|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||60/3909 ; P ; 55/306|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 26 인용 특허 : 0|
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.
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 interi...