A vibration damping system for a turbine nozzle or blade includes a vibration damping element including a plurality of contacting members including a plurality of damper pins. Each damper pin includes a body. A wire mesh member surrounds the body of at least one of the plurality of damper pins. The wire mesh member has a first outer dimension sized for frictionally engaging within a body opening in the turbine nozzle or blade to damp vibration. Spacer members devoid of a wire mesh member may also be used. The damper pins can have different sizes to accommodate contiguous body openings of different sizes in the nozzle or blade. The body opening can be angled relative to a radial extent of the nozzle or blade.

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.

A vibration damping element for a vibration damping system for a turbine nozzle or blade includes an elongated body and a wire mesh member that surrounds the elongated body. The wire mesh member has a first outer dimension in an inoperative state and a second, larger outer dimension in an operative state. In the operative state, the wire mesh member frictionally engages with an inner surface of a body opening in the turbine nozzle or blade to damp vibration. In the inoperative state, the wire mesh member slides freely in the body opening in the turbine nozzle or blade. A retention system includes a retention member on the elongated body that fixes the wire mesh member relative to a length of the elongated body in the operative state in the body opening of the turbine nozzle or blade.

A secondary air system for an aircraft engine comprises an air flow path communicating between a source of pressurized cooling air and an air consuming component. A filter is disposed in the air flow path upstream from the air consuming component. The filter has at least one of: openings of a size selected for capturing suspended particles; and a filter surface material for binding with chemical contaminants.

A vibration damping system for a turbine nozzle or blade includes a body opening extending through a body of the turbine nozzle or blade between a tip end and a base end thereof. Elongated vibration damping element is disposed in the body opening and includes an elongated body having a first, free end and a second end fixed relative to one of the base end and the tip end. At least one wire mesh member surrounds the elongated body. The wire mesh member(s) frictionally engage with an inner surface of the body opening to damp vibration. A related method is also disclosed.

An improved stator assembly for use in a gas-turbine engine is disclosed. The stator assembly may comprise a vane, an inner diameter (ID) ring, an outer diameter (OD) ring, a vane disposed between the ID ring and the OD ring, a potting component coupling the vane to at least one of the OD ring or the ID ring, and a potting embedded component disposed within the potting component. The potting embedded component may prevent disbond of the potting component during operation of the gas-turbine engine.

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% nickel, 12.0-20.0% cobalt, 5.0-15.0% aluminum, and 5.0-15.0% chromium.

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.

The present disclosure is directed to a system and method for repairing an abradable material coated on a casing of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the gas turbine engine. Further, the articulating guide has a proximal end and a distal end. The system also includes a repair tool configured at a distal end of the articulating guide. The repair tool includes a body having a proximal end and a shaped distal end, with the shaped distal end extending away from the body. Thus, the shaped distal body is configured to trench out an area of the abradable material comprising a defect. The system also includes a filler material for filling the trenched out area.

A bearing includes a thrust gas bearing attached to a journal bearing and two or more converging-diverging orifices defined in a surface of at least one of the thrust gas bearing and the journal bearing. The converging-diverging orifices supply at least one pressurized gas to an interior of the bearing. Hydrodynamic lifting grooves are provided on the faces of the thrust gas bearing and the journal bearing and provide improved load capacity and sealing capabilities. Control over the ratios of the pressurized gases provides for additional sealing capabilities and reduced leakage. A metal mesh damper provides increased damping of the gas bearing.