GB1421153A - Propulsion nozzle for ducted fan gas turbine jet propulsion engines - Google Patents

Propulsion nozzle for ducted fan gas turbine jet propulsion engines

Info

Publication number
GB1421153A
GB1421153A GB1411272A GB1411272A GB1421153A GB 1421153 A GB1421153 A GB 1421153A GB 1411272 A GB1411272 A GB 1411272A GB 1411272 A GB1411272 A GB 1411272A GB 1421153 A GB1421153 A GB 1421153A
Authority
GB
United Kingdom
Prior art keywords
flaps
downstream
casing
gas turbine
ducted fan
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
GB1411272A
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 GB1411272A priority Critical patent/GB1421153A/en
Publication of GB1421153A publication Critical patent/GB1421153A/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
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1261—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a substantially axially movable structure

Abstract

1421153 Deflecting propulsion jets ROLLSROYCE (1971) Ltd 22 March 1973 [25 March 1972] 14112/72 Heading B7G A ducted fan gas turbine engine has a fan (not shown) positioned at the front end of an annular duct 7 formed between the outer casing 6 of a core engine and an outer cowl 8, the cowl 8 comprising a fixed upstream portion 17 and a translatable downstream portion 18. A cascade of flow deflecting vanes 20 is connected to the upstream portion and is masked, in the position shown in Fig. 2, by the downstream portion 18 which is sealed at 28 to the upstream portion. The downstream end of portion 18 terminates in a ring of flaps 14 pivoted thereto, each flap being pivotally connected at its midpoint to one end of a link 16, pivoted at its other end to casing 6. Screw jacks 32, one for each flap, are operated by a single motor 34 and each jack carries a traveller nut 38 secured to portion 18. In operation, in the initial position shown in Fig. 2 the flaps 14 are in the normal cruise position. For take-off or landing the jack 32 is operated to translate portion 18 downstream to a position in which flaps 14 are substantially parallel to the engine axis and for thrust reversal the portion 18 is moved fully downstream causing flaps 14 to seat on casing 6 to close the aft end of the duct and vanes 20 are fully exposed thereby permitting the forward flow of air. In a further embodiment (Fig. 6, not shown) the radially inner ends of the links 16 are each mounted on an adjustable pivot to enable the flaps 14 to be moved without translation of portion 14.
GB1411272A 1972-03-25 1972-03-25 Propulsion nozzle for ducted fan gas turbine jet propulsion engines Expired GB1421153A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1411272A GB1421153A (en) 1972-03-25 1972-03-25 Propulsion nozzle for ducted fan gas turbine jet propulsion engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1411272A GB1421153A (en) 1972-03-25 1972-03-25 Propulsion nozzle for ducted fan gas turbine jet propulsion engines

Publications (1)

Publication Number Publication Date
GB1421153A true GB1421153A (en) 1976-01-14

Family

ID=10035212

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1411272A Expired GB1421153A (en) 1972-03-25 1972-03-25 Propulsion nozzle for ducted fan gas turbine jet propulsion engines

Country Status (1)

