Entries |
Document | Title | Date |
20080197212 | Method and device to increase thrust and efficiency of jet engine - A method and device for adding special substances to the gaseous outflow of the jet engine in order to create a “virtual wall” of increased pressure zone behind the jet engine nozzle which can serve as a support for the jet engine gas outflow to push against, thus increasing the thrust power of the jet engine. This increase in acceleration power results in the accelerated movement of the jet engine equipped vehicle or higher fuel efficiency. A device that adds the special substances to the gaseous outflow is proposed. Characteristics of the special substances, which if added into the jet engine gaseous outflow may create a “virtual wall” of increased pressure zone behind the jet engine, are proposed. | 08-21-2008 |
20080210778 | Aircraft engine exhaust shroud - A shroud for an aircraft engine exhaust plume, the shroud being formed of a flexible material secured at one end to the exhaust nozzle and selectively extendable downstream with the exhaust plume so as to surround and shroud it, thereby to reduce infrared/radar/noise emissions from the aircraft engine. | 09-04-2008 |
20080251606 | Air Spray Gun Improvements in Nozzle and Aircap - The feeder passages ( | 10-16-2008 |
20090014554 | FUEL INJECTOR FOR AN INTERNAL COMBUSTION ENGINE - A fuel injector for an internal combustion engine, particularly of inwards or outwards opening needle injector type, includes an injector body, e.g., forming a nozzle ending in an injection office, a mechanism for closing off the injection orifice of the injector body, the closing-off mechanism including a vibrating pintle ending in a head for closing off the injection orifice, a return mechanism returning the closing-off to the position in which they close off the injection orifice, and a mechanism for setting the pintle and/or the nozzle into cyclic longitudinal vibration so as to open and close the injection orifice alternately. The fuel injector includes a selectively activatable mechanism immobilizing the pintle with respect to the body. | 01-15-2009 |
20090065608 | FUEL INJECTION SYSTEM - A fuel-injection system for direct injection of fuel into a combustion chamber through a combustion-chamber top arranged opposite a piston has a fuel injector which includes an actuable valve-closure member. The valve-closure member cooperates with a valve-seat surface to form a sealing seat. A multitude of spray-discharge orifices generates a spray cloud, each spray-discharge orifice generating a fuel jet, and the multitude of fuel jets generating the spray cloud in the combustion chamber. A first opening angle of the spray cloud in a first plane is greater than a second opening angle in a second plane extending perpendicular to the first plane. | 03-12-2009 |
20090108100 | Hydrogen chrolide gas ejecting nozzle, reaction apparatus for producing trichlorosilane and method for producing trichlorosilane - There is provided a hydrogen chrolide gas ejecting nozzle I used in a reaction apparatus for producing trichlorosilane in which metal silicon powder is reacted with hydrogen chloride gas to generate trichlorosilane. The member is provided with a shaft portion extending in the longitudinal direction and a head portion that is provided on an end of the shaft portion and extends in a direction intersecting the longitudinal direction of the shaft portion. A supply hole extending in the longitudinal direction is formed in the shaft portion, a plurality of ejection holes are formed in the head portion, and each of the ejection holes is communicatively connected to the supply hole and opened on the outer surface of the head portion toward a direction intersecting the direction to which the supply hole extends. | 04-30-2009 |
20090114740 | NOZZLE ASSEMBLY WITH FLOW CONDUITS - A nozzle assembly for a turbine engine has a convergent portion for converging fluid flow from a turbine engine core. A divergent portion for diverging fluid flow from the turbine engine core is in fluid communication with the convergent portion. A conduit is in communication with a bypass fluid flow. The conduit has a thrust vectoring port located near the divergent portion. | 05-07-2009 |
20090230212 | Pintle-Controlled Propulsion System With External Ring Actuator - A propulsion system with a divergent-convergent nozzle is provided with variable thrust by a pintle whose position relative to the nozzle throat is controlled by an actuator that includes a rotor that external to, and encircling, the nozzle, and that is coupled to either the pintle or to the nozzle shell by a linkage that translates the rotary movement of the rotor into linear movement of either the pintle or the shell. | 09-17-2009 |
20100012750 | FUEL NOZZLE CENTERBODY AND METHOD OF ASSEMBLING THE SAME - A fuel nozzle centerbody is provided that includes a cylindrical cross-sectional area, and a baffle co-axially aligned within the centerbody. The baffle includes a plurality of circumferentially-spaced apertures configured to channel an airflow radially outward such that the channeled airflow impinges a centerbody inner surface. | 01-21-2010 |
20110215172 | Aircraft engine with optimized oil heat exchanger - This invention relates town ejector nozzle tube | 09-08-2011 |
20110233305 | STRUCTURE FOR THRUST INVERTER - The invention relates to a structure for a thrust inverter, that comprises: a boom ( | 09-29-2011 |
20110266366 | SPRING FOR A CASCADE-TYPE THRUST REVERSER SHUTTER FOR AN AIRCRAFT JET ENGINE - This leaf spring ( | 11-03-2011 |
20110297758 | EXTERNAL FLAP RETAINING MECHANISM - An external flap connection assembly for a turbine engine nozzle has a track frame, a slider track, and an external flap. The external flap is removably connected to the slider track via a retaining member which has a slider block. | 12-08-2011 |
20120031995 | ACTUATOR SYSTEM FOR A MOBILE PANEL OF A NACELLE OF A TURBOJET - The invention relates to a system for actuating a plurality of actuators ( | 02-09-2012 |
20120037723 | TORQUE LIMITER IN PARTICULAR FOR AN ACTUATOR OF THE NACELLE OF AN AIRCRAFT TURBOJET ENGINE - The invention relates to a torque limiter for an actuator including a screw ( | 02-16-2012 |
20120097761 | TWELVE-HOUR STRUCTURE FOR THRUST REVERSER, IN PARTICULAR WITH GRIDS - The invention relates to a twelve-hour structure for a thrust reverser, that comprises a half beam ( | 04-26-2012 |
20120187214 | CONVERGING BLOCKER DOOR SYSTEM FOR USE WITH A THRUST REVERSER - A blocker door system to be used with an aircraft engine thrust reverser comprises a push ring, a plurality of connecting rods, a plurality of crankshafts, a plurality of blocker doors, and a plurality of linking elements. The push ring may encircle the aircraft engine. The connecting rods may connect along the circumference of the push ring. The crankshafts may rotatably couple to the connecting rods. The blocker doors may be positioned adjacent one another around the circumference of the aircraft engine wherein at least a portion of one blocker door covers at least a portion of the adjacent blocker door. The linking elements may connect one blocker door to the adjacent blocker door and may be operable to guide the motion of the blocker doors relative to one another. | 07-26-2012 |
