DE102012100266B4 - Gekrümmte Kühlkanäle für eine Turbinenkomponente - Google Patents

Gekrümmte Kühlkanäle für eine Turbinenkomponente Download PDF

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Publication number
DE102012100266B4
DE102012100266B4 DE102012100266.5A DE102012100266A DE102012100266B4 DE 102012100266 B4 DE102012100266 B4 DE 102012100266B4 DE 102012100266 A DE102012100266 A DE 102012100266A DE 102012100266 B4 DE102012100266 B4 DE 102012100266B4
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Germany
Prior art keywords
airfoil
cooling
cooling passage
curved
curved cooling
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
DE102012100266.5A
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German (de)
English (en)
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DE102012100266A1 (de
Inventor
Benjamin Lacy
Victor John Morgan
Brian P. Arness
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
General Electric Technology GmbH
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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Publication of DE102012100266A1 publication Critical patent/DE102012100266A1/de
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Publication of DE102012100266B4 publication Critical patent/DE102012100266B4/de
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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
    • 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
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
DE102012100266.5A 2011-01-14 2012-01-12 Gekrümmte Kühlkanäle für eine Turbinenkomponente Active DE102012100266B4 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13/006,914 US8753083B2 (en) 2011-01-14 2011-01-14 Curved cooling passages for a turbine component
US13/006,914 2011-01-14

Publications (2)

Publication Number Publication Date
DE102012100266A1 DE102012100266A1 (de) 2012-07-19
DE102012100266B4 true DE102012100266B4 (de) 2025-03-20

Family

ID=46397768

Family Applications (1)

Application Number Title Priority Date Filing Date
DE102012100266.5A Active DE102012100266B4 (de) 2011-01-14 2012-01-12 Gekrümmte Kühlkanäle für eine Turbinenkomponente

Country Status (5)

Country Link
US (1) US8753083B2 (enExample)
JP (1) JP6001862B2 (enExample)
CN (1) CN102606221B (enExample)
DE (1) DE102012100266B4 (enExample)
FR (1) FR2970502B1 (enExample)

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US20160090843A1 (en) * 2014-09-30 2016-03-31 General Electric Company Turbine components with stepped apertures
US10190420B2 (en) * 2015-02-10 2019-01-29 United Technologies Corporation Flared crossovers for airfoils
US10502066B2 (en) * 2015-05-08 2019-12-10 United Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US10099283B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having an internal passage defined therein
US9987677B2 (en) 2015-12-17 2018-06-05 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
US10118217B2 (en) 2015-12-17 2018-11-06 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
US10137499B2 (en) 2015-12-17 2018-11-27 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
US10099284B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having a catalyzed 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
US9968991B2 (en) 2015-12-17 2018-05-15 General Electric Company Method and assembly for forming components having internal passages using a lattice structure
US10046389B2 (en) 2015-12-17 2018-08-14 General Electric Company Method and assembly for forming components having internal passages 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
US10335853B2 (en) 2016-04-27 2019-07-02 General Electric Company Method and assembly for forming components using a jacketed core
US10436048B2 (en) * 2016-08-12 2019-10-08 General Electric Comapny Systems for removing heat from turbine components
US20180179899A1 (en) * 2016-12-22 2018-06-28 General Electric Company Method and apparatus for brazed engine components
US10927680B2 (en) 2017-05-31 2021-02-23 General Electric Company Adaptive cover for cooling pathway by additive manufacture
US10704399B2 (en) 2017-05-31 2020-07-07 General Electric Company Adaptively opening cooling pathway
US11041389B2 (en) 2017-05-31 2021-06-22 General Electric Company Adaptive cover for cooling pathway by additive manufacture
US10760430B2 (en) 2017-05-31 2020-09-01 General Electric Company Adaptively opening backup cooling pathway
US10837291B2 (en) * 2017-11-17 2020-11-17 General Electric Company Turbine engine with component having a cooled tip
US10830053B2 (en) * 2017-11-20 2020-11-10 General Electric Company Engine component cooling hole
US10408065B2 (en) 2017-12-06 2019-09-10 General Electric Company Turbine component with rail coolant directing chamber
US10570750B2 (en) 2017-12-06 2020-02-25 General Electric Company Turbine component with tip rail cooling passage
US20190218917A1 (en) 2018-01-17 2019-07-18 General Electric Company Engine component with set of cooling holes
US10753210B2 (en) * 2018-05-02 2020-08-25 Raytheon Technologies Corporation Airfoil having improved cooling scheme
CN113027537B (zh) * 2021-03-11 2022-10-04 湖南三一工业职业技术学院 一种气膜孔结构及涡轮叶片
CN113153446B (zh) * 2021-04-15 2022-08-02 中国航发湖南动力机械研究所 一种涡轮导向器及具有其的大膨胀比向心涡轮
US11572803B1 (en) 2022-08-01 2023-02-07 General Electric Company Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method
GB2638477A (en) * 2024-02-26 2025-08-27 Siemens Energy Global Gmbh & Co Kg Airfoil for turbine vane or turbine blade of an axial gas turbine

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US6916150B2 (en) 2003-11-26 2005-07-12 Siemens Westinghouse Power Corporation Cooling system for a tip of a turbine blade
US7717675B1 (en) 2007-05-24 2010-05-18 Florida Turbine Technologies, Inc. Turbine airfoil with a near wall mini serpentine cooling circuit

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US6164912A (en) 1998-12-21 2000-12-26 United Technologies Corporation Hollow airfoil for a gas turbine engine
US6916150B2 (en) 2003-11-26 2005-07-12 Siemens Westinghouse Power Corporation Cooling system for a tip of a turbine blade
US7717675B1 (en) 2007-05-24 2010-05-18 Florida Turbine Technologies, Inc. Turbine airfoil with a near wall mini serpentine cooling circuit

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Also Published As

Publication number Publication date
CN102606221A (zh) 2012-07-25
FR2970502A1 (fr) 2012-07-20
FR2970502B1 (fr) 2019-12-13
JP2012149641A (ja) 2012-08-09
US20120183412A1 (en) 2012-07-19
DE102012100266A1 (de) 2012-07-19
US8753083B2 (en) 2014-06-17
CN102606221B (zh) 2015-07-15
JP6001862B2 (ja) 2016-10-05

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Ipc: F01D0005180000

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Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

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