Country Link
GB (1) GB1421153A (en)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2588312A1 (en) * 1985-10-08 1987-04-10 Rolls Royce PUSH INVERTER FOR A GAS TURBINE ENGINE
US4716724A (en) * 1986-04-25 1988-01-05 Rolls-Royce Plc Gas turbine engine powerplant with flow control devices
EP0779429A2 (en) * 1995-12-14 1997-06-18 United Technologies Corporation Variable area exhaust nozzle for turbofan
US5778659A (en) * 1994-10-20 1998-07-14 United Technologies Corporation Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
US5806302A (en) * 1996-09-24 1998-09-15 Rohr, Inc. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser
EP0884470A1 (en) * 1997-06-12 1998-12-16 Hispano-Suiza Aérostructures Thrust reverser for a turbofan with variable outlet area
FR2815672A1 (en) * 2000-10-19 2002-04-26 Short Brothers Plc Propulsive power unit, for aeroplane, has power inverter structure such that, when power flow is inverted, the redirection zone includes a cavity, which develops a counter pressure, which aids inversion.
GB2372729A (en) * 2001-03-03 2002-09-04 Rolls Royce Plc Thrust reverser arrangement with means for reducing noise
FR2925607A1 (en) * 2007-12-21 2009-06-26 Aircelle Sa NACELLE FOR AIRCRAFT ENGINE WITH VARIABLE SECTION TUBE
FR2929998A1 (en) * 2008-04-14 2009-10-16 Aircelle Sa DOUBLE FLOW TURBOREACTOR NACELLE
FR2930762A1 (en) * 2008-04-30 2009-11-06 Aircelle Sa DOWNSTAGE ASSEMBLY OF A TURBOREACTOR NACELLE
FR2934327A1 (en) * 2008-07-28 2010-01-29 Aircelle Sa PUSH REVERSING DEVICE
FR2934326A1 (en) * 2008-07-28 2010-01-29 Aircelle Sa PUSH REVERSING DEVICE
FR2939477A1 (en) * 2008-12-10 2010-06-11 Aircelle Sa VANABLE TUBE SECTION TURBOELECTOR BOOM
WO2010109109A1 (en) * 2009-03-27 2010-09-30 Aircelle Bent connecting rod fitted with at least one self-aligning means
US20120031995A1 (en) * 2009-04-16 2012-02-09 Sagem Defense Securite Actuator system for a mobile panel of a nacelle of a turbojet
EP3249203A1 (en) * 2016-05-24 2017-11-29 Rolls-Royce plc Aircraft gas turbine engine nacelle
WO2020249896A1 (en) * 2019-06-14 2020-12-17 Safran Nacelles Mobile-cowl thrust reverser comprising a thrust-reduction mechanism that is independent of the mobile cowl
US11293376B2 (en) * 2019-01-22 2022-04-05 Airbus Operations Sas Jet engine nacelle comprising a mobile assembly and a reinforced fixed structure

