In general, techniques are described for fused filament fabrication of abradable coatings. An additive manufacturing system comprising a substrate defining a major surface, a filament delivery device, and a computing device may be configured to perform various aspects of the techniques. The computing device may be configured to control the filament delivery device to deposit a filament on the substrate, the filament including a powder and a binder, wherein the binder is configured to be substantially removed from the filament and the powder includes a metal or alloy configured to be sintered to form an abradable layer.

A durable light weight, high temperature acoustic CMC liner system. A thin ceramic matrix composite skin, also referred to as a facesheet, forms an outer layer of a cell in the CMC liner system, forming the boundary with the flow of hot gases in the exhaust. A backplate forms the opposite boundary for the cell. The truss structure is formed between the backplate and the facesheet and provides the cell with strength. When the CMC system replaces the metal liner, the backplate thickness is increased so that it is about the thickness of the liner system that it replaces. The truss structure extends between the backplate and the facesheet, forming channels or volumetric spaces. These channels or volumetric spaces are filled with high temperature air permeable acoustic materials that attenuate sound propagated by cooling air in the acoustic range.

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.

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 hot gas path component of an industrial machine includes a cooling pathway with a lattice structure therein. The component and lattice structure are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; a thermal barrier coating over the outer surface; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. A lattice structure is in the cooling pathway at the outer surface. The lattice structure is configured to support the thermal barrier coating over the cooling pathway and in response to a spall in the thermal barrier coating occurring over the cooling pathway, allow a cooling medium from the internal cooling circuit to pass therethrough.

A connecting clip for connecting two pipelines, having a first clip arm, which is designed to extend at least partially around a circumference of a first pipeline, and a second clip arm, which is designed to extend at least partially around a circumference of a second pipeline. The first and the second clip arm are connected to one another in a damping manner, and at least one metal mat is provided as damping element.

An inlet panel for a supercharger comprises a first portion, the first portion comprising one of a perforated material, a micro-perforated material, and a mesh layer. The inlet panel also comprises a second portion, the second portion comprising a recess and an axis. The recess is bordered in part by a side wall and a back wall. The first portion is offset from the back wall in the axial direction. The side wall has an edge located a distance away from the back wall in the axial direction.

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.

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 variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections on the inner and/or outer shroud protrude into the annular gas path, each projection being at least partially circumferentially disposed between two variable vanes and located adjacent the overhang portion thereof. The projections have an angled planar surface that is substantially parallel to a plane defined by a terminal edge of the overhang portion of the variable vanes when pivoted through a vane pivot arc.