US3807637A - Variable-geometry convergent-divergent nozzles for jet propulsion engines - Google Patents

Variable-geometry convergent-divergent nozzles for jet propulsion engines Download PDF

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Publication number
US3807637A
US3807637A US00351578A US35157873A US3807637A US 3807637 A US3807637 A US 3807637A US 00351578 A US00351578 A US 00351578A US 35157873 A US35157873 A US 35157873A US 3807637 A US3807637 A US 3807637A
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United States
Prior art keywords
nozzle
flaps
upstream
downstream
link
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Expired - Lifetime
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US00351578A
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English (en)
Inventor
A Camboulives
G Jourdain
Maout T Le
R Vandenbroucke
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Safran Aircraft Engines SAS
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SNECMA SAS
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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
    • F02K1/1223—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/90—Variable geometry
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/50—Kinematic linkage, i.e. transmission of position

Definitions

  • ABSTRACT A primary variable-geometry convergent-divergent nozzle is controllable so that both the throat section and the exit section of the nozzle can be varied simultaneously.
  • a first series of upstream controlled flaps of variable inclination are connected to a fixed structure, each being mounted for articulation about a hinge pin to vary the throat section of the nozzle.
  • a second series of downstream controlled flaps of variable inclination are directly connected, respectively, to the first series of flaps and are each mounted for articulation about a hinge pin relatively to the corresponding upstream flap to vary the exit section of the nozzle.
  • the inclinations of both series of flaps are variable by a control system which comprises, for each pair of interconnected upstream and downstream flaps, an active control element and a passive control element.
  • the active control element is connected on the one hand to the corresponding upstream flap and on the other hand to a controllable actuating element forming part of a jack.
  • the passive control element is connected on the one hand to the corresponding downstream flap and on the other hand to the fixed structure,
  • the present invention relates to a primary convergent-divergent nozzle of the kind comprising: a first set of actuated flaps, or upstream flaps, of variable inclination and each of which has an upstream portion connected to a fixed structure for articulation about a hinge pin, and a downstream portion; a second set of actuated flaps, or downstream flaps, of variable inclination and each of whichhas an upstream portion directly connected for relative articulation to the downstream portion of an upstream flap about a hinge pin, and a free downstream portion; and a control system for the inclination of said upstream and downstream flaps, so that it is possible to vary simultaneously both the throat area and the exit area of the nozzle.
  • the nozzle is designated more particularly for a jet propulsion engine, for example a turbojet engine, utilized to propel a flying machine, such as an aircraft.
  • a jet propulsion engine for example a turbojet engine, utilized to propel a flying machine, such as an aircraft.
  • the object of the present invention is to provide a nozzle of the kind referred to with a system, which is both simple and economical, to control the inclination of the upstream and downstream flaps, making it possible simultaneously and in accordance with a predetermined function, to adjust the throat area and the exit area of the nozzle in order to facilitate the matching of the engine to various flight conditions of the aircraft.
  • said control system comprises, in combination and for each pair of flaps constituted by an upstream flap and a downstream flap connected together for relative articulation, two separate control elements, namely an active" element connected on the one hand solely-to the upstream flap and, on the other hand, to a controllable actuating element, and a passive" control element connected on the one hand to the downstream flap and, on the other hand, to said fixed structure.
  • the controllable actuating element to which the active" control element is connected may, for example, constitute part of a jack. So far as the passive control is concerned, this may advantageously comprise a link with one end connected to the downstream flap for articulation about a hinge pin other than the common hinge pin linking upstream and downstream flaps of the same pair, and the other end connected to the fixed structure for articulation about a hinge pin other than the hinge pin connecting said upstream flap to the fixed structure.
  • said link has a' fixed length throughout the whole of the nozzle adjustment range. In another embodiment of the invention, said link has a fixed length throughout part of the nozzle adjustment range and a variable length throughout another part of said range.
  • the link may advantageously comprise, assembled so as to be slidable one in relation to the other, a first portion fixed to one end of the link and a second portion fixed to the other end.
  • each link is associated with a stop device which stops the relative sliding movement of the said portions of the link at a certain predetermined limit.
  • the mutually slidable link portions may cooperate with elastic return means which tends to reduce the total link length.
  • each pair of flaps constituted by an upstream flap and a downstream flap is associated with a stop device which stops the pivoting movement of the downstream flap in relation to the upstream flap at a predetermined angular limit.
  • This stop device may comprise, for example, two stop elements cooperating with each other and respectively carried by the two flaps of said pair thereof.
