Ram air intakes of rotary-wing aircraft turbine engines
AssigneeSociete Nationale Industrielle Aerospatiale
InventorAnicet Derue
Life of this patent
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Abstract
The invention relates to equipment for the air intake of an aircraft turbine engine, which equipment includes an inlet duct capable of being obturated by a bullet therein, and a bullet thrust mechanism connected to the duct by studs forming bullet guides. Part of the duct is formed by box members for receiving a plurality of separating elements downstream of deflectors, the internal face of the duct lip together with the external face of the bullet and of a jack piston and cylinder of said thrust mechanism being made of soundproofing material.
Claims5
Air intake apparatus for a turbine engine of an aircraft particularly for a helicopter comprising in combination an inlet duct formed of an annular hollow housing having exterior and interior walls forming an opening at the forward end and flaring divergently outward toward the rear end, a streamlined bullet located within said duct, a thrust mechanism located within said duct for axially moving said bullet into and out of sealing position in said central opening, said thrust mechanism being supported on a plurality of radial struts secured to the interior wall of said duct and partially blocking said duct, a plurality of inertial particle separators radially aligned between the exterior and interior walls of said housing intermediate the forward and rear ends thereof, each of said separators having an inlet in the external wall of said housing for free communication with external air, a first outlet in said interior wall for communication with said duct and a second outlet communicating into the space between the external and internal walls of said housing for the accumulation of particles therein, said inlet and first outlet of said separator being constantly open to provide free flow of air into said duct, at least one channel extending rearwardly from the space between said external and internal walls of said housing and opening in the exterior wall of said housing for the discharge of said particles, and deflector elements stationarily positioned externally about said duct upstream of said separator to disturb the flow of said external air reaching the inlet of said separators.
Air intake apparatus for a turbine engine of an aircraft and more particularly a helicopter, comprising in combination, a divergent annular air inlet duct, a streamlined bullet capable of sealing off the interior of said duct and axially movable by a thrust mechanism connected to said inlet duct, said duct being formed by an annular hollow housing having an internal and external wall, a plurality of radially aligned inertial particle separator elements within said housing in an intermediate section thereof extending with their longitudinal axes radial of said duct and arranged in a plural number of groups symmetrically about the annular duct housing, each group being separated by a longitudinal section of duct, said separator elements having an inlet open on the external wall of said housing and being fed with external air and having an outlet open within said housing to accumulate said particles, at least one channel extended from between said longitudinal sections outwardly of said external wall for discharge of said particles and deflector elements positioned externally about said duct section upstream of said separators to disturb the flow of said external air reaching the inlet of said separators, the internal surface of the forward end of said duct, the external surface of the cone and of said thrust mechanism being made of sound-dampening material.
Dependencies are inferred from the claim text.