ITTO20020607A1 - Metodo per la realizzazione ed il montaggio di un dispositivo di raffreddamento in una paletta di una turbina assiale a gas e paletta per un - Google Patents

Metodo per la realizzazione ed il montaggio di un dispositivo di raffreddamento in una paletta di una turbina assiale a gas e paletta per un

Info

Publication number
ITTO20020607A1
ITTO20020607A1 IT2002TO000607A ITTO20020607A ITTO20020607A1 IT TO20020607 A1 ITTO20020607 A1 IT TO20020607A1 IT 2002TO000607 A IT2002TO000607 A IT 2002TO000607A IT TO20020607 A ITTO20020607 A IT TO20020607A IT TO20020607 A1 ITTO20020607 A1 IT TO20020607A1
Authority
IT
Italy
Prior art keywords
bucket
realization
assembly
gas turbine
cooling device
Prior art date
Application number
IT2002TO000607A
Other languages
English (en)
Inventor
Daniele Coutandin
Paolo Lorenzo Ciacci
Domenico Dellecrode
Original Assignee
Fiatavio Spa
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 Fiatavio Spa filed Critical Fiatavio Spa
Priority to IT2002TO000607A priority Critical patent/ITTO20020607A1/it
Publication of ITTO20020607A0 publication Critical patent/ITTO20020607A0/it
Priority to EP03015872A priority patent/EP1380725A3/en
Priority to US10/604,337 priority patent/US20040109763A1/en
Priority to CA002435070A priority patent/CA2435070A1/en
Publication of ITTO20020607A1 publication Critical patent/ITTO20020607A1/it

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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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)
IT2002TO000607A 2002-07-12 2002-07-12 Metodo per la realizzazione ed il montaggio di un dispositivo di raffreddamento in una paletta di una turbina assiale a gas e paletta per un ITTO20020607A1 (it)

Priority Applications (4)

Application Number Priority Date Filing Date Title
IT2002TO000607A ITTO20020607A1 (it) 2002-07-12 2002-07-12 Metodo per la realizzazione ed il montaggio di un dispositivo di raffreddamento in una paletta di una turbina assiale a gas e paletta per un
EP03015872A EP1380725A3 (en) 2002-07-12 2003-07-11 Method of producing and assembling a cooling device inside an axial-flow gas turbine blade, and blade produced using such a method
US10/604,337 US20040109763A1 (en) 2002-07-12 2003-07-11 Method of producing and assembling a cooling device inside an axial-flow gas turbine blade, and axial-flow gas turbine blade produced using such a method
CA002435070A CA2435070A1 (en) 2002-07-12 2003-07-11 Method of producing and assembling a cooling device inside an axial-flow gas turbine blade, and axial-flow gas turbine blade produced using such a method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT2002TO000607A ITTO20020607A1 (it) 2002-07-12 2002-07-12 Metodo per la realizzazione ed il montaggio di un dispositivo di raffreddamento in una paletta di una turbina assiale a gas e paletta per un

Publications (2)

Publication Number Publication Date
ITTO20020607A0 ITTO20020607A0 (it) 2002-07-12
ITTO20020607A1 true ITTO20020607A1 (it) 2004-01-12

Family

ID=11459488

Family Applications (1)

Application Number Title Priority Date Filing Date
IT2002TO000607A ITTO20020607A1 (it) 2002-07-12 2002-07-12 Metodo per la realizzazione ed il montaggio di un dispositivo di raffreddamento in una paletta di una turbina assiale a gas e paletta per un

Country Status (4)

Country Link
US (1) US20040109763A1 (it)
EP (1) EP1380725A3 (it)
CA (1) CA2435070A1 (it)
IT (1) ITTO20020607A1 (it)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITTO20020699A1 (it) * 2002-08-06 2004-02-07 Fiatavio Spa Paletta per lo statore di una turbina a geometria variabile,
EP2469029A1 (en) * 2010-12-22 2012-06-27 Siemens Aktiengesellschaft Impingement cooling of gas turbine blades or vanes
EP2540969A1 (en) 2011-06-27 2013-01-02 Siemens Aktiengesellschaft Impingement cooling of turbine blades or vanes
EP2573325A1 (en) 2011-09-23 2013-03-27 Siemens Aktiengesellschaft Impingement cooling of turbine blades or vanes
EP2860348A1 (de) * 2013-10-08 2015-04-15 Siemens Aktiengesellschaft Einsatz für eine Turbinenschaufel aus mehreren Bauteilen und zugehöriges Verfahren
US10422244B2 (en) 2015-03-16 2019-09-24 General Electric Company System for cooling a turbine shroud
JP6651378B2 (ja) * 2016-02-22 2020-02-19 三菱日立パワーシステムズ株式会社 インサート組品、翼、ガスタービン、および、翼の製造方法
US10502070B2 (en) 2016-11-17 2019-12-10 United Technologies Corporation Airfoil with laterally insertable baffle

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1605194A (en) * 1974-10-17 1983-04-07 Rolls Royce Rotor blade for gas turbine engines
SE395934B (sv) * 1976-01-19 1977-08-29 Stal Laval Turbin Ab Kyld-ihalig ledskovel for gasturbin
US4257734A (en) * 1978-03-22 1981-03-24 Rolls-Royce Limited Guide vanes for gas turbine engines
US4798515A (en) * 1986-05-19 1989-01-17 The United States Of America As Represented By The Secretary Of The Air Force Variable nozzle area turbine vane cooling
US6543993B2 (en) * 2000-12-28 2003-04-08 General Electric Company Apparatus and methods for localized cooling of gas turbine nozzle walls

Also Published As

Publication number Publication date
US20040109763A1 (en) 2004-06-10
ITTO20020607A0 (it) 2002-07-12
EP1380725A3 (en) 2004-09-15
EP1380725A2 (en) 2004-01-14
CA2435070A1 (en) 2004-01-12

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