GB2014663A - Gas Turbine Ducted Fan Engine - Google Patents

Gas Turbine Ducted Fan Engine

Info

Publication number
GB2014663A
GB2014663A GB7901490A GB7901490A GB2014663A GB 2014663 A GB2014663 A GB 2014663A GB 7901490 A GB7901490 A GB 7901490A GB 7901490 A GB7901490 A GB 7901490A GB 2014663 A GB2014663 A GB 2014663A
Authority
GB
United Kingdom
Prior art keywords
compressor
ducted fan
gas turbine
fan engine
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.)
Granted
Application number
GB7901490A
Other versions
GB2014663B (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)

Abstract

In a ducted fan engine including a multi-stage axial flow compressor 15, at least the most upstream stage 30 of the compressor is adapted to compress fluid in excess of that required by the remainder of the compressor, the excess fluid being continuously discharged through at least one aperture 29 within the compressor casing into the fan duct of the engine. The aperture 29 may be a circumferentially extending slot, including means to allow variation of its cross-sectional area. <IMAGE>
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 true GB2014663A (en) 1979-08-30
GB2014663B 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)

Cited By (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
EP1249618A1 (en) * 2001-04-12 2002-10-16 Snecma Moteurs Bleed system for a turbofan with simplified control
WO2008045074A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
CN113847163A (en) * 2021-10-25 2021-12-28 中国航发沈阳发动机研究所 Jet system of outer duct of fan of aircraft engine

Cited By (8)

* 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
EP1249618A1 (en) * 2001-04-12 2002-10-16 Snecma Moteurs Bleed system for a turbofan with simplified control
FR2823532A1 (en) * 2001-04-12 2002-10-18 Snecma Moteurs DISCHARGE SYSTEM FOR A TURBO-JET OR TURBO-PROPELLER WITH SIMPLIFIED CONTROL
US6622475B2 (en) 2001-04-12 2003-09-23 Snecma Moteurs Bleed system driven in simplified manner for a turbojet or turboprop engine
WO2008045074A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
US8480350B2 (en) 2006-10-12 2013-07-09 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
CN113847163A (en) * 2021-10-25 2021-12-28 中国航发沈阳发动机研究所 Jet system of outer duct of fan of aircraft engine
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
GB2014663B (en) 1982-05-06

Similar Documents

Publication Publication Date Title
MX154244A (en) IMPROVEMENTS TO DIFFUSER FOR CENTRIFUGAL TURBOMACHINES, FOR EXAMPLE GAS COMPRESSORS
NL7502219A (en) TURBOFAN ENGINE WITH ADJUSTABLE BYPASS AND VARIABLE CYCLE.
SE7906912L (en) VACUUM CLEANER
GB1549422A (en) Axial flow gas turbine engine compressor
SE7901025L (en) AXIAL FLEX DEVICE
DE68928865T2 (en) turbocharger
SE7809557L (en) CO-AXIAL ROD CONNECTION
GB2234295B (en) Gas turbine engine compressor assembly
FR2661944B1 (en) TURBOMACHINE FLOOR WITH REDUCED SECONDARY LOSSES.
GB2014663A (en) Gas Turbine Ducted Fan Engine
GB2063366A (en) Turbocharger and adaptions thereof
GB2097863B (en) Variable air inlet for gas turbine engine
JPS5377319A (en) Axial-flow fan
FR2360758A1 (en) Gas turbine for aviation propulsion - has differential gear between turbine and compressor and blower drive shafts
GB2074659A (en) Steam-and-gas turbine plant
JPS5587892A (en) Pump
JPS557936A (en) Stage structure of axial-flow turbine
GB935231A (en) Radial flow turbines
GB1246955A (en) Aircraft having forward thrust and/or lift fans
JPS52142313A (en) Voltex blower
JPS5638526A (en) Gear box for gas turbine
FR2417644A1 (en) Gas turbine ducted fan engine - has multistage axial flow compressor with initial stage over-pressurising, with excess fluid discharged via variable area ports into duct
JPS5691131A (en) Cooling device for liner of gas-turbine combustor
JPS5412041A (en) Exhaust gas reflux mechanism of engine with turbo-charger
JPS5537524A (en) Centrifugal air blower

Legal Events

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