  • FIG. 1 is an axial sectional view, on the line II of FIG. 2, through a convergent-divergent variablegeometry nozzle in accordance with a first embodiment of the invention
  • FIG. 2 is an external view, in the direction of the arrow II of FIG. 1, of the nozzle shown in FIG. 1;
  • FIG. 3 is a transverse sectional view on the line III- III of FIG. 1 of a detail of the nozzle shown in FIG.
  • FIG. 4 is a transverse sectional view on the line IV-IV of FIG. 1, through another detail of the nozzle shown in FIG. 1;
  • FIG. 5 is an axial sectional view, on the line V-V of FIG. 7, through a convergent-divergent variablegeometry nozzle in accordance with a second embodiment of the invention, nozzle being illustrated in one of its extreme configurations;
  • FIG. 6 is a view similar to that of FIG. 5, but with the nozzle illustrated in the other of its extreme configurations, and
  • FIG. 7 is an external view, in the direction of the arrow VII in FIG. 5, through the nozzle shown in FIG. 5.
  • the general reference 1 is used to designate an exhaust system forming part of a jet engine designed to propel a flying machine such as an aircraft.
  • This exhaust system is, by way of example, of the composite" or fan type, with a primary duct 2 and a secondary fairing 3.
  • the primary duct 2 comprises a fixed jet pipe 4 connected at the forward end to a hot gas generator (not shown), for example a gas turbine, and extending towards the rear in the form of a variable-geometry primary nozzle 5, with an exit orifice 6.
  • a hot gas generator for example a gas turbine
  • the secondary fairing 3 whose transverse section is larger than that of the primary duct 2, surrounds said primary duct and extends towards the rear beyond the exit orifice 6 of the primary nozzle.
  • the primary duct 2 and the secondary fairing 3 define between them a secondary or by-pass duct 7.
  • a primary gas flow F passes through the primary nozzle 5, whilst the secondary by-pass airflow F passes through the secondary duct 7.
  • the present invention is concerned with the primary nozzle 5 and, more particularly, with its control. Selfevidently: the invention applies equally to cases where the primary nozzle 5 is not surrounded by a secondary fairing 3.
  • the jet pipe 4 at its rear end, has a flange 8 to which a flange 9 forming part of a ring 10 surrounding said jet pipe is bolted.
  • the ring 10 at its rear portion, has spaced ribs 11 and at its front end is integral with a suspension ring 12 likewise provided with spaced ribs 13.
  • a suspension ring 12 Around the whole of the ring spaced longitudinally extending plates 14a, 14b are arranged. Each of these plates is attached, at the forward end, to the suspension ring 12 by means of a hingebolt 15 passing through the corresponding rib 13 of said ring. It is also attached, at the rear, to a yoke 16 by means of a hinge bolt 17.
  • the yoke 16 is itself attached to the ring 10 by means of a hinge bolt 18 passing through the ribs 11 of said ring.
  • the assembly constituted by the longitudinal plates 14a, 14b creates a fixed structure designed to carry the variable geometry nozzle 5 as well as its control.
  • the nozzle 5 has two sets of actuated flaps of variable incliation, namely a series of upstream actuated flaps and a set of downstream actuated flaps 30. It also comprises upstream follower flaps 40 and downstream follower flaps 50 designed, in a manner known per se, to ensure peripheral sealing of the nozzle. As FIG. 3 shows, each follower flap (in this case an upstream follower flap 40) is located between two control flaps and is applied, by the pressure of the gas flow F against the internal edges of said actuated flaps.
  • Each upstream actuated flap 20 is articulated, at its upstream end, to the fixed structure 14a, 14b about a hinge pin 21.
  • An annular seal 19 provides sealing between the downstream portion of the jet pipe 4 and the upstream flaps 20 and 40.
  • Each downstream actuated flap is directly articulated, at its upstream end, to the downstream portion of an upstream actuated flap 20, about a hinge pin 31. Its downstream portion, which defines the exit section of the nozzle 5, is free.
  • the follower flaps and are relatively articulated one to the other in a similar manner.
  • a pair of actuated flaps constituted by an upstream actuated flap 20 and a downstream actuated flap 30, are considered.
  • an improved control system which makes it possible simultaneously to vary the throat section and the exit section of the nozzle, which is the object of the present invention.
  • This control system comprises two separate control elements, namely an activecontrol element 22 and a passive control element 32.
  • the active" control element 22 is connected, at one of its ends, solely to the upstream controlled flap by a hinge pin 23. At its other end the element 22 is fixed to a controllable actuatih g e lement such as the rod of a hydraulic jack 25.
  • the jack is articulated to the fixed structure 14a, 14b by means of stub shafts 26.
  • the reference 27 indicates an operating fluid pipe for the jack 25.
  • the passive" control element 32 is constituted by a forked link of a fixed length, with a handle 32c and two branches 32a, 32b.
  • the free end of the handle 320 of the link 32 is articulated to the downstream flap 30 about a pin 33 other than the mutual hinge pin 31 linking the upstream flap 20 and the downstream flap 30.
  • the free end of each of the branches 32a, 32b of the link is articulated to the fixed structure 14a, 14b about a hinge pin 34 other than the pin 21 articulating the upstream flap 20 to said fixed structure.
  • the nozzle comprises, for example, twelve pairs of actuated flaps 20, 30, with each of which there are associated a separate jack 25 and a separate link 32. All the jacks 25 are synchronized with one another.
  • each of the upstream actuated flaps 20 pivots about its hinge pin 21.
  • the point" 31 (which is fixed in relation both to an upstream actuated flap 20 and to a downstream actuated flap 30) thus describes a circular arc whose centre is 21 and radius R
