 1994-04-14 | 1995-10-27 | Mitsubishi Heavy Ind Ltd | 重質油焚き用ガスタービン冷却翼 |
US5472316A (en) * | 1994-09-19 | 1995-12-05 | General Electric Company | Enhanced cooling apparatus for gas turbine engine airfoils |
US5771577A (en) * | 1996-05-17 | 1998-06-30 | General Electric Company | Method for making a fluid cooled article with protective coating |
DE59808819D1 (de) * | 1998-05-20 | 2003-07-31 | Alstom Switzerland Ltd | Gestaffelte Anordnung von Filmkühlungsbohrungen |
US6210488B1 (en) * | 1998-12-30 | 2001-04-03 | General Electric Company | Method of removing a thermal barrier coating |
US6406260B1 (en) * | 1999-10-22 | 2002-06-18 | Pratt & Whitney Canada Corp. | Heat transfer promotion structure for internally convectively cooled airfoils |
US6283708B1 (en) * | 1999-12-03 | 2001-09-04 | United Technologies Corporation | Coolable vane or blade for a turbomachine |
US6270317B1 (en) | 1999-12-18 | 2001-08-07 | General Electric Company | Turbine nozzle with sloped film cooling |
US6506013B1 (en) | 2000-04-28 | 2003-01-14 | General Electric Company | Film cooling for a closed loop cooled airfoil |
US6402471B1 (en) * | 2000-11-03 | 2002-06-11 | General Electric Company | Turbine blade for gas turbine engine and method of cooling same |
US20060018854A1 (en) * | 2002-10-02 | 2006-01-26 | Christophe Dumousseaux | Cosmetic compositions |
US7014424B2 (en) * | 2003-04-08 | 2006-03-21 | United Technologies Corporation | Turbine element |
US7008186B2 (en) * | 2003-09-17 | 2006-03-07 | General Electric Company | Teardrop film cooled blade |
US7051532B2 (en) | 2003-10-17 | 2006-05-30 | General Electric Company | Methods and apparatus for film cooling gas turbine engine combustors |
US6966756B2 (en) | 2004-01-09 | 2005-11-22 | General Electric Company | Turbine bucket cooling passages and internal core for producing the passages |
US7232290B2 (en) * | 2004-06-17 | 2007-06-19 | United Technologies Corporation | Drillable super blades |
US7278826B2 (en) * | 2004-08-18 | 2007-10-09 | Pratt & Whitney Canada Corp. | Airfoil cooling passage trailing edge flow restriction |
US7300252B2 (en) | 2004-10-04 | 2007-11-27 | Alstom Technology Ltd | Gas turbine airfoil leading edge cooling construction |
US7186085B2 (en) * | 2004-11-18 | 2007-03-06 | General Electric Company | Multiform film cooling holes |
US7316539B2 (en) * | 2005-04-07 | 2008-01-08 | Siemens Power Generation, Inc. | Vane assembly with metal trailing edge segment |
US7241107B2 (en) * | 2005-05-19 | 2007-07-10 | Spanks Jr William A | Gas turbine airfoil with adjustable cooling air flow passages |
US7413405B2 (en) * | 2005-06-14 | 2008-08-19 | General Electric Company | Bipedal damper turbine blade |
GB2429515B (en) * | 2005-08-11 | 2008-06-25 | Rolls Royce Plc | Cooling method and apparatus |
US7249934B2 (en) | 2005-08-31 | 2007-07-31 | General Electric Company | Pattern cooled turbine airfoil |
US7296973B2 (en) | 2005-12-05 | 2007-11-20 | General Electric Company | Parallel serpentine cooled blade |
US7413403B2 (en) * | 2005-12-22 | 2008-08-19 | United Technologies Corporation | Turbine blade tip cooling |
US7513743B2 (en) * | 2006-05-02 | 2009-04-07 | Siemens Energy, Inc. | Turbine blade with wavy squealer tip rail |
US7704047B2 (en) * | 2006-11-21 | 2010-04-27 | Siemens Energy, Inc. | Cooling of turbine blade suction tip rail |
US7866947B2 (en) * | 2007-01-03 | 2011-01-11 | United Technologies Corporation | Turbine blade trip strip orientation |
US7780415B2 (en) * | 2007-02-15 | 2010-08-24 | Siemens Energy, Inc. | Turbine blade having a convergent cavity cooling system for a trailing edge |
US7887300B2 (en) * | 2007-02-27 | 2011-02-15 | Siemens Energy, Inc. | CMC airfoil with thin trailing edge |
US7967567B2 (en) * | 2007-03-27 | 2011-06-28 | Siemens Energy, Inc. | Multi-pass cooling for turbine airfoils |
US7785070B2 (en) * | 2007-03-27 | 2010-08-31 | Siemens Energy, Inc. | Wavy flow cooling concept for turbine airfoils |
US7736124B2 (en) * | 2007-04-10 | 2010-06-15 | General Electric Company | Damper configured turbine blade |
JP2009162119A (ja) * | 2008-01-08 | 2009-07-23 | Ihi Corp | タービン翼の冷却構造 |
US20100239409A1 (en) * | 2009-03-18 | 2010-09-23 | General Electric Company | Method of Using and Reconstructing a Film-Cooling Augmentation Device for a Turbine Airfoil |
-
2009
- 2009-03-18 US US12/406,277 patent/US8052378B2/en active Active
-
2010
- 2010-03-08 JP JP2010049993A patent/JP5600449B2/ja active Active
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11708762B2 (en) | 2019-06-07 | 2023-07-25 | Ihi Corporation | Film cooling structure and turbine blade for gas turbine engine |
US11732591B2 (en) | 2019-06-07 | 2023-08-22 | Ihi Corporation | Film cooling structure and turbine blade for gas turbine engine |
Also Published As
Publication number | Publication date |
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CN101852099B (zh) | 2013-08-28 |
US20100239412A1 (en) | 2010-09-23 |
CN101852099A (zh) | 2010-10-06 |
EP2230384A2 (en) | 2010-09-22 |
JP2010216471A (ja) | 2010-09-30 |
EP2230384A3 (en) | 2012-03-21 |
EP2230384B1 (en) | 2015-07-01 |
US8052378B2 (en) | 2011-11-08 |
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