A hydrophilic surface pattern on a removal surface of a steam turbine directs surface moisture in at least one predetermined direction to enhance moisture management by enhancing moisture removal or otherwise reducing erosion caused by moisture in the steam turbine. In some embodiments, the removal surface is located on the outer surface of the nozzle wall adjacent an extraction opening. In some embodiments, the removal surface is located on the surface of the bucket and directs moisture toward the turbine rotor. In some embodiments, the removal surface is located on the surface of the turbine casing or the surface of the nozzle and directs moisture toward a drain in the turbine casing. The hydrophilic surface pattern is preferably laser-etched as a nano-scale pattern to create the hydrophilic surface. In some embodiments, the hydrophilic surface pattern creates a superhydrophilic surface.

A turbocharger includes a turbine housing that is a cast component, a turbine scroll passage, a discharge port, and a discharge port defining member. The turbine scroll passage surrounds the circumference of a turbine chamber defined in the turbine housing and the circumference of the turbine chamber. Exhaust gas that has passed through the turbine chamber is conducted to the discharge port. The discharge port defining member constitutes a wall surface of the discharge port. The discharge port defining member includes a tubular main body wall and an outer circumferential edge. The main body wall constitutes a wall surface of the discharge port. The outer circumferential edge extends from the distal end of the main body wall and outward in the radial direction of the impeller shaft. The outer circumferential edge is fixed between the turbine housing and a downstream exhaust pipe, which is connected to the discharge port.

A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer comprising a metallic matrix and a solid lubricant; and the metallic matrix comprises, by weight, 35% copper, 30.0-45.0% combined nickel, cobalt, and iron with combined iron and cobalt content at most one-third of the nickel content, 2.0-8.0% aluminum, and 5.0-15.0% chromium.

An insulated seal seat assembly comprises a shaft configured and arranged to rotate about an axial axis, a seal seat that is secured to the shaft, and a thermal insulator configured and arranged radially between the shaft and the seal seat.

A component for a gas turbine engine including: a body portion enclosing an interior compartment of the component, the body portion including an interior surface defining the interior compartment, an exterior surface opposite the interior surface, and one or more cooling holes within the body portion, wherein each of the one or more cooling holes extend from the interior surface to the exterior surface; and a porous mesh liner at least partially enclosing the exterior surface of the body portion, the porous mesh liner being fluidly connected to the one or more cooling holes, wherein the cooling holes in operation direct cooling airflow from the interior compartment of the component into the porous mesh liner.

The present disclosure relates to a damping device for absorbing structural vibrations or high excitation frequencies between a first component and a second component of a turbomachine, particularly in connection with high temperature operating conditions. The first component may be a combustor or a burner of a gas turbine and the second component may be a fuel supply line, connected to or passed through a wall of the first component. The damping device may include at least one wire mesh element which is inserted into a housing with a radially outer surface of the wire mesh element being compressed by the housing, and a radially inner surface of the wire mesh element closely surrounding the second component, wherein the housing is fixedly connected to the wall of the first component by a weld seam.

Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.

Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.

A fan blade includes a blade body and a shape memory alloy actuator. The blade body has a pressure side disposed opposite a suction side. Each of the pressure side and the suction side extends radially from a root towards a tip and extends axially from a leading edge towards a trailing edge. The blade body defines a passageway that is disposed between the pressure side and the suction side. The shape memory alloy actuator is received within the passageway and is operatively connected to the blade body.

A fairing for a power generation machine, the fairing comprising: a first layer comprising a metallic material; a second layer comprising a composite; and a third layer positioned between the first layer and the second layer, the third layer being configured to attenuate acoustic waves over a predetermined frequency range.