Abstract: Crack-free powder-based, near net shaped parts are fabricated using a die assembly and cold isostatic pressing. Soft materials are introduced on both sides of die components in order to balance compression loads applied to the die component, and thereby avoid deformation of the die component.

Abstract: Crack-free powder-based, near net shaped parts are fabricated using a die assembly and cold isostatic pressing. Soft materials are introduced on both sides of die components in order to balance compression loads applied to the die component, and thereby avoid deformation of the die component.

Abstract: Crack-free powder-based, near net shaped parts are fabricated using a die assembly and cold isostatic pressing. Soft materials are introduced on both sides of die components in order to balance compression loads applied to the die component, and thereby avoid deformation of the die component.

Abstract: Crack-free powder-based, near net shaped parts are fabricated using a die assembly and cold isostatic pressing. Soft materials are introduced on both sides of die components in order to balance compression loads applied to the die component, and thereby avoid deformation of the die component.

Abstract: Methods for making skin panels suitable for use in aircraft structures and fuel tank structures, such as fuselages and reusable launch vehicle propellant tanks. A first method includes the following steps: machining a starting plate to a final part geometry; and explosive forming the machined plate to at least one of a uniaxial curvature and a biaxial curvature. A second method includes the following steps: explosive forming a starting plate to at least one of a uniaxial curvature and a biaxial curvature; and machining the curved plate to a final part geometry. Accordingly, the invention enables making integrally stiffened unitized axial load carrying skin panels that are either uniaxially or biaxially curved.

Abstract: Methods for making skin panels suitable for use in aircraft structures and fuel tanks structures, such as fuselages and reusable launch vehicle propellant tanks. A first method includes the following steps: machining a starting plate to a final part geometry; and explosive forming the machined plate to at least one of a uniaxial curvature and a biaxial curvature. A second method includes the following steps: explosive forming a starting plate to at least one of a uniaxial curvature and a biaxial curvature; and machining the curved plate to a final part geometry. Accordingly, the invention enables making integrally stiffened unitized axial load carrying skin panels that are either uniaxially or biaxially curved.

Abstract: In one broad aspect the present invention comprises the steps of providing a titanium-based material preform and superplastically forming the preform to a final helmet shape. In another broad aspect, a first piece of fiber-reinforced titanium matrix composite material is hot isostatically pressed (HIP'ed) to form a side wall section. A second piece of fiber-reinforced titanium matrix composite material is hot pressed to form an upper dome section. The side wall section is then HIP/diffusion bonded to the upper dome section.

Abstract: The invention is a process for simultaneously improving at least two mechanical properties of mill-processed (.alpha.+.beta.) titanium alloy, which may or may not contain silicon, which includes steps of heat treating the mill-processed titanium alloy such that the (.alpha.+.beta.) microstructure of said alloy is transformed into an (.alpha.+.alpha..sub.2 +.beta.) microstructure, preferably containing no silicides. The heat treating steps involve subjecting the mill-processed titanium alloy to a sequence of thermomechanical process steps, and the mechanical properties which are simultaneously improved include (a) tensile strength at room, cryogenic, and elevated temperatures; (b) fracture toughness; (c) creep resistance; (d) elastic stiffness; (e) thermal stability; (f) hydrogen embrittlement resistance; (g) fatigue; and (h) cryogenic temperature embrittlement resistance. As a consequence of the process, the (.alpha.+.alpha..sub.2 +.beta.) microstructure contains equiaxed alpha phase strengthened with .alpha.

Abstract: A process for enhancing the bond strength of resistance welded joints between titanium alloy articles includes a first step of resistance welding two titanium alloy articles and a second step of heat treating the resistance welded titanium alloy articles in a vacuum or inert environment at temperatures in a range of 1675.degree. F. to 1825.degree. F. for a period of 15 minutes to 4 hours. The process of the present invention is particularly useful in providing efficient joining of face sheets to a honecomb core element.

Abstract: The invention is a process for simultaneously improving at least two mechanical properties of mill-processed (.alpha.+.beta.) titanium alloy, which may or may not contain silicon, which includes steps of heat treating the mill-processed titanium alloy such that the (.alpha.+.beta.) microstructure of said alloy is transformed into an (.alpha.+.alpha..sub.2 +.beta.) microstructure, preferably containing no silicides. The heat treating steps involve subjecting the mill-processed titanium alloy to a sequence of thermomechanical process steps, and the mechanical properties which are simultaneously improved include (a) tensile strength at room, cryogenic, and elevated temperatures; (b) fracture toughness; (c) creep resistance; (d) elastic stiffness; (e) thermal stability; (f) hydrogen embrittlement resistance; (g) fatigue; and (h) cryogenic temperature embrittlement resistance. As a consequence of the process, the (.alpha.+.alpha..sub.2 +.beta.) microstructure contains equiaxed alpha phase strengthened with .alpha.

Abstract: A method for thermomechanically processing gamma titanium aluminide alloy wrought products comprises the following steps: a) a near gamma titanium aluminide alloy ingot is cast; b) the ingot is hot isostatically pressed (HIP'ed) to seal off casting defects; c) the HIP'ed ingot is prepared into suitable forging preforms with or without intermediate homogenization heat treatment; d) the forging preforms are isothermally forged into suitable end product preforms at temperatures sufficiently close to the phase line between the alpha+gamma and alpha-two+gamma phase fields so as to break down the ingot microstructure and to yield a largely equiaxed gamma microstructure; and e) the end product preforms are processed into the desired wrought end products through a controlled rolling process or a closed-die forging operation.