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| Number | Title | Issue Date |
| 7299636 | Extendible exhaust nozzle bell for a rocket engine An exhaust nozzle bell for a rocket engine including a first part arranged on a motor of the rocket engine, and a second part coupled to the first part. The second part having a stowed position in which the second part surrounds the first part and is positioned clos... | 11/27/2007 |
| 7293401 | Jet engine noise suppressor An embodiment of the invention is a technique to suppress noise in a jet engine. A noise suppressor includes an exhaust duct to exhaust a first stream from an air stream taken from an inlet. The exhaust duct has an exit end. The air stream is divided into the first ... | 11/13/2007 |
| 7287369 | Method for extending a nozzle and extended nozzle for rocket drives A method for extending a nozzle for a rocket engine is described, in which at least one second region of the contour of the nozzle is arranged as an extension of a first region of the contour of the nozzle. This extension of the first region by the second region occ... | 10/30/2007 |
| 7278257 | Turbojet electromechanical thrust reverser with synchronized locking devices A turbojet thrust reverser has two doors that are displaceable between a reverser open position and a reverser closed position, each door being controlled by a respective electronic control unit connected to a FADEC, and each door having a respective locking device ... | 10/09/2007 |
| 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 |
| 7210283 | Maintenance and inhibition plate for a thrust reverser Each manual control unit for a moving part of a thrust reverser is associated with a maintenance plate that is pivotable between at least two positions: a first or “normal operation” position in which said plate prevents the manual control unit with which it is ... | 05/01/2007 |
| 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 |
| 7178338 | Variable area nozzle An exhaust nozzle assembly for a gas turbine engine, the assembly comprises a main axis, an inner nozzle, an outer nozzle, a translatable centre-body and an actuator for translating the centre-body between a forward position and a rearward position. The centre-body ... | 02/20/2007 |
| 7174704 | Split shroud exhaust nozzle A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a throat section of increased diameter. An inner shroud surrounds the centerbody and cooperates with t... | 02/13/2007 |
| 7165744 | Turbine engine arrangements A fan turbine engine arrangement is provided in which a core engine is aligned such that an input of a nacelle is aligned with the upwash of a wing to which the arrangement is secured. The engine drives a fan such that bypass flows produced by the fan are guided by ... | 01/23/2007 |
| 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 |
| 6983588 | Turbofan variable fan nozzle A turbofan exhaust nozzle includes a fan duct defined between a fan nacelle and core engine cowling. The duct includes an arcuate outlet at the trailing edge of the nacelle. A movable flap is disposed in a minor portion of the fan duct, with a remaining major portio... | 01/10/2006 |
| 6962044 | Method and apparatus of asymmetric injection into subsonic flow of a high aspect ratio/complex geometry nozzle The present invention reveals a method and apparatus for controlling the effective area and thrust vector angle of a fluid flow. In one embodiment, the fluid flow is controlled in an advanced, high aspect ratio, complex aperture geometry nozzle using asymmetric inje... | 11/08/2005 |
| 6948317 | Methods and apparatus for flade engine nozzle A method for adjusting a throat area of a jet aircraft exhaust nozzle assembly includes positioning a lower structure within a substantially rectangular nozzle assembly, coupling a ramp flap to the lower structure, and coupling an outer flap to the nozzle assembly s... | 09/27/2005 |
| 6938408 | Thrust vectoring and variable exhaust area for jet engine nozzle A jet engine nozzle having a pair of pivoting extension arms and a pair of pivoting shells connected to a jet pipe is provided. The first extension arm is pivotally connected to the jet pipe at a first location, while the second extension arm is pivotally connected ... | 09/06/2005 |
| 6935118 | Exhaust nozzle segmented basesheet and production method thereof A basesheet for use in an aircraft gas turbine engine exhaust nozzle includes a plurality of basesheet segments extending between longitudinally extending spaced apart basesheet leading and trailing edges, respectively, of the basesheet. Right and left hand baseshee... | 08/30/2005 |
| 6901740 | Engine with a central spike for a space launcher The pointed end of a central spike, used in an engine of a space launcher, may have a deformable structure that can adopt either a folded position or a deployed position. ... | 06/07/2005 |
| 6705547 | Active noise reducing nozzle A nozzle where the sector into which noise reduction is sought (the direction of populated areas) has a moving lip, driven by actuators in an oscillatory, periodic or sinusoidal motion, around the mid position, to and from the axis, so as to cause the shear layer to... | 03/16/2004 |
