| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 239265330 | Radially outermost flow defining wall adjustable | 35 |
| 20080230629 | 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 slot. A slider interconnects a strut end to the backbone. In one example, the slider includes a body that is slidingly received within the slot. A boss extends from the body and provides a first feature. The strut end includes a second feature that cooperates with the first feature to prevent relative rotation between the slider and a portion of the strut end. | 09-25-2008 |
| 20090266912 | FAN VARIABLE AREA NOZZLE FOR A GAS TURBINE ENGINE FAN NACELLE WITH SLIDING ACTUATION SYSTEM - A fan variable area nozzle (FVAN) includes a flap assembly which varies a fan nozzle exit area. An actuator system drives a sliding drive ring relative a multitude of slider tracks mounted to a fan nacelle to adjust each flap of the flap assembly through the flap linkage to pitch the flap assembly about a circumferential hinge line to vary the diameter of the annular fan nozzle exit area between the fan nacelle and the core nacelle. The FVAN may be separated into a multiple of drive ring sectors which are each independently adjustable by an associated actuator of the actuator system to provide a low profile drag asymmetrical fan nozzle exit area. | 10-29-2009 |
| 20110017843 | SYSTEM FOR ACTUATING AND CONTROLLING THE MOBILE COWLING OF A TURBOJET ENGINE NACELLE - The invention relates to a system for actuating and controlling at least one mobile cowling ( | 01-27-2011 |
| 20110139897 | MOBILE THRUST REVERSER COWL AND THRUST REVERSER PROVIDED WITH SUCH A COWL - Said mobile cowl ( | 06-16-2011 |
| 20110284660 | THRUST REVERSER FOR A TURBOFAN ENGINE NACELLE - The invention relates to a thrust reverser for a turbofan engine nacelle including a stationary portion ( | 11-24-2011 |
| 20120067975 | THRUST REVERSING DEVICE - The invention relates to a thrust reversing device ( | 03-22-2012 |
| 20140117113 | METHODS AND APPARATUS FOR SEALING VARIABLE AREA FAN NOZZLES OF JET ENGINES - Methods and apparatus for sealing variable area fan nozzles of jet engines are disclosed. An apparatus in accordance with the teachings of this disclosure includes a frame and a seal to be coupled to the frame. The seal to enclose petals of a variable area fan nozzle to substantially prevent airflow between the petals. | 05-01-2014 |
| 20140131481 | THREADED ROD FOR SYSTEM FOR DEPLOYING A DEPLOYABLE DIVERGENT SEGMENT OF A THRUSTER - The divergent segment comprises a stationary divergent portion and a movable divergent portion suitable for occupying a retracted position and a deployed position. The threaded rod has a head suitable for being supported by a support secured to the stationary divergent portion in cooperation with rotary drive means for driving the threaded rod in rotation, and a tip suitable for being inserted in a holder sleeve secured to the stationary divergent portion. The threaded rod is suitable for co-operating with a nut secured to the movable divergent portion so that rotation of said rod causes the movable divergent portion to move. The tip presents an enlargement having at least one groove passing axially therethrough. | 05-15-2014 |
| 20150361919 | Fan Variable Area Nozzle for a Gas Turbine Engine Fan Nacelle With Sliding Actuation System - A linkage comprises a drive ring, a flap linkage mounted to each of a multiple of flaps and the drive ring, and an actuator system which drives the drive ring to cause the multiple of flaps to pivot. A method of driving a multiple of flaps is also disclosed. | 12-17-2015 |
| 20160003190 | VARIABLE AREA NOZZLE FOR GAS TURBINE ENGINE - A variable area fan nozzle comprises an actuator flap and a follower flap. The actuator flap has a portion in contact with a portion of the follower flap. A bias member biases the follower flap outwardly. An actuator actuates the actuator flap inwardly and outwardly to, in turn, move the follower flap against the bias member and to vary an area of an exhaust nozzle. The flap actuator is operable to drive the actuator flap out of contact with the follower flap into a thrust reverser position. | 01-07-2016 |
| 20160076484 | TURBOJET ENGINE NACELLE THRUST REVERSER COMPRISING CASCADES SECURED TO THE MOBILE COWLS - A thrust reverser of a turbojet engine nacelle includes mobile cowls which retreat with respect to a front frame while causing via cylinders the tipping of the shutters initially folded inside these cowls, so as to substantially close an annular stream of cold air, and cascades disposed around the annular stream which receive the cold air flow in order to send it towards the front. In particular, the cascades are secured to the mobile cowls and slide. | 03-17-2016 |
| 20160131078 | SLEEVE LINKAGE FOR THRUST REVERSER - Aspects of the disclosure are directed to a system for a thrust reverser of an aircraft comprising: a primary sleeve, and a secondary sleeve, wherein a first stroke associated with the primary sleeve is different from a second stroke associated with the secondary sleeve, and wherein the primary sleeve traverses a first distance associated with the first stroke at the outset of a deployment of the thrust reverser and a second distance associated with the first stroke at a later stage of the deployment. | 05-12-2016 |
| 239265350 | Nozzle aiming adjustable | 9 |
| 20080203189 | Apparatus for driving body with three-degree of freedom angular motion - An apparatus for driving a body with 3-degree of freedom angular motion, comprises: a body connected to a fixing part so as to be rotatable centering around a pitch axis, a yaw axis, and a roll axis; a pitch axis driving unit for rotating the body centering around the pitch axis; and a yaw axis driving unit for rotating the body centering around the yaw axis. Since one of the pitch axis driving unit and the yaw axis driving unit restricts the body from rotating centering around the roll axis fixed to the body, the conventional roll-rotation restricting link is not needed between the body and the fixing part. Accordingly, a size of the apparatus is reduced. | 08-28-2008 |
| 20080223956 | Mounting structure for variable nozzle mechanism in variable-throat exhaust turbocharger - Provided is a variable-throat exhaust turbocharger in which a nozzle assembly including a nozzle mount and nozzle vanes has a firm support structure without affection by a thermal deformation of a turbine casing and an external force exerted to the turbine casing, and a scroll portion is formed in a substantially opened configuration so that the nozzle assembly can be simply formed in order to reduce the number of mold cores for a scroll during casting of the turbine casing, thereby it is possible to enhance the productivity of the turbine casing. | 09-18-2008 |
| 20090230213 | METAL INJECTION MOLDING ATTACHMENT HANGER SYSTEM FOR A COOLING LINER WITHIN A GAS TURBINE ENGINE SWIVEL EXHAUST DUCT - An exhaust duct assembly includes an attachment hanger system having at least one component manufactured by metal injection molding (MIM). | 09-17-2009 |
| 20100025493 | Actuator arrangement - An actuator arrangement for moving a first component relative to a second component, the arrangement comprising: an actuator chamber for receiving a fluid under pressure, a side wall of the chamber being fixed relative to the first component; an actuating element fixed relative to the second component and located inside the chamber for sliding movement along the chamber, relative to the side-wall; and a sealing element which provides a corresponding sliding seal between the actuating element and the sidewall for maintaining an actuating fluid pressure differential across the actuating element thereby to drive the actuating element relative to said side-wall, under said fluid pressure differential, for driving said relative movement of the first and second components; wherein the arrangement further comprises an external side-wall brace connected to the second component for corresponding movement with the actuating element along the outside of the sidewall, the brace being slidably or rollably braced against the outside of the side-wall close to the sealing element thereby to provide respective local reinforcement of the side-wall at or near the sliding seal, in accordance with the position of the actuating element. | 02-04-2010 |
| 20110095099 | MECHANISM FOR A VECTORING EXHAUST NOZZLE - A nozzle device defines a passageway including an outlet to discharge working fluid to produce thrust. This device includes a vectoring mechanism having three or more vanes pivotally mounted across the passageway and a linkage pivotally coupling the vanes together. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed to a second one of the vanes to pivot therewith about a second pivot axis, and a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. A first connecting link pivotally couples the first arm and the second arm together, and a second connecting link pivotally couples the third arm and the fourth arm together. The relative angular positioning of the arms with respect to the corresponding pivot axes and/or the arm links can be varied to define different vectoring schedules with the mechanism linkage. In one particular form, the nozzle is utilized with a lift fan of an aircraft to perform V/STOL operations. | 04-28-2011 |