20120199670 | REDUCED DRAG AFTERBURNER NOZZLE ACTUATION SYSTEM - An afterburner nozzle actuation system includes a case, an actuation structure, a plurality of cam plates, a plurality of nozzle flaps and seals, and a plurality of rollers. The actuation structure surrounds at least a portion of the case and includes an aft end that has a polygonal cross section shape. The cam plates are removably coupled to an inner surface of the actuation structure, and each includes a cam surface. The nozzle flaps are rotationally coupled to the case and extend at least partially from the actuation structure aft end. Each nozzle flap is movably coupled to a different one of the cam plates. The rollers are each rotationally mounted on a different one of the nozzle flaps and engage the cam surface of one of the cam plates. | 08-09-2012 |
20120217320 | THRUST INVERTER - The present invention relates to a thrust inverter for a turbojet engine nacelle ( | 08-30-2012 |
20130056553 | METHOD FOR MIXING AIRFLOWS IN A TURBOFAN AND ENGINE OUTLET FOR OPERATION - The invention aims at providing a sufficient air exchange in the engine area without raising the static pressure in the outlet area of the air exchange duct. In order to do this, the invention provides for an outlet section capable of concentrating the outlet of the exchange airflow towards zones with smaller static pressure. | 03-07-2013 |
20130056554 | REVERSER WITH DOORS - A thrust reverser with doors having at least one stationary structure is provided, on which at least one door is mounted pivoting between a closed position in which the door closes the reverser and makes up an outer cowling part, and an open position in which the door opens a passage in the stationary structure and can at least partially block a flow of air generated by a turbojet engine so as to reorient the door. The stationary structure includes at least two sets of cascade vanes that can be covered by the door when in the closed position. | 03-07-2013 |
20130062433 | NACELLE FOR AN AIRCRAFT ENGINE WITH VARIABLE CROSS-SECTION NOZZLE - A nacelle for an aircraft engine is provided that includes a thrust reverser cowling slideably mounted between a direct jet position and a reversed jet position, an outlet jet pipe nozzle with variable cross-section positioned in a downstream extension of the reverser cowling, and means for respectively actuating the cowling and the nozzle. The nozzle is slideably mounted on the thrust reverser cowling, and the means includes at least one actuator for actuating said thrust reverser cowling, at least one driving pinion rotatably mounted on a fixed structure of said nacelle, and at least one rack for actuating the nozzle, secured to the nozzle and meshing with the driving pinion when the thrust reverser cowling is in the direct jet position, and escaping from this pinion when said reverser cowling is in the reversed jet position. | 03-14-2013 |
20130062434 | ARRANGEMENT OF THRUST REVERSER FLAP LINK RODS ON THE INTERNAL FIXED STRUCTURE OF A TURBOJET ENGINE NACELLE - An arrangement is provided that includes a thrust reverser flap link rod on an internal fixed structure of a turbojet engine nacelle. The link rod is connected to the internal fixed structure by an elastic means that is a spring. | 03-14-2013 |
20130075492 | THRUST REVERSER TRANSLATING SLEEVE ASSEMBLY - A translating sleeve assembly for use with an aircraft engine thrust reverser broadly comprises a slider track, a lifting bolt, and a hinge. The slider track may include a tubular sidewall and a guide channel formed therein that follows a curved path along a length thereof. The lifting bolt may be slidably positioned within the slider track. The hinge may include a first hinge element with a base coupled to an outer cowl shroud, a second hinge element with a hinge rod slidably positioned within the guide channel, and a pin about which the first hinge element and the second hinge element pivot. During deployment of the thrust reverser, the lifting bolt slides aftward and the hinge rod slides within the guide channel, urging the lifting bolt to pivot and the hinge to open, thereby lifting the outer cowl shroud away from the center of the aircraft engine. | 03-28-2013 |
20130075493 | AIRPLANE JET ENGINE THRUST REVERSER HAVING GRATINGS OR CASCADES - A cascade thrust reverser for an airplane dual flow jet engine nacelle is provided that includes a front frame holding a plurality of cascades, a cowling slidably mounted between a direct jet position and a reverse jet position. The cowl includes a substantially annular diaphragm that is placed edge-to-edge with the front frame and radially inside said cascades when said cowl is located in the direct jet position. Thrust reversal flaps are pivotably mounted onto the diaphragm, and cylinders for actuating the cowl are also provided. Upstream ends of the cylinders are mounted on a stationary portion of the nacelle, and the downstream ends of the cylinders are mounted on an upstream edge of the diaphragm. | 03-28-2013 |
20130112776 | NOZZLE ARRANGEMENT AND METHOD OF MAKING THE SAME - A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body. | 05-09-2013 |
20130126638 | THRUST REVERSER HAVING AN AERODYNAMIC COUPLING FOR A FRONT FRAME - A thrust reversal device for a turbojet engine nacelle is provided that includes a deflection means and at least one cowl moveable relative to at least one fixed structure including at least one at least partly peripheral front frame and equipped with means for connection to a corresponding upstream portion. The front frame has a deflection edge having an upstream extension forming a deformable flap intended to become an aerodynamic interface with the corresponding upstream portion to which is attached the front frame, and in that a portion of the moveable cowl is conformed so as to, in the closing position, interface with said upstream attachment portion by forcing withdrawal of the deformable flap. | 05-23-2013 |
20130161414 | ACTUATION SYSTEM FOR A TRANSLATING VARIABLE AREA FAN NOZZLE - A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating thrust reverser sleeve with a trailing edge. The thrust reverser sleeve is movably disposed aft of the nacelle's aft edge and is movable between a forward position and an aft position. A translating fan nozzle having a forward edge is movably disposed behind the trailing edge, and is movable between a stowed position and a deployed position. An upstream bypass flow exit is defined between the trailing edge and the forward edge when the fan nozzle is in the deployed position. An extendable actuation system is configured to move the fan nozzle between the stowed position and the deployed position. | 06-27-2013 |
20130161415 | BEAM FOR A CASCADE THRUST REVERSER - The present disclosure relates to a beam, in particular for a cascade thrust reverser, including a skin made of a composite material and defining a closed section, wherein said beam is filled with a core material. | 06-27-2013 |
