US3899133A - Nozzles having a variable cross-section - Google Patents

Nozzles having a variable cross-section Download PDF

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Publication number
US3899133A
US3899133A US506869A US50686974A US3899133A US 3899133 A US3899133 A US 3899133A US 506869 A US506869 A US 506869A US 50686974 A US50686974 A US 50686974A US 3899133 A US3899133 A US 3899133A
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United States
Prior art keywords
nozzle
flap
controlled
disposed
flaps
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Expired - Lifetime
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US506869A
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English (en)
Inventor
Andre Alphonse Med Camboulives
Maout Theophile Francois Le
Bernard Arthur Zibette
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Safran Aircraft Engines SAS
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Moteurs D Aviat De France Soc
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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 variable-section nozzle comprising a fixed structure embodying a fixed nozzle casing, a plurality of controlled flaps distributed around and in extension of the downstream portion of said fixed nozzle casing, a plurality of levers disposed in alternation with said controlled flaps, a plurality of connecting links and a plurality of mobile control elements, wherein each intermediate lever extends up to the neighbourhood of the respective central planes of two successive controlled flaps; and for each controlled flap, two associated connecting links are disposed substantially in the central plane of said flap.
  • the present invention relates in a general way to variable cross-section nozzles designed for incorporation in particular into jet engines such as turbojet engines.
  • a nozzle of the kind already described in the U.S. Pat. No. 3 537 647 which comprises a fixed structure embodying a fixed nozzle casing, a plurality of controlled flaps distributed around and in extension of the downstream portion of said fixed nozzle casing, each of which flaps extends to either side of a central plane containing the longitudinal axis of the nozzle, and is articulated, about a first geometric axis disposed substantially tangential in relation to the nozzle, to said fixed structure, a plurality of intermediate levers disposed in alternation with said controlled flaps, each articulated, about a second geometric axis substantially tangential in relation to the nozzle, to said fixed structure, a plurality of connecting links each of which is articulated on the one hand, about a third geometric axis substantially tangential in relation to the nozzle, to a controlled flap, and, on the other hand, about a fourth geometric axis substantially tangential in relation to the nozzle, to an intermediate lever adjacent said flap in order
  • the object of the present invention is to improve a nozzle of the kind described hereinbefore with a view to achieving an improvement in the operation of the aforesaid kinematic chain. More precisely, the aim of the invention is to get rid of (or at any rate very largely reduce) certain parasitic couples which develop in the known kinematic chain, and to improve the efficiency of the transmission of forces between each control jack and the corresponding controlled flap.
  • each intermediate lever extends up to the neighbourhood of the respective central planes of two successive controlled flaps, and that for each controlled flap, the two associated connecting links are disposed substantially in the central plane of said flap.
  • the mobile control element corresponding to a flap is hooked into said kinematic chain at a point located on one of said two connecting links.
  • the present invention relates more particularly to the case where said first, second, third and fourth geometric axes relating to a controlled flap and to an intermediate lever adjacent same, are disposed in relation to one another in such a manner that the quadrilateral figure they define by their respective projections on to the central plane of said flap substantially takes the form of a parallelogram which deforms during the course of the variation in the nozzle section, said deformable parallelogram having a fixed side constituted by the straight line section linking together the projections, on said plane, of said first and second geometric axes, and a moving side which is substantially parallel to said fixed side and is constituted by the straight line section linking together the projections, on to said same plane, of said third and fourth geometric axes, said fixed side and said moving side being separated from one another by a variable interval constituting the height of the deformable parallelogram.
  • the point of hook-in of the mobile control element is disposed on one of said connecting links in a zone thereof which is located at any instant at a distance from the fixed side of the parallelogram, which is less than the height of the parallelogram. In this fashion, the efficiency of transmission of force between each control element and the corresponding controlled flap, is improved.
  • FIG. 1 is a perspective view illustrating schematically the operation of a variable section nozzle equipped with a kinematic chain
  • FIG. la is a diagram illustrating certain geometric features of said kinematic chain
  • FIG. 2 is a longitudinal sectional view on a line IIIl of FIG. 3 of a variable section nozzle equipped with a kinematic chain in accordance with the present invention
  • FIG. 2a is a view similar to that of FIG. 2, showing the nozzle in a different (open) configuration
  • FIG. 3 is a plan view, partially cut away, of the nozzle shown in FIG. 2;
  • FIGS. 4, 5 and 6 are fragmentary transverse sectional DESCRIPTION OF PREFERRED EMBODIMENTS
