Abstract: A synergistic blade and hub structure for a cooling fan. Helical gussets are provided which proceed from the central hub member adjacent one blade member to the trailing edge of an adjacent blade member. The helical gussets provide structural load paths as well as aerodynamic flow guides. The helical gussets extend axially rearwardly to the trailing edges of preceding blade members and provide structural attachments between the leading and trailing edges of adjacent blade members. Hollow triangular structures are also provided on the rear of the fan structure and the triangulation area provides superior stiffness.

Abstract: A synergistic blade and hub structure for a cooling fan. Helical gussets are provided which proceed from the central hub member adjacent one blade member to the trailing edge of an adjacent blade member. The helical gussets provide structural load paths as well as aerodynamic flow guides. The helical gussets extend axially rearwardly to the trailing edges of preceding blade members and provide structural attachments between the leading and trailing edges of adjacent blade members. Hollow triangular structures are also provided on the rear of the fan structure and the triangulation area provides superior stiffness.

Abstract: A cooling fan (10) includes a plurality of blades (12) molded about a central hub plate (11) at an annular molded ring (13). A plurality of helical gussets (30) are formed on inlet side (25) of the molded ring (13) at the blade root (15) that are spaced apart to define flow gaps (32) therebetween, and are curved to substantially follow the airflow path through those gaps (32). A like plurality of radial ribs (40) may be formed at the outlet side (26) of the fan (10) that can include an indented stacking surface (41) that engages a contact surface (42) on the inlet side (25) to facilitate stacking of multiple fans. In another aspect, the fan blades (10) are configured to include elliptical or parabolic camber lines (C) that vary along the radial length of the blade so that the blade stacking, or the centers of gravity (CG) of radial blade segments, achieve a predetermined alignment under normal operating loads to minimize bending moments between blade sections.

Abstract: A method of producing a rocket combustion chamber/nozzle assembly in which a liner blank is deformed against the forming surface of a die to form a finished cooling liner, a structural jacket is electro-formed about the finished cooling liner, and fluid manifolds are secured to the finished cooling liner and structural jacket assembly.