SI2025869T1 - Gas turbine blade with internal cooling structure - Google Patents
Gas turbine blade with internal cooling structureInfo
- Publication number
- SI2025869T1 SI2025869T1 SI200730541T SI200730541T SI2025869T1 SI 2025869 T1 SI2025869 T1 SI 2025869T1 SI 200730541 T SI200730541 T SI 200730541T SI 200730541 T SI200730541 T SI 200730541T SI 2025869 T1 SI2025869 T1 SI 2025869T1
- Authority
- SI
- Slovenia
- Prior art keywords
- cooling structure
- trip strips
- gas turbine
- passage
- internal cooling
- Prior art date
Links
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
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- 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
- F05D2250/00—Geometry
- F05D2250/30—Arrangement of components
- F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
- F05D2250/313—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being perpendicular to each other
-
- 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
-
- 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
- F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
- F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A gas turbine rotating blade (1) comprises an internal cooling structure having at least three cooling air passages (5-7) in fluid connection with one another by means of turns (9, 10). An opening (12) provides an outlet for dissolved core material to be removed from the blade following casting of the cooling structure without any residue remaining within. According to the invention, the cooling structure comprises trip strips (13, 15) in the first and second passage (5, 6) with specified ratio of height to distance between trip strips and the trip strips (13) in the first passage being arranged at 90° with respect to the direction of airflow. In a particular embodiment, the trip strips (15) in the second passage (6) are arranged at angle of 45°. The design according to the invention assures sufficient airflow through first and second air passages (5, 6).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP07113996A EP2025869B1 (en) | 2007-08-08 | 2007-08-08 | Gas turbine blade with internal cooling structure |
Publications (1)
Publication Number | Publication Date |
---|---|
SI2025869T1 true SI2025869T1 (en) | 2011-04-29 |
Family
ID=38805662
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
SI200730541T SI2025869T1 (en) | 2007-08-08 | 2007-08-08 | Gas turbine blade with internal cooling structure |
Country Status (8)
Country | Link |
---|---|
US (1) | US20090041587A1 (en) |
EP (1) | EP2025869B1 (en) |
AT (1) | ATE491863T1 (en) |
CA (1) | CA2638535C (en) |
DE (1) | DE602007011256D1 (en) |
MX (1) | MX2008010091A (en) |
SI (1) | SI2025869T1 (en) |
TW (1) | TWI374214B (en) |
Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11149548B2 (en) | 2013-11-13 | 2021-10-19 | Raytheon Technologies Corporation | Method of reducing manufacturing variation related to blocked cooling holes |
US10107110B2 (en) | 2013-11-15 | 2018-10-23 | United Technologies Corporation | Fluidic machining method and system |
US10156157B2 (en) * | 2015-02-13 | 2018-12-18 | United Technologies Corporation | S-shaped trip strips in internally cooled components |
US10137499B2 (en) | 2015-12-17 | 2018-11-27 | General Electric Company | Method and assembly for forming components having an internal passage defined therein |
US10099283B2 (en) | 2015-12-17 | 2018-10-16 | General Electric Company | Method and assembly for forming components having an internal passage defined therein |
US10150158B2 (en) | 2015-12-17 | 2018-12-11 | General Electric Company | Method and assembly for forming components having internal passages using a jacketed core |
US10099276B2 (en) | 2015-12-17 | 2018-10-16 | General Electric Company | Method and assembly for forming components having an internal passage defined therein |
US10118217B2 (en) | 2015-12-17 | 2018-11-06 | General Electric Company | Method and assembly for forming components having internal passages using a jacketed core |
US9579714B1 (en) | 2015-12-17 | 2017-02-28 | General Electric Company | Method and assembly for forming components having internal passages using a lattice structure |
