Abstract: A jet engine intake deflector system for preventing foreign objects from entering the intake of a jet engine. The jet engine intake deflector system generally includes an air intake frame, a plurality of fins and a deflection member. The air intake frame is generally comprised of a plurality of laterally extending outer supports arranged at equidistance from each other in a substantially circular configuration around a center support. Each fin is generally comprised of a flat plate, wherein a front end of each fin is attached to the deflection member and a rear end of each fin is attached to the air intake frame. The free end of the air intake frame is generally welded directly onto a jet engine to protect its intake from foreign objects, such as birds. Upon striking a foreign object, the deflector member will direct the foreign object out and away from the jet engine intake.

Abstract: The present patent disclosure presents a class of patent aviation engine inlets using tangential blowing airflow grazing over buzz saw lining surface to prevent buzz saw noise from propagation out of the engine inlet, to alleviate airport noise problem and to reduce airplane cabin noise level for passenger comfort. The robustness of the concept of tangential blowing in the improvement of the attenuation of buzz saw tones by buss saw lining is that, practically, the significant buzz saw tones are eliminated. Tangential Blowing also serves to rectify undesirable inlet flows such as excessive boundary layer growth or flow separation that caused by cross wind, high angle of attack of inlet inflow during low flight speed operations of the aircraft. The relief of the inlet flow complications at low flight speed renders the airplane designer the freedom to shape/re-shape the engine inlet/nacelle contours for minimum cruise drag and best airplane trip fuel economy.

Abstract: Coupling device for connecting the two half-shells (1?) of an aircraft engine nacelle, comprising a connecting rod (17) which can be mounted in an articulated manner on one (1?) of the two half-shells, a retention member for this connecting rod (17) that can be mounted on the other half-shell, and means designed to allow limited movements of said connecting rod with respect to said retention member.

Abstract: A turbofan flow delivery system includes a fan case housing a fan. Flow exit guide vanes are arranged downstream from the fan and extend radially inwardly from the fan case toward a bypass flow path. A supply passage includes an opening provided in the fan case between the fan and flow exit guide vanes configured to selectively provide pressurized air to a component using air from the bypass flow path. Swirling air from the bypass flow path enters the supply passage and is converted to a static pressure.

Abstract: A turbojet engine nacelle, including an air intake structure for directing an airflow towards a fan of the turbojet engine, a middle structure attached to the air intake structure for surrounding the fan of the turbojet engine, the air intake structure including an inner panel attached to the middle structure and defining a fixed structure with the middle structure, and an outer panel including an air intake lip at the end thereof opposite the middle structure, the outer panel being longitudinally translatably movable relative to the inner panel. The nacelle further includes at least one rod having one end attached onto a flange of the air intake lip and a mechanism rigidly connected to the middle structure for securing and locking the other end of each rod by applying a traction force thereon.

Abstract: An aircraft nacelle includes an outside wall (22), at least one air system with at least one air intake (30), whereby the nacelle is connected by connecting element to a mast that is itself connected to the aircraft, with the connecting element allowing a relative movement between the nacelle and the mast in the longitudinal direction of the nacelle, whereby at the front of the junction zone with the nacelle, the mast includes an aerodynamic surface that is called a fairing (24) that covers and exposes a zone of the outside wall called an overlapping zone (28) based on the position of the nacelle (10) relative to the mast, characterized in that an air intake (30) for an air system is arranged at the overlapping zone (28).

Abstract: The invention relates to a method for closing a mobile element (1) actuated by at least one actuator (2) such as a cylinder equipped with a terminal backlash device (4), said cover also being associated with at least one locking means, the closing method comprising the following steps which aim:—by means of the cylinder, to drive the mobile cover to close on a portion of the travel thereof, until said cover reaches the proximity of an area with closing forces, the distance remaining to be travelled being less than the available backlash of the cylinder;—by means of the locking means, to complete the travel of the mobile cover until said cover closes, the cylinder being located in the backlash area thereof.

