Abstract: A lubricant scoop is disclosed. The lubricant scoop includes an annular body configured for engagement with a shaft rotating about a central axis. The annular body includes a first annular portion and a second annular portion disposed adjacent the first annular portion. The first annular portion includes a radially oriented entrance surface and a first axially oriented transition surface. The second annular portion includes a second axially oriented transition surface, a primary redirection member spaced radially outward from the second axially oriented transition surface, a radially oriented exit surface and an exit conduit having an opening positioned on the radially oriented exit surface.

Abstract: A support ring for a gas turbine engine includes a main body portion extending circumferentially about a center axis, a radially extending portion extending radially inward from the main body portion and having a plurality of openings, and a plurality of anti-rotation tabs extending radially inward from the main body portion and axially spaced from the radially extending portion.

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. A airfoil skin cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The airfoil skin cooling passage extends to a platform skin cooling passage arranged in the platform. The platform skin cooling passage resupplied by a backside of the platform.

Abstract: A system for monitoring fuel additives on board a vehicle includes a fuel line carrying fuel from a fuel source to an engine; a fuel additive sensor configured to measure concentration of additives in fuel at a point along the fuel line; a fuel additive dispenser connected in parallel to the fuel line; at least one flow control device for controlling an amount of flow from the fuel line into the fuel additive dispenser; and a controller configured to receive input from the fuel additive sensor and to control the flow control device to adjust the amount of the flow from the fuel line into the fuel additive dispenser.

Abstract: A blade outer air seal has at least one internal surface and a layer atop the at least one internal surface. The layer has: a matrix comprising at least one of hafnium silicate (HfSiO4) and zirconium silicate (ZrSiO4), ytterbium disilicate (Yb2Si2O7); and barium magnesium alumino silicate (BMAS) or other alkaline earth aluminosilicate.

Abstract: An interface for a gas turbine engine. The interface includes a full-hoop vane ring around the engine axis, the full-hoop vane ring comprises a forward vane rail with a vane ring forward contact surface and a vane ring anti-rotation tab, the vane ring anti-rotation tab engaged with the anti-rotation case slot; and a multiple of BOAS segments around the engine axis, each of the multiple of BOAS segments comprise a BOAS aft engagement feature and a BOAS aft contact surface, the BOAS aft engagement feature engaged with the outer case and the anti-rotation case slot, the BOAS aft contact surface abuts the vane ring forward contact surface.

Abstract: An interface assembly for a gas turbine engine. The interface a full-hoop vane ring around the engine axis, the full-hoop vane ring comprises an aft vane rail with a vane ring contact surface, the aft vane rail engaged with the anti-rotation case slot at a vane ring anti-rotation tab; and a multiple of BOAS segments around the engine axis, each of the multiple of BOAS segments comprise a BOAS forward engagement feature and a BOAS contact surface, the BOAS forward engagement feature engaged with the outer case, the BOAS contact surface abuts the vane ring contact surface.

Abstract: An apparatus for countergravity casting a metallic material, comprises: a crucible for holding melted metallic material; a casting chamber for containing a mold; a fill tube capable of extending into the crucible to communicate melted metallic material to the casting chamber; a gas source coupled a headspace of the melting vessel to allow the gas source to pressurize said headspace to establish a pressure differential to force the melted metallic material upwardly through said fill tube into said mold; and means for gettering sulfur.

Abstract: A seal ring for a non-contact seal may comprise an annular body comprising a first side surface, a second side surface, an outer surface, and an inner surface, and a plurality of window openings disposed in the annular body. The plurality of window openings may be configured to provide access to the seal for installation of a melting member to secure the seal shoes in an outboard direction during installation.

Abstract: An additive manufacturing method includes segmenting a CAD file of a component along a build interface to define at least a first component segment and a second component segment, each of the first component segment and the second component segment sized to fit within an additive manufacturing build chamber; additive manufacturing the first component segment and the second component segment within the build chamber; and bonding the first component segment and the second component segment to form the component.

Abstract: A combustor for a gas turbine engine including a forward liner panel mounted to a support shell via a multiple of studs, the forward liner panel including an aft non-linear circumferential edge and an aft liner panel mounted to the support shell via a multiple of studs, the aft liner panel including a forward non-linear circumferential edge that is complementary to the aft non-linear circumferential edge.

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.

Abstract: An abrasive tip comprises an additive, the additive is configured to prevent adhesion of an organic component from an abradable seal onto an abrasive blade tip.

Abstract: An airfoil includes a first airfoil piece and a second airfoil piece bonded to the first airfoil piece at a joint. The first airfoil piece and the second airfoil piece are formed of aluminum alloys. At least one of the aluminum alloys is an aluminum alloy composition that has greater than 0.8% by weight of zinc.

Abstract: Component for gas turbine engines are provided. The components include a platform, the platform defining a platform cavity on a first side, an airfoil extending from a second side of the platform, wherein the airfoil comprises at least one airfoil cavity located within the airfoil, the at least one airfoil cavity fluidly connected to the platform cavity through an airfoil cavity inlet, and a platform flow turning element positioned on the first side of the platform, the platform flow turning element having a turning portion and a tapering portion, wherein the turning portion directs incoming air to turn from the platform cavity into the airfoil cavity and the tapering portion extends through the airfoil cavity inlet and into the airfoil cavity.

Abstract: A cover plate according to an exemplary aspect of the present disclosure includes, among other things, a body, a first tab near a bore of the body, and a second tab circumferentially spaced from the first tab. A slot is defined between the first tab and the second tab, the first tab, the second tab and the slot extending at an angle relative to a slot axis that extends through the bore. In another embodiment, the cover plate includes a bumper that limits deflection of the body.

Abstract: A seal assembly for a bearing compartment of a gas turbine engine includes a seal carrier, a seal element, a seal plate, and a trough. At least a portion of the seal element is within the seal carrier. The seal plate is in contact with the seal element and is configured to rotate relative to the seal element. The trough extends around the seal plate and comprises an annular channel positioned to capture oil slung from the seal plate.

Abstract: A preloaded ball bearing assembly includes a primary bearing assembly disposed between a rotating component and a static structure. The assembly also includes a preload bearing assembly disposed in contact with the rotating component. The assembly further includes a flexible support disposed between the primary bearing assembly and the preload bearing assembly.

Abstract: A system for controlling a plurality of electromechanical effectors operably connected to an engine to control engine parameters. The system also includes a plurality of sensors operably connected to measure a state or parameter of each effector, a power supply configured to supply power to the plurality of effectors, and a controller operably connected to the plurality of sensors, the plurality of effectors, and the power supply. The controller executes a method for an adaptive model-based control for controlling each effector, The method includes receiving a request indicative of a desired state for each effector, receiving a weighting associated each request, obtaining information about a current state of each effector, and updating an adaptive model based control (MBC) based upon the information. The method also includes generating a control command for an effector based upon the adaptive MBC and commanding the effector based upon the control command.

Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A tip trench is provided in the tip and wrapping at least a portion of the airfoil from the pressure side wall around the leading edge to the suction side wall. The tip trench is provided by a recess.