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| Number | Title | Issue Date |
| 7302793 | Methods and apparatus to reduce turbine engine nozzle basesheet stresses A method facilitates assembling a flap system for a gas turbine engine exhaust nozzle including at least one backbone assembly. The method comprises providing a basesheet including a pair of circumferentially-spaced sides coupled together by an upstream side and a d... | 12/04/2007 |
| 7240493 | Method and device for reducing engine noise A method and device to reduce the noise produced by jet aircraft engines and/or other supersonic nozzles involves the use of corrugated engine seals (30) for the secondary internal divergent flaps (14) of the nozzle (10). Such corrugated seals (... | 07/10/2007 |
| 7188477 | High temperature dynamic seal for scramjet variable geometry A seal assembly for use in an engine, such as a scramjet engine, having a movable element, such as inlet cowl flap, is provided. The movable element has an outboard structural member which requires thermal protection. The seal assembly includes a sealing element and... | 03/13/2007 |
| 7117682 | Turbojet axisymmetric nozzle controlled hot flap shutter A controlled hot flap shutter for a turbojet nozzle includes a friction surface made of metal, and including straight lateral flanks to reduce the gap between each controlled hot flap shutter and the tracking flap shutters adjacent thereto. ... | 10/10/2006 |
| 7096661 | Axial divergent section slot nozzle An axial divergent section slot nozzle for an engine is provided. The nozzle has a plurality of spaced apart divergent flaps, at least one device for moving the divergent flaps to change a cross sectional area of the nozzle in a throat region, and a bridge member po... | 08/29/2006 |
| 7062901 | Variable geometry nozzle with flexible side wall The disclosed device is directed toward a periodic combustion propulsion system. The periodic combustion propulsion system comprises at least one periodic combustion chamber configured to contain periodic combustion and at least one supersonic exhaust nozzle coupled... | 06/20/2006 |
| 7032835 | Convergent/divergent nozzle with modulated cooling A nozzle system includes a multiple of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer boundary of a gas path. Each divergent flap includes a multiple of cooling... | 04/25/2006 |
| 7013650 | Flexible flap for a variable-section turbomachine nozzle In a variable-section turbomachine nozzle, a plurality of flexible follower flaps are provided that are interposed between adjacent controlled flaps against which the follower flaps are held by fastener means, each follower flap comprising a plurality of independent... | 03/21/2006 |
| 7007483 | Turbine engine nozzle A convergent/divergent nozzle for a gas turbine engine has a throat portion of non-constant radius of curvature varying from an upstream high value to an intermediate low value and then to a downstream high value. ... | 03/07/2006 |
| 6993914 | Convergent-divergent turbojet nozzle The present invention relates to a convergent-divergent turbojet nozzle (1) comprising driven divergent flaps (4a), follower divergent flaps (4b) interposed between the driven flaps, and means (32) for supplying cooling air ... | 02/07/2006 |
| 6983602 | Ejector cooled nozzle A gas turbine engine exhaust nozzle includes a divergent section located aft of a convergent section and a throat therebetween. An exterior fairing is spaced radially outwardly of the divergent section. An ejector cooling air flowpath leads from an ejector cooling a... | 01/10/2006 |
| 6966189 | System for sealing the secondary flow at the inlet to a nozzle of a turbomachine having a post-combustion chamber A turbomachine comprising, downstream from the turbine, a post-combustion chamber defined by a thermal protection lining inside a casing defining an annular channel for a secondary flow, an annular diaphragm secured at the downstream end of said channel, said nozzle... | 11/22/2005 |
| 6779336 | Cooled variable geometry exhaust nozzle A variable geometry exhaust nozzle 10 for a turbine engine includes convergent and divergent flaps 12, 18 that circumscribe a gaspath 26 and define convergent and divergent nozzle sections 30, 32 with a throat 34 therebetween. A pr... | 08/24/2004 |
| 6398129 | Throat configuration for axisymmetric nozzle The radius of the hinged portion of the convergent/divergent axisymmetrical exhaust nozzle of a gas turbine engine is configured at the surface seeing the flow to be contoured at a critical radius so to enhance the flow characteristics of the nozzle and i... | 06/04/2002 |