Abstract: The invention relates to a method for manufacturing a structure with cellular cores (202) that can be used in the structural panel of a turbojet nacelle, including at least one block of cellular cores (A, B) having a central portion (5a, 5b) with core honeycomb cells (7a, 7b) and at least two side portions (9a, 9a?, 9b, 9b?) each including side honeycomb cells (11a, 11b), wherein said method includes the following steps: A) forming junction walls on the side honeycomb cells (11a, 11b), the junction walls being capable of interacting for forming a junction area (213); B) unfolding the junction walls thus formed; and C) joining the walls thus unfolded (46) and belonging to two different side portions (9a, 9b) end-to-end so that said junction walls (46) are fitted together so as to form a junction area (213). The invention also relates to a structural panel and to a nacelle including a structure with cellular cores obtained by said method.

Abstract: The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside.

Abstract: The invention relates to a jet engine nacelle intended to equip an aircraft, comprising a forward air inlet section, a mid-section intended to surround a fan of the jet engine, and an aft section formed from at least first and second half-shells (9, 10) rotatably mounted about an axis (A) such that they can each be deployed between a working position in which the half-shells (9, 10) are drawn towards one another and a maintenance position in which the half-shells (9, 10) are spaced apart, the mid- and aft sections being connected to one another by a frame (12) which is fixed with respect to the jet engine, the first and second half-shells (9, 10) being equipped with positioning means (13) which in the working position cooperate with complementary positioning means (14) formed on the fixed frame (12).

Abstract: An air intake for an aeroplane engine of type with unducted propellers, which intake can be connected by a pylon to a fuselage of an aeroplane, a local length of the air intake, measured parallel to the axis of the engine between a point on a leading edge of the air intake and a transverse plane situated at an inlet impeller of the engine compressor, is longer in a region of the air intake connected to the pylon and shorter in a region of the air intake opposite the pylon.

Abstract: The invention relates to a nacelle (1) for a turbojet engine (8) comprising: an air intake structure (4) able to channel a flow of air towards a fan (7) of the turbojet engine (8), comprising an air intake lip (21) upstream of the nacelle (1) and attached at its ends to an outer panel (25) and an inner panel (23); a central structure (5) intended to surround said fan (7) and to which the air intake structure (4) is attached in such a way as to ensure aerodynamic continuity, said central structure (5) comprising a secondary, or bypass, flow path outer ring section (11) intended to surround the engine and a central outer cowl (13), and a downstream section (6), the outer panel (25) comprising a moving part (25a) attached to the air intake lip (21) and extending downstream of the inner panel (23) and at least one fixed part (25b) fixed to the central structure (5) or to the downstream section (6) and intended to nest together with the moving part (25a) through their having complementary shapes.

Abstract: The present invention relates to a jet engine nacelle (1) comprising an aft section (5) having an internal structure (9) intended to surround an aft portion of an engine compartment and to define, with an exhaust nozzle (6), a calibrated outlet section for the ventilation of the engine compartment by way of spacing means arranged in the outlet section, characterized in that the spacing means are divided into rigid spacing means (11) designed to provide a constant spacing and into compensating means (13) designed so as to be able to adapt to the relative movements of the jet engine with respect to the nacelle.

Abstract: An engine arrangement for a component subject to icing. The arrangement comprising a manifold as part of a flow path incident upon a heated component. The manifold including holes to create jets having an exit angle toward the component subject to icing. The jets of hot gas are entrained in a core flow passing through the main flow path before washing over a desired incident area of the component. The exit angle and spacing between the jet and the component are determined to reduce disruption of the core flow and/or provide the desired incident area on the component and/or use the minimum amount of hot air.

Abstract: 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.

Abstract: An apparatus and method for an improved morphing flow path. A flexible structure has a plurality of sections which include a first section and a second section. An actuator system is connected to the flexible structure and includes a number of actuators. The actuator system is capable of changing a configuration of the flexible structure. A controller is connected to the actuator system. The controller is capable of changing a position of a number of actuators within the actuator system.

Abstract: Apparatuses are provided for reducing noise generation from a dead ended conduit in a gas turbine engine. In particular A scooped bellmouth is provided that comprises a bellmouth within a surface having an outer perimeter an inner perimeter and a ramp diverging from the surface at a first end, the ramp extending radially through the outer perimeter of the bellmouth at a second end. The ramp diverts an airflow away from the bellmouth thereby preventing the development of a low pressure area at the bellmouth without affecting the efficiency of the gas turbine engine.

