|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||244/54 ; 248/5 ; 60/3931|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 99 인용 특허 : 0|
A nacelle assembly including an inlet channel, an exterior cowl, a fan channel, and a turbine exhaust nozzle is directly mounted on a turbofan jet propulsion engine. The engine in turn is shock mounted directly on a strut, in turn affixed to an aircraft. A central portion of the outer cowl is hinged to open in a clam shell manner about hinges positioned adjacent the strut location to expose the fan casing and engine accessories for maintenance and removal. A rearward portion of the nacelle assembly is formed in two D-duct structures that are also hinged ...
In a structure for mounting a turbofan engine on a aircraft fuselage, said turbofan engine having a high bypass ratio and including a turbine casing housing a turbine engine, the rearward end of a turbine nozzle operably associated with said turbine casing for directing propulsion gases rearwardly from said engine, an annular fan casing surrounding and spaced outwardly from said turbine casing, a low pressure fan mounted within said fan casing and driven by said turbine engine, said fan casing being structurally coupled to said turbine casing, an improve...