Patent application number | Description | Published |
20100038475 | ICE PROTECTION SYSTEM FOR A MULTI-SEGMENT AIRCRAFT COMPONENT - An aircraft component includes a first segment having a first leading edge surface that extends to a first end of the first segment. The aircraft component also includes a second segment having a second leading edge surface that extends to a second end of the second segment. The second end is substantially adjacent to the first end of the first segment, and is connected to the first end. The first leading edge surface includes electrical resistance heating that extends to the first end of the first segment. In addition, the second leading edge surface includes electrical resistance heating that extends to the second end of the second segment. The electrical resistance heating is capable of providing ice protection heating immediately on either side of a juncture between the connected first and second ends. | 02-18-2010 |
20100109208 | 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. | 05-06-2010 |
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 |
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 |
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 |
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 |
20140064927 | 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. | 03-06-2014 |
20140234081 | 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. | 08-21-2014 |