A nacelle, a part of which is the fairing device, surrounds a gas turbine engine and a support pylon on an aircraft fuselage. The pylon extends into a substantially horizontal plane of symmetry containing the longitudinal axis of the propulsion power unit, and includes a central compartment that is
A nacelle, a part of which is the fairing device, surrounds a gas turbine engine and a support pylon on an aircraft fuselage. The pylon extends into a substantially horizontal plane of symmetry containing the longitudinal axis of the propulsion power unit, and includes a central compartment that is open on the top and on the bottom and provided for housing devices. The pylon is attached to the fuselage by a distal edge extending parallel to the longitudinal axis of the propulsion power unit. The fairing device includes an upper half-cowl (2) and a lower half-cowl substantially symmetrical relative to the plane of symmetry, and lockable therebetween, in a closed position. The upper half-cowl and lower half-cowl are individually pivotably mounted on the distal edge of the pylon such that, in an open position, access is provided at the same time to the engine and to the central compartment of the pylon.
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1. A fairing device for a propulsion power unit comprising a gas turbine engine, a nacelle, of which said fairing device forms a part, and which surrounds the engine, and a pylon for securing to a fuselage of an aircraft, said pylon extending in a substantially horizontal plane of symmetry containin
1. A fairing device for a propulsion power unit comprising a gas turbine engine, a nacelle, of which said fairing device forms a part, and which surrounds the engine, and a pylon for securing to a fuselage of an aircraft, said pylon extending in a substantially horizontal plane of symmetry containing a longitudinal axis of the propulsion power unit, and comprising a central compartment open from the top and from the bottom, and designed to house equipment, said pylon being configured to be attached to the fuselage by a distal edge running parallel to the longitudinal axis of the propulsion power unit, the fairing device comprising: an upper half-cowl and a lower half-cowl which are substantially symmetric with respect to said horizontal plane of symmetry and can be locked together, in a closed position, at a meeting point between the upper and lower half-cowls by a locking device,wherein said upper and lower half-cowls are mounted so as to be pivotable individually and independently on said distal edge of the pylon so as, in an open position, to provide access both to the engine and to the central compartment of the pylon,wherein the upper half-cowl includes a substantially planar first part which closes the top of the central compartment of the pylon in the closed position and a semi-cylindrical second part belonging to an upper part of the nacelle, a first end of the first part of the upper half-cowl being a free end which is pivot-mounted on the distal edge of the pylon via a first pivot device, a second end of the first part of the upper half-cowl being fixed to a first end of the second part of the upper half-cowl, and a second end of the second part of the upper half-cowl including a first portion of the locking device, andwherein the lower half-cowl includes a substantially planar first part which closes the bottom of the central compartment of the pylon in the closed position and a semi-cylindrical second part belonging to a lower part of the nacelle, a first end of the first part of the lower half-cowl being a free end which is pivot-mounted on the distal edge of the pylon via a second pivot device, a second end of the first part of the lower half-cowl being fixed to a first end of the second part of the lower half-cowl, and a second end of the second part of the lower half-cowl including a second portion of the locking device. 2. The fairing device for a propulsion power unit as claimed in claim 1, wherein the second part of the upper half-cowl is formed of at least two portions articulated to one another about an axis running parallel to the longitudinal axis of the propulsion power unit, a first of said portions being made as one piece with said first part of the upper half-cowl. 3. The fairing device for a propulsion power unit as claimed in claim 2, wherein said faring device comprises at least one holding means for keeping the upper half-cowl in the open position, said holding means is an arm, a first end of the holding arm is pivot-mounted on the second end on said first part of the upper half-cowl and a second end of the holding arm rests against the pylon so as to immobilize the upper half-cowl in the open position. 4. The fairing device for a propulsion power unit as claimed in claim 3, wherein, in the open position, a center of gravity of the second portion of the upper half-cowl lies in a vertical plane passing through the first end of said holding arm. 5. The fairing device for a propulsion power unit as claimed in claim 1, wherein said fairing device comprises at least one holding means for keeping the upper half-cowl in the open position. 6. The fairing device for a propulsion power unit as claimed in claim 5, wherein said holding means is an arm, a first end of the holding arm is pivot-mounted on the second end on said first part of the upper half-cowl and a second end of the holding arm rests against the pylon so as to immobilize the upper half-cowl in the open position. 7. The fairing device for a propulsion power unit as claimed in claim 1, wherein the second part of the half-cowl is formed of at least two portions articulated to one another about an axis running parallel to the longitudinal axis of the propulsion power unit, a first of said portions being made as one piece with said first part of the lower half-cowl. 8. The fairing device for a propulsion power unit as claimed in claim 7, wherein said fairing device comprises at least one holding means for keeping the lower half-cowl in the open position. 9. The fairing device for a propulsion power unit as claimed in claim 8, wherein said holding means is an arm, a first end of the holding arm is pivot-mounted on the second end on said first part of the lower half-cowl and a second end of the holding arm catches on the pylon so as to immobilize the lower half-cowl in the open position. 10. The fairing device for a propulsion power unit as claimed in claim 9, wherein, in the open position, a center of gravity of the second portion of the lower half-cowl lies in a vertical plane passing through said first end of said holding arm. 11. The fairing device for a propulsion power unit as claimed in claim 1, wherein said fairing device comprises at least one holding means for keeping the lower half-cowl in the open position. 12. The fairing device for a propulsion power unit as claimed in claim 11, wherein said holding means is an arm, a first end of the holding arm is pivot-mounted on the second end on said first part of the lower half-cowl and a second end of the holding arm catches on the pylon so as to immobilize the lower half-cowl in the open position. 13. A propulsion power unit comprising the fairing device as claimed in claim 1. 14. The fairing device for a propulsion power unit as claimed in claim 1, wherein outer surfaces of the first part of the upper half-cowl and the first part of lower half-cowl directly face an outside of the engine.
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이 특허에 인용된 특허 (8)
Klamka Andrew ; Parham Dean Leon, Aircraft engine and associated aircraft engine cowl.
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