US3837580A - Nozzles having an adjustable cross-section - Google Patents

Nozzles having an adjustable cross-section Download PDF

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Publication number
US3837580A
US3837580A US00402836A US40283673A US3837580A US 3837580 A US3837580 A US 3837580A US 00402836 A US00402836 A US 00402836A US 40283673 A US40283673 A US 40283673A US 3837580 A US3837580 A US 3837580A
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US
United States
Prior art keywords
nozzle
flap
actuated
parallelogram
fixed
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 - Lifetime
Application number
US00402836A
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English (en)
Inventor
Maout T Le
A Camboulives
G Jourdain
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
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Expired - Lifetime legal-status Critical Current

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    • 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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • ABSTRACT A jet propulsion nozzle comprising a plurality of actuated flaps articulated at their upstream ends about substantially tangentially disposed axes distributed circumferentially around the downstream portion of a fixed nozzle duct, said flaps being adapted, under the control of a plurality of actuators, to pivot about their respective axes in order to vary the cross-sectional area of the nozzle, said nozzle comprising furthermore a plurality of intermediate levers separate from the ac tuators and disposed respectively each between two consecutive actuated flaps, each of said levers being connected through the medium of connecting rods to the two consecutive actuated flaps and being itself articulated about a substantially tangential axis, wherein the flap axes and the intermediate lever axes are carried by a system of longitudinal side plates distributed circumferentially about the nozzle axis and themselves carried by the fixed duct of
  • NOZZLES HAVING AN ADJUSTABLE CROSS-SECTION The present invention relates, in a general way, to nozzles having an adjustable cross-sectional area which are intended to be fitted, in particular, to jet propulsion engines such as gas turbine jet propulsion engines.
  • the invention is more particularly concerned with a jet propulsion nozzle of the type comprising: a fixed structure comprising a fixed nozzle duct; a plurality of actuated flaps which are distributed circumferentially around, and in the prolongation of, the downstream part of the said fixed nozzle duct, and of which each one is hinged, about a first geometrical axis which is substantially tangential in relation to the nozzle, to the said fixed structure, in such a way as to vary the crosssectional area of the said nozzle; a plurality of actuators, each of which corresponds to an actuated flap and comprises a moving part which makes it possible to rotate the said flap about the said first geometrical axis; a plurality of intermediate levers which are disposed in alternation with the said flaps and each of which is hinged, about a second geometrical axis which is substantially tangential in relation to the nozzle, to the said fixed structure; a plurality of connecting rods, each of which is hinged, on the one hand, to an actuated
  • the aim of the present invention is to improve a nozzle of the type described above, with a view to increasing the efficiency with which force is transmitted between each actuator and the actuated flap associated with it. More specifically, the aim of the invention is to make it possible either to increase for a given size of the actuator the driving torque applied to the flap, or else to reduce for a given driving torque the dimensions (particularly the overall dimensions in the radial direction) of the said actuator.
  • the moving part (for example a rod) of each actuator corresponding to an actuated flap is fastened, in a nozzle according to the present invention, to a cross-bar which extends in a substantially tangential direction, relative to the nozzle, and connects the two connecting rods associated with the said flap, this rocking link being disposed in such a way that its trace, onto the plane of the above-mentioned deformable parallelogram, is separated from the fixed side of the parallelogram, at any moment, by a distance which is smaller than the height of this parallelogram.
  • FIG. 1 is a diagrammatic view, in perspective, of a portion of nozzle having an adjustable cross-sectional area according to prior art
  • FIG. 2 diagrammatically illustrates this same nozzle, viewed in section through a plane passing through the axis of the said nozzle;
  • FIG. 3 is a view which is similar to that in FIG. 2 and illustrates the general principle underlying a nozzle which has been improved in accordance with the present invention
  • FIG. 4 is a developed plan view, partially cut away, of a portion of nozzle according to one embodiment of the present invention.
  • FIG. 5 is a section, taken along the line VV, of the portion of nozzle illustrated in FIG. 4;
  • FIG. 6 is a section, taken along the line VIVI, of the portion of nozzle illustrated in FIG. 4;
  • FIG. 7 is a diagrammatic view, in perspective, of the portion of nozzle illustrated in FIGS. 4, 5 and 6.
  • FIGS. 1 and 2 A diagrammatic illustration has been given, in FIGS. 1 and 2, of a portion of nozzle according to the prior art, the said nozzle forming part of a jet propulsion engine (not illustrated).
  • This nozzle comprises a fixed structure 1, which itself comprises a fixed nozzle duct (not illustrated), and a plurality of actuated flaps 2 distributed circumferentially around, and in the prolongation of the downstream part of the said fixed duct.
