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8020386 |
Rollertrack pivoting axi-nozzle
A mechanism included in a convergent-divergent nozzle connected to an aftward portion of a gas turbine engine, which mechanism includes at least one actuator configured to be connected to the...
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8015819 |
Wet active chevron nozzle for controllable jet noise reduction
Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream...
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8015820 |
Gas turbine engine exhaust component and manufacturing method of same
A gas turbine exhaust component, such as an exhaust nozzle, is provided that includes circumferential ribs arranged along a longitudinal axis. Longitudinal strakes are supported by the...
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7966824 |
Jet engine nozzle exit configurations and associated systems and methods
Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow...
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7926285 |
Modular chevron exhaust nozzle
An exhaust nozzle for a gas turbine engine includes a modular chevron. The chevron includes dual skins fixedly joined together at a base flange, and at a rim extending along the trailing edge of...
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7854124 |
Combined control for supplying cooling air and support air in a turbine engine nozzle
A balance pressure control is provided for flaps which pivot in a rear of a gas turbine engine nozzle to change the cross-sectional area of the nozzle. An actuator drives a sync ring to move the...
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7845176 |
Mode strut and divergent flap interface
In one example, a gas turbine engine includes an exhaust nozzle. The exhaust nozzle includes a flap supported relative to a static structure by a strut. The flap includes a backbone providing a...
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7797944 |
Gas turbine engine having slim-line nacelle
A nacelle assembly for a gas turbine engine includes a nacelle, a variable area fan nozzle, a sensor that detects a windmilling condition and a controller that communicates with the sensor. The...
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7775048 |
Seal assembly
A sprung seal assembly includes a flexible sprung seal having a center section disposed between opposing curved and cantilevered first and second end sections. First and second free edges of the...
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7770399 |
Gas turbine engine nozzle liner with thermally compliant attachment brackets
A gas turbine engine has the convergent flaps and seals of an adjustable cross-sectional area nozzle connected to associated liners with a thermally compliant bracket. The bracket includes spaced...
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7757477 |
Convergent divergent nozzle with slot cooled nozzle liner
A nozzle system includes a multitude of circumferentially distributed convergent flaps and seals that circumscribe an engine centerline. A cooling liner body cooperates with a cooling liner panel...
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7685825 |
Axially split nozzle liner for convergent nozzle
A convergent/divergent nozzle for a gas turbine engine includes liners that are attached to the convergent flaps and seals. The liner is formed of two separate plates. By splitting the liner into...
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7637095 |
Thrust vectorable fan variable area nozzle for a gas turbine engine fan nacelle
A thrust vectorable fan variable area nozzle (FVAN) includes a synchronizing ring, a static ring, and a flap assembly mounted within a fan nacelle. An actuator assembly selectively rotates...
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7624567 |
Convergent divergent nozzle with interlocking divergent flaps
A nozzle system includes a multitude of circumferentially distributed convergent flaps, divergent flaps and inter-flap seals which circumscribe an engine centerline and define the radial outer...
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7617685 |
Quick change fastener system for attaching liner bracket to convergent flap and seal in turbine nozzle
A quick change connection is provided for attaching a bracket and liner subassembly to convergent flaps and seals in an adjustable nozzle for a gas turbine engine. A threaded attachment member has...
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7600384 |
Gas exhaust nozzle for a bypass turbomachine having an exhaust or throat section that can be varied by moving the secondary cowl
The invention relates to an exhaust nozzle for a bypass turbomachine, the nozzle comprising a central body, a primary cowl surrounding the central body to define a primary channel, and a secondary...
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7578133 |
Reduced radar cross section exhaust nozzle assembly
An exhaust nozzle assembly includes a plurality of interfitting flap assemblies that are moveable between a maximum area ratio and a minimum area ratio. Each of the pluralities of flap assemblies...
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7555904 |
Thermally compliant rivet connection for connecting turbine engine liner to convergent flap and seal for turbine nozzle
A bracket for attaching a liner to the divergent flaps and seals in a gas turbine engine convergent/divergent nozzle includes a rivet connection. There is clearance between a rivet and an opening...
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7520135 |
Variable-section turbomachine nozzle
A variable-section turbomachine nozzle comprises a plurality of moving flaps, and a moving flap control system comprising control levers each associated with a respective moving flap, the control...
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7475547 |
Convergent turbojet exhaust nozzle
A convergent turbojet exhaust nozzle comprising a ring of hinged flaps made up of controlled flaps and of follower flaps disposed in alternation and co-operating at their upstream ends with a...
