초록 ▼

An aircraft engine variable area fan nozzle structure disposed abaft a thrust reverser, including a sleeve translatable over a cascade array, comprises two semi cylindrical segments that can be axially translated and radially tilted to enlarge the fan duct exhaust area in order to optimize exhaust p

An aircraft engine variable area fan nozzle structure disposed abaft a thrust reverser, including a sleeve translatable over a cascade array, comprises two semi cylindrical segments that can be axially translated and radially tilted to enlarge the fan duct exhaust area in order to optimize exhaust pressure and associated noise in high thrust circumstances such as on take-off, and to constrict that area under lower thrust conditions such as cruise. The segments are moved by actuators anchored to the fixed engine framework and independently of the thrust reverser translating sleeve. Each actuator incorporates a linear variable differential transformer acting as a fan nozzle position sensor. The tilting movement is imposed by the pivoting links of each segment to carriages that ride in a non-linear trackway secured to a thrust reverser translating sleeve slider. In an alternate embodiment of the invention, the thrust reverser sleeve actuator and the variable area fan nozzle actuator are coaxially mounted in a compact assembly anchored to stationary components of the nacelle.

대표청구항 ▼

1. In an aircraft gas turbine nacelle assembly having a fore-and-aft central axis, a stationary structure, including an annular torque box girder, at least two longitudinal beams and a transversal crosstie ring, said assembly further including a thrust reverser cascade array between said girder and

1. In an aircraft gas turbine nacelle assembly having a fore-and-aft central axis, a stationary structure, including an annular torque box girder, at least two longitudinal beams and a transversal crosstie ring, said assembly further including a thrust reverser cascade array between said girder and said ring, a movable sleeve having axial sliders shaped and dimensioned to translate said sleeve across and close said array, and a plurality of movable fan nozzle segments abaft said sleeve, an improvement which comprises: at least one of said segments being slidingly and rockingly connected to at least two of said sliders, whereby said nozzle can be axially translated and radially varied; wherein said sleeve and said one of said segments are axially translated by first and second actuators both anchored to said stationary structure; wherein said first and second actuators are coaxially mounted in an assembly anchored to said stationary structure;wherein said assembly comprises: a translatable first ballnut attached to said sleeve; anda non-translatable tubular first ballscrew engaging said first ballnut; and,wherein said assembly further comprises: a translatable second ballnut;a torque tube coaxially mounted within said first ballscrew and secured to said second ballnut; anda translatable second ballscrew engaging said second ballnut and having a distal end attached to said segment. 2. The improvement of claim 1, which further comprises a gear box including: a rotatable input shaft;a first output shaft rotatively driving said first ballscrew; anda second output shaft rotatively driving said torque tube. 3. The improvement of claim 2, wherein said gear box comprises: a clutch mechanism and a rotation reverser mechanism between said input shaft and each of said output shafts. 4. In an aircraft gas turbine nacelle assembly having a fore-and-aft central axis, a stationary structure, including an annular torque box girder, at least two longitudinal beams and a transversal crosstie ring, said assembly further including a thrust reverser cascade array between said girder and said ring, a movable sleeve having axial sliders shaped and dimensioned to translate said sleeve across and close said array, and a plurality of movable fan nozzle segments abaft said sleeve, an improvement which comprises: at least one of said segments being slidingly and rockingly connected to at least two of said sliders, whereby said nozzle can be axially translated and radially varied; wherein said sleeve and said one of said segments are axially translated by first and second actuators both anchored to said stationary structure; wherein said first and second actuators are coaxially mounted in an assembly anchored to said stationary structure;wherein said assembly comprises: a translatable first ballnut attached to said sleeve; anda non-translatable tubular first ballscrew engaging said first ballnut; and,wherein said assembly further comprises: a slide tube coaxially surrounding said first ballscrew; and,a bearing attached to one of said beams and slidingly supporting said slide tube. 5. The improvement of claim 4, wherein said assembly further comprises: an arm extending axially from said second ballscrew distally outside said bearing; anda bracket connecting said arm to said segment.