Abstract: A panel assembly of the kind found in the air intake of a gas turbine engine or a fan duct is designed to be demountable for maintenance purposes. Consequently there exists between the panels a gap to be sealed. Thus, the assembly has a deformable seal for such a purpose and has an elongated, hollow resilient member mounted on a flange at the edge of one of the panels and arranged to be pressed against a flange at the confronting edge of the adjacent panel. The flanges are shaped such that the hollow member when pressed between the flanges effectively seals the gap between the panels and a portion of the seal member lies flush between the panel edges.

Abstract: A nacelle assembly for a gas turbine engine includes a fan cowl disposed about an axis, a core cowl within the fan cowl and a bleed passage having an inlet that receives a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The bleed airflow is selectively introduced near a boundary layer of an inlet lip section of the fan cowl.

Abstract: A supersonic inlet includes a cowl and an innerbody. An airflow duct entrance, between the cowl and the centerbody, receives an incoming airflow. An airflow duct exit, between the cowl and the centerbody, delivers a subsonic airflow. A controlled airflow separation initiator, on the innerbody and upstream of a lip of the cowl, which, when actuated, creates a separation in the incoming airflow. The separation region changes the local flow field aerodynamics such that an airflow weight flow at the cowl lip matches an airflow weight flow at a duct minimum area, between the airflow duct entrance and the airflow duct exit.

Abstract: An inlet apparatus and method for use with a cabin air compressor on a high speed, airborne mobile platform, such as a commercial or military aircraft. The apparatus includes a Pitot inlet of a desired shape that is supported outside an exterior surface of a fuselage of the aircraft by a diverter structure. The diverter structure diverts a low energy portion of a boundary layer so that the low energy portion does not enter the Pitot inlet. The Pitot inlet receives the higher energy portion of the boundary layer and channels a ram airflow to an inlet of a cabin air compressor. The apparatus provides a recovery factor (RF) of at least about 0.8 at a cabin air compressor (CAC) inlet face, which keeps the electric power required to drive the CAC within available power limits, while minimizing the drag of the inlet apparatus.

Abstract: 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 guarantee that the systems on board the aircraft are supplied, in a simple and reliable way, with the required ambient air in any operational state of the aircraft, i.e. both during the flight and on the ground, the ram air channel (10) has a second air inlet (24) which is independent from the first air inlet (12).

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: The intake cone for a gas-turbine engine is wound in one piece from fiber compound material with fiber layers crossing one another. It is provided with a fiber compound belt, wound in the circumferential direction of the intake cone, in the connecting area with a mounting flange, which is of segmented design and thus features reduced circumferential stiffness, of a metallic retaining ring attached to a fan rotor disk. The intake cone is easily manufacturable with almost constant wall thickness and in high quality, can reliably be subjected to non-destructive testing and, in combination with the mounting flange, which is flexible in the radial direction, ensures safe connection of the two components despite the different thermal and elastic behavior of the respective materials.

Abstract: 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 control jets and vortex generating vanes are used in combination to reduce distortion across a range of inlet operating conditions. Together, the vortex generating vanes can reduce most of the inlet distortion and the active flow control jets can be used at a significantly reduced control jet mass flow rate to make sure the inlet distortion stays low as the inlet mass flow rate varies. Overall inlet distortion, measured and described as average SAE circumferential distortion descriptor, was maintained at a value of 0.02 or less. Advantageous arrangements and orientations of the active flow control jets and the vortex generating vanes were developed using computational fluid dynamics simulations and wind tunnel experimentations.

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: 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: A system, method, and apparatus for throat corner scoop offtake for mixed compression inlets for high speed aircraft engine applications is disclosed. The throat corner scoops are small air intakes located inside the large mixed compression inlet. They are positioned in a region otherwise prone to generate low pressure airflow. The throat corner scoops capture and remove the low pressure airflow from the bulk stream that is passed on to the engine. This location also provides inlet stability enhancement, and the airflow is used on the auxiliary systems.

Abstract: An intake cone for a gas-turbine engine has an essentially conical body 5 located on a retaining ring 3 connected to a fan rotor disk, with the body 5 being designed as one piece over its axial length and connected at a conical locating area to a rigidly designed conical supporting area borne on a fan rotor disk.

Abstract: Embodiments of the invention relate to a supersonic nacelle design employing a bypass flow path internal to the nacelle and around the engine. By shaping the nacelle, embodiments of the invention may function to reduce sonic boom strength, cowl drag, and/or airframe interference drag. Embodiments of the invention may also function to improve total pressure recovery and/or total thrust of the primary flow path through the engine.