| 6375095 | Swiveling, converging-diverging, axisymmetric exhaust nozzle An axisymmetric, converging-diverging and swiveling exhaust nozzle includes converging flaps (3) driven by an axially displaceable drive ring (7). The diverging flaps (15) are connected by linkrods (20) to a pivoting ring (21). The pivoting ring (21) is m... | 04/23/2002 |
| 6327846 | Universal-joint vectoring system for a turbojet-engine exhaust nozzle The invention relates to a wide-vectoring, axisymmetric turbojet-engine exhaust nozzle including vectoring structure (12) supporting a plurality of converging flaps (21). The vectoring structure is mounted on the downstream end of an exhaust housing (2) b... | 12/11/2001 |
| 6276126 | Axisymmetric, directable and adjustable turbojet-engine exhaust nozzle An axially symmetric turbojet-engine exhaust nozzle which is directable as a unit. The exhaust nozzle is situated downstream of an exhaust duct (1) fitted with a spherical wall (5). A single control ring (12) driven by linear actuators (30) allows regulat... | 08/21/2001 |
| 6199772 | Linear actuation and vectoring ring support mechanism for axisymmetric vectoring nozzle Three vectoring ring support and actuation apparatuses are disposed in an equi-angular manner circumferentially about the engine casing. Each of the vectoring ring support and actuation apparatuses includes a vectoring ring means to transfer side loads fr... | 03/13/2001 |
| 6192671 | Cross bar centering mechanism for slave petals in covergent divergent nozzles with variable geometry Divergent petal arrangement for convergent-divergent nozzles with thrust vectoring capability through changes in the divergent section geometry, in which the position of each slave divergent petals 4 is determined by a centering mechanism 31, made up by t... | 02/27/2001 |
| 6148608 | Divergent petal arrangement for a convergent-divergent aircraft engine nozzle Divergent petal arrangement for convergent-divergent nozzles for application in aircraft engines, where the divergent section comprises master divergent petals (3) and slave divergent petals (4), having the latter a bent cross section with the concave sid... | 11/21/2000 |
| 6102307 | Load strut for a variable geometry nozzle A load strut for divergent master petals of variable geometry nozzles, of the type which exhibit a control system constituted by three ring-like pieces, the external ring piece being divided into two half-rings, which joins the two half-rings and the corr... | 08/15/2000 |
| 6098400 | Divergent petal for gas turbine engine nozzle Divergent petal for a gas turbine engine nozzle. This petal (2) is articulated in its front edge to a convergent petal (1), by means of a cylindrical joint (4) while its back surface is articulated at an intermediate point to a compression bar (5) by mean... | 08/08/2000 |
| 6067793 | Variable geometry axisymmetric nozzle with 2-d thrust vectoring intended for a gas turbine engine Axisymmetric nozzles of variable geometry and orientation of flow intended for gas turbine engines, especially for aircraft. The nozzle comprises control means for adjusting the throat area and vectoring the thrust, which means are formed by three rings c... | 05/30/2000 |
| 5970705 | Variable configuration final nozzle assembly for a combined rocket/ramjet engine A variable configuration final nozzle assembly for a combined rocket/ramjet engine consists of a fixed annular plug 20 together with upstream and downstream arrays of flaps 10,14 pivoted to the wall of a jet pipe 1 at their upstream and downstream ends 12... | 10/26/1999 |
| 5820024 | Hollow nozzle actuating ring A hollow actuating ring and apparatus for actuating and/or vectoring the flaps of an aircraft gas turbine engine nozzle by transferring actuation loads from a small number of actuators to a greater number of pivotal divergent flap members of the nozzle. T... | 10/13/1998 |
| 5794850 | Enclosed pressure balanced sync ring nozzle The C/D axisymmetrical exhaust nozzle for a gas turbine engine is designed to fit on the engine and STOVL aircraft and includes an hydraulic actuator and a combined load balancing piston/sync ring that is judiciously mounted in the assembly and discretely... | 08/18/1998 |
| 5716025 | Specially configured deflection edge thrust reverser for jet engine The reverser includes a partition (28) exhibiting openings (19) and separating the cavity (16) which exists, when the doors (2) are in the closed position, between the front part (7) of the internal panel (11) of the door and the stream of gaseous flow (1... | 02/10/1998 |
