GB1330904A - Gas turbine jet propulsion engines - Google Patents

Gas turbine jet propulsion engines

Info

Publication number
GB1330904A
GB1330904A GB1330904DA GB1330904A GB 1330904 A GB1330904 A GB 1330904A GB 1330904D A GB1330904D A GB 1330904DA GB 1330904 A GB1330904 A GB 1330904A
Authority
GB
United Kingdom
Prior art keywords
turbine
fan
duct
engine
gas
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 GB1330904A publication Critical patent/GB1330904A/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
    • F02K3/077—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
    • 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

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

1330904 Gas turbine ducted fan engines DEFENCE SECRETARY OF STATE FOR 19 April 1971 [10 Feb 1970] 6402/70 Heading F1J A gas turbine engine comprises a gas generator, means for directing gases issuing from the gas generator to drive a turbine which is connected to drive a fan, a duct extending axially through the fan-driving turbine, and valve means disposed within the duct and selectively operable for bleeding some of the gases from the generator away from the fan driving turbine and through the duct, the valve means being normally closed so that gases are normally prevented from flowing therethrough. Fig. 2 shows the rearward part only of a gas turbine engine having an aft fan, the blades 31 of which are mounted on the tips of the blades 42 of a turbine. The turbine is driven by the hot gases discharged by a by-pass engine, not shown. There is a duct 34 through the turbine, and a butterfly valve which regulates the amount of gas passing through the duct, the valve being remotely controlled from the pilot's panel. Reduction of the gas flow through the turbine (by 10-20%) reduces the fan speed and hence noise from the fan, in order to reduce the overall engine noise to an acceptable value during the landing approach. The by-pass engine continues to run at a fairly large throttle opening so that there is no danger of the engine going out and full power can be quickly restored by closing the butterfly valve. In a modification, the valve is replaced by a slidable sleeve having ports which can be brought into alignment with ports in the wall of the duct.
GB1330904D 1971-04-19 1971-04-19 Gas turbine jet propulsion engines Expired GB1330904A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB640270 1971-04-19

Publications (1)

Publication Number Publication Date
GB1330904A true GB1330904A (en) 1973-09-19

Family

ID=9813869

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1330904D Expired GB1330904A (en) 1971-04-19 1971-04-19 Gas turbine jet propulsion engines

Country Status (1)

Country Link
GB (1) GB1330904A (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2192234A (en) * 1986-07-02 1988-01-06 Rolls Royce Plc A turbofan gas turbine engine
US4731991A (en) * 1985-10-08 1988-03-22 Rolls-Royce Plc Gas turbine engine thrust reverser
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
EP1533510A2 (en) 2003-11-21 2005-05-25 General Electric Company Two-spool variable cycle gas turbine engine
EP1607612A1 (en) * 2004-05-28 2005-12-21 Rolls-Royce Plc Gas turbine engine
JP2006132533A (en) * 2004-11-05 2006-05-25 General Electric Co <Ge> Flade type gas turbine engine and aircraft
DE102010009477A1 (en) * 2010-02-26 2011-09-01 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine engine
CN102305152A (en) * 2011-05-20 2012-01-04 中国科学院工程热物理研究所 Hybrid exhaust aircraft engine
FR2972769A1 (en) * 2011-03-16 2012-09-21 Snecma Triple- flow turbine engine for aircraft, has mixer arranged downstream of combustion chamber and upstream of turbine wheel, mixing primary flow and secondary flow and sending mixture to turbine wheel
EP3239511A1 (en) * 2016-04-27 2017-11-01 General Electric Company Turbofan assembly and method of assembling
WO2018009420A1 (en) * 2016-07-06 2018-01-11 General Electric Company Turbine engine and method of assembling
CN110005544A (en) * 2019-05-12 2019-07-12 西北工业大学 From driving by-pass air duct annular flabellum compression set

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4731991A (en) * 1985-10-08 1988-03-22 Rolls-Royce Plc Gas turbine engine thrust reverser
GB2192234A (en) * 1986-07-02 1988-01-06 Rolls Royce Plc A turbofan gas turbine engine
US4934139A (en) * 1986-07-02 1990-06-19 Rolls-Royce Plc Turbofan gas turbine engine
GB2192234B (en) * 1986-07-02 1991-04-17 Rolls Royce Plc A turbofan gas turbine engine
EP0952330A3 (en) * 1998-04-13 2000-05-24 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
US6209311B1 (en) 1998-04-13 2001-04-03 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
EP0950808A2 (en) * 1998-04-13 1999-10-20 Nikkiso Company, Ltd. Turbofan engine including fans with reduced speed
EP1533510A2 (en) 2003-11-21 2005-05-25 General Electric Company Two-spool variable cycle gas turbine engine
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
US7500352B2 (en) 2004-05-28 2009-03-10 Rolls-Royce Plc Gas turbine engine
EP1607612A1 (en) * 2004-05-28 2005-12-21 Rolls-Royce Plc Gas turbine engine
JP2006132533A (en) * 2004-11-05 2006-05-25 General Electric Co <Ge> Flade type gas turbine engine and aircraft
DE102010009477A1 (en) * 2010-02-26 2011-09-01 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine engine
US8720208B2 (en) 2010-02-26 2014-05-13 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine engine
FR2972769A1 (en) * 2011-03-16 2012-09-21 Snecma Triple- flow turbine engine for aircraft, has mixer arranged downstream of combustion chamber and upstream of turbine wheel, mixing primary flow and secondary flow and sending mixture to turbine wheel
CN102305152A (en) * 2011-05-20 2012-01-04 中国科学院工程热物理研究所 Hybrid exhaust aircraft engine
EP3239511A1 (en) * 2016-04-27 2017-11-01 General Electric Company Turbofan assembly and method of assembling
JP2017198208A (en) * 2016-04-27 2017-11-02 ゼネラル・エレクトリック・カンパニイ Turbofan assembly and method of assembling
WO2018009420A1 (en) * 2016-07-06 2018-01-11 General Electric Company Turbine engine and method of assembling
US10563516B2 (en) 2016-07-06 2020-02-18 General Electric Company Turbine engine and method of assembling
CN110005544A (en) * 2019-05-12 2019-07-12 西北工业大学 From driving by-pass air duct annular flabellum compression set

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees