Abstract: A nacelle is configured to be coupled to an underside of a wing so as to form a clearance space therebetween. The nacelle includes at least a first cowling which at least partially defines an inlet of the nacelle and which at least partially defines an outlet of the nacelle. The first cowling can include a unitary portion that extends continuously from the inlet to the outlet. The first cowling can also include a flattened surface.

Abstract: 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.

Abstract: The present invention relates to an emergency ram air inlet valve, also designated as an ERAI valve, of an aircraft. The valve includes an actuating element for opening and/or closing the valve and a controller operatively coupled to the valve, by which the valve can be set at different open angles. The open angle is set as a function of a temperature prevailing or preset in the aircraft cabin.

Abstract: 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 dynamic inlet duct (30), said dynamic inlet duct (30) extending along a dynamic axis (AX1) towards a front flow section (31), said dynamic inlet duct (30) being provided with a grid (40) for protection against ingesting foreign bodies. The grid (40) is suitable for moving in translation along said dynamic axis (AX1) relative to said front flow section (31), and said air inlet (10) includes at least one lateral inlet (50) arranged in said side wall (21) and cover means (41) for covering said lateral inlet (50) that are movable relative to said lateral inlet (50), said air inlet (10) including movement means (60) controlled by said movement in translation of the grid (40) to request movement of said cover means (41) relative to said lateral inlet (50).

Abstract: A retractable deflector to deflect birds and debris from an air intake duct of an aircraft jet engine. The duct has a central longitudinal axis and a forward opening for air receipt. The deflector includes a plurality of elongate first support members disposed on the duct having leading ends which extend from a perimeter of the opening, mounted for movement to extend and retract the leading ends. A second support member is coupled to these leading ends to retain them in spaced relation. The second support member is extendible in length and configured to hold the leading ends of the first support members sufficiently close together to cause the first support members to deflect at least one of a bird and debris when deployed, and to allow the leading ends to maintain a spaced-apart relation along a line which approximately corresponds to the perimeter of the duct when retracted.

Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance.

Abstract: A ram air fan inlet housing for containing a ram air fan rotor. The inlet housing includes a flanged surface and an interior surface. The flanged surface is perpendicular to an axis of the inlet housing and defines a flange plane at an axial end of the inlet housing. The interior surface is symmetric about the axis of the inlet housing and includes a flange section, a transition section, an outlet section, a rotor section, and an inlet section.

Abstract: The object of the invention is an aircraft nacelle comprising a lip extended by an inner conduit forming an air intake, a front frame delimiting with said lip annular channel within which hot air circulates, and a panel for acoustic treatment comprising, from outside inwardly, an acoustic resistive layer, at least one honeycomb structure and one reflective layer as well as ducts for channeling hot air, at least one conduit with opening which opens into annular channel being provided for carrying hot air up to the panel for acoustic treatment, wherein opening is used for channeling hot air in direction which forms an angle ? of less than 60° with hot air flow direction into annular channel.

Abstract: A nacelle for a gas turbine engine has an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has, an intake lip and a diffuser. The diffuser has a main diffuser section and an optional shorter straight wall diffuser section. The main diffuser section is bounded by an inner wall of the nacelle, the inner wall curving in the airflow direction of the engine. On each longitudinal section containing the engine axis, at the downstream end of the main diffuser section the inner wall has a non zero curvature. Thus each circumferential position on the inner wall at the downstream end of the main diffuser section has a curvature defined by a respective radius of curvature. However, one or more of the radii of curvature differ from the others of the radii of curvature.

Abstract: An inlet apparatus for a gas turbine engine includes: a fan duct adapted to surround at least one row of rotating fan blades, the fan duct having a circular frontal area, and defining a first inlet plane; and an outer duct surrounding the fan duct, the outer duct including: a first frontal area shape at the first inlet plane which defines, cooperatively with an exterior of the fan duct, at least one lobe through which air can pass; and a second frontal area shape at a second inlet plane located axially downstream from the forward end which is circular, and which defines, cooperatively with an exterior of the fan duct, an annulus through which air can pass.