  • Each actuated flap 2 is hinged about a first geometrical axis A which is substantially tangential in relation to the nozzle, to the fixed structure 1, in such a way as to vary the cross-sectional area of the nozzle.
  • An actuator 3 disposed in the longitudinal direction of the nozzle is provided for each actuated flap 2.
  • each actuator 3 comprises a moving part (such as a rod) 4 which makes it possible to rotate the said flap about its axis of articulation A.
  • the nozzle also comprises a plurality of intermediate levers 5 (also called synchronization levers) which are disposed in alternation with the actuated flaps 2 and of which each one is hinged, about a second geometrical axis B which is substantially tangential in relation to the nozzle, onto the fixed structure 1.
  • intermediate levers 5 also called synchronization levers
  • each actuated flap 2 Associated with each actuated flap 2 are two connecting rods 6a, 6b by means of which the said flap is connected, respectively, to the two intermediate levers 5 which enframe it.
  • Each link 6a or 6b is hinged, on the one hand, to an actuated flap 2, about a third geometrical axis C which is substantially tangential in relation to the nozzle, and, onto the other hand, on an intermediate lever 5 adjacent to the said flap, about a fourth geometrical axis D which is substantially tangential in relation to the nozzle.
  • the rod 4 of the actuator 3 is hinged on a point on the flap 2 which is situated on the geometrical axis C.
  • the four geometrical axes of articulation A, B, C, D relating to an actuated flap 2 and to an intermediate lever 5, which is adjacent to the latter, are so disposed, relative to one another, that the quadrilateral which they determine by their respective traces onto a plane containing the axis of the nozzle (under the circumstances, the plane in FIG. 2), is substantially a parallelogram ABCD which is deformed during variations in the cross-sectional area of the nozzle.
  • This deformable parallelogram comprises a fixed side AB (see FIG. 2) constituted by the segment of straight line which connects the traces, onto the abovementioned plane, of the axes A and B; it also comprises a moving side CD which is substantially equal and parallel to the side AB and is constituted by the segment of straight line which connects the traces, onto the same plane, of the axes C and D.
  • the fixed side AB and the moving side CD are separated from one another by a variable distance, which constitutes the height h, of the deformable parallelogram.
  • FIG. 3 illustrates, still in a very diagrammatic manner, an adjustable nozzle which has been improved according to the invention.
  • FIGS. 1 and 2 The main elements already illustrated in FIGS. 1 and 2 will again be found in this figure, namely: a fixed structure 101, an actuated flap 102, an actuator jack 103 fitted with a moving rod 104, an intermediate (or synchronization) lever 105, connecting rods 106a and 106b, and the four tangential axes A, B, C, D, the traces of which are distributed, as before, along the vertices of a deformable parallelogram ABCD having a fixed side AB.
  • the rod 104 of the actuator 103 is no longer hinged directly to the flap 102, but to a crossbar 107 (more clearly visible in FIGS. 4 to 7) which connects the two connecting rods 106a and 10612 associated with the said flap.
  • This cross-bar extends in a direction which is substantially tangential in relation to the nozzle, and its trace onto the plane of the para]- lelogram ABCD has been designated by the reference symbol E in FIG. 3.
  • the point E is selected in such a way that the distance between this point and the fixed side AB of the parallelogram is, at each moment, smaller than the height h, of the said parallelogram.
  • H, (H,) the mean radial distance between the fixed structure 1 (101) and that generatrix of the said actuator which is furthest off the said fixed structure;
  • the arrangement according to the invention therefore has the initial advantage of making it possible, while retaining the same driving moment which is exerted upon the flaps, to reduce the power and diameter of the actuators 103 compared with the actuators 3.
  • the second advantage of this arrangement is that it makes it possible, under the same conditions, to reduce the overall dimension H in the radial direction involved by the actuators 103, compared with the overall dimension H, which results from the presence of the actuators 3.
  • the surprising result is thus arrived at, that the consequence of increasing the height of the deformable parallelogram ABCD is a reduction in the total overall dimension involved by the actuators for controlling the flaps.
  • the arrangement according to the invention therefore has the advantage of making it possible, with equal power from the actuator, to increase the driving moment exerted by this actuator upon the flap.
  • FIGS. 4 to 7 illustrate a practical embodiment of an adjustable nozzle according to the invention.
  • the same reference numerals have been used to designate the components already described in connection with FIG. 3.
  • the nozzle therefore comprises a fixed structure 101, which itself comprises a fixed nozzle duct 110 terminated, on the downstream side, by an annular reinforcing gutter 111, over the outer periphery of which there are provided yokes 112 which are spaced apart from one another in the peripheral direction of the nozzle.
  • the fixed nozzle duct 110 also carries, on its outer periphery, a ring of lugs 113.
  • the fixed structure 101 also comprises a plurality of longitudinal side-plates 114a, 1141). In the vicinity of its upstream end, each of these side-plates is hinged about an axis G, to a yoke 115a (1151)) which is itself hinged about an axis H, to a rocking lever 116 which is in turn hinged, about an axis J, to two lugs 113 which are con secutive in the peripheral direction. Further downstream, each of the side-plates 114a, 114b is likewise hinged about an axis K, to a yoke 112. As will be realized, this method of attaching the side-plates makes it possible to make allowance for their expansion during operation.
  • the fixed nozzle duct 110 is succeeded by a ring of adjustable flaps comprising, on the one hand, the actuated flaps 102, and, on the other hand, follower flaps 122.
  • Each actuated flap 102 comprises a leaf 102x to which there is fastened a cranked lever 102y.
  • the latter is hinged about a first geometrical axis A which is substantially tangential in relation to the nozzle, to two, peripherally consecutive, side-plates 114a, 114b, which form part of the fixed structure 101.
  • the follower flaps 122 are respectively located between the actuated flaps 102, and are applied, during operation, against the internal flanges of their neighbours by the pressure of the jet of gases which passes through the nozzle.
  • An annular seal plate 123 ensures tightness at the joint between the fixed nozzle duct 110 and the flaps 102-122.
  • Each actuator 103 associated with an actuated flap 102 is enframed by two, peripherally consecutive, sideplates 114a and 114b, and has, at its upstream end, two lugs 103a, 103b by means of which the body of the said actuator is hinged, about the aforesaid axis G, to the said side-plates.
  • An intermediate (or synchronization) lever 105 is disposed, as has been stated, between two successive actuated flaps 102.
  • This intermediate lever is hinged, about a second axis B which is substantially tangential in relation to the nozzle, to two, peripherally consecutive side-plates 114a and 114b.
  • each connecting rod 106a or 106 is hinged, on the one hand, to the cranked lever 102y forming part of an actuated flap 102, about a third axis C which is substantially tangential in relation to the nozzle and, on the other hand, to an intermediate lever 105 adjacent to the said flap, about a fourth geometrical axis D which is substantially tangential in relation to the nozzle.
  • the four axes of articulation, A, B, C, D, are disposed in such a way, relative to one another, that their respective traces, onto the plane of the said Figure, substantially form the four vertices of a deformable parallelogram ABCD having a fixed side AB.
  • the height, which is variable, of this parallelogram is constituted by the distance between the said side AB and the side CD opposite the latter.
  • Each cross-bar 107 is hinged, about the aforesaid axis E, to the two interconnecting links 106a, 106b which are associated with the same actuated flap 102.
  • the point E is selected in such a way that its distance from the fixed side AB of the parallelogram ABCD is, at any moment, less than the height of the said parallelogram.
  • the functioning of the nozzle thus described is substantially the same as heretofore known.
  • the unit made up of the actuated flaps 102, the synchronization levers 105 and the connecting rods 106a, 1061) constitutes an indented kinematic chain which is closed around the nozzle and compels each of the actuated flaps to adopt a mean position which is common to all the flaps. Under all its operating conditions, therefore, the nozzle thus retains a circular transverse section which is concentric with itself, even in the event of dissymetry in the functioning of the actuators jacks 103 for the said flaps.
  • the present invention applies both to single nozzles made up of an only ring of flaps (as is the case with the nozzle which has just been described), and to ejector type nozzles comprising two rings of actuated flaps which are respectively associated with a primary nozzle duct and with a secondary nozzle duct (as is the case with the nozzle described in the prior art.
  • the present invention which, as has been seen, leads to a substantial reduction in the overall dimension, in the radial direction, involved by the actuators can also be put into practice in an advantageous manner in the case of an exhaust unit comprising two primary nozzles disposed inside a single nacelle.
  • a jet propulsion nozzle having an adjustable crosssectional area comprising:
  • a fixed structure comprising a fixed nozzle duct
  • actuated flaps which are distributed circumferentially around, and in the prolongation of, the downstream part of the said fixed nozzle duct, and of which each one is hinged, about a first geometrical axis which is substantially tangential in relation to the nozzle, to the said fixed structure, in such a way as to vary the cross-sectional area of the said nozzle;
  • a plurality of actuators each of which corresponds to an actuated flap and comprises a moving part which makes it possible to rotate the said flap about the said first geometrical axis;
  • a plurality of intermediate levers which are disposed a plurality of connecting rods, each of which is hinged, on the one hand, to an actuated flap, about a third geometrical axis which is substantially tangential in relation to the nozzle and, on the other hand, to an intermediate lever adjacent to the said flap, about a fourth geometrical axis which is substantially tangential in relation to the nozzle, in such a way that there are associated with each actuated flap, two connecting rods by means of which the said flap is connected, respectively, to the two intermediate levers which enframe it; the said first, second, third and fourth geometrical axes, which relate to an actuated flap and to an intermediate lever adjacent to the latter, being disposed in such a way, relative to one another, that the quadrilateral which they determine by their respective traces onto a plane containing the axis of the nozzle, is substantially a parallelogram which is deformed during variations in the crosssectional area of the nozzle, the said deformable parallelogram having a fixed

