Abstract: A method of making a refractory article having excellent high-temperature thermal shock resistance and creep resistance is provided. The method includes the step of providing a refractory composition primarily composed of chamotte having controlled particle sizes. The refractory composition may also include mullite, fused silica, calcined alumina and microsilica having controlled particle sizes, and further includes an aqueous colloidal silica binder. The refractory composition is then formed into a refractory article, which is dried and hardened.

Abstract: In an aspect of the disclosure, a three dimensional (3D) printing system includes a printhead and an ink supply subsystem. The printhead is for ejecting drops of phase change ink to define a three dimensional article of manufacture. The ink supply subsystem includes an ink tube, a helical resistor, a return conductor, and an outer tube. The ink tube has an inside surface for contacting and transporting the phase change ink and an outer tubular surface. The resistor is helically wound around the outer tubular surface of the ink tube. The return conductor is helically wound around the resistor and has a resistance that is lower than that of the resistor. The outer tube surrounds and protects the resistor and the return conductor and provides insulation to the heated ink transport component.

Abstract: A waste removal and transfer assembly for a 3D printing system comprises a waste material remover and a waste material collector. The waste material remover comprises a movable waste removing element selectively movable into contact with a planerizer roller to remove 3D printing waste material from the planerizer roller. The waste material remover is coupled to translate with the planerizer roller and comprises an opening leading to a waste material receptacle configured to receive waste material and at least one port selectively operable to transfer waste material from the waste receptacle. The waste material collector has a receiving position that is stationary relative to the waste material remover. The waste material collector comprises an opening and a waste material storage recess to receive waste material transferred from the waste material remover via the at least one port and to store the received waste material for subsequent disposal.

Abstract: A rotatable sealing structure for a gas turbine engine includes a first blade and a second blade. A seal is arranged between the blades and has a body that is configured for operative association with the first and second blades in a first orientation and in a second orientation to seal a gap defined between the blades.

Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure. The hollow vascular engineered lattice structure further has at least one resupply inlet hole between the inlet hole and the outlet hole to communicate additional fluid into the hollow vascular engineered lattice structure.

Abstract: A refractory composition yields refractory articles having excellent resistance to high-temperature thermal shock and creep. The refractory composition is based primarily on chamotte having controlled particle sizes, and may also include mullite, fused silica, calcined alumina and microsilica, having controlled particle sizes. The refractory composition includes an aqueous colloidal silica binder that provides excellent castability and binding between the ingredients following drying.

Abstract: A seal and damper system is provided. The system comprises a blade assembly seal with a central portion defining a recess and a depression. The system also includes a damper comprising a center body and an arm extending from the center body and configured to engage the depression. A blade assembly is also provided comprising a blade platform, a seal configured to press against the blade platform, and a damper clipped onto the seal.

Abstract: An attachment root of an airfoil is provided. The attachment root may comprise a serration profile, a symmetry plane bisecting the serration profile, and a line perpendicular to the symmetry plane. A first lobe of the serration profile may have a first contact face angled 135 degrees from the line. A second lobe of the serration profile may have a second contact face angled 135 degrees from the line. A third lobe of the serration profile may have a third contact face angled 135 degrees from the line.

Abstract: Transfer of content between documents of different storage types is provided. Different versions of an endpoint (e.g., a productivity application) such as a mobile version and a desktop version, for example, may be enabled to process the same document and synchronize changes to the document content, even though the different versions or endpoints may use distinct formats for the same document.

Abstract: Transfer of content between documents of different storage types is provided. Different versions of an endpoint (e.g., a productivity application) such as a mobile version and a desktop version, for example, may be enabled to process the same document and synchronize changes to the document content, even though the different versions or endpoints may use distinct formats for the same document.

Abstract: A method of providing a chemically inert concrete includes the steps of providing and mixing an aqueous colloidal silica dispersion with a quantity of glass particles. The chemically inert concrete includes, based on dry weight, about 50% to about 95% by weight of the glass particles and about 3% to about 40% by weight of the colloidal silica particles. The chemically inert concrete is substantially or totally free of Group I and Group II metal oxides, exclusive of the glass particles, and is substantially or totally free of cement.

Abstract: An assembly for a gas turbine that engine includes a fan section. A turbine section is configured to drive the fan section. The turbine section includes a rotor hub with a rotor lug. A heat shield engages the rotor lug. The heat shield and the rotor lug define a cooling passage.

Abstract: An exemplary gas turbine engine assembly includes a damping device having a first side and a second side facing away from the first side. The first side is configured to hold a seal when the second side engages an extension from a gas turbine engine component. The first side is further configured to engage the extension when the second side holds the seal.

Abstract: A damper-seal assembly for a gas turbine engine includes an additively manufactured seal and an additively manufactured damper inseparably assembled with the additively manufactured seal.

Abstract: A chemically inert concrete composition includes, based on dry weight, about 50% to about 95% by weight glass particles and about 3% to about 40% by weight colloidal silica particles. Optional additional chemically inert ingredients can be included in amounts of about 3% to about 40% by weight. The concrete composition is substantially or totally free of Group I and Group II metal oxides, exclusive of the glass particles, and is substantially or totally free of cement.

Abstract: A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a second condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.

Abstract: A flowpath component for a gas turbine engine includes a first platform including a vascular engineered lattice structure, a body extending from, and supported by the first platform. The body is configured to at least partially span a flowpath in an installed position and the vascular engineered lattice structure including at least one purge air inlet, and at least one spent air outlet.

Abstract: In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.

Abstract: Compounds and pharmaceutical compositions that modulate kinase activity, including PI3 kinase activity, and compounds, pharmaceutical compositions, and methods of treatment of diseases and conditions associated with kinase activity, including PI3 kinase activity, are described herein.

Abstract: Compounds and pharmaceutical compositions that modulate kinase activity, including PI3 kinase activity, and compounds, pharmaceutical compositions, and methods of treatment of diseases and conditions associated with kinase activity, including P13 kinase activity, are described herein.