20130200178 | CASCADE-STYLE VARIABLE AREA FAN DUCT NOZZLE - An aircraft nacelle comprising an outer cowl having an inner wall and an outer wall surrounding the inner wall. The inner wall may have an inner opening formed therethrough and the outer wall may have an outer opening formed therethrough at an aft end of the nacelle. The nacelle may further comprise a translating panel configured to cover the inner and outer openings in a stowed position and to translate aft to a deployed position. The translating panel may be fixed to cascade guide vane panels which rest between the inner and outer wall in the stowed position and are exposed to airflow via the inner and outer openings when translated aft to the deployed position, thereby increasing a nozzle area of the nacelle. Guide vanes of the cascade guide vane panels are angled slightly aftward to direct the nacelle's airflow outward and aftward. | 08-08-2013 |
20130264399 | THRUST REVERSER ACTUATOR WITH PRIMARY LOCK - Actuator assembly includes a housing assembly, a ball screw, a ball nut, and a lock. The ball screw is rotationally mounted on and extends from the housing assembly, is coupled to receive an actuator drive torque, and is configured, upon receipt thereof, to rotate. The ball nut is rotationally supported on the ball screw and is configured, in response to rotation of the ball screw, to translate thereon between a stowed position and a deployed position. The lock is disposed at least partially within the housing assembly and is configured to move between a lock position and an unlock position. The lock prevents the ball nut from translating out of the stowed position when the lock is in the lock position and the ball nut is in the stowed position. | 10-10-2013 |
20130277454 | AIRCRAFT PROPULSION ASSEMBLY - The disclosure relates to an aircraft propulsion assembly including a nacelle having an intermediate housing and a front frame that is to be mounted downstream of an outer envelope of the intermediate housing. The front frame includes a deviation edge and an element forming a direct or indirect support for at least one flow deviation vanes, in particular, the deviation edge and the support-forming element are built into the outer envelope of the intermediate housing. | 10-24-2013 |
20130292489 | THRUST REVERSER HAVING A LOCKABLE VARIABLE NOZZLE SECTION - The present disclosure relates to a thrust reverser including at least one translatably movable cowl capable of alternately shifting between a closed position in which same ensures the aerodynamic continuity of the nacelle and which covers the deflecting means, and an open position in which same opens a passage in the nacelle and uncovers the deflecting means, said thrust reverser likewise including at least one variable nozzle section arranged in the extension of the movable thrust-reversing cowl and provided with at least one locking means capable of engaging with a complementary locking means of the movable reversing cowl so as to optionally mechanically link the movable nozzle section of the movable reversing cowl. | 11-07-2013 |
20130341426 | FLEXIBLE LEAF SPRING SEAL FOR SEALING AN AIR GAP BETWEEN MOVING PLATES - A sealed joint may include a first plate with a seal land, a second plate that moves relative to the seal land, and a leaf spring seal. The leaf spring seal includes a stack of seal leaf elements that extend laterally from a first stack end, which is connected to the second plate, towards a distal second stack end. The stack may include a seal land contact segment and a base segment. The seal land contact segment is engaged with the seal land, and spatially separated from the second plate. The base segment is configured laterally between the seal land contact segment and the first stack end, and spatially separated from the first plate. A first of the seal leaf elements has a first longitudinal length, and a second of the seal leaf elements has a second longitudinal length that is different than the first longitudinal length. | 12-26-2013 |
20140027536 | TRANSLATING CASCADES - 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 reverse thrust apparatus that is movable between a stowed position, and a deployed position. When the reverse thrust apparatus is deployed, the translatable sleeve is moved aft to a position away from the aft edge of the forward nacelle potion to expose a cascade assembly comprising an opening in the bypass duct, and one or more blocker doors are deployed so as to extend into the bypass duct, such that at least a portion of the airflow in the bypass duct is directed out the bypass duct through the cascade assembly. Also, during deployment of the reverse thrust apparatus, at least a portion of the cascade assembly translates toward the engine centerline. The cascade assembly may have a cross-section that is non-uniform. | 01-30-2014 |
20140061332 | THRUST REVERSER FOR AN AIRCRAFT JET ENGINE - An assembly includes a suspension pylon and a thrust reverser which has vanes for deflecting flow and a cowl able to move between an open position and a closed position by an actuator. The thrust reverser further includes rails able to slide in slideways. In particular, the actuator is disposed in line with a corresponding rail. The actuator may be an actuator having a rotating nut connected to an endless screw or an actuator suitable for pulling on the corresponding rail or on the corresponding slideway. | 03-06-2014 |
20140076998 | SYSTEM FOR DECOUPLING DRIVE SHAFT OF VARIABLE AREA FAN NOZZLE - A nacelle assembly includes a thrust reverser moveable between a stowed position and a deployed position, a variable area fan nozzle, a motor to move the variable area fan nozzle, a drive shaft including a first portion coupled to the motor and a second portion coupled to the variable area fan nozzle, and a clutch mechanism that couples the first portion of the drive shaft and the second portion of the drive shaft The first portion of the drive shaft decouples from the second portion of the drive shaft when the thrust reverser moves from the stowed position to the deployed position. | 03-20-2014 |
20140076999 | TERTIARY LOCKING ASSEMBLY FOR A THRUST REVERSER - A tertiary locking assembly for a thrust reverser includes a tertiary lock, a primary control line associated with the tertiary lock, and a secondary control line. The primary control line includes a primary electromechanical valve and a primary power supply line connected to the primary electromechanical valve. In addition, the secondary control line has a secondary electromechanical control valve and a secondary power supply line connected to the secondary electromechanical control valve. In particular, the secondary control line is provided with at least one manually controlled switch. | 03-20-2014 |
20140097271 | AIRCRAFT ENGINE WITH AN APPARATUS FOR PULSATING EXPIRATION OF GAS INTO THE EXHAUS NOZZLE - An aircraft jet engine includes an exhaust-gas nozzle having a device configured to blow out an exhaust gas in a pulsating manner into an exhaust-gas stream so as to reduce noise. The exhaust-gas nozzle includes openings distributed along a circumference of the exhaust-gas nozzle and disposed upstream from a nozzle outlet. The openings communicate with the device. | 04-10-2014 |
