A method for assembly of a rotor of a gas turbine with a housing and a channel which diverges in a direction of flow includes axially displacing the rotor in the direction of flow. Then, an outer sealing ring whose minimum inside diameter is smaller than the maximum outside diameter of the rotor is axially displaced in the direction of flow.

A method for disassembly of a rotor, in particular the front rotor of a gas turbine with a housing and a channel which diverges in a direction of flow and in which the rotor is arranged, is disclosed. An embodiment of the method includes axially displacing an outer sealing ring that is radially opposite the rotor, and whose minimum inside diameter is smaller than the maximum outside diameter of the rotor, against the direction of flow. Then, the rotor is axially displaced against the direction of flow, in particular out of the housing. A method for assembly of such a rotor, as well as a tool for the same, is also disclosed.

A method for estimating rotor torques of an aircraft capable of hovering and comprising a plurality of rotors, which are rotatable under the action of respective rotor torques; and an engine, which is operatively connected to the rotors to provide them with an engine torque. Each rotor comprises a hub and a plurality of blades articulated on the respective hub in such a way that respective collective pitch angles are adjustable. The method comprises the steps of i) calculating a symmetric component on the basis of the engine torque; ii) receiving a signal associated with collective pitch angles; iii) calculating an asymmetric component on the basis of a pitch angle difference between the collective pitch angles; and iv) calculating each rotor torque as the algebraic sum of the symmetric component and the respective asymmetric component.

A turbine rotor blade according to at least one embodiment of the present disclosure comprises a blade root in which a first internal passage extending in a blade height direction is formed and a first opening on one-end side of the first internal passage is formed at the bottom, and an adjustment member attached to the bottom and having formed therein a first through hole overlapping the first opening when viewed from the blade height direction. The first through hole intersects with the first opening when viewed from the blade height direction, and has a first overlapping area that overlaps the first opening and a first non-overlapping area that does not overlap the first opening.

The present invention relates to a rubbing position identification device for a rotating machine provided with a fixed part and a rotating part. This device is provided with an AE sensor, an axial vibration sensor and a rubbing position identification unit. In the case of rubbing occurring in the rotating machine, the rubbing position identification unit calculates the AE phase, which corresponds to the peak of an envelope determined on the base of change over time in the AE signal detected by the AE sensor, and the axial vibration phase, which corresponds to the high spot position of the rotating part specified on the basis of the change over time in the axial vibration signal detected by the axial vibration sensor, and, on the basis of the phase difference between these, identifies the circumferential-direction position of where rubbing has occurred in the rotating machine.