Abstract: An APU air intake (AI) is disclosed having a foldable intake door (101), comprising a frame (102) with airfoil profiles (103, 103a, 103b). The frame (102) is turned to an aperture angle (?) with respect to the frame support (121), and each airfoil profile (103, 103a, 103b) is turned to a profile angle (?i) with respect to the frame (102). The aperture angle (?) varies from 0° to 22°, and the profile angles (?i) vary from 0° to 110°. The frame (102) is moved by an actuator (109) and the airfoil profiles (103a, 103b) are operated by extendable rods (111) and secondary rods (118), each secondary rod (118) having rod supports (119a, 119b). A latching mechanism is assembled onto each extendable rod (111), comprising a rare earth magnet (112) and either a magnet contact plate (113) or a plate with another magnet.

Abstract: The present invention provides an air intake valve for an aircraft and a method for the production of an air intake valve. The air intake valve has an opening region for letting ambient air through into a fuselage inner region of the aircraft and a flap for opening and closing the opening region, the opening region and the flap each having a shape which is capable of forming air vortices on edges of the opening region when ambient air flows through the air intake valve.

Abstract: A nacelle assembly includes an inlet section having a plurality of discrete sections. Each of the plurality of discrete sections includes an adaptive structure. A thickness of each of the plurality of discrete sections is selectively adjustable between a first position and a second position to influence the adaptive structure of each of the plurality of discrete sections.

Abstract: An air intake arrangement includes a mobile plate controlled by at least one fluid communication passage or opening extending between the outer and inner surfaces of the mobile plate. The fluid communication passage or opening is located at least in the vicinity of a limited downstream area of the outer surface, is at a high pressure when the aircraft flies at cruising speed, and is capable of transmitting the high pressure to an extended area of the inner surface. The air flowing through the air intake arrangement may be used to refresh an enclosed area with electrical or mechanical equipment.

Abstract: The invention relates to an air inlet for a vehicle comprising an opening with an opening contour in an outer skin of the vehicle; at least one bottom element; one or several walls between the opening contour and the bottom element; and an air guide channel with a longitudinal axis, wherein the bottom element extends from the outer skin of the vehicle to an interior region of the vehicle underneath a border edge of the opening, and the air guide channel adjoins from between the bottom element and the border edge, wherein at least one transition region between the opening contour and the walls at least in some regions comprises an essentially convex-shaped profile that essentially extends parallel to the air guide channel. The air inlet according to the invention is in a position to remove air from a flow boundary layer and to provide said air to air-consuming systems.

Abstract: A supersonic inlet with a cowl lip may be configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.

Abstract: A supersonic inlet includes a relaxed isentropic compression surface to improve net propulsive force by shaping the compression surface of the inlet to defocus the resulting shocklets away from the cowl lip. Relaxed isentropic compression shaping of the inlet compression surface functions to reduce the cowl lip surface angle, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining overall engine performance.

Abstract: An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.

Abstract: An exemplary pressure influencing assembly for an aircraft auxiliary system an inlet opening to an aircraft auxiliary system and an exhaust opening from the aircraft auxiliary system. Both the inlet opening and the exhaust opening face at least partially radially away from an axis. At least some of the inlet opening is circumferentially aligned with at least some of the exhaust opening relative to the axis.

Abstract: A collapsible flow control structure for an axisymmetric inlet employs trapezoidal alternating actuated and non-actuated strips having leading edges hinged to a missile forebody and free trailing edges extending into an inlet aperture, the strips positionable to form a variable angle frustum of a cone. An interengagement mechanism secures adjacent strips and actuators are attached to an inner surface of the actuated strips for urging the strips between a collapsed, retracted position for a first angle frustrum to an extended position for a second angle frustrum for aerodynamic flow control.

