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GB1415509A - Ducted fan gas turbine jet propulsion engines - Google Patents

Ducted fan gas turbine jet propulsion engines

Info

Publication number
GB1415509A
GB1415509A GB3511672A GB3511672A GB1415509A GB 1415509 A GB1415509 A GB 1415509A GB 3511672 A GB3511672 A GB 3511672A GB 3511672 A GB3511672 A GB 3511672A GB 1415509 A GB1415509 A GB 1415509A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
valve
reheat
valves
jet pipe
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
GB3511672A
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 GB3511672A priority Critical patent/GB1415509A/en
Priority to DE19732338046 priority patent/DE2338046C3/en
Publication of GB1415509A publication Critical patent/GB1415509A/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
    • F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)

Abstract

1415509 Gas turbine ducted-fan jet engine ROLLS-ROYCE (1971) Ltd 18 Sept 1973 [27 July 1972] 35116/72 Heading F1J A gas turbine jet engine of the ducted-fan type for aircraft includes a jet pipe 14 with a fixed outlet area nozzle and reheat equipment 40 in the jet pipe, the fan duct 18 being provided with angularly adjustable nozzles 24 (vane cascades as shown), having an associated axially slidable valve 28 and being disconnectable from the jet pipe 14 by means of flap valves 38 operated in conjunction with valve 28 so that the engine operates either (a) with reheat, when valves 38 are closed and valve 28 open, or (b) without reheat, when valve 28 is closed and valves 38 open. Vanes 24 may be rotated to various positions to provide, e.g. rearward or downward thrust. The vanes may be in the form of angularly adjustable elbow members.
GB3511672A 1972-07-27 1972-07-27 Ducted fan gas turbine jet propulsion engines Expired GB1415509A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB3511672A GB1415509A (en) 1972-07-27 1972-07-27 Ducted fan gas turbine jet propulsion engines
DE19732338046 DE2338046C3 (en) 1972-07-27 1973-07-26 Bypass gas turbine jet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3511672A GB1415509A (en) 1972-07-27 1972-07-27 Ducted fan gas turbine jet propulsion engines

Publications (1)

Publication Number Publication Date
GB1415509A true GB1415509A (en) 1975-11-26

Family

ID=10374013

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3511672A Expired GB1415509A (en) 1972-07-27 1972-07-27 Ducted fan gas turbine jet propulsion engines

Country Status (1)

Country Link
GB (1) GB1415509A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4732535A (en) * 1986-01-25 1988-03-22 Rolls-Royce Plc Fluid flow reversing apparatus
GB2280223A (en) * 1988-06-28 1995-01-25 Rolls Royce Plc Valve for diverting fluid flows in turbomachines
US5417055A (en) * 1988-06-28 1995-05-23 Rolls-Royce Plc Valve for diverting fluid flows in turbomachines
GB2305976A (en) * 1981-12-21 1997-04-23 British Aerospace Jet propulsion powerplants
CN103429880A (en) * 2011-03-14 2013-12-04 斯奈克玛 Turbomachine with fan(s) for aircraft, with mobile jet nozzle
CN108252935A (en) * 2016-12-29 2018-07-06 上海鼓风机厂有限公司 Multistage culvert type axial flow compressor

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2305976A (en) * 1981-12-21 1997-04-23 British Aerospace Jet propulsion powerplants
GB2305976B (en) * 1981-12-21 1998-01-07 British Aerospace Jet propulsion powerplants
US4732535A (en) * 1986-01-25 1988-03-22 Rolls-Royce Plc Fluid flow reversing apparatus
GB2280223A (en) * 1988-06-28 1995-01-25 Rolls Royce Plc Valve for diverting fluid flows in turbomachines
US5417055A (en) * 1988-06-28 1995-05-23 Rolls-Royce Plc Valve for diverting fluid flows in turbomachines
GB2280223B (en) * 1988-06-28 1995-06-28 Rolls Royce Plc Valve for diverting fluid flows in a variable cycle gas turbine engine
CN103429880A (en) * 2011-03-14 2013-12-04 斯奈克玛 Turbomachine with fan(s) for aircraft, with mobile jet nozzle
CN103429880B (en) * 2011-03-14 2015-12-02 斯奈克玛 There is aircraft fan, there is the turbines of moving nozzle
CN108252935A (en) * 2016-12-29 2018-07-06 上海鼓风机厂有限公司 Multistage culvert type axial flow compressor

Also Published As

Publication number Publication date
DE2338046B2 (en) 1976-01-29
DE2338046A1 (en) 1974-02-14

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Legal Events

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