Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.

Abstract: A fuel/oil manifold includes first and second manifold flanges and a manifold tube. The first and second manifold flanges are located in non-parallel planes with respect to one another. The manifold tube is connected at a first end to the first manifold flange and at a second end to the second manifold flange and includes at least one turn between the first and the second end that includes a non-zero tube bend radius defined as the ratio of a turn radius to a diameter of the manifold tube.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity.

Abstract: A method of preparing a casting article for use in manufacturing a gas turbine engine part according to an exemplary aspect of the present disclosure includes, among other things, communicating a powdered material to an additive manufacturing system and preparing a casting article that includes at least one trunk and a skin core that extends from the at least one trunk out of the powdered material.

Abstract: An airfoil has a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A leading edge wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the leading edge wall to provide an impingement cavity between the leading edge wall and the impingement wall and multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall. A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another, joining the layers to one another with reference to CAD data relating to a particular cross-section of an airfoil, and producing the airfoil.

Abstract: A gas turbine engine includes a plurality of airfoils that are circumferentially arranged to rotate about an engine central axis. Each of the airfoils includes a base and a free tip end. The tip end includes first and second porous abradable elements that are axially spaced apart. The first porous abradable elements of the airfoils circumferentially align with each other, and the second porous abradable elements of the airfoils circumferentially align with each other.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is loose within the cavity.

Abstract: An airfoil for a gas turbine engine includes a body having leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface defined by a perimeter wall. An interior wall is arranged interiorly and adjacent to the perimeter wall to provide a cooling passage there between. A cooling passage with first and second portions is tapered and respectively has first and second thicknesses. The first thickness is greater than the second thickness. The second thickness is less than 0.060 inch (1.52 mm).

Abstract: A method of manufacturing an airfoil includes the steps of depositing multiple layers of powdered metal onto one another. The layers are joined to one another with reference to CAD data relating to a particular cross-section of an airfoil. The airfoil is produced with leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. An exterior wall provides the exterior airfoil surface at the leading edge. An impingement wall is integrally formed with the exterior wall to provide an impingement cavity between the exterior wall and the impingement wall. Multiple impingement holes are provided in the impingement wall. The impingement holes are spaced laterally across the impingement wall.

Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define at least one longitudinally elongated cavity in the airfoil body. A plurality of loose particles is enclosed in the at least one longitudinally elongated cavity.

Abstract: A blade includes an airfoil having a base and a free, tip end. The tip end includes at least one porous, abradable element.

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first sidewall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. At least one of the first side wall and the second side wall includes at least one longitudinally elongated buttress that tapers longitudinally. The at least one longitudinally elongated buttress defines an increased thickness of, respectively, the first side wall or the second sidewall. The at least one longitudinally elongated buttress projects partially across the cavity toward the other of the first side wall or the second sidewall.

Abstract: According to an example embodiment, a machine includes, among other things, a housing and a support situated for supporting a work piece in a selected position relative to the housing. A radiation source is situated for emitting a beam of radiation in the housing. A magnetic field generator is situated for generating a magnetic field in the housing near the support. The magnetic field has a selectively variable strength at a plurality of locations in the housing for selectively steering the beam of radiation toward the support.

Abstract: An example multi-dimensional component building system includes a first chamber having at least one base disposed therein, a second chamber adjacent to and in fluid communication with the first chamber through a first door, and a third chamber adjacent to and in fluid communication with the second chamber through a second door. The second chamber is fluidly sealed from the first chamber if the first door is in a closed position. The second chamber is configured to receive the at least one base via a first transfer mechanism if the fluid parameters of the first chamber are approximately equal to the fluid parameters of the second chamber. The second chamber includes a directed heat source and a build-up material configured to form a component on the at least one base by melting or sintering. The third chamber is fluidly sealed from the second chamber if the first door is in a closed position.

Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is faced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity. The damper member includes a first end and a second end. The first end is connected in a first joint to the first sidewall at a first longitudinal location and the second end is connected in a second joint to the second sidewall at a second, different longitudinal location.

Abstract: An example multi-dimensional component building system includes a first chamber having at least one base, a second chamber adjacent to and in fluid communication with the first chamber through a first door, and a third chamber adjacent to and in fluid communication with the second chamber through a second door. The second chamber is fluidly sealed from the first chamber if the first door is in a closed position. The second chamber includes a directed heat source, a build-up material and is configured to receive the at least one base if the fluid parameters of the first chamber and second chamber are approximately equal. The third chamber is fluidly sealed from the second chamber if the first door is in a closed position. The third chamber is configured to receive the at least one base, having a formed component disposed thereon, if the second door is in an open position.

Abstract: An example apparatus for aligning a pressure tapping tool includes a base having an engagement portion. The engagement portion engages a component to limit relative movement between the base and the component. At least one guide mounts adjacent the base. Positioning a pressure tapping tool against the guide aligns the pressure tapping tool for pressure tapping the component. An example method of pressure tapping a component includes limiting relative movement between a fixture and a component and guiding a tool along a fixture when pressure tapping the component. The example may include guiding the tool along different portions of the fixture to pressure tap different portions of the component.

Abstract: According to an example embodiment, a machine includes, among other things, a housing and a support situated for supporting a work piece in a selected position relative to the housing. A radiation source is situated for emitting a beam of radiation in the housing. A magnetic field generator is situated for generating a magnetic field in the housing near the support. The magnetic field has a selectively variable strength at a plurality of locations in the housing for selectively steering the beam of radiation toward the support.

Abstract: Uber-cooled multi-alloy integrally bladed rotors (IBR) are made having blades with internal cooling passages with a cavity in the root portion attached to a disk having a protrusion on the periphery of the disk. The blades are put on the protrusion and the blade and disk are forced together, followed by locally heating the blade cavity/disk protrusion to a temperature between the blade and disk material softening temperatures, causing the protrusion to deform against the blade cavity, and holding them in place until bonding occurs. Subsequent to bonding the portion of the blade that defines the cavity is removed.