Matches 1 - 50 out of 105 1 2 3 >


Match Document Document Title
US20130248657 DEPLOYABLE INLET SCOOP FOR AN INBOARD RAM AIR TURBINE  
An aircraft includes a fuselage that has an exterior contour with an opening and a duct that is arranged interiorly of the exterior contour and extends from the opening. A ram air turbine is...
US20130087663 SELF-ALIGNING INLET PLENUM SYSTEM FOR ROTORCRAFT  
An inlet system for a rotorcraft includes a cowl door assembly and a plenum assembly. The cowl door assembly includes a door member, a cowl inlet opening, and a cowl inlet duct. The plenum...
US20150122952 GAS TURBINE ENGINE INLET WALL DESIGN  
A gas turbine engine has an inlet duct formed to have a shape with a first ellipse in one half and a second ellipse in a second half. The second half has an upstream most end which is smaller than...
US20110001019 RAM DOOR ASSEMBLIES  
A ram door assembly is provided for an intake opening of an intake duct of an auxiliary power unit of an aircraft. The ram door assembly includes a ram door hingeably mounted adjacent to the...
US20120261521 NACELLE INCORPORATING AN ELEMENT FOR CONNECTING A LIP AND AN ACOUSTIC ATTENUATION PANEL TOGETHER  
An aircraft nacelle includes a first subassembly consisting of a pipe (112) channeling an airflow in the direction of an engine having a covering or panel (118) for acoustic treatment, including,...
US20110108676 AIR INLET FOR AN AIRCRAFT TURBINE ENGINE, AN AIRCRAFT PROVIDED WITH SUCH AN AIR INLET, AND A METHOD OF OPTIMIZING THE OPERATION OF AN AIRCRAFT TURBINE ENGINE WITH THE HELP OF AN AIR INLET  
The present invention relates to an air inlet (10) for a turbine engine (2) of an aircraft (1), the air inlet comprising an air delivery duct (20) defined by a side wall (21) and extended by a...
US20130001369 AUXILIARY POWER UNIT INLET  
An aircraft auxiliary power unit assembly includes an aircraft skin providing a cavity. The aircraft skin is secured to a structure in an assembled condition and provides an opening. An auxiliary...
US20130228648 AUXILIARY POWER UNIT INLET  
An aircraft auxiliary power unit assembly includes an aircraft skin that provides a cavity. It is secured to a structure in an assembled condition and it provides an opening. An auxiliary power...
US20120325978 NACELLE FLOW ASSEMBLY  
A nacelle assembly for a turbine engine has a cowl for a turbine engine. The cowl has a first surface spaced from a second surface. The second surface defines defining a bypass flow passage. A...
US20130313371 ENGINE INLET  
An inlet duct for an engine or multiple engines includes two or more joining duct legs and a pressure relief pathway located at each duct leg to condition inlet airflow from the duct legs. A...
US20100327120 AIR OUTLET SYSTEM FOR AIRCRAFT LEADING EDGE  
An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges...
US20130168502 AIRCRAFT AIR INLET DIVERTER ASSEMBLIES WITH IMPROVED AERODYNAMIC CHARACTERISTICS  
Diverter assemblies for aircraft air inlets include a diverter structure at least substantially surrounding the air inlet, and a fairing mounted to an upper edge of the diverter structure...
US20130306788 UNMANNED AIR SYSTEM (UAS)  
An unmanned air system and method with blown flaps are presented. Air is guided to a fuel cell carried by the unmanned air system. The fuel cell is ventilated by the guided air such that the air...
US20140158833 AIR INLET COMBINING A FILTER AND A BYPASS DEVICE FOR USE WITH A TURBINE ENGINE  
An air inlet (10) for an engine (20) of an aircraft (50), the air inlet (10) having a duct (2) feeding outside air to said engine (20) together with a filter system combining at least one filter...
US20110139940 WAVE ATTENUATION PANEL INSERTED BETWEEN THE MOTOR AND AIR INLET OF AN AIRCRAFT NACELLE  
An aircraft nacelle includes an air intake for channeling air flow in the direction of a power plant. The air intake includes an inside pipe that forms an aerodynamic surface in contact with the...
US20140224940 PROPULSION SYSTEM USING LARGE SCALE VORTEX GENERATORS FOR FLOW REDISTRIBUTION AND SUPERSONIC AIRCRAFT EQUIPPED WITH THE PROPULSION SYSTEM  
A propulsion system for a supersonic aircraft includes an engine, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the...
