GB802123A - Improvements in or relating to jet nozzle arrangements for jet-reaction-propulsion purposes - Google Patents

Improvements in or relating to jet nozzle arrangements for jet-reaction-propulsion purposes

Info

Publication number
GB802123A
GB802123A GB6086/56A GB608656A GB802123A GB 802123 A GB802123 A GB 802123A GB 6086/56 A GB6086/56 A GB 6086/56A GB 608656 A GB608656 A GB 608656A GB 802123 A GB802123 A GB 802123A
Authority
GB
United Kingdom
Prior art keywords
jet
sleeve
jet pipe
nozzle
group xxvi
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
GB6086/56A
Inventor
Harry William Thomas Leedham
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 GB6086/56A priority Critical patent/GB802123A/en
Publication of GB802123A publication Critical patent/GB802123A/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
    • F02K1/56—Reversing jet main flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
    • 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
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • F02K1/48—Corrugated nozzles

Abstract

802,123. Jet thrust reversing apparatus. ROLLS-ROYCE, Ltd. Feb. 19, 1957 [Feb. 27, 1956], No. 6086/56. Class 4. [Also in Group XXVI] In a jet thrust reversing mechanism wherein the jet nozzle is formed with circumferentiallyspaced axially extending channels to suppress jet noise (see Group XXVI) each gas channel 13c formed by radially extending walls 12a boxed in pairs by an inner wall 12b and a rear wall 12c and a tongue 10a formed on the jet pipe 10 is provided with a gas outlet which communicates with a port 14a in a rotatable sleeve 14 driven by an electric motor 15. The rear end of sleeve 14 is formed with pieces 18 which, when the sleeve is rotated to open the ports 14a, blank off the outlet ends of channels 13c. In addition, sliding plates 19 are each connected by a link 20 to sleeve 14 so that they are moved radially inwards and outwards by rotation of the sleeve to close the central part of the jet pipe orifice, as shown in Fig. 2a. The ports 14a communicate with ducts 23 formed between the jet pipe 10 and nacelle fairing 11, and these are closed by flaps 25. In a further embodiment, the axially extending ducts meet on the axis of the jet pipe at the rear end of the nozzle so that blanking members such as pieces 18 are alone sufficient to close the nozzle outlet when the sleeve 14 is rotated. Parts of the mechanism in contact with the propulsion gases may have internal passages for conveying cooling air. Specification 768,553 [Group XXVI] is referred to.
GB6086/56A 1956-02-27 1956-02-27 Improvements in or relating to jet nozzle arrangements for jet-reaction-propulsion purposes Expired GB802123A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB6086/56A GB802123A (en) 1956-02-27 1956-02-27 Improvements in or relating to jet nozzle arrangements for jet-reaction-propulsion purposes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB6086/56A GB802123A (en) 1956-02-27 1956-02-27 Improvements in or relating to jet nozzle arrangements for jet-reaction-propulsion purposes

Publications (1)

Publication Number Publication Date
GB802123A true GB802123A (en) 1958-10-01

Family

ID=9808116

Family Applications (1)

Application Number Title Priority Date Filing Date
GB6086/56A Expired GB802123A (en) 1956-02-27 1956-02-27 Improvements in or relating to jet nozzle arrangements for jet-reaction-propulsion purposes

Country Status (1)

Country Link
GB (1) GB802123A (en)

Cited By (1)

* 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

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
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

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