Abstract: A centerbody assembly includes a center tube, a forward bulkhead, an aft bulkhead, at least one baffle, and an outer skin. The center tube extends circumferentially about an axial centerline. The center tube extends between and to a first axial tube end and a second axial tube end. The forward bulkhead is mounted to the center tube at the first axial tube end. The aft bulkhead is mounted to the center tube at the second axial tube end. The at least one baffle extends axially from the forward bulkhead to the aft bulkhead. At least the forward bulkhead, the aft bulkhead, or the at least one baffle include one or more thermal beads. The outer skin circumscribes the center tube, the forward bulkhead, the aft bulkhead, and the at least one baffle to form an acoustic cavity radially inside the outer skin.

Abstract: A wall structure is provided for an aircraft. This wall structure includes a first wall section, a second wall section and a fastener system fastening the second wall section to the first wall section. The second wall section includes an aperture extending axially along an axis through the second wall section. The second wall section is axially spaced from the first wall section. The fastener system includes a mount and a retainer. The mount is connected to the first wall section. The mount includes a post that projects axially into the aperture. The retainer includes a head and a spring clip connected to the head. The head axially engages the second wall section. The spring clip is disposed in the aperture and is mated with the post.

Abstract: A fluid conduit assembly is provided that includes a first conduit coupler, a second conduit coupler and a lock. The second conduit coupler is mated with the first conduit coupler at a threaded interface. The lock is configured to rotationally fix the first conduit coupler with the second conduit coupler. The lock includes a flange, a clip and a fastener. The flange is arranged with the first conduit coupler. The flange is configured with a plurality of flange apertures arranged circumferentially about an axis of the first conduit coupler. The clip is arranged with the second conduit coupler. The clip is configured with a clip aperture. The fastener is mated with the clip aperture and any one of the plurality of flange apertures.

Abstract: An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a first end configured to deliver heated gas to a plenum and a second end spaced from the first end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a seal system disposed proximate the second end, the seal system including a first annular seal having a radially inner end positioned proximate a flange disposed on the inner duct.

Abstract: A fluid conduit assembly is provided that includes a first conduit coupler, a second conduit coupler and a lock. The second conduit coupler is mated with the first conduit coupler at a threaded interface. The lock is configured to rotationally fix the first conduit coupler with the second conduit coupler. The lock includes a flange, a clip and a fastener. The flange is arranged with the first conduit coupler. The flange is configured with a plurality of flange apertures arranged circumferentially about an axis of the first conduit coupler. The clip is arranged with the second conduit coupler. The clip is configured with a clip aperture. The fastener is mated with the clip aperture and any one of the plurality of flange apertures.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a first component, a second component and a tubular fire seal. The first component includes a first passage. The second component includes a second passage. The tubular fire seal seals a gap between the first component and the second component. The tubular fire seal includes an outer shroud. At least a portion of the outer shroud has a wavy sectional geometry. The first passage is fluidly coupled with the second passage through an inner bore of the tubular fire seal.

Abstract: An aircraft cowl arrangement may comprise a first half, and a second half rotatable between an open position and a closed position, a first seal coupled to the first half, a second seal coupled to the second half, and a latch arrangement for preventing relative movement between the first half and the second half. The latch arrangement may comprise a tie rod comprising a first end coupled to the first half, a second end, and a frame having an opening for receiving the second end of the tie rod, a latch handle rotatably mounted to the frame, and a hook operably coupled to the latch handle, wherein the latch handle is configured to move between a first position wherein the hook is engaged with the second end of the tie rod and a second position wherein the hook is disengaged from the second end of the tie rod.

Abstract: An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a first end configured to deliver heated gas to a plenum and a second end spaced from the first end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a seal system disposed proximate the second end, the seal system including a first annular seal having a radially inner end positioned proximate a flange disposed on the inner duct.

Abstract: A portable exercise device for exercising the muscles of the upper body and thighs. The device comprises a pair of elongate members having a body engaging element for receiving the thighs of the user to hold the device in a stable, fixed position, a spring portion that joins the elongate members in a generally parallel configuration, and optionally a pair of handgrips at the ends of the elongate members. Methods of using the device of the invention are also provided.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a first component, a second component and a tubular fire seal. The first component includes a first passage. The second component includes a second passage, The tubular fire seal seals a gap between the first component and the second component. The tubular fire seal includes an outer shroud. At least a portion of the outer shroud has a wavy sectional geometry. The first passage is fluidly coupled with the second passage through an inner bore of the tubular fire seal.