  • the point" 33 which is fixed in relation to the control downstream actuated flap 30, describes a circular arc whose centre is 34 and with radius R
  • the present construction has the advantage that it makes it possible, by means of a single set ofjacks 25, simultaneously to control the upstream flaps 20 and the downstream flaps 30 of the nozzle.
  • This result is obtained by the use of links 32 each of which, although passive, performs the same function as an active" control element (such as a jack) with the advantages of a lower weight and lower cost, with a higher reliability.
  • FIGS. 5 to 7 relate to a second embodiment of the invention.
  • the same references have been used to indicate elements which are identical or similar to those already described with reference to FIGS. 1 to 4.
  • the fixed structure 14a, 14b and a pair 20, 30 of actuated flaps articulated to one another about a hinge pin 31.
  • a control system comprising an active control element 22 (associated with a jack 25) and a passive control element which is now indicated by the reference 132.
  • the passive control element 132 is constituted by a forked link having a handle" 132C and two branches 132a, 132b.
  • the free end of the handle 1326' of the link 132 is articulated to the downstream flap 30 about a hinge pin 33 other than the pin 32 which is responsible for linking together the upstream flap 20 and the downstream flap 30.
  • the free end of each of the branches 132a, 132b of the link is articulated to the fixed structure 14a, 14b about a hinge pin 34 other than the pin 21 articulating the upstream flap 20 to said fixed structure.
  • the handle 1320 of the link 132 comprises, telescopically slidable in relation to each other, a first portion or piston 132 cx articulated to the downstream flap 30 about the hinge pin 33, and a second portion or cylinder 132cy fixed to the branches 132a, 1321: of the link.
  • Two stop elements 150, 151 cooperating with one another and respectively carried by the piston 132cx and by the cylinder l32cy, engage to stop the relative sliding movement of the piston and cylinder at a predetermined limit.
  • each pair 20, 30 of controlled flaps is associated with an angular stop device designed to stop the pivotal movement of the downstream flap 30 in relation to the upstream flap 20, at a predetermined angular limit.
  • This angular stop device comprises two stop elements 160, 161 which cooperate with one another and which are carried respectively by the upstream flap and by the downstream flap 30.
  • the angular stop elements 160, 161 move together until they eventually contact.
  • the stop elements 150, 151 then disengage one another and the handle 1320 of the link 132 commences to extend. From this instant onwards, the link 132 ceases to have any effect upon the downstream flap 30 whose position, in relation to the upstream flap 20, is now solely defined by the angular stop elements 160, 161.
  • This second embodiment has the advantage over the first that it makes it possible to impose a variation in the ratio of exit section/throat section which is a more complex function. Accordingly, a greater degree of freedom in the choice of the locations of the hinge pins 33 and 34, to which the link 132 is articulated, is available and this makes it possible to satisfy other requirements or conditions such as that of minimum external size.
  • the reference 170 designates an elastic return device, such as the spring illustrated, urging the piston 132cx and the cylinder l32cy, of the handle 1320 of the link 132, in the direction of reducing total length of the link. This arrangement ensures automatic opening of the downstream flaps 30 when the nozzle 5 is inoperative.
  • a primary variable-geometry divergent nozzle comprising:
  • a first series of upstream actuated flaps of variable inclination each of which has a downstream portion and an upstream portion connected for articulation about a hinge pin to a fixed structure;
  • a system for controlling the inclination of said upstream and downstream flaps operative to vary simultaneously both the throat section and the exit section of the nozzle;
  • which system comprises, in combination and for each pair of flaps constituted by one of said upstream flaps and the corresponding one of said downstream flaps, two separate control elements, namely an active control element connected on the one hand solely tothe upstream flap and the other hand to a controllable actuating element, and a passive control element connected on the one hand to the downstream flap and on the other hand to said fixed structure.
  • each passive control element comprises a link with a first end connected to the corresponding downstream flap for articulation about a hinge pin other than that which interconnects the two flaps of the corresponding pair thereof, and a second end connected to the fixed structure for articulation about a hinge pin other than that which connects the corresponding upstream flap to said fixed structure.
  • a nozzle as claimed in claim 5, wherein said link comprises, slidably mounted in relation to each other, a first portion integral with said first end of the link and a second portion integral with said' second end of the link.
  • each link is associated with a stop device which stops the relative sliding movement of said link portions at a predetermined limit.
  • a nozzle as claimed in claim 7, wherein said stop device comprises two stop elements cooperating one with the other and respectively carried by said portions of the link.
  • each pair of flaps constituted by an upstream flap and a downstream flap is associated with a stop device to stop the pivotal movement of the downstream flap in relation to the upstream flap at a predetermined angular limit.
  • a nozzle as claimed in claim 10, wherein said angular stop device comprises two stop elements cooperating with each other and respectively carried by the two flaps of the corresponding pair thereof.

