A method for joining engine components includes positioning a first plurality of thermal protection structures across a thermal protection space between a first thermal protection surface and a second thermal protection surface. The first and second engine components are locally joined by forming a first plurality of transient liquid phase (TLP) or partial transient liquid phase (PTLP) bonds along corresponding ones of the first plurality of thermal protection structures between the first thermal protection surface and the second thermal protection surface. The second thermal protection surface is formed from a second surface material different from a first surface material of the first thermal protection surface.

A pillar shaped honeycomb structure for induction heating, the honeycomb structure being made of ceramics and including: an outer peripheral wall; and a partition wall disposed on an inner side of the outer peripheral wall, the partition wall defining a plurality of cells, each of the cells penetrating from one end face to other end face to form a flow path, wherein a composite material containing a conductor and a non-conductor is provided in the cells in a region of 50% or less of the total length of the honeycomb structure from one end face, and wherein the conductor is a conductor that generates heat in response to a change in a magnetic field.

A method of assembling together by brazing two parts made of composite material, each part having an assembly face for brazing with the assembly face of the other part, the method including: making a plurality of cavities in the assembly face of at least one of the two composite material parts, at least some of the cavities opening out into one or more portions of the part that are situated outside the assembly face; interposing capillary elements between the assembly faces of the composite material parts; placing a brazing composition in contact with a portion of the capillary elements; and applying heat treatment to liquefy the brazing composition so as to cause the molten brazing composition to spread by capillarity between the assembly faces of the composite material parts.

A method including applying layers of multiple constituents where the constituents are capable of producing a non-equilibrium condition on the contacting surfaces of a ceramic matrix composite component and a gas turbine engine component where one outer coating includes a first constituent and the other outer coating includes a second constituent; forming a component assembly with the ceramic matrix composite component coupled to the gas turbine engine component with contact between the outer coatings; adding an energy to facilitate an equilibrium reaction between the first constituent of the first outer coating and the second constituent of the second outer coating; and as a result of adding the energy, forming a bond structure in the component assembly with a product of the equilibrium reaction where the bond structure affixes the ceramic matrix composite component to the gas turbine engine component between the first constituent and the second constituent.

There is herein described a ceramic phosphor target which may be used in a laser-activated remote phosphor application. The target comprises a substantially flat ceramic phosphor converter comprised of a photoluminescent polycrystalline ceramic which is attached to a reflective metal substrate by a high thermal conductivity adhesive.

The present disclosure relates to a brazed superabrasive assemblies and method of producing brazed superabrasive assemblies. The brazed superabrasive assemblies may include a plurality of braze alloy layers that are positioned opposite a stress relieving layer. The stress relieving layer may have a solidus temperature that is greater than a solidus temperature of the plurality of braze alloy layers.

A method for attaching an insert to a substrate includes: rubbing the insert against the substrate; forming a heat-affected zone in the substrate; forming plasticized substrate material from friction resulting from the rubbing; moving the insert to a first depth in the heat-affected zone in the substrate; moving the insert to a second depth in the heat-affected zone in the substrate where the first depth is deeper than the second depth; flowing the plasticized material against the insert; and releasing the insert.

A method for modifying a composite component may include positioning a barrier segment between an infiltrated segment of the composite component and a green segment to form an assembly; and initiating an infiltration process. The barrier segment may have a barrier segment permeability that is lower than a permeability of the infiltrated segment, a permeability of the green segment, or both. A composite component may include an infiltrated segment infiltrated with a molten material during a prior infiltration process; a green segment that is uninfiltrated; and a barrier segment having a microstructure different from the infiltrated segment, the green segment, or both. The microstructure of the barrier segment may be configured to slow a flow of material between the infiltrated segment and the green segment during a subsequent infiltration process.

A composite component may include an infiltrated segment infiltrated with a molten material during a prior infiltration process, a green segment that is uninfiltrated, and a barrier segment having a microstructure different from the infiltrated segment, the green segment, or both. The microstructure of the barrier segment may be configured to slow a flow of material between the infiltrated segment and the green segment during a subsequent infiltration process.

A method for limiting void formation in a melt-infiltrated ceramic matrix composite (MI-CMC) component includes arranging one or more infiltrant feedstocks in fluid communication with a targeted area of the MI-CMC component. The one or more infiltrant feedstocks have a nominal melting point at or below a nominal melting point of an alloy within the MI-CMC component. The method includes heating the one or more infiltrant feedstocks to a first temperature at or above the nominal melting point of the one or more infiltrant feedstocks to form a molten phase. The method also includes infiltrating the targeted area of the MI-CMC component with the molten phase. As such, the molten phase reacts with a solid phase in the targeted area of the MI-CMC component. Further, the method includes cooling the MI-CMC component to a second temperature that is below the first temperature to solidify the molten phase.