  • FIG. 1 there has been schematically illustrated a portion of a variable section nozzle for a jet engine, equipped with a kinematic chain.
  • This nozzle comprises a fixed structure 1, which itself embodies a fixed nozzle casing (not shown), and a plurality of controlled flaps 2 distributed around and in extension of, the downstream portion of said fixed casing.
  • Each flap 2 extends to either side of a central plane P containing the longitudinal axis of the nozzle and is articulated, about a first geometric axis A substantially tangential to the nozzle, to the fixed structure 1.
  • each controlled flap 2 there corresponds a mobile control element 3 such as the rod of a jack 4, hooked into said flap and making it possible to pivot it about its pivot axis A in order to vary the transverse cross-sectional area of the nozzle.
  • a mobile control element 3 such as the rod of a jack 4
  • a plurality of intermediate levers 5 (also known as synchronising levers) is arranged in alternation with the controlled flaps 2, each of them being articulated, about a second geometric axis B substantially tangential to the nozzle, to said same fixed structure I.
  • each controlled flap 2 there are associated two connecting links 6 and 7 by means of which said flap is respectively connected to two successive intermediate levers surrounding it.
  • Each link 6 or 7 is articulated, axis the one hand, about a third geometric axis C substantially tangential to the nozzle, to a controlled flap 2 and, on the other hand, about a fourth geometric axis D substantially tangential to the nozzle, to an intermediate lever 5 adjacent said flap.
  • FIGS. 1 and 1a show, the four geometric axes A, B, C, D, associated with a controlled flap 2 and an intermediate lever 5 adjacent same, are disposed in relation to one another in such a fashion that the quadrilateral figure they define by their respective projections on to a plane containing the longitudinal axis of the nozzle (in the present instance the central plane P of the flap), is substantially a parallelogram ABCD which deforms during the course of the variations in the nozzle section.
  • This deformable parallelogram has a fixed side AB (see FIG. 1a) constituted by the straight line segment linking together the projections, on to the aforesaid plane, of the axes A and B; it also exhibits a moving side CD substantially equal and parallel to the side AB and constituted by the straight line segment which links together the projections, on to said same plane, of the axes C and D.
  • the assembly formed by the controlled flaps 2, the intermediate levers 5 and the connecting links 6 and 7, constitutes an indented kinematic chain, closed around the nozzle, which causes each of the controlled flaps 2 to take up a position common to the assembly of all the flaps.
  • the nozzle thus, under all operating conditions and whatever the opening, retains a circular crosssection, concentric with itself, this even in the event of asymmetry in the operation of the mobile control elements 3 of said flaps.
  • the reference 311 designates the point of hookin to said kinematic chain, of the mobile control element 3 of a flap 2. As FIG. 1 shows, this point 3a is located in the central plane P of said flap.
  • variable section nozzle equipped with a kinematic chain in accordance with the present invention in which the drawback referred to is overcome or at any rate very substantially reduced.
  • This nozzle comprises a fixed structure 101 which itself embodies a nozzle casing 110 terminated at the rear by a reinforcing ring 1 l l and a plurality of longitudinal supporting beams 112 distributed in a regular manner around said casing, each of them taking the form of a yoke with a stem 1126 which splits into two arms 112a, 1 12b.
  • Each of the supporting beams 112 is attached to the nozzle casing 110, on the one hand in the neighbourhood of its upstream end through the medium of a cross-member M attached to said casing by means which have not been shown, and, on the other hand, further downstream, through the medium of a pivot pin N passing through a lug 113 disposed at the periphery of the reinforcing ring 111.
  • Each controlled flap 102 comprises a flap surface 102): fixed to a cranked lever 102y, the assembly constituted by said flap surface and said cranked lever having a symmetrical shape in relation to a central plane P passing through the longitudinal axis of the nozzle (see FIG. 3).
  • Each cranked lever l02y is articulated, about a first geometric axis A substantially tangential in relation to the nozzle, to a yoke the two sides of which are formed by the arms 1 12a, 1 12b, ofa supporting beam 112.
  • the follower flaps 112 are disposed respectively between the controlled flaps 102 and in operation they are applied against the intemal edges of their neighbours by the pressure of the gas stream flowing through the nozzle.
  • An elastic annular apron (not shown) seals the joint between the fixed nozzle casing l 10 and the flaps With each controlled flap 102 there corresponds a mobile control element 103 constituted, for example, by the rod of a jack 104.
  • the body of the jack at its upstream end has two lugs 1040, 104b through the medium of which it is articulated about an axis R, to the two arms 112a, 1 12b of a supporting beam 112.
  • Intermediate or synchronising levers 105 are articulated in each case about a second geometric axis B (B substantially tangential to the nozzle, to the stems 1126 of two peripherally successive supporting beams 112. It will be observed that the geometric axes B and B respectively, of two intermediate levers 105 105 which peripherally succeed one another, are offset in relation to one another in the longitudinal direction of the nozzle, in order that one of them (3,) is located upstream of the other (B