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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)
  • Transmission Devices (AREA)
US00351578A 1972-04-17 1973-04-16 Variable-geometry convergent-divergent nozzles for jet propulsion engines Expired - Lifetime US3807637A (en)

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FR7213397A FR2180440B1 (enrdf_load_stackoverflow) 1972-04-17 1972-04-17

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US (1) US3807637A (enrdf_load_stackoverflow)
DE (1) DE2318607C3 (enrdf_load_stackoverflow)
FR (1) FR2180440B1 (enrdf_load_stackoverflow)
GB (1) GB1418077A (enrdf_load_stackoverflow)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4052007A (en) * 1975-11-25 1977-10-04 United Technologies Corporation Flap-type two-dimensional nozzle
US4176792A (en) * 1977-07-11 1979-12-04 General Electric Company Variable area exhaust nozzle
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
US5140809A (en) * 1990-02-12 1992-08-25 General Electric Company Exhaust nozzle idle thrust spoiling method
US5235808A (en) * 1990-02-12 1993-08-17 General Electric Company Exhaust nozzle including idle thrust spoiling
US20090065610A1 (en) * 2007-08-21 2009-03-12 United Technologies Corporation Rollertrack pivoting axi-nozzle
US20090072049A1 (en) * 2007-08-21 2009-03-19 United Technologies Corporation Nozzle-area ratio float bias
US20120255806A1 (en) * 2011-04-06 2012-10-11 Lockheed Martin Corporation Noise reduction of supersonic jet engines
US20150050072A1 (en) * 2013-08-16 2015-02-19 Rolls-Royce Plc Panel attachment system
US9856956B2 (en) * 2015-01-20 2018-01-02 United Technologies Corporation Rod-and-bracket connector system for securing a pivoting member to a guide anchor moveably secured within a guide track
US11306680B2 (en) 2019-10-31 2022-04-19 Rolls-Royce Plc Exhaust nozzle
US11319896B2 (en) 2019-10-31 2022-05-03 Rolls-Royce Plc Exhaust nozzle
US11473526B2 (en) * 2019-10-31 2022-10-18 Rolls-Royce Plc Exhaust nozzle
CN115234402A (zh) * 2022-04-14 2022-10-25 中国航发沈阳发动机研究所 一种轴对称喷管控制机构
US20240003316A1 (en) * 2020-11-09 2024-01-04 Safran Aircraft Engines Turbojet engine rear part comprising a nozzle having flaps comprising levers that are movable by means of upstream and downstream bearing walls

