Abstract:
PROBLEM TO BE SOLVED: To manufacture a light air foil, having rigidity adaptable to a load generated by a gas turbine engine, at a low cost. SOLUTION: An air foil 30 of which, for example, a fan outlet guide vane consists has a body with geometrical cross section comprising a first wall 44; a second wall 46 arranged opposite to the first wall; a front edge 48; a rear edge 50 arranged opposite to the front edge; and at least one of cavities 52 and 54. The cavities 52 and 54 are formed between the first and second walls 44 and 46 and between the front and rear edges 48 and 50. The air foil 30 is extrusion-molded by using non-continuous reinforced aluminum such that the body with geometrical cross section is extended between first and second ends.
Abstract:
PROBLEM TO BE SOLVED: To provide an aluminum alloy having excellent mechanical properties at the temperature up to about 300 deg.C. SOLUTION: This aluminum alloy strengthened by high strength dispersion consists of an aluminum solid solution matrix strengthened by the dispersion of particles based on a compound Al3X having an L12 structure. Various alloy elements are used so that the matrix and particles have similar lattice constants, thus the lattice constants of the matrix and particles are modified. The alloy is produced from a melt by rapid solidification.
Abstract:
A method of making an aluminum airfoil includes brazing a first airfoil piece and a second airfoil piece together using a braze material that includes an element selected from magnesium and zinc, to form a braze joint between the first airfoil piece and the second airfoil piece. At least one of the first airfoil piece or the second airfoil piece has an aluminum alloy composition that includes greater than 0.8% by weight of zinc.
Abstract:
A method for forming an article by introducing one or more powders into a bag. Vacuum is applied to the bag. The bag is sealed. The one or more powders in the sealed bag are forged.
Abstract:
An airfoil includes an airfoil body that extends at least between leading and trailing edges, first and second sides, and radially inner and outer ends. The airfoil body includes an aluminum alloy that has a controlled crystallographic texture with respect to a predefined three-dimensional coordinate system. The airfoil can be used in the fan of a gas turbine engine.
Abstract:
A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt% and about 3.0 wt% of lithium.
Abstract:
A fan blade includes first and second titanium portions that are secured to one another with an aluminum alloy braze. A method of manufacturing a fan blade includes providing first and second titanium portions, applying an aluminum alloy braze to at least one of the first and second titanium portions, and heating the fan blade to melt the aluminum alloy braze and join the first and second portions to one another to provide a fan blade with an airfoil exterior contour.
Abstract:
The invention provides a hollow airfoil which is extruded from discontinuously reinforced aluminum (DRA). Preferably the DRA include silicon carbide particles as a reinforcing element. Preferably the silicon carbide is present in an amount between 10-30 volume percent, most preferably 17.5 volume percent. The matrix material is preferably a 6000 aluminium alloy.
Abstract:
High strength, high ductility aluminum base alloys consisting of: from 3.0 to 18.5 weight percent nickel, from 3.0 to 14.0 weight percent yttrium, optionally at least one addition selected from the group consisting of from 0.1 to 6.5 weight percent magnesium, from 0.05 to 5.0 weight percent scandium, from 0.1 to 4.0 weight percent titanium, from 0.1 to 4.0 wt% zirconium, from 0.1 to 3.5 weight percent iron, from 0.1 to 3.5 weight percent cobalt, and from 0.1 to 10 weight percent gadolinium, optionally at least one alloying addition selected from the group consisting of gadolinium, cerium, praseodymium, neodymium, and scandium in a combined sum total of from 3.0 to 33 weight percent, and the balance aluminum, and said alloy being in the devitrified state and containing less than 40 percent intermetallic phases.