  • the intermediate levers 105 and 105 are disposed in alternation with the controlled flaps 102 and each extend up to the neighbourhood of the respective central planes P of two successive controlled flaps. Two successive intermediate levers are disposed to either side of the central plane of each flap.
  • each controlled flap 102 there are associated two connecting links 106, 107 by means of which said flap is respectively connected to two successive intermediate levers 105,, 105
  • Each link 106 (107) is articulated, on the one hand, about a third geometric axis C (C substantially tangential to the nozzle, to the lever l02y of a controlled flap 102, and, on the other hand, about a fourth geometric axis D (D substantially tangential to the nozzle, to an intermediate lever 105 (105 adjacent said flap.
  • the two connecting links 106, 107 associated with one and the same controlled flap are disposed substantially in the central plane P of said flap.
  • the four geometric axes A, B (B C (C D (D associated with a controlled flap 102 and an intermediate lever 105, (105 adjacent the latter, are disposed in relation to one another in such a fashion that the quadrilateralfigure determined by their respective p'rojections on to the central plane P of said flap, substantially takes the forrh of a parallelogram AB,C D, (AB C D which deforms as the nozzle section varies.
  • This parallelogram has a fixed side AB, (AB and a moving side C D '(C D substantially equal and parallel to said fixed side, .from which latter it is separated by a variable distance h constituting the height of the parallelogram.
  • a parallelogram has a fixed side AB, (AB and a moving side C D '(C D substantially equal and parallel to said fixed side, .from which latter it is separated by a variable distance h constituting the height of the parallelogram.
  • the assembly formed by the controlled flaps 102, the intermediate levers 105, and 105 and the connecting links 106 and 107, constitutes an indented kinematic chain, closed around the nozzle, which compels each of the controlled flaps 102 to adopt a mean position which is common to the assembly of all the flaps.
  • Each mobile control element 103 corresponding to a controlled flap is hooked in at one end 103a, to the aforesaid kinematic chain at a point located in the central plane P of the flap.
  • one of the two links 106, 107 associated with said flap for example that 107, can be equipped with a lug 107a to which the end 103a of the control element 103 is hooked by means of a pivot pin F.
  • the lug 107a of the connecting link 107 to which hooking in is effected, is located at any instant at a fixed distance 12' from the fixed side AB (AB of the parallelogram AB C D (AB C D which is less than the height h of the parallelogram.
  • FIG. 7 illustrates in a highly schematic fashion and in perspective, the kinematic chain fitted to the nozzle in accordance with the invention.
  • the levers 102 of the controlled flaps 102 (not the flap surfaces 102x of the flaps), have been shown, and it has been assumed furthermore that the axes C and C by means of which the levers l02y are respectively articulated to the connecting links 106 and 107, are coaxial.
  • connecting links 106 and 107 which, for each controlled flap 102, are disposed, like the point of hook-in 1070 of the end 103a of the mobile control element 103, in the central plane P of said flap
  • the parasitic couples which develop in the known kinematic chain and to which reference has been made earlier are eliminated at least to a very large extent.
  • the links 107 act as force-transmitting elements.
  • the advantage is achieved that a substantial improvement in the efficiency of force transmission between each mobile control element 103 and the associated controlled flap 102 is obtained, this improvement being translated into terms either (for a given dimension of the jack 104) of an increase in the motive couple applied to the flap, or (for a given 44 motive couple) of a reduction in the dimensions (substantially the radial size) of said jack.
  • the present invention is applicable equally well to simple" nozzles, comprising a single ring of controlled flaps (as was the case in the nozzle just described), and to composite flame tube systems comprising two rings of controlled flaps associated respectively with a primary nozzle and a secondary nozzle.
  • variable-section nozzle of the type comprising a fixed structure embodying a fixed nozzle casing; a plurality of controlled flaps distributed around and in extension of the downstream portion of said fixed nozzle casing, each of which flaps extends to either side of a central plane containing the longitudinal axis of the nozzle, and is articulated about a first geometric axis disposed substantially tangential in relation to the nozzle, to said fixed structure; a plurality of intermediate levers disposed in alternation with said controlled flaps, each articulated, about a second geometric axis substantially tangential in relation to the nozzle, to said fixed structure; a plurality of connecting links each of which is articulated on the one hand about a third geometric axis substantially tangential in relation to the nozzle, to a controlled flap, and, on the other hand, about a fourth geometric axis substantially tangential in relation to the nozzle, to an intermediate lever adjacent said flap in order that each control flap is respectively attached to two successive intermediate levers, the assembly formed by said controlled flap
  • a nozzle as claimed in claim 1 in which said mobile control element corresponding to a flap is hooked into said kinematic chain at a point located on one of said two connecting links.
  • a nozzle as claimed in claim 4 in which two successive intermediate levers are disposed on either side of the central plane of each flap.

