FR2039215A1 - - Google Patents

Info

Publication number
FR2039215A1
FR2039215A1 FR7013602A FR7013602A FR2039215A1 FR 2039215 A1 FR2039215 A1 FR 2039215A1 FR 7013602 A FR7013602 A FR 7013602A FR 7013602 A FR7013602 A FR 7013602A FR 2039215 A1 FR2039215 A1 FR 2039215A1
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.)
Granted
Application number
FR7013602A
Other languages
French (fr)
Other versions
FR2039215B1 (cs
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 FR2039215A1 publication Critical patent/FR2039215A1/fr
Application granted granted Critical
Publication of FR2039215B1 publication Critical patent/FR2039215B1/fr
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
    • 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)
FR7013602A 1969-04-16 1970-04-15 Expired FR2039215B1 (cs)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1936069 1969-04-16

Publications (2)

Publication Number Publication Date
FR2039215A1 true FR2039215A1 (cs) 1971-01-15
FR2039215B1 FR2039215B1 (cs) 1974-11-08

Family

ID=10128051

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7013602A Expired FR2039215B1 (cs) 1969-04-16 1970-04-15

Country Status (4)

Country Link
US (1) US3620020A (cs)
DE (1) DE2018077C3 (cs)
FR (1) FR2039215B1 (cs)
GB (1) GB1257497A (cs)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3747343A (en) * 1972-02-10 1973-07-24 United Aircraft Corp Low noise prop-fan
US3861139A (en) * 1973-02-12 1975-01-21 Gen Electric Turbofan engine having counterrotating compressor and turbine elements and unique fan disposition
GB2382382B (en) 2001-11-23 2005-08-10 Rolls Royce Plc A fan for a turbofan gas turbine engine
GB0809759D0 (en) * 2008-05-30 2008-07-09 Rolls Royce Plc Gas turbine engine
US8166748B2 (en) * 2008-11-21 2012-05-01 General Electric Company Gas turbine engine booster having rotatable radially inwardly extending blades and non-rotatable vanes
US20150345426A1 (en) 2012-01-31 2015-12-03 United Technologies Corporation Geared turbofan gas turbine engine architecture
US8935913B2 (en) 2012-01-31 2015-01-20 United Technologies Corporation Geared turbofan gas turbine engine architecture
US10287914B2 (en) 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US10036350B2 (en) 2012-04-30 2018-07-31 United Technologies Corporation Geared turbofan with three turbines all co-rotating
DE102014226696A1 (de) * 2014-12-19 2016-06-23 Rolls-Royce Deutschland Ltd & Co Kg Vorverdichtervorrichtung, Nachrüstsatz und Flugzeugtriebwerk
CA2923331A1 (en) * 2015-03-19 2016-09-19 David P. Houston Geared turbofan gas turbine engine architecture

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
NEANT *

Also Published As

Publication number Publication date
US3620020A (en) 1971-11-16
DE2018077A1 (de) 1970-11-19
GB1257497A (cs) 1971-12-22
DE2018077C3 (de) 1975-02-06
FR2039215B1 (cs) 1974-11-08
DE2018077B2 (de) 1974-06-20

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Legal Events

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