An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.

An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.

A coating method includes depositing a slurry including a coarsely particulate ceramic and a finely particulate ceramic on a base material configured with an oxide-based ceramics matrix composite such that a proportion of coarse particles decreases towards a surface of the base material; forming a bond coating by performing a heat treatment on the base material on which the slurry has been deposited; and forming a top coating by thermally spraying a ceramic onto the bond coating. The oxide-based ceramics matrix composite is an alumina silica type oxide-based ceramics matrix composite. The coarsely particulate ceramic and the finely particulate ceramic are alumina-based powder.

A method for coating a part having a surface that has cooling fluid openings that adjoin cooling fluid ducts inside the part. A device analyzes the surface of a part having a surface that has cooling fluid openings which adjoin cooling fluid ducts inside the part, the device being usable in the aforementioned method. The disclosed device and/or the disclosed method is used during the manufacturing and/or overhauling of parts of a turbomachine.

A method for forming a vertically cracked thermal barrier coating is disclosed including positioning an article relative to a heat source. The article includes a thermal barrier coating disposed on a first surface of a substrate, and the substrate includes a second surface distal across the substrate from the first surface. Heat is applied locally to at least one discrete portion of the second surface of the substrate. At least one vertical crack in the thermal barrier coating is formed disposed over the at least one discrete portion. An article is disclosed including a substrate and a vertically-cracked thermal barrier coating disposed on the substrate. The vertically cracked thermal barrier coating includes at least one vertical crack in the thermal barrier coating and at least one of a low density of less than 85% of a theoretical density for the thermal barrier coating and a selective crack distribution.

The invention concerns a flow straightener unit (1) for a fan module of a turbomachine, the straightener unit (1) comprising a plurality of blades (2) distributed about an axis of rotation, each blade (2) is made of a composite material and comprises an aerofoil (21) and a root (22) intended to be assembled on a hub (4) of the turbomachine. The unit (1) comprises a centring and attachment plate (3) of the blade (2) on the turbomachine intended to be attached to the hub (4) at a determined azimuthal position and to the root (22) of the blade (2), the plate (3) is designed to be screwed to the hub (4) by screws (51a) that are longitudinal with respect to the axis of rotation of the unit (1) and screwed to the root (22) of the blade (2) by screws (52) that are radial with respect to the axis of rotation of the unit (1).

A method of forming a ceramic matrix composite component having an internal cooling circuit includes wrapping at least a first sheet around a first mandrel, wrapping at least a second sheet around a second mandrel, creating a first plurality of holes in the first sheet corresponding to a plurality of openings in the first mandrel, creating a second plurality of holes in the second sheet corresponding to a plurality of openings in the second mandrel, aligning the first mandrel and the second mandrel such that the first plurality of holes face and are aligned with the second plurality of holes, wrapping at least a third sheet around both the first mandrel and second mandrel to form a preform, the preform comprising each of the first sheet, the second sheet, and the third sheet, and densifying the preform. The first sheet, second sheet, and third sheet are formed from a ceramic fiber material.

A method for making a ceramic matrix composite component includes densifying a fibrous preform of the component with a ceramic matrix to form an intermediate component; infiltrating a hole in the intermediate component with an infiltrate material comprising a solid and a metallic alloy whose reaction forms a carbide, silicide, boride or combination thereof, heating the infiltrate material to a temperature in excess of a melting point of the metallic alloy; and sequentially cooling regions of the hole starting from an interior end of the hole to the outer surface of the intermediate component to form a solidified through-thickness reinforcement element. The hole extends in a through-thickness direction and is open to an exterior surface of the intermediate component.

A method of assembling a ceramic matrix composite (CMC) component is provided. The method includes assessing which portions of the CMC component require relatively high-temperature capability and which portions require at least one of strength, thickness and increased thermal conductivity, making the portions that require the relatively high temperature capability with chemical vapor infiltration (CVI), making the portions that require the at least one of strength, thickness and increased thermal conductivity with melt infiltration (MI) and combining the portions that require the relatively high temperature capability with the CVI and the portions that require the at least one of strength, thickness and increased thermal conductivity with the MI.

A vane assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart radially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends radially between and interconnects the outer platform and the inner platform.