20140110503 | THRUST REVERSER AND NACELLE FOR AIRCRAFT EQUIPPED WITH AT LEAST ONE SUCH REVERSER - A thrust reverser for a double-flow nacelle that has a cowling, with the thrust reverser having an internal door and an external door designed to be made within the thickness of the cowling. The reverser also has means for simultaneously displacing the doors between a first position called the rest position, in which the doors are integrated into the cowling so as to form an aerodynamic continuity with the external wall and the internal wall of the cowling, and a second active position, in which the doors are open so that the internal and external doors extend toward the inside and toward the outside of the nacelle, respectively, thus at least partially blocking the annular channel of the secondary flow, to deflect the secondary flow and to generate a thrust reversal, with the means being designed to be received in a compartment arranged inside the cowling formed by the doors in the rest position. | 04-24-2014 |
20140131479 | AIRCRAFT TURBOJET ENGINE THRUST REVERSER WITH A LOWER NUMBER OF ACTUATORS - This cascade-type thrust reverser with one-piece moving cowl includes rails able to slide in guideways positioned on each side of a suspension pylon. This thrust reverser includes just two actuators positioned near the rails and able to cause this cowl to slide on the guideways between its direct-jet and reverse-jet positions. It also has means capable of compensating for forces that have a tendency to misalign the rails with respect to the guideways, thus preventing them from jamming in one another. | 05-15-2014 |
20140131480 | THRUST REVERSER DEVICE WITHOUT A CONTROL ROD IN THE STREAM - A jet engine nacelle has one thrust reverser device which includes a deflection means and one cowl translatable in a direction substantially parallel to a longitudinal axis of the nacelle. The cowl can translate between a closed position and an open position. In the open position, the cowl ensures the aerodynamic continuity of the nacelle and covers the deflection means. In the open position, the cowl opens a passage into the nacelle and uncovers the deflection means. The thrust reverser device moreover includes one blocking flap pivotably mounted by one end attached to a rear portion of the deflection means, and slidingly connected to the moving cowl. The pivoting end is also translatably connected to the rear portion of the deflection means. | 05-15-2014 |
20140145008 | GAS TURBINE ENGINE EXHAUST NOZZLE - An exhaust nozzle | 05-29-2014 |
20140175191 | SYSTEM FOR REDUCING THE DYNAMIC BEHAVIOR OF THE MOVABLE SEGMENT OF A DEPLOYABLE NOZZLE FOR A ROCKET ENGINE - A deployable nozzle for a rocket engine, the nozzle including at least a stationary divergent segment and a movable divergent segment that is coaxial about the stationary divergent segment and configured to move along the stationary divergent segment from a retracted position towards a deployed position. The deployable nozzle further includes a transverse stiffener that is prestressed in tension and that extends transversely relative to the movable divergent segment in a vicinity of a downstream end of the movable divergent segment between at least two points at a periphery of an inside wall of the movable divergent segment. | 06-26-2014 |
20140246514 | TURBOMACHINE THRUST REVERSER - An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary aspect of the present disclosure includes, among other things, a first cowl moveable between a stowed position and a deployed position relative to a second cowl. The first cowl in the deployed position configured to permit thrust to be redirected from an engine to slow the engine. The first cowl forming a portion of a substantially annular encasement of the engine. The first cowl directly interfaces with second cowl of the encasement at a cowl interface position that is more than 18 degrees circumferentially offset from the top circumferential apex when the first cowl is in the stowed position. | 09-04-2014 |
20140319243 | REVERSER HAVING MOVABLE CASCADES, AND TRANSLATABLY VARIABLE NOZZLE - The thrust reverser includes a reverser cowl of which a downstream part of the reverser cowl forms a jet nozzle, cascade vanes fixed upstream from the reverser cowl, thrust reverser flaps, and an actuator. The thrust reverser is translatable under an effect of the actuator between a folded position of the thrust reverser flaps for operation of the nacelle in a direct jet mode, and a deployed position of the thrust reverser flaps for operation of the nacelle in a reverse jet mode. In particular, the stretching of the actuator results in causing a variation in a nozzle section of the jet nozzle as long as the stretching is below a predetermined value, and exposing the cascade vanes and deploying the thrust reverser flaps so as to perform the reverse jet mode beyond the predetermined value. | 10-30-2014 |
20150083823 | COUPLING AND UNCOUPLING MECHANISM FOR AN ONBOARD DEVICE OF A TURBOJET ENGINE NACELLE - A mechanism for coupling and uncoupling a motor inlet shaft and an outlet shaft, in particular, the inlet shaft is mounted in rotation on a front frame, and the outlet shaft is mounted in rotation on a rear frame. The outlet shaft rotates an outlet pinion, and the rear frame is slidably mounted to translate between a forward compact position and a backward deployed position. The mechanism includes a coupler, and first and second lockers to couple or uncouple the inlet and outlet shafts according to the translation of the rear frame between the forward compact position and the backward deployed position. The first locker locks in rotation the inlet shaft on the front frame, the second locker locks the outlet shaft on the rear frame. In particular, the second locker automatically locks the inlet and outlet shafts in rotation respectively, according to the displacement of the rear frame. | 03-26-2015 |
20150090810 | THRUST REVERSER HYDRAULIC ACTUATION SYSTEM WITH SERVO SYNCHRONIZATION - A thrust reverser system and method for controlling actuation thereof. The thrust reverser system may have a control system, two thrust reverser doors actuatable between an open position and a closed position, hydraulic actuators attached to and used to actuate each of the thrust reverser doors, servo valves each communicatively coupled with one of the hydraulic actuators to control hydraulic flow to and from the hydraulic actuators, and position sensors mounted on each of the thrust reverser doors to provide signals associated with a position thereof to the control system. The control system may send command signals to the servo valves to independently adjust at least one of hydraulic flow rate, hydraulic pressure, direction, and position of the hydraulic actuators depending on an amount of offset between the signals received from the position sensors. | 04-02-2015 |
20150097055 | ACTUATOR SUPPORT SYSTEM AND APPARATUS - A cascade support structure for a cascade type thrust reverser system is provided. One or more cascades may comprise one or more flanges. One or more actuators may also comprise one or more flanges. The cascades may be coupled to and/or supported by the actuators via the flanges. The cascades and/or actuators may also be configured to couple to one or more track beams via the ore or more flanges. | 04-09-2015 |