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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)
  • Supercharger (AREA)
US506869A 1973-09-21 1974-09-17 Nozzles having a variable cross-section Expired - Lifetime US3899133A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7333962A FR2244917B2 (enrdf_load_stackoverflow) 1973-09-21 1973-09-21

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US3899133A true US3899133A (en) 1975-08-12

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US506869A Expired - Lifetime US3899133A (en) 1973-09-21 1974-09-17 Nozzles having a variable cross-section

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US (1) US3899133A (enrdf_load_stackoverflow)
DE (1) DE2444485C2 (enrdf_load_stackoverflow)
FR (1) FR2244917B2 (enrdf_load_stackoverflow)
GB (1) GB1457790A (enrdf_load_stackoverflow)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5102050A (en) * 1991-01-22 1992-04-07 General Electric Company Divergent flap actuation system for two-dimensional convergent - divergent turbojet exhaust nozzle
US5566884A (en) * 1980-12-30 1996-10-22 Societe Natinale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Supersonic nozzle for a turbojet engine
EP0833047A2 (en) 1996-09-27 1998-04-01 United Technologies Corporation Pressure balanced synchronizing nozzle
EP0833046A2 (en) 1996-09-27 1998-04-01 United Technologies Corporation Compact pressure balanced nozzle
US20060086093A1 (en) * 2004-10-26 2006-04-27 Snecma Variable-section turbomachine nozzle with a one-piece control lever support

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2168047C1 (ru) * 1999-10-11 2001-05-27 Государственное унитарное предприятие "Завод имени В.Я. Климова" - дочернее предприятие государственного унитарного предприятия Военно-промышленный комплекс "МАПО" Сопло с отклоняемым вектором тяги

Citations (5)

* 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
US3837580A (en) * 1972-10-06 1974-09-24 Etude Et Construction De Moteu Nozzles having an adjustable cross-section

Patent Citations (5)

* 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
US3837580A (en) * 1972-10-06 1974-09-24 Etude Et Construction De Moteu Nozzles having an adjustable cross-section

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5566884A (en) * 1980-12-30 1996-10-22 Societe Natinale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Supersonic nozzle for a turbojet engine
US5102050A (en) * 1991-01-22 1992-04-07 General Electric Company Divergent flap actuation system for two-dimensional convergent - divergent turbojet exhaust nozzle
EP0833047A2 (en) 1996-09-27 1998-04-01 United Technologies Corporation Pressure balanced synchronizing nozzle
EP0833046A2 (en) 1996-09-27 1998-04-01 United Technologies Corporation Compact pressure balanced nozzle
US5813611A (en) * 1996-09-27 1998-09-29 United Technologies Corporation Compact pressure balanced fulcrum-link nozzle
US20060086093A1 (en) * 2004-10-26 2006-04-27 Snecma Variable-section turbomachine nozzle with a one-piece control lever support

Also Published As

Publication number Publication date
FR2244917A2 (enrdf_load_stackoverflow) 1975-04-18
DE2444485A1 (de) 1975-03-27
GB1457790A (en) 1976-12-08
DE2444485C2 (de) 1982-04-08
FR2244917B2 (enrdf_load_stackoverflow) 1978-01-13

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