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Nozzles (AREA)
  • Transmission Devices (AREA)
US00402836A 1972-10-06 1973-10-02 Nozzles having an adjustable cross-section Expired - Lifetime US3837580A (en)

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FR7235502A FR2202234B2 (zh) 1972-10-06 1972-10-06

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DE (1) DE2349560C3 (zh)
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GB (1) GB1433936A (zh)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3899133A (en) * 1973-09-21 1975-08-12 Moteurs D Aviat De France Soc Nozzles having a variable cross-section
US4311276A (en) * 1978-06-24 1982-01-19 Rolls-Royce Limited Variable area nozzle for a gas turbine engine
US4466573A (en) * 1980-01-25 1984-08-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation ("S.N.E.C.M.A.") Wet pipe device for turbojet engines
US4641783A (en) * 1983-12-21 1987-02-10 Societe Nationale D'etude Et De Construction De Meteur D'aviation (Snecma) Exhaust nozzle assembly for a turbojet engine
US5031836A (en) * 1990-07-10 1991-07-16 United Technologies Corporation Flexible fairing for airframe/nozzle interface
US5520336A (en) * 1980-01-14 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.A.) Nozzle for a jet engine containing an adjustable convergent-divergent portion
US5542607A (en) * 1981-11-24 1996-08-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Supersonic nozzle, in particular for a turbojet engine
FR2875853A1 (fr) * 2004-09-29 2006-03-31 Snecma Moteurs Sa Turboreacteur avec une tuyere a section variable dont chaque volet pivote autour d'un axe, axes pour les volets
US20060086093A1 (en) * 2004-10-26 2006-04-27 Snecma Variable-section turbomachine nozzle with a one-piece control lever support
US20060213199A1 (en) * 2004-07-28 2006-09-28 Snecma Convergent turbojet exhaust nozzle
US20090313825A1 (en) * 2008-06-03 2009-12-24 Harris Andrew H Gas turbine engine exhaust component and manufacturing method of same
US10662895B2 (en) 2016-05-24 2020-05-26 Rolls -Royce Plc Aircraft gas turbine engine nacelle

