Abstract: A means for attaching a metallic component to a non-metallic component using a compliant material having thermal properties intermediate those of the metallic component to a non-metallic component is provided. The method can accommodate CTE mismatches and wear-type problems common to many assemblies of dissimilar materials. In particular, the method provides a sufficient wear surface to accommodate relative motion and provide a durable wear surface that does not excessively wear/gall/mico-weld itself together and provides the necessary damping and motion for proper operation in aeronautical applications.

Abstract: An example system for fabricating an infiltrated downhole tool includes a mold assembly having one or more component parts and defining an infiltration chamber to receive and contain matrix reinforcement materials and a binder material used to form the infiltrated downhole tool. One or more thermal conduits are positioned within the one or more component parts for circulating a thermal fluid through at least one of the one or more component parts and thereby placing the thermal fluid in thermal communication with the infiltration chamber.

Abstract: A mold transfer assembly includes a transfer housing providing an interior defined by one or more sidewalls and a top. The transfer housing is sized to receive and encapsulate a mold as the mold is moved between a furnace and a thermal heat sink. An arm is coupled to the transfer housing to move the transfer housing and the mold encapsulated within the transfer housing between the furnace and a thermal heat sink. The transfer housing exhibits one or more thermal properties to control a thermal profile of the mold.

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a combustion chamber. The heat shield is connected to the shell by a bonded connection, and defines a portion of the combustion chamber. A cooling cavity is defined between the shell and the heat shield.

Abstract: Drill bits and associated methods of manufacture and use employ a pre-diffused mandrel bonded to a composite metal-matrix material. The pre-diffused mandrel includes a chemically altered surface composition that enhances the bond with the composite metal-matrix component formed by infiltrating a metal-matrix component with a binder. The chemically altered surface may be configured to reduce binder-rich zones adjacent the mandrel, mechanically interlock the with the composite metal-matrix component or prevent the formation of brittle intermetallic particles along the bond.

Abstract: A system for fabricating an infiltrated downhole tool for introduction into a wellbore includes a mold assembly including a binder bowl, a mold, a preformed blank, and a funnel. The binder bowl has a lower portion and a plurality of apertures extending through the lower portion. The preformed blank is disposed within the infiltration chamber to provide an attachment area for a body of the infiltrated downhole tool, and the funnel is disposed intermediate the binder bowl and the mold. The system further includes a binder flow channel which extends through at least one of the preformed blank, the funnel, or a displacement core disposed within the mold assembly, the blank being concentrically arranged around the displacement core.

Abstract: 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.

Abstract: A metal matrix composite (MMC) may be formed with two or more portions each having different reinforcing particles that enhance strength, wear resistance, or both of their respective portions of the MMC. Selective placement of the different reinforcing particles may be achieved using magnetic members. For example, in some instances, forming an MMC may involve placing reinforcement materials within an infiltration chamber of a mold assembly, the reinforcement materials comprising magnetic reinforcing particles and non-magnetic reinforcing particles; positioning one or more magnetic members relative to the mold assembly to selectively locate the magnetic reinforcing particles within the infiltration chamber with respect to the non-magnetic reinforcing particles; and infiltrating the reinforcement materials with a binder material to form a hard composite.

Abstract: A metal matrix composite tool includes a body having hard composite portion that includes reinforcing particles dispersed in a binder material. At least some of the reinforcing particles comprise a monolithic particle structure including a core having irregular outer surface features integral with the core.

Abstract: The present disclosure relates to a method of manufacturing composite airfoils bonded to a metallic root. A composite body may be formed with a metallic co-molded member. The co-molded member may be transient liquid phase (TLP) bonded to a metallic root. The metallic root may allow the composite body to be attached to a rotor. The airfoil may also have a metallic edge which is TLP bonded to the composite body via a co-molded edge.

Abstract: A gas turbine engine component assembly includes a ceramic component having a first thermal characteristic. A metallic component has a second thermal characteristic. A bonding material secures the ceramic component to the metallic component. The bonding material includes at least one of a transient liquid phase bond and a partial transient liquid phase bond. The bonding material is configured to withstand a shear stress parameter relating to a differential between the first and second thermal characteristics.

Abstract: A metal matrix composite (MMC) tool includes a mesoscale-reinforced hard composite portion that comprises reinforcing particles and mesoscale reinforcing structures dispersed in a binder material. The mesoscale reinforcing structures are printed using at least one additive manufacturing technique and are larger than an average powder-size distribution of the reinforcing particles.

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a combustion chamber. The heat shield is connected to the shell by a bonded connection, and defines a portion of the combustion chamber. A cooling cavity is defined between the shell and the heat shield.

Abstract: Systems and methods for manufacturing a macroscopically reinforced metal-matrix composite (MMC) fixed-cutter bit are provided. The reinforced drill bit may include a bit body constructed from an infiltrated MMC material and featuring several blade portions extending radially outward and downward from a shank of the drill bit. These blade portions are designed for contacting a subterranean formation. The drill bit also includes the shank, which is coupled to an end of the bit body opposite the blade portions, to connect the bit body to an upstream component of a drill string. The drill bit further includes a number of macroscopic bit reinforcements that are at least partially enclosed within the bit body. These bit reinforcements are each disposed in and aligned substantially with a corresponding blade portion of the bit body.

Abstract: A part includes a three-dimensional porous metallic workpiece printed via an additive manufacturing process and subsequently subjected to a diffusion-based process to convert at least a portion of the porous metallic workpiece to a ceramic workpiece or an intermetallic workpiece.

Abstract: The present disclosure provides a sintering assembly and a polycrystalline diamond compact (PDC) including a acid-labile leach-enhancing material, a PDC including cavities formed by removal of an acid-labile leach-enhancing material, and a method of forming a leached PDC using an acid-labile leach-enhancing material. The present disclosure further includes drill bits using PDCs formed suing an acid-labile leach-enhancing material.

Abstract: Methods of bonding first structures to second structures are disclosed wherein the first and second structures are fabricated materials having different physical characteristics. For example, the first structure may be a composite fan blade and the second structure may be a composite or metallic rotor, both for use in gas turbine engines. The method includes providing the first and second structures and plating or otherwise coating a portion of the first structure with a metal to provide a metal-coated portion. The method includes applying at least one intermediate material onto the metal-coated portion of the first structure. The method further includes bonding the metal-coated portion of the first structure and the intermediate material to the second structure. The bonding is carried out using a relatively low-temperature process, such as liquid phase bonding, including TLP and PTLP bonding. Brazing is also a suitable technique, depending on the materials chosen for the first and second structures.

Abstract: A part includes a three-dimensional porous metallic workpiece printed via an additive manufacturing process and subsequently subjected to a diffusion-based process to convert at least a portion of the porous metallic workpiece to a ceramic workpiece or an intermetallic workpiece.

Abstract: Tools, for example, fixed cutter drill bits, may be manufactured to include hard composite portions having reinforcing particles dispersed in a continuous binder phase and auxiliary portions that are more machinable than the hard composite portions. For example, a tool may include a hard composite portion having a machinability rating 0.2 or less; and an auxiliary portion having a machinability rating of 0.6 or greater in contact with the hard composite portion. The boundary or interface between the hard composite portion and the auxiliary portion may be designed so that upon removal of the most or all of the auxiliary portion the resultant tool has a desired geometry without having to machine the hard composite portion.

Abstract: An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.