Abstract: An improved barrel for use in a weapon includes a housing which is cast as one piece of a directionally solidified superalloy which is free of generally spherical, randomly oriented crystals. The housing has first properties in a direction extending parallel to its central axis and properties which are different than the first properties in a direction transverse to the central axis of the housing. The superalloy forming the housing may be directionally solidified with a columnar grain crystallographic structure. Alternatively, the superalloy of the housing may be directionally solidified with a plurality of single crystal sections, one or more of which extend between opposite end portions of the housing. As another alternative, the superalloy may be directionally solidified as a single crystal which extends between opposite end portions of the housing.

Abstract: The present invention provides a new and improved method of forming a turbine engine component having a plurality of airfoils disposed in an annular array between inner and outer shroud rings. The method includes forming inner and outer shroud ring patterns. The inner and outer shroud ring patterns may advantageously be formed by solid freeform fabrication techniques, such as stereolithography. An assembly fixture may be utilized to position the inner and outer shroud rings and an array of airfoils in a coaxial relationship. When the inner and outer shroud rings are to be assembled, axially inner and outer shroud ring patterns may be interconnected by providing relative rotation between annular sections of the shroud ring patterns. In addition, adhesive may be utilized to interconnect the sections of the shroud ring patterns.

Abstract: The present invention provides a new and improved method of forming a turbine engine component having a plurality of airfoils disposed in an annular array between inner and outer shroud rings. The method includes forming inner and outer shroud ring patterns. The inner and outer shroud ring patterns may advantageously be formed by solid freeform fabrication techniques, such as stereolithography. An assembly fixture may be utilized to position the inner and outer shroud rings and an array of airfoils in a coaxial relationship. When the inner and outer shroud rings are to be assembled, axially inner and outer shroud ring patterns may be interconnected by providing relative rotation between annular sections of the shroud ring patterns. In addition, adhesive may be utilized to interconnect the sections of the shroud ring patterns.

Abstract: A drainmast (10) for discharging liquid from a moving aircraft (12). The drainmast (10) includes a fairing (20) having a mounting flange (24), a flow-controlling cap (26), and an aerodynamically advantageous mast (28) extending therebetween. The flow-controlling cap (26) has a lower surface defining an airflow-redirecting zone, a liquid-release zone, and a liquid-recirculation zone. The redirecting zone is shaped to redirect airflow (A) into the release zone in a direction parallel to the discharge direction (D) of the drain tube (22). The release zone is shaped to encourage the redirected airflow (Aredir) to sweep a substantial portion of the released liquid away from the fairing in a primary flow path (L). The recirculation zone captures escaped liquid from the release zone and recirculates this escaped liquid back into the release zone in recirculation flow path (Lrec1). The rear and side surfaces of the cap (26) may include a continuous groove (66) aligned with the airflow direction A.

Abstract: An aircraft deicer panel (10) including an inner support layer (20) which is electrically insulating, an outer cover layer (26) which is thermally conducting, a heater layer (22) which is electrically insulating, and an electrical heating element (28) attached to the heater layer (22). The heating element (28) comprises an electrically conductive strand (30) stitched in the layer (22) in a heat-dissipating pattern such as, for example, a winding path of closely spaced and sharply curved turns formed by a continuous length of the electrically conductive strand (30). During manufacture of the aircraft panel (10), an industrial sewing machine can be programmed to stitch the desired pattern of the electrically conductive strand (30).

Abstract: A drainmast (10) for discharging liquid from a moving aircraft (12). The drainmast (10) includes a fairing (20) having a mounting flange (24), a flow-controlling cap (26), and an aerodynamically advantageous mast (28) extending therebetween. The flow-controlling cap (26) has a lower surface defining an airflow-redirecting zone, a liquid-release zone, and a liquid-recirculation zone. The redirecting zone is shaped to redirect airflow (A) into the release zone in a direction parallel to the discharge direction (D) of the drain tube (22). The release zone is shaped to encourage the redirected airflow (Aredir) to sweep a substantial portion of the released liquid away from the fairing in a primary flow path (L). The recirculation zone captures escaped liquid from the release zone and recirculates this escaped liquid back into the release zone in recirculation flow path (Lrec1). The rear and side surfaces of the cap (26) may include a continuous groove (66) aligned with the airflow direction A.