Embodiments of the present disclosure generally relate to oxide layer compositions for turbine engine components and methods for depositing the oxide layer compositions. In one or more embodiments, a turbine engine component includes a superalloy substrate and a bond coat disposed over the superalloy substrate. The turbine engine component includes an oxide layer disposed over the bond coat, where the oxide layer includes aluminum oxide and a metal dopant. The turbine engine component includes a thermal barrier coating disposed over the oxide layer.

Sealing arrangements and rotor assemblies are provided. A sealing arrangement includes a stationary component, a rotating component spaced apart from the stationary component. A clearance is defined between the stationary component and the rotating component. The sealing arrangement further includes a plurality of magnets embedded within the rotating component. The sealing arrangement further includes a brush seal having a frame and a plurality of magnetically responsive filaments. The plurality of magnetically responsive filaments each extending from the frame to a free end. The plurality of magnetically responsive filaments are attracted to the rotating component by the plurality of magnets. The plurality of magnetically responsive filaments at least partially covering the clearance, such that a flow of fluid across the clearance is restricted.

Flow restricting arrangements and rotor assemblies are provided. A flow restricting arrangement includes a stationary component and a rotating component. The rotating component is radially spaced apart from the stationary component such that a clearance is defined between the stationary component and the rotating component. A first magnet is embedded within the stationary component. A second magnet embedded within the rotating component. A plurality of magnetically responsive particles is contained within the clearance by a magnetic field produced by the first magnet and the second magnet. The plurality of magnetically responsive particles at least partially span the clearance.

A method for stripping a coating off of a blade includes discharging liquid nitrogen through a nozzle onto the blade at a coating to cause lifting of the coating from a substrate of the blade and traversing the nozzle along the blade to cause peeling of the coating off of the substrate of the blade as the nozzle traverses the blade.

A shrouded impeller for centrifugal compressors, and methods for manufacturing shrouded impellers for centrifugal compressors are provided. In one embodiment, the method includes manufacturing an impeller base, then depositing by cold spraying at least one layer of metallic material on the surface of the frontal part of the impeller corresponding to the shroud of the impeller and machining the impeller to complete and finish the structure thereof. The at least one layer deposited by cold spraying may include grooves adapted to optimize the dynamic behavior of the impeller by modifying and tuning the local natural frequencies.

An assembly is provided for a turbine engine. This turbine engine assembly includes an impeller rotor, a seal land and a lip seal. The impeller rotor is configured to rotate about a rotational axis. The impeller rotor is configured from or otherwise includes impeller rotor material. The seal land extends axially along and circumferentially about the rotational axis. The seal land is mechanically attached to and rotatable with the impeller rotor. The seal land is configured from or otherwise includes seal land material that is different than the impeller rotor material. The lip seal radially engages the seal land.

An airfoil includes a first airfoil piece and a second airfoil piece that is 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. The joint includes a braze element of magnesium, zinc, or combinations thereof in a higher concentration than in other portions of the first airfoil piece and the second airfoil piece.

A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nozzle is aft of the fan and defines an exit area. The fan nozzle has a body with an airfoil cross-section geometry. The body includes a wall that has a controlled mechanical property distribution that varies in material macro- or micro-structure by location on the wall in accordance with a desired flutter characteristic at the location.

A blade body for a centrifugal fan assemble including a blade body and an extension blade portion integral to the blade body which when installed on a mounting disc protrudes beyond the mounting disc. Also provided a centrifugal fan assembly including a plurality of fan blades installed on a mounting disc, in which each fan blade includes an extension blade portion protruding beyond the mounting disc and proximal to the driving motor. When the centrifugal fan assembly is in operation, the extension blade portion can provide cooling for the driving motor.

A split ring seal has: a first circumferential end and a second circumferential end; an inner diameter surface and an outer diameter surface; a first axial end face and a second axial end face. A circumferentially distributed first plurality of open channels are along the first axial end face. A circumferentially distributed second plurality of open channels are along the second axial end face.