| 6622472 | Apparatus and method for thrust vector control A multi-lobed, low friction vane, thrust vector controller is disclosed. Low friction vanes are independently movable into and out of the thrust of the exhaust of a jet engine. All vanes may be used together to adjust exhaust surface area to maximize thru... | 09/23/2003 |
| 6546716 | Jet engine nozzle with variable thrust vectoring and exhaust area A variable area exhaust nozzle with a variable thrust vector angle for a turbo-fan engine and mounted on the aft portion of the nacelle which wraps said engine. The nozzle may include a fixed structure having at least two lateral arms separating two radia... | 04/15/2003 |
| 6415599 | Engine interface for axisymmetric vectoring nozzle An aircraft gas turbine axisymmetric vectoring nozzle has an interface ring centered about a nozzle, a vectoring ring disposed radially inwardly of and apart from the interface ring, and a bearing radially disposed between the vectoring ring and the inter... | 07/09/2002 |
| 6318070 | Variable area nozzle for gas turbine engines driven by shape memory alloy actuators A gas turbine engine includes a variable area nozzle having a plurality of flaps. The flaps are actuated by a plurality of actuating mechanisms driven by shape memory alloy (SMA) actuators to vary fan exist nozzle area. The SMA actuator has a deformed sha... | 11/20/2001 |
| 6240720 | Hybrid-composite gas turbine exhaust nozzle compression link A hybrid-composite gas turbine exhaust nozzle compression link is formed as an elongated hollow tubular cylindrical shell having an axis of elongation. In cross section taken perpendicular to the axis of elongation, the shell has a structure of an inner r... | 06/05/2001 |
| 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 |
| 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 |
| 6142416 | Hydraulic failsafe system and method for an axisymmetric vectoring nozzle A nozzle failsafe nozzle actuating system for an aircraft gas turbine engine variable exhaust nozzle having a plurality of pivotal flaps circumferentially disposed about a nozzle centerline and bounding an exhaust gas flowpath in the nozzle is provided wi... | 11/07/2000 |
| 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 |
| 6045091 | Thrust reverser with improved impact strength An aircraft gas turbine-engine thrust-reverser specifically designed to withstand impacts possibly caused by objects propelled from the engines around which they are mounted, for instance disk or blade fragments. These impacts have the energy to distort t... | 04/04/2000 |
| 6000216 | Actuating system for a cascade type thrust reverser A thrust reverser is disclosed for a turbojet engine having a cowling with a longitudinal axis, the cowling having an inner surface forming an outer boundary of a gas flow duct and a reverse thrust opening. The thrust reverser has a panel movable with res... | 12/14/1999 |
| 6000635 | Exhaust nozzle for a turbojet engine The invention is an exhaust nozzle for an after-burning turbojet engine having an exhaust passage mounted in an aircraft, The exhaust nozzle includes a duct having an open first end coupled to the exhaust passage of the turbojet engine, a open second end,... | 12/14/1999 |
| 5934564 | Variable geometry turbojet engine exhaust nozzle A variable geometry exhaust nozzle is disclosed for a turbojet engine having a rear portion, the nozzle having an outer flap ring with a plurality of driven outer flaps and a plurality of outer interlock flaps, each outer flap being pivotally connected to... | 08/10/1999 |
| 5893265 | Pivoting door thrust reverser with deflecting vane The present invention relates to a thrust reverser for a turbojet engine having a cowling bounding a flow duct through which gases flow from the front of the cowling towards a rear of the cowling, the cowling having at least one reverse thrust opening com... | 04/13/1999 |
| 5819528 | Turbojet engine thrust reverser having dual pivoting doors A thrust reverser for a turbojet engine is disclosed having a first thrust reverser door pivotally attached to the engine cowling so as to be movable between a forward thrust position and a reverse thrust position, the first thrust reverser door having a ... | 10/13/1998 |
| 5813609 | Hinged lined exhaust nozzle An exhaust nozzle includes circumferentially adjoining primary flaps and seals hinged at forward ends to an annular casing. The primary flaps and seals are actuated between open and closed positions for varying flow area of a throat defined at the aft end... | 09/29/1998 |
| 5806302 | Variable fan exhaust area nozzle for aircraft gas turbine engine with thrust reverser A structure to provide a variable nozzle for the fan air flow of a turbofan aircraft gas turbine engine with the nozzle being defined by the exit throat area defined by the aft edge of a trailing edge portion of the fan cowl and the core engine housing. A... | 09/15/1998 |
| 5799903 | Pivoting door thrust reverser with cooperating panels A thrust reverser is disclosed for a turbojet engine having an outer cowling and an inner cowling forming a generally annular gas flow duct therebetween, the thrust reverser having at least one thrust reverser door pivotally attached to the outer cowling ... | 09/01/1998 |