| 20120145808 | METHOD AND APPARATUS FOR VARIABLE EXHAUST NOZZLE EXIT AREA - A nozzle effective exit area control system is created with a convergent-divergent nozzle with a divergent portion of the nozzle having a wall at a predetermined angle of at least 12° from the freestream direction. Disturbance generators are located substantially symmetrically oppositely on the wall to induce flow separation from the wall with the predetermined wall angle inducing flow separation to extend upstream from each disturbance generator substantially to a throat of the nozzle pressurizing the wall and reducing the effective area of the jet flow at the nozzle exit. | 06-14-2012 |
| 20140027537 | INTEGRATED VARIABLE AREA FAN NOZZLE AND THRUST REVERSER - A nacelle assembly for a turbofan engine includes a forward nacelle portion having an aft edge and defining a bypass duct that transports bypass airflow of the turbofan engine, a translatable sleeve that is translatable aft of the forward nacelle portion, and a variable area fan nozzle (VAFN) airfoil that is movable between a stowed position, a VAFN flow position, and a thrust reverse position. Blocker doors for the thrust position are integrated into the VAFN airfoil. | 01-30-2014 |
| 20150102129 | MOUNTING ASSEMBLY - The invention relates to a mounting assembly for a rocket nozzle for an engine that may be operable in rocket mode, in which the engine combusts stored oxygen and hydrogen, or in air-breathing mode, in which the engine combusts air from the atmosphere and stored hydrogen. A plurality of ducts and pipes are connected to the nozzle to supply fuel and other fluids. As it is desirable to allow the nozzle to pivot, the mounting assembly may include flexible couplings on the ducts and pipes about selected pivot points allowing the desired freedom of motion. The flexible couplings are designed to withstand various pressure forces in the rocket/aircraft flight environment, and may be composed of spaced annular elements, wherein a partial toroid element connects consecutive pairs of annular elements. | 04-16-2015 |
| 20190145349 | METHODS OF FORMING FLEXIBLE STRUCTURES FOR A ROCKET MOTOR ASSEMBLY | 05-16-2019 |
| 239265370 | Radially inwardly movable wall | 14 |
| 20090065610 | 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 aftward portion of the engine and to move through one or more positions, a first link pivotally connected to the at least one actuator, a convergent flap pivotally connected to the first link, a divergent flap rotatably connected to the convergent flap and configured to be kinematically connected to an annular ring connected to the at least one actuator, and at least one track configured to extend from the aftward portion of the engine and to movably and pivotally receive the pivotal connection between the convergent flap and the first link. | 03-12-2009 |
| 20090072049 | Nozzle-area ratio float bias - A mechanism included in a convergent-divergent nozzle connected to an aft portion of a gas turbine engine, which mechanism includes a convergent flap configured to be kinematically connected to the aft portion of the gas turbine engine, a divergent flap pivotally connected to the convergent flap and configured to be kinematically connected to the aft portion of the gas turbine engine, at least one actuator configured to be connected to the aft portion of the gas turbine engine and to mechanically prescribe the position of the convergent flap and the divergent flap by moving through one or more positions, and at least one biasing apparatus. The biasing apparatus is configured to position at least one of the convergent flap and the divergent flap independent of the positions of the actuator by substantially balancing a force on the at least one of the convergent flap and the divergent flap produced by a gas pressure on the nozzle. | 03-19-2009 |
| 20110127353 | AIRCRAFT NACELLE THAT INCORPORATES A THRUST REVERSAL DEVICE - An aircraft nacelle in which a power plant with an outside surface ( | 06-02-2011 |
| 20120067976 | SYSTEM FOR CONTROLLING THE TRAJECTORY OF A JET-PROPELLED MOBILE - The system of the present disclosure includes at least one flow deflector located outside the nozzle of the mobile and hinged on the rear bottom of the latter, and angular orientation means for the deflector by rotation about the longitudinal axis of the nozzle. | 03-22-2012 |
| 20130062435 | NACELLE FOR AN AIRCRAFT ENGINE WITH CASCADE-TYPE THRUST REVERSER AND VARIABLE-GEOMETRY NOZZLE - An aircraft engine nacelle is provided that includes a fixed front frame, a thrust reverser cowling mounted to slide with respect to the front frame between a direct-jet position and a reversed-jet position, a variable-geometry nozzle positioned in a downstream continuation of the reverser cowling, thrust-reversal jacks interposed between the front frame and the thrust-reverser cowling, adaptive nozzle jacks interposed between said thrust reverser cowling and the variable-geometry nozzle, drive shafts mounted on the front frame, transmission shafts extending along the thrust reverser cowling as far as the variable-geometry nozzle jacks, and mechanical means for coupling said transmission shafts to said drive shafts, and means for locking rotation of said transmission shafts before decoupling of the transmission shafts from their respective drive shafts, and when the decoupling is completed. | 03-14-2013 |
