A guide vane segment 10 for a turbomachine includes a radially inner shroud plate 13 having a shroud plate surface 14 that is adapted to be configured in the turbomachine to face a rotor blade 20 adjacent to the guide vane segment, and thereby essentially extend along an outer conical surface K.sub.1 whose cone axis coincides with the axis of rotation A of a rotor shaft 30. In a radially inner region, a rotor blade 20 for a turbomachine has a base plate 23 having a base plate surface 24 that is adapted to be configured in the turbomachine to face a shroud of a guide vane row 10 adjacent to the rotor blade and thereby essentially extend along an outer conical surface K.sub.2 whose cone axis coincides with the axis of rotation A of a rotor shaft 30.

An arrangement for detecting a shaft break, including a shaft and a reference shaft that can be rotated together with the shaft, wherein an opening in the shaft overlaps with an opening in the reference shaft in an operational state of the shaft according to the intended use, and a signal conductor that can be severed extends through the two openings and is operatively connected to an evaluation unit, and the evaluation unit is configured to detect a severing of the signal conductor by applying a signal to the signal conductor to detect a shaft break of the shaft. The invention further relates to a turbomachine and a method.

An arrangement for detecting a shaft break, including a shaft and a reference shaft that can be rotated together with the shaft, wherein an opening in the shaft overlaps with an opening in the reference shaft in an operational state of the shaft according to the intended use, and a signal conductor that can be severed extends through the two openings and is operatively connected to an evaluation unit, and the evaluation unit is configured to detect a severing of the signal conductor by applying a signal to the signal conductor to detect a shaft break of the shaft. The invention further relates to a turbomachine and a method.

A turbomachine includes a fan shaft driven by a turbine shaft via a device for reducing a speed of rotation. The turbomachine includes an uncoupling device interposed between the reduction device and the turbine shaft. The uncoupling device is configured to uncouple the reduction device and the turbine shaft in response to the exceeding of a determined resistant torque exerted by the reduction device on the turbine shaft.

A turbomachine includes a fan shaft driven by a turbine shaft via a device for reducing a speed of rotation. The turbomachine includes an uncoupling device interposed between the reduction device and the turbine shaft. The uncoupling device is configured to uncouple the reduction device and the turbine shaft in response to the exceeding of a determined resistant torque exerted by the reduction device on the turbine shaft.

The invention regards a gas turbine engine control system and a method for limiting turbine overspeed in case of a shaft failure. The control system includes: an overspeed protection system that activates an activation member in case a shaft failure is detected; a fuel limiting mechanism coupled with the activation member, wherein the fuel limiting mechanism is configured to limit the fuel supply to the gas turbine engine combustor if the activation member is activated; a variable stator vane mechanism which is configured to adjust variable stator vanes of a compressor of the gas turbine engine in their rotational position, the variable stator vanes having a closed position which blocks air flow through the compressor. A connecting fuel line connecting the fuel limiting mechanism and the variable stator vane mechanism is provided, wherein upon activation of the activation member the fuel limiting mechanism pressurizes the connecting fuel line, thereby activating the variable stator vane mechanism to move at least one row of the variable stator vanes into the closed position.

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.

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 abnormality treatment apparatus includes: a sensor which outputs a signal upon detecting an event caused by contact of a rotor of a rotating machine during rotation of the rotor; and a control unit which executes at least one of rotation number control of reducing the number of rotations of the rotor step by step, liquid injection control of injecting liquid into a housing chamber of the rotor step by step, and pressure control of lowering a discharge pressure of the rotating machine step by step based on reception of the signal output from the sensor.

A safety apparatus for containing a release of energy from a tension stud of a rotor assembly, the safety apparatus includes an elongate member defining a longitudinal axis and at least two arms projecting away from the longitudinal axis of the elongate member. In use, in a first orientation, the elongate member is configured to be connected to a tool apparatus for applying a load energy to the tension stud and the at least two arms of the safety apparatus are configured to overlap with at least part of the tool apparatus in the direction of the longitudinal axis of the elongate member to contain the release of energy therebetween.