| Entries |
| Document | Title | Date |
|---|
| 20080250770 | BY-PASS TURBOJET INCLUDING A THRUST REVERSER - A by-pass turbojet including a thrust reverser. The thrust reverse comprises deflector means for deflecting all or part of the primary stream gas in such a manner that the deflected primary stream gas encounters the secondary stream, thereby reducing the injection speed of the secondary stream in an aft direction, and thus generating the thrust-reversal effect. The secondary stream escapes from the aft end of the nacelle. In the thrust-reversal position, the deflector means are inscribed radially substantially within the section of the primary nozzle cowl at the aft end of the nacelle. Such a thrust reverser is particularly simple in design, inexpensive, and makes it possible to avoid having moving parts present on the outside portion of the nacelle, thus simplifying the design of the turbojet. | 10-16-2008 |
| 20080271432 | SEALING ARRANGEMENTS FOR GAS TURBINE ENGINE THRUST REVERSER - A transcowl for a gas turbine engine thrust reverser includes an arcuate outer wall; an arcuate inner wall; and an arcuate baffle positioned between the inner and outer walls at a forward end of the transcowl. The baffle has an arcuate cross-sectional shape which defines a forward-facing interior area. An arcuate forward seal is carried at a forward end of the inner wall. The forward seal includes a plurality of axially-extending, spaced-apart arcuate seal teeth which collectively define a labyrinth seal. | 11-06-2008 |
| 20090064658 | BYPASS TURBOMACHINE WITH REDUCTION OF JET NOISE - In a bypass turbomachine, at least one air takeoff orifice is provided in the primary channel, said orifice leading to an air takeoff pipe housed inside an air inlet sleeve of the nacelle. The air takeoff pipe opens out in the vicinity of the pylon into two air diffusion pipes each secured to a respective maintenance cover, each air diffusion pipe opening out into an air injection pipe secured to a thrust reverser cover and itself opening out to the outside of the nacelle via the trailing edge thereof, each air injection pipe being suitable for uncoupling from the corresponding air diffusion pipe when the corresponding thrust reverser cover slides downstream. | 03-12-2009 |
| 20090071122 | THRUST REVERSER MOUNTING STRUCTURE - A gas turbine engine comprising a core engine surrounded by a core casing, at least one C-duct having radially inner and outer walls and a thrust reverser unit; the engine is mounted to an aircraft pylon via at least one thrust member attached to the core engine; the thrust reverser unit is mounted within the outer wall of the C-duct; the C-duct is secured to the core casing via a vee-groove attachment comprising vee-groove and vee-blade parts, the attachment is arranged to transfer loads between the thrust reverser unit and the pylon; wherein one cooperating part of the attachment is mounted to a torsion box mounted on the inner wall of the C-duct. | 03-19-2009 |
| 20090107108 | NACELL FOR BYPASS ENGINE WITH HIGH BYPASS RATIO - This invention relates to a nacelle for bypass engine with a high bypass ratio comprising an interior flow channel for a secondary flow generated by the bypass engine and having an external structure provided with a reverse thrust device capable of alternately shifting from a closed position in which it enables circulation of the direct-jet secondary flow inside the interior channel, to an open position in which it uncovers an opening in the external structure so as to enable reorientation of the secondary flow in an angled flow via activation of the reverse thrust means; in open position, the reverse thrust device partially blocks the interior channel so as to provide a leakage section therein, enabling circulation of a controlled leakage flow, said nacelle being characterized in that, when the thrust reversal device is in open position and has an angled-jet reversal section and a leakage section through the interior channel the sum of which is substantially equal to a direct-jet secondary flow discharge section, when the thrust reversal device is in closed position. | 04-30-2009 |
| 20090126339 | Thrust Reverser Door - A thrust reverser door provides in one aspect a separation of structural and aerodynamic functions through the provision of individual structures. In some embodiments, an aerodynamic element is adjustable in position, while in other embodiments, the relative positions are fixed. An exemplary aerodynamic element extends radially into the reverser flow to redirect the flow away from the door surface. | 05-21-2009 |
| 20090126340 | Pivoting Door Thrust Reverser for a Turbofan Gas Turbine Engine - A pivot arrangement for a thrust reverser door of a gas turbine engine, the pivot fitting having a base and a shaft projecting from a main side of the base. The shaft receives a preferably curved pivot arm of the door to provide a low profile arrangement which improves performance when the doors are stowed. | 05-21-2009 |
| 20090126341 | Thrust Reverser - The thrust reverser is used with an aircraft gas turbine engine and includes upper and lower doors pivotable between a stowed position and a deployed position. When deployed, the doors redirect a portion of the efflux to generate a nose-down pitching moment on an aircraft to improve handling during thrust reversing on a runway. | 05-21-2009 |
| 20090126342 | Thrust Reverser Door - A thrust reverser door is provided, in one configuration, with a plurality of peripherally-disposed frames circumferentially spaced apart from one another and projecting radially inwardly on an interior side of the door to thereby provide a channel for redirecting thrust. | 05-21-2009 |
| 20090188233 | THRUST REVERSER FORMING AN ADAPTIVE NOZZLE - The present invention relates to a thrust reverser for the nacelle of a turbojet engine comprising, on the one hand, means ( | 07-30-2009 |
| 20090193789 | VARIABLE AREA FAN NOZZLE THRUST REVERSER - A nozzle for use in a gas turbine engine includes nozzle doors coupled with a fan nacelle wherein the nozzle doors move in unison between a plurality of positions to influence a bypass airflow through a fan bypass passage. A linkage connects the nozzle doors and an actuator. A louver section coupled with the linkage moves in unison with the nozzle doors between a plurality of louver positions to direct a portion of the bypass airflow in a selected direction. | 08-06-2009 |
| 20090199536 | PROCESS FOR REVERSING THE THRUST PRODUCED BY A PROPULSION UNIT OF AN AIRCRAFT, DEVICE FOR ITS IMPLEMENTATION, NACELLE EQUIPPED WITH SAID DEVICE - The object of the invention is a process whose purpose is to reduce, cancel or reverse the thrust generated by at least one air flow exiting from a propulsion unit of an aircraft by deflecting at least a portion of the flow that is able to assist the thrust, characterized in that it consists in injecting at the level of the propulsion unit a fluid called a thrust reversal fluid to deflect by an entrainment effect, from the inside of the nacelle toward the outside of the nacelle, at least a portion of the flow that is able to assist the thrust. | 08-13-2009 |
| 20090205312 | SWEPT FAN RAMP FOR PIVOT DOOR THRUST REVERSER - A swept fan ramp for a pivot door thrust reverser includes a cylindrical unit with an elliptical flared portion, a side portion, and a rectangular flared portion. The elliptical flared portion is operable to reduce drag on airflow in a reverse direction and is coupled to the top center and bottom center of the circumference of the cylindrical unit. The side portion is operable to reduce side spillage airflow and is coupled to the central left side and central right side of the aft circumference of the cylindrical unit. The rectangular flared portion is operable to promote separation of airflow into an upper airflow path and a lower airflow path, is coupled with the aft circumference of the cylindrical unit, and is connected to the elliptical flared portion and the side portion. | 08-20-2009 |
| 20090260344 | Rear fan case for a gas turbine engine - A rear fan case for a gas turbine engine includes a main body and a discrete joining arrangement mounted on the outside of the main body towards its rear end. The joining arrangement provides a substantially radial groove around the main body, which can receive a joining blade on a thrust reverser unit to form a joint between the rear fan case and the thrust reverser unit. The joining arrangement may be made of metal while the main body is made of composite material. Features may be provided to ensure proper alignment and location of the joining arrangement. | 10-22-2009 |
| 20090301056 | AIRCRAFT ENGINE THRUST REVERSER - A power unit for providing propulsive thrust includes an efflux duct defining a first fluid flow path along which gaseous fluid travels for discharge from a first fluid exit opening to provide propulsive thrust. The power unit also has a thrust reversing structure which, when in a deployed position, redirects the flow of gaseous fluid along a second fluid flow path to discharge from a second fluid exit opening to provide reverse thrust. The thrust reversing structure includes longitudinally translating cowl portions, which are moveable from a stowed position to the deployed position where the translating cowl portions block a major portion of the first fluid exit opening to cause gaseous fluid to efflux from the second fluid exit opening. The translating cowl portions move in a generally longitudinal direction towards the deployed position along a path which is inclined to the power unit axis. | 12-10-2009 |
| 20090313969 | Thrust Reverser for a Turbofan Gas Turbine Engine - The thrust reverser comprises sections, such as arms and skins, which may be connected along joints to provide a thrust reverser body. A plurality of fittings may be integrally formed on a surface of each arm. | 12-24-2009 |
| 20090320444 | ACTUATING OF A THRUST REVERSER IN A TURBOMACHINE - Turbomachine, comprising at least one thrust reverser and means for actuating this thrust reverser which comprise at least one hydraulic engine supplied with pressurised fluid by a fuel circuit of the turbomachine. | 12-31-2009 |
| 20100024387 | AIRCRAFT NACELLE WHICH INCLUDES THRUST REVERSER SYSTEM AND AIRCRAFT INCORPORATING AT LEAST ONE SUCH NACELLE - Aircraft nacelle which includes a cowl with a longitudinal axis, an engine housed in the cowl, an annular channel surrounding the engine and designed to receive a secondary flow, wherein the cowl includes a fixed part and a moving part which slides along the longitudinal axis to define a radial opening between the moving and fixed parts, a thrust reverser system which includes internal flaps mounted so that they rotate and which are designed to block the annular channel, at least partially, in the deployed position, where the moving part of the cowl includes a radial housing to receive the internal flaps in the at-rest position and where a system of applying an elastic force on each flap towards deployment is provided. Thus control over the position of the internal flaps is obtained directly by sliding the moving part. | 02-04-2010 |
| 20100031630 | AIRCRAFT NACELLE THAT INCORPORATES A DEVICE FOR REVERSING THRUST - An aircraft nacelle in which a power plant is arranged and delimits a duct for a flow which assists the thrust. The nacelle includes a device for reducing, canceling, or reversing the thrust that includes at least one flap that can an active position in which it deflects—in the direction of a radial opening—at least a portion of the flow and an at-rest position in which the flap does not interfere with the flow, whereby the wall of the nacelle delimiting the duct includes at least one moving part that can occupy a first position in which it is interposed between the flow to be deflected and the flap and another position in which it releases the flap so as to allow the flap to change position and to move from the at-rest position to the active position. Each flap includes articulation elements with a first pivoting axis and a second pivoting axis, whereby the pivoting axes are essentially parallel to the vertical median axis of the nacelle. | 02-11-2010 |
| 20100037587 | Turbojet Nacelle Equipped With Means For Reducing The Noise Produced By Said Turbojet - This nacelle ( | 02-18-2010 |
| 20100058736 | DEVICE FOR OPENING AND CLOSING A THRUST REVERSER DOOR OF A JET ENGINE - A device for opening and closing a thrust reverser door ( | 03-11-2010 |
| 20100064659 | TRANSLATING VARIABLE AREA FAN NOZZLE WITH SPLIT BEAVERTAIL FAIRINGS - A nacelle assembly includes a first portion having an outer fairing and a trailing edge, and a translatable variable area fan nozzle. The fan nozzle includes two or more nozzle segments, each nozzle segment having first and second opposed ends and a leading edge. The nozzle segments are selectively movable between a stowed position and one or more deployed positions. In the deployed position, an upstream bypass flow exit is formed between the trailing edge and the leading edge. The nacelle assembly further includes a guide mechanism for guiding the nozzle segments between the stowed position and the deployed position. A split beavertail failing shields the guide mechanism against air flow when the nozzle segments are in the stowed position. | 03-18-2010 |
| 20100064660 | JET ENGINE NACELLE MEMBER - The invention relates to an nacelle member ( | 03-18-2010 |
| 20100089029 | Actuator - An actuator comprises a screw shaft, a nut translatable along the screw shaft upon relative rotation occurring therebetween, and articulated connection means securing an output member to the nut, the output member being of elongate form and extending substantially parallel to or coaxial with the screw shaft when the actuator is in a retracted position. | 04-15-2010 |
| 20100107598 | SELF-CALIBRATION METHOD FOR THE ELECTRIC JACKS OF A TURBOJET NACELLE - The invention relates to a method for the self-calibration of electric jacks ( | 05-06-2010 |
| 20100107599 | THRUST REVERSER FOR A JET ENGINE - The invention relates to a thrust reverser ( | 05-06-2010 |
| 20100115915 | METHOD FOR CONTROLLING ELECTRIC MOTORS OF A THRUST REVERSER - The invention relates to a method for controlling an electric motor actuating a mobile hood provided in a thrust reverser for a turboreactor, said method being characterised in that it comprises steps of: determining the operating state of the electric motor; interrupting the supply of the electric motor if said motor is not in operation during a defined period of time; reactivating the electric motor after an idle period and repeating the previous steps or definitively stopping the motor if the steps have already been repeated a pre-defined number of times. The invention also relates to a method for managing the electrical supply of a motor provided in a device arranged in the vicinity of a turboreactor. | 05-13-2010 |
| 20100115916 | NACELLE FOR TURBOJET JET FITTED WITH A SINGLE DOOR THRUST REVERSER SYSTEM - A nacelle for a turbojet includes an air inlet structure capable of channeling an air flow toward a fan of the turbojet, a middle structure designed to surround the fan and a downstream section fitted with a pivoting-door thrust reverser system having a single thrust reverser door mounted so as to pivot between a closed position in which it allows an air flow to travel from the turbojet in a direct jet and in which it ensures the internal and external aerodynamic continuity of the nacelle and an open position in which it pivots toward a position substantially perpendicular to the axis of the nacelle, a downstream portion of the door moving inside the nacelle to close off at least a portion of the air flow of the turbojet and direct it in a direction oriented toward the front of the nacelle, where the downstream section has, downstream of the door, a ring extending over the whole periphery. | 05-13-2010 |
| 20100126139 | PIVOTING FAN NOZZLE NACELLE - A variable area nozzle system for a gas turbine engine includes a fan duct inner wall, a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, and a fan nozzle. The fan nozzle defines at least a portion of the fan duct outer wall and includes a nozzle aft edge. The fan duct inner wall and the nozzle aft edge collectively define a fan duct nozzle throat area. The fan nozzle is configured to pivot about a pivot axis that may be oriented transversely relative to a longitudinal axis of the gas turbine engine. The fan nozzle may be pivoted from a stowed position to a deployed position in order to vary the fan duct nozzle throat area. | 05-27-2010 |
| 20100132331 | BAFFLE SEAL FOR GAS TURBINE ENGINE THRUST REVERSER - A baffle seal for a thrust reverser of a gas turbine engine includes a seal body of a resilient material. The seal body has a relatively flat central portion with opposed front and back sides. A raised sealing rim extends at least partially around the central portion. An outer periphery of the sealing rim extends beyond an outer periphery of the central portion so as to define an exposed sealing surface. | 06-03-2010 |
| 20100132332 | CASCADE-TYPE THRUST REVERSER FOR JET ENGINE - A fan duct ( | 06-03-2010 |
| 20100139242 | THRUST REVERSER WITH GRIDS FOR JET ENGINE - The invention relates to a thrust reverser ( | 06-10-2010 |
| 20100146933 | NACELLE REAR ASSEMBLY FOR TURBOJET ENGINE - The invention relates to a nacelle rear assembly for a turbojet engine, that comprises: a hood, an inner structure in the shape of a sheath in which at least the rear portion ( | 06-17-2010 |
| 20100205931 | DOUBLE-ACTING TELESCOPIC LINEAR ACTUATOR WITH SINGLE-MOTOR DRIVE SYSTEM - The present invention relates to a telescopic linear actuator for moving a first ( | 08-19-2010 |
| 20100212286 | THRUST REVERSER CONFIGURATION FOR A SHORT FAN DUCT - A thrust reverser comprises a translating sleeve, a torque beam, a plurality of cascades, a plurality of blocker doors, and a plurality of actuators. The translating sleeve is positioned at the rear of an aircraft nacelle and is translated rearward during thrust reverser deployment. The torque beam is positioned within the nacelle and configured to prevent airflow into the nacelle during thrust reverser deployment. The plurality of cascades are positioned around the circumference of the torque beam during thrust reverser stowage and are translated rearward during thrust reverser deployment. The plurality of blocker doors are positioned in alignment with the plurality of cascades and direct airflow through the plurality of cascades during thrust reverser deployment. The plurality of actuators are coupled to the forward edge of the sleeve and configured to translate the sleeve rearward during thrust reverser deployment. | 08-26-2010 |
| 20100212287 | THRUST REVERSER WITH A SYSTEM FOR BRAKING THE ACTUATORS - The present invention relates to a thrust reverser for a jet engine nacelle comprising at least one movable cowl ( | 08-26-2010 |
| 20100218479 | LINEAR TELESCOPIC ACTUATOR FOR MOVING A FIRST AND A SECOND ELEMENT RELATIVE TO A STATIONARY ELEMENT - The invention relates to a linear telescopic actuator for moving a first ( | 09-02-2010 |
| 20100218480 | ACTUATOR FOR AN AIRCRAFT NACELLE MOBILE STRUCTURE, AND NACELLE COMPRISING AT LEAST ONE SUCH ACTUATOR - This actuator for an aircraft engine nacelle mobile structure ( | 09-02-2010 |
| 20100229527 | TRANSLATING VARIABLE AREA FAN NOZZLE PROVIDING AN UPSTREAM BYPASS FLOW EXIT - A variable area fan nozzle assembly for a turbofan engine includes a nacelle having an aft edge and a translating nozzle segment having a forward edge and a first end. The nozzle segment is movably disposed behind the aft edge such that an upstream bypass flow exit is defined between the aft edge and the forward edge when the nozzle segment is in a deployed position. A deflector is disposed between the aft edge and the forward edge proximate to the first end. The deflector substantially prevents bypass flow from exiting the upstream bypass flow exit in a region that is proximate to the first end. | 09-16-2010 |
| 20100229528 | 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. | 09-16-2010 |
| 20100242434 | METHOD OF MONITORING A THRUST REVERSER - The method of the invention for monitoring a thrust reverser of a turbojet having an actuator controlled by an electric motor consists in determining a maintenance notice from a weighted combination of provisional notices, each provisional notice relating to a category of parameters associated with at least one phase of an operating cycle of the reverser, the category being selected from a category of parameters representative of a duration of said phase, of an energy seen by the motor during said phase, of a torque seen by the motor at a predefined instant of said phase, and of a duration during which the setpoint speed of rotation and the measured speed of rotation of the motor differ during said phase, each provisional notice being generated by analyzing values obtained during at least one cycle for at least one parameter of said category relative to a degradation threshold. | 09-30-2010 |
| 20100251693 | CASCADE-TYPE THRUST REVERSER - The invention relates to a grid-type thrust reverser comprising: a fixed structure ( | 10-07-2010 |
| 20100257841 | VARIABLE AREA FAN NOZZLE AND THRUST REVERSER - A nozzle for use in a gas turbine engine includes a nozzle door having a first end, a second end opposed from the first end, and a pivot between the first end and the second end. A linkage connects to the nozzle door and to an actuator. The actuator is selectively operative to move the linkage to in turn move the nozzle door about the pivot between a plurality of positions, such as a stowed position, an intermediate position, and a thrust reverse position, to influence a bypass airflow through a fan bypass passage. | 10-14-2010 |
| 20100281849 | DOOR-TYPE THRUST REVERSER FOR A JET ENGINE - This thrust reverser comprises at least two doors ( | 11-11-2010 |
| 20100287910 | NACELLE WITH SIMPLIFIED COWLING ARRANGEMENT - The invention relates to a nacelle ( | 11-18-2010 |
| 20100307130 | NON-HANDED THRUST REVERSER FOR INSTALLATION ON HANDED AIRCRAFT GAS TURBINE PROPULSION ENGINES - An assembly for an aircraft gas turbine propulsion engine includes an engine nacelle and a thrust reverser. The engine nacelle is configured to have at least a portion of an aircraft gas turbine propulsion engine mounted therein, and comprises an intake end, an exhaust end, and an outer surface that extends between the intake end and the exhaust end. At least the engine nacelle outer surface proximate the exhaust end has a semicircular section and a noncircular section. The thrust reverser includes a forward end, an aft end, and an outer surface that extends between the forward and aft ends. The thrust reverser forward end is coupled to the engine nacelle exhaust end. At least the thrust reverser outer surface proximate the forward end has an arc section and a noncircular section. The arc section subtends an angle greater than π radians. | 12-09-2010 |
| 20100313546 | CONTROL SYSTEM FOR TURBOJET ENGINE NACELLE - The invention relates to a turbojet engine nacelle that includes a power supply source ( | 12-16-2010 |
| 20100326047 | SYSTEM AND METHOD FOR ASSEMBLING A THRUST REVERSER FOR A GAS TURBINE PROPULSION SYSTEM - A method of assembling a thrust reverser assembly for use in an aircraft gas turbine propulsion system. The method includes coupling a translating cowl to a fixed cowling, such that the translating cowl at least partially covers an engine, and is movable between an open position and a closed position. A rod end assembly is coupled to the translating cowl and an actuator is coupled to the rod end assembly, such that the actuator is movable between a first position and a second position. A torque bracket is coupled to the rod end assembly. The torque bracket includes at least two arms that each extend outward from the rod end assembly, such that a bending loading induced to the rod end assembly is induced to the translating cowl by the torque bracket. | 12-30-2010 |
| 20110016846 | METHOD AND SYSTEM FOR CONTROLLING AT LEAST ONE ACTUATOR OF THE COWLINGS OF A TURBOJET ENGINE THRUST INVERTER - The invention relates to a control system for at least one actuator ( | 01-27-2011 |
| 20110030338 | BYPASS TURBOJET ENGINE NACELLE - The invention relates to a bypass turbojet engine nacelle comprising a downstream section equipped with a thrust reverser device comprising a moving cowl ( | 02-10-2011 |
| 20110072780 | Thrust Reverser Actuation - A thrust reverser drive arrangement is described for use in driving a thrust reverser cowl for movement relative to first and second guide tracks, the drive arrangement comprising a first actuator located, in use, close to the first guide track, and a second actuator located, in use, close to the second guide track, the actuators being arranged to be driven in synchronism and at the same speed by a drive motor to drive the cowl for movement, wherein at least one of the first and second actuators is provided with a load limiter to limit the transmission of loads through that actuator in the event that that actuator is subject to a compressive loading greater than a predetermined level. | 03-31-2011 |
| 20110120078 | VARIABLE AREA FAN NOZZLE TRACK - A variable area fan nozzle for a high-bypass gas turbine engine includes a first track slider movable relative to the hinge beam along a first interface. A second track slider is movable relative to the first track slider along a second interface that is more closely controlled than the first interface. A VAFN cowl is mounted to the second track slider. | 05-26-2011 |
| 20110120079 | VARIABLE AREA FAN NOZZLE STIFFENERS AND PLACEMENT - A nacelle assembly for a high-bypass gas turbine engine is disclosed and includes a variable area fan nozzle (VAFN) including at least one second fan nacelle section movable relative to the first fan nacelle section to modify an area of the bypass flow path. At least one stiffener is mounted between the first fan nacelle section and the second fan nacelle section. The stiffeners modify mode shapes and natural frequencies to substantially reduce or eliminate flutter within operating ranges that are produced by unsteady aerodynamic loads. | 05-26-2011 |
| 20110146230 | Integrated Nacelle Assembly - An assembly includes a unitary nacelle structure and an integrated fan housing for a gas turbine engine assembly. The unitary nacelle structure includes an inlet region and a fan cowl region, and is configured to at least partially circumscribe the integrated fan housing. The integrated fan housing comprises an integral composite structure and includes a fan case sized and configured for encircling a fan blade assembly of an associated gas turbine engine, a fan hub, and a plurality of fan outlet guide vanes. The unitary nacelle structure cooperates with the integrated fan housing to transfer static and dynamic loads directly to a support structure, rather than through the engine core, to minimize backbone bending. | 06-23-2011 |
| 20110167790 | TRANSLATABLE CASCADE THRUST REVERSER - A nacelle assembly for a high-bypass gas turbine engine includes a fan nacelle that includes a first fan nacelle section and a second fan nacelle section, the second fan nacelle section movable relative to the first fan nacelle section. A cascade array is mounted to the first fan nacelle section for movement relative thereto between a stored position and a deployed position, the stored position locates the cascade array at least partially within the first fan nacelle section. | 07-14-2011 |
| 20110192135 | Control System - A control system comprises a TRAS actuator | 08-11-2011 |
| 20110265446 | SYSTEM FOR CONTROLLING AT LEAST ONE ACTUATOR OF THE COWLINGS OF A TURBOJET ENGINE THRUST REVERSER - The control system of the invention includes at least one actuator ( | 11-03-2011 |
| 20110277448 | GUIDE SYSTEM FOR NACELLE ASSEMBLY - A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member and a track liner engaged therewith. The track guide member includes a track channel configured to receive the track liner. The track liner defines an interior surface and includes a projection portion projecting inwardly of the track channel to define a convex surface. The slider assembly translatably engages the track assembly and includes a slider member having a head portion configured to be received within the track channel. The head portion defines a concave surface substantially corresponding to the convex surface of the track liner and is configured to mate therewith. The slider member further includes an extension portion extending from the head portion and outwardly of the track assembly. | 11-17-2011 |
| 20110289900 | THRUST REVERSING VARIABLE AREA NOZZLE - A gas turbine engine system includes a first nozzle section associated with a gas turbine engine bypass passage and a second nozzle section that includes a plurality of positions relative to the first nozzle section. In at least one of the positions, there is a gap between the first nozzle section and the second nozzle section. A movable door between the first nozzle section and the second nozzle section selectively opens or closes the gap. | 12-01-2011 |
| 20110296812 | THRUST REVERSER ACTUATION SYSTEM ARCHITECTURE - A thrust reverser actuation system includes a plurality of actuators, a power drive unit, and a gear set. Each actuator is coupled to receive an actuator input torque and is configured, upon receipt of the actuator input torque, to move between a stowed position and a deployed position. The power drive unit has only one output shaft, and is configured to supply a drive torque via the output shaft. The gear set is connected to the output shaft and is coupled to each of the actuators. The gear set is configured to receive the drive torque via the output shaft and to supply the actuator input torque to each of the actuators. | 12-08-2011 |
| 20120006000 | BENT CONNECTING ROD FITTED WITH AT LEAST ONE SELF-ALIGNING MEANS - The invention relates to a bent connecting rod ( | 01-12-2012 |
| 20120011826 | TURBOJET ENGINE WITH AN ELEMENT OF THE NACELLE ATTACHED TO THE INTERMEDIATE CASING - The present invention relates to a turbojet engine with a fan ( | 01-19-2012 |
| 20120023900 | AIRCRAFT NACELLE - The invention relates to an aircraft nacelle comprising a cowling, an engine housed in an internal volume of the cowling and at least one thrust reverser, an air passage duct ( | 02-02-2012 |
| 20120036830 | THRUST REVERSAL DEVICE - The invention relates to a thrust reversal device comprising at least one cowl arranged in such a way that it can be moved between a closed position and an open position, said cowl being actuated by at least one actuator that can be driven by at least one electric engine. The invention is characterised in that at least one electric engine is connected to at least two separate power supplies ( | 02-16-2012 |
| 20120067024 | THRUST REVERSER FOR A DUAL-FLOW TURBINE ENGINE NACELLE - The invention relates to a thrust reverser ( | 03-22-2012 |
| 20120073262 | AIR DISCHARGING DEVICE FOR AN AIRCRAFT DOUBLE-FLOW TURBINE ENGINE - An air discharging device ( | 03-29-2012 |
| 20120079804 | COWL ASSEMBLY - An assembly for a turbofan engine includes a first cowl member comprising an aft portion and a translatable cowl member comprising a forward portion configured to be received within the aft portion. The translatable cowl member is configured to be moveable with respect to the first cowl member between a first operational position wherein the forward portion is received within the aft portion of the first cowl member, and a second operational position wherein a smaller portion of the forward portion is received within the aft portion than in the first operational position. The translatable cowl member is configured to cooperate with a core cowl of the turbofan engine to define a portion of a fan duct having an exit nozzle, and the translatable cowl member is configured to define a flow control location near the exit nozzle that is associated with a controlling fan duct area. | 04-05-2012 |
| 20120079805 | THRUST REVERSER ASSEMBLY - A thrust reverser assembly includes a first cowl member and a second cowl member repositionable relative to the first cowl member and operable to open a gap between the first cowl member and the second cowl member. A movable member is in supported connection with the second cowl member. The movable member is passively actuatable to move between a generally axially extending disposition and a generally radially extending disposition to direct bypass airflow of a turbofan engine. | 04-05-2012 |
| 20120137656 | ACTUATION SYSTEM - A system to provide differential movement between a first surface, a second surface and a fixed surface includes a first surface movable between a first position and a second position; a second surface movable with the first surface and further movable beyond the first surface; a shaft connected to the second surface to move the second surface; and a drive unit connected to the fixed surface to drive the shaft to move the second surface relative to the first surface and to allow the shaft to move through the drive unit when the second surface is being moved by the first surface. | 06-07-2012 |
| 20120272637 | REPLACING AN APERTURE IN A LAMINATED COMPONENT - An example method of replacing an aperture in a component includes placing layers of a filler material into a first aperture. The layers of the filler material arranged in a stacked relationship relative to each other within the first aperture. The method cures the filler material and establishes a second aperture that is at least partially defined by the filler material. | 11-01-2012 |
| 20120291415 | DUAL FUNCTION CASCADE INTEGRATED VARIABLE AREA FAN NOZZLE AND THRUST REVERSER - A gas turbine engine system according to an exemplary aspect of the present disclosure may include a core engine defined about an axis, a fan driven by the core engine about the axis to generate bypass flow, and at least one integrated mechanism in communication with the bypass flow. The bypass flow defines a bypass ratio greater than about six (6). The at least one integrated mechanism includes a variable area fan nozzle (VAFN) and thrust reverser, and a plurality of positions to control bypass flow. | 11-22-2012 |
| 20120291416 | Crack and Delamination Stoppers For Aircraft Propulsion System Components - An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin. | 11-22-2012 |
| 20120304621 | CLAMPING SYSTEM AND METHOD FOR THRUST REVERSER ATTACHMENT - A method and system suitable facilitating the connection and disconnection of a thrust reverser assembly to a fan case of a nacelle of a gas turbine engine. The method and system entail operating a clamping system to simultaneously engage and disengage flanges associated with the fan case and flanges associated with the fixed structure of the thrust reverser assembly. The clamping system includes a plurality of over-center clamping mechanisms, each of which is movable to simultaneously clamp together complementary flanges of the thrust reverser assembly and the fan case. | 12-06-2012 |
| 20130008145 | INTEGRATED ELECTRIC VARIABLE AREA FAN NOZZLE THRUST REVERSAL ACTUATION SYSTEM - An integrated variable area fan nozzle (VAFN) and thrust reversing actuation system (TRAS) system includes movable surfaces for adjusting an exit area for bypass flow and cowls moved for directing discharge flow in a reverser manner. The movable surfaces of the VAFN and TRAS systems are both coupled for movement by a common actuator arrangement. A power drive unit drives each of the actuators on each of the actuators through a gearbox or other linkage such that one common motor or motor combination is utilized for driving all of the actuators. A series of redundant and separately actuateable locks control deployment of the surfaces of the thrust reverse system such that thrust reversing system can move to an open or deployed position only in response to each of the locks being actuated to an unlocked condition. | 01-10-2013 |
| 20130025259 | DUCTED FAN GAS TURBINE ASSEMBLY - A ducted fan gas turbine assembly has a propulsive fan driven by a core engine. The turbine assembly has an annular bypass duct which receives an airflow from the fan and is bounded on the radially inward side by the core engine and on the radially outward side by an engine nacelle. The turbine assembly has a thrust reverser assembly having a vane arrangement including a first set of turning vanes for channelling airflow from the duct in a rearward direction, a second set of turning vanes for channelling airflow from the bypass duct in a forward direction. The thrust reverser assembly includes a plurality of blocker doors which are deployable to block the bypass duct. The nacelle has stationary and movable cowl portions that cooperate with the thrust reverser assembly to provide several operational configurations. | 01-31-2013 |
| 20130025260 | AIRCRAFT PROPULSION SYSTEM PROVIDED WITH REVERSE THRUST MEANS - The invention relates to a propulsion system including a nacelle and, inside said nacelle, a dual flow turbojet engine that itself includes a fan casing ( | 01-31-2013 |
| 20130047580 | TURBINE ENGINE - A turbine engine includes an engine core bounded by a bypass duct, a first portion of the bypass duct defined by a fan casing having a radially inner wall and a radially outer wall, a second portion of the bypass duct defined by a radially inner wall and a radially outer wall, a third portion of the bypass duct provided as at least one access door comprising a flow guide structure; and a thrust reverser mechanism coupled to the fan casing. | 02-28-2013 |
| 20130061572 | HYDRAULIC CONTROL SYSTEM FOR A THRUST REVERSAL DEVICE - A control system of a hydraulic type for a thrust reversal device with which a jet engine nacelle is equipped, and associated with a nozzle variation device, is provided by the present disclosure. The control system includes at least one additional control unit hydraulically connecting actuators together, wherein hydraulic supply lines from the control unit in a nozzle mode and from the control unit in a reverser mode are then able to communicate hydraulically with each other. A plurality of control valves are laid out so that when the unit for driving the actuators in a nozzle mode is active, a corresponding hydraulic signal controls the valves of the control unit in a position such that the hydraulic supply lines of the actuators from the driving unit according to a reverser mode are cut off. | 03-14-2013 |
| 20130067885 | FAN CASE THRUST REVERSER - A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis, a thrust reverser cascade section downstream of the blade containment section and a Fan Exit Guide Vane section downstream of the thrust reverser cascade section. | 03-21-2013 |
| 20130091825 | TURBOJET ENGINE NACELLE INCLUDING A DEVICE FOR ABSORBING CIRCUMFERENTIAL STRESSES - A nacelle for a turbojet engine of an aircraft is provided that includes a fan case, an internal structure positioned upstream from the fan case, and a thrust reverser positioned downstream from the fan case. The thrust reverser includes a cowl delimiting an external line (LE) and including two removable half cowls. A device for absorbing circumferential stresses are shaped so as to lock the half cowls in the closed position when it occupies a locking configuration on the one hand and for allowing the opening of the half cowls when it occupies an unlocking configuration on the other hand. The stress absorbing device is positioned under an upstream portion of a pylon and is exclusively attached to the half cowls in order to allow the opening of the two half cowls independently of the opening/closing of an external fan cowl. | 04-18-2013 |
| 20130097998 | THRUST REVERSER FOR AN AIRCRAFT HAVING SEMI-RECESSED TURBOFAN ENGINES - A jet propulsion unit of an aircraft, which comprises a turbofan engine ( | 04-25-2013 |
| 20130145743 | CASE ASSEMBLY WITH FUEL DRIVEN ACTUATION SYSTEMS - A thrust reverser actuation system (TRAS) for a case assembly of an aircraft is provided. The TRAS includes a fuel-driven motor; one or more actuators coupled to the fuel-driven motor; and a transcowl coupled to the actuators such that the fuel-driven drives the transcowl during operation. | 06-13-2013 |
| 20130205753 | Aircraft gas turbine thrust-reversing device - An aircraft gas turbine thrust-reversing device has an engine cowling, the rear area of which is displaceable in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular space to a front and stationary area of the engine cowling. The rear area of the engine cowling is coupled to deflecting elements and blocker doors, which in the forward thrust position are arranged completely inside the front area of the engine cowling. A drive element is provided between the front area and the rear area, which effects the axial displacement of the rear area. The drive element is a two-stage drive element, effecting in a first stage an axial displacement by an axial partial displacement path, and in a second stage an axial displacement by the full axial displacement path. | 08-15-2013 |
| 20130219857 | BYPASS DUCT WITH ANGLED DRAG LINKS - A gas turbine engine includes an engine core outer casing and a fan nacelle spaced radially outwardly relative to the engine core outer casing to define a bypass duct. A plurality of drag links is used to pivot blocker doors into a flow blocking position in the bypass duct when a thrust reverser is deployed. The plurality of drag links is located within the bypass duct in an area of non-uniform flow defined by a plurality of local airflow angles. Each drag link is individually configured to align with one of the local flow angles. | 08-29-2013 |
| 20130255225 | GAS TURBINE ENGINE THRUST REVERSER SYSTEM - A gas turbine engine thrust reverser system includes a fan nacelle having a fixed portion and a movable portion configured to move relative to the fixed portion between opened and closed positions in response to a command to selectively provide an opening between the fixed and movable portions. A fan case is arranged within the fan nacelle. The fan case includes an integral bull nose adjacent to the opening in the open position and to the movable portion in the closed position. The bull nose has a curved wall sloping radially outward. | 10-03-2013 |
| 20130298524 | DEVICE FOR LINKING A FRONT FRAME TO A FAN CASING - The present disclosure relates to a device for linking a front frame of a thrust reverser to a fan casing, which includes a linking flange capable of engaging with a receiving part secured to the casing and an annular receiving part secured to the front frame. The linking flange is made up of two flange sectors, movably mounted around an axis, pivoting between an engaged position and an open position. In the engaged position, the flange engages with the annular receiving part of the fan casing and the annular receiving part of the front frame so as to connect them. In the open position, the flange is radially separated from the annular receiving part of the fan casing and the annular receiving part of the front frame. | 11-14-2013 |
| 20130312387 | VARIABLE AREA FAN NOZZLE ACTUATION SYSTEM - An aircraft nacelle having a fixed structure fixed relative to an aircraft pylon, a translating thrust reverser sleeve translatable aftward, relative to the fixed structure, and a translating variable area fan nozzle (VAFN) panel translatable aftward, relative to the translating thrust reverser sleeve. The nacelle may also include a VAFN actuator mounted on the translating thrust reverser sleeve and a VAFN drive unit attached to the fixed structure. The VAFN drive unit may be coupled to drive the VAFN actuator via first and second coupling components when the translating thrust reverser sleeve is stowed. When the translating thrust reverser sleeve is deployed, the first and second coupling components may decouple, disconnecting the VAFN drive unit from the VAFN actuator. | 11-28-2013 |
| 20130318945 | AVIATION GAS TURBINE THRUST REVERSING DEVICE - The present invention relates to an aircraft gas turbine thrust-reversing device with an engine having an engine cowling, the rear area of which can be displaced in the axial direction of the engine from a closed forward thrust position into a rearwardly displaced thrust reversal position, resulting in an essentially annular free space towards a forward stationary area of the engine cowling, with the rear area of the engine cowling being functionally coupled to deflecting elements arranged in the forward thrust position within the front area of the engine cowling, with the deflecting elements during displacement of the rear area of the engine cowling being moveable on a partial-circular path facing the central axis of the engine and contactable by their rear end areas with a cowling of the core engine. | 12-05-2013 |
| 20130327014 | Devices and Methods to Optimize Aircraft Power Plant and Aircraft Operations - Several improvements to optimize aircraft power plant and aircraft operations are disclosed, as well as methods of using these improvements to reduce fuel consumption, gas emission, noise, aircraft weight, maintenance costs, operating costs, aircraft incident and accidents, and improving aircraft performance. The improvements consist of a power plant fitted with a front propulsor, core engine, and aft propulsor. The fan of each propulsor is separated mechanically from the core engine. The front fan is separated mechanically from the aft fan. The aft fan is driven by free turbine that is supplied by exhaust gas of the core engine. If the core engine fails, both propulsors operate and provide thrust and reversed thrust when needed. If one propulsor fails, the other propulsor of the same power plant operates and provides thrust and reversed thrust. | 12-12-2013 |
| 20140000237 | THRUST REVERSER MAINTENANCE ACTUATION SYSTEM | 01-02-2014 |
| 20140000238 | LOCKING/UNLOCKING DEVICE FOR A THURST REVERSER WITH A SLIDING COVER AND ADAPTIVE NOZZLE FOR AIRCRAFT ENGINE NACELLE | 01-02-2014 |
| 20140053533 | REVERSE FLOW GAS TURBINE ENGINE WITH THRUST REVERSER - A gas turbine engine has an outer housing defining an exit nozzle at a downstream end of the engine. A fan is mounted at an upstream end of the engine, and rotates on a first axis. The nozzle is centered on the first axis. A core engine includes a compressor section, a combustor and a turbine section. The turbine section is closest to the fan, the combustor section and then the compressor section and positioned further away from the fan relative to the turbine section. A downstream end of the nozzle has at least one pivoting shell and an actuator to pivot the at least one shell between an in-flight position and a deployed position in which the at least one shell inhibits a flow cross-sectional area of said nozzle to provide a thrust reverser. | 02-27-2014 |
| 20140116024 | LOCK FOR A TRANSLATING SLEEVE OF A NACELLE - A locking system for a cascade thrust reverser on a bypass turbofan is disclosed. The locking system includes a translating sleeve configured to move between a stowed position and a deployed position. A lock member is mounted to a beam and has a locking portion which contacts a roller on the translating sleeve to retract the locking portion when the translating sleeve moves to the stowed position. | 05-01-2014 |
| 20140116025 | AEROENGINE THRUST REVERSER ARRANGEMENT - A blocker door for a gas turbine engine thrust reverser having a tray with a base and sidewalk extending about the base to define a volume, the volume being dosed by a cover that extends beyond the periphery of the tray. The extension of the cover beyond the periphery provides a sealing feature. | 05-01-2014 |
| 20140116026 | AEROENGINE THRUST REVERSER ARRANGEMENT - A gas turbine engine has a core engine and a nacelle having a cowl translatable along the axis of the engine from a stowed position to a deployed position, A thrust reverser cascade extends circumferentially about the engine axis. To obviate the need for additional blanking cascades the cowl has a forwardly extending tongue that in the deployed position of the cowl is at the same axial position as the thrust reverser cascade. | 05-01-2014 |
| 20140137540 | ENGINE AND THRUST REVERSER ACTUATION SYSTEM - A thrust reverser actuation system for a jet engine having a turbine engine surrounded by a nacelle to define an annular air flow path between the turbine engine and the nacelle, with a thrust reverser having a movable element to reverse the direction of at least a portion of the air flow along the air flow path, where the thrust reverser actuation system includes a hydraulic actuator configured to be operably coupled to the movable element, and a remote actuator that controls the inhibit function of the hydraulic system. | 05-22-2014 |
| 20140137541 | AIRCRAFT PROPULSION UNIT INCLUDING AT LEAST ONE TURBOJET ENGINE AND A NACELLE - The present disclosure relates to a nacelle for a dual-flow turbojet engine includes a cold airstream having a non-constant cross-section over the periphery of the nacelle, such that at least one flap is radially offset with respect to the central axis of the turbojet engine, relative to the adjacent flaps. The system for driving the radially offset flaps is suitable for ensuring that the kinematics of the flaps are offset relative to the kinematics of the flaps mounted along the remainder of the periphery of the airstream. | 05-22-2014 |
| 20140150404 | THRUST REVERSER DEVICE FOR COMPACT JET PIPE - A bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings. A thrust reverser device is housed in the nacelle and includes flow reverser flaps and cascades of vanes providing radial guidance for the flow. The cascades of vanes providing radial guidance for the flow can move in translation along the axis of the nacelle between a retracted position into the first steamlining element and an active flow-guidance position, the second streamlining element being secured to the cascades of vanes, the reverser flaps being mounted to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes. | 06-05-2014 |
| 20140216005 | Gas Turbine Engine Assembly Including A Thrust Reverser - An exemplary gas turbine engine assembly includes a thrust reverser that is selectively moveable between a stowed position and a thrust reversing position. The thrust reverser includes an outer surface having a first outer surface area when the thrust reverser is in the stowed position and a second, smaller outer surface area when the thrust reverser is in the thrust reversing position. | 08-07-2014 |
| 20140245716 | TWIN-DOOR THRUST REVERSER - A thrust reverser for a turbojet aircraft engine nacelle includes a pair of twin doors including an upstream door and a downstream door which is connected to the upstream door by a connecting rod. The thrust reverse also includes an actuating cylinder for operating the upstream door between a direct jet position in which the two doors are closed and a reversed jet position in which the two doors are open and deflects a portion of a cold air stream flowing inside the nacelle. A locking system of the thrust reverser locks the upstream and downstream doors relative to one another by the operation of the actuating cylinder alone. | 09-04-2014 |
| 20140250863 | REAR MOUNTED REVERSE CORE ENGINE THRUST REVERSER - In one embodiment, a gas turbine engine for mounting to a rear of an aircraft fuselage has a propulsor that rotates on a first axis, and an engine core including a compressor section, a combustor section, and a turbine section, with the turbine section being closer to the propulsor than the compressor section. The engine core is aerodynamically connected to the propulsor and has a second axis. A nacelle is positioned around the propulsor and engine core. The nacelle is attached to the wing of the aircraft. A downstream end of the nacelle has at least one pivoting door with an actuation mechanism to pivot the door between a stowed position and a vertical deployed position in which the door inhibits a flow to provide a thrust reverse of the flow. | 09-11-2014 |
| 20140325957 | SYSTEM AND APPARATUS FOR A SPLIT CASCADE - A split cascade comprises a fixed portion and a translating portion. The translating portion may be coupled to, mounted on, or otherwise attached to a translating sleeve of an aircraft nacelle. The fixed portion and the translating portion form a cascade assembly, in response to the translating sleeve being in the active position (e.g., when the thrust reverser is active). Moreover, the split cascade provides a smaller overall package when stowed (e.g., when the translating sleeve is in a forward position and seals or joins the nacelle), providing more room in the nacelle for access and equipment. | 11-06-2014 |
| 20140360158 | TWIN-DOOR THRUST REVERSER - A thrust reverser for aircraft turbojet engine nacelle includes at least one upstream door and a downstream door. The upstream and downstream doors move in concert between a direct jet position and a reverse jet position. In the direct jet position, two doors are closed, and in the reverse jet position the two doors are open and able to deflect a part of a cold air flow circulating inside the nacelle. The thrust reverser further includes a curved downstream edge of the upstream door to make adapted a part of cold air flow circulating between an upper camber of the upstream door and a lower camber of the downstream door. | 12-11-2014 |
| 20140373506 | REVERSE SCISSOR THRIST REVERSER FOR A TURBINE ENGINE - A turbine engine system includes a nacelle and a thrust reverser. The nacelle includes a first portion and a second portion that are arranged along an axis. The second portion of the nacelle moves axially relative to the first portion of the nacelle. The thrust reverser includes a blocker door and a linkage that links the blocker door to the first portion of the nacelle. The blocker door is located within and pivotally connected to the second portion of the nacelle. | 12-25-2014 |
| 20150068190 | THRUST REVERSER WITH A DEPLOYMENT-CONTROLLED BLOCKING FLAP - A thrust reverser device for a turbojet engine nacelle includes a mobile cowl movably mounted to translate between a closed position which the mobile cowl covers grids deflecting some of the air flow of the turbojet engine and an open position in which it opens a passage and uncovers the grids. The mobile cowl is associated with a blocking flap to pivot between a retracted position and a blocking position corresponding to the open position of the mobile cowl. The blocking flap is fitted with at least one lever forming a drive mechanism which includes at least one adjustable-stiffness shock absorber. | 03-12-2015 |
| 20150107220 | VARIABLE AREA FAN NOZZLE SYSTEMS WITH IMPROVED DRIVE COUPLINGS - A VAFN system is provided for a fan case of an engine. The system includes a motor; a gearbox; an actuator; a nozzle; and a drive coupling extending between the gearbox and the actuator and configured to transmit the mechanical torque from the motor to the actuator. The drive coupling includes an external tube extending from a first one of the gearbox or the actuator, the external tube defining first and second slots extending in a longitudinal direction, and an internal tube extending from a second one of the gearbox or the actuator and at least partially extending within the external tube, the internal tube including a pin with first and second ends respectively positioned within the first and second slots such that the internal tube is configured to translate within the external tube and to be rotatably coupled to the external tube. | 04-23-2015 |
| 20150107221 | THRUST REVERSER FAN RAMP WITH BLOCKER DOOR POCKET - 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 first blocker door pocket. 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 first blocker door pocket is operable to receive at least a portion of a forward edge of a first blocker door included in the nacelle. | 04-23-2015 |
| 20150107222 | THRUST REVERSER FAN RAMP PARTIALLY FORMED ON AFT END OF FAN CASE - A fan ramp aerodynamically guides bypass duct air from the aft end of the fan case to the forward end of the cascades. To improve packaging of the thrust reverser assembly, the fan ramp begins on the interior of the fan case n continues onto the structure surrounding the cascade. | 04-23-2015 |
| 20150113944 | THRUST REVERSER DOORS HAVING SIDE OPENINGS - A door for a door-type thrust reverser is able to move between a direct jet mode of a nacelle and a reverse jet mode. The door includes an inner wall being integrated into a flow path of an air flow generated by a turbojet engine, an outer wall, at least one side wall connecting the inner wall to the outer wall of the door, and a deflector to deflect the air flow. In particular, the deflector includes a cavity of the door which is shaped to convey a fraction of the air flow from one air inlet rigidly secured to the inner wall of the door to one air outlet rigidly secured to the side wall of the door, so as to redirect, during operation of the nacelle in the reverse jet mode, a part of the air flow upstream from the inner wall of the door. | 04-30-2015 |
