The Boeing Company

Other

Benjamin P Van Kampen

Mark Alan Shelly

Theron Lee Cutler

James A Carns

Theron L Cutler

Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems. A representative fitting includes a first member having a flange and a barrel. The barrel further includes a passageway. A first flange seal is positioned at a face of the flange and can be sealably coupled to a surface, for example, a tank wall. A second flange seal is disposed outwardly from the first flange seal to seal against the surface. The fitting further includes a second member positioned within the passageway of the barrel. The fitting further includes first and second barrel seals positioned between the barrel and the second member.

Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems

Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, are disclosed herein. An aircraft system in accordance with one embodiment of the invention includes a fluid conduit carried by an aircraft and a housing fixedly attached to the fluid conduit. The housing can include a first attachment feature having one of a projection extending outwardly from the housing or an aperture extending at least partially through the housing. The system further includes a support member having an attachment portion positioned proximate to the attachment feature. The attachment portion includes a support member aperture positioned over at least a portion of the first attachment feature. An adjustable fitting couples the support member to the housing. The adjustable fitting can include a first side, a second side opposite the first side, and an engagement portion at the second side positioned within at least a portion of the support member aperture. The fitting can also include a second attachment feature mated with the first attachment feature. The second attachment feature includes the other one of the projection or the aperture. The second attachment feature has a center point eccentrically offset from a center point of the fitting.

Adjustable fittings for attaching support members to fluid conduits, including aircraft fuel conduits, and associated systems and methods

Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits. An aircraft configured in accordance with one embodiment of the invention includes a fuselage portion, a wing portion, and a fuel tank carried by least one of the fuselage portion and the wing portion. The aircraft also includes a spar carried by at least one of the fuselage portion and the wing portion. The spar includes a first spar rib and a second spar rib spaced apart from the first spar rib. The aircraft further includes a fluid conduit proximate to the spar and operably coupled to the fuel tank. A support member carrying the fluid conduit is operably coupled to the spar. The support member can be positioned to transfer at least approximately all of the axial loads from the fluid conduit to at least one of the first spar rib and the second spar rib.

Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits

Fittings with redundant seals for aircraft fuel lines, fuel tanks, and other systems are disclosed. A fitting in accordance with one embodiment can be positioned adjacent to an aperture in a fuel tank wall having an inner surface and an outer surface. The fitting can include a first member having a flange and a barrel. The barrel can further include a passageway. A first flange seal can be positioned at a face of the flange and can be sealably coupled to a surface, for example, the tank wall. A second flange seal can be disposed outwardly from the first flange seal against the surface. The fitting can further include a second member (e.g., a sensor) positioned within the passageway of the barrel. The fitting can further include first and second barrel seals positioned between the barrel and the second member.

A shrouded valve apparatus including an outer conduit, an inner conduit disposed within the outer conduit, and a valve member operable to regulate flow through the inner conduit. This apparatus is useful in shrouded aircraft fuel systems.

Shrouded valve apparatus and related methods

Systems and methods for distributing loads from fluid conduits, including aircraft fuel conduits, are disclosed. An aircraft configured in accordance with one embodiment of the invention includes a fuselage portion, a wing portion, and a fuel tank carried by least one of the fuselage portion and the wing portion. The aircraft also includes a spar carried by at least one of the fuselage portion and the wing portion. The spar includes a first spar rib and a second spar rib spaced apart from the first spar rib. The aircraft further includes a fluid conduit proximate to the spar and operably coupled to the fuel tank. A support member carrying the fluid conduit is operably coupled to the spar. The support member can be positioned to transfer at least approximately all of the axial loads from the fluid conduit to at least one of the first spar rib and the second spar rib.

System and methods for distributing loads from fluid conduits, including aircraft fuel conduits

Valves for annular conduits and associated systems and methods are disclosed. A fluid transmission system in accordance with one embodiment of the invention includes a first conduit having a first wall aligned with a flow direction in the first conduit and a second conduit disposed annularly around the first conduit with a second wall aligned with the flow direction. An access channel can be positioned to have an aperture in fluid communication with the first conduit and can be isolated from fluid communication with the second conduit. A valve element can be positioned in fluid communication with the access channel and can be movable between a first position and a second position, with the valve element being positioned to allow a first amount of flow through the access channel when in the first position and being positioned to allow no flow or a second amount of flow less than the first amount of flow through the access channel when in the second position. The valve can be installed in aircraft fuel lines or other systems.

Growing community of inventors

Wichita, KS, United States of America

Benjamin P Van Kampen