DE69834858D1 - Segmentierte Durchflussregelvorrichtung für ein Gasturbinentriebwerk - Google Patents

Segmentierte Durchflussregelvorrichtung für ein Gasturbinentriebwerk

Info

Publication number
DE69834858D1
DE69834858D1 DE69834858T DE69834858T DE69834858D1 DE 69834858 D1 DE69834858 D1 DE 69834858D1 DE 69834858 T DE69834858 T DE 69834858T DE 69834858 T DE69834858 T DE 69834858T DE 69834858 D1 DE69834858 D1 DE 69834858D1
Authority
DE
Germany
Prior art keywords
control device
flow control
gas turbine
turbine engine
segmented flow
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.)
Expired - Lifetime
Application number
DE69834858T
Other languages
English (en)
Other versions
DE69834858T2 (de
Inventor
Russel L Thornock
Russel S Brinton
Joel E Hansen
Leonard J Hebert
Michael R Holle
Jeffrey P Kane
John G Kladouris
Michael B Scholey
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.)
Boeing Co
Original Assignee
Boeing Co
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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=25249444&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=DE69834858(D1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Boeing Co filed Critical Boeing Co
Publication of DE69834858D1 publication Critical patent/DE69834858D1/de
Application granted granted Critical
Publication of DE69834858T2 publication Critical patent/DE69834858T2/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
    • 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
    • F02K1/52—Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Exhaust Silencers (AREA)
DE69834858T 1997-03-28 1998-03-23 Segmentierte Durchflussregelvorrichtung für ein Gasturbinentriebwerk Expired - Lifetime DE69834858T2 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US08/827,523 US5887822A (en) 1997-03-28 1997-03-28 Segmented engine flow control device
US827523 1997-03-28

Publications (2)

Publication Number Publication Date
DE69834858D1 true DE69834858D1 (de) 2006-07-27
DE69834858T2 DE69834858T2 (de) 2007-01-18

Family

ID=25249444

Family Applications (1)

Application Number Title Priority Date Filing Date
DE69834858T Expired - Lifetime DE69834858T2 (de) 1997-03-28 1998-03-23 Segmentierte Durchflussregelvorrichtung für ein Gasturbinentriebwerk

Country Status (3)

Country Link
US (1) US5887822A (de)
EP (1) EP0867366B2 (de)
DE (1) DE69834858T2 (de)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6983912B2 (en) * 2002-04-30 2006-01-10 The Boeing Company Hybrid exhaust heat shield for pylon mounted gas turbine engines
US7232289B2 (en) * 2005-05-12 2007-06-19 Honeywell International, Inc. Shroud for an air turbine starter
FR2920146B1 (fr) * 2007-08-20 2009-10-30 Aircelle Sa Nacelle a section de sortie adaptable
US9284887B2 (en) 2009-12-31 2016-03-15 Rolls-Royce North American Technologies, Inc. Gas turbine engine and frame
FR2988688B1 (fr) * 2012-03-27 2014-05-09 Airbus Operations Sas Carenage aerodynamique arriere a tenue en temperature amelioree pour mat d'accrochage d'ensemble propulsif d'aeronef
FR3000721B1 (fr) * 2013-01-09 2016-10-14 Airbus Operations Sas Ensemble propulsif d'aeronef comprenant un carenage aerodynamique arriere de mat d'accrochage a parois laterales profilees pour l'injection d'air frais le long d'un plancher de protection thermique
WO2014151673A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Aerodynamic track fairing for a gas turbine engine fan nacelle
FR3009339B1 (fr) * 2013-07-30 2018-01-26 Safran Aircraft Engines Turbomachine comprenant un dispositif de refroidissement du pylone
FR3010052B1 (fr) * 2013-08-29 2015-09-25 Aircelle Sa Bras de servitude d’une nacelle de turboreacteur a double flux, comportant deux parties
FR3021029B1 (fr) * 2014-05-16 2016-05-06 Airbus Operations Sas Carenage aerodynamique
US10759541B2 (en) * 2016-10-14 2020-09-01 Rohr, Inc. Nacelle bifurcation with leading edge structure
US11827373B2 (en) * 2019-09-27 2023-11-28 The Boeing Company Aircraft engine exhaust systems enabling reduced length aft strut fairings
US11846548B2 (en) * 2021-03-16 2023-12-19 Kidde Technologies, Inc. Protective sleeves for fire and overheat detection systems for aircraft applications

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3101920A (en) * 1960-01-27 1963-08-27 United Aircraft Corp Boundary layer control
GB1073222A (en) * 1963-04-16 1967-06-21 British Aircraft Corp Opperati Improvements in aeroplanes
GB1118340A (en) * 1966-12-30 1968-07-03 Rolls Royce Mounting means for an aircraft engine
US4466587A (en) * 1981-12-21 1984-08-21 General Electric Company Nacelle installation
US4427169A (en) * 1982-06-08 1984-01-24 Boeing Commercial Airplane Company Variable camber flap end seal
US4712750A (en) * 1986-05-02 1987-12-15 The Boeing Company Temperature control device for jet engine nacelle associated structure
US5524846A (en) * 1993-12-21 1996-06-11 The Boeing Company Fire protection system for airplanes

Also Published As

Publication number Publication date
EP0867366A2 (de) 1998-09-30
EP0867366B2 (de) 2011-09-14
EP0867366A3 (de) 1999-09-15
US5887822A (en) 1999-03-30
DE69834858T2 (de) 2007-01-18
EP0867366B1 (de) 2006-06-14

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Legal Events

Date Code Title Description
8363 Opposition against the patent
R102 Epo decision maintaining patent in amended form now final

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