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7458221 |
Variable area nozzle including a plurality of convexly vanes with a crowned contour, in a vane to vane sealing arrangement and with nonuniform lengths
A variable area nozzle comprising a concentric support and a plurality of convexly contoured self sealing vanes is disclosed and claimed. The vanes are circumferentially and rotatably mounted to...
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7430852 |
Turbojet having a large bypass ratio
A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its...
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7377099 |
System and method for cooling lateral edge regions of a divergent seal of an axisymmetric nozzle
An axisymmetric nozzle for a gas turbine engine has divergent flaps and seals disposed about a central longitudinal axis thereof. The divergent flaps and seals each have an inner surface defining...
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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...
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7296397 |
Ventilation system for a convergent divergent exhaust nozzle
The invention relates to a ventilation system for a convergent divergent exhaust nozzle in a bypass turbojet comprising an afterburn chamber surrounded by an annular passage through which...
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7178325 |
Divergent flap for a gas turbine engine
A divergent flap assembly of a gas turbine engine includes a hotsheet, a backbone structure for supporting the hotsheet, and a plow portion secured to the backbone structure to bridge a gap between...
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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...
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6895742 |
Bifold door thrust reverser
A fan thrust reverser includes an outer louver door joined to an inner blocker door by a drive link in a bifold configuration. The louver door is stowed closed in the outer skin of a fan nacelle...
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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...
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6658854 |
Methods and apparatus for retaining gas turbine engine nozzle basesheets
A method for assembling a flap and seal system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates attaching a basesheet to a backbone. The method...
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6378781 |
Exit area control mechanism for convergent divergent nozzles
A convergent-divergent nozzle with an exit area control mechanism includes convergent and divergent petals extending from a nozzle structure on which a synchronising ring is allowed to rotate and...
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6378294 |
System for activating an adjustable tube by means of an elastic ring for a thrust nozzle
A steerable nozzle for a reaction engine comprises a fixed portion (1) for connection to the engine, a plurality of steerable flaps (21) mounted on one end (11) of the fixed portion, and flap...
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6360527 |
Axisymmetric, converging-diverging exhaust nozzle swiveled by a guided ring
An axisymmetric, converging-diverging exhaust nozzle swiveled by a guided vectoring ring (20). The guides comprise three axial apertures (44) which are each located in a base firmly joined to...
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6349539 |
Axisymmetric, converging-diverging, jet-deflecting turbojet-engine exhaust-nozzle
An axisymmetric, converging-diverging turbojet-engine exhaust nozzle for jet deflection. The diverging flaps are connected by linkrods to a vectoring ring (13). The vectoring ring (13) is driven by...
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6347510 |
Axi-nozzle ejector seal
A nozzle for a gas turbine engine is provided which includes an outer casing, a convergent section, a divergent section, an external fairing, and a collapsible seal member. The divergent section...
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6299077 |
Actuation system for convergent/divergent nozzle
The horsepower requirements for the actuation system for a convergent/divergent exhaust nozzle for a gas turbine engine is reduced by the judicious selection of the crank arms and their location on...
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6298658 |
Multi-stable thrust vectoring nozzle
A stream of primary gas flowing through a bi-stable thrust vectoring nozzle becomes attached to a first or second surface extending downstream of the nozzle, each surface incorporating one or more...
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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...
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6212877 |
Vectoring ring support and actuation mechanism for axisymmetric vectoring nozzle with a universal joint
A vectoring ring support and actuation apparatus is provided for transferring the side loads acting on a vectoring ring and generated by a gas turbine engine thrust vectoring nozzle to a relatively...
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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...
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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...
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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),...
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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...
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6109021 |
Vectoring nozzle calibration
A method and system are used to calibrate a plurality of actuators joined to an actuation ring in a control system for vectoring exhaust flaps in a vectoring nozzle. The actuators include output...
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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...
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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...
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6070830 |
Faceted exhaust nozzle
A fixed geometry duct defining a gas turbine engine exhaust nozzle includes a plurality of circumferentially adjoining flat triangular facets and coaxial first and second openings at opposite ends...
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5893518 |
Attachment means for flaps of variable exhaust nozzle
The external flaps of a variable exhaust nozzle for a gas turbine engine are attached to the nozzle by a pair of pivotal rods attached to the nozzle's internal support structure and slidably fits...
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5842643 |
Articulated exhaust nozzle fairing
A variable area exhaust nozzle includes a divergent flap joined to an outer flap for allowing relative rotation and translation therebetween. An articulated fairing joins the aft ends of the...
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5839663 |
Gas turbine exhaust nozzle flap and flap seal apparatus
An exhaust nozzle for a gas turbine engine is provided which includes a plurality of flaps and an abradable coating. Each flap includes seal surfaces with depressions disposed therein. The flaps...
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