Composite liners (such as acoustic panels, fan track liners, and/or ice impact panels or boxes for turbofan engines) and techniques for forming composite liners. In some examples, the composite liner includes at least one region comprising a reinforcement architecture comprising a matrix material, a plurality of relatively tough polymer-based reinforcement elements, and a plurality of second reinforcement elements. The plurality of relatively tough polymer-based reinforcement elements and the plurality of second reinforcement elements are embedded in the matrix material.

An assembly for mounting an auxiliary component to an engine case of a gas turbine includes a support bracket, the support bracket having a first end configured for attachment to a first flange of the engine case, a second end configured for attachment to a second flange of the engine case, and an intermediate portion located intermediate the first end and the second end; a bearing member disposed within the intermediate portion; and a mechanical fuse disposed within the bearing member.

A mounting assembly for mounting an auxiliary component to an engine case of a gas turbine engine includes a first flange configured for attaching the mounting assembly to the engine case; a second flange configured for attaching the mounting assembly to the auxiliary component; and a mechanical fuse disposed between the first flange and the second flange and configured to shear during an overload event.

A device for making a fan or compressor for the aeronautical industry includes an annular casing with a main axis (A) and defines an internal flow duct for a gas flow along this axis. The device further includes a bladed wheel mounted inside the casing and having an axis of rotation coincident with the axis (A) of the casing. A system for retaining debris in the event of breakage of the bladed wheel has a retaining annulus mounted around the casing, which includes two radially outwardly projecting annular bosses located respectively upstream and downstream of the bladed wheel. Upstream and downstream edges of the retaining annulus are applied and attached to the bosses.

A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin and having an outer surface. The composite fan casing further includes at least one stiffener integrally coupled to an aft portion of the outer surface of the core relative to the central axis. Additionally, the at least one stiffener comprises an elastic material.

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.

This composite-material blade formed by using a fiber-reinforced resin containing a resin and reinforcing fibers is provided with: a base material part provided on the inner surface of the composite-material blade; and a first cover part for covering the outer surface of the base material part. The base material part is formed by using a carbon fiber-reinforced resin containing a first resin and carbon fibers. The first cover part is formed from an elastic polymer fiber-reinforced resin containing a second resin and elastic polymer fibers, and has more resistance to impact than the base material part.

An assembly for a turbine engine turbine includes a turbine rotor disc centered on a longitudinal axis, a turbine shaft centered on the longitudinal axis and driven in rotation by the rotor disc. The assembly further includes first means of transmitting torque from the rotor disc to the shaft, wherein the rotor disc is locked in translation relative to the shaft in the direction of the longitudinal axis by a screwed member on the said shaft and second means of transmitting torque from the rotor disc to the screwed member. The screwed member has an unscrewing direction identical to the direction of rotation of the rotor disc in operation, and the second means of transmitting torque are configured to transmit the rotational torque from the rotor disc to the screwed member when the first means of transmitting torque cease to transmit torque from the rotor disc to the shaft.

Woven preforms, for example those used for jet aircraft engine fancases, may need additional stiffeners to improve the strength and/or dynamic performance of the preform assembly, as well as to serve as attachment points. The present invention describes several improved woven preforms that include circumferential or axial stiffeners, as well as methods of manufacturing the same. One embodiment includes circumferential stiffeners added to a woven preform. Another embodiment includes sub-preforms with integral flanges that combine to make integral stiffeners. A further embodiment includes an intermediate stiffener wrapped onto a base sub-preform wrap, wherein the intermediate stiffener wrap incorporates intermediate stiffeners. Another embodiment incorporates bifurcations in one or more layers of an outermost wrap of a multi-layer fabric composite that forms a preform, wherein the bifurcated outer wrap is folded to form stiffeners that may be oriented circumferentially or axially.

A turbine assembly for a turbocharger and method of assembling is disclosed. The turbine assembly may comprise a turbine wheel coupled to a rotatable turbocharger shaft, and a turbine housing that at least partially encloses the turbine wheel. The turbine housing may include an exhaust diffuser configured to direct a flow of exhaust, a support member coupled to the exhaust diffuser by a clamp assembly, the clamp assembly, a diffuser gap and a support gap. The clamp assembly may be disposed on the exhaust diffuser and on the support member. The clamp assembly includes a containment ring and a clamp plate. The containment ring may include a channel. The clamp plate may be disposed in the channel. The diffuser gap may be disposed between the containment ring and the exhaust diffuser. The support gap may be disposed between the containment ring and the support member.