Cited By (45)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2588312A1 (en) * 1985-10-08 1987-04-10 Rolls Royce PUSH INVERTER FOR A GAS TURBINE ENGINE
US4716724A (en) * 1986-04-25 1988-01-05 Rolls-Royce Plc Gas turbine engine powerplant with flow control devices
US5778659A (en) * 1994-10-20 1998-07-14 United Technologies Corporation Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems
EP0779429A3 (en) * 1995-12-14 1999-04-21 United Technologies Corporation Variable area exhaust nozzle for turbofan
EP0779429A2 (en) * 1995-12-14 1997-06-18 United Technologies Corporation Variable area exhaust nozzle for turbofan
US5806302A (en) * 1996-09-24 1998-09-15 Rohr, Inc. Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser
WO1998057056A1 (en) * 1997-06-12 1998-12-17 Hispano-Suiza Aerostructures Turbojet thrust reverser having doors with variable exhaust section
FR2764643A1 (en) * 1997-06-12 1998-12-18 Hispano Suiza Sa PUSH INVERTER WITH TURBOREACTOR DOORS WITH VARIABLE EJECTION SECTION
EP0884470A1 (en) * 1997-06-12 1998-12-16 Hispano-Suiza Aérostructures Thrust reverser for a turbofan with variable outlet area
US5996937A (en) * 1997-06-12 1999-12-07 Societe Hispano Suiza Aerostructures Variable cross-section turbofan exhaust duct with door type thrust reverser for aircraft
FR2815672A1 (en) * 2000-10-19 2002-04-26 Short Brothers Plc Propulsive power unit, for aeroplane, has power inverter structure such that, when power flow is inverted, the redirection zone includes a cavity, which develops a counter pressure, which aids inversion.
GB2372729A (en) * 2001-03-03 2002-09-04 Rolls Royce Plc Thrust reverser arrangement with means for reducing noise
FR2925607A1 (en) * 2007-12-21 2009-06-26 Aircelle Sa NACELLE FOR AIRCRAFT ENGINE WITH VARIABLE SECTION TUBE
WO2009103905A1 (en) * 2007-12-21 2009-08-27 Aircelle Nacelle for aircraft engine having a nozzle with a variable section
US9133789B2 (en) 2007-12-21 2015-09-15 Aircelle Nacelle for aircraft engine having a nozzle with a variable section
CN101896712A (en) * 2007-12-21 2010-11-24 埃尔塞乐公司 Nacelle for aircraft engine having a nozzle with a variable section
RU2494273C2 (en) * 2007-12-21 2013-09-27 Эрсель Aircraft nacelle with adjustable-section nozzle
RU2499904C2 (en) * 2008-04-14 2013-11-27 Эрсель Bypass turbojet nacelle
FR2929998A1 (en) * 2008-04-14 2009-10-16 Aircelle Sa DOUBLE FLOW TURBOREACTOR NACELLE
WO2009136096A3 (en) * 2008-04-14 2010-01-07 Aircelle Bypass turbojet engine nacelle
WO2009136096A2 (en) * 2008-04-14 2009-11-12 Aircelle Bypass turbojet engine nacelle
CN102007284A (en) * 2008-04-14 2011-04-06 埃尔塞乐公司 Bypass turbojet engine nacelle
WO2009138681A3 (en) * 2008-04-30 2010-05-14 Aircelle Turbojet engine nacelle downstream assembly
WO2009138681A2 (en) * 2008-04-30 2009-11-19 Aircelle Turbojet engine nacelle downstream assembly
FR2930762A1 (en) * 2008-04-30 2009-11-06 Aircelle Sa DOWNSTAGE ASSEMBLY OF A TURBOREACTOR NACELLE
FR2934326A1 (en) * 2008-07-28 2010-01-29 Aircelle Sa PUSH REVERSING DEVICE
WO2010012874A3 (en) * 2008-07-28 2010-03-25 Aircelle Thrust reverser device
WO2010012878A1 (en) * 2008-07-28 2010-02-04 Aircelle Thrust reverser device
FR2934327A1 (en) * 2008-07-28 2010-01-29 Aircelle Sa PUSH REVERSING DEVICE
WO2010012874A2 (en) * 2008-07-28 2010-02-04 Aircelle Thrust reverser device
FR2939477A1 (en) * 2008-12-10 2010-06-11 Aircelle Sa VANABLE TUBE SECTION TURBOELECTOR BOOM
WO2010066957A1 (en) * 2008-12-10 2010-06-17 Aircelle A turbojet engine nacelle with variable nozzle section
WO2010109109A1 (en) * 2009-03-27 2010-09-30 Aircelle Bent connecting rod fitted with at least one self-aligning means
RU2524831C2 (en) * 2009-03-27 2014-08-10 Эрсель Crooked connecting rod fitted by at least one self-alignment element
FR2943749A1 (en) * 2009-03-27 2010-10-01 Aircelle Sa RIBBON EQUIPPED WITH AT LEAST ONE MEANS OF SELF-ALIGNMENT
US9212689B2 (en) 2009-03-27 2015-12-15 Aircelle Bent connecting rod fitted with at least one self-aligning means
US20120031995A1 (en) * 2009-04-16 2012-02-09 Sagem Defense Securite Actuator system for a mobile panel of a nacelle of a turbojet
US8991151B2 (en) * 2009-04-16 2015-03-31 Aircelle Actuator system for a mobile panel of a nacelle of a turbojet
EP3249203A1 (en) * 2016-05-24 2017-11-29 Rolls-Royce plc Aircraft gas turbine engine nacelle
US10662895B2 (en) 2016-05-24 2020-05-26 Rolls -Royce Plc Aircraft gas turbine engine nacelle
US11293376B2 (en) * 2019-01-22 2022-04-05 Airbus Operations Sas Jet engine nacelle comprising a mobile assembly and a reinforced fixed structure
WO2020249896A1 (en) * 2019-06-14 2020-12-17 Safran Nacelles Mobile-cowl thrust reverser comprising a thrust-reduction mechanism that is independent of the mobile cowl
FR3097275A1 (en) * 2019-06-14 2020-12-18 Safran Nacelles Movable cowl thrust reverser comprising a thrust reduction mechanism independent of the movable cowl
CN114051557A (en) * 2019-06-14 2022-02-15 赛峰短舱公司 Movable cowl thrust reverser including a thrust reducing mechanism independent of the movable cowl
US11939933B2 (en) 2019-06-14 2024-03-26 Safran Nacelles Mobile-cowl thrust reverser comprising a thrust-reduction mechanism that is independent of the mobile cowl

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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