US2763984A - Device for regulating the effective cross-section of a discharge-nozzle - Google Patents

Device for regulating the effective cross-section of a discharge-nozzle Download PDF

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Publication number
US2763984A
US2763984A US534119A US53411955A US2763984A US 2763984 A US2763984 A US 2763984A US 534119 A US534119 A US 534119A US 53411955 A US53411955 A US 53411955A US 2763984 A US2763984 A US 2763984A
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US
United States
Prior art keywords
nozzle
discharge
section
jet
cross
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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 - Lifetime
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US534119A
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English (en)
Inventor
Kadosch Marcel
Raymond H 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
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SNECMA SAS
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
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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

Definitions

  • nit n7 rates Patent filed December 9, 1953; Ser. No. 455,852, filed September 14, 1954-; and Ser. No. 485,179, filed January 31, 1955, is described a method enabling the flow of a gaseous fluid inside a conduit to be controlled, and in particular the cross-section of passage available to the said flow, the said method consisting in directing on to the said fiow an auxiliary jet of a gas at suitable pressure, the initial speed of which has a component at right angles to the direction of the said flow.
  • the discharge-nozzles of reaction motors form convergent surfaces with a double curvature, the extremity of which is tangential to a cylinder parallel to the axis (see Fig. l of the attached drawings showing in axial cross-section the cylindrical extremity 1 of a discharge-nozzle of this kind).
  • reaction jets can be produced such that all the molecules are discharged in a direction truly parallel to the axis of the discharge-nozzle and at the same speed, the jet retaining a constant cross-section for some time after its discharge from the nozzle, this cross-section being identical with that of the extremity of the said discharge-nozzle.
  • Fig. 1 is a view in axial cross-section of a dischargenozzle with a cylindrical extremity, and has already been referred to in the preamble to the present description.
  • Fig. 2 is a view in axial cross-section of a truncated discharge-nozzle provided with an application of the invention.
  • Fig. 3 is a detail view to a larger scale and in crosssection of the extremity of this dischargenozzle.
  • the discharge-nozzle 2 shown in Figs. 2 and 3 is given a shape which converges continuously towards a point located on the axis and on the downstream side of the outlet orifice.
  • Its terminal portion 3 may be formed, for example, by a frustum of a cone having its apex on the axis A-A, and an apex angle of 45.
  • Around the outlet orifice is formed an annular slot 41 through which a nozzle 5, also of annular form, discharges into the main conduit, the nozzle 5 communicating with an annular collector 6 which is supplied with auxiliary gas from a suitable source, for example from the air compressor of the reaction unit, through the medium of a pipe 7 which may be provided with a control valve 7a.
  • the gas in the collector 6 should have a total pressure greater than the static pressure applied by the main jet on the wall or" the discharge nozzle in the zone of the slot i.
  • the nozzle 5 has a form suitable for the complete expansion of this gas by causing it to penetrate into the discharge-nozzle in the form of an annular jet at high velocity.
  • the nozzle 5 is disposed in such a way that the jets of gas which are discharged through it when the valve 7a is opened, have a speed V1 substantially parallel to the axis A-A, or slightly oblique with respect to the said axis, and have a direction in the opposite sense to the speed of how of the main jet.
  • the auxiliary jet curves inward following the lines shown dotted, and passes out of the discharge-nozzle with a speed V2.
  • a device for the aerodynamic control of the crosssection of a discharge-nozzle comprising a main discharge nozzle having a convergent shape, an auxiliary nozzle provided on the inner wall of said main nozzle ahead of its outlet orifice and means for feeding said auxiliary nozzle with fluid under pressure so as to form a fluid jet which escapes into said main nozzle, said auxiliary nozzle having a direction substantially parallel to the axis of the main discharge-nozzle, opening towards the upstream part of the main nozzle.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Testing Of Engines (AREA)
US534119A 1954-09-17 1955-09-13 Device for regulating the effective cross-section of a discharge-nozzle Expired - Lifetime US2763984A (en)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
US2763984A true US2763984A (en) 1956-09-25

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ID=9598975

Family Applications (1)

Application Number Title Priority Date Filing Date
US534119A Expired - Lifetime US2763984A (en) 1954-09-17 1955-09-13 Device for regulating the effective cross-section of a discharge-nozzle

Country Status (4)