Abstract: A jet engine nacelle for a supersonic aircraft may include an air inlet structure that has an inlet face with an elliptical conical cross section. The elliptical conical cross section is defined by the intersection of a conical shock wave generated by a conical compression ramp and a first plane. The first plane is inclined with respect to a second plane that is orthogonal to a longitudinal general direction of the nacelle so that the free side of the inlet face is set back, in the air inlet direction, with respect to the opposite side intended to face the aircraft.

Abstract: A tandem inlet apparatus for use with a high speed mobile platform, for example a commercial or military aircraft. The tandem inlet apparatus includes a Pitot inlet for feeding air to a cabin air compressor (CAC) of an air conditioning pack carried on the mobile platform. A flush heat exchanger inlet is disposed forwardly of the Pitot inlet and longitudinally aligned with the Pitot inlet, for supplying cooling air to a heat exchanger of the air conditioning pack. By locating the heat exchanger inlet forwardly and longitudinally in line with the Pitot inlet, the heat exchanger inlet is able to effectively swallow a large portion of the boundary layer, which results in a thinner boundary layer at the inlet face of the Pitot inlet. This enables a smaller throat area Pitot inlet to be used, as well as a shorter diverter height to be employed with the Pitot inlet, while still realizing an improved recovery factor (RF) performance with the Pitot inlet. The reduced height Pitot inlet also enables drag to be reduced.

Abstract: Ram air inlets for use with aircraft environmental control systems and other aircraft and non-aircraft systems are described herein. In one embodiment, a ram air inlet configured in accordance with the present invention includes an inlet lip spaced apart from an inlet housing. An inlet door is moveably attached to the inlet housing, and includes a first surface portion, a second surface portion, and a transition region extending between the first and second surface portions. The first surface portion is moveably positioned at least approximately forward of the inlet lip. The second surface portion is fixed at an angle relative to the first surface portion, and is moveably positioned at least approximately aft of the inlet lip. The transition region is positioned at least approximately adjacent to the inlet lip to form an inlet opening therebetween. Movement of the inlet door in a first direction reduces the size of the inlet opening to thereby decrease the flow of ram air through the inlet.

Abstract: A method operable to improve pressure recovery and/or distortion within engine inlet is disclosed. A first fluid flow is provided to primary jet vortex generator(s) operable to inject fluid at a first injection rate into a boundary layer of a primary fluid flow within the inlet. A secondary fluid flow is injected by secondary jet vortex generator(s) at a second injection rate into the boundary layer of the primary fluid flow, The fluid injected at the first injection rate and second injection rate is operable to induce secondary flow structures within the boundary layer. These secondary close structures are then operable to improve or manipulate the pressure recovery of the inlet. At specific engine conditions, this method may redistribute the ratio of the first injection rate and second injection rate in order to improve pressure recovery and/or distortion of the inlet when the particular engine conditions.

Abstract: According to the invention, the internal wall of the air intake (2) and the housing of the fan (3) form a single tubular piece (30) made from a fibre/resin composite material.

Abstract: An air induction system for an engine having an improved mechanism for control of an intake door. The system includes a housing having an opening for receiving intake air. A power activated door is pivotable between a closed position wherein the opening is closed and an open position wherein intake air may enter through the opening. Linkages operatively connect an actuator cylinder to the door. The linkages are configured such that movement of the cylinder produces a corresponding rotation of the door which is non-uniform across the cylinder's range of motion. The linkages include first and second bellcranks mounted for pivotal motion, and a link which interconnects the bellcranks. Movement of the cylinder at a first position causes pivoting of the door, while movement at a second position causes substantially no pivoting of the door.

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: The present invention includes a supersonic inlet having a converging portion and a diverging portion operable to diffuse engine airflow from supersonic speeds to subsonic speeds. A physical throat includes a fixed flow area at a fixed location is between the converging and diverging portions of the inlet. A fluidic injector injects pressurized fluid into the inlet to form a variable effective throat within the inlet and improve the off design efficiency of the inlet.

Abstract: An auxiliary power unit (APU) compartment air inlet system seals, via one or more inlet doors driven by a single actuator, an APU compartment, and isolates the APU inlet and cooling system inlets from each other. The system includes either one or two inlet doors, depending on the number of ram air inlets formed in the APU compartment. In either instance, however, a single actuator is used to move the inlet door(s) between open and closed positions.

