GB835134A - Noise suppression nozzle with thrust reversal provision for jet propulsion engines - Google Patents

Noise suppression nozzle with thrust reversal provision for jet propulsion engines

Info

Publication number
GB835134A
GB835134A GB2502/57A GB250257A GB835134A GB 835134 A GB835134 A GB 835134A GB 2502/57 A GB2502/57 A GB 2502/57A GB 250257 A GB250257 A GB 250257A GB 835134 A GB835134 A GB 835134A
Authority
GB
United Kingdom
Prior art keywords
jet
members
sleeve
housings
apertures
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
GB2502/57A
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.)
Boeing Co
Original Assignee
Boeing Co
Boeing Airplane Co
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 Boeing Co, Boeing Airplane Co filed Critical Boeing Co
Publication of GB835134A publication Critical patent/GB835134A/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
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet

Abstract

835,134. Controlling jet-propelled aircraft. BOEING AIRPLANE CO. Jan. 23, 1957 [Feb. 7, 1956], No. 2502/57. Class 4. For a jet propulsion engine C, jet deflection means, which is associated with members for dividing the jet into a plurality of separate streams for noise suppression, comprises a fixed nozzle part 10 formed with a coaxial extension 10a formed with a plurality of circumferentially spaced apertures 10b, the part 10a being surrounded by a relatively rotatable sleeve 22 also formed with apertures 22a which, by rotation of the sleeve, may be brought in to and out of registry with the apertures 10b. The members 18 that divide the jet are supported between the part 10 and a central nozzle part 16 and are extended rearwardly by housings 26 mounted on a rotatable central core 28 which forms a faired extension of part 16. Each housing 26 is segmental in shape when viewed axially of the nozzle and each encloses a curved fairing 24. The sleeve 22 is provided with a pin 38 which engages a cam slot in a bellcrank 30, actuated by a jack 42. Operation of the jack causes rotation of sleeve 22 from one position in which the housings 26 form faired extensions of members 18 and the jet unimpeded passage between such members, to another position in which housings 26 and fairings 24 block the passages between members 18 and deflect the jet outwardly and forwardly. Specification 831,152 is referred to. Reference has been directed by the Comptroller to Specification 783,228.
GB2502/57A 1956-02-07 1957-01-23 Noise suppression nozzle with thrust reversal provision for jet propulsion engines Expired GB835134A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US835134XA 1956-02-07 1956-02-07

Publications (1)

Publication Number Publication Date
GB835134A true GB835134A (en) 1960-05-18

Family

ID=22178810

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2502/57A Expired GB835134A (en) 1956-02-07 1957-01-23 Noise suppression nozzle with thrust reversal provision for jet propulsion engines

Country Status (1)

Country Link
GB (1) GB835134A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008045071A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with a variable exit area fan nozzle, nacelle assembly of such a engine, and corresponding operating method
EP3460226A1 (en) * 2017-09-21 2019-03-27 United Technologies Corporation Moveable exhaust plug

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008045071A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with a variable exit area fan nozzle, nacelle assembly of such a engine, and corresponding operating method
US8256225B2 (en) 2006-10-12 2012-09-04 United Technologies Corporation Gas turbine engine with a variable exit area fan nozzle, nacelle assembly of such a engine, and corresponding operating method
EP3460226A1 (en) * 2017-09-21 2019-03-27 United Technologies Corporation Moveable exhaust plug
US10570852B2 (en) 2017-09-21 2020-02-25 United Technologies Corporation Moveable exhaust plug liner

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