CA2638535C - Aube de turbine avec structure de refroidissement interne - Google Patents

Aube de turbine avec structure de refroidissement interne Download PDF

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Publication number
CA2638535C
CA2638535C CA2638535A CA2638535A CA2638535C CA 2638535 C CA2638535 C CA 2638535C CA 2638535 A CA2638535 A CA 2638535A CA 2638535 A CA2638535 A CA 2638535A CA 2638535 C CA2638535 C CA 2638535C
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CA
Canada
Prior art keywords
passage
cooling
blade
trip strips
cooling structure
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
Application number
CA2638535A
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English (en)
Other versions
CA2638535A1 (fr
Inventor
Maxim Konter
Anton Sumin
Sergey Vorontsov
Alexander Khanin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
GE Vernova GmbH
Original Assignee
Alstom Technology AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of CA2638535A1 publication Critical patent/CA2638535A1/fr
Application granted granted Critical
Publication of CA2638535C publication Critical patent/CA2638535C/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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

Une aube rotative (1) pour une turbine à gaz comprend une structure de refroidissement interne avec au moins trois passages dair de refroidissement (5-7) en liaison fluidique les unes avec les autres au moyen de virages (9, 10). Une ouverture (12) procure une sortie pour le matériau dissous du noyau à retirer de laube après la coulée de la structure de refroidissement sans quil ne reste aucun résidu à lintérieur. Conformément à linvention, la structure de refroidissement comprend des bandes perturbatrices (13, 15) dans les premier et second passages (5, 6) avec un rapport indiqué de la hauteur à la distance entre les bandes perturbatrices et les bandes perturbatrices (13) dans le premier passage étant fixé à 9000 en ce qui a trait à la direction du flux dair. Dans un mode de réalisation particulier, les bandes perturbatrices (15) dans le second passage (6) sont réglées à un angle de 45°. La conception selon linvention assure un flux dair suffisant au travers des premier et second passages (5, 6).
CA2638535A 2007-08-08 2008-08-07 Aube de turbine avec structure de refroidissement interne Active CA2638535C (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP07113996A EP2025869B1 (fr) 2007-08-08 2007-08-08 Aube de turbine à gaz avec structure de refroidissement interne
EP07113996.8 2007-08-08

Publications (2)

Publication Number Publication Date
CA2638535A1 CA2638535A1 (fr) 2009-02-08
CA2638535C true CA2638535C (fr) 2015-02-24

Family

ID=38805662

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2638535A Active CA2638535C (fr) 2007-08-08 2008-08-07 Aube de turbine avec structure de refroidissement interne

Country Status (8)

Country Link
US (1) US20090041587A1 (fr)
EP (1) EP2025869B1 (fr)
AT (1) ATE491863T1 (fr)
CA (1) CA2638535C (fr)
DE (1) DE602007011256D1 (fr)
MX (1) MX2008010091A (fr)
SI (1) SI2025869T1 (fr)
TW (1) TWI374214B (fr)

Families Citing this family (22)

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US11149548B2 (en) 2013-11-13 2021-10-19 Raytheon Technologies Corporation Method of reducing manufacturing variation related to blocked cooling holes
WO2015073845A1 (fr) 2013-11-15 2015-05-21 United Technologies Corporation Procédé et système d'usinage fluidique
US10156157B2 (en) * 2015-02-13 2018-12-18 United Technologies Corporation S-shaped trip strips in internally cooled components
US10099276B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having an internal passage defined therein
US9579714B1 (en) 2015-12-17 2017-02-28 General Electric Company Method and assembly for forming components having internal passages using a lattice structure
US10099283B2 (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
US10137499B2 (en) 2015-12-17 2018-11-27 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
US9987677B2 (en) 2015-12-17 2018-06-05 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
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
US10099284B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having a catalyzed internal passage defined therein
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
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
US11154956B2 (en) 2017-02-22 2021-10-26 General Electric Company Method of repairing turbine component using ultra-thin plate
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 (ja) * 2017-11-09 2022-01-17 三菱パワー株式会社 タービン翼及びガスタービン
JP7096695B2 (ja) * 2018-04-17 2022-07-06 三菱重工業株式会社 タービン翼及びガスタービン
JP7847031B2 (ja) * 2022-05-06 2026-04-16 三菱重工業株式会社 タービン翼及びガスタービン

Family Cites Families (13)

* Cited by examiner, † Cited by third party
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 (ja) * 1998-02-26 1999-09-07 Toshiba Corp ガスタービン翼
EP0945595A3 (fr) * 1998-03-26 2001-10-10 Mitsubishi Heavy Industries, Ltd. Aube refroidie pour turbine à gaz
EP1022435B1 (fr) * 1999-01-25 2009-06-03 General Electric Company Circuit de refroidissement interne pour une aube de turbine à gaz
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

Also Published As

Publication number Publication date
MX2008010091A (es) 2009-02-27
TWI374214B (en) 2012-10-11
ATE491863T1 (de) 2011-01-15
EP2025869A1 (fr) 2009-02-18
DE602007011256D1 (de) 2011-01-27
EP2025869B1 (fr) 2010-12-15
US20090041587A1 (en) 2009-02-12
CA2638535A1 (fr) 2009-02-08
SI2025869T1 (sl) 2011-04-29
TW200928075A (en) 2009-07-01

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