Abstract: A heat shield assembly adapted for use with gas turbine engines, airframes, and aircraft includes a carrier and a heat-shield tile. The carrier is adapted to couple to the gas turbine engine, airframe, or aircraft. The heat-shield tile includes material different than the carrier and is arranged to cover the carrier to protect the carrier from high-temperature gases surrounding the heat shield assembly.

Abstract: A method for selectively adhering braze powders to a surface comprises applying a braze powder to a surface, and then directing a laser beam onto the braze powder while the laser beam moves along a predetermined path relative to the surface. The laser beam selectively heats the braze powder along the predetermined path such that the braze powder is sintered and bonded to the surface. Thus, a braze deposit is formed at one or more predetermined locations on the surface. After forming the braze deposit, excess braze powder, that is, the braze powder not selectively heated by the laser, is removed from the surface.

Abstract: A heat shield assembly adapted for use with gas turbine engines, airframes, and aircraft includes a carrier and a heat-shield tile. The carrier is adapted to couple to the gas turbine engine, airframe, or aircraft. The heat-shield tile includes material different than the carrier and is arranged to cover the carrier to protect the carrier from high-temperature gases surrounding the heat shield assembly.

Abstract: A method for selectively adhering braze powders to a surface comprises applying a braze powder to a surface, and then directing a laser beam onto the braze powder while the laser beam moves along a predetermined path relative to the surface. The laser beam selectively heats the braze powder along the predetermined path such that the braze powder is sintered and bonded to the surface. Thus, a braze deposit is formed at one or more predetermined locations on the surface. After forming the braze deposit, excess braze powder, that is, the braze powder not selectively heated by the laser, is removed from the surface.

Abstract: A gas turbine engine component may include a coating adapted to protect the component during use. The coating may be applied by sintering metallic particles to form a metallic matrix fused to the component.

Abstract: A dual wall component for use in a gas turbine engine and a method for making the same are disclosed herein. The dual wall component includes an inner support wall and an outer shield wall that extends around the inner support wall to act as a heat shield for the inner support wall.

Abstract: A gas turbine engine component may include a coating adapted to protect the component during use. The coating may be applied by sintering metallic particles to form a metallic matrix fused to the component.

Abstract: A gas turbine engine component may include a coating adapted to protect the component during use. The coating may be applied by sintering metallic particles to form a metallic matrix fused to the component.

Abstract: A material deposition system and method for cooling a component after material deposition. The method of deposition and cooling comprising a platform, a deposition head, and a cooling mechanism. The platform adapted to support a component for the addition of material. The deposition head including a material depositor configured to deposit material on a surface of a component supported on the platform an and an energy source configured to energize material deposited onto a surface of a component supported on the platform to bond the material to the component. The cooling system including bristles.

Abstract: Embodiments are disclosed of a turbomachinery component having an outer part that is captured between a cap and a base of the component. In one form, the outer part is placed in compression between the cap and the base. The outer part can be formed prior to being placed between the cap and the base. In some forms, the outer part can be formed partially or completely while engaged with the component. A fugitive spacer can be placed between the outer part and an extension of the component. In various embodiments, the extension can reach into an opening of the outer part and the cap can be coupled with the extension.

Abstract: A method of applying a laser metal formed build layer on a surface of an article is disclosed. A laser deposition head including a light source and a nozzle is positioned relative to the surface of the article by a distance that is about normal to the surface. The surface of the article is melted locally using the laser light source to form a melt pool. Powdered metal is injected into the melt pool using the nozzle. The melt pool is solidified to form the build layer having a desired microstructure on the surface of the article.

Abstract: A material deposition system and method for cooling a component after material deposition. The method of deposition and cooling comprising a platform, a deposition head, and a cooling mechanism. The platform adapted to support a component for the addition of material. The deposition head including a material depositor configured to deposit material on a surface of a component supported on the platform an and an energy source configured to energize material deposited onto a surface of a component supported on the platform to bond the material to the component. The cooling system including bristles.

Abstract: A dual wall component for use in a gas turbine engine and a method for making the same are disclosed herein. The dual wall component includes an inner support wall and an outer shield wall that extends around the inner support wall to act as a heat shield for the inner support wall.

Abstract: A furnace comprising a container and a moveable stage. The container defining a monolithic internal volume configured to maintain a single vacuum level throughout the monolithic internal volume. The stage moveable between a first position arranged to support an assembly within a first zone of the monolithic internal volume and a second position arranged to support an assembly within a second zone of the monolithic internal volume.

Abstract: A method for repairing a blade for use in a gas turbine engine, the method comprising removing a distal tip of an airfoil included in the blade to remove damaged portions of the airfoil and to expose previously internal cooling passages. The method further comprising positioning a tip cap in the place of the removed distal tip to cover the internal cooling passages, and welding the tip cap to the airfoil by applying a directed energy beam onto the tip cap and the airfoil at a joint between the tip cap and the airfoil.

Abstract: A gas turbine engine component may include a coating adapted to protect the component during use. The coating may be applied by sintering metallic particles to form a metallic matrix fused to the component.

Abstract: The present disclosure relates to a method and apparatus for forming a three-dimensional article. The method includes establishing control commands effective to form a three-dimensional article and dispensing a first layer of particulate material onto a build platform. The method also includes irradiating the first layer of particulate material with microwaves and guiding a directed energy, according to the control commands, at the first layer of particulate material to form a first consolidated layer of the three-dimensional article.

Abstract: A method of applying a laser metal formed build layer on a surface of an article is disclosed. A laser deposition head including a light source and a nozzle is positioned relative to the surface of the article by a distance that is about normal to the surface. The surface of the article is melted locally using the laser light source to form a melt pool. Powdered metal is injected into the melt pool using the nozzle. The melt pool is solidified to form the build layer having a desired microstructure on the surface of the article.

Abstract: A metal additive method includes directing sonic and/or ultrasonic energy from a probe that is directed toward a melt pool during solidification of the melt pool and formation of a layer, wherein a solid portion of an object on which the pool is positioned at least partially surrounds the melt pool.

Abstract: Embodiments are disclosed of a turbomachinery component having an outer part that is captured between a cap and a base of the component. In one form, the outer part is placed in compression between the cap and the base. The outer part can be formed prior to being placed between the cap and the base. In some forms, the outer part can be formed partially or completely while engaged with the component. A fugitive spacer can be placed between the outer part and an extension of the component. In various embodiments, the extension can reach into an opening of the outer part and the cap can be coupled with the extension.