초록 ▼

An aircraft pylon is disclosed, the pylon including a strut, a modular fluid containment structure and a modular firewall. The strut presents an open structure and connects an aircraft external element to the aircraft. The fluid containment structure is associated with a fluid transfer component, wh

An aircraft pylon is disclosed, the pylon including a strut, a modular fluid containment structure and a modular firewall. The strut presents an open structure and connects an aircraft external element to the aircraft. The fluid containment structure is associated with a fluid transfer component, wherein the fluid containment structure contains escaped fluid from the fluid transfer component and channels the escaped fluid away from the aircraft. Both the fluid containment component and the firewall are modular and separable from the strut.

대표청구항 ▼

1. An aircraft pylon comprising: a strut for connecting an aircraft external element to the aircraft;a plurality of fluid transfer components extending from the aircraft to the aircraft external element; anda fluid containment structure associated with the fluid transfer components, the fluid contai

1. An aircraft pylon comprising: a strut for connecting an aircraft external element to the aircraft;a plurality of fluid transfer components extending from the aircraft to the aircraft external element; anda fluid containment structure associated with the fluid transfer components, the fluid containment structure including a sink structure positioned in an aft portion of the fluid containment structure and a shroud structure positioned in a forward portion of the fluid containment structure, the sink structure including a forward wall, an opposing aft wall, a bottom wall, and opposing side walls positioned between the forward wall and the aft wall, the forward wall including a plurality of openings for the fluid transfer components to pass therethrough, the side walls being angled downward from side edges toward the bottom wall to channel fluid onto the bottom wall, andthe shroud structure attached to the forward wall of the sink structure and including left and right sidewalls, a top wall, and a bottom wall that completely enclose at least a portion of the fluid transfer components, the shroud portion coupled to the forward wall of the sink portion and extending forward therefrom to the aircraft external element. 2. The aircraft pylon as set forth in claim 1, the strut presenting an open structure. 3. The aircraft pylon as set forth in claim 1, the fluid containment structure being supported by the strut. 4. The aircraft pylon as set forth in claim 1, wherein the sink portion cooperates with at least one pylon fairing panel to create an enclosed fluid containment volume. 5. The aircraft pylon as set forth in claim 1, the sink portion including a drain and configured to catch at least a portion of the escaped fluid and presenting at least one angled surface to channel the escaped fluid toward the drain. 6. The aircraft pylon as set forth in claim 1, the fluid containment structure including a drain for allowing the escaped fluid to exit the pylon away from a danger zone of the aircraft external element. 7. The aircraft pylon as set forth in claim 1, the fluid containment structure including a first attachment element for attaching the fluid containment structure to the strut, the first attachment element being integrally formed in the fluid containment structure. 8. The aircraft pylon as set forth in claim 7, the fluid containment structure including a second attachment element for attaching to at least one fairing, the second attachment element being integrally formed in the fluid containment structure. 9. The aircraft pylon as set forth in claim 1, wherein the strut presents a truss structure. 10. The aircraft pylon as set forth in claim 1, wherein the aircraft external element is an engine. 11. The aircraft pylon as set forth in claim 1, further comprising a fire barrier component interposed between the strut and the aircraft external element, the fire barrier component being modular and separable from the strut. 12. An aircraft pylon comprising: a strut for connecting an aircraft external element to the aircraft, the strut presenting an open structure; anda fire barrier component interposed between the strut and the aircraft external element, at least a portion of the fire barrier component being modular and separable from the strut, the fire barrier operable to provide a barrier between an aircraft engine and the strut, the fire barrier including an aft portion with a planar upper surface contacting a lower wall of the strut and a forward portion with a lower wall, a left sidewall, and a right sidewall whose inner surfaces face at least a portion of the outer surfaces of the lower wall, a left sidewall, and a right sidewall, respectively, of the strut. 13. The aircraft pylon of claim 12, the fire barrier component including attachment elements integrally formed therein for attaching the fire barrier component to the strut. 14. The aircraft pylon of claim 12, a first portion of the fire barrier forming part of the external element structure, and a second portion of the fire barrier being modular and separable from the strut and from the external element. 15. The aircraft pylon of claim 14, the aircraft external element including an engine, and the first portion of the fire barrier being integrally formed with a portion of a nacelle associated with the engine. 16. An aircraft engine pylon comprising: a strut for connecting an aircraft engine to an aircraft structure, the strut presenting a truss structure;a plurality of fluid transfer components extending from the aircraft structure to the aircraft engine;a fluid containment structure associated with the fluid transfer components, the fluid containment structure including a sink structure positioned in an aft portion of the fluid containment structure and a shroud structure positioned in a forward portion of the fluid containment structure, the sink structure including a forward wall, an opposing aft wall, a bottom wall, and opposing side walls positioned between the forward wall and the aft wall, the forward wall including a plurality of openings for the fluid transfer components to pass therethrough, the side walls being angled downward from side edges toward the bottom wall to channel fluid onto the bottom wall, andthe shroud structure including left and right sidewalls, a top wall, and a bottom wall that completely enclose at least a portion of the fluid transfer components, the shroud portion coupled to the forward wall of the sink portion and extending forward therefrom to the aircraft external element; anda fire barrier component interposed between the strut and the aircraft external element, at least a portion of the fire barrier component being modular and separable from the strut, the fire barrier operable to provide a barrier between an aircraft engine and the strut, the fire barrier including an aft portion with a planar upper surface contacting a lower wall of the strut and a forward portion with a lower wall, a left sidewall, and a right sidewall whose inner surfaces face at least a portion of the outer surfaces of the lower wall, a left sidewall, and a right sidewall, respectively, of the strut. 17. The aircraft engine pylon of claim 16, the fluid containment structure including a plurality of attachment elements for attaching the fluid containment structure to the strut, the attachment elements being integrally formed with the fluid containment structure. 18. The aircraft engine pylon of claim 16, the fluid containment structure including a plurality of attachment elements for attaching to one or more fairing panels. 19. A fire barrier system for an aircraft engine, the system comprising: a first fire barrier element placed on a first component of a thrust reverser positioned on a first side of the engine, the first fire barrier element including a first sidewall with a first lower edge;a second fire barrier element placed on a second component of the thrust reverser positioned on an opposing second side of the engine, the second fire barrier element including a second sidewall with a second lower edge; anda third fire barrier element secured to and surrounding a mount structure for mounting the engine onto a pylon,each of the elements arranged such that when the thrust reverser is in a closed position, the first fire barrier element, the second fire barrier element, and the third fire barrier element cooperate to form a firewall between the engine and the pylon, wherein the first sidewall and the second sidewall overlap the third fire barrier element and the first lower edge and the second lower edge contact a lower edge of the third fire barrier element. 20. The fire barrier system of claim 19, each of the elements arranged such that when the thrust reverser is in an open position, the first fire barrier element and the second fire barrier element are positioned to expose a portion of the pylon proximate the engine for inspection. 21. The fire barrier system of claim 19, wherein when the thrust reverser is in an open position, the first fire barrier element is separated from a first side of the third fire barrier element and the second fire barrier element is separated from an opposing second side of the third fire barrier element.