A safety apparatus for containing a release of energy from a tension stud of a rotor assembly, the safety apparatus including a containment member configured to pivot about a pivot location, the containment member including a retaining arm located on a first side of the pivot location and a catch located on a second side of the pivot location, wherein the containment member is movable about the pivot location to a first position in which the catch is engaged with a lip of a disc of the rotor assembly to position the retaining arm in a containment position.

A safety apparatus for containing a release of energy from a tension stud of a rotor assembly, the safety apparatus including a containment member configured to pivot about a pivot location, the containment member including a retaining arm located on a first side of the pivot location and a catch located on a second side of the pivot location, wherein the containment member is movable about the pivot location to a first position in which the catch is engaged with a lip of a disc of the rotor assembly to position the retaining arm in a containment position.

A mount according to an example of the present disclosure includes a locating pin, a load pin, a fastener, the fastener configured to retain a component on at least one of the locating pin and the load pin, the fastener including a bolt, a mounting boss and a spring, the spring allowing the mounting boss to move with respect to the bolt, and wherein the bolt is held captive in the mounting boss with a captive feature. A gas turbine engine and a method of mounting a component are also disclosed.

A mount according to an example of the present disclosure includes a locating pin, a load pin, a fastener, the fastener configured to retain a component on at least one of the locating pin and the load pin, the fastener including a bolt, a mounting boss and a spring, the spring allowing the mounting boss to move with respect to the bolt, and wherein the bolt is held captive in the mounting boss with a captive feature. A gas turbine engine and a method of mounting a component are also disclosed.

A housing for a gas turbine engine accessory includes an enclosure having a drive end with an opening and a closure. The closure is seated in the opening, defines therethrough a shaft aperture and has a v-band flange extending about a periphery of the closure to limit load carried by the enclosure when the engine accessory is mounted to an accessory gearbox mount in a cantilevered arrangement. Engine accessories for gas turbine engines and mounting arrangements for gas turbine engine accessories are also described.

A turbine exhaust case (TEC) has an outer case and an inner case structurally interconnected by a plurality of circumferentially spaced-apart struts. At least one of the struts has an airfoil body with a hollow core. The airfoil body has opposed pressure and suction sides extending chordwise from a leading edge to a trailing edge and spanwise from a radially inner end to a radially outer end. The radially inner end of the strut has a strut wall extension that extends through the inner case to a location radially inward of the inner case relative to the central axis.

A gas turbine engine for an aircraft comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, and a front mount and a rear mount, the front and rear mounts being configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to a casing of the engine core and the front mount is located at substantially the same axial position as a centre of gravity (CG) of the gas turbine engine or forward of the centre of gravity of the gas turbine engine.

A gas turbine engine for an aircraft comprising an engine core comprising a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan comprising a plurality of fan blades; a gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft, and a front mount and a rear mount, the front and rear mounts being configured to connect the gas turbine engine to the aircraft, wherein the front mount is coupled to a casing of the engine core and the front mount is located at substantially the same axial position as a centre of gravity (CG) of the gas turbine engine or forward of the centre of gravity of the gas turbine engine.

The invention relates to an assembly comprising a turbomachine casing (7) and a nozzle made of ceramic matrix composite material having a blade (21), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part (31) of the nozzle to the casing (7), said connecting part (31) extending substantially radially outwards, the blade (21) and said connecting part (31) being formed in one piece, said assembly being characterized in that the connecting part (31) is fastened to a first radial wall (51) integral with the casing (7) by fastening means (53).

The invention relates to an assembly comprising a turbomachine casing (7) and a nozzle made of ceramic matrix composite material having a blade (21), the frontside and backside surfaces of which delimit an internal cavity, and which is connected at its radially external end by a connecting part (31) of the nozzle to the casing (7), said connecting part (31) extending substantially radially outwards, the blade (21) and said connecting part (31) being formed in one piece, said assembly being characterized in that the connecting part (31) is fastened to a first radial wall (51) integral with the casing (7) by fastening means (53).