20150097056 | THRUST REVERSER WITH RETRACTABLE CASCADE VANES - A thrust reverser for a turbojet engine nacelle includes a movable cowl, cascade vanes and a portion forming a movable variable nozzle. The cowl translates between a closing position and a maintenance position which is located beyond a thrust reversal position. In the maintenance position, the cowl opens a passage within the nacelle and allows access the inside of the nacelle. The variable nozzle is translated by an actuator between reduced ejection section and increased section positions. In particular, the cascade vanes move between retracted and active positions and are housed in an envelope formed by a fan casing and an outer cowl in the retracted position. In the active position, the cascade vanes are displaced downstream by an actuator through a passage open by the movable cowl in the nacelle. The actuator of the cascade vanes is dissociable from the actuator driving the variable nozzle. | 04-09-2015 |
20150102128 | FORMING A COMPLEXLY CURVED METALLIC SANDWICH PANEL - Aspects of the disclosure are directed to a bonding of a first skin and a second skin to a core material, coupling a sheet to the first skin to form with the first skin an enclosure containing the second skin and the core material, exposing the first skin, the second skin, and the core material to heat, and based on the exposition of heat, applying pressure via the enclosure to the first skin to cause the first skin to deform and expand to a shape of a die. | 04-16-2015 |
20150108247 | INVERTED TRACK BEAM ATTACHMENT FLANGE - A “U” shaped inverted track beam flange for a thrust reverser is described. The geometry of the inverted track beam flange increases the total noise cancellation capabilities of a nacelle structure comprising the inverted track beam flange. An inner fixed structure is coupled to an inverted track beam flange. The inner fixed structure is coupled to the inverted track beam flange along an attachment flange. The coupling is along a commercial jet aircraft engine fan duct airflow surface. | 04-23-2015 |
20150108248 | THRUST REVERSER FAN RAMP WITH NOISE SUPPRESSION - A fan ramp for use in a thrust reverser portion of a nacelle is disclosed. The nacelle is included in a propulsion system. The fan ramp extends circumferentially about an axial fan ramp centerline. The fan ramp includes a forward edge, an aft edge, and a noise suppression feature. The forward edge is disposed proximate an aft end of a fan case. The fan case at least partially surrounds a fan section of a gas turbine engine. The aft edge is disposed proximate a forward end of an array of cascades. The array of cascades is operable to permit a bypass airstream to pass there through during a thrust reversing operation. The noise suppression feature is operable to suppress noise within the propulsion system. | 04-23-2015 |
20150108249 | HYDRAULIC BLOCKER DOOR DEPLOYMENT SYSTEMS - A hydraulic circuit for a jet engine thrust reverser is disclosed. The hydraulic circuit may comprise a primary hydraulic actuator cylinder assembly and a secondary hydraulic actuator cylinder assembly. The primary hydraulic actuator cylinder assembly may be hydraulically coupled to the secondary hydraulic actuator cylinder assembly, in a master-slave relationship, and the secondary hydraulic actuator cylinder assembly may drive a thrust reverser blocker door. The primary hydraulic actuator cylinder assembly may comprise a rod, and the rod may comprise a channel through which hydraulic fluid is capable of flowing. The hydraulic circuit may further comprise a group of secondary hydraulic actuator cylinder assemblies, wherein the group of secondary hydraulic actuator cylinder assemblies may be coupled to the primary hydraulic actuator cylinder assembly. | 04-23-2015 |
20150108250 | ACOUSTICALLY TREATED THRUST REVERSER TRACK BEAM - A thrust reverser track beam is disclosed. The thrust reverser track beam may comprise a recess defined by a reception surface and/or a perimeter surface surrounding the reception surface and extending away from the reception surface, wherein the reception surface and the perimeter surface bound a recess that is configured to receive a noise suppressing structure. The thrust reverser track beam may further comprise the noise suppressing structure. The recess is generally triangular in shape and may extend away from a plane. The noise suppressing structure may be generally triangular in shape and may extend away from a plane. The noise suppressing structure may be coupled within the recess of the track beam and/or to the track beam. | 04-23-2015 |
20150115061 | GIMBAL PIN FOR JET PROPULSION SYSTEM - A thrust reverser actuator gimbal assembly for mounting a thrust reverser actuator to fixed structure of the thrust reverser is disclosed. The thrust reverser actuator gimbal assembly may comprise a gimbal, first and second gimbal pins mounted to the gimbal and defining a first pivot axis, the first and second gimbal pins adapted to form a pivotal joint with the fixed structure of the thrust reverser, third and fourth gimbal pins mounted to the gimbal and defining a second pivot axis normal to the first pivot axis, the third and fourth gimbal pins adapted to farm a pivotal joint with the thrust reverser actuator, wherein the first and second gimbal pins each include a shaft and a flange integrally formed together, the flange including a pair of bores for receiving a fastener to fasten the respective gimbal pin to the thrust reverser fixed structure. | 04-30-2015 |
20150122912 | TANDEM THRUST REVERSER WITH MULTI-POINT ACTUATION - One embodiment includes a pivot thrust reverser comprising a first tandem pivot door subassembly comprising an inner panel and outer panel connected. A second tandem pivot door subassembly is included comprising an inner panel and outer panel connected. Also included are a first actuator located on a first side of an attachment location to pivot the first tandem pivot door subassembly, a second actuator located on a second side of the attachment location to pivot the second tandem pivot door subassembly, and a third actuator located substantially radially opposite the attachment location to pivot both the first tandem pivot door subassembly and the second tandem pivot door subassembly. The first tandem pivot door is configured to be pivoted from stowed to deployed by the first actuator and the third actuator, and the second tandem pivot door is configured to be pivoted from stowed to deployed by the second actuator and the third actuator. | 05-07-2015 |
20150136875 | SYSTEM AND METHOD FOR MOUNTING OF THRUST REVERSER TO PYLON - A propulsion system of an aircraft is described herein. In this system, the inner fixed structure (IFS) and the outer sleeve may be separately coupled to the pylon. For instance, the inner fixed structure and the outer sleeve may be hinged separately and attached to different locations of the pylon. Thus, portions of the pylon are exposed to the fan duct air flow path. | 05-21-2015 |
20150308375 | AERODYNAMIC FEATURE FOR AFT EDGE PORTIONS OF THRUST REVERSER LOWER BIFURCATION WALL - A thrust reverser of a propulsion system nacelle is provided. The thrust reverser includes a fixed structure, a translating structure, and an aerodynamic feature. The fixed structure includes an annular wall that partially defines an annular bypass airstream duct. The fixed structure is bifurcated into left and right side sections. The annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section. The translating structure is moveable relative to the fixed structure, between a stowed position and a deployed position. The aerodynamic feature that includes a flange disposed relative to an aft end portion of one of the lower bifurcation walls. The flange aids in preventing aerodynamic drag. | 10-29-2015 |