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2714422A1 (fr) * 1983-01-13 1995-06-30 Snecma Tuyère convergente-divergente, en particulier pour turboréacteur.
FR2617910A1 (fr) * 1987-07-08 1989-01-13 Snecma Tuyere axisymetrique de turboreacteur convergente divergente
FR2661716B1 (fr) * 1990-05-03 1992-07-03 Snecma Dispositif de tuyere de turboreacteur.
CN112555049A (zh) * 2020-12-03 2021-03-26 北方工业大学 一种微型涡轮喷气发动机的外套式矢量喷管结构

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990029A (en) * 1956-03-16 1961-06-27 Rolls Royce Variable area jet propulsion nozzles
US3004385A (en) * 1958-06-25 1961-10-17 Gen Motors Corp Variable convergent-divergent jet nozzle
US3537647A (en) * 1968-01-19 1970-11-03 Snecma Variable area nozzles
US3612106A (en) * 1969-07-03 1971-10-12 Snecma Arrangement for controlling and supporting a variable-geometry duct

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990029A (en) * 1956-03-16 1961-06-27 Rolls Royce Variable area jet propulsion nozzles
US3004385A (en) * 1958-06-25 1961-10-17 Gen Motors Corp Variable convergent-divergent jet nozzle
US3537647A (en) * 1968-01-19 1970-11-03 Snecma Variable area nozzles
US3612106A (en) * 1969-07-03 1971-10-12 Snecma Arrangement for controlling and supporting a variable-geometry duct

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3899133A (en) * 1973-09-21 1975-08-12 Moteurs D Aviat De France Soc Nozzles having a variable cross-section
US4311276A (en) * 1978-06-24 1982-01-19 Rolls-Royce Limited Variable area nozzle for a gas turbine engine
US5520336A (en) * 1980-01-14 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.A.) Nozzle for a jet engine containing an adjustable convergent-divergent portion
US4466573A (en) * 1980-01-25 1984-08-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation ("S.N.E.C.M.A.") Wet pipe device for turbojet engines
US5542607A (en) * 1981-11-24 1996-08-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Supersonic nozzle, in particular for a turbojet engine
US4641783A (en) * 1983-12-21 1987-02-10 Societe Nationale D'etude Et De Construction De Meteur D'aviation (Snecma) Exhaust nozzle assembly for a turbojet engine
US5031836A (en) * 1990-07-10 1991-07-16 United Technologies Corporation Flexible fairing for airframe/nozzle interface
US20060213199A1 (en) * 2004-07-28 2006-09-28 Snecma Convergent turbojet exhaust nozzle
US7475547B2 (en) * 2004-07-28 2009-01-13 Snecma Convergent turbojet exhaust nozzle
US20060225427A1 (en) * 2004-09-29 2006-10-12 Snecma Jet engine with a variable section nozzle of which at least one flap pivots about a pin, pins for flaps
FR2875853A1 (fr) * 2004-09-29 2006-03-31 Snecma Moteurs Sa Turboreacteur avec une tuyere a section variable dont chaque volet pivote autour d'un axe, axes pour les volets
US7533533B2 (en) 2004-09-29 2009-05-19 Snecma Jet engine with a variable section nozzle of which at least one flap pivots about a pin, pins for flaps
EP1674707A1 (fr) * 2004-10-26 2006-06-28 Snecma Tuyère a section variable de turbomachine à support de levier de commande monobloc
FR2877052A1 (fr) * 2004-10-26 2006-04-28 Snecma Moteurs Sa Tuyere a section variable de turbomachine a support de levier de commande monobloc
US20060086093A1 (en) * 2004-10-26 2006-04-27 Snecma Variable-section turbomachine nozzle with a one-piece control lever support
US20090313825A1 (en) * 2008-06-03 2009-12-24 Harris Andrew H Gas turbine engine exhaust component and manufacturing method of same
US8015820B2 (en) * 2008-06-03 2011-09-13 United Technologies Corporation Gas turbine engine exhaust component and manufacturing method of same
US10662895B2 (en) 2016-05-24 2020-05-26 Rolls -Royce Plc Aircraft gas turbine engine nacelle

Also Published As

Publication number Publication date
DE2349560B2 (de) 1979-08-02
DE2349560C3 (de) 1980-04-03
DE2349560A1 (de) 1974-04-18
FR2202234B2 (zh) 1976-03-26
GB1433936A (en) 1976-04-28
FR2202234A2 (zh) 1974-05-03

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