Abstract: A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component.

Abstract: An exemplary gearbox assembly includes a shear bracket connectable to a flange of a housing structure, and a support pin extending along a longitudinal axis, the support pin supporting the shear bracket relative to a turbomachine, the shear bracket moveable axially relative to the support pin.

Abstract: A component for a gas turbine engine according to an exemplary embodiment of the present disclosure includes, among other possible things, a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.

Abstract: An apparatus for depositing a coating on one or more parts (21) has: a chamber (22); a part holder (64) for carrying the part(s); a bias voltage source (94) coupled to the part(s) to apply a bias voltage to the part(s); a source (34) of the coating material; a plurality of temperature sensors (76); and a plurality of leads (90) passing outputs of the temperature sensors out from the chamber. A temperature monitoring system (150) has a temperature data processor (300). At least one fiber optic link (223) couples the temperature data processor to the temperature sensors so as to electrically isolate the temperature data processor from the bias voltage.

Abstract: An air seal for use with rotating parts includes a thermal barrier coating layer adhered to a substrate. An abradable layer is adhered to the thermal barrier coating layer. The abradable layer comprises a matrix of agglomerated hexagonal boron nitride and a metallic alloy. Another hexagonal boron nitride is interspersed with the matrix.

Abstract: A fuel system is disclosed. The fuel system may include a fuel supply, a fuel supply conduit fluidly connecting the fuel supply to an engine, and a fuel pump in fluid communication with the fuel supply conduit. The fuel system may also include a bypass conduit including a first end fluidly connected to the fuel supply conduit proximate an inlet of the fuel pump, and a second end fluidly connected to the fuel supply conduit proximate an outlet of the fuel pump. The fuel system may also include a bypass valve in fluid communication with the bypass conduit. The bypass valve may be configured to allow fuel to flow from the first end to the second end of the bypass conduit.

Abstract: A lubrication system includes an auxiliary lubricant tank 48, a supply conduit 58 extending from a source of lubricant 26 to the auxiliary lubricant tank. A reduced-G bypass line 108 branches from the conduit and enters the auxiliary tank at a first elevation E1. The system also includes an auxiliary tank discharge conduit 116, a portion of which resides within the tank. The resident portion has an opening 122 at least partially at a second elevation E2 higher than the first elevation.

Abstract: Helmet mounted display apparatus for use in aircraft and rotorcraft includes an first image source for generating images comprising pilotage symbol information, a second image source for sensing and generating images of the exterior scene, and relay optical components that optically superimpose the two images together and subsequently project the superimposed image into the observer's forward field of view.