US10099284B2 (en) | 2015-12-17 | 2018-10-16 | General Electric Company | Method and assembly for forming components having a catalyzed internal passage defined therein |
US10046389B2 (en) | 2015-12-17 | 2018-08-14 | General Electric Company | Method and assembly for forming components having internal passages using a jacketed core |
US9968991B2 (en) | 2015-12-17 | 2018-05-15 | General Electric Company | Method and assembly for forming components having internal passages using a lattice structure |
US9987677B2 (en) | 2015-12-17 | 2018-06-05 | General Electric Company | Method and assembly for forming components having internal passages using a jacketed core |
US10335853B2 (en) | 2016-04-27 | 2019-07-02 | General Electric Company | Method and assembly for forming components using a jacketed core |
US10286450B2 (en) | 2016-04-27 | 2019-05-14 | General Electric Company | Method and assembly for forming components using a jacketed core |
US11154956B2 (en) | 2017-02-22 | 2021-10-26 | General Electric Company | Method of repairing turbine component using ultra-thin plate |
US10702958B2 (en) | 2017-02-22 | 2020-07-07 | General Electric Company | Method of manufacturing turbine airfoil and tip component thereof using ceramic core with witness feature |
US10717130B2 (en) * | 2017-02-22 | 2020-07-21 | General Electric Company | Method of manufacturing turbine airfoil and tip component thereof |
US10612394B2 (en) * | 2017-07-21 | 2020-04-07 | United Technologies Corporation | Airfoil having serpentine core resupply flow control |
JP6996947B2 (en) | 2017-11-09 | 2022-01-17 | 三菱パワー株式会社 | Turbine blades and gas turbines |
JP7096695B2 (en) * | 2018-04-17 | 2022-07-06 | 三菱重工業株式会社 | Turbine blades and gas turbines |
JP2023165485A (en) * | 2022-05-06 | 2023-11-16 | 三菱重工業株式会社 | Turbine blade and gas turbine |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4278400A (en) * | 1978-09-05 | 1981-07-14 | United Technologies Corporation | Coolable rotor blade |
US4775296A (en) * | 1981-12-28 | 1988-10-04 | United Technologies Corporation | Coolable airfoil for a rotary machine |
US5232343A (en) * | 1984-05-24 | 1993-08-03 | General Electric Company | Turbine blade |
US5700132A (en) * | 1991-12-17 | 1997-12-23 | General Electric Company | Turbine blade having opposing wall turbulators |
US5403159A (en) * | 1992-11-30 | 1995-04-04 | United Technoligies Corporation | Coolable airfoil structure |
US6139269A (en) * | 1997-12-17 | 2000-10-31 | United Technologies Corporation | Turbine blade with multi-pass cooling and cooling air addition |
JPH11241602A (en) * | 1998-02-26 | 1999-09-07 | Toshiba Corp | Gas turbine blade |
EP0945595A3 (en) * | 1998-03-26 | 2001-10-10 | Mitsubishi Heavy Industries, Ltd. | Gas turbine cooled blade |
EP1022435B1 (en) * | 1999-01-25 | 2009-06-03 | General Electric Company | Internal cooling circuit for a gas turbine bucket |
US6634858B2 (en) * | 2001-06-11 | 2003-10-21 | Alstom (Switzerland) Ltd | Gas turbine airfoil |
US6884036B2 (en) * | 2003-04-15 | 2005-04-26 | General Electric Company | Complementary cooled turbine nozzle |
US7097419B2 (en) * | 2004-07-26 | 2006-08-29 | General Electric Company | Common tip chamber blade |
US7431561B2 (en) * | 2006-02-16 | 2008-10-07 | General Electric Company | Method and apparatus for cooling gas turbine rotor blades |
-
2007
- 2007-08-08 DE DE602007011256T patent/DE602007011256D1/en active Active
- 2007-08-08 EP EP07113996A patent/EP2025869B1/en active Active
- 2007-08-08 SI SI200730541T patent/SI2025869T1/en unknown
- 2007-08-08 AT AT07113996T patent/ATE491863T1/en not_active IP Right Cessation
-
2008
- 2008-08-04 US US12/185,593 patent/US20090041587A1/en not_active Abandoned
- 2008-08-06 MX MX2008010091A patent/MX2008010091A/en active IP Right Grant
- 2008-08-06 TW TW097129913A patent/TWI374214B/en not_active IP Right Cessation
- 2008-08-07 CA CA2638535A patent/CA2638535C/en active Active
Also Published As
Publication number | Publication date |
---|---|
CA2638535A1 (en) | 2009-02-08 |
EP2025869B1 (en) | 2010-12-15 |
CA2638535C (en) | 2015-02-24 |
TWI374214B (en) | 2012-10-11 |
TW200928075A (en) | 2009-07-01 |
US20090041587A1 (en) | 2009-02-12 |
EP2025869A1 (en) | 2009-02-18 |
ATE491863T1 (en) | 2011-01-15 |
DE602007011256D1 (en) | 2011-01-27 |
MX2008010091A (en) | 2009-02-27 |
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