DE602006019989D1 - Innenhaubenschaufelblatt für turbinentriebwerk - Google Patents

Innenhaubenschaufelblatt für turbinentriebwerk

Info

Publication number
DE602006019989D1
DE602006019989D1 DE602006019989T DE602006019989T DE602006019989D1 DE 602006019989 D1 DE602006019989 D1 DE 602006019989D1 DE 602006019989 T DE602006019989 T DE 602006019989T DE 602006019989 T DE602006019989 T DE 602006019989T DE 602006019989 D1 DE602006019989 D1 DE 602006019989D1
Authority
DE
Germany
Prior art keywords
turbine engine
cover sheet
interior cover
interior
sheet
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
DE602006019989T
Other languages
English (en)
Inventor
Edward F Migliaro Jr
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 DE602006019989D1 publication Critical patent/DE602006019989D1/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
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • 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
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/58—Reversers mounted on the inner cone or the nozzle housing or the fuselage
    • 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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
DE602006019989T 2006-10-12 2006-10-12 Innenhaubenschaufelblatt für turbinentriebwerk Active DE602006019989D1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US2006/040247 WO2008045089A1 (en) 2006-10-12 2006-10-12 Core cowl airfoil for a gas turbine engine

Publications (1)

Publication Number Publication Date
DE602006019989D1 true DE602006019989D1 (de) 2011-03-17

Family

ID=38626436

Family Applications (1)

Application Number Title Priority Date Filing Date
DE602006019989T Active DE602006019989D1 (de) 2006-10-12 2006-10-12 Innenhaubenschaufelblatt für turbinentriebwerk

Country Status (4)

Country Link
US (1) US8272204B2 (de)
EP (1) EP2074303B1 (de)
DE (1) DE602006019989D1 (de)
WO (1) WO2008045089A1 (de)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8667802B2 (en) * 2010-05-06 2014-03-11 Spirit Aerosystems, Inc. Variable fan duct nozzle translatable core/inner cowl including two overlapping portions made of different materials
US20140161603A1 (en) * 2012-12-07 2014-06-12 General Electric Company Exhaust diffuser
GB201412189D0 (en) * 2014-07-09 2014-08-20 Rolls Royce Plc A nozzle arrangement for a gas turbine engine
US10337401B2 (en) 2015-02-13 2019-07-02 United Technologies Corporation Turbine engine with a turbo-compressor
US10100731B2 (en) 2015-02-13 2018-10-16 United Technologies Corporation Turbine engine with a turbo-compressor
US10125722B2 (en) * 2015-02-13 2018-11-13 United Technologies Corporation Turbine engine with a turbo-compressor

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB875496A (en) 1959-12-07 1961-08-23 Gen Electric Improvements in or relating to ducted-fan gas turbine jet propulsion engines
GB1111219A (en) * 1966-02-14 1968-04-24 Rolls Royce Gas turbine engine
FR1504543A (fr) * 1966-07-28 1967-12-08 Snecma Perfectionnements aux turboréacteurs et autres réacteurs à double flux
US3598318A (en) * 1970-04-10 1971-08-10 Boeing Co Movable acoustic splitter for nozzle area control and thrust reversal
US3877663A (en) * 1973-11-19 1975-04-15 Aeritalia Spa Translating splitter variable area nozzle and reverser
US3936226A (en) * 1974-06-07 1976-02-03 United Technologies Corporation Control system for variable pitch fan propulsor with reverse pitch
US4651521A (en) * 1985-11-21 1987-03-24 Avco Corporation Convertible turbo-fan, turbo-shaft aircraft propulsion system
GB2198999B (en) * 1986-12-17 1990-08-29 Rolls Royce Plc Fluid propulsion engine with flow exit control device
FR2650861A1 (fr) * 1989-08-08 1991-02-15 Snecma Inverseur de poussee de turboreacteur double flux, a obstacles lies au capot primaire
US5706649A (en) 1995-04-03 1998-01-13 Boeing North American, Inc. Multi axis thrust vectoring for turbo fan engines
US5782431A (en) * 1995-08-18 1998-07-21 Gal-Or; Benjamin Thrust vectoring/reversing systems

Also Published As

Publication number Publication date
EP2074303A1 (de) 2009-07-01
WO2008045089A1 (en) 2008-04-17
EP2074303B1 (de) 2011-02-02
US20100077724A1 (en) 2010-04-01
US8272204B2 (en) 2012-09-25

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