An aircraft engine guard, for protecting an aircraft engine against ingestion of large objects, includes a generally cone-shaped body, a base section of the rear end of the guard body and a dome section at the distal forward end of the guard body, at least three, vertical, peripherally extending walls located between the base and the dome section, with successive ones of the peripheral walls having different peripheral dimensions, peripherally cylindrical, with the dimension increasing from the base toward the dome section. A plurality of air intake openings are defined in and between the peripheral walls with at least one dimensional size which is small enough to prevent having birds from being able to pass through the guard into the aircraft engine.

A system includes an engine cover covering a side-facing rotorcraft engine and having an opening and an ice protection member mounted on the engine cover between the opening and the engine, an area of the ice protection member smaller than an area of the opening. The ice protection member is configured to partially cover the opening to prevent ice having a particular size from entering into the engine and to allow air flow downstream into the engine.

An aircraft propulsion assembly, comprising a gas generator and two fans rotated by the gas generator and offset on either side of a vertical plane passing through the axis of said gas generator. The propulsion assembly comprises an air inlet sleeve comprising an inlet pipe oriented along a first axis that is substantially parallel and offset with respect to a longitudinal axis of the gas generator, the inlet pipe dividing into a supply pipe that is connected to an inlet opening of the gas generator and a discharge pipe configured such that particles ingested by the inlet pipe are discharged without entering the gas generator.

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 protective cover for an aircraft engine comprises a lower portion mountable to a corresponding lower portion of an opening of the engine, and an upper portion articulated to the lower portion. The upper portion is deployable from a collapsed position to a deployed position in which the upper portion extends upwardly from the lower portion. A handling tool may be used to operate the panel from a remote location on the ground.

A system for an aircraft includes an aircraft engine having a central axis with a flowpath projecting into the aircraft engine from an airflow inlet. An inlet plenum at the airflow inlet extends between a front wall and a rear wall along the central axis. An inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen extending circumferentially about the central axis. The first screen has a first screen axial width L1 extending from the front wall to the rear wall. The inlet guard further includes a second screen extending at least partially circumferentially about the central axis. The second screen is disposed radially outward of the first screen and axially overlaps the first screen. The second screen has a second screen axial width L2 less than the first screen axial width L1.

A system for preventing objects from entering the intake of a jet engine including a deflector mounted to the turbine shaft and including a de-icing device to minimize collection of ice on the deflector. The deflector includes a sensor in one embodiment for measuring object strikes so that comprehensive impact data may be obtained to generate an impact report so that measures can be taken to minimize object impacts.

A system for an aircraft includes an aircraft engine having a central axis with a flowpath projecting into the aircraft engine from an airflow inlet. An inlet plenum at the airflow inlet extends between a front wall and a rear wall along the central axis. An inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen extending circumferentially about the central axis and axially from the front wall to the rear wall, and a second screen radially outward of the first screen and axially overlapping the first screen. An actuator is operable to move the first screen and the second screen relative to one another in one or more of a radial, axial and circumferential direction to shed ice from the inlet guard.

A system is provided for an aircraft. This aircraft system includes a gas turbine engine, a flowpath and an inlet guard. The gas turbine engine includes a compressor section. The flowpath projects longitudinally into the gas turbine engine from an airflow inlet and longitudinally through the compressor section. The inlet guard extends across the flowpath longitudinally upstream of the compressor section. The inlet guard extends circumferentially about an axis. The inlet guard includes a first screen and a second screen. The first screen includes a plurality of first perforations with a first perforation size. The second screen is circumferentially adjacent the first screen about the axis. The second screen includes a plurality of second perforations with a second perforation size that is different than the first perforation size.

A protective cover for an aircraft engine comprises a lower portion mountable to a corresponding lower portion of an opening of the engine, and an upper portion articulated to the lower portion. The upper portion is deployable from a collapsed position to a deployed position in which the upper portion extends upwardly from the lower portion. A handling tool may be used to operate the panel from a remote location on the ground.