| 5667140 | Engine exhaust nozzle seal A seal for a gas turbine engine exhaust nozzle is provided, comprising a body, a spine member attached to one side of the body, and a plurality of face segments attached to the side of the body opposite that to which the spine member is attached. The body... | 09/16/1997 |
| 5613636 | Axisymmetric nozzles of variable geometry and orientation of the flow which are intended for gas turbine engines Improvements in orientable axisymmetric nozzles of variable geometry which are intended for gas turbine engines, which nozzles comprise a convergent zone (2) followed by a divergent zone (3), both formed by main petals (4-5) and secondary petals (33-34), ... | 03/25/1997 |
| 5611489 | Actuating system for a variable area exhaust nozzle An actuating system for a variable area exhaust nozzle is disclosed having inner and outer flaps pivotally connected to an airframe whose positions may be varied by a single set of control cylinders. The control cylinders have a case in which is slidably ... | 03/18/1997 |
| 5566884 | Supersonic nozzle for a turbojet engine Convergent flaps of a jet engine nozzle are controlled by actuating cylinders through actuating levers hinged to the fixed structure of the engine and by connecting rods. Divergent flaps are slaved to the convergent flaps by connecting rods themselves dri... | 10/22/1996 |
| 5542607 | Supersonic nozzle, in particular for a turbojet engine A turbojet engine has an outlet duct to which an annular array of actuating cylinders for nozzle flaps are hinged. The housings for the cylinders are connected together by transverse members to form a rigid structure coaxial with the outlet duct. The arra... | 08/06/1996 |
| 5513799 | Divergent master petal for orientable nozzles of variable geometry intended for gas turbine engines A divergent master petal for orientable nozzles of variable geometry intended for gas turbine engines, which is connected by means of articulations to the convergent master petal (4) and to a bar (12) which connects the master petal to the control mechani... | 05/07/1996 |
| 5511376 | Axisymmetric vectoring nozzle A convergent/divergent nozzle (14) has five trains of flaps. Each train is comprised of an inboard (26) and outboard (20) convergent flap, an inboard (48) and outboard (44) divergent flap and an external flap (62). The five external flaps (62) maintain th... | 04/30/1996 |
| 5494221 | Variable geometry turbojet engine exhaust nozzle A variable geometry exhaust nozzle for a turbojet engine is disclosed having an array of outer flaps and an array of inner flaps radially spaced apart and extending about a central axis of the exhaust duct structure. The array of outer flaps comprises a p... | 02/27/1996 |
| 5485959 | Axisymmetric vectoring exhaust nozzle thermal shield A thrust vectoring axisymmetric vectoring exhaust nozzle having universally pivoting divergent flaps is provided with a surrounding thermal shield of overlapping outer flaps and seals generally disposed in an aftwards converging conical arrangement and ha... | 01/23/1996 |
| 5461856 | Divergent slave petal for sealing in variable geometry exhaust nozzles for gas turbine propulsion units A divergent slave petal for sealing in variable geometry exhaust nozzles for gas turbine propulsion units includes a base plate for bearing axial forces but having minimum capacity for transmitting torsional forces and a plurality of discrete transverse e... | 10/31/1995 |
| 5364029 | Axisymmetric convergent/divergent nozzle with external flaps The gas turbine engine nozzle has fifteen divergent flaps (18) secured to fifteen convergent flaps (14). Five external flaps (30), are each of a "V" shape, and surround the divergent flaps. The position of all flaps is adjustable (22) for varying the nozz... | 11/15/1994 |
| 5359851 | Variable geometry exhaust nozzle for a turbojet engine A variable geometry nozzle for a turbojet engine is disclosed wherein the adjustment of the cross-sectional area of the nozzle in a converging-diverging configuration is controlled by a single control system. The single control system varies the positions... | 11/01/1994 |
| 5351888 | Multi-axis vectorable exhaust nozzle A convergent-divergent exhaust nozzle is mounted to an exhaust duct of a jet aircraft engine by a circumferentially-spaced set of hydraulic cylinders. The cylinders are interconnected in captured flow via hydraulic circuits which allow the cylinders to fu... | 10/04/1994 |
