GB750623A - Thrust reducing or reversing device for jet propelling nozzles - Google Patents

Thrust reducing or reversing device for jet propelling nozzles

Info

Publication number
GB750623A
GB750623A GB19540/53A GB1954053A GB750623A GB 750623 A GB750623 A GB 750623A GB 19540/53 A GB19540/53 A GB 19540/53A GB 1954053 A GB1954053 A GB 1954053A GB 750623 A GB750623 A GB 750623A
Authority
GB
United Kingdom
Prior art keywords
jet
axially
vanes
stream
nozzle
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
GB19540/53A
Inventor
Marcel Kadosch
Francois Gilbert Paris
Jean Bertin
Raymond Hippolyte Marchal
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of GB750623A publication Critical patent/GB750623A/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
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/32—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for reversing thrust

Abstract

750,623. Jet propulsion plant. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. May 10, 1951 [June 16, 1950], No. 19540/53. Divided out of 750,601. Class 110(3) [Also in Group XXXIII] Means for deflecting the jet stream flowing axially through a jet propulsion nozzle of a jet propulsion engine comprises a series of axially-spaced guide vanes which define passages laterally of the jet stream and opening into the atmosphere, controllable means being provided for urging the jet towards the inner ends and into the passages so that the jet issues at an angle to the axis of the nozzle. The jet nozzle in Fig. 2 is formed with an annular orifice 13 in the wall, a series of annular curved vanes 44 being disposed in the orifice. The inner cone 11 is axially movable in the fixed guide 12 in order to vary the cross-sectional area of the nozzle and is also formed with an annular step or barrier 40 which may be covered by an axially movable hood 41. The hood 41 is connected by arms 43 to a ring 23 which is movable axially by means of pulleys 31, 32, cable 29 and pin 27 which slides in a slot 28 in the sleeve 20. When the step is covered as in the lower part of the Figure, the jet stream, which may be the exhaust gas stream of a gas turbine engine, flows axially without deflection, but when the step is uncovered as in the upper part of the Figure. the jet is deflected between the vanes in the orifice 13. In Figs. 4, 5, the jet nozzle has two lateral orifices 13, 13a in which are disposed curved vanes 44 and the jet stream is deflected into the orifices by means of blasts of air under pressure from the slots 54 in the tapered member 53 which is disposed vertically in the jet nozzle. In further embodiments, the jet stream is similarly deflected into the lateral passages by blasts of air under pressure, but auxiliary barriers or obstacles are disposed so that the stream is deflected thereby should the air pressure be insufficient, for example if the gas turbine engine is throttled down. In Fig. 8, vanes 15a, 15b are disposed in orifice 13 and the opening may be closed by means of an axially-slidable sleeve 13a. When the jet stream is to be deflected, the orifice is opened by rearward movement of the sleeve, and suction is applied to the slots 15c. The vanes may be so curved that the jet stream issues with a forward component thus exerting a braking effect upon an aircraft in which the device is fitted. Specifications 691,302 and 691,948 [Group XXXIII] are referred to.
GB19540/53A 1950-06-16 1951-05-10 Thrust reducing or reversing device for jet propelling nozzles Expired GB750623A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR750623X 1950-06-16

Publications (1)

Publication Number Publication Date
GB750623A true GB750623A (en) 1956-06-20

Family

ID=9151857

Family Applications (1)

Application Number Title Priority Date Filing Date
GB19540/53A Expired GB750623A (en) 1950-06-16 1951-05-10 Thrust reducing or reversing device for jet propelling nozzles

Country Status (1)

Country Link
GB (1) GB750623A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2274490A (en) * 1993-01-26 1994-07-27 Short Brothers Plc Nacelle for an aircraft propulsive power unit
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 (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2274490A (en) * 1993-01-26 1994-07-27 Short Brothers Plc Nacelle for an aircraft propulsive power unit
GB2274490B (en) * 1993-01-26 1996-09-18 Short Brothers Plc An aircraft propulsive power unit
US5609313A (en) * 1993-01-26 1997-03-11 Short Brothers Plc Aircraft propulsive power unit
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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