A method for manufacturing a titanium aluminide blade of a turbine engine, including production of a titanium aluminide ingot, extrusion of the ingot through an opening in a die having one main arm and at least one side arm, such as to obtain a extruded ingot having the shape of a bar with a cross-section having one main arm and at least one side arm substantially perpendicular to the main arm, transverse cutting of the extruded ingot such as to obtain sections of extruded ingot, forging of each section of extruded ingot such as to obtain a turbine engine blade.

The present invention concerns a connecting element for connecting a blade, or airfoil profile, to the hub of an industrial axial fan, a blade system comprising said connecting element, and an industrial axial fan comprising such blade system. The connecting element (1) for connecting a blade (10) to the hub (20) of an industrial axial fan according to the present invention, is realized in a single L-shaped piece comprising a first part (1a) having a substantially straight develop and a second part (1b) having a substantially straight develop, said first (1a) and second (1b) part being connected by a linking part (1c) presenting a curvature radius, said first (1a) and second (1b) parts lying on substantially perpendicular planes. The connecting element according to the present invention allows to achieve several advantages with respect to the prior art, one of said advantages consisting of its extremely simple shape and manufacturing process, which render the connecting element economically advantageous.

A method of producing a propellant material element, such as an electrically-operated propellant material, includes extruding a propellant material through a heated nozzle. The nozzle may be heated to a temperature that is above the boiling point of a solvent that is part of the propellant material, yet is below a decomposition temperature of the propellant material. This allows some of the solvent to be driven off during the extruding process, while still preventing initiation of an energy-creating reaction within the material. The heating of the material in the extruding process, and especially the heating of the nozzle that the material is extruded through, may be controlled to remove an amount of solvent that results in the extruded material having desirable properties.

Fan assemblies, and in particular fan wheels and stator assemblies for fan assemblies, are disclosed. In one embodiment, the fan wheel includes a wheel back having an outer surface forming one of a curved dome-shape and a truncated cone-shape. The fan wheel may also include a plurality of fan blades radially spaced about and mounted to the outer surface of the wheel back. In one embodiment, each of the fan blades is formed from a segment of an airfoil-shaped aluminum extrusion defining at least one internal cavity. The fan blade first ends can be provided with a compound cut profile with at least one curved cut such that the first end of the blade is mounted flush to the wheel back outer surface. The stator assembly can also be provided with a plurality of stator blades formed from airfoil-shaped aluminum extrusion segments and provided with compound cut profiles.

A fan slider for use in a fan assembly to push a fan blade radially outward of a rotating axis of the gas turbine engine. The fan slider may include a fan slider body coated with a nanocrystalline metallic coating and a slider spring.

A method of making an engine system component is disclosed. The method may include loading a first metal-based material and a second metal-based material into an extrusion chamber. The first metal-based material may concentrically surround the second metal-based material, and the first metal-based material may have at least one of a thermal property and a wear resistance different than the second metal-based material. The method may additionally include forming an extrudate by simultaneously passing the first metal-based material and the second metal-based material through a die. The first metal-based material of the extrudate may be metallurgically bonded to the second metal-based material of the extrudate. The method may also include forging the extrudate.

An extruded profile for manufacturing a blade of an outlet guide vane of a turbine engine. A cross-sectional area has an axial length LAX and a thickness D/LAX relative to the axial length LAX. A cross-sectional area has an at least nearly axisymmetric leading edge region, a first transition region having a varying relative thickness D/LAX. A first constant region has a relative thickness D/LAX at least substantially constant and, relative to a leading edge of the extruded profile, begins at the closest at 10% LAX and ends at the furthest at 50% LAX. A second transition region has a varying relative thickness D/LAX and, relative to the leading edge of the extruded profile, begins at the closest at 30% LAX and ends at the furthest at 90% LAX. A second constant region has a relative thickness D/LAX at least substantially constant and an axial length X of 40% LAX at most; and an at least nearly axisymmetric trailing edge region.

A method of making a machine component includes extruding a supply of an aluminum alloy to produce an extrusion. The extrusion is formed under temperature-limited forming conditions of 275 C. or less to produce a blank. The blank is machined to at least one predetermined tolerance to produce the machine component.

A number of variations may include a method that may include casting or providing a central core comprising titanium aluminide; and metal injection molding a shell comprising titanium aluminide around the central core to produce a rotor assembly.

A method for producing a can formed from a can part and a flange part is provided, the flange part being formed as an annular body and, on a side oriented inward toward an axis of symmetry of the annular body, an interface forming a bearing for the can part. A base and a lateral wall are formed on the can part, and the can part is deep drawn and made into a target geometry with a defined wall thickness by virtue of the lateral wall being flow formed. The lateral wall has a formed interface with a material thickness greater than the wall thickness of the lateral wall, and the flange part is connected to the can part at the interface.