A method is provided including the steps: —first excitation of the object via a multifrequency signal; —detecting a first response signal of the object at one or multiple measuring points at the object; —transforming the first response signal from a time range into a frequency-dependent range; —selecting one or multiple frequencies, based on the frequency-dependent range; —second excitation of the object based on the selected frequencies; —detecting a second response signal of the object at one or multiple measuring points of the object; —ascertaining a mechanical parameter based on the second response signal.

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.

Embodiments of bladed rotors and methods for manufacturing bladed rotors are provided herein. The method for manufacturing bladed rotors includes providing a workpiece including a first rotor blade segment. The first rotor blade segment includes a first platform portion on a radially outward end portion of the first rotor blade segment. Further, the method includes forming a second rotor blade segment, by additive manufacturing, removing a side portion of the first platform portion, and removing a side portion of the second rotor blade segment, whereby a second platform portion remains on a radially outward end portion of the second rotor blade segment.

Embodiments of bladed rotors and methods for manufacturing bladed rotors are provided herein. The method for manufacturing bladed rotors includes providing a workpiece including a first rotor blade segment. The first rotor blade segment includes a first platform portion on a radially outward end portion of the first rotor blade segment. Further, the method includes forming a second rotor blade segment, by additive manufacturing, removing a side portion of the first platform portion, and removing a side portion of the second rotor blade segment, whereby a second platform portion remains on a radially outward end portion of the second rotor blade segment.

The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23) connected to the platform (13), a leading edge (21) and a trailing edge (22), a groove formed in the platform (13) around part of the root (23) of each blade (20) in an area adjacent to the leading edge (21) and/or the trailing edge (22), and a joint (30) placed in the groove (15) in such a way that it extends in the extension of the radially outer face (14) of the platform (13) in order to ensure a continuity of the inner flow stream.

The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23) connected to the platform (13), a leading edge (21) and a trailing edge (22), a groove formed in the platform (13) around part of the root (23) of each blade (20) in an area adjacent to the leading edge (21) and/or the trailing edge (22), and a joint (30) placed in the groove (15) in such a way that it extends in the extension of the radially outer face (14) of the platform (13) in order to ensure a continuity of the inner flow stream.

Methods for creating a cast component, along with the resulting cast components, are provided. The method may include heating a mold having a cavity therein; supplying a first molten metal material into the cavity of the mold such that the first molten metal material is directed to a first portion of the cavity of the mold; supplying a second molten metal material into the cavity of the mold such that the second molten metal material is directed to a second portion of the cavity of the mold, wherein the first molten metal material is compositionally different than the second molten metal material; and thereafter, allowing the first molten metal material and the second molten metal material to form the cast component.

Cast components are provided that include a first section comprising a first metal material and having first grains with a first average grain size and a second section comprising a second metal material and having second grains with a second average grain size.

A method repairs welding of an aircraft turbine engine blade that has a lower surface and an upper surface connected by a leading edge and a trailing edge The blade further includes a free end referred to as the tip. The method includes the repair welding of the tip and including the steps of: securing a first stop to the leading edge at the tip and a second stop to the trailing edge at the tip, depositing a repair weld bead on the tip, from the first stop to the second stop, and removing the first and second stops. The first and second stops are secured solely by squeezing same on the leading and trailing edges.

A method repairs welding of an aircraft turbine engine blade that has a lower surface and an upper surface connected by a leading edge and a trailing edge The blade further includes a free end referred to as the tip. The method includes the repair welding of the tip and including the steps of: securing a first stop to the leading edge at the tip and a second stop to the trailing edge at the tip, depositing a repair weld bead on the tip, from the first stop to the second stop, and removing the first and second stops. The first and second stops are secured solely by squeezing same on the leading and trailing edges.