The present invention provides a method of manufacturing an abradable section to be formed on the interior of the casing of a gas turbine engine. The abradable section is formed by an additive manufacturing process to be of a lower density than the surrounding portions of the casing, but integrally formed with those portions. The abradable section thus formed can result in reduced blade fin tip wear, and may also have an improved performance. It may also have lower manufacturing costs. Formation of cooling passages in the abradable section is also easier and a wider range of designs of cooling passages can be provided. A gas turbine engine included such a casing is also provided.

An air seal for use in a gas turbine engine. The seal includes a thermally sprayed abradable seal layer. The abradable material is composed of aluminum powder forming a metal matrix, and co-deposited methyl methacrylate particles and/or hexagonal boron nitride particles embedded as filler in the metal matrix.

A turbomachine casing including a substantially cylindrical wall and an annular one-piece acoustic insulation panel mounted inside the wall, the panel including an annular surface that is radially external opposite a radially internal annular surface of the wall, wherein the wall includes on its internal angular surface first projecting members which bear axially against second projecting members belonging to the external annular surface of the panel and which are fixed to these second members in a dismountable manner.

A thermally conductive lightweight elastomeric seal including a stator substrate having an external surface; a casing coupled to the external surface, the casing including radial walls extending orthogonal radially from the external surface; an abradable material disposed within the casing, the abradable material comprises an elastomer material with imbedded metal-coated hollow microspheres, wherein the abradable material comprises a density of 0.5 to 0.6 grams/cubic centimeter; the abradable material and the casing being coupled together.

A fan case assembly extend along and around a center axis. The fan case assembly may comprise a barrel extending along and around the center axis, the barrel configured to fasten to a flange of an engine case. The fan case assembly may comprise a fan track liner disposed radially inward of the barrel and a containment hook, wherein the containment hook is a discrete component separate from the barrel. The containment hook may include a front segment configured to fasten to the flange, and an axial segment disposed radially inward of the barrel. The axial segment may extend between the flange and the fan track liner and the front segment may extend radially outward from an end of the axial segment. The containment hook may also include a protruding segment extending radially inward from the axial segment.

A blade outer air seal (BOAS) for a gas turbine engine includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.

Described is an abradable component for a gas turbine engine that includes a base having an outboard side which receives a supply of cooling air in use and an inboard side with a plurality of walls thereon. The walls intersect one another to define an abradable network of open faced cells on a gas washed surface thereof, and at least one of the walls includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use.

A blade outer air seal includes a seal arc segment that has a surface layer and an array of internal pockets. The surface layer defines a radially inner side of the seal arc segment. The surface layers conformal with the array of internal pockets such that the surface layer includes an array of ridges that correspond in location and shape to the array of internal pockets.

A method of depositing abradable coating on an engine component is provided wherein the engine component is formed of ceramic matrix composite (CMC) and one or more layers, including at least one environmental barrier coating, may be disposed on the outer layer of the CMC. An outermost layer of the structure may further comprise a porous abradable layer that is disposed on the environmental barrier coating and provides a breakable structure which inhibits blade damage. The abradable layer may be gel-cast on the component and sintered or may be direct written by extrusion process and subsequently sintered.

A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine.