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GB2014663B - Gas turbine ducted fan engine - Google Patents

Gas turbine ducted fan engine

Info

Publication number
GB2014663B
GB2014663B GB7901490A GB7901490A GB2014663B GB 2014663 B GB2014663 B GB 2014663B GB 7901490 A GB7901490 A GB 7901490A GB 7901490 A GB7901490 A GB 7901490A GB 2014663 B GB2014663 B GB 2014663B
Authority
GB
United Kingdom
Prior art keywords
gas turbine
ducted fan
fan engine
turbine ducted
engine
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
GB7901490A
Other versions
GB2014663A (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.)
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
Priority to GB7901490A priority Critical patent/GB2014663B/en
Publication of GB2014663A publication Critical patent/GB2014663A/en
Application granted granted Critical
Publication of GB2014663B publication Critical patent/GB2014663B/en
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)
GB7901490A 1978-02-18 1979-01-15 Gas turbine ducted fan engine Expired GB2014663B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7901490A GB2014663B (en) 1978-02-18 1979-01-15 Gas turbine ducted fan engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB655778 1978-02-18
GB7901490A GB2014663B (en) 1978-02-18 1979-01-15 Gas turbine ducted fan engine

Publications (2)

Publication Number Publication Date
GB2014663A GB2014663A (en) 1979-08-30
GB2014663B true GB2014663B (en) 1982-05-06

Family

ID=26240782

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7901490A Expired GB2014663B (en) 1978-02-18 1979-01-15 Gas turbine ducted fan engine

Country Status (1)

Country Link
GB (1) GB2014663B (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4463552A (en) * 1981-12-14 1984-08-07 United Technologies Corporation Combined surge bleed and dust removal system for a fan-jet engine
FR2823532B1 (en) * 2001-04-12 2003-07-18 Snecma Moteurs DISCHARGE SYSTEM FOR A TURBO-JET OR TURBO-PROPELLER WITH SIMPLIFIED CONTROL
EP2426342B1 (en) * 2006-10-12 2018-02-28 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
CN113847163B (en) * 2021-10-25 2024-02-23 中国航发沈阳发动机研究所 Outer duct injection system of aeroengine fan

Also Published As

Publication number Publication date
GB2014663A (en) 1979-08-30

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Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee