| Rohr, Inc. Patent applications |
| Patent application number | Title | Published |
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| 20120037448 | SYSTEM AND METHOD FOR NOISE SUPPRESSION - Systems and methods for noise suppression are disclosed herein. In one embodiment, an acoustic structure has a core that includes a plurality of cells. Each of the plurality of cells includes one or more engaging structures for positioning a septum relative to the cell. The acoustic structure further includes a plurality of septums positioned relative to the plurality of cells. | 02-16-2012 |
| 20120034093 | BLADE - A rotor blade has a chord and a span length perpendicular to the chord. The rotor blade includes a first skin having an inner surface and a first plurality of elements extending from the inner surface. The first plurality of elements are distributed along at least a portion of the span length and inclined with respect to the chord of the rotor blade. A second skin is attached to the first skin so as to form an outer surface of the rotor blade. The second skin has a second plurality of elements extending towards the inner surface of the first skin and engaging with the first plurality of elements to form a plurality of ribs within the rotor blade. | 02-09-2012 |
| 20110318173 | 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 having a track channel. The slider assembly translatably engages the track assembly. The slider assembly includes a slider body configured to be received within the track channel. The slider assembly further includes a slider arm member pivotably coupled to the slider body with a hinge joint disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided. | 12-29-2011 |
| 20110308723 | Multi-Segment Tool and Method for Composite Formation - A multi-segment tool and tooling system for vacuum forming a composite part. A tool can include a first tool having first and second surfaces. A second tool can have an opening positioned on a first tool in a location other than the first surface or the second surface. The first tool and second tool can receive at least a portion of a preform composite. The first tool can have a vacuum barrier attached to the first surface and to the second surface encapsulating the preform composite and the second tool. A tooling system can include a first tool having a core and a base with a core extending upwards from the base. A second tool can be positioned upon the core where the core extends above the second tool. A vacuum barrier sealed to the base and the core can include a composite, the first tool and the second tool. | 12-22-2011 |
| 20110296813 | VARIABLE AREA FAN NOZZLE WITH BYPASS FLOW - The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag. | 12-08-2011 |
| 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 |
| 20110200786 | COMPOSITE HONEYCOMB STRUCTURE - Adjoining edges of adjacent honeycomb core panel sections are mechanically interlocked. In one embodiment, the method includes forming a first edge along a first cellular core panel section. The first edge includes a first plurality of edge cell walls along the first edge. The method further includes forming a second edge along a second cellular core panel section, wherein the second edge includes a second plurality of edge cell walls along the second edge. The first edge is positioned proximate to the second edge. At least a portion of at least one of the first plurality of edge cell walls is mechanically interlocked with at least a portion of at least one of the second plurality of edge cell walls to form a joint therebetween. The invention also includes a composite structure at least partially produced by such a method. | 08-18-2011 |
| 20110197973 | INLET SECTION OF AN AIRCRAFT ENGINE NACELLE - A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange. | 08-18-2011 |
| 20110192135 | Control System - A control system comprises a TRAS actuator | 08-11-2011 |
| 20110167606 | AIRCRAFT ENGINE INLET HAVING ZONE OF DEFORMATION - An inlet assembly for an aircraft engine nacelle includes an inner barrel, an outer barrel radially spaced from the inner barrel, and a rear support for supporting the outer barrel relative to the inner barrel. The rear support includes at least one radially extending stiffener and at least one energy absorber defining a zone of deformation adjacent the inner barrel. The rear support is deformable in the zone of deformation in response to forces applied during a fan blade-out event to prevent fracture of the rear support. | 07-14-2011 |
| 20110162910 | LINEAR ACOUSTIC LINER - A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings. | 07-07-2011 |
| 20110127370 | FAN COWL SUPPORT FOR A TURBO FAN ENGINE - A fan cowl support for an aircraft having an engine pylon, an engine fan case and an engine fan cowl. The fan cowl support includes a support having a forward end connected to the engine fan case and an aft end connected to the engine pylon with a spherical connector. At least a portion of the engine fan cowl is connected to the support. | 06-02-2011 |
| 20110127367 | FAN COWL SUPPORT FOR A TURBOFAN ENGINE - A fan cowl support for an aircraft having an engine pylon, an engine fan case and an engine fan cowl. The fan cowl support includes a support having a forward end connected to the engine fan case and an aft end connected to the engine pylon. At least a portion of the engine fan cowl is connected to the support. | 06-02-2011 |
| 20110072637 | SYSTEM FOR JOINING ACOUSTIC CELLULAR PANEL SECTIONS IN EDGE-TO-EDGE RELATION - The invention includes a joint assembly for connecting first and second longitudinal edges of portions of an acoustic barrel or panel having an open cell core, a perforated inner skin, and an outer skin. The joint assembly includes at least one strip covering a plurality of openings in walls of cells along the first and second longitudinal edges. The strip is separate from the inner and outer skins. A plate includes a first portion connected to the outer skin proximate to the first longitudinal edge, and a second portion connected to the outer skin proximate to the second longitudinal edge. | 03-31-2011 |