20150308376 | LADDER CASCADE TORQUE BOX - Torque boxes and thrust reversers are disclosed. Torque boxes include a torque box comprising a hinge beam, a forward wall having a bullnose profile connected to the hinge beam to support a torque load, an aft wall having a bullnose profile connected to the hinge beam to support the torque load, the aft wall located aft of the forward wall, and a vane connected to an aft surface of the forward wall and a forward surface of the aft wall, wherein the aft surface of the forward wall and the forward surface of the aft wall are configured to direct air flow in a forward direction and the vane is configured to direct air flow radially outward. Thrust reversers include a translating sleeve, a blocker door mounted to the translating sleeve, and a torque box. | 10-29-2015 |
20150308378 | THRUST REVERSER WITH ONE OR MORE BUTRESSING CORNER CASCADE PORTIONS - A thrust reverser of a propulsion system nacelle is provided. The thrust reverser extends circumferentially about a lengthwise-extending centerline. The thrust reverser includes a lengthwise-extending upper track beam, a lengthwise-extending lower track beam, an annular torque box extending circumferentially between the upper and lower track beams, and an annular cascade array extending circumferentially between the upper and lower track beams. The cascade array is circumferentially segmented into a plurality of cascade portions. At least one of the plurality of cascade portions is made at least substantially of a material that permits the at least one cascade portion to bear high loads during both a forward thrust operation of the thrust reverser and a thrust reversing operation of the thrust reverser. | 10-29-2015 |
20150345423 | VARIABLE-SECTION NOZZLE, AND AIRCRAFT TURBOJET ENGINE NACELLE EQUIPPED WITH SUCH A NOZZLE - A variable-section nozzle for an aircraft nacelle includes a deformable portion of which is movable between a narrow section position and a wide section position. In particular, the variable-section nozzle includes piezoelectric actuators and a controller to control the piezoelectric actuators in order to displace the deformable portion between the narrow and wide section positions. The piezoelectric actuators can be disposed on at least one faces of the deformable portion or be disposed end-to-end to form actuating rods. | 12-03-2015 |
20150345424 | THRUST REVERSER TORQUE BOX WITH DISCRETE MAJOR FITTINGS - A thrust reverser torque box assembly for an aircraft engine is constructed with a torque tube having a cross section configuration tailored and conducive to carrying torsion and discrete major fittings at opposite ends of the torque tube that connect the torque tube and thrust reverser actuation and reacts loading due to reverse thrust operation to the aircraft engine fan case. | 12-03-2015 |
20150354499 | TURBOJET ENGINE NACELLE HAVING A VARIABLE NOZZLE - A turbojet engine nacelle has a thrust reverser device and an actuating system for said thrust reverser device, and the thrust reverser device includes a moving cowl mounted translatably alternating between a closed position and an open position, and a jet nozzle section for gases that extends the moving cowl. In particular, the jet nozzle section includes a nozzle flap mounted movable between a closed position and an open position in which the nozzle flap opens a leakage passage toward the outside of the nozzle section. The actuating system has an actuator shared with the moving cowl and the nozzle flap to activate the translational movement of the moving cowl and to pivot the nozzle flap between three following positions: an idle position, an open position of the nozzle flap and an open position of the moving cowl. | 12-10-2015 |
20150369175 | A NOZZLE HAVING A MOVABLE DIVERGENT SECTION WITH A THERMAL PROTECTION SYSTEM - A nozzle having a movable diverging section, the nozzle including a stationary throat forming a ball joint and a diverging section having a top portion that is movably mounted around the throat; an annular lubrication chamber being interposed between the stationary throat and the top portion of the diverging section, the annular lubrication chamber containing a grease seal; an annular throttling element arranged between the stationary throat and the diverging section downstream from the annular lubrication chamber, the annular throttling element being made of refractory material; and an annular thermal protection element arranged between the stationary throat and the diverging section downstream from the annular lubrication chamber and upstream from the annular throttling element, the annular thermal protection element closing the lubrication chamber in its bottom portion. | 12-24-2015 |
20150377182 | ACTUATING DEVICE FOR MOVING A THRUST REVERSER - The invention concerns an actuating device ( | 12-31-2015 |
20160001889 | HYDRAULICALLY ACTUATED MECHANICAL LOCK ASSEMBLY - A hydraulically actuated mechanical lock assembly, including a lock actuator comprising a lock housing and a moveable element mounted in the lock housing, wherein the housing is arranged to receive hydraulic fluid at a first end (Chamber A) from a source of high pressure fluid via a return line, and at a second end (Chamber B) from a source of high pressure fluid via a control line, whereby the relative pressures in Chambers A and B are controlled, via the control line, to cause movement of the moveable element between a locked position and an unlocked position; and a lock valve arranged between the return line and the control line to control the flow of hydraulic fluid into Chambers A and B; wherein the return line is configured to be connected between the source of high pressure fluid and the lock valve via chamber A of the lock actuator. | 01-07-2016 |
20160003188 | DEVICE FOR CONTROLLING A NOZZLE OF VARIABLE CROSS-SECTION OF AN AIRCRAFT - The invention relates to a control device of a nozzle of variable cross-section of an aircraft comprising at least two movable parts enabling medication of the cross-section of the nozzle, the control device comprising a system for regulation of the engine connected to a control element which drives at least one electric motor which creates the movement of the movable parts, wherein it comprises an electric motor for each movable part and two mechanical transmission systems for each movable part connected only to the same electric motor. | 01-07-2016 |
20160003195 | NOZZLE HAVING A VARIABLE NECK SECTION FOR A SPACECRAFT THRUSTER PROVIDED WITH A MOBILE NEEDLE - A nozzle of variable throat section for an aerospace vehicle thruster, the nozzle including a cylindrical housing presenting a throat of aperture diameter less than the diameter of the housing, and a needle suitable for sliding inside the housing between a high discharge rate front position in which the nose is set back from the throat of the housing, and a low discharge rate rear position in which the nose is in abutment against the throat, the needle including a rod for sliding inside the housing of the nozzle, the rod terminating in a nose of decreasing diameter. The nose of the rod is suitable for coming into abutment against the throat of the nozzle housing forming a seat and includes at least two axial grooves formed in its outer periphery to allow gas to pass when the nose is axially in abutment against the throat of the housing of the nozzle. | 01-07-2016 |
