A tool for simultaneous local stress relief of each of a multiple of linear friction welds includes a columnar track defined along an axis, the columnar track having a helical slot; and a support structure engaged with the helical slot to translate and rotate a heat treat fixture portion along the axis.

A method of manufacturing an airfoil includes creating a plurality of cavities separated by a plurality of internal ribs in an airfoil forging. At least one hole is drilled in at least one of the plurality of internal ribs with a laser drilling tool. At least one hole extends perpendicularly to a wall of the rib.

In a pump housing having an interior for accommodating a pump rotor, which may be transferred from a radially compressed state into a radially expanded state, and comprises a housing skin revolving in circumferential direction, as well as at least one reinforcement element, a stretch-resistant element revolving in circumferential direction is provided, which is stretched less than 5% in the expanded state as opposed to the force-free state in circumferential direction, and which limits any further expansion of the pump housing in radial direction.

The invention relates to a movable blade made of aluminum and titanium alloy, for a turbojet engine turbine comprising a vane and at least one root at a distal end of the vane. The root has at least one azimuthal contact surface with another directly adjacent blade. A hard abrasion-resistant material, called wear-resistant material, is deposited onto the at least one azimuthal contact surface. A cavity is produced in said at least one azimuthal contact surface, the wear-resistant material being deposited in the cavity.

A structural guide vane including a vane body contact surface and a vane edge, wherein at least one of the vane body contact surface or the vane edge comprises a fiber metal laminate.

A turbine rotor for an aircraft engine includes a plurality of blades compressed by a compression ring made of ceramic matrix composite (CMC). The CMC includes at least one of: monofilaments and silicon carbide fibers. A method of extracting energy from an airflow using a turbine rotor of an aircraft engine is also disclosed.

A method is provided for adding material to a turbine engine component. The method includes cold spraying a powder towards a region of the component to form a deposit on the region of the component, the component being formed of a parent material, the parent material being a superalloy or a titanium alloy and defining a parent material property value, and the deposit defining a deposit material property value equal to at least fifty percent of the parent material property.

Provided is a blade manufacturing method by which a blade of a stable quality can be manufactured. The present invention involves: a shaping process in which a blade is molded by means of metal injection molding by injecting metal powder toward a mold; a jig attaching process in which a jig serving as a mold, which is divided into at least two parts forming the shape of the blade therebetween, is attached to the blade by sandwiching the blade between the shape-forming surfaces; and a thermal treatment process in which a thermal treatment is applied to the blade to which the jig has been attached.

A method of manufacturing a turbo-machine impeller, which includes a hub and a plurality of blades, using powder material in an additive-manufacturing process. The method includes: applying energy to the powder material by way of a high energy source, and solidifying the powder material. At least one bulky portion of the hub is irradiated such that the powder material solidifies in a lattice structure surrounded by an outer solid skin structure enclosing the lattice structure.

A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin and having an outer surface. The composite fan casing further includes at least one stiffener integrally coupled to an aft portion of the outer surface of the core relative to the central axis. Additionally, the at least one stiffener comprises an elastic material.