Abstract: A rotor for an aircraft engine includes a hub having a rotation axis, a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections defined by opposite edges of a structural member of the structural members that corresponds to that cross-section, and a circumferential array of airfoils extending radially outward from the annular ring.

Abstract: A rotor for an aircraft engine includes a hub having a rotation axis, a circumferential array of structural members extending radially outward from the hub to an annular ring, the structural members having cross-sections that increase in length as the structural members extend from the hub to the annular ring, the length of each cross-section of the cross-sections defined by opposite edges of a structural member of the structural members that corresponds to that cross-section, and a circumferential array of airfoils extending radially outward from the annular ring.

Abstract: A gas turbine engine rotor disk has a single-piece hub with a radially-outer surface, and with an annular cavity inside the single-piece hub. The annular cavity is defined by a radially-elongated cross-sectional profile revolved at least partly about the axis of rotation. Blades extend outwardly from the radially-outer surface.

Abstract: A gas turbine engine rotor disk has a single-piece hub with a radially-outer surface, and with an annular cavity inside the single-piece hub. The annular cavity is defined by a radially-elongated cross-sectional profile revolved at least partly about the axis of rotation. Blades extend outwardly from the radially-outer surface.

Abstract: The turbine exhaust structure for a gas turbine engine includes a turbine exhaust duct and a bearing housing. The turbine exhaust duct includes annular inner and outer case portions radially spaced apart to define an annular gas path therebetween and a plurality of struts extending between and structurally interconnecting the inner and outer case portions. The struts are circumferentially spaced apart about within the annular gas path. The bearing housing is disposed within the inner case portion of the turbine exhaust duct. A plurality of structural ribs extend between the bearing housing and the inner annular case portion. The structural ribs are circumferentially spaced from one another and are circumferentially offset from the struts.

Abstract: The compressor inlet can have two walls forming an annular fluid path with a radial inlet end, and a support structure extending axially between the two walls, the support structure having a plurality of circumferentially-interspaced supports, each one of the plurality of supports extending freely between the two walls across the radial inlet end of the annular fluid path, each support having at least one node at an intermediary location between the two walls, at least one branch extending from the node to a first one of the walls, and at least two branches branching off from the node and leading to the second one of the walls.