Abstract: Vertical etch heterolithic integrated circuit devices are described. A method of manufacturing NIP diodes is described in one example. A P-type substrate is provided, and an intrinsic layer is formed on the P-type substrate. An oxide layer is formed on the intrinsic layer, and one or more openings are formed in the oxide layer. One or more N-type regions are implanted in the intrinsic layer through the openings in the oxide layer. The N-type regions form cathodes of the NIP diodes. A dielectric layer deposited over the oxide layer is selectively etched away with the oxide layer to expose certain ranges of the intrinsic layer to define a geometry of the NIP diodes. The intrinsic layer and the P-type substrate are vertically etched away within the ranges to expose sidewalls of the intrinsic layer and the P-type substrate. The P-type substrate forms the anodes of the NIP diodes.

Abstract: A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

Abstract: An example technique includes extruding, by a tow deposition device, on a tow-by-tow basis, respective impregnated tows of a plurality of respective impregnated tows to form a layer of material on a major surface of a substrate. Each respective impregnated tow includes at least one ceramic fiber and a curable resin coating the at least one ceramic fiber. The example technique includes curing the curable resin to form a cured composite component. An example system includes a tow deposition device, an energy source, and a computing device. The computing device is configured to control the tow deposition device to extrude, on a tow-by-tow basis, respective impregnated tows of a plurality of respective impregnated tows to form a layer of material, and is configured to control the energy source to cure the curable resin to form a cured composite component.

Abstract: Vertical etch heterolithic integrated circuit devices are described. A method of manufacturing NIP diodes is described in one example. A P-type substrate is provided, and an intrinsic layer is formed on the P-type substrate. An oxide layer is formed on the intrinsic layer, and one or more openings are formed in the oxide layer. One or more N-type regions are implanted in the intrinsic layer through the openings in the oxide layer. The N-type regions form cathodes of the NIP diodes. A dielectric layer deposited over the oxide layer is selectively etched away with the oxide layer to expose certain ranges of the intrinsic layer to define a geometry of the NIP diodes. The intrinsic layer and the P-type substrate are vertically etched away within the ranges to expose sidewalls of the intrinsic layer and the P-type substrate. The P-type substrate forms the anodes of the NIP diodes.

Abstract: Vertical etch heterolithic integrated circuit devices are described. A method of manufacturing NIP diodes is described in one example. A P-type substrate is provided, and an intrinsic layer is formed on the P-type substrate. An oxide layer is formed on the intrinsic layer, and one or more openings are formed in the oxide layer. One or more N-type regions are implanted in the intrinsic layer through the openings in the oxide layer. The N-type regions form cathodes of the NIP diodes. A dielectric layer deposited over the oxide layer is selectively etched away with the oxide layer to expose certain ranges of the intrinsic layer to define a geometry of the NIP diodes. The intrinsic layer and the P-type substrate are vertically etched away within the ranges to expose sidewalls of the intrinsic layer and the P-type substrate. The P-type substrate forms the anodes of the NIP diodes.

Abstract: A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

Abstract: A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

Abstract: A gas turbine engine component assembly includes first and second portions, wherein at least one of the first and second portions is a ceramic material. The first portion includes an aperture having a first angled surface. The second portion is disposed within the aperture and includes a second angled surface adjacent to the first angled surface. The first and second angled surfaces lock the first and second portions to one another under a pulling load. A bonding material operatively secures the first and second angled surfaces to one another.

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a vane. The support strut is made of metallic materials. The vane is made of composite materials and is arranged around the support strut to insulate the metallic materials of the support strut during use of the turbine vane assembly.

Abstract: A method of treating a component adapted for use in a gas turbine engine is described herein. The component may comprise ceramic matrix composite materials. The treatment to the ceramic matrix composite component may reduce or eliminate the wear or damage of crack propagation in the ceramic matrix composite component.

Abstract: An airfoil includes a core having a first surface, a skin having a second surface disposed over at least a portion of the first surface of the core, and at least one of a transient liquid phase (TLP) bond and a partial transient liquid phase (PTLP) bond. The bond(s) are disposed between the first surface and the second surface, joining the skin to the core.

Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support strut and a vane. The support strut is made of metallic materials. The vane is made of composite materials and is arranged around the support strut to insulate the metallic materials of the support strut during use of the turbine vane assembly.

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: An example technique includes extruding, by a tow deposition device, on a tow-by-tow basis, respective impregnated tows of a plurality of respective impregnated tows to form a layer of material on a major surface of a substrate. Each respective impregnated tow includes at least one ceramic fiber and a curable resin coating the at least one ceramic fiber. The example technique includes curing the curable resin to form a cured composite component. An example system includes a tow deposition device, an energy source, and a computing device. The computing device is configured to control the tow deposition device to extrude, on a tow-by-tow basis, respective impregnated tows of a plurality of respective impregnated tows to form a layer of material, and is configured to control the energy source to cure the curable resin to form a cured composite component.

Abstract: Vertical etch heterolithic integrated circuit devices are described. A method of manufacturing NIP diodes is described in one example. A P-type substrate is provided, and an intrinsic layer is formed on the P-type substrate. An oxide layer is formed on the intrinsic layer, and one or more openings are formed in the oxide layer. One or more N-type regions are implanted in the intrinsic layer through the openings in the oxide layer. The N-type regions form cathodes of the NIP diodes. A dielectric layer deposited over the oxide layer is selectively etched away with the oxide layer to expose certain ranges of the intrinsic layer to define a geometry of the NIP diodes. The intrinsic layer and the P-type substrate are vertically etched away within the ranges to expose sidewalls of the intrinsic layer and the P-type substrate. The P-type substrate forms the anodes of the NIP diodes.

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.

Abstract: A blade for a gas turbine engine includes composite layers that include a uni-directional layer and a fabric compliant wedge layer that are arranged adjacent to the uni-directional layer. The fabric compliant wedge layer has a reduced compressive Young's modulus compared to the uni-directional layer.

Abstract: A process for manufacturing a ceramic matrix composite component, said process comprising inserting at least one fibrous sheet into a resin transfer molding system. The process includes wetting the at least one (dry or partially wetted) fibrous sheet with a neat first pre-ceramic polymer resin. The process includes injecting a second pre-ceramic polymer resin including a filler material into at least one fibrous sheet and curing the pre-ceramic polymer resin.

Abstract: A process for manufacturing a ceramic matrix composite component, said process comprising inserting at least one fibrous sheet into a resin transfer molding system. The process includes wetting the at least one fibrous sheet with a pre-ceramic polymer resin. The process includes applying a pressure to the at least one fibrous sheet and pre-ceramic polymer resin with an intensifier responsive to thermal expansion and curing the pre-ceramic polymer resin.

Abstract: A system includes, in one example, a shroud configured to circumscribe a plurality of rotor blades of a gas rotor engine, and at least one rub button including a head portion having a height configured to extend into a flow path region of the shroud along a central axis of the rub button that extends radially into the flow path region. The head portion includes a profile, orthogonal to the central axis, that varies according to a defined function of the height of the head portion.