Abstract: A gas turbine engine system includes nacelle, a first boundary layer control device, a second boundary layer control device, at least one sensor, and a controller. The nacelle is defined about an axis and includes an inlet lip section, an inlet internal diffuser section, and a variable area fan nozzle moveable to influence a discharge airflow area of the nacelle. The first boundary layer control device is positioned near the inlet lip section and is actuable to introduce a first airflow at the inlet lip section. The second boundary layer control device is positioned near the inlet internal diffuser section and is actuable to introduce a second airflow at the inlet internal diffuser section. The sensor produces a signal that represents an operability condition.

Abstract: A flow control device generates counter-rotating vortices in the boundary layer of the flow in a supersonic inlet diffuser for an aircraft turbine engine. The flow control device comprises a flap attached to the duct wall for selective deployment, wherein it extends into the boundary layer, and retraction, wherein it lies substantially flush with the duct wall. In one embodiment an actuating mechanism comprising one or more shape-memory alloy wires moves the flap between two stable positions. In another embodiment the deployment height of the flap can be controlled as desired, preferably using a shape-memory alloy actuating mechanism. Typically, an array of plural flow control devices is disposed in the inlet duct for selective actuation according to a predetermined schedule.

Abstract: 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 compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

Abstract: 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 compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

Abstract: A diverterless hypersonic inlet (DHI) for a high speed, air-breathing propulsion system reduces the ingested boundary layer flow, drag, and weight, and maintains a high capture area for hypersonic applications. The design enables high vehicle fineness ratios, low-observable features, and enhances ramjet operability limits. The DHI is optimized for a particular design flight Mach number. A forebody segment generates and focuses a system of multiple upstream shock waves at desired strengths and angles to facilitate required inlet and engine airflow conditions. The forebody contour diverts boundary layer flow to the inlet sides, effectively reducing the thickness of the boundary layer that is ingested by the inlet, while maintaining the capture area required by the hypersonic propulsion system. The cowl assembly is shaped to integrate with the forebody shock system and the thinned boundary layer region.

Abstract: An inlet for removal of a boundary layer from an incoming air flow of an engine is disclosed. The inlet includes at least one compression element proximate to an inlet aperture of the engine. The compression element is selectably moveable between a first position and a second position along an axis. A boundary layer removal aperture is open when the compression element is in the first position and the boundary layer removal aperture is closed when the compression element is in the second position.

Abstract: A gas turbine engine comprising a fan section, a compressor, a combustor and a turbine, includes a nacelle having an inner nacelle surface defining an inlet duct designed to reduce an inlet duct area of the inlet duct to increase acoustic attenuation. The gas turbine engine also includes a spinner, disposed forward of the fan section, that includes features to increase acoustic attenuation. In one embodiment of the present invention, the nacelle includes a nacelle contoured surface protruding radially inward from the inner nacelle surface to reduce the inlet duct area. In a further embodiment of the present invention, the spinner includes a spinner contoured surface for reducing the inlet duct area. In other embodiments, the nacelle and/or the spinner include an inflatable bladder, a SMA actuator, a fluidic actuator, or a combination thereof, selectively activated to increase acoustic attenuation during certain conditions of an aircraft.

Abstract: 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 compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

Abstract: The present invention relates to a nacelle rear assembly (1) including a pod-shaped internal structure (11), said internal structure comprising at least one downstream portion (15) and one upstream portion (13) that are each movably mounted between an operative position, in which said portions are connected, and at least one maintenance position, in which said portions are separate from each other, the downstream portion being movably mounted by means of sliding while the upstream portion is movable by opening at least one door. The downstream portion and upstream portion are provided with a connection means that is capable of engaging therebetween. Said assembly is characterized in that at least one of the downstream and upstream portions is provided with a hinging means (131, 151) having a range of movement in at least one direction so as to enable stress-free control and operation of the portion in question.

Abstract: An inlet of a nacelle for channeling inlet airflow to a fan of a gas turbine engine includes a forward lip and an inner surface. The forward lip extends around a centerline axis of the engine and is adapted to accommodate a flow angle of incoming airflow. The inner surface extends from the forward lip along the centerline axis of the engine to adjacent the fan. The inner surface has a first profile above the centerline axis of the engine and a second profile below the centerline axis of the engine. The first profile and the second profile are adapted to define an inlet centerline axis that extends below the centerline axis of the engine at a face of the fan.

Abstract: Methods, aircraft, and engine nacelles are disclosed. A wing leading edge of a planform is superimposed on a wing shockwave that extends in a first direction from a shockwave apex toward the wing leading edge. A waverider shape is streamline traced between the wing leading edge and a trailing edge of the planform to form a waverider wing. A position of an engine inlet vertex relative to the waverider wing is identified. An inlet shockwave is projected from the inlet vertex in a second direction generally opposed to the first direction. The inlet shockwave intersects the wing shockwave. An inlet leading edge of an engine inlet includes a lower leading edge including a plurality of points where the inlet shockwave intersects the wing shockwave.

Abstract: A ventilation device for a compartment, preferably a compartment of an aircraft engine, the device including an air intake adapted to capture a flow of air outside the compartment, an air diffuser adapted to guide the air flow into the compartment, and an air distributor adapted to distribute the air flow within the compartment, the air distributor in this device being separated from the air diffuser, and being placed inside the compartment at a distance from the air diffuser

Abstract: 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 compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

Abstract: A gas turbine engine system for an aircraft includes a nacelle having a fan cowl with an inlet lip section and a core cowl, at least one compressor and at least one turbine, at least one combustor between the compressor and the turbine, a bleed passage, and a controller. The bleed passage includes an inlet for receiving a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The controller identifies an operability condition and selectively introduces the bleed airflow near a boundary layer of the inlet lip section in response to the operability condition.

Abstract: A nacelle assembly includes an inlet lip section and a cowl section positioned downstream of the inlet lip section. At least a portion of the cowl section is moveable to influence an effective boundary layer thickness of the nacelle assembly.

Abstract: An air inlet for nacelle of an aircraft propulsion unit comprising an inner envelope provided with a plurality of orifices for passage of fluid passing through said envelope, and a lip connected to the upstream edge of said inner envelope, and having a portion devoid of orifices for passage of fluid with an axial span of between 20% and 90% of the span of said inner envelope, and a circumferential span ? of between 60° and 150° about a longitudinal axis of said air inlet. A process for repairing an air inlet comprising cutting out a recess in an upstream edge of an inner envelope of the air inlet, then arranging and fixing an impermeable panel in said recess so as to create an air inlet of the type described above.

Abstract: 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 barrel aft edge is configured to be affixed to the fan case forward edge in a stationary position on the engine. The nacelle also includes a translating inlet cowl having an inlet lip with an aft inlet lip edge and an outer skin with rear edge. The translating inlet cowl is configured to be movably attached to one or more stationary portions of the engine such that the inlet cowl is selectively movable between a stowed flight position and an extended service position.

Abstract: The invention relates to a structure of a leading edge (1), in particular for the air intake of an aircraft nacelle, including a leading edge (2) and an inner partition wall (3) defining a longitudinal compartment (5) inside the leading edge (2). The leading edge (2) and said inner partition wall (3) are made of multiaxial composite materials.

Abstract: An annular cowl for a turbomachine nozzle, the cowl including a plurality of patterns arranged to extend a trailing edge of the cowl and circumferentially spaced apart from one another. Each pattern has an outline of substantially polygonal shape with a base formed by a portion of the trailing edge of the cowl and at least one vertex that is spaced downstream from the base and that is connected thereto by lateral edges, and in each of its lateral edges, each pattern includes at least one fin, each fin being inclined radially relative to the pattern in a plane that is inclined at an angle lying in the range 0° to 45° relative to a radial direction.

Abstract: An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation.

Abstract: An aircraft nacelle includes at its outside wall a cowl that can move relative to the rest of the nacelle so as to block or unblock an opening. The cowl includes an articulation relative to the rest of the nacelle and locking/unlocking elements distant from the upstream edge of the cowl that includes elements for limiting the appearance of scooping phenomena. The limiting elements include at least one electromagnetic torque, having one element integral with the rest of the nacelle and the other element integral with the cowl, with at least one of these two elements emitting a magnetic field that generates a force of attraction on the other element, and the surfaces of the two elements of the electromagnetic torque that are flattened against one another are arranged in planes having at least one component in the radial direction.