20160010591 | DEVICE FOR MODULATING A GAS EJECTION SECTION | 01-14-2016 |
20160025039 | THRUST REVERSER DEVICE - A thrust reverser device for an aircraft turbojet engine includes: a movable cowl, translating cascades connected to the movable cowl, a mast; and a front suspension to suspend the turbojet engine. The cascades translates between a direct jet position where the cascades are retracted in a fan casing, and an indirect jet position where the cascades are brought out of the fan casing. In particular, the cascades have a sliding connection with the mast by means of at least one spacer connected to the mast downstream of the front suspension. | 01-28-2016 |
20160040624 | NACELLE JET PIPE DEVICES FOR REGULATING PRESSURE - A nacelle jet pipe is equipped with a device for regulating the pressure of a flow of air leaving the jet pipe. The device includes an annular element surrounding the downstream end of the jet pipe, and an adjuster to adjust the position of part of the annular element in relation to the downstream end of the jet pipe. In particular, the annular element forms, with the downstream end of the jet pipe, a constricted zone the widest part of which is situated upstream of the narrowest part and the profile of which can be varied according to the position of the annular element. | 02-11-2016 |
20160047333 | THRUST REVERSER CASCADE ELEMENT OF AN AIRCRAFT GAS TURBINE - The present invention relates to a thrust reverser cascade element of an aircraft gas turbine with a rigid frame and with several thrust reverser profiles mounted in the frame, wherein the thrust reverser cascade element is made of fiber-plastic composite. | 02-18-2016 |
20160047334 | THRUST REVERSER ACTUATOR WITH PRIMARY LOCK - Actuator assembly includes a housing assembly, a ball screw, a ball nut, and a lock. The ball screw is rotationally mounted on and extends from the housing assembly, is coupled to receive an actuator drive torque, and is configured, upon receipt thereof, to rotate. The ball nut is rotationally supported on the ball screw and is configured, in response to rotation of the ball screw, to translate thereon between a stowed position and a deployed position. The lock is disposed at least partially within the housing assembly and is configured to move between a lock position and an unlock position. The lock prevents the ball nut from translating out of the stowed position when the lock is in the lock position and the ball nut is in the stowed position. | 02-18-2016 |
20160053719 | AUTOMATIC DEFLECTION LIMITING LATCHES FOR A THRUST REVERSER - A nacelle may include a pylon and a thrust reverser having an inner fixed structure. A locking mechanism may automatically engage and prevent relative movement between thrust reverser halves. A bumper may be coupled to the inner fixed structure. The locking mechanism may limit deflections between the thrust reverser and the pylon in response to a burst duct. A locking mechanism in the inner fixed structure may include a pressure relief door and an arrestor which hooks onto a retaining bar in a pylon bracket. The locking mechanism may allow the thrust reverser halves to be opened for access to the engine. | 02-25-2016 |
20160076487 | System and Method for Improved Thrust Reverser With Increased Reverse Thrust and Reduced Noise - A system and method for providing reverse thrust is disclosed. The system can include one or more cascade elements. The one or more cascade elements can each include a plurality of vanes to redirect engine thrust in a forward direction relative to travel. Some, or all, of the vanes can include raised geometric patterns configured to increase the mixing of the airstreams between the reversed engine thrust and the airstream over the vehicle to reduce noise and improve reverse thrust. The angle, curvature, and geometric pattern of the vanes can be optimized for a particular cascade element, engine, location on the engine, row, or can be optimized individually to maximize reverse thrust and minimize noise. | 03-17-2016 |
20160083103 | DEVICE FOR CONTROLLING THE POWER OF AN ENGINE AND FOR CONTROLLING A THRUST REVERSER DEVICE - A device for controlling the power of an engine and of a thrust reverser device. The invention includes a frame on which a primary cam track is formed,—a thrust lever hinged to the frame,—a thrust reverser lever hinged to the thrust lever,—a bearing face arranged on the thrust reverser lever,—a locking lever hinged to the thrust lever and comprising a first end and a second end. When the thrust lever has been pivoted by a predefined angle relative to the idle position of same, actuation of the thrust reverser lever is blocked, both by the second end of the locking lever pressing against the bearing face of the thrust reverser lever, and by the first end of the locking lever pressing against the primary cam track. | 03-24-2016 |
20160102633 | CONTROL DEVICE FOR A TURBOJET ENGINE THRUST REVERSER, BLOCKING THE REVERSER - A control device for a thrust reverser of a turbojet engine nacelle, which includes movable portions actuated by actuators, includes: a first blocking control acting on a motor-actuated system; and a second blocking control acting, mechanically, on the movable portions. The second blocking control may inhibit, when activated, a deployment of the movable portions. The control device further includes a device inhibiting disengagement of the first blocking control when a mechanical control is activated. | 04-14-2016 |
20160108852 | THRUST REVERSER FOR A TURBOJET ENGINE NACELLE, COMPRISING CASCADES PARTIALLY INTEGRATED IN THE COWLS - A thrust reverser for a turbojet engine nacelle includes movable cowls which move backward relative to a front frame under the action of an actuation system, thereby making flaps tilt, via a control mechanism, so as to substantially close the annular cold air flow path, and by opening cascades disposed around this flow path and which receive the cold air flow and return it forward. When the thrust reverser is closed, the cascades are partially integrated in the cowls, and the thrust reverser includes an actuation system which makes the cascades move backward along a stroke which is shorter than the stroke of the cowl. | 04-21-2016 |
20160108853 | THRUST REVERSER ACTUATOR DAMPER SYSTEM - A nacelle may comprise a thrust reverser. The thrust reverser may comprise a translating sleeve, a cascade array, and a TRAS actuator. The TRAS actuator may pass through an aperture in an aft cascade ring of the cascade array. A retainer may be coupled to the aft cascade ring. A damper may be coupled to the retainer. The damper may circumscribe the TRAS actuator. The damper may be configured to damp vibrations in the TRAS actuator. As an amplitude of vibration or deflection of the TRAS actuator increases, a reaction force applied by the damper on the TRAS actuator increases, which prevents the TRAS actuator from contacting the aft cascade ring. | 04-21-2016 |
20160115902 | NACELLE FOR A TURBOJET ENGINE WITH A VARIABLE NOZZLE - The present disclosure provides a turbojet engine nacelle having a downstream section including a cowl which is ended with a hinged flap constituting a nozzle. In particular, the hinged flap is hingedly and translatably hinged to the cowl. | 04-28-2016 |
