A housing section of a turbine engine compressor stage or a turbine engine turbine stage that, in particular, has a closed and annular-shaped, radially outer casing. The radially outer casing has radially inwardly extending webs that are angled at a slant relative to the radius.

A fan containment system arranged to be fitted around an array of radially extending fan blades mounted on a hub in an axial gas turbine engine. Each fan blade has a respective tip. The system includes: a cylindrical fan case including a hook projecting in a radially inward direction and positioned axially forward of the radial array of fan blades; a fan track liner disposed on the radially inner surface of the fan case; and a damaging tool which projects radially inwards from the fan case towards the tips. The damaging tool has a tip radially outward of the fan blade tips. The damaging tool is configured that in the event that one of the fan blades is released from the hub, the tip of the damaging tool damages the fan blade tip of the released fan blade to promote penetration of the fan blade into the fan track liner.

A gas turbine casing made of composite material from fiber reinforcement densified by a matrix. The casing includes at least one stiffener portion extending at a radius greater than the radius of upstream and downstream portions of the casing that are adjacent to the stiffener portion so as to form an annular recess in the inside surface of the casing.

A fan track liner for a fan containment arrangement for a gas turbine includes a cellular impact structure and a supporting sub-laminate integrally formed with each other from fibre-reinforced material. The fan track liner further includes a ballistic barrier comprising a woven reinforcing fibre ply and a layer of reinforcing fibre felt. There is also disclosed an associated fan containment arrangement and a method of manufacturing a fan track liner.

A shroud having an annular member extending along an axis from a first end to a second end. The annular member has an inside surface radially inward from an outside surface that diverges from the first end towards the second end relative to the axis. The shroud further includes a flange that extends radially outward from the outside surface and a recess, each located at the second end. The recess extends radially outward from the inside surface and circumferentially about the axis. An axial extent of the recess at least partially coincides with an axial extent of the flange.

A safety apparatus for containing a release of energy from a tension stud of a rotor assembly. The safety apparatus includes a containment member configured to pivot about a pivot location. The containment member includes a tail located on a first side of the pivot location, an elongate region on a second side of the pivot location, the elongate region defining a longitudinal axis and an arm located towards a distal end of the elongate region and projecting away from the longitudinal axis. The containment member is configured to be connected to a tool apparatus. In use, the containment member is configured to pivot between an open position and a containment position in which the arm overlaps with at least part of the tool apparatus in the direction of the longitudinal axis of the elongate region to contain the load energy within the safety apparatus.

A safety apparatus for containing an energy release from a rotor sub-assembly, the safety apparatus includes a plurality of containment members. The containment member has an elongate region defining a longitudinal axis; and at least two arms projecting away from the longitudinal axis of the elongate region; and at least one connecting member connected to at least two of the plurality of containment members. In use the at least one connecting member is configured to connect the safety apparatus to the sub-assembly and the plurality of containment members are configured to withstand an energy release from the sub-assembly.

The disclosure describes 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 air turbine starter for starting an engine, comprising a housing having an interior surface defining an interior, at least one turbine member rotatably mounted within the interior about a rotational axis, and having a plurality of circumferentially spaced blades, and a containment structure radially overlying and circumferentially surrounding at least a portion of the at least one turbine member.

A turbine engine including a fan shaft driven by a turbine shaft with a rotational speed reduction device. A decoupling element is interposed between the reduction device and the fan shaft which operates to decouple the reduction device and the fan shaft. The reduction device is coupled to the fan shaft by a coupling having trapezoidal teeth of the curvic type which are used during the said decoupling operation. The decoupling element is configured to decouple the reduction device and the fan shaft in response to a predetermined resistive torque, referred to as the decoupling torque, which acts between the fan shaft and the reduction device.