IPC분류정보
| 국가/구분 |
United States(US) Patent
등록
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| 국제특허분류(IPC7판) |
|
| 출원번호 |
US-0644915
(1975-12-29)
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발명자
/ 주소 |
- Moorehead James R. (Bellevue WA)
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| 출원인 / 주소 |
- The Boeing Company (Seattle WA 02)
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| 인용정보 |
피인용 횟수 :
99 인용 특허 :
0 |
초록
▼
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
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 to open in a clam shell manner about hinges positioned adjacent the strut location. The D-duct structures include portions of the outer cowl and of the fan duct walls. When the D-duct structures are open, the turbine casing of the turbofan engine is exposed for maintenance, repair and removal. A pair of beams, affixed at one end to the aircraft fuselage, and enclosed by an aerodynamic fairing, constitute the mounting strut. The beams extend beyond the fairing into the nacelle and through a fan duct bifurcating structure. The forward of the two beams forks into a yoke-like structure that surrounds a portion of and is affixed by shock mounts to the exterior of the fan casing. The rear beam is also affixed to the turbine casing by a shock mount.
대표청구항
▼
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 f
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 improved structure for interchangeably mounting said turbofan engine to a plurality of locations on a fuselage comprising: a structural yoke and means for affixing said yoke to the fuselage of an airplane, said yoke extending about a portion of the periphery of said fan casing and being spaced therefrom, said yoke having a central portion, a first end spaced in a first direction from said central portion and a second end spaced in the opposite direction from said central portion, first shock absorbing mounting means associated with the first end of said yoke for releasably coupling the first end to a first location on the periphery of said fan casing, second shock absorbing mounting means associated with the second end of said yoke for releasably coupling the second end of said yoke to a second location on the periphery of said fan casing, said second location being spaced from said first location, a mounting arm and means for affixing said arm to the fuselage of an airplane, said arm having an outer end located adjacent said turbine casing and rearwardly from said yoke, said arm extending in a generally radial direction toward said turbofan engine, third shock absorbing mounting means associated with the outer end of said arm for releasably coupling said outer end to said turbine casing, nacelle means associated with said engine and including inner and outer fan duct walls defining an annular fan duct associated with and extending rearwardly from said fan casing for receiving fan air from said fan and directing said fan air rearwardly relative to said engine, and bifurcation means affixed to said engine and associated with said fan duct for splitting the flow of air therethrough, said bifurcation means extending longitudinally along said duct from a forward location adjacent said fan casing to a location rearwardly thereof, said bifurcation means being located in said fan channel adjacent the central portion of said yoke and having a central channel therethrough communicating between the region inside the inner fan duct wall and the region outside the outer fan duct wall, said mounting arm extending through said central channel, said nacelle means being coupled to said bifurcation means and said engine so as to be isolated from said mounting arm and said yoke when said engine is mounted thereon, and to remain coupled to said bifurcation means and said engine when said engine is released from said yoke and said mounting arm.
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