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

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2875578A (en) * 1950-06-16 1959-03-03 Snecma Device for controlling the flow direction of a reaction jet issuing from a nozzle
US2906089A (en) * 1951-01-04 1959-09-29 Snecma Air intake control for jet propulsion units
US2934896A (en) * 1952-06-05 1960-05-03 Snecma Variable-area propelling nozzle combined with a thrust spoiler
US3000178A (en) * 1957-09-16 1961-09-19 Snecma Ejection nozzles having variable cross-sectional area
US3029011A (en) * 1955-10-13 1962-04-10 Bristol Siddeley Engines Ltd Rotary compressors or turbines
US3041823A (en) * 1952-09-18 1962-07-03 Snecma Control for varying the cross-sectional area of a 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
US3288373A (en) * 1964-06-18 1966-11-29 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
WO1996020867A1 (en) 1994-12-30 1996-07-11 Grumman Aerospace Corporation Fluidic control thrust vectoring nozzle
US6021637A (en) * 1997-09-29 2000-02-08 General Electric Company Integrated fluidic CD nozzle for gas turbine engine
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
WO2008088328A1 (en) * 2007-01-17 2008-07-24 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
US20100068039A1 (en) * 2006-10-12 2010-03-18 Michael Winter Turbofan engine with variable bypass nozzle exit area and method of operation
US20130319773A1 (en) * 2011-02-25 2013-12-05 Cmte Development Limited Fluid drilling head nozzle design
US20170096965A1 (en) * 2013-11-27 2017-04-06 Lockheed Martin Corporation Exhaust plume cooling using periodic interruption of exhaust gas flow to form ambient air entraining vortices

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1183751B (de) * 1958-06-19 1964-12-17 Snecma Einrichtung zur Beeinflussung der Richtung und der Querschnittsflaeche eines aus einer Lavalduese austretenden UEberschallstrahls
DE1275840B (de) * 1961-01-12 1968-08-22 Bristol Siddeley Engines Ltd Gasturbinen-Strahltriebwerk mit schwenkbarer Strahlduese
DE3301355C2 (de) * 1983-01-18 1984-11-08 Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5000 Köln Starthilfeeinrichtung für eine Hochdruckbrennkammer

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1012341A (fr) * 1949-07-15 1952-07-08 Hispano Suiza Sa Perfectionnements apportés aux engins à tuyère réactive, notamment aux turbomachines à post-combustion pour aérodynes

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2875578A (en) * 1950-06-16 1959-03-03 Snecma Device for controlling the flow direction of a reaction jet issuing from a nozzle
US2906089A (en) * 1951-01-04 1959-09-29 Snecma Air intake control for jet propulsion units
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
US3000178A (en) * 1957-09-16 1961-09-19 Snecma Ejection nozzles having variable cross-sectional area
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
US3288373A (en) * 1964-06-18 1966-11-29 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
WO1996020867A1 (en) 1994-12-30 1996-07-11 Grumman Aerospace Corporation Fluidic control thrust vectoring nozzle
US6112512A (en) * 1997-08-05 2000-09-05 Lockheed Martin Corporation Method and apparatus of pulsed injection for improved nozzle flow control
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
US6021637A (en) * 1997-09-29 2000-02-08 General Electric Company Integrated fluidic CD nozzle for gas turbine engine
US20100068039A1 (en) * 2006-10-12 2010-03-18 Michael Winter Turbofan engine with variable bypass nozzle exit area and method of operation
EP2426342A3 (de) * 2006-10-12 2012-05-09 United Technologies Corporation Turbofan mit variabler Bypassdüsen-Austrittsfläche und Betriebsverfahren
US8480350B2 (en) 2006-10-12 2013-07-09 United Technologies Corporation Turbofan engine with variable bypass nozzle exit area and method of operation
WO2008088328A1 (en) * 2007-01-17 2008-07-24 United Technologies Corporation Core reflex nozzle for turbofan engine
GB2452459A (en) * 2007-01-17 2009-03-04 United Technologies Corp Core reflex nozzle for turbofan engine
US20100221102A1 (en) * 2007-01-17 2010-09-02 Dawson Stacie M Core reflex nozzle for turbofan engine
US8002520B2 (en) * 2007-01-17 2011-08-23 United Technologies Corporation Core reflex nozzle for turbofan engine
GB2452459B (en) * 2007-01-17 2011-10-26 United Technologies Corp Core reflex nozzle for turbofan engine
US20090165864A1 (en) * 2007-12-26 2009-07-02 Rolls-Royce North American Technologies, Inc. Supersonic inlet
US20130319773A1 (en) * 2011-02-25 2013-12-05 Cmte Development Limited Fluid drilling head nozzle design
US20170096965A1 (en) * 2013-11-27 2017-04-06 Lockheed Martin Corporation Exhaust plume cooling using periodic interruption of exhaust gas flow to form ambient air entraining vortices
US10794329B2 (en) * 2013-11-27 2020-10-06 Lockheed Martin Corporation Exhaust plume cooling using periodic interruption of exhaust gas flow to form ambient air entraining vortices

Also Published As

Publication number Publication date
FR1111633A (fr) 1956-03-02
GB782323A (en) 1957-09-04
DE1059247B (de) 1959-06-11

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