A shaft failure protection system includes an engine core comprising a turbine, a compressor, and a shaft connecting the turbine and compressor; a first braking element connected to a rotating part of the turbine; and a second braking element connected to a static part of the turbine. The first and second braking elements are arranged at an axial distance under normal operating conditions and configured to contact each other in case of a failure of the shaft and an associated axial displacement of the rotating part. The first braking element includes a first friction material and the second braking element comprises a second friction material, wherein the first and second friction materials each comprise a carbon-silica composite or a carbon-fibre-reinforced carbon. Upon shaft failure and associated axial displacement of the rotating part, the first and second friction materials contact each other to reduce speed of the rotating part.

A turbomachine, a computing system for a turbomachine, and a method for overspeed protection are provided. The turbomachine includes a first rotor assembly interdigitated with a second rotor assembly together operably coupled to a gear assembly. A plurality of sensors is configured to receive rotor state data indicative of one or more of a speed, geometric dimension, or capacitance, or change thereof, or rate of change thereof, relative to the first rotor assembly or the second rotor assembly. A controller executes operations including receiving rotor state data from the plurality of sensors; comparing rotor state data to one or more rotor state limits; and contacting one or more of the first rotor assembly or the second rotor assembly to a contact surface adjacent to the respective first rotor assembly or the second rotor assembly if the rotor state data exceeds the rotor state limit.

An automotive cooling fan assembly includes fan driven by a motor. The motor supported by a motor support structure of a shroud. The motor support structure includes a motor carrier and support arms extend radially outward from an outer surface of the motor carrier. The fan includes a central hub and blades that extend radially outward from the side of the hub. An axial operating gap is disposed between an end of the hub and the motor support structure. The motor support structure includes a protrusion that protrudes axially into the operating gap and serves to govern an extent of deflection of the fan during a water fording event.

A bearing assembly for a gas turbine engine comprises a bearing; a bearing bracket, which holds the bearing and is secured by a predetermined breaking device on a connecting element, which can be connected or is connected to a support structure of the gas turbine engine; and a clutch for transmitting a torque from a first clutch element connected in a fixed manner to the rotor of the bearing to a second clutch element supported on the bearing bracket, wherein the clutch elements are spaced apart when the predetermined breaking device is intact and can be brought into contact with one another by destruction of the predetermined breaking device. A gas turbine engine and a method are furthermore provided.

Systems, methods, and devices are provided for a turbine driven pump gearbox. A turbine engine may drive a primary shaft having gears. The gears may selectably engage with gears of a secondary shaft that drives a machine (e.g., pump). By changing which gears of the primary shaft engage with which gears of the secondary shaft, a gear ratio may be changed. A power takeoff device (e.g., a generator) may be connected to the primary shaft and may be operated in reverse as a motor to rotate, slow, stop, and/or reverse rotation of the primary shaft. Brakes may be associated with one or more of the primary and secondary shafts. The power takeoff device and one or more of the brakes may be controlled to shift engagement of the shafts between different positions, changing the gear ratio and/or disengaging the shafts from each other.

A thrust reverser for an aircraft propulsion unit, of the type having a mobile cowl able to move between a closed position that allows the propulsion unit to generate thrust and an open position that allows the propulsion unit to generate a reverse-thrust for slowing the aircraft. The reverser includes braking elements such as a slot and a peg respectively integral with a fixed part of the reverser and with the mobile cowl. These braking elements are configured to cooperate with one another by sliding, with friction, when the mobile cowl effects an overtravel, beyond the open position, so as to generate a braking force that opposes this movement. In one preferred embodiment, the slot for this purpose includes a restriction in section along the direction of travel of the mobile cowl.

Fan (16), in particular for an aircraft cooling unit, having a wheel (128) comprising a hub (138) and an annular array of blades (140), a shaft assembly (136) for driving the wheel about an axis (A), and fusible means for connecting the hub of the wheel to the shaft assembly, said fusible connecting means comprising a first mounting sleeve through which the shaft assembly extends and which is surrounded by the hub, and fusible safety elements (174) which extend parallel to the axis (A) and are configured to break and to disengage the wheel from the shaft assembly when said wheel rotates and a driving torque of the wheel transmitted by the shaft assembly exceeds a certain threshold, characterised in that the connecting means comprise a second wearing sleeve (143) which is inserted between the first sleeve and the hub and through which the fusible elements extend, the second sleeve being made of a material which is different from that of the first sleeve and subject to wear by friction and/or by heating if the shaft assembly continues to rotate following the aforementioned disengagement.

A bidirectional thrust assembly comprises a motor, a selective power transfer mechanism, and a plurality of fans; wherein a change in direction of rotation of the motor causes the selective power transfer mechanism to change a torque transfer among the plurality of fans, wherein the fans may be opposing, and wherein the fans may be unidirectional. The bidirectional thrust assembly may be used in or by a plurality of craft or with respect to other objects which may need to be maneuvered, included suspended load control systems, vertical takeoff and landing craft, watercraft.

A gas turbine engine, includes: an engine core including a turbine, compressor, and shaft system connecting the turbine to the compressor, and forming a torque path therebetween. The shaft system is axially located by a thrust bearing located forward of the turbine, and the engine is configured, in the event of a shaft break which divides the shaft system into a front portion located by the thrust bearing and a rear portion unlocated by the thrust bearing, the rear portion is free to move axially rearwardly under a gas load. The engine further includes a shaft break detector having a forward speed sensor configured to measure a rotational speed of the front portion of the shaft system, and a rear microwave sensor configured to measure a rotational speed of the rear portion of the shaft system, wherein a shaft break can be detected based on differences in the measured speeds.

A bidirectional thrust assembly comprises a motor, a selective power transfer mechanism, and a plurality of fans; wherein a change in direction of rotation of the motor causes the selective power transfer mechanism to change a torque transfer among the plurality of fans, wherein the fans may be opposing, and wherein the fans may be unidirectional. The bidirectional thrust assembly may be used in or by a plurality of craft or with respect to other objects which may need to be maneuvered, included suspended load control systems, vertical takeoff and landing craft, watercraft.