A method of processing a joint, including forming an actively brazed joint in a vacuum furnace, wherein the actively brazed joint is formed from at least two components coupled together by a volume of a joining metal alloy having a solidus temperature and a liquidus temperature, wherein the joining metal alloy is heated to a first temperature that is higher than the liquidus temperature in the vacuum furnace. The method also includes cooling the actively brazed joint to a second temperature lower than the solidus temperature, and maintaining the second temperature within the vacuum furnace for a predefined duration to form at least one region of segregated crystallization within the volume of the joining metal alloy, the at least one region of segregated crystallization is configured to increase the liquidus temperature of a layer of brazed metal, formed from the joining metal alloy, between the at least two components.

A variable geometry aerodynamic blade system employs a blade having a leading edge and a trailing edge. At least one shape memory alloy component is integrated in the blade for aerodynamic repositioning of one or both of the leading and trailing edges. At least one heating element interacts with the at least one shape memory alloy component to provide heating for transition between an austenitic and a martensitic phase. The at least one shape memory alloy component is responsive to the at least one heating element to alter one of a camber and twist of the blade responsive to a control signal. A control system is operatively engaged to the at least one heating element, the control system receiving a command signal and outputting the control signal responsive to the command signal.

In some examples, a method may include depositing, from a slurry comprising particles including silicon metal, a bond coat precursor layer including the particles comprising silicon metal directly on a ceramic matrix composite substrate. The method also may include locally heating the bond coat precursor layer to form a bond coat comprising silicon metal. Additionally, the method may include forming a protective coating on the bond coat. In some examples, an article may include a ceramic matrix composite substrate, a bond coat directly on the substrate, and a protective coating on the bond coat. The bond coat may include silicon metal and a metal comprising at least one of Zr, Y, Yb, Hf, Ti, Al, Cr, Mo, Nb, Ta, or a rare earth metal.

Methods for removing a fiber-reinforced wrap from a fan casing are provided. The method may include heating the fiber-reinforced wrap while on a metal support (e.g., aluminum, steel, etc.) of the fan casing, unwinding a layer of the fiber-reinforced wrap from the fan casing, and winding the layer of the fiber-reinforced wrap onto a collection drum. The fiber-reinforced wrap may heated to a temperature of about 120 C. to about 200 C. (e.g., about 125 C. to about 185 C.). Systems are also generally provided for removing a fiber-reinforced wrap from a fan casing.

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.

A method of forming an impurity barrier layer on a CMC substrate may include introducing, to a heated plume of a thermal spray gun, a composite feedstock that includes a first coating material including a plurality of first particles; and a second coating material that may be different from the first coating material, where the second coating material at least partially encapsulates at least a portion of respective surfaces of the plurality of first particles; and directing, using the heated plume, at least the first coating material to a surface of a CMC substrate to deposit an impurity barrier layer including at least the first coating material.

An arrangement comprising a component (203) adjacent to a ceramic matrix composite in a gas turbine engine is shown. The component comprises a nickel-base superalloy substrate (301) and a cobalt-modified beta-nickel-aluminide coating (302) on the substrate to prevent interdiffusion between the substrate and the ceramic matrix composite. The substrate is coated by depositing a cobalt layer on the substrate, depositing an aluminium layer on the cobalt layer and then forming a cobalt-modified beta nickel aluminide coating.

Disclosed herein is a method of coating, comprising providing an article having an internal passage therein to be coated; electrolytically applying a first layer that comprises chromium or a chromium alloy onto a surface of the internal passage; electrolytically applying a second layer comprising aluminum or an aluminum alloy onto the first layer; and heat treating the article to promote interdiffusion between the first layer and the second layer.

A thermal barrier coating includes a highly porous layer and a dense layer. The highly porous layer is formed on a heat-resistant base, is made of ceramic, has pores, has a layer thickness of equal to or larger than 0.3 mm and equal to or smaller than 1.0 mm, and has a pore ratio of equal to or higher than 1 vol % and equal to or lower than 30 vol %. The dense layer is formed on the highly porous layer, is made of ceramic, has a pore ratio of equal to or lower than 0.9 vol % that is equal to or lower than the pore ratio of the highly porous layer, and has a layer thickness of equal to or smaller than 0.05 mm.

Disclosed is a rotating component for a turbine engine including a first rotating component having a first snap surface and a second rotating component having a second snap surface wherein the first snap surface is configured to interlock with the second snap surface, and further wherein at least one of the first snap surface and the second snap surface have a friction enhancing material.