A debris deflector for a jet engine. The debris deflector includes a housing having a base and a nose, wherein the housing tapers radially inwardly from the base towards the nose, such that the nose can deflect debris away from the housing. The housing includes a flexible shroud that extends between the base and the nose, such that the housing can selectively move between a collapsed position and an extended position, such that a linear distance between the nose and the base is less when in the collapsed position. A fastener is disposed on the base to removably secure the housing to a jet engine cowling. The debris deflector is useful for deflecting debris, such as wildlife or small aircraft, away from the jet engine during flight.

An aircraft includes a fuselage, an engine exhaust port extending through the fuselage, an air intake extending through the fuselage forward from, and adjacent to, the engine exhaust port, and an air cleaning assembly positioned over the air intake. The aircraft also includes a pressure recovery device including an outer wall positioned above the air cleaning assembly. A distance from a forward edge of the outer wall to the air cleaning assembly is greater than a distance from an aft edge of the outer wall to the air cleaning assembly. An inlet flow axis is defined normal to a cross-sectional flow area of the pressure recovery device at the forward edge, and is oriented upward at an acute angle relative to a longitudinal axis of the aircraft.

A leading edge for an airfoil of an aircraft includes a leading plate with a convex side and a concave side, and at least one container filled with a non-Newtonian fluid. The leading edge is configured to be secured to the torsion box of the airfoil. The at least one container is arranged between the concave side of the leading plate and the torsion box of the airfoil. An airfoil is also provided including such a leading edge. A method is provided for assembling such a leading edge.

This instant invention provides an airplane design mainly to eject rearward the high-speed exhaust gas from the engine of the airplane to flow through the upper surface of the wing, such that the forward propulsion forcing can be obtained via rearward ejecting the high-speed exhaust gas to push the air rearward, and also larger uplift forcing induced by a larger velocity difference vertically across the wing can be obtained to ascend the airplane at the same time. This velocity difference is generated because the air over the wing is accelerated by the ejected high-speed exhaust gas, but the air below the wing stays the same velocity, such that a bigger velocity difference is directly produced vertically across the wing, and thus more uplift forcing can be provided to ascend the airplane.

A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.

A barrier device is provided for an inlet cowl for an aircraft engine including an inner barrel circumferentially surrounding an opening in the inlet cowl formed along an axis of rotation of the aircraft engine, through which air passes to the aircraft engine, the inner barrel including a face sheet disposed on a radially inward side of the inner barrel relative to the axis. The barrier device includes a containment doubler of the inner barrel, disposed on a radially outward side of the inner barrel, and a blade fragment barrier including one or more strips disposed between the containment doubler and the face sheet, so as to extend circumferentially at least partially around the opening and to occupy a radial distance between the containment doubler and the face sheet.

An anti-icing system for a gas turbine system includes multiple nozzles arranged in a grid and configured to inject fluid within an air intake system of the gas turbine system upstream of a filter to keep ice from forming on the filter. Each nozzle of the multiple nozzles includes multiple orifices for injecting the fluid via jets. The anti-icing system also includes a nozzle head coupled to a nozzle of the multiple nozzles. The nozzle head is disposed over the multiple orifices and is configured to rotate relative to the nozzle. The nozzle head includes at least one outlet for injecting the fluid from the jets via at least one jet.

Disclosed is an apparatus for protecting an engine of an aircraft to prevent an inlet of an engine of an aircraft from being damaged. The apparatus includes: a protective net attached to an inlet arranged at a front of the engine of the aircraft; and hangers configured to fix the protective net along a side surface of the engine, wherein the protective net includes a plurality of circular fibers concentrically arranged while forming a circle, and a fixing fiber configured to fix an outer peripheral surface of the circular fibers to an outer surface of the engine while being bound to inner surfaces of the circular fibers and passing through a center of the circular fibers.

A turbomachine of the open rotor type or a turboprop engine comprises a nacelle defining an air inlet, a central hub and an annular air intake section surrounding the central hub and opening into a air supply main section, with the central hub comprising a central trap having an aperture for trapping the foreign objects in an air flow entering the turbomachine, and an air recovery channel having a discharge end, through which said air recovery channel opens into the main section, is provided on the central hub.

An anterior part of a nacelle of an aircraft propulsion unit. A rigidifying frame annular about a longitudinal axis of extension of the nacelle is at the rear end of the anterior part. An annular shield is in front of the rigidifying frame and connects an internal peripheral edge of the rigidifying frame to an internal structure. The shield has a portion extending towards the external panel beyond the internal peripheral edge of the rigidifying frame, the portion forming a non-zero angle with respect to the rigidifying frame to form a free space with respect to the rigidifying frame behind the portion. The shield can thus deform in the event of an impact of a foreign object entering through the air inlet lip, without the rigidifying frame itself being deformed, thereby absorbing all or some of the impact energy. A nacelle can have such an anterior part, and an aircraft can have such a nacelle.