An assembly of a gas turbine engine includes a low pressure compressor, a high pressure compressor, an intermediate case between the low pressure compressor and the high pressure compressor, and a cleaning apparatus having an annular arrangement about the intermediate case. A core flow path is defined through the low pressure compressor, the intermediate case, and the high pressure compressor. The annular arrangement includes a scroll portion configured to extract debris from an airstream at an outer diameter wall of the core flow path and return the airstream to the core flow path.

A differential pressure transducer provides measurements for determining the restriction, updated in real time, of an inlet barrier filter for a turboshaft engine of an aircraft. The percentage of restriction of the air inlet barrier filter, which corresponds to the condition of the air inlet barrier filter, is determined as a function of mass air flow into the engine during operation. The restriction percentage is indicated on the instrument panel of the rotorcraft.

A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.

A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.

The present invention discloses a soundproof cabin of a turbine engine. The soundproof cabin is sleeved on the turbine engine. The soundproof cabin includes a cabin body, an intake noise reduction unit and a ventilation noise reduction unit, wherein the intake noise reduction unit and the ventilation noise reduction unit are disposed on the cabin body, the surrounding of which is filled with soundproof materials, the intake noise reduction unit is used to reduce the induction noise of the turbine engine, the ventilation noise reduction unit is used to reduce the noise of the ventilation system of the turbine engine. Beneficial effects: an intake noise reduction unit is disposed at an air inlet of the turbine engine to reduce the induction noise of the turbine engine; a ventilation noise reduction unit is disposed on the transmission direction of the turbine engine to reduce the ventilation and cooling noise of the turbine engine; the surrounding of the turbine engine is filled with soundproof materials to achieve the overall noise reduction around the turbine engine.

An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

An air intake unit for an engine of an aircraft; the intake unit has: a tubular housing; a first inlet opening which is obtained through an outer wall of the tubular housing and through which external air can be taken in; an air filter which engages the first inlet opening; a second inlet opening which is obtained through the outer wall of the tubular housing and through which external air can be taken in; a shutter device which is coupled to the second inlet opening and is movable between a closed position, in which it closes the second inlet opening, and an open position, in which it sets the passage through the second inlet opening free; and an actuator, which moves the shutter device.

An air intake unit for an engine of an aircraft; the intake unit has: a tubular housing; a first inlet opening which is obtained through an outer wall of the tubular housing and through which external air can be taken in; an air filter which engages the first inlet opening; a second inlet opening which is obtained through the outer wall of the tubular housing and through which external air can be taken in; a shutter device which is coupled to the second inlet opening and is movable between a closed position, in which it closes the second inlet opening, and an open position, in which it sets the passage through the second inlet opening free; and an actuator, which moves the shutter device.

An air intake structure for a nacelle of an aircraft is disclosed having an air intake lip with a U-shaped section open towards the rear, an acoustic panel that extends the air intake lip towards the rear and on an inner side, an outer panel extending the air intake lip towards the rear and on an outer side, and a rear strengthening frame fixed between the outer panel and the acoustic panel, where the rear strengthening frame partly defines an inner volume that is immediately in front of the rear strengthening frame. The air intake structure comprises an impact absorber element positioned in the inner volume and the impact absorber element assumes the form of a structure that is deformable during an impact and that is at least partially filled with a fluid. The impact absorber element is a flexible shroud filled with a pressurized gas.