An inertial particle separator, having: an inlet duct defining an intake; an intermediate duct extending from the inlet duct to an engine inlet; a bypass duct in fluid communication with and extending downstream from the inlet duct, the bypass duct defining an outlet communicating with the environment of the aircraft engine, a splitter defined at an intersection of a wall of the bypass duct and a wall of the intermediate duct; a splitter vane within the intermediate duct and having a leading edge located upstream of the splitter relative to a flow circulating through the separator, the splitter vane and the wall of the intermediate duct defining a channel therebetween; and a porous plate extending across the channel and defining openings sized so as to aggregate ice and be blocked by ice under icing conditions.

The present invention is a safety shield to be secured with nacelle of aircraft. Safety shield is shaped like nacelle such that nacelle is covered by use of safety shield. Shield frame of safety shield is provided with a plurality of openings of pre-defined size and shape and disposed at desired orientations. Openings facilitate ventilation to a mechanical engine provided in nacelle. Safety shield is connected to nacelle by clamping elements that securely clamps safety shield with nacelle. In operation, safety shield prevents collision of birds and foreign particles with fan blade of mechanical engine and thus saves life and failure of mechanical engine.

The invention defines a combined system of sensor(s), control logic, air intake and contaminant deflector for a fuel cell system mounted on an aircraft, which will detect contamination in the free air flow surrounding the aircraft and if excessive contamination is detected will activate the contaminant deflector to protect the fuel cell system from contamination, damage and power loss. The system ensures constant speed of the aircraft by adjusting the power of the fuel cells to compensate any change in aircraft drag and adjusts the speed of any connected compressors to maintain and achieve necessary changes in power and compensation for any air pressure losses the system creates.

A system and method of an airflow control system for a vehicle is described herein. The airflow control system (100) includes an airflow housing (120) defining an airflow passageway (125) extending between a bypass opening (122) and an intake outlet (124). The airflow housing also defines a duct opening (126) positioned between the bypass opening (122) and the intake outlet (124). The intake outlet (124) may be in fluid communication with an engine intake (12) of the vehicle such that air passes from the bypass opening (122) and/or the duct opening (126) to the engine intake (12). The airflow control system (100) also includes a movable duct (160) movably connected to the airflow housing (120) to selectively allow or prevent air passage through the duct opening (126) and into the engine intake (12), and further includes a bypass door (140) movably connected to the airflow housing (120) to selectively allow or prevent air passage through the bypass opening (122) and into the engine intake (12).

An element including a leading edge forming a box delimited by a skin forming a lower surface and an upper surface and pierced with holes, in which the skin includes an inner wall and an outer wall that are electrically conductive and an electrically insulating intermediate wall, a pump for expelling or injecting air from or into the box. Each hole is equipped with an anti-clogging system including a conductive base, a needle made of piezoelectric material, one end of which is secured to the base, an electrical generator generating an electrical current in the needle, in which the form of the needle is such that a space is created between the needle and the edges of the hole, and in which the base has a recess in the extension of the space. Such an installation makes it possible to eliminate the residues which are lodged in the holes.

The disclosed embodiments describe cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, an engine cover assembly, and a controller. The engine has moving parts and defines a fluid opening. The fluid opening exposes the moving parts to an ambient environment. The first sensor component is located proximate to the engine. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The second sensor component is attached to the engine cover and is configured to interact with the first sensor component. The controller is configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.

A wing comprising a leading edge forming a caisson delimited by a wall and an electrically conductive skin forming a lower surface and an upper surface and pierced with holes. A pump is provided to suck the air present in the caisson and/or to inject air into the caisson. The wing includes a voltage generator. Each hole is equipped with an anti-clogging system which comprises an electrically conductive electrode, an electrically insulating body having a stem which lodges in the hole and which has a central orifice in which the electrode lodges. The outer face of the stem has at least one tooth, where each tooth protrudes from the outer face of the stem and extends over the height of the stem. The at least one tooth is distributed around the stem so as to create at least one channel.

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 turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

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.