Abstract: A system of controlling airflow into a pulse detonation engine includes a rotary airflow controller valve receiving air from a high-speed inlet. An engine frame includes a plurality of detonation chambers. A sealing mechanism is between the rotary airflow controller valve and the engine frame. The sealing mechanism is associated with the engine frame and limits leakage of a gas from a first of the detonation chambers to a second of the detonation chambers.

Abstract: Embodiments of the invention relate to a supersonic inlet having a cowl lip 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: The aft stiffening frame of an air intake structure for an aircraft engine nacelle is made with an inflection area such that the part between the inflection area and one of its ends could be subjected to a large deformation when a constraint occurs in the direction of the frame part defined by the inflection area and its other end, usually normal to the casing. This particular shape of the aft stiffening frame makes it possible to improve its flexibility so that the air intake structure has better resistance to severe deformed shapes that could occur, for example, when a fan breaks on a wide body aircraft.

Abstract: There are provided a nozzle capable of enhancing the straight-advancing capability of jetted fluid to increase the back wash effect of a filter member, and a filter-type dust collector capable of effectively carrying out dust removal from a filter member with such a nozzle. To this end, the nozzle has a Laval nozzle section secured to the inside of an outer tube at its proximal end and a fluid guide section disposed at the leading end of the outer tube. The fluid guide section has a plurality of suction holes elongated in the flowing direction of the pressurized fluid. This nozzle is mounted on a pulse header tube of a dust removal device.

Abstract: Embodiments of the invention relate to a supersonic inlet employing 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. Using supersonic inlets in accordance with the invention also demonstrated reductions in peak sonic boom overpressure while maintaining performance.

Abstract: Methods and apparatus for a fluid inlet according to various aspects of the present invention comprise a housing and a ramp at least partially within the housing. The housing and the ramp define a passage through which air may flow to the engine and a cavity on the opposite side of the ramp from the passage. The ramp is moveable within the housing to change the size of the passage and the cavity. The system further comprises a seal substantially disposed across the cavity.

Abstract: A nose cone for a turbomachine, such as a turbojet in particular, the cone being mounted on the end of a shaft carrying fan blades and being associated with a controlled axial displacement mechanism, thereby making it possible to modify the axial position of the cone relative to the fan blades.

Abstract: An integrated mount duct includes a load ring for mounting a turbomachine to a flight vehicle, wherein the load ring has a cylindrical shape with a flange edge and a stepped edge, and comprises one or more mechanical attachment members disposed on an outside surface of the load ring, the mechanical attachment members configured to mate with a strut.

Abstract: Dual flow auxiliary power unit (APU) inlets and associated systems and methods are disclosed. An inlet in accordance with one embodiment of the invention includes an entrance aperture and a divider positioned in the inlet and located to separate a first portion of the inlet from a second portion of the inlet. The first portion can be configured to couple to an engine air intake of an APU, and the second portion can be configured to direct air away from the air intake. The divider can be positioned to direct air having a first total pressure level and a first distortion level to the first portion of the inlet, and direct air having a second total pressure level and second distortion level to the second portion of the inlet. The first total pressure level can be approximately the same as or higher than the second total pressure level, or the second distortion level can be approximately the same as or higher than the first distortion level, or both.

Abstract: A multi-spectral shield and associated inlet structure is provided for reducing the signature of an air inlet port defined within an exterior wall of an aircraft, ship, or land-based vehicle across radar and infrared wavelengths. The multi-spectral inlet shield includes a plate disposed in front of the air inlet port. The plate is sized to visibly eclipse the air inlet port, when viewed from a direction perpendicular to the plate. The plate is supported in this position by a plate mount or splitter that extends from within the air inlet port and attaches to the plate. A support may optionally combine with the splitter to support the plate in this position. Air passes behind the plate and into the air inlet port via a channel defined around at least a portion of the plate.

Abstract: Apparatus and methods for reducing foreign object debris ingestion into aircraft engines. The apparatus includes a door disposed at a forward end portion of a housing portion of the engine. The door is movable with respect to the engine between a first position in which a first engine inlet is open and a second engine inlet is substantially blocked by the door, and a second position in which the second engine inlet is open and the first engine inlet is substantially blocked by the door. Accordingly, moving the door to its first position during taxiing, takeoff, and landing substantially reduces the risk of foreign object debris ingestion into the second engine inlet.