GB1321657A - Ducted fan gas turbine jet propulsion engine - Google Patents

Ducted fan gas turbine jet propulsion engine

Info

Publication number
GB1321657A
GB1321657A GB1321657DA GB1321657A GB 1321657 A GB1321657 A GB 1321657A GB 1321657D A GB1321657D A GB 1321657DA GB 1321657 A GB1321657 A GB 1321657A
Authority
GB
United Kingdom
Prior art keywords
fan
pass
passage
pass passage
turbine
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
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.)
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Publication of GB1321657A publication Critical patent/GB1321657A/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
    • F02K3/065—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 and aft fans
    • 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
    • F02K3/077—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 the plant being of the multiple flow type, i.e. having three or more flows

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

1321657 Gas turbine ducted fan engines DEFENCE SECRETARY OF STATE FOR 10 Sept 1971 [16 Sept 1970] 44178/70 Heading F1J A by-pass type gas turbine jet engine comprises compressor means, combustion chamber and turbine means, a first fan disposed upstream of the combustion chamber, a second fan, disposed downstream of the combustion chamber, an inner by-pass passage which extends substantially the whole length of the engine, and an outer annular by-pass passage which surrounds at least a portion of the inner passage, the blading of one of the fans extending across only one of the two by-pass passages, the blading of the other fan extending across both of the passages. The engine shown in Fig.1 comprises compressor 2, combustion equipment 4 and H.P. turbine 6 which drives the compressor through shaft 9. The engine comprises also an inner by-pass passage 12 and an outer by-pass passage 16 which is disposed around the upstream end of the inner by-pass passage. A front fan 20 extends across both by-pass passages 12 and 16 while a rear fan 28 extends across the inner by-pass passage 12 only. The two fans are driven by an LP turbine 22, the front fan being driven through shaft 24 and the rear fan being mounted at the tips of the LP turbine blades. In Fig. 2, the outer by-pass 30 is disposed around the downstream end of the inner by-pass passage 12 only while the rear fan 26 extends across both the inner and the outer bypass passages 12 and 30. In both engines, part of the air from the front fan passes to the compressor 2.
GB1321657D 1970-09-16 1970-09-16 Ducted fan gas turbine jet propulsion engine Expired GB1321657A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4417870 1970-09-16

Publications (1)

Publication Number Publication Date
GB1321657A true GB1321657A (en) 1973-06-27

Family

ID=10432134

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1321657D Expired GB1321657A (en) 1970-09-16 1970-09-16 Ducted fan gas turbine jet propulsion engine

Country Status (1)

Country Link
GB (1) GB1321657A (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2189844A (en) * 1986-04-30 1987-11-04 Rolls Royce Gas turbine engines
EP0950808A2 (en) * 1998-04-13 1999-10-20 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
EP0952330A2 (en) * 1998-04-13 1999-10-27 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
US6209311B1 (en) 1998-04-13 2001-04-03 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
JP2005155621A (en) * 2003-11-21 2005-06-16 General Electric Co <Ge> Rear flade type engine
ES2342586A1 (en) * 2008-04-30 2010-07-08 Futur Investment Partners, S.A. Turbopropulsor aeronautical (Machine-translation by Google Translate, not legally binding)
ES2370308A1 (en) * 2008-12-31 2011-12-14 Futur Investment Partners, S.A. Aeronautical motor. (Machine-translation by Google Translate, not legally binding)
FR3050485A1 (en) * 2016-04-26 2017-10-27 Snecma DOUBLE FLOW TURBOMACHINE
EP3617059A1 (en) * 2018-08-22 2020-03-04 Rolls-Royce plc Turbomachine
EP3623282A1 (en) * 2018-08-22 2020-03-18 Rolls-Royce plc Turbomachine
EP3623285A1 (en) * 2018-08-22 2020-03-18 Rolls-Royce plc Turbomachine
EP3623284A1 (en) * 2018-08-22 2020-03-18 Rolls-Royce plc Turbomachine
EP3623283A1 (en) * 2018-08-22 2020-03-18 Rolls-Royce plc Turbomachine

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2189844A (en) * 1986-04-30 1987-11-04 Rolls Royce Gas turbine engines
EP0950808A2 (en) * 1998-04-13 1999-10-20 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
EP0952330A2 (en) * 1998-04-13 1999-10-27 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
EP0950808A3 (en) * 1998-04-13 2000-05-24 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
EP0952330A3 (en) * 1998-04-13 2000-05-24 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
US6209311B1 (en) 1998-04-13 2001-04-03 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
JP2005155621A (en) * 2003-11-21 2005-06-16 General Electric Co <Ge> Rear flade type engine
EP1533510A3 (en) * 2003-11-21 2009-02-18 General Electric Company Two-spool variable cycle gas turbine engine
ES2342586A1 (en) * 2008-04-30 2010-07-08 Futur Investment Partners, S.A. Turbopropulsor aeronautical (Machine-translation by Google Translate, not legally binding)
ES2370308A1 (en) * 2008-12-31 2011-12-14 Futur Investment Partners, S.A. Aeronautical motor. (Machine-translation by Google Translate, not legally binding)
FR3050485A1 (en) * 2016-04-26 2017-10-27 Snecma DOUBLE FLOW TURBOMACHINE
EP3617059A1 (en) * 2018-08-22 2020-03-04 Rolls-Royce plc Turbomachine
EP3623282A1 (en) * 2018-08-22 2020-03-18 Rolls-Royce plc Turbomachine
EP3623285A1 (en) * 2018-08-22 2020-03-18 Rolls-Royce plc Turbomachine
EP3623284A1 (en) * 2018-08-22 2020-03-18 Rolls-Royce plc Turbomachine
EP3623283A1 (en) * 2018-08-22 2020-03-18 Rolls-Royce plc Turbomachine
US11247780B2 (en) 2018-08-22 2022-02-15 Rolls-Royce Plc Turbomachine having inner and outer fans with hub-tip ratios
US11306682B2 (en) 2018-08-22 2022-04-19 Rolls-Royce Plc Concentric turbomachine with trailing edge
US11313327B2 (en) 2018-08-22 2022-04-26 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371467B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine
US11371350B2 (en) 2018-08-22 2022-06-28 Rolls-Royce Plc Concentric turbomachine with electric machine

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Legal Events

Date Code Title Description
CSNS Application of which complete specification have been accepted and published, but patent is not sealed