ITTO20020624A1 - Dispositivo di incernieramento di un organo rotante in un motore aeronautico - Google Patents

Dispositivo di incernieramento di un organo rotante in un motore aeronautico

Info

Publication number
ITTO20020624A1
ITTO20020624A1 IT2002TO000624A ITTO20020624A ITTO20020624A1 IT TO20020624 A1 ITTO20020624 A1 IT TO20020624A1 IT 2002TO000624 A IT2002TO000624 A IT 2002TO000624A IT TO20020624 A ITTO20020624 A IT TO20020624A IT TO20020624 A1 ITTO20020624 A1 IT TO20020624A1
Authority
IT
Italy
Prior art keywords
rotating body
hinge device
aircraft engine
aircraft
engine
Prior art date
Application number
IT2002TO000624A
Other languages
English (en)
Inventor
Daniele Coutandin
Crode Domenico Dalle
Paolo Lorenzo Ciacci
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 IT2002TO000624A priority Critical patent/ITTO20020624A1/it
Publication of ITTO20020624A0 publication Critical patent/ITTO20020624A0/it
Priority to CA002436106A priority patent/CA2436106A1/en
Priority to US10/604,346 priority patent/US20040107538A1/en
Priority to EP03016086A priority patent/EP1382804A3/en
Publication of ITTO20020624A1 publication Critical patent/ITTO20020624A1/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
    • 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
    • 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)
  • Pivots And Pivotal Connections (AREA)
  • Hinges (AREA)
IT2002TO000624A 2002-07-16 2002-07-16 Dispositivo di incernieramento di un organo rotante in un motore aeronautico ITTO20020624A1 (it)

Priority Applications (4)

Application Number Priority Date Filing Date Title
IT2002TO000624A ITTO20020624A1 (it) 2002-07-16 2002-07-16 Dispositivo di incernieramento di un organo rotante in un motore aeronautico
CA002436106A CA2436106A1 (en) 2002-07-16 2003-07-14 Hinge device for a rotary member of an aircraft engine
US10/604,346 US20040107538A1 (en) 2002-07-16 2003-07-14 Hinge device for a rotary member of an aircraft engine
EP03016086A EP1382804A3 (en) 2002-07-16 2003-07-15 Hinge device for a rotary member of an aircraft engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT2002TO000624A ITTO20020624A1 (it) 2002-07-16 2002-07-16 Dispositivo di incernieramento di un organo rotante in un motore aeronautico

Publications (2)

Publication Number Publication Date
ITTO20020624A0 ITTO20020624A0 (it) 2002-07-16
ITTO20020624A1 true ITTO20020624A1 (it) 2004-01-16

Family

ID=11459505

Family Applications (1)

Application Number Title Priority Date Filing Date
IT2002TO000624A ITTO20020624A1 (it) 2002-07-16 2002-07-16 Dispositivo di incernieramento di un organo rotante in un motore aeronautico

Country Status (4)

Country Link
US (1) US20040107538A1 (it)
EP (1) EP1382804A3 (it)
CA (1) CA2436106A1 (it)
IT (1) ITTO20020624A1 (it)

Families Citing this family (4)

* 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,
US10830096B2 (en) * 2013-10-03 2020-11-10 Raytheon Technologies Corporation Rotating turbine vane bearing cooling
DE102019218909A1 (de) * 2019-12-04 2021-06-10 MTU Aero Engines AG Strömungsmaschine
US11248404B2 (en) 2020-01-28 2022-02-15 Lockheed Martin Corporation Fluid transfer hinge

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE514728A (it) * 1951-10-10
FR1053647A (fr) * 1952-04-05 1954-02-03 Snecma Perfectionnements aux propulseurs à turbine à gaz
FR2030895A5 (it) * 1969-05-23 1970-11-13 Motoren Turbinen Union
US3895689A (en) * 1970-01-07 1975-07-22 Judson S Swearingen Thrust bearing lubricant measurement and balance
US4503683A (en) * 1983-12-16 1985-03-12 The Garrett Corporation Compact cooling turbine-heat exchanger assembly
US4644202A (en) * 1985-04-15 1987-02-17 Rockwell International Corporation Sealed and balanced motor and fluid pump system
GB2210935B (en) * 1987-10-10 1992-05-27 Rolls Royce Plc Variable stator vane assembly
US5055009A (en) * 1989-12-12 1991-10-08 Allied-Signal Inc. Turbocharger with improved roller bearing shaft support
DE4213678A1 (de) * 1992-04-25 1993-10-28 Asea Brown Boveri Axialdurchströmte Abgasturboladerturbine
DE4435322B4 (de) * 1994-10-01 2005-05-04 Alstom Verfahren und Vorrichtung zur Wellendichtung und zur Kühlung auf der Abgasseite einer axialdurchströmten Gasturbine
TW390936B (en) * 1997-12-20 2000-05-21 Allied Signal Inc Microturbine power generating system
JP4527824B2 (ja) * 1998-12-22 2010-08-18 ゼネラル・エレクトリック・カンパニイ タービンロータの軸受用冷却系
JP3481596B2 (ja) * 2001-02-14 2003-12-22 株式会社日立製作所 ガスタービン
ITTO20010446A1 (it) * 2001-05-11 2002-11-11 Fiatavio Spa Paletta per uno statore di una turbina a geometria variabile, in particolare per motori aeronautici.

Also Published As

Publication number Publication date
EP1382804A3 (en) 2004-09-15
ITTO20020624A0 (it) 2002-07-16
EP1382804A2 (en) 2004-01-21
US20040107538A1 (en) 2004-06-10
CA2436106A1 (en) 2004-01-16

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