US20130087661 PROPULSIVE UNIT FOR AN AIRCRAFT  
This invention relates to a propulsive unit for an aircraft, comprising: a nacelle which defines a duct for channeling an airflow when in use and which provides an outwardly facing surface of the...
US20110073716 Ram Air Duct Flap Arrangement And Ram Air Duct  
A ram air duct flap arrangement (22) comprises at least one ram air duct flap (24, 26) which is designed to close, in a closed position, a ram air inlet (14) or a ram air outlet (18) of a ram air...
US20120292455 AUXILIARY POWER UNIT INLET DUCT SCREEN ASSEMBLY  
An example inlet duct screen assembly includes a grid portion having a plurality of apertures and a frame portion circumscribing the grid portion. The grid portion and the frame portion are formed...
US20140008497 APPARTUS AND METHOD FOR PREVENTING GAS TURBINE ENGINE FREEZING  
A system for reducing moisture in a gas turbine engine with one or more air ducts includes one or more one or more covers, each with an outer face and an inner face, with the inner face...
US20080315042 THRUST GENERATOR FOR A PROPULSION SYSTEM  
A thrust generator is provided. The thrust generator includes an air inlet configured to introduce air within the thrust generator and a plenum configured to receive exhaust gas from a gas...
US20110147534 MEASUREMENT INSTRUMENT SUPPORT INTERPOSED BETWEEN A DRIVE UNIT AND AN AIR INTAKE OF AN AIRCRAFT NACELLE  
An aircraft nacelle includes an air intake (40) that makes it possible to channel a stream of air (42) in the direction of a power plant (44), whereby the air intake (40) includes an inside pipe...
US20090314899 STRUCTURAL ELEMENT OF AN AIRCRAFT  
A rear frame of an air intake of a nacelle of an aircraft, is made in part of composite material that is based on a fiber-reinforced geopolymer resin and includes at least one part (56) that...
US20150122954 VARIABLE GEOMETRY HELICOPTER ENGINE INLET  
A variable area engine inlet of a helicopter is provided and includes first inlet portions disposed to face one another in opposite directions and at a distance from one another and second inlet...
US20120091286 ISENTROPIC COMPRESSION INLET FOR SUPERSONIC AIRCRAFT  
A supersonic inlet employs relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet...
US20080179448 ACOUSTIC NACELLE INLET LIP HAVING COMPOSITE CONSTRUCTION AND AN INTEGRAL ELECTRIC ICE PROTECTION HEATER DISPOSED THEREIN  
An engine nacelle inlet lip includes both acoustic treatment and electric heating for ice protection. The inlet lip has a composite outer skin and a composite inner skin, with the composite outer...
US20060076456 Thrust/airflow control device  
A device used in a ducted fan (shrouded propeller or similar axial flow, air moving producer) that's positioned on or about the ducted fan so as to disrupt or distort the subsequent laminar...
US20110277483 GAS TURBINE ENGINE WITH EJECTOR  
The present inventions include a boundary layer ejector fluidically connecting boundary layer bleed slots from an external surface of an aircraft to reduce aircraft/nacelle/pylon drag, reduce jet...
US20110114796 DEVICE FOR SHROUDING AN AIRCRAFT NACELLE  
An aircraft nacelle includes an air intake (12) followed at the upper part by a part (14) integral with the mast, called a cap, and at least one door (16) with a curved profile, and a device for...
US20100320316 AIR INTAKE FOR AIRCRAFT NACELLE, AND PROPULSION ASSEMBLY INCLUDING SUCH AIR INTAKE  
The invention relates to an air intake for an aircraft nacelle that comprises a shroud (19) that can be mounted on the fan casing (15) of a turbojet engine (1). The shroud (19) is sized so as to...
US20090140104 TURBOJET NACELLE AND METHOD FOR CONTROLLING SEPARATION IN A TURBOJET NACELLE  
An aircraft turbojet nacelle comprising blowing means intended to inject a tangential airflow (Ft) into the internal volume (V) of the nacelle, said blowing means being provided in a wall of the...
US20080308684 NACELLE WITH ARTICULATING LEADING EDGE SLATES  
A nacelle includes leading edge slates movable to modify inlet shape and area airflow into the nacelle. The articulating leading edge slats are movable for tailoring incoming airflow to current...
