A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.

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.

An article comprising a substrate and at least one coating layer disposed on the substrate. The coating layer includes a silicate glass matrix, an oxygen scavenger phase dispersed through the silicate glass matrix, and at least one metal in metallic form.

A method of fabricating a gas turbine casing out of composite material of varying thickness, the method including making a strip-shaped fiber texture by three-dimensional weaving; winding the fiber texture as a plurality of superposed layers onto a mandrel of profile corresponding to the profile of the casing that is to be fabricated, so as to obtain a fiber preform of shape corresponding to the shape of the casing that is to be fabricated; and densifying the fiber preform with a matrix; wherein, before beginning to wind the fiber texture onto the mandrel, a reinforcing band of width smaller than the width of the fiber texture is placed on the mandrel in a zone that is to form a retention zone of the casing.

A composite airfoil having a non-metallic leading edge protective wrap is provided. In one aspect, the airfoil has a composite core having a pressure sidewall and a suction sidewall each extending between a core leading edge and a core trailing edge. A leading edge protective wrap protects the core leading edge and includes a trailing wrap and a leading wrap. The trailing wrap wraps around the core leading edge and is connected to the composite core. The leading wrap wraps around the core leading edge and is connected to the trailing wrap. The trailing and leading wraps both have leading edges that are spaced from one another. A filler is positioned between the leading edges of the trailing and leading wraps. A protective nose is connected to the leading edge of the leading wrap. The components of the leading edge protective wrap are formed of non-metallic materials.

An apparatus and method for a multiple layer fan casing surrounding a fan having a plurality of circumferentially spaced blades rotatable about a rotational axis and having a sub-portion defining a blade impact zone, the multiple layers comprising an inner fiber layer confronting the blades, an outer fiber layer overlying the inner carbon layer, a glass layer sandwiched between the inner and outer composite fiber layers.

An annulus filler may include an outer lid defining an airflow surface for air being drawn through the engine in an axial airflow direction and a support structure configured to connect the outer lid to a rotor disc. The annulus filler may include a composite material including a plurality of relatively high-modulus reinforcement elements, a plurality of relatively tough polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively high-modulus reinforcement elements and the plurality of relatively tough reinforcement elements.

A turbofan having a dilution rate of at least 10 and including a fan having a disc provided with blades at the periphery thereof, a distance between the head of the blades and the housing of the fan being less than or equal to ten millimeters; a primary flow space and secondary flow space that are concentric; a turbine, housed in the primary flow space and in fluid communication with the fan; and a reduction mechanism coupling the turbine and the fan.

A blade includes an airfoil section extending between leading and trailing edges, first and second opposed sides each joining the leading and trailing edges, and an inner end and a free end. The blade also includes an abrasive tip at the free end of the airfoil section. The abrasive tip includes particles disposed in a matrix material. The matrix material is a polymeric material that has a glass transition temperature greater than or equal to about 225 degrees C. (437 degrees F.). A gas turbine engine and a method of fabricating a blade are also disclosed.