Abstract: An aircraft cowl arrangement may comprise a first half, and a second half rotatable between an open position and a closed position, a first seal coupled to the first half, a second seal coupled to the second half, and a latch arrangement for preventing relative movement between the first half and the second half. The latch arrangement may comprise a tie rod comprising a first end coupled to the first half, a second end, and a frame having an opening for receiving the second end of the tie rod, a latch handle rotatably mounted to the frame, and a hook operably coupled to the latch handle, wherein the latch handle is configured to move between a first position wherein the hook is engaged with the second end of the tie rod and a second position wherein the hook is disengaged from the second end of the tie rod.

Abstract: A portable exercise device for exercising the muscles of the upper body and thighs. The device comprises a pair of elongate members having a body engaging element for receiving the thighs of the user to hold the device in a stable, fixed position, a spring portion that joins the elongate members in a generally parallel configuration, and optionally a pair of handgrips at the ends of the elongate members. Methods of using the device of the invention are also provided.

Abstract: Methods and fire sealing systems for a panel of a gas turbine engine are provided. The fire sealing systems include a thermal blanket mounted on the panel, the thermal blanket having a close-out and defining a seal landing at a periphery edge of the panel, a seal retainer mounted to the panel along the seal landing, and a fire seal securely retained within the seal retainer, wherein at least one of the seal retainer or the fire seal comprises an extension portion and a blanket engaging portion such that a close-out volume formed between the thermal blanket and the fire seal above the close-out of the thermal blanket is enclosed.

Abstract: An assembly is provided for an aircraft propulsion system. The assembly includes a first component, a second component and a seal assembly configured to seal a gap between the first and the second components. The seal assembly includes a metal spring seal element and an elastomeric seal element. The metal spring seal element is mounted to the first component. The metal spring seal element is sealingly engaged with the second component. The elastomeric seal element is mounted to the metal spring seal element. The elastomeric seal element is sealingly engaged with the second component.

Abstract: An assembly is provided for an aircraft propulsion system. The assembly includes a first component, a second component and a seal assembly configured to seal a gap between the first and the second components. The seal assembly includes a metal spring seal element and an elastomeric seal element. The metal spring seal element is mounted to the first component. The metal spring seal element is sealingly engaged with the second component. The elastomeric seal element is mounted to the metal spring seal element. The elastomeric seal element is sealingly engaged with the second component.

Abstract: Methods and fire sealing systems for a panel of a gas turbine engine are provided. The fire sealing systems include a thermal blanket mounted on the panel, the thermal blanket having a close-out and defining a seal landing at a periphery edge of the panel, a seal retainer mounted to the panel along the seal landing, and a fire seal securely retained within the seal retainer, wherein at least one of the seal retainer or the fire seal comprises an extension portion and a blanket engaging portion such that a close-out volume formed between the thermal blanket and the fire seal above the close-out of the thermal blanket is enclosed.

Abstract: A hybrid inner fixed structure is disclosed. The inner fixed structure may have an inner fixed structure panel having an inner fixed structure panel surface and an inset panel having an inset panel surface disposed in at least partial contact with a first portion of the inner fixed structure panel surface. In this manner, a hybrid inner fixed structure may be designed to be both lightweight and heat tolerant.

Abstract: A mounting system for a fire detection system for a turbofan engine propulsion system is provided to mount fire detection sensors on the inner fixed structure (IFS) of the nacelle. The mounting system mounts to an inner, engine facing surface of the IFS. Two IFS halves cooperate to form a substantially enclosed space around an engine core. The mounting system includes part of a fastening system mounted to the IFS, and an orientation clip mounted to a thermal blanket. Brackets for mounting the fire detection system sensing wires are positioned on the orientation clip, and the fastening system fixes the bracket to the IFS and traps the thermal blanket therebetween.

Abstract: An air scoop includes a base which is attachable to a nacelle of a turbomachine, an air outlet defined in the base, and a scoop body disposed on the base and defining a scoop inlet. The scoop inlet is in fluid communication with the air outlet to supply scoop air to the air outlet. The air scoop also includes separator lip extending from the base to the scoop inlet which spaces the scoop inlet apart from the base to raise the scoop body above liquids streaking along the base.