US20100314501 LOCKING SYSTEM FOR AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE  
The invention relates to a nacelle for a turbojet engine that includes an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and a middle structure for...
US20130075539 COMPOSITE AEROSPACE STRUCTURE WITH INTEGRATED CONVEYANCE ELEMENT  
A composite structure for aerospace applications includes a structural member having multiple composite layers providing a longitudinally extending cavity. A conveyance element is arranged between...
US20090321585 NACELLE INLET LIP  
A nacelle inlet lip has a simplified geometry. The nacelle inlet lip has a constant cross-section all along a circumference thereof and is wholly concentric relative to the engine centerline,...
US20100148012 AIRCRAFT ENGINE NACELLE WITH TRANSLATING INLET COWL  
A nacelle for a turbofan aircraft engine having a fan case with a fan case forward edge includes an inlet inner barrel having an inner barrel forward edge and an inner barrel aft edge. The inner...
US20100084507 REMOVABLE AIR INTAKE STRUCTURE FOR TURBOJET ENGINE NACELLE  
The present invention relates to a nacelle (1) for a turbojet engine comprising an air intake structure (4) capable of ducting a flow of air towards a fan and a central structure (5) intended to...
US20110163207 AIRPLANE HAVING ENGINES PARTIALLY ENCASED IN THE FUSELAGE  
An airplane provided with dual-flow turbojet engines having nacelles at least partially encased in the fuselage, wherein the air intake of each engine is connected to the fuselage by two boundary...
US20120280090 CONNECTING DEVICE PARTICULARLY ADAPTED FOR THE CONNECTION BETWEEN AN AIR INTAKE AND AN ENGINE OF AN AIRCRAFT NACELLE  
A connecting device between two cylindrical parts that are connected at a junction plane, more particularly suited for connecting an air intake and a power plant of an aircraft nacelle,...
US20070176052 AIR INLET FOR A TURBOFAN ENGINE  
The present invention relates to an air inlet for a nacelle of a jet engine with a front fan, comprising an upper part (115S), a lower part (115I), an inner lateral part (115int) and an outer...
US20110265650 ENGINE AIR PARTICLE SEPARATOR  
A filtration system for a gas turbine engine includes an inlet main body which defines an inner inlet fairing section and a bellmouth inlet faring section transverse thereto. An Engine Air...
US20090194633 ICING PROTECTION FOR AIRCRAFT AIR INLET SCOOPS  
Aircraft air scoop icing protection systems and methods include an air duct having air inlet and outlet openings and a fairing which covers the air duct and defines an interior fairing space in...
US20070221790 Ducted Fan Air Data System  
An air data system and method for a ducted fan air-vehicle is described. The air data system includes a plurality of air pressure sensors placed around a lip of an air duct of the ducted fan...
US20070125906 Ram air channel for the supply of ambient air in an aircraft  
A ram air channel (10) for the supply of ambient air in an aircraft includes a first air inlet (12) and a main flow channel (16) which extends downstream of the first air inlet (12). In order to...
US20110215204 SYSTEM AND METHOD FOR GENERATING THRUST  
A thrust generator includes an air inlet configured to introduce air within the thrust generator and a plenum having a plurality of fluid injection devices. The plenum is configured to receive an...
US20100059634 LOCKING SYSTEM FOR A MOVABLE NACELLE COWL  
The present invention relates to a locking system (20) for a movable lateral cowl (8) of a turbine engine nacelle intended to be connected to a pylon (4) of an aircraft, comprising, on the one...
US20080173768 Power plant for a rotary wing aircraft  
The present invention relates to a power plant (18) comprising at least one turboshaft engine (8) behind a gearbox (7) for driving a rotor (3) of a rotary wing aircraft (1), the air inlet body...
US20110168852 METHOD OF DEPOSITING A COATING FOR IMPROVING LAMINAR FLOW  
A process for deposition of a coating whose purpose is to improve the laminar flows at a junction between a first panel (36) of a leading edge and a second panel (34) of an adjacent surface...
US20080164378 Boundary-Layer-Ingesting Inlet Flow Control System  
A system for reducing distortion at the aerodynamic interface plane of a boundary-layer-ingesting inlet using a combination of active and passive flow control devices is disclosed. Active flow...
US20110253843 Air Intake Arrangement For An Aircraft  
The invention relates to an arrangement (1) that comprises a mobile plate (18) controlled by a means for fluid communication (23) between the outer (18A) and inner surfaces of the mobile plate...

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