FR2970502B1 - Composant de turbine muni de passages de refroidissement incurves. - Google Patents

Composant de turbine muni de passages de refroidissement incurves. Download PDF

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Publication number
FR2970502B1
FR2970502B1 FR1250354A FR1250354A FR2970502B1 FR 2970502 B1 FR2970502 B1 FR 2970502B1 FR 1250354 A FR1250354 A FR 1250354A FR 1250354 A FR1250354 A FR 1250354A FR 2970502 B1 FR2970502 B1 FR 2970502B1
Authority
FR
France
Prior art keywords
blade
cooling passages
turbine component
curved cooling
curved
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.)
Expired - Fee Related
Application number
FR1250354A
Other languages
English (en)
Other versions
FR2970502A1 (fr
Inventor
Benjamin Paul Lacy
Brian Peter Arness
Victor John Morgan
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.)
General Electric Co
Original Assignee
General Electric Co
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 Co filed Critical General Electric Co
Publication of FR2970502A1 publication Critical patent/FR2970502A1/fr
Application granted granted Critical
Publication of FR2970502B1 publication Critical patent/FR2970502B1/fr
Expired - Fee Related 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
    • F01D5/186—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)

Abstract

La pale (24) comprend un côté pression (38) et un côté aspiration (40) s'étendant entre un bord d'attaque (42) et un bord de fuite (44). Un circuit de refroidissement (46) de pale peut être au moins partiellement disposé à l'intérieur de la pale (24) et peut être conçu pour faire circuler un agent de refroidissement à travers la pale (24). Le passage de refroidissement courbe (60, 62) peut globalement être en communication fluidique avec le circuit de refroidissement de pale afin que l'agent de refroidissement circulant dans le circuit de refroidissement de pale puisse être amené à entrer dans le passage de refroidissement (60, 62). De plus, le passage de refroidissement courbe (60, 62) peut globalement s'étendre dans le sens de la longueur à l'intérieur de la pale (24) entre les bords d'attaque et de fuite (42, 44) le long d'au moins une partie du côté pression (38) ou du côté aspiration de la pale profilée (24).
FR1250354A 2011-01-14 2012-01-13 Composant de turbine muni de passages de refroidissement incurves. Expired - Fee Related FR2970502B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US13006914 2011-01-14
US13/006,914 US8753083B2 (en) 2011-01-14 2011-01-14 Curved cooling passages for a turbine component

Publications (2)

Publication Number Publication Date
FR2970502A1 FR2970502A1 (fr) 2012-07-20
FR2970502B1 true FR2970502B1 (fr) 2019-12-13

Family

ID=46397768

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1250354A Expired - Fee Related FR2970502B1 (fr) 2011-01-14 2012-01-13 Composant de turbine muni de passages de refroidissement incurves.

Country Status (5)

Country Link
US (1) US8753083B2 (fr)
JP (1) JP6001862B2 (fr)
CN (1) CN102606221B (fr)
DE (1) DE102012100266A1 (fr)
FR (1) FR2970502B1 (fr)

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US9810072B2 (en) * 2014-05-28 2017-11-07 General Electric Company Rotor blade cooling
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
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
US10099284B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having a catalyzed 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
US10118217B2 (en) 2015-12-17 2018-11-06 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
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
US10137499B2 (en) 2015-12-17 2018-11-27 General Electric Company Method and assembly for forming components having an 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
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
US10760430B2 (en) 2017-05-31 2020-09-01 General Electric Company Adaptively opening backup cooling pathway
US10927680B2 (en) 2017-05-31 2021-02-23 General Electric Company Adaptive cover for cooling pathway by additive manufacture
US11041389B2 (en) 2017-05-31 2021-06-22 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
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
US10570750B2 (en) 2017-12-06 2020-02-25 General Electric Company Turbine component with tip rail cooling passage
US10408065B2 (en) 2017-12-06 2019-09-10 General Electric Company Turbine component with rail coolant directing chamber
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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

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Also Published As

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

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