Abstract: An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure (30) and a reflective layer (32), between which are located—in a direction that is essentially perpendicular to the longitudinal direction of the nacelle—bands (34) of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes (36) for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer (30) up to the reflective layer (32) in such a way as to insulate the bands (34) of cells in the longitudinal direction.

Abstract: An aircraft nacelle includes a lip whose surface contacts with the aerodynamic streams extends inside the nacelle by an inside wall that delimits a layer that empties at a power plant and outside of the nacelle by an outside wall, a first front frame connects the inside and outside walls, delimiting an annular pipe with the lip, and a rear frame connects the inside and outside walls at a junction zone between the inside pipe and power plant pipe, for a given cross-section of the nacelle along a plane that contains the longitudinal axis of the nacelle, a point A at the intersection between the rear frame and the inside wall, and a point B at the intersection between the rear frame and the outside wall, with B being offset toward the rear of the nacelle relative to A over more than 50% of the rear frame's periphery.

Abstract: 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 compression surface functions to reduce cowl lip surface angles, thereby improving inlet drag characteristics and interference drag characteristics. Supersonic inlets in accordance with the invention also demonstrate reductions in peak sonic boom overpressure while maintaining performance.

Abstract: An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50?) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52?) that is in contact with the air stream and an edge (54, 54?) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54?)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.

Abstract: An aircraft nacelle includes a wall that delimits an inside pipe (42) that channels a stream of air to a power plant, at the front a lip (44) and on the outside an outside wall (46) that delimits a cavity (54), whereby the outside wall includes—at its inside surface—at least one stiffener (58) that is arranged in a transverse plane, characterized in that the at least one stiffener (58) includes at least one drainage opening that allows the flow of liquids through the stiffener (58) in the direction of a discharge opening (56) that is located away from the lip in such a way as to limit the risks of air being sucked inside the cavity (54).

Abstract: An aircraft nacelle including a pipe (32), a peripheral wall (34), a lip (36), and a front frame (38) connecting the peripheral wall (34) and the pipe (32) and forming with the lip (36) a space (50) in which the hot air that is provided for frost treatment can circulate, with the pipe (32) including a coating (44) for the composite material acoustic treatment, is characterized in that the nacelle includes at least one element (52) made of a heat-conducting material inserted between the lip (36) and the pipe (32) ensuring the continuity of the aerodynamic surfaces of the lip (36) and the pipe (32) and the propagation of heat from the space (50) toward the rear of the nacelle, whereby the at least one element (52) includes a coating (54) for acoustic treatment that is made of a heat-resistant material.

Abstract: Aluminum-based alloys for casting or wrought processing having improved combinations of properties, including improved high temperature strength, are provided. The alloys generally comprise copper, magnesium, silver, and titanium, along with scandium and/or cobalt. Zirconium, zinc, and/or vanadium may also optionally be present in the alloy. When cobalt is present in the alloy, nickel may also optionally be present. Cast and wrought products, as well as methods of making the same using the alloys, are also disclosed.

Abstract: A jet engine air intake guard system wherein direct axial air flow into an engine during takeoff and landing may be temporarily closed off while air intake is provided laterally through screened air intake ports located on a cylindrical housing that extends forward of the conventional air intake cowling openings.

Abstract: An air inlet duct for an air-breathing combined-cycle aircraft engines is internally divided into separate channels for low-speed and high-speed components of the engine, and contains one or more movable panels that are fully contained within the duct and pivotal between an open position in which incoming air is directed to both channels and a closed position in which all incoming air is directed to the channel leading to the high-speed engine. This integrated duct utilizes all incoming air at all stages of flight with no change in either the geometry of the air capture portion of the engine or the engine itself, and no exposure of movable leading edges. The result is a minimum of shock waves and a high degree of efficiency in operation of the engine.