CH706964A8 - Cooling arrangement for platform region of turbine blade. - Google Patents

Cooling arrangement for platform region of turbine blade.

Info

Publication number
CH706964A8
CH706964A8 CH01466/13A CH14662013A CH706964A8 CH 706964 A8 CH706964 A8 CH 706964A8 CH 01466/13 A CH01466/13 A CH 01466/13A CH 14662013 A CH14662013 A CH 14662013A CH 706964 A8 CH706964 A8 CH 706964A8
Authority
CH
Switzerland
Prior art keywords
platform
cooling
turbine blade
cooling arrangement
side wall
Prior art date
Application number
CH01466/13A
Other languages
German (de)
Other versions
CH706964A2 (en
Inventor
Xiuzhang James Zhang
Christopher William Kester
Camilo Andres Sampayo
Adebukola Oluwaseun Benson
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of CH706964A2 publication Critical patent/CH706964A2/en
Publication of CH706964A8 publication Critical patent/CH706964A8/en

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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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

Die Erfindung betrifft eine Plattformkühlanordnung in einer Turbinenlaufschaufel, die an einer Übergangsstelle zwischen einem Schaufelblatt (102) und einer Wurzel eine Plattform (110) hat. Die Plattform (110) weist eine druckseitige Schlitzseitenwand und eine saugseitige Schlitzseitenwand auf. Die Plattformkühlanordnung umfasst Folgendes: einen im Inneren der Plattform (110) ausgebildeten Kühlkanal, wobei der Kühlkanal von einem ersten Ende in Richtung auf die druckseitige Schlitzseitenwand oder die saugseitige Schlitzseitenwand verläuft. An einem zweiten Ende weist der Kühlkanal eine Tasche (104) auf. Die Tasche weist, knapp bevor der Kühlkanal die Schlitzseitenwand erreicht, eine abrupte Vergrösserung des Strömungsquerschnitts auf.The invention relates to a platform cooling arrangement in a turbine blade having a platform (110) at an interface between an airfoil (102) and a root. The platform (110) has a pressure-side slot side wall and a suction-side slot side wall. The platform cooling assembly includes: a cooling passage formed inside the platform (110), the cooling passage extending from a first end toward the pressure-side slit sidewall or the suction-side slit sidewall. At a second end, the cooling channel has a pocket (104). The pocket has, just before the cooling channel reaches the slot side wall, an abrupt increase in the flow cross-section.

CH01466/13A 2012-08-31 2013-08-29 Cooling arrangement for platform region of turbine blade. CH706964A8 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/600,782 US20140064984A1 (en) 2012-08-31 2012-08-31 Cooling arrangement for platform region of turbine rotor blade

Publications (2)

Publication Number Publication Date
CH706964A2 CH706964A2 (en) 2014-03-14
CH706964A8 true CH706964A8 (en) 2014-08-29

Family

ID=50098556

Family Applications (1)

Application Number Title Priority Date Filing Date
CH01466/13A CH706964A8 (en) 2012-08-31 2013-08-29 Cooling arrangement for platform region of turbine blade.

Country Status (4)

Country Link
US (1) US20140064984A1 (en)
JP (1) JP2014047786A (en)
CH (1) CH706964A8 (en)
DE (1) DE102013109146A1 (en)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10533453B2 (en) * 2013-08-05 2020-01-14 United Technologies Corporation Engine component having platform with passageway
WO2015187163A1 (en) * 2014-06-05 2015-12-10 Siemens Energy, Inc. Turbine airfoil cooling system with platform cooling channels
JP5606648B1 (en) * 2014-06-27 2014-10-15 三菱日立パワーシステムズ株式会社 Rotor blade and gas turbine provided with the same
US9982542B2 (en) 2014-07-21 2018-05-29 United Technologies Corporation Airfoil platform impingement cooling holes
GB201506728D0 (en) * 2015-04-21 2015-06-03 Rolls Royce Plc Thermal shielding in a gas turbine
JP5905631B1 (en) * 2015-09-15 2016-04-20 三菱日立パワーシステムズ株式会社 Rotor blade, gas turbine provided with the same, and method of manufacturing rotor blade
US10066488B2 (en) * 2015-12-01 2018-09-04 General Electric Company Turbomachine blade with generally radial cooling conduit to wheel space
US10060269B2 (en) 2015-12-21 2018-08-28 General Electric Company Cooling circuits for a multi-wall blade
EP3249158A1 (en) * 2016-05-23 2017-11-29 Siemens Aktiengesellschaft Turbine blade and axial flow machine
EP3258065A1 (en) * 2016-06-17 2017-12-20 Siemens Aktiengesellschaft Turbine blade with a cooled blade platform and corresponding turbomachine
US10267162B2 (en) * 2016-08-18 2019-04-23 General Electric Company Platform core feed for a multi-wall blade
KR101873156B1 (en) * 2017-04-12 2018-06-29 두산중공업 주식회사 Turbine vane and gas turbine having the same
US11225873B2 (en) * 2020-01-13 2022-01-18 Rolls-Royce Corporation Combustion turbine vane cooling system
US11136890B1 (en) * 2020-03-25 2021-10-05 General Electric Company Cooling circuit for a turbomachine component
US11401819B2 (en) * 2020-12-17 2022-08-02 Solar Turbines Incorporated Turbine blade platform cooling holes

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1605335A (en) * 1975-08-23 1991-12-18 Rolls Royce A rotor blade for a gas turbine engine
US5382135A (en) * 1992-11-24 1995-01-17 United Technologies Corporation Rotor blade with cooled integral platform
EP1013884B1 (en) * 1998-12-24 2005-07-27 ALSTOM Technology Ltd Turbine blade with actively cooled head platform
US6508620B2 (en) * 2001-05-17 2003-01-21 Pratt & Whitney Canada Corp. Inner platform impingement cooling by supply air from outside
US6811378B2 (en) * 2002-07-31 2004-11-02 Power Systems Mfg, Llc Insulated cooling passageway for cooling a shroud of a turbine blade
US7650926B2 (en) * 2006-09-28 2010-01-26 United Technologies Corporation Blade outer air seals, cores, and manufacture methods
US20110020115A1 (en) * 2009-07-27 2011-01-27 United Technologies Corporation Refractory metal core integrally cast exit trench
US8794921B2 (en) * 2010-09-30 2014-08-05 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US8851846B2 (en) * 2010-09-30 2014-10-07 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US9249674B2 (en) * 2011-12-30 2016-02-02 General Electric Company Turbine rotor blade platform cooling
US10364680B2 (en) * 2012-08-14 2019-07-30 United Technologies Corporation Gas turbine engine component having platform trench

Also Published As

Publication number Publication date
CH706964A2 (en) 2014-03-14
DE102013109146A1 (en) 2014-03-06
US20140064984A1 (en) 2014-03-06
JP2014047786A (en) 2014-03-17

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Legal Events

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