| 20110049292 | LIGHTNING STRIKE PROTECTION - An aircraft component having an external surface includes an improved lightning strike protection surface film disposed on or proximate to the external surface. The surface film includes a preform that includes a substrate having a first areal weight density and a plurality of spaced carbon nanotubes grown on the substrate, the nanotubes having a second areal weight density. The sum of the first areal weight density and the second areal weight density is less than about 500 grams per square meter, and the preform has a surface resistance less than about 1 ohm/square. | 03-03-2011 |
| 20110001086 | Methods of making nanoreinforced carbon fiber and components comprising nanoreinforced carbon fiber - Methods for enhancing the strength and stiffness of fibers, including nanoreinforced fibers and fiber tows, composite materials including the nanoreinforced fibers and tows, and articles of manufacture including the composite materials, are disclosed. The methods involve adhering random or aligned nanoreinforcement materials, such as carbon nanotubes, nanofibers, graphene plates, nanowires, nanoparticles, into or onto a spread carbon tow or yarn to form modified fibers wherein nanoreinforcement is adhered or trapped within the carbon tow. The carbon nanotubes or nanofibers can be aligned. Carbon fiber tows including the modified carbon fibers can be processed or woven for impregnation with a thermoset resin or thermoplastic to form a composite structure. The performance increase of the modified fibers relative to the unmodified fibers can be greater than the weight increase caused by the modification. Increased fiber stiffness and strength can result in a significant weight saving. | 01-06-2011 |
| 20100260602 | INLET SECTION OF AN AIRCRAFT ENGINE NACELLE - A nacelle inlet for an aircraft engine of a type having an engine fan case with a forward flange includes an acoustic inner barrel having a forward edge and an aft edge, an outer shell having a nose lip portion with a trailing inner edge, and an outer barrel portion having an aft portion. The nacelle inlet also includes an aft attachment flange configured to attach the inlet to the forward flange of the engine fan case, and an aft bulkhead having an aft end and connecting the outer barrel portion of the outer shell to the aft attachment flange. The forward edge of the acoustic inner barrel is connected to the trailing inner edge of the nose lip portion, and the aft portion of the inner barrel is attached to the aft attachment flange. | 10-14-2010 |
| 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 |
| 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 |
| 20100170633 | Method and Apparatus for Making a Tubular Composite Structure - A tool for making a composite tubular structure, such as the inner skin of an acoustic liner, includes a base on which are mounted a plurality of sectors, each having an outer panel provided with a predetermined shaped surface. The predetermined shaped surface corresponds to a portion of the contour of the tubular structure to be formed. At least one of the sectors is fixed relative to the base while the remaining sectors are movable in a radial direction and separable from all the other sectors. The sectors are provided with air bearings to facilitate movement along a radial direction. Splice plates are used to form a joint between the outer panels of adjacent sectors. After composite material is applied on the outer panels, a vacuum bag is formed to surround the composite material and also the joint areas on the inner surface of the tool. The entire tool may be placed in an autoclave for curing. The thus-formed composite tubular structure may be remounted on the tool for bonding to additional exterior layers. | 07-08-2010 |
| 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 |
| 20100059185 | Apparatus and Method for Making a Tubular Composite Barrel - A 360° tool for making a one-piece composite tubular structure, such as a skin of an acoustic liner, is adjustable between a molding position and a non-molding position. The tool includes a base, a fixed segment mounted to the base, first and second doors hingedly connected on either side of the fixed sector, and third door hingedly connected to the second door. The third door has a circumferential extent that is less than one-fourth that of either the first or second door. Sealing members are provided between the doors. Collectively, the fixed sector, and the first, second and third doors have a predetermined shaped surface that corresponds to a portion of the contour of the tubular structure to be formed. After composite material is applied on the outer surfaces of the fixed sector and the doors, a vacuum bag is formed to surround the composite material and also the joint areas on the inner surface of the tool. The entire tool may be placed in an autoclave for curing. The tool may also be used for the layup and bonding of an acoustic core sandwiched between pre-cured skins. | 03-11-2010 |
| 20090314887 | THRUST REVERSER CASCADE ASSEMBLY AND AFT CASCADE RING WITH FLOW DEFLECTOR PORTION - An aircraft engine thrust reverser cascade assembly includes a plurality of circumferentially spaced cascade segments, each cascade segment including a plurality of spaced vanes including an aft-most vane, and an aft end. The cascade assembly also includes an aft cascade ring removably attached to the aft ends of the cascade segments. The aft cascade ring includes a deflector portion that at least partially extends forward of the aft ends of the cascade segments. The deflector portion is configured to at least partially redirect at least a portion of a volume of air as the air outwardly passes between the aft-most vanes and the aft ends of the cascade segments. | 12-24-2009 |
