Described is a shaft support system for a gas turbine engine comprising: a rotatable fan shaft; first and second support structures extending in parallel from the shaft to a load bearing structure to provide radial location of the shaft within an engine casing, wherein the first support and second support structures include first and second respective mechanical fusible joints; wherein the first fusible joint is a two-stage fuse which partially fails within a first predetermined load range, the second fusible joint fails within a second predetermined load range which is different to the first load range, and the first fusible joint fully fails only when the second fusible joint has failed.

The invention relates to a torque limiting device in a torque bearing connecting structure between a gearbox and a stationary structure in a gas turbine engine, wherein the torque limiting device comprises a mechanical fuse in the connection structure comprising an at least partially circumferential weakening of the material. The invention also relates to a gas turbine engine.

An accessory assembly of a turbine engine has a support structure and a shaft coupled to the support structure by means of a pair of main bearings and provided with an end portion, which has a shear neck designed to break when the torque transmitted to that shaft exceeds a predetermined design threshold; the accessory assembly also has a gear, which defines a motion inlet, is fixed to the end portion and, when said shear neck breaks, remains supported by a single secondary bearing; the latter is distinct from said main bearings and is arranged axially between said shear neck and the gear.

Aspects of the disclosure are directed to a system associated with an aircraft engine, comprising: a gearbox, a link coupled to the gearbox, and a bracket coupled to the link, where the bracket includes at least one notch formed in the bracket to provide a pilot for a fuse trigger, and where a portion of the bracket contained within the at least one notch breaks away from the bracket when the system experiences a load that is less than a nominal load associated with a fan blade out event of the aircraft engine.

A vaned ring for a turbomachine stator includes an outer shell (42), a vane (46) having a vane head (52), and two platforms (60) arranged circumferentially on either side of the vane head, and fixed on a radially inner face (61) of the outer shell by means of detachable fasteners. The vane head has first conical seatings (70) bearing on respective second conical seatings (72) of the two platforms so as to prevent a displacement of the vane radially inwards and along the circumferential direction. The vaned ring comprises a frangible pin (73) including a base (73A) mounted on the outer shell and a head (73B) projecting radially inwards with respect to the outer shell and having a head surface (73C) forming, vis-a-vis a top surface (74) of the vane head, a stop opposing a displacement of the vane radially outwards.

A method of reducing loads in a rotor assembly during an imbalance condition, a shape memory alloy recoupler device, and a hybrid bearing support system are provided. The hybrid bearing support system includes a shaft extension fixedly coupled to a rotatable member at a radially inner end of the shaft extension, a radially outer end of said shaft extension fixedly coupled to a rotatable race of a bearing supporting the rotatable member, and a recoupler device formed of a shape memory alloy (SMA) material coupled in parallel with at least a portion of said shaft extension between the radially inner end and the radially outer end.

A turbomachine (10) comprising a fan (12) shaft driven by a turbine shaft (16) by intermediary of a rotational speed reduction device (20), said turbomachine comprising decoupling means (28) interposed between the reduction device (20) and the fan shaft (18), which decoupling means are able to decouple the reduction device (20) and the fan shaft (18), characterized in that the reduction device (20) is coupled to the fan shaft via the intermediary of a coupling (17) having trapezoidal teeth of the curvic type which comprises said decoupling means (28), said decoupling means (28) being configured to decouple the reduction device (20) and the fan shaft (18) in response to a predetermined resistive torque (C.sub.D), referred to as the decoupling torque, being exceeded, which torque acts between the fan shaft (18) and the reduction device (20).

A method for compression of an incoming feed air stream using at least two variable speed compressor drive assemblies controlled in tandem is provided. The first variable speed drive assembly drives at least one compression stage in the lower pressure compressor unit driven while the second variable speed drive assembly drives higher pressure compression stage disposed either in the common air compression train or the split functional compression train of the air separation plant. The first and second variable speed drive assemblies are preferably high speed, variable speed electric motor assemblies each having a motor body, a motor housing, and a motor shaft with one or more impellers directly and rigidly coupled to the motor shaft via a sacrificial rigid shaft coupling.

A method for compression of an incoming feed air stream using at least two variable speed compressor drive assemblies controlled in tandem is provided. The first variable speed drive assembly drives at least one compression stage in the lower pressure compressor unit driven while the second variable speed drive assembly drives higher pressure compression stage disposed either in the common air compression train or the split functional compression train of the air separation plant. The first and second variable speed drive assemblies are preferably high speed, variable speed electric motor assemblies each having a motor body, a motor housing, and a motor shaft with one or more impellers directly and rigidly coupled to the motor shaft via a sacrificial rigid shaft coupling.

An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas. A gear train is drivingly coupled with the turbine member, a drive train is operably coupled with the gear train, and an output shaft is selectively operably coupled to rotate with the engine via a decoupler.