Patent application number | Description | Published |
20090126151 | SYSTEM FOR ADJUSTMENT OF THRUST REVERSER PIVOT DOOR - A system that allows for quick and easy adjustment of the position of a thrust reverser pivot door comprises an actuator rod end bolt and a pair of pivot door hinge pins, all of which have an eccentric element. The actuator rod end bolt includes a cylindrical portion along the center of the length of the bolt that has an eccentric element which protrudes beyond the outer surface of the cylinder. Each pivot door hinge pin includes a cylindrical portion along the center of the length of the pin that has an eccentric element which protrudes beyond the outer surface of the cylinder. Rotation of either the actuator rod end bolt or the pivot door hinge pins or both the actuator rod end bolt and the pivot door hinge pins adjusts the position of the pivot door. | 05-21-2009 |
20090127806 | LOW-LEAKAGE SEAL SYSTEM FOR PIVOT DOOR TYPE THRUST REVERSER - A low-leakage seal system for a pivot door type thrust reverser comprises a forward seal, an aft seal, and a pair of seal stops. The forward seal is attached to a forward portion of a thrust reverser. The aft seal is attached to an aft portion of the pivot door. The seal stops are attached to opposing sides of the pivot door and each seal stop couples with a pivot door hinge pin. Each seal stop includes a forward tab and an aft tab. The forward tabs of the seal stops make flush contact with the forward seal and the aft tabs make flush contact with the aft seal such that a continuous seal is formed between the pivot door and the fixed structure of the thrust reverser when the pivot door is stowed. | 05-21-2009 |
20090152401 | NACELLE INLET THERMAL ANTI-ICING SPRAY DUCT SUPPORT SYSTEM - An anti-icing system for an aircraft engine nacelle comprises a generally ring-shaped hollow spray tube for directing hot gasses toward a portion of the nacelle; a plurality of fasteners for attaching the spray tube to a support structure of the aircraft engine; and a supply duct for delivering the hot gasses from the aircraft engine to the spray tube. The spray tube includes two closed ends which define a thermal expansion gap therebetween to accommodate thermal expansions and contractions caused by the hot gasses. Each of the fasteners comprises a support bracket for attachment to the support structure of the aircraft and a guide assembly for supporting the spray tube to the support bracket. The guide assembly includes a generally ring-shaped block for encircling the spray tube, a bushing positioned within the block for contact with a bearing sleeve of the spray tube, and a pair of bushing retainers positioned on opposite sides of the block for retaining the bushing within the block. The bushings permit the spray tube to slip relative to the fasteners to further accommodate thermal expansions and contractions. | 06-18-2009 |
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 |
20100236862 | ENGINE INLET DEEP ACOUSTIC LINER SECTION - An inlet of an aircraft nacelle having an acoustic barrel configured to reduce engine fan flutter by attenuating various frequencies. The acoustic barrel may comprise an acoustic panel of a honeycomb configuration sandwiched between a first back sheet and a face sheet and extending from a forward bulkhead to an aft bulkhead of the inlet. The acoustic barrel may further comprise a deep liner section bonded to and sandwiched between the first back sheet and a second back sheet. The deep liner section may have a narrower width than the acoustic panel and may be located proximate the aft bulkhead. The sections of the first back sheet, the face sheet, and a septum of the acoustic panel may be perforated and may contain additional holes formed in portions aligned radially inward of the deep liner section. | 09-23-2010 |
20100264676 | TERTIARY LOCK FOR PIVOT DOOR THRUST REVERSER - A locking assembly partially housed between a forward bulkhead and an aft bulkhead of an aircraft's fan duct for preventing a pivot door of a thrust reverser from inadvertently opening during flight and providing over-stow assistance during opening and closing of the pivot door. The locking assembly may comprise a lock arm configured to mate with a lock arm receiver fixed to the pivot door. The lock arm may have a first portion pivotally attached to a locking assembly housing mounted between the bulkheads, and a second portion extending aftward through an opening in the aft bulkhead. When the lock arm is pivoted away from the pivot door, the second portion may be configured to push inward against the lock arm receiver, urging the pivot door inward while simultaneously moving the lock arm away from the lock arm receiver to allow the pivot door to open outward. | 10-21-2010 |
Patent application number | Description | Published |
20130126265 | ENGINE INLET VARYING IMPEDANCE ACOUSTIC LINER SECTION - An inlet for an aircraft engine nacelle having an acoustic barrel panel, a septum buried or sandwiched within the acoustic barrel panel, and a perforated face sheet. The inlet may be located forward of an engine and/or an engine fan housed within the aircraft engine nacelle. Both the septum and the perforated face sheet may have perforations or holes therein of varying sizes and varying distances apart from each other. The smaller the area of the perforations or holes and the further apart they are from each other, the higher the impedance of a given area of the septum or the perforated face sheet. The impedance of the septum and/or the perforated face sheet may progressively increase in a direction away from the engine fan. | 05-23-2013 |
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 |
20140263837 | NACELLE INLET THERMAL ANTI-ICE SPRAY DUCT - An anti-icing system for a nacelle inlet of an aircraft engine includes a spray tube for directing hot gasses toward a portion of the nacelle inlet. The spray tube includes a plurality of sections arranged such that the ends of adjacent sections are separated by a space thereby defining a thermal expansion gap between the sections. A plurality of expansion joints interconnect adjacent ends of the spray tube sections and enclose the expansion gaps. The joints allow the spray tube to expand and contract without adversely affecting the performance or structure of the spray tube. Annular sealing elements positioned in opposed axial margins of the expansion joints provide an air-tight or nearly air-tight seal between the expansion joints and the spray tube sections. | 09-18-2014 |