An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.

An environmental defense shield includes symmetric airfoil-shaped vanes contributing to and positioned around a plenum space and positioned in front of a turbine engine. An annular band stiffener is set into the vanes, which projects forward in a diminishing size, the vanes merging together to create or attaching to a solid nose. The environmental defense shield serves to protect the engine from debris while also smoothing airflow into the engine.

A helicopter engine air intake including an anti-icing grid that provides a large bypass flow in event of icing. The air intake includes air intake lips and an anti-icing grid mounted on outer ends of the air intake lips, being interposed in the air flow penetrating into the air intake, at least one air intake lip being formed by a thin metal sheet.

A gas turbine engine includes a nacelle defining a centerline axis and an annular splitter radially inward from the nacelle. A spinner is radially inward of the nacelle forward of a compressor section. A fan blade extends from a fan blade platform. A distance X is the axial distance from a first point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defined on a leading edge of the fan blade where the fan blade meets the fan blade platform. A distance H is the radial distance from the first point to the second point. The relative position of the first point and the second point is governed by the ratio of $\frac{X}{H}1.5$
for reducing foreign object debris (FOD) intake into the compressor section.

An aircraft system comprising a deflector assembly including, a base having mounting apertures; an inner ring concentrically positioned within an outer ring, the inner ring and the outer ring have an annulus defined therebetween via a base plate, a plurality of rods attached within the annulus and culminating at an apex creating a conical profile; and a forward-mounted cone-shaped deflecting member. The base plate comprises a through hole allowing airflow through the deflector assembly to supply an airplane engine. The aircraft safety device system further comprises at least one locking latch for removably securing the deflector assembly to a housing of the airplane engine. The aircraft safety device is mountable inside a lip of the housing of the airplane engine. Further, the aircraft safety device provides protection for airplane engines from air born animate and inanimate objects.

An apparatus for providing foreign object debris protection an air intake of an aircraft engine. The apparatus includes a frame and a plurality of cross-members. The cross-members are positioned in the frame to define a plurality of screen openings. At least one of the cross-members has an aerodynamically efficient cross section.

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.

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 gas turbine engine comprises an outer nacelle. A nose cone is spaced radially inward of the outer nacelle. The nose cone defines a particle separator for directing an outer air flow and an inner airflow. The inner airflow is directed through a core inlet to a compressor. The engine further comprises a drive gear system for driving at least one propeller. A variable pitch control system may alter a pitch angle of the at least one propeller. Some of the outer air flow is directed to at least one of the drive gear system and the pitch control system.

An intake for feeding air to an engine of an aircraft includes an opening for sucking in air, which opening faces in the direction of movement of the aircraft; and an air duct between the opening and the engine, which air duct is curved such that an impact region is arranged in the air duct after the opening in relation to the direction of movement of the aircraft. An object flying into the opening contacts the impact region. The impact region has a penetration region, which is designed to be penetrated by the impinging object.