DE602007008299D1 - Fandüse mit variablem querschnitt für eine gasturbinentriebwerksfangondel mit antriebsringbetätigungssystem - Google Patents

Fandüse mit variablem querschnitt für eine gasturbinentriebwerksfangondel mit antriebsringbetätigungssystem

Info

Publication number
DE602007008299D1
DE602007008299D1 DE602007008299T DE602007008299T DE602007008299D1 DE 602007008299 D1 DE602007008299 D1 DE 602007008299D1 DE 602007008299 T DE602007008299 T DE 602007008299T DE 602007008299 T DE602007008299 T DE 602007008299T DE 602007008299 D1 DE602007008299 D1 DE 602007008299D1
Authority
DE
Germany
Prior art keywords
control system
gas turbine
turbine engine
return control
transfer wire
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
DE602007008299T
Other languages
English (en)
Inventor
Kenneth C Baran
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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 United Technologies Corp filed Critical United Technologies Corp
Publication of DE602007008299D1 publication Critical patent/DE602007008299D1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/15—Control or regulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/42—Movement of components with two degrees of freedom

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
  • Control Of Throttle Valves Provided In The Intake System Or In The Exhaust System (AREA)
  • Supercharger (AREA)
DE602007008299T 2007-03-05 2007-03-05 Fandüse mit variablem querschnitt für eine gasturbinentriebwerksfangondel mit antriebsringbetätigungssystem Active DE602007008299D1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2007/063255 WO2008108847A1 (en) 2007-03-05 2007-03-05 Fan variable area nozzle for a gas turbine engine fan nacelle with drive ring actuation system

Publications (1)

Publication Number Publication Date
DE602007008299D1 true DE602007008299D1 (de) 2010-09-16

Family

ID=38828999

Family Applications (1)

Application Number Title Priority Date Filing Date
DE602007008299T Active DE602007008299D1 (de) 2007-03-05 2007-03-05 Fandüse mit variablem querschnitt für eine gasturbinentriebwerksfangondel mit antriebsringbetätigungssystem

Country Status (5)

Country Link
US (1) US8316646B2 (de)
EP (1) EP2134949B1 (de)
AT (1) ATE476594T1 (de)
DE (1) DE602007008299D1 (de)
WO (1) WO2008108847A1 (de)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0820175D0 (en) * 2008-11-05 2008-12-10 Rolls Royce Plc A gas turbine engine variable area exhuast nozzle
US8961114B2 (en) 2010-11-22 2015-02-24 General Electric Company Integrated variable geometry flow restrictor and heat exchanger
FR2972768B1 (fr) * 2011-03-14 2015-07-17 Snecma Turbomachine a helice(s) pour aeronef, a tuyere mobile
US9447695B2 (en) 2012-03-01 2016-09-20 United Technologies Corporation Diffuser seal for geared turbofan or turboprop engines
US9091230B2 (en) * 2012-05-16 2015-07-28 The Boeing Company Linked ring petal actuation for variable area fan nozzle
FR2993932B1 (fr) * 2012-07-27 2015-09-25 Aircelle Sa Dispositif d'entrainement de volets notamment pour tuyere adaptative
US11585293B2 (en) * 2012-10-01 2023-02-21 Raytheon Technologies Corporation Low weight large fan gas turbine engine
US9989009B2 (en) * 2012-10-31 2018-06-05 The Boeing Company Methods and apparatus for sealing variable area fan nozzles of jet engines
US10400621B2 (en) 2013-03-04 2019-09-03 United Technologies Corporation Pivot door thrust reverser with variable area nozzle
WO2014197030A2 (en) * 2013-03-12 2014-12-11 United Technologies Corporation Expanding shell flow control device
US9650991B2 (en) 2013-06-27 2017-05-16 The Boeing Company Pivoting ring petal actuation for variable area fan nozzle
US9488130B2 (en) 2013-10-17 2016-11-08 Honeywell International Inc. Variable area fan nozzle systems with improved drive couplings
US9869190B2 (en) 2014-05-30 2018-01-16 General Electric Company Variable-pitch rotor with remote counterweights
US10072510B2 (en) 2014-11-21 2018-09-11 General Electric Company Variable pitch fan for gas turbine engine and method of assembling the same
US10100653B2 (en) 2015-10-08 2018-10-16 General Electric Company Variable pitch fan blade retention system
FR3042226B1 (fr) * 2015-10-13 2019-06-07 Safran Nacelles Tuyere de section variable pour nacelle d'aeronef et nacelle pour un turboreacteur d'aeronef comportant une telle tuyere
US10302044B2 (en) * 2015-12-18 2019-05-28 Rohr, Inc. Translating cascade thrust reverser with control of blocker door
US20190293020A1 (en) * 2018-03-21 2019-09-26 Spirit Aerosystems, Inc. Flexible sleeve for adjustable fan duct nozzle
US11674435B2 (en) 2021-06-29 2023-06-13 General Electric Company Levered counterweight feathering system
US11795964B2 (en) 2021-07-16 2023-10-24 General Electric Company Levered counterweight feathering system

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2800766A (en) * 1952-09-25 1957-07-30 Gen Electric Annular means for changing the area of a variable exhaust nozzle
GB1365491A (en) * 1971-01-02 1974-09-04 Dowty Rotol Ltd Gas turbine ducted fan engines and fans therefor
GB1424193A (en) * 1972-03-21 1976-02-11 Rolls Royce Gas turbine ducted fan engines
GB2120172B (en) 1982-10-26 1985-09-11 Meurer Druck And Carton Gmbh Sheet processing appparatus
US5261605A (en) * 1990-08-23 1993-11-16 United Technologies Corporation Axisymmetric nozzle with gimbled unison ring
US5174502A (en) 1991-05-10 1992-12-29 General Electric Company Support for a translating nozzle vectoring ring
US5782431A (en) * 1995-08-18 1998-07-21 Gal-Or; Benjamin Thrust vectoring/reversing systems
US6299077B1 (en) * 1999-12-18 2001-10-09 United Technologies Corporation Actuation system for convergent/divergent nozzle
US7721551B2 (en) * 2006-06-29 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle
EP2074304B1 (de) * 2006-10-12 2015-03-25 United Technologies Corporation Gasturbinentriebwerk mit Dreifachkörper-Gebläsedüse mit variablem Querschnitt und Schubumkehrvorrichtung
WO2008045062A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle with sliding actuation system
US7797944B2 (en) * 2006-10-20 2010-09-21 United Technologies Corporation Gas turbine engine having slim-line nacelle
US7721549B2 (en) * 2007-02-08 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system

Also Published As

Publication number Publication date
WO2008108847A1 (en) 2008-09-12
EP2134949B1 (de) 2010-08-04
US8316646B2 (en) 2012-11-27
US20100058769A1 (en) 2010-03-11
ATE476594T1 (de) 2010-08-15
EP2134949A1 (de) 2009-12-23

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