Abstract: A wing may include a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer may be characterized by a stacked plurality of generally planar plies of reinforcement material structurally joined as a stack to an interior surface of the wing skin and extending generally parallel to the interior surface and a span-wise direction of the wing along a substantial portion of the interior surface. The first stringer may have a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction. The rib may be positioned adjacent the interior surface, and may extend generally perpendicular to the span-wise direction. The trapezoidal cross section may be interfaced with the rib flange. The fastener may extend through the wing skin, the trapezoidal cross section, and the rib flange.

Abstract: A wing may include a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer may be characterized by a stacked plurality of generally planar plies of reinforcement material structurally joined as a stack to an interior surface of the wing skin and extending generally parallel to the interior surface and a span-wise direction of the wing along a substantial portion of the interior surface. The first stringer may have a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction. The rib may be positioned adjacent the interior surface, and may extend generally perpendicular to the span-wise direction. The trapezoidal cross section may be interfaced with the rib flange. The fastener may extend through the wing skin, the trapezoidal cross section, and the rib flange.

Abstract: The invention is directed to a process and more particularly, to utilizing polymer solutions to make thick film compositions. In one embodiment the process is directed to the formation of photoimageable thick film compositions for use in photo-patterning methods to make photoimageable electrodes in flat panel display applications, including plasma display panels (PDP). Polymer solutions are obtained by directly polymerizing desired monomers in a desired solvent to form a desired polymer, rather than by dissolving a pre-made polymer in a desired solvent. Other ingredients are added to the polymer solution to directly form thick film pastes, including photoimageable thick film pastes.

Abstract: The invention is directed to a screen-printable getter composition comprising: (a) glass frit; and (b) pre-hydrated desiccant material; dispersed in (c) organic medium. The present invention further relates to a getter composition utilizing low-softening temperature glasses comprising, based on weight %, 1-50% SiO2, 0-80% B2O3, 0-90% Bi2O3, 0-90% PbO, 0-90% P2O5, 0-60% Li2O, 0-30% Al2O3, 0-10% K2O, 0-10% Na2O, and 0-30% MO where M is selected from Ba, Sr, Ca, Zn, Cu, Mg and mixtures thereof. The glasses described herein may contain several other oxide constituents that can substitute glass network-forming elements or modify glass structure. The desiccant material is pre-hydrated to reach its saturation level of moisture absorption. The process of pre-hydration can be done by exposing the desiccant in a normal temperature/humidity environment of for example, 25° C. and 50-60% RH. for 24 to 48 hours or up to the time when weight gain (due to moisture absorption) stops increasing.

Abstract: This invention is directed to a process for the fabrication of features on a silicon wafer utilizing fibers comprising organic polymer and inorganic material.

Abstract: This invention is directed to a process for the fabrication of features on a silicon wafer utilizing ribbons comprising organic polymer and inorganic material.

Abstract: This invention is directed to a process for the fabrication of features on a silicon wafer utilizing ribbons comprising organic polymer and inorganic material.

Abstract: A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge, forming a plurality of slots in the pressure side of the airfoil extending towards the trailing edge, and extending a plurality of pins arranged in rows between the airfoil suction and pressure sides, such that at each of a first row of pins has a substantially elliptical cross-sectional area, wherein the first row of pins is between the remaining rows of pins and the airfoil pressure side slots.

Abstract: A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge, forming a plurality of slots in the pressure side of the airfoil extending towards the trailing edge, and extending a plurality of pins arranged in rows between the airfoil suction and pressure sides, such that at each of a first row of pins has a substantially elliptical cross-sectional area, wherein the first row of pins is between the remaining rows of pins and the airfoil pressure side slots.