| 20130292490 | DOOR FOR THRUST REVERSER OF AN AIRCRAFT NACELLE - A door for a thrust reverser of a nacelle of an aircraft being pivotally amounted on a fixed structure of the nacelle, in particular, the door being fitted with deflectors deflecting air flow is disclosed. The deflectors are arranged at an upstream end of the door and mounted such that they can move in a deflection plane perpendicular to the plane of the door. Each deflector is associated at its ends with an articulation arm capable of rotating about a pivot axis perpendicular to the deflection plane, allowing the deflectors to move in a straight line in the deflection plane. The present disclosure also relates to a thrust reverser system including the door and a fixed structure on which the door is pivotally mounted between a closing position and an open position. | 11-07-2013 |
| 20140103141 | VARIABLE JET ENGINE OUTLET WITH A MAINLY CIRCLE SECTOR-FORMED CROSS SECTION - The present invention relates to a low signature jet engine outlet comprising movable border segments forming at least one circular arc and being movable radially for controlling the form and area of the outlet, at least one stationary border element for defining the form and area of the outlet, and movable coupling means for connecting the at least one circular arc to the at least one stationary border element. The coupling means are movable along a connection part of the at least one stationary border element, and the connection part of the at least one stationary border element is substantially flat and extending in a substantially radial direction of the at least one circular arc. | 04-17-2014 |
| 20150053789 | LINKAGE TO CONTROL AND RESTRAIN FLAP MOVEMENT - The present disclosure relates to systems for controlling movement of a divergent flap ( | 02-26-2015 |
| 20150292437 | GAS TURBINE ENGINE CONVERGENT/DIVERGENT EXHAUST NOZZLE DIVERGENT SEAL WITH DOVETAIL INTERFACE - A divergent flap seal includes a flap seal body with a spine, the flap seal body manufactured of a non-metallic material. A mount is engaged with the spine at the dovetail interface and a resilient member at the dovetail interface. | 10-15-2015 |
| 20160102574 | Gas Turbine Engine Convergent/Divergent Nozzle With Unitary Synchronization Ring For Roller Track Nozzle - A nozzle system includes a static structure including a multiple of convergent flap rails and a synchronization ring including an inner ring radially spaced from an outer ring via a multiple of struts. The multiple of convergent flap rails extend at least partially between the inner ring and the outer ring. | 04-14-2016 |
| 239265390 | At least three pivoted flaps form outlet | 3 |
| 20130327847 | TURBINE ENGINE EXHAUST NOZZLE FLAP - An exhaust nozzle flap for a turbine engine may include an exhaust nozzle flap linkage, an exhaust nozzle flap panel and a mounting pin. The linkage may include a first linkage segment that extends longitudinally from a linkage end to a second linkage segment, and a mounting aperture that extends transversely through the second linkage segment. The panel may include a first panel segment that extends longitudinally from a panel end to a second panel segment. The first panel segment may be pivotally engaged with the first linkage segment. The mounting pin may extend through and move transversely within the mounting aperture, and may be connected to the second panel segment. | 12-12-2013 |
| 20140263737 | THREE STREAM, VARIABLE AREA FIXED APERTURE NOZZLE WITH PNEUMATIC ACTUATION - An exemplary nozzle having a variable internal exhaust area for a gas turbine engine can have a plurality of flap trains extending around a periphery of the gas turbine engine. Each flap train can include a convergent flap pivotally attached to an engine body and a divergent flap pivotally attached to the engine body downstream of the convergent flap. The nozzle can further have a fluid circuit in communication with the convergent and divergent flaps and configured to pivot the convergent and divergent flaps between a radially inward position and a radially outward position. | 09-18-2014 |
| 20160010489 | VARIABLE NOZZLE FOR AERONAUTIC GAS TURBINE ENGINE | 01-14-2016 |
| 239265430 | Resilient or deformable wall | 1 |
| 20140027538 | VARIABLE GEOMETRY STRUCTURE - A variable geometry ( | 01-30-2014 |