| 20150113945 | Pivoting Blocker Door - A gas turbine engine that has a fan case radially surrounding a fan hub, and plural fan exit guide vanes rotatably connected between the fan hub and the fan case. The fan section also has a thrust reverser opening within the case, axially upstream of the guide vanes. The gas turbine engine also has a core case containing a core engine. | 04-30-2015 |
| 20150143795 | AIRCRAFT PROPULSION SYSTEM FAN CASE COMPRISING THRUST REVERSING ASSEMBLY - An aircraft propulsion system may include a generally annular fan case defined by a fan configured to be disposed at a forward end thereof and a stator blade array configured to be disposed at an of end thereof, a thrust reversing assembly comprising at least a portion of the fan case, the fan case comprising a generally annular cascade array, and/or a sleeve situated at least partially about the cascade array, the sleeve configured to deploy to expose the cascade array. The aircraft propulsion system may further comprise a blocker door coupled to at least one of the cascade array and an inner surface of the fan case, the blocker door configured to deploy to redirect airflow through the cascade array. | 05-28-2015 |
| 20150143796 | SYSTEM AND METHOD FOR CAPTURED INNER FIXED STRUCTURE - A propulsion system of an aircraft includes an inner fixed structure (IFS) and the outer sleeve that may be separately coupled to the pylon. For instance, the inner fixed structure and the outer sleeve may move independently with respect to each other. A single latch of the latching system disclosed herein, may be configured to latch all 4 panels, (e.g. both halves of the IFS and both doors of the outer sleeve) together and/or in a closed and retained position. | 05-28-2015 |
| 20150292436 | LOCKING/UNLOCKING DEVICE FOR A ONE-PIECE COWL OF A THRUST REVERSER OF A TURBOJET ENGINE NACELLE - An assembly for a turbojet engine includes a pylon, a nacelle supported by the pylon, and a locking device interposed between the pylon and a cowl of the nacelle. The cowl slides between operating and maintenance positions. The locking device is movable between active and inhibited positions, and the device allows an operation mode in the active position and a maintenance mode in the inhibited position. In particular, the locking device comprises a rocker to maintain the cowl to the pylon, and the rocker includes an inhibiting lever and an activation lever. The inhibiting and activation levers are mounted on a switching shaft of the locking device. The inhibiting lever is set in rotation through an actuator, providing direct access from a bypass flow duct in the active position while the activation lever is set in rotation from the bypass duct in the inhibited position. | 10-15-2015 |
| 20150300294 | ROTARY HYDRAULIC MOTOR DRIVEN HYBRID THRUST REVERSER ACTUATION SYSTEM WITH END-OF-STROKE SNUBBING - An aircraft thrust reverser actuation system includes a plurality of actuator assemblies that are each configured, upon receipt of a drive torque, to move to a position. The rotary hydraulic motor is coupled to each of the actuator assemblies and is configured, upon receipt of hydraulic fluid, to rotate and supply the drive torque to each of the actuator assemblies. The control valve is in fluid communication with the rotary hydraulic motor and is configured, upon receipt of electrical current, to move to a valve position based on the magnitude of the received electrical current, to thereby control the direction and flow of hydraulic fluid to the hydraulic motor. The valve control is configured, upon receipt of thrust reverser commands, to supply the electrical current to the control valve and selectively vary the magnitude of the electrical current based on the positions of the actuator assemblies. | 10-22-2015 |
| 20150308379 | INTEGRAL CASCADE-VARIABLE AREA FAN NOZZLE SYSTEM AND METHOD - A cascade-variable area fan nozzle system (the “CVAFN System”) is provided. The CVAFN system may comprise a cascade portion and a variable area fan nozzle (“VAFN”) portion. The VAFN portion may include a VAFN panel. The cascade and VAFN panel may be integrally formed with one another. The CVAFN system may include an actuation system (e.g., a jack screw) that is configured to translate the cascade and VAFN panel forward and aft. The cascade and VAFN panel may be translated aft in response to activation of the thrust reverser and/or CVAFN system. | 10-29-2015 |
| 20150308380 | SYSTEM AND APPARATUS FOR A THRUST REVERSER - A thrust reverser system includes a translating cascade, a blocker door, and a drive link. The drive link may be pivotably coupled to the translating cascade and the blocker door. The translating cascade may be coupled to a translating sleeve of a nacelle. The drive link may cause the blocker door to deploy in response to the translating cascade moving in an aft direction. The blocker door may be pivotably coupled to a fixed aft portion of the nacelle. | 10-29-2015 |
| 20150308381 | DRAG LINK ASSEMBLY INCLUDING BURIED DRAG LINK FITTING - A drag link assembly for use in a thrust reverser of a propulsion system is provided. The thrust reverser includes a fixed structure and a translating structure that at least partially define an annular airstream bypass duct there between. The translating structure is moveable relative to the fixed structure. The translating structure includes a blocker door disposed at least partially within the airstream bypass duct. The drag link assembly includes a drag link fitting and a drag link. The drag link fitting is fastened to the fixed structure of the thrust reverser. The drag link includes a first end portion and an opposing second end portion. The first end portion is pivotably connected to the blocker door. The second end portion is pivotably connected to the drag link fitting. The second end portion includes a curved section. | 10-29-2015 |
| 20150308382 | TRANSLATING SLEEVE ACTUATION SYSTEM AND APPARATUS - A translating sleeve actuation system is provided. The translating sleeve actuation system may be configured with one or more screws coupled to one or more motors configured to drive the screws. The screws may be disposed in channels defined in the track beams. The translating sleeve actuation system may also comprise one or more shuttles configured to translate forward and aft along the screw in the track beam channels. | 10-29-2015 |
| 20150354500 | ACTUATOR FOR AIRCRAFT ENGINE NACELLE - The present disclosure provides an actuator for an aircraft turbojet engine nacelle, which is interposed between a stationary front part of the nacelle and a moveable rear part of the nacelle. The actuator includes a main actuating arm, and a secondary actuating arm which axially extends from a rear section suitable for being connected on the moveable rear part of the nacelle, to a front section secured to a main nut screwed on a worm drive, in particular, the secondary actuating arm being designed for overcoming a breakdown of the main actuating arm. | 12-10-2015 |
| 20150369171 | VENTILATION SYSTEM USING THRUST REVERSER LINKAGES - A gas turbine engine includes a fan duct, an inner fixed structure, and a thrust reverser assembly. The inner fixed structure forms an inner diameter of the fan duct and encloses a core compartment. The thrust reverser assembly includes a linkage assembly mounted to the inner fixed structure within the fan duct. The linkage assembly is adapted to act as a ventilation system that allows for communication between the fan duct and the core compartment. | 12-24-2015 |
| 20160040626 | TWIN TARGET THRUST REVERSER MODULE - A nozzle assembly for a dual gas turbine engine propulsion system includes a housing mountable proximate to a first bypass passage of a first gas turbine engine and a second bypass passage of a second gas turbine engine, first and second upper doors, and first and second lower doors. Each of the first and second upper doors and the first and second lower doors are pivotally mounted to the housing for movement between a stowed position and a deployed position in which airflow through the first and second bypass passages is redirected relative to respective centerline axes of the first and second gas turbine engines. | 02-11-2016 |
| 20180023509 | THRUST REVERSER STRUCTURE MOUNTED TO FAN CASE | 01-25-2018 |