| 20090236779 | Apparatus and Method for Making a Tubular Composite Barrel - A 360° tool for making a one-piece composite tubular structure, such as a skin of an acoustic liner, is adjustable between a molding position and a non-molding position. The tool includes a base, a fixed segment mounted to the base, first and second doors hingedly connected on either side of the fixed sector, and third door hingedly connected to the second door. The third door has a circumferential extent that is less than one-fourth that of either the first or second door. Sealing members are provided between the doors. Collectively, the fixed sector, and the first, second and third doors have a predetermined shaped surface that corresponds to a portion of the contour of the tubular structure to be formed. After composite material is applied on the outer surfaces of the fixed sector and the doors, a vacuum bag is formed to surround the composite material and also the joint areas on the inner surface of the tool. The entire tool may be placed in an autoclave for curing. The tool may also be used for the layup and bonding of an acoustic core sandwiched between pre-cured skins. | 09-24-2009 |
| 20090199959 | SEGMENTED MANDREL FOR HIGH TEMPERATURE BONDING OF METALLIC AXISYMMETRIC SHELLS HAVING COMPLEX CURVATURES - A tool for use in bonding a composite multi-layer shell having complex curvature by the delta-alpha high temperature bonding process. The tool includes a plurality of segments that combine to form a mandrel assembly having a substantially continuous outer surface. The outer surface has a substantially axisymmetric shape including a complex curvature. When the segments are combined to form the mandrel assembly, at least one of the segments is configured to be movable in a substantially inward direction without substantial obstruction by any other segment. The segments are constructed of a first material have a first coefficient of thermal expansion that is greater than a second coefficient of thermal expansion of a second material of a composite multi-layer shell to be bonded together using the tool. | 08-13-2009 |
| 20090199946 | TOOL AND METHOD FOR BONDING LAYERS OF A METALLIC AXISYMMETRIC STRUCTURE HAVING COMPLEX CURVATURES - A tool and method for bonding layers of a shell by the differential pressure bonding process. The tool and method includes a plurality of separable mandrel segments that combine to form a mandrel having a longitudinal axis, an outer surface, an upper end, and at least one substantially continuous inner surface. The inner surface has a substantially axisymmetric shape having complex curvature. In this embodiment, the tool further includes a retort configured to at least partially shroud the outer surface and upper end of the hollow body. The retort includes at least one vacuum port. The tool is configured to facilitate the compression of a plurality of layers of a multi-layer shell having complex curvature as the shell layers and an interdisposed bonding material are heated to an elevated bonding temperature. | 08-13-2009 |
| 20090173823 | Method and component for determining load on a latch assembly - A cowl assembly for an engine nacelle including a first and second cowl door mounted for movement between an open position and a closed position. A latch assembly retains the first and second cowl doors in the closed position by having a latch retained in a latch housing on the first cowl door to engage a keeper retained in a keeper housing on the second cowl door. A pin retains the latch to the latch housing. The pin defines an internal bore. A sensor in the internal bore determines a signal indicative of a load on the pin, wherein the signal is determinative of whether the cowl doors are in the open or closed position. A transmitter conveys the signal to a location remote from the sensor. The signal can also be used to set the pre-load on the latch assembly. | 07-09-2009 |
| 20090045009 | LINEAR ACOUSTIC LINER - A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings. | 02-19-2009 |
| 20090014598 | AIRCRAFT ENGINE NACELLE INLET HAVING ACCESS OPENING FOR ELECTRICAL ICE PROTECTION SYSTEM - An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on an outside surface. An inner barrel portion and an outer barrel portion of the nacelle inlet define a space therebetween. Ice protection-related equipment such as controllers, cables, switches, connectors, and the like, may reside in this space. One or more access openings are formed in the outer barrel to enable an operator to gain access to this equipment. The inlet cowling attaches to the inner and outer barrels with its outer lip extending sufficiently far in the aft direction to cover the access opening. When the cowling is removed, the access opening is uncovered, thereby permitting access to the equipment. | 01-15-2009 |
| 20090013664 | Actuator Arrangement - An actuator arrangement comprises an actuator having a rotatable drive input, a motor, and a drive transmission arrangement for transmitting rotary drive from the motor to the rotatable drive input of the actuator, wherein the transmission arrangement includes a telescopic drive coupling. | 01-15-2009 |
| 20090008509 | AIRCRAFT ENGINE NACELLE INLET HAVING ACCESS OPENING FOR ELECTRICAL ICE PROTECTION SYSTEM - An aircraft engine nacelle inlet is provided with an inlet cowling. The inlet cowling includes an inner lip, an outer lip, and a leading edge portion connecting the inner and outer lips. Heating elements are provided proximate the leading edge, either on an inside surface of the cowling or on an outside surface. An inner barrel portion and an outer barrel portion of the nacelle inlet define a space therebetween. Ice protection-related equipment such as controllers, cables, switches, connectors, and the like, may reside in this space. One or more access openings are formed in the outer barrel to enable an operator to gain access to this equipment. The inlet cowling attaches to the inner and outer barrels with its outer lip extending sufficiently far in the aft direction to cover the access opening. When the cowling is removed, the access opening is uncovered, thereby permitting access to the equipment. | 01-08-2009 |
