FR2025182A1 - - Google Patents

Info

Publication number
FR2025182A1
FR2025182A1 FR6941531A FR6941531A FR2025182A1 FR 2025182 A1 FR2025182 A1 FR 2025182A1 FR 6941531 A FR6941531 A FR 6941531A FR 6941531 A FR6941531 A FR 6941531A FR 2025182 A1 FR2025182 A1 FR 2025182A1
Authority
FR
France
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.)
Withdrawn
Application number
FR6941531A
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 FR2025182A1 publication Critical patent/FR2025182A1/fr
Withdrawn legal-status Critical Current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
    • F02K3/065—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 and aft fans
FR6941531A 1968-12-04 1969-12-02 Withdrawn FR2025182A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB5759968 1968-12-04

Publications (1)

Publication Number Publication Date
FR2025182A1 true FR2025182A1 (fr) 1970-09-04

Family

ID=10479561

Family Applications (1)

Application Number Title Priority Date Filing Date
FR6941531A Withdrawn FR2025182A1 (fr) 1968-12-04 1969-12-02

Country Status (4)

Country Link
US (1) US3620009A (fr)
DE (1) DE1960479B2 (fr)
FR (1) FR2025182A1 (fr)
GB (1) GB1229007A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0022692A1 (fr) * 1979-07-16 1981-01-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turboréacteur multiflux à taux de dilution pilotable

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3861139A (en) * 1973-02-12 1975-01-21 Gen Electric Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition
US4611464A (en) * 1984-05-02 1986-09-16 United Technologies Corporation Rotor assembly for a gas turbine engine and method of disassembly
US4685286A (en) * 1984-05-02 1987-08-11 United Technologies Corporation Method of disassembly for a gas turbine engine
US4704862A (en) * 1985-05-29 1987-11-10 United Technologies Corporation Ducted prop engine
US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine
US4790133A (en) * 1986-08-29 1988-12-13 General Electric Company High bypass ratio counterrotating turbofan engine
US4900221A (en) * 1988-12-16 1990-02-13 General Electric Company Jet engine fan and compressor bearing support
FR2645911B1 (fr) * 1989-04-18 1991-06-07 Snecma Moteur a grand taux de dilution a soufflante amont et soufflante aval
EP1777379A3 (fr) * 2003-07-29 2011-03-09 Pratt & Whitney Canada Corp. Enveloppe de réacteur à double flux et procédé de fabrication
US7370467B2 (en) * 2003-07-29 2008-05-13 Pratt & Whitney Canada Corp. Turbofan case and method of making
EP1607612B1 (fr) * 2004-05-28 2009-03-04 Rolls-Royce Plc Turbine à gaz
FR2908452A1 (fr) * 2006-11-15 2008-05-16 Snecma Sa Dispositif de fixation de stator de turbine libre par double centrage.
GB0911100D0 (en) 2009-06-29 2009-08-12 Rolls Royce Plc Propulsive fan system
FR2966522B1 (fr) * 2010-10-26 2015-04-24 Snecma Turbomachine a double soufflante et triple flux
US9498850B2 (en) 2012-03-27 2016-11-22 Pratt & Whitney Canada Corp. Structural case for aircraft gas turbine engine
GB201510167D0 (en) * 2015-06-11 2015-07-29 Rolls Royce Plc Gas turbine engine
US10711702B2 (en) * 2015-08-18 2020-07-14 General Electric Company Mixed flow turbocore
GB2603148A (en) * 2021-01-28 2022-08-03 Rolls Royce Plc Gas turbine engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0022692A1 (fr) * 1979-07-16 1981-01-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Turboréacteur multiflux à taux de dilution pilotable

Also Published As

Publication number Publication date
DE1960479B2 (de) 1976-11-18
GB1229007A (fr) 1971-04-21
DE1960479A1 (de) 1970-08-06
US3620009A (en) 1971-11-16

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Legal Events

Date Code Title Description
TP Transmission of property
TP Transmission of property
TP Transmission of property
ST Notification of lapse