A protective coating composition for providing protection to a component of a ram air turbine system in need thereof. The protective coating composition comprises an aqueous-soluble or alkaline-soluble polymer matrix, one or more compressible fillers, and one or more non-compressible fillers. The disclosure also provides a method for providing a protective coating onto components of a ram air turbine system in need thereof for providing indentation and scratch resistance thereto.

An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil that has an airfoil section extending from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction. A platform is dimensioned to receive a retention pin to mount the platform to a rotatable hub. At least one of the airfoil and the platform includes a plurality of composite layers that define an internal cavity. A lattice structure in the internal cavity extends between the plurality of composite layers. The lattice structure has a plurality of branches that extend from a plurality of nodes.

A fan of a gas turbine engine includes a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end, wherein the airfoil comprises pockets filled with an elastomeric composite.

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.

An abradable material for a rub strip of a gas turbine engine component includes a polymer matrix, and an organic or inorganic filler distributed through the matrix, wherein the abradable material has a compression spring rate profile including: less than 50,000 lb/in at ?65? F., less than 35,000 lb/in at room temperature, and less than 35,000 lb/in at 200? F.

A stator assembly having: an inner air seal carrier having a mounting body; a plurality of guide vanes secured to the mounting body via a plurality of fasteners; and a fastener retention mechanism secured to the mounting body via the plurality of fasteners. The fastener retention mechanism having: a housing defining an inner chamber; and a filler located within the inner chamber. The portions of the plurality of fasteners are encapsulated within the filler.

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 system comprising a plurality of layers including a relatively erosion-resistant first layer atop a relatively abradable second layer.

A component is provided for a turbine engine. The component can include an airfoil defining a surface, and an energy absorbing composite positioned on the surface of the airfoil or within the airfoil. The energy absorbing composite includes a shear thickening fluid distributed through a matrix.

A turbocharger, with a turbine for expanding a first medium, a compressor for compressing a second medium utilising energy extracted in the turbine during the expansion of the first medium, a turbine housing of the turbine and a compressor housing of the compressor connected to a bearing housing arranged between the same, with a casing that radially and axially surrounds one or more of the turbine housing, the compressor housing, and the bearing housing at least in sections. At least one loose fibre of a defined length is introduced into a hollow space between the casing and a respective housing.

A fan of a gas turbine engine includes a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end, wherein the airfoil comprises pockets filled with an elastomeric composite.