Senior IP Gmbh

Eric M Possert

Christopher Thompson

Muhannad Owdeh

Matthew J Parker

Karim Ali

Shailesh N Mistry

Matthew Parker

Shailesh Mistry

A sealed joint assembly for transmitting high temperature and high pressure fluid between adjoining ducts in, for example, an aircraft bleed air system, includes a gimbal ring and two annular clevises. Each clevis includes a pair of axially-extending lobes that each includes a bore hole extending therethrough. The bore holes of the clevis lobes may each align with a respective bore hole formed within the gimbal ring, through which a pin may be inserted to couple the clevises to the gimbal ring. The clevises and gimbal ring may be formed using additive manufacturing. The gimbal ring may include a strut or truss network, and may be comprised of an inner gimbal ring and an outer gimbal ring.

Gimbal joints for bleed air systems

A sealed joint assembly for transmitting high temperature and high pressure fluid between adjoining ducts in, for example, an aircraft bleed air system, includes a gimbal ring and two annular clevises. Each clevis includes a pair of axially-extending lobes that each includes a bore hole extending therethrough. The bore holes of the clevis lobes may each align with a respective bore hole formed within the gimbal ring, through which a pin may be inserted to couple the clevises to the gimbal ring. The clevises and gimbal ring may be formed using additive manufacturing, to produce component geometries and topologies that reduce the overall weight of the joint assembly while maintaining or improving its structural integrity. For example, the clevis lobes may include a plurality of gaps, such that the remaining material forms a shear web. The gimbal ring may also include strut or truss networks to enhance structural integrity.

An integrated drain mast structure for use in draining fluids emanating from aircraft components, such as turbine engines and fuselages, for facilitating the detection of fluids leaking from said components. A self-supporting tube section including a plurality of generally aligned fluid passages each having a peripheral wall, at least a portion of which is common with at least a portion of another aligned adjacent fluid passage is connected to one or more of these aircraft components. An aerodynamic fairing includes a plurality of fairing fluid passages each connected to a respective fluid passage of the tube section and having respective fluid outlets. The tube section and fairing section can comprise a single integral structure.

Integrated drain mast structure

A manifold assembly configured for integration with a joint cover apparatus in a ducting system to detect leaking gas comprises an elastomeric manifold block having a substantially circular inlet aperture and one or more gas passages fluidly coupled to the inlet aperture. The assembly includes a flow control valve configured to maintain a closed state in which a component of the flow control valve sealingly engages with the inlet aperture to preclude gas at the inlet aperture from flowing into the one or more gas passages until said gas reaches a pressure corresponding to a pressure threshold. The assembly also includes at least one aperture control plate disposed substantially proximate to a lower end of the manifold block and including a substantially circular opening. The aperture control plate is adapted to maintain the substantial circularity of the inlet aperture, so as to ensure a substantially fluid-tight seal.

Joint cover with improved manifold block for duct leak detection system

A compensator junction assembly for carrying pressurized hot gases in an aircraft ducting system comprises a substantially spherical inner race having at least three apertures and at least three corresponding retainer assemblies, where the apertures in the retainer assemblies align with the apertures in the inner race, and at least three outer races, each having apertures generally aligned with the at least three inner race apertures, respectively. The retainer assemblies may include at least one bottom channel and at least one top channel for receiving one or more bearings and seals. Spherically rotational movement of the retainer assemblies between the inner and outer races accommodates stresses caused by the pressurized hot gases and external forces.

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Pacoima, CA, United States of America

Eric M Possert