FR1325278A - Turboréacteurs - Google Patents

Turboréacteurs

Info

Publication number
FR1325278A
FR1325278A FR898747A FR898747A FR1325278A FR 1325278 A FR1325278 A FR 1325278A FR 898747 A FR898747 A FR 898747A FR 898747 A FR898747 A FR 898747A FR 1325278 A FR1325278 A FR 1325278A
Authority
FR
France
Prior art keywords
turbojets
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
FR898747A
Other languages
English (en)
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.)
Bristol Siddeley Engines Ltd
Original Assignee
De Havilland Engine Co Ltd
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 De Havilland Engine Co Ltd filed Critical De Havilland Engine Co Ltd
Priority to FR898747A priority Critical patent/FR1325278A/fr
Application granted granted Critical
Publication of FR1325278A publication Critical patent/FR1325278A/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
    • F02K3/062—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 aft fan
    • 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)
FR898747A 1962-05-25 1962-05-25 Turboréacteurs Expired FR1325278A (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR898747A FR1325278A (fr) 1962-05-25 1962-05-25 Turboréacteurs

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR898747A FR1325278A (fr) 1962-05-25 1962-05-25 Turboréacteurs

Publications (1)

Publication Number Publication Date
FR1325278A true FR1325278A (fr) 1963-04-26

Family

ID=8779764

Family Applications (1)

Application Number Title Priority Date Filing Date
FR898747A Expired FR1325278A (fr) 1962-05-25 1962-05-25 Turboréacteurs

Country Status (1)

Country Link
FR (1) FR1325278A (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3394548A (en) * 1964-09-05 1968-07-30 Daimler Benz Ag Two-stage turbine unit
FR2622637A1 (fr) * 1987-10-22 1989-05-05 United Technologies Corp Buse d'echappement pour un dispositif de propulsion a helice propulsive
DE102008060488A1 (de) * 2008-12-05 2010-06-10 Rolls-Royce Deutschland Ltd & Co Kg Verfahren und Vorrichtung zum Betrieb eines mit Schubpropellern versehenen Turboprop-Flugtriebwerkes
US20170184020A1 (en) * 2015-12-29 2017-06-29 General Electric Company Method and system for in-line distributed propulsion
CN108367812A (zh) * 2015-07-17 2018-08-03 斯卡莱温斯知识产权公司 用于飞机的驱动装置及配备该驱动装置的飞机

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3394548A (en) * 1964-09-05 1968-07-30 Daimler Benz Ag Two-stage turbine unit
FR2622637A1 (fr) * 1987-10-22 1989-05-05 United Technologies Corp Buse d'echappement pour un dispositif de propulsion a helice propulsive
DE102008060488A1 (de) * 2008-12-05 2010-06-10 Rolls-Royce Deutschland Ltd & Co Kg Verfahren und Vorrichtung zum Betrieb eines mit Schubpropellern versehenen Turboprop-Flugtriebwerkes
US8701385B2 (en) 2008-12-05 2014-04-22 Rolls-Royce Deutschland Ltd & Co Kg Method and apparatus for the operation of a turboprop aircraft engine provided with pusher propellers
CN108367812A (zh) * 2015-07-17 2018-08-03 斯卡莱温斯知识产权公司 用于飞机的驱动装置及配备该驱动装置的飞机
US20170184020A1 (en) * 2015-12-29 2017-06-29 General Electric Company Method and system for in-line distributed propulsion
US10677158B2 (en) * 2015-12-29 2020-06-09 General Electric Company Method and system for in-line distributed propulsion

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