GB782323A - Improvements in devices for regulating the effective cross-section of a discharge nozzle - Google Patents

Improvements in devices for regulating the effective cross-section of a discharge nozzle

Info

Publication number
GB782323A
GB782323A GB26146/55A GB2614655A GB782323A GB 782323 A GB782323 A GB 782323A GB 26146/55 A GB26146/55 A GB 26146/55A GB 2614655 A GB2614655 A GB 2614655A GB 782323 A GB782323 A GB 782323A
Authority
GB
United Kingdom
Prior art keywords
nozzle
auxiliary gas
jet
truncated
axis
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
GB26146/55A
Inventor
Marcel Kadosch
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 GB782323A publication Critical patent/GB782323A/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
    • F02K1/30—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 varying effective area of jet pipe or nozzle

Abstract

782,323. Jet-propulsion nozzles. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Sept. 13, 1955 [Sept. 17, 1954], No. 26146/55. Class 110 (3). The discharge area of a truncated jetpropulsion nozzle is controlled by auxiliary gas which is injected into the nozzle in the upstream direction and substantially parallel to the axis of the main discharge nozzle. A truncated nozzle is stated to be one in which the extremity of the nozzle is tangential to a convergent cone. The truncated convergent nozzle 2 has its terminal portion 3 formed by a frustum of a cone having its apex on the nozzle axis A-A and an apex angle of 45 degrees. An annular nozzle 5 formed around the outlet orifice is supplied with air from a manifold 6 fed with an auxiliary gas under pressure, e.g. air from the compressor of the jet-propulsion engine. Control means are provided to vary the supply of auxiliary gas. The nozzle 5 completes the expansion of the auxiliary gas and discharges it in the form of a high velocity annular jet in a direction parallel to the axis A -A and opposite to the main jet flow. Specification 745,630 is referred to.
GB26146/55A 1954-09-17 1955-09-13 Improvements in devices for regulating the effective cross-section of a discharge nozzle Expired GB782323A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1059247X 1954-09-17

Publications (1)

Publication Number Publication Date
GB782323A true GB782323A (en) 1957-09-04

Family

ID=9598975

Family Applications (1)

Application Number Title Priority Date Filing Date
GB26146/55A Expired GB782323A (en) 1954-09-17 1955-09-13 Improvements in devices for regulating the effective cross-section of a discharge nozzle

Country Status (4)

Country Link
US (1) US2763984A (en)
DE (1) DE1059247B (en)
FR (1) FR1111633A (en)
GB (1) GB782323A (en)

Families Citing this family (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB750687A (en) * 1950-06-16 1956-06-20 Snecma Improvements in or relating to jet propulsion units for aircraft
FR1030483A (en) * 1951-01-04 1953-06-15 Snecma Method and devices for controlling a flow and their various applications
US2934896A (en) * 1952-06-05 1960-05-03 Snecma Variable-area propelling nozzle combined with a thrust spoiler
US3041823A (en) * 1952-09-18 1962-07-03 Snecma Control for varying the cross-sectional area of a nozzle
US3029011A (en) * 1955-10-13 1962-04-10 Bristol Siddeley Engines Ltd Rotary compressors or turbines
FR1182810A (en) * 1957-09-16 1959-06-30 Snecma Improvements to adjustable section ejection nozzles
DE1183751B (en) * 1958-06-19 1964-12-17 Snecma Device for influencing the direction and the cross-sectional area of a supersonic jet emerging from a Laval nozzle
DE1275840B (en) * 1961-01-12 1968-08-22 Bristol Siddeley Engines Ltd Gas turbine jet engine with swiveling jet nozzle
US3132476A (en) * 1961-04-27 1964-05-12 Earl W Conrad Thrust vector control apparatus
US3273801A (en) * 1962-08-30 1966-09-20 Thiokol Chemical Corp Rocket acceleration and direction control by fluid injection
GB1019203A (en) * 1964-06-18 1966-02-02 Rolls Royce Jet nozzle
US3371743A (en) * 1965-04-29 1968-03-05 American Radiator & Standard Jet exhaust silencing nozzle with suction applied at exit wall
US5183323A (en) * 1982-09-29 1993-02-02 Maurice Daniel Flat panel illumination system
DE3301355C2 (en) * 1983-01-18 1984-11-08 Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5000 Köln Jump start device for a high pressure combustion chamber
EP0796196A4 (en) 1994-12-30 1998-04-01 Grumman Aerospace Corp Fluidic control thrust vectoring nozzle
US6112513A (en) * 1997-08-05 2000-09-05 Lockheed Martin Corporation Method and apparatus of asymmetric injection at the subsonic portion of a nozzle flow
US6112512A (en) * 1997-08-05 2000-09-05 Lockheed Martin Corporation Method and apparatus of pulsed injection for improved nozzle flow control
US6021637A (en) * 1997-09-29 2000-02-08 General Electric Company Integrated fluidic CD nozzle for gas turbine engine
WO2008045074A1 (en) * 2006-10-12 2008-04-17 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
US8002520B2 (en) * 2007-01-17 2011-08-23 United Technologies Corporation Core reflex nozzle for turbofan engine
US20090165864A1 (en) * 2007-12-26 2009-07-02 Rolls-Royce North American Technologies, Inc. Supersonic inlet
RU2016111932A (en) * 2011-02-25 2018-11-27 СиЭмТиИ ДЕВЕЛОПМЕНТ ЛИМИТЕД Hydraulic cutting head
US9541030B2 (en) * 2013-11-27 2017-01-10 Lockheed Martin Corporation Exhaust plume cooling using periodic interruption of exhaust gas flow to form ambient air entraining vortices

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1012341A (en) * 1949-07-15 1952-07-08 Hispano Suiza Sa Improvements made to reactive nozzle devices, in particular to post-combustion turbomachines for aerodynes

Also Published As

Publication number Publication date
DE1059247B (en) 1959-06-11
FR1111633A (en) 1956-03-02
US2763984A (en) 1956-09-25

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