DE3039869C2 - Anordnung und Befestigung einer Triebwerksgondel an einem Flugzeug - Google Patents

Anordnung und Befestigung einer Triebwerksgondel an einem Flugzeug

Info

Publication number
DE3039869C2
DE3039869C2 DE3039869A DE3039869A DE3039869C2 DE 3039869 C2 DE3039869 C2 DE 3039869C2 DE 3039869 A DE3039869 A DE 3039869A DE 3039869 A DE3039869 A DE 3039869A DE 3039869 C2 DE3039869 C2 DE 3039869C2
Authority
DE
Germany
Prior art keywords
core engine
housing
fan
engine
nozzle
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
Application number
DE3039869A
Other languages
German (de)
English (en)
Other versions
DE3039869A1 (de
Inventor
Harry Duffield Derby Hurdis
Alan James Allestree Derby Tudor
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of DE3039869A1 publication Critical patent/DE3039869A1/de
Application granted granted Critical
Publication of DE3039869C2 publication Critical patent/DE3039869C2/de
Expired legal-status Critical Current

Links

Classifications

    • 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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
DE3039869A 1979-10-23 1980-10-22 Anordnung und Befestigung einer Triebwerksgondel an einem Flugzeug Expired DE3039869C2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB7936690A GB2061389B (en) 1979-10-23 1979-10-23 Rod installation for a gas turbine engine

Publications (2)

Publication Number Publication Date
DE3039869A1 DE3039869A1 (de) 1981-05-07
DE3039869C2 true DE3039869C2 (de) 1986-06-19

Family

ID=10508709

Family Applications (1)

Application Number Title Priority Date Filing Date
DE3039869A Expired DE3039869C2 (de) 1979-10-23 1980-10-22 Anordnung und Befestigung einer Triebwerksgondel an einem Flugzeug

Country Status (5)

Country Link
US (1) US4384453A (enExample)
JP (1) JPS5936095B2 (enExample)
DE (1) DE3039869C2 (enExample)
FR (1) FR2467776A1 (enExample)
GB (1) GB2061389B (enExample)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4417848A (en) 1982-02-01 1983-11-29 United Technologies Corporation Containment shell for a fan section of a gas turbine engine
US4437627A (en) 1982-03-12 1984-03-20 The Boeing Company Integrated power plant installation system
US4603821A (en) * 1983-12-30 1986-08-05 The Boeing Company System for mounting a jet engine
FR2560854B1 (fr) * 1984-03-07 1986-09-12 Snecma Capotages structuraux participant a la rigidite d'ensemble d'un turboreacteur
GB2188987B (en) * 1986-04-09 1990-02-14 Rolls Royce A turbofan gas turbine engine and mountings therefor
GB2194593B (en) * 1986-08-29 1991-05-15 Gen Electric High bypass ratio, counter rotating gearless front fan engine
GB2215290B (en) * 1988-03-08 1991-09-04 Rolls Royce Plc A method of mounting a ducted fan gas turbine engine on an aircraft
US5307623A (en) * 1991-05-28 1994-05-03 General Electric Company Apparatus and method for the diassembly of an ultra high bypass engine
FR2825976B1 (fr) * 2001-06-13 2003-09-05 Eads Airbus Sa Dispositif de reprise d'efforts generes par un moteur d'aeronef
US20110101158A1 (en) * 2005-03-29 2011-05-05 The Boeing Company Thrust Reversers Including Monolithic Components
FR2903734B1 (fr) * 2006-07-12 2008-09-12 Airbus France Sas Turbomoteur pour aeronef.
US7900433B2 (en) * 2006-08-31 2011-03-08 United Technologies Corporation Fan exhaust nozzle for turbofan engine
US20080157418A1 (en) * 2006-12-27 2008-07-03 Lee Alan Blanton Methods for fabricating composite structures with flanges having tethered corners
US9957918B2 (en) * 2007-08-28 2018-05-01 United Technologies Corporation Gas turbine engine front architecture
US8814081B2 (en) 2010-12-27 2014-08-26 Rolls-Royce North American Technologies, Inc. Aircraft and external pod for aircraft
EP3059413B1 (en) 2011-03-29 2019-05-08 Rolls-Royce North American Technologies, Inc. Vehicle system
FR3010147B1 (fr) * 2013-08-28 2015-08-21 Snecma Suspension isostatique d'un turboreacteur par double support arriere
US10519863B2 (en) * 2014-12-04 2019-12-31 United Technologies Corporation Turbine engine case attachment and a method of using the same
CN111332477B (zh) * 2020-02-21 2022-09-20 中国电子科技集团公司第二十九研究所 一种逆升压涡轮旁路控制装置及方法

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB685944A (en) * 1949-09-30 1953-01-14 Rateau Soc Improvements in jet propulsion engines
GB1211192A (en) * 1964-07-01 1970-11-04 Gen Electric Improvements in low drag exhaust nozzle and nacelle arrangement for turbofan engines
US3385064A (en) * 1966-01-07 1968-05-28 Rolls Royce Gas turbine engine
GB1135129A (en) * 1967-09-15 1968-11-27 Rolls Royce Gas turbine engine
US3496725A (en) * 1967-11-01 1970-02-24 Gen Applied Science Lab Inc Rocket action turbofan engine
GB1318748A (en) * 1970-08-11 1973-05-31 Secr Defence Gas turgine ducted fan engines for aircraft
GB1411601A (en) * 1972-03-04 1975-10-29 Rolls Royce Ducted fan gas turbine engine supported by an aircraft wing mainspar
US3978256A (en) * 1974-06-14 1976-08-31 The Boeing Company Three-dimensional monocoque open-ended annular structure
GB1533551A (en) * 1974-11-08 1978-11-29 Gen Electric Gas turbofan engines
GB1516980A (en) * 1974-12-24 1978-07-05 Rolls Royce Mounting ducted fan gas turbine engines on aircraft
US4022018A (en) * 1975-04-29 1977-05-10 General Electric Company Mounting system for a thrust generating engine
US4147029A (en) * 1976-01-02 1979-04-03 General Electric Company Long duct mixed flow gas turbine engine
JPS53114704A (en) * 1977-02-28 1978-10-06 Taiheiyo Eng Operating device of selfftravelling frame* etc*
US4227370A (en) * 1977-11-04 1980-10-14 Rolls-Royce Limited By-pass gas turbine engines

Also Published As

Publication number Publication date
GB2061389B (en) 1983-05-18
FR2467776B1 (enExample) 1984-05-18
GB2061389A (en) 1981-05-13
JPS5681227A (en) 1981-07-03
FR2467776A1 (fr) 1981-04-30
US4384453A (en) 1983-05-24
JPS5936095B2 (ja) 1984-09-01
DE3039869A1 (de) 1981-05-07

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Legal Events

Date Code Title Description
OP8 Request for examination as to paragraph 44 patent law
D2 Grant after examination
8364 No opposition during term of opposition
8327 Change in the person/name/address of the patent owner

Owner name: ROLLS-ROYCE PLC, LONDON, GB

8339 Ceased/non-payment of the annual fee