Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load shell structure and a plurality of struts. The single point load shell structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load shell structure to the mount.

Abstract: An expandable mid-turbine frame assembly includes a first bearing cone, a second bearing cone and a mid-turbine frame. The mid-turbine frame assembly connects to a gas turbine engine casing and transfers a first load from a first bearing and a second load from a second bearing towards the engine casing. The first bearing cone transfers the first load from the first bearing. The second bearing cone transfers the second load from the second bearing. The mid-turbine frame is connected to the first and second bearing cones and includes segments. Each segment includes a pre-stressed support for equilibrating the first and second loads.

Abstract: An engine casing for a mid-turbine frame having a plurality of radially extending struts includes a ring structure and at least one mount. The ring structure has an interior surface, an exterior surface, and a plurality of equally spaced dimples along the exterior surface and protruding from the interior surface. The ring structure is connected to each of the plurality of struts at the interior surface at the dimples. The mount is positioned within each of the dimples and transfers load to the engine casing.

Abstract: A mid-turbine frame has a pre-stress design and is connected to an engine casing of a jet turbine engine to distribute a first load from a first bearing and a second load from a second bearing. The mid-turbine frame includes at least one torque box, a first bearing, a second bearing, and at least one strut. The torque box absorbs the first and second loads. The first bearing cone connects the first bearing to the torque box and the second bearing cone connects the second bearing to the torque box. The strut connects the torque box to the engine casing.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a plurality of inverted panels and a plurality of struts. The inverted panels convert the first and second loads to a shear flow. The struts are connected to the inverted panels and transfer the shear flow to the mount.

Abstract: A mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a single point load structure and a plurality of struts. The single point load structure combines the first load and the second load into a combined load. The plurality of struts is connected to the single point load structure and transfers the combined load from the single point load structure to the mount.

Abstract: The present invention provides a magnet support structure. A cylindrical portion comprises a plurality of laminated composite layers concentrically assembled to one another along a longitudinal axis. An integral left flange is comprised of the laminated composite layers concentrically assembled with respect to a left flange axis. The left flange axis is perpendicular to the longitudinal axis. An integral right flange is comprised of the laminated composite layers concentrically assembled with respect to a right flange axis. The right flange axis is perpendicular to the longitudinal axis. A method for fabricating the magnet support structure comprises concentrically assembling the plurality of laminated composite layers along the longitudinal axis forming the cylindrical portion. Concentrically assembling the laminated composite layers with respect to the left flange axis forming the integral left flange.

Abstract: The present invention provides a magnet support structure. A cylindrical portion comprises a plurality of laminated composite layers concentrically assembled to one another along a longitudinal axis. An integral left flange is comprised of the laminated composite layers concentrically assembled with respect to a left flange axis. The left flange axis is perpendicular to the longitudinal axis. An integral right flange is comprised of the laminated composite layers concentrically assembled with respect to a right flange axis. The right flange axis is perpendicular to the longitudinal axis. A method for fabricating the magnet support structure comprises concentrically assembling the plurality of laminated composite layers along the longitudinal axis forming the cylindrical portion. Concentrically assembling the laminated composite layers with respect to the left flange axis forming the integral left flange.

Abstract: An energy management system comprises: an energy storage system comprising flywheels and batteries; and an energy storage system controller adapted to cause the flywheels and batteries to store energy during load-supplying periods and to supply energy during load-receiving periods. The flywheels may be situated in respective ones of a plurality of compartments in a vehicle platform, and the batteries may be situated above the flywheels.

Abstract: A laminated composite shell assembly includes composite shells assembled together and having joint bonds connecting the assembly with an external structure and pinch rings assembled to the shells adjacent the joint bonds so as to reinforce the same. The composite shells and pinch rings are cylindrical in configuration and made of layers of graphite-epoxy material having fibers oriented in desired stacking sequences. The shells and pinch rings are concentrically assembled in a desired sequence with some of the shells being adapted to perform a structural load bearing function while others of the shells are adapted to perform a load transfer function and with the pinch rings adapted to perform additional stiffening as well as load redistributing and transfer functions in the regions of the joint bonds between the assembled shells and the external structure.

Abstract: A uniform stiffness laminated composite shell assembly includes a plurality of composite shells. The shells are made of layers of laminates of graphite-epoxy material having fibers oriented in various stacking sequences for performing different functions in the assembly. The shells are concentrically assembled in a desired sequence with some of the adjacent ones of the shells being at least equal to or greater in axial length than others thereof and with some of the shells being adapted to perform a structural load bearing function while others of the shells being adapted to perform a load transfer function. The desired sequence of shells of the composite shell assembly provides enhanced thermal insulating properties and efficient load distributing properties for enabling use of the assembly as a tube suspension in a superconductive magnet.

Abstract: A superconductive magnet includes a superconductive coil assembly having a cryogenic vessel, a thermal shield enclosing the cryogenic vessel, and a vacuum enclosure enclosing the thermal shield. The cryogenic vessel, thermal shield and vacuum vessel have annular shells radially spaced apart from one another with reference to a common longitudinal axis and coaxially aligned with the common longitudinal axis. The magnet also includes a tube suspension assembly having a plurality of tubes located between respective ones of the cryogenic vessel, thermal shield and vacuum enclosure. The tubes are axially overlapped and are interconnected with one another and with the cryogenic vessel, thermal shield and vacuum enclosure. One tube has an end forming a sliding joint with the cryogenic vessel that allows both radial and axial movement of the cryogenic vessel relative to the thermal shield and vacuum enclosure during cooldown of the cryogenic vessel from ambient to cryogenic temperatures.