Methods for material build-up on a tip of a blade of a gas turbine engine are provided. The method can include inserting a material supply and an inflatable bladder between the tip and a shroud such that the material supply is exposed to the tip and the inflatable bladder is positioned between the material supply and a shroud, inflating the inflatable bladder to force contact between the material supply and the tip, and causing relative movement between the material supply and the tip. The relative movement, in combination with the radial biased contact between the material supply and the tip, creates heat through friction. As such, the relative movement can frictionally weld new material from the material supply onto the tip of the blade. For example, the heat created can be sufficient to melt the surface of the material supply to transfer material from the material supply to the tip.

A method of friction welding a first component to a second component, the method having the steps of: rotating the first component relative to the second component about a rotation axis; and bringing the first component into contact with the second component; wherein, while the first component and the second component are in contact, a first average force is applied during a first stage of the friction welding process and a second average force is applied during a second stage of the friction welding process; and the second average force is different from the first average force.

A selectively reinforced component comprises a metal body with at least one metal matrix composite insert embedded in a first surface of the metal body, with at least one weld bonding an outer surface of the metal matrix composite insert to the metal body. The selectively reinforced component is formed by introducing the or each metal matrix composite insert into a recess in the first surface of the metal body, before forming the at least one weld to bond the outer surface of the metal matrix composite insert to an opposing inner peripheral surface of the recess.

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 blade for a propulsion apparatus that includes a body formed of a first material having opposed pressure and suction sides, and extending in span between a root and a boundary, and extending in chord between a leading edge and a trailing edge. A tip region that is formed of a second material and that is positioned such that it extends from the body and defines a tip. The tip region joins the body at the boundary. The tip region is configured to fail when a predetermined force is applied to the tip such that the tip separates from the blade and defines a fused tip.

An impeller 1 according to the present invention includes a disc portion 30 fixed to a rotary shaft 101 that rotates around an axis line O, a cover portion 50 disposed to face the disc portion 30, and a plurality of blade portions 40 provided between the disc portion 30 and the cover portion 50. The impeller 1 includes a first segment SG1 configured of a first disc portion 31 that is a portion of the disc portion 30 on one side of the axis line O, a second segment SG2 in which a second disc portion 35 that is a portion of the disc portion 30 on another side of the axis line O, the cover portion 50, and the blade portions 40 are integrally configured, and a joining layer CL configured to join, by friction welding, the first segment SG1 and the second segment SG2.

Disclosed herein is a gimbal body comprising: an end part (51) for use in welding the gimbal body to a pipe; and a main body (53) attached to the end part (51); wherein: the end part (51) is made of a first material; and the main body (53) is made of a second material that is different from the first material. Embodiments provide a new method of manufacturing a gimbal that allows the use of the most appropriate materials for high temperature and high pressure performance whilst overcoming manufacturing and installation problems experienced by known gimbals constructed with such materials.

In a method for manufacturing a turbine engine element such as a blade or vane, the element has an airfoil. The method includes: applying a load across an assembly of a first cast portion of the airfoil and a second cast portion of the airfoil; and applying current across a junction of the first cast portion and the second cast portion to fuse the second cast portion to the first cast portion.

A turbine rotor disk and a method of making the turbine rotor disk using solid state bonding techniques are disclosed. The turbine rotor disk includes a radially inner portion comprising a wrought nickel alloy having a yield strength of at least 126 ksi at 1,000° F. The turbine rotor disk also includes a radially outer portion bonded to the radially inner portion, said radially outer portion comprising a cast nickel alloy configured as a single crystal or with a grain size of ASTM 2 or larger.

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.