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2714421B1 (fr) * 1980-01-14 1996-03-01 Snecma Tuyère comportant un convergent-divergent réglable, notamment pour moteur à réaction.
FR2724977B1 (fr) * 1980-12-30 1996-12-13 Snecma Tuyere convergente-divergente en particulier pour turboreacteur
FR2723145B1 (fr) * 1981-11-24 1996-12-13 Snecma Tuyere convergente-divergente, en particulier pour turboreacteur
FR2714422A1 (fr) * 1983-01-13 1995-06-30 Snecma Tuyère convergente-divergente, en particulier pour turboréacteur.
FR2734323A1 (fr) * 1985-04-17 1996-11-22 Snecma Perfectionnement aux tuyeres bidimensionnelles comportant en particulier un deviateur de jet
ES2105929B1 (es) * 1993-11-23 1998-05-01 Sener Ing & Sist Tobera axisimetrica orientable de geometria variable para propulsores de turbina de gas.
ES2194171T3 (es) * 1997-01-23 2003-11-16 Turbo Propulsores Ind Petalo divergente para una tobera de motor de turbina de gas.
RU2317432C1 (ru) * 2006-11-30 2008-02-20 Открытое акционерное общество "Климов" Система синхронизации створок сопла турбореактивного двигателя

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1329959A (fr) * 1962-07-27 1963-06-14 Rolls Royce Moteurs à réaction à tuyère convergente-divergente
FR1537247A (fr) * 1967-08-18 1968-08-23 United Aircraft Corp Tuyère d'éjection articulée à libre flottement

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4052007A (en) * 1975-11-25 1977-10-04 United Technologies Corporation Flap-type two-dimensional nozzle
US4176792A (en) * 1977-07-11 1979-12-04 General Electric Company Variable area exhaust nozzle
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
US5140809A (en) * 1990-02-12 1992-08-25 General Electric Company Exhaust nozzle idle thrust spoiling method
US5235808A (en) * 1990-02-12 1993-08-17 General Electric Company Exhaust nozzle including idle thrust spoiling
US8733107B2 (en) 2007-08-21 2014-05-27 United Technologies Corporation Nozzle-area ratio float bias
US20090065610A1 (en) * 2007-08-21 2009-03-12 United Technologies Corporation Rollertrack pivoting axi-nozzle
US20090072049A1 (en) * 2007-08-21 2009-03-19 United Technologies Corporation Nozzle-area ratio float bias
US7874160B2 (en) 2007-08-21 2011-01-25 United Technologies Corporation Nozzle-area ratio float bias
US20110088403A1 (en) * 2007-08-21 2011-04-21 United Technologies Corporation Nozzle-area ratio float bias
US8020386B2 (en) 2007-08-21 2011-09-20 United Technologies Corporation Rollertrack pivoting axi-nozzle
US20120255806A1 (en) * 2011-04-06 2012-10-11 Lockheed Martin Corporation Noise reduction of supersonic jet engines
US8443931B2 (en) * 2011-04-06 2013-05-21 Lockheed Martin Corporation Noise reduction of supersonic jet engines
US20150050072A1 (en) * 2013-08-16 2015-02-19 Rolls-Royce Plc Panel attachment system
US9243654B2 (en) * 2013-08-16 2016-01-26 Rolls-Royce Plc Panel attachment system
US9856956B2 (en) * 2015-01-20 2018-01-02 United Technologies Corporation Rod-and-bracket connector system for securing a pivoting member to a guide anchor moveably secured within a guide track
US11306680B2 (en) 2019-10-31 2022-04-19 Rolls-Royce Plc Exhaust nozzle
US11319896B2 (en) 2019-10-31 2022-05-03 Rolls-Royce Plc Exhaust nozzle
US11473526B2 (en) * 2019-10-31 2022-10-18 Rolls-Royce Plc Exhaust nozzle
US20240003316A1 (en) * 2020-11-09 2024-01-04 Safran Aircraft Engines Turbojet engine rear part comprising a nozzle having flaps comprising levers that are movable by means of upstream and downstream bearing walls
US12018628B2 (en) * 2020-11-09 2024-06-25 Safran Aircraft Engines Turbojet engine rear part comprising a nozzle having flaps comprising levers that are movable by means of upstream and downstream bearing walls
CN115234402A (zh) * 2022-04-14 2022-10-25 中国航发沈阳发动机研究所 一种轴对称喷管控制机构

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Publication number Publication date
DE2318607B2 (de) 1977-08-04
FR2180440A1 (enrdf_load_stackoverflow) 1973-11-30
FR2180440B1 (enrdf_load_stackoverflow) 1976-06-11
GB1418077A (en) 1975-12-17
DE2318607A1 (de) 1973-11-08
DE2318607C3 (de) 1978-03-16

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