20160115903 | Aircraft gas turbine thrust-reversing device having a guide rail - The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling whose rear area can be moved in the axial direction of the engine from a closed forward-thrust position into a rearward moved thrust-reversing position in which a free, substantially annular space to a front and fixed area of the engine cowling is present, where on the engine cowling guide rails are arranged, inside which mounting elements can be moved by means of rolling or sliding elements, with which mounting elements the rear area of the engine cowling his mounted, characterized in that the guide rails have an oval and C-shaped cross-section, provided on a longitudinal side with a slot-like opening, and are mounted using mounting projections arranged centrally and opposite to one another and designed in one piece with the C-shaped cross-section. | 04-28-2016 |
20160131079 | Engine cowling of a gas turbine with thrust-reversing device and adjustable outlet nozzle - An engine cowling of an aircraft gas turbine having a front cowling and a single rear cowling movable in the axial direction. By a drive device, the rear cowling is movable into different positions including a closed cruise position, a partially opened maximum thrust position and a completely opened thrust-reversing position. The drive device includes at least two actuators arranged in series relative to one another and actuated independently of one another, the actuators having power supply systems separated from one another and separately operating, where one of the actuators is designed for the maximum thrust position and the other actuator for the thrust-reversing position. The rear cowling can be locked in the maximum thrust position or the thrust-reversing position by two independent locking devices. | 05-12-2016 |
20160131080 | PROPULSION UNIT FOR AN AIRCRAFT - An aircraft propulsion assembly including a turbojet nacelle, and the nacelle includes a stationary structure and a movable structure. The movable structure includes: a thrust reversal device including a cowl translatable along a substantially longitudinal axis of the nacelle between a retracted position, and a deployed position; and a secondary air flow exhaust nozzle including a device for electrically controlling and actuating the nozzle. In particular, the device for controlling and actuating the nozzle includes an electrical switch suitable for being closed during a direct jet operation of the nacelle and moreover suitable for being open during a reverse jet operation. The electrical switch includes a stationary connector and a movable connector. | 05-12-2016 |
20160131081 | ELECTRIC THRUST REVERSER SYSTEM FOR AN AIRCRAFT ENGINE NACELLE AND AIRCRAFT ENGINE NACELLE EQUIPPED WITH SAME - The present disclosure provides an electric thrust reverser system for an aircraft engine nacelle, including a mechanism for actuating a thrust reverser mechanism. The actuating mechanism includes a first drive cylinder and a second drive cylinder. Each cylinder includes a mechanical connection casing, a primary lock ( | 05-12-2016 |
20160131082 | THRUST REVERSER WITH HIDDEN LINKAGE BLOCKER DOORS - Aspects are directed to a system that includes an outer structure of a thrust reverser, a blocker door, and a plurality of four-bar mechanisms arranged in series with one another that couple the outer structure and the blocker door. Aspects are directed to a system for a thrust reverser of an aircraft that includes a blocker door, a kinematic mechanism configured to actuate the blocker door, and a pressure shelf, where the blocker door is configured to reside below the pressure shelf in proximity to a duct of the thrust reverser, and where at least a portion of the kinematic mechanism is configured to reside above the pressure shelf. | 05-12-2016 |
20160160796 | Thrust reverser for an aircraft engine, pod assembly and corresponding powerplant - A thrust reverser for an aircraft engine assembly, comprising two sub-assemblies configured to surround an engine, each of the sub-assemblies comprising an inner fixed structure, a translating cowl, a torque box, a substantially vertical 12 o'clock bifurcation, and a substantially vertical 6 o'clock bifurcation. At least one of the sub-assemblies comprises at least one separating partition extending between the inner fixed structure, the translating cowl and the torque box of the sub-assembly, the separating partition being rigidly fixed to the inner fixed structure and the torque box, and connected to the translating cowl via a sliding connection. | 06-09-2016 |
20160160798 | INTEGRATED THRUST REVERSER DEVICE AND AIRCRAFT ENGINE NACELLE EQUIPPED THEREWITH - The present disclosure provides a thrust reverser device that is integrated in an aircraft nacelle. Blocking flaps are stored inside a mobile cowl disposed in a downstream section of the nacelle, under deflection cascade assemblies during direct-jet operation of the nacelle. Various devices are provided for executing the passage from direct-jet operation to reverse-jet operation in two stages: the mobile cowl moves in translation towards the downstream end of the nacelle; and each flap is then deployed in the main air flow path. | 06-09-2016 |
20160160799 | SPLIT SLEEVE HIDDEN DOOR THRUST REVERSER - A system for a thrust reverser of an aircraft includes a primary sleeve and a secondary sleeve having cascades. The secondary sleeve is coupled to a set of blocker doors. The sliding motions of the primary sleeve and the secondary sleeve are not directly coupled when each moves between its stowed and deployed positions. The sliding motion of the primary sleeve may begin at a different time and continue at a different rate from the sliding motion of the secondary sleeve. | 06-09-2016 |
20160169156 | THRUST REVERSER SYSTEM WITH TRANSLATING-ROTATING HINGE ASSEMBLY | 06-16-2016 |
20160169158 | ACTUATION SYSTEM FOR A TRANSLATING VARIABLE AREA FAN NOZZLE | 06-16-2016 |
20160186688 | INTEGRATED THRUST REVERSER ACTUATION SYSTEM - A turbofan engine having a turbine engine, a nacelle surrounding a portion of the turbine engine, and a thrust reverser. The thrust reverser comprises a movable control surface movable to and from a reversing position and a thrust reverser actuation system having at least one actuator operably coupled to the movable control surface to move the movable control surface into and out of the reversing position. A guide comprising a rail and a bogie having at least one rotatable bearing surface coupled to the rail for relative translational movement between the rail and bogie connects the turbine engine to the movable control surface such that operation of the at least one actuator moves the movable control surface by translation movement between the rail and the bogie. | 06-30-2016 |
20160186689 | Thermoformed Cascades for Jet Engine Thrust Reversers - A cascade for a jet engine thrust reverser is fabricated by co-consolidating pre-consolidated thermoplastic strongbacks and vanes. The strongbacks are reinforced with continuous fibers, and the vanes are reinforced with discontinuous fibers. | 06-30-2016 |
20160201600 | THRUST REVERSER SLIDING DOOR ASSEMBLY | 07-14-2016 |