Described is a heat-protection element (50) for a gas turbine (10), in particular an aircraft gas turbine, the heat-protection element (50) being adapted to at least partially surround a bearing chamber (60) of the gas turbine (10) and having at least one connecting portion (52) which is disposed in an axially forward region (VB) and connectable or connected by a material-to-material bond to a protective element (54) of a seal carrier, in particular a seal carrier with a carbon seal, at least one supporting portion (58) which is disposed in an axially central region (MB) and adapted to support the heat-protection element (50) radially on the bearing chamber (60), an end portion (64) which is disposed in an axially rearward region (HB) and forms a free end (66) of the heat-protection element (50) and which is configured such that the end portion surrounds (64) the bearing chamber (60) in a contactless manner.

A radio frequency waveguide communication system includes a guided electromagnetic transmission network, and a cooling air source. The guided electromagnetic transmission network includes one or more remote node in fluid communication with one or more waveguides. The cooling air source is in fluid communication with the guided electromagnetic transmission network and is configured to provide pressurized cooling air to the waveguide. The waveguides direct the pressurized cooling air to the remote node.

A coated article, comprising an article having at least one surface having disposed thereupon an oxidation resistant coating comprising at least two constituents to form a composition, a first constituent comprising at least one thermal expansion component comprising at least about 10% by volume to up to about 99% by volume of the composition, a second constituent comprising at least one oxygen scavenger comprising at least about 1% by volume to up to about 90% by volume of the composition.

A coated article, comprising an article having at least one surface having disposed thereupon an oxidation resistant coating comprising at least two constituents to form a composition, a first constituent comprising at least one thermal expansion component comprising at least about 10% by volume to up to about 99% by volume of the composition, a second constituent comprising at least one oxygen scavenger comprising at least about 1% by volume to up to about 90% by volume of the composition.

A compressor comprising: a casing; an upstream impeller and a downstream impeller for rotation in the casing; a diaphragm comprised of an internal portion and an external portion; an upstream diffuser fluidly coupled to an outlet of the upstream impeller; a return channel fluidly coupled to the upstream diffuser and to an inlet of the downstream impeller, the return channel has a plurality of return-channel blades connecting the internal and external diaphragm portions; and a downstream diffuser fluidly coupled to an outlet of the downstream impeller is disclosed. A first coolant passage is in the internal diaphragm portion and extends around an inner core, the first coolant passage being in heat-exchange relationship with the upstream diffuser and the return channel. A second coolant passage and third coolant passage are separated by a second inner core in the external diaphragm portion and in a heat-exchange relationship with the return channel and the downstream diffuser.

Ionic liquid bath plating methods for depositing aluminum-containing layers utilizing shaped consumable aluminum anodes are provided, as are turbomachine components having three dimensionally-tailored, aluminum-containing coatings produced from such aluminum-containing layers. In one embodiment, the ionic liquid bath plating method includes the step or process of obtaining a consumable aluminum anode including a workpiece-facing anode surface substantially conforming with the geometry of the non-planar workpiece surface. The workpiece-facing anode surface and the non-planar workpiece surface are positioned in an adjacent, non-contacting relationship, while the workpiece and the consumable aluminum anode are submerged in an ionic liquid aluminum plating bath. An electrical potential is then applied across the consumable aluminum anode and the workpiece to deposit an aluminum-containing layer onto the non-planar workpiece surface. In certain implementations, additional steps are then performed to convert or incorporate the aluminum-containing layer into a high temperature aluminum-containing coating, such as an aluminide coating.

Refractory metal cores for manufacturing components of gas turbine engines, manufactured components, and related methods are provided. A refractory metal core includes a trunk configured to attach to a cavity core structure, a first branch extending from the trunk and configured to form a first portion of a cooling circuit in the component, and a second branch extending from the trunk and configured to form a second portion of the cooling circuit in the component. The first branch and the second branch are configured to define fluid exits at two different locations on an exterior of the component.

Refractory metal cores for manufacturing components of gas turbine engines, manufactured components, and related methods are provided. A refractory metal core includes a trunk configured to attach to a cavity core structure, a first branch extending from the trunk and configured to form a first portion of a cooling circuit in the component, and a second branch extending from the trunk and configured to form a second portion of the cooling circuit in the component. The first branch and the second branch are configured to define fluid exits at two different locations on an exterior of the component.

A turbocharger rotor shaft assembly and associated turbocharger that includes at least one turbine rotor member having a first face and an opposed second face; and a rotor shaft having a first end and an opposed second end distal from the first end, wherein the rotor shaft is connected to the at least one turbine rotor at a location proximate to the first end and projects outward therefrom, the rotor shaft having an outwardly oriented face and an interior chamber defined therein, the interior chamber having an interior chamber volume. The turbocharger rotor shaft also includes at least one thermal transfer material contained in the interior chamber of the rotor shaft that has a thermal conductivity value that is greater than the thermal conductivity value of the material of construction of the rotor shaft.

An apparatus and method relating to a film-hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film-hole.