An epicyclic gear train for a turbine engine includes a gutter with an annular channel. A rotating structure includes a ring gear that has an aperture that is axially aligned with the annular channel. Axially spaced apart walls extend radially outward relative to the rotating structure to define a passageway. The passageway is arranged radially between and axially aligned with the aperture and the annular channel. The walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel.

The invention relates to a rotor for integration in a turbomachine, with a rotor base body, wherein, on the rotor base body in a rotor outer space of the rotor, at least one blade element or airfoil is mounted, wherein the rotor base body extends in an axial direction of the rotor and comprises a connecting section, which extends in an axial direction of the rotor for connection to at least one further rotor and separates the rotor outer space from a rotor inner space of the rotor, wherein the connecting section comprises, in the axial direction, at a front side, preferably in the axial direction at a downstream-lying front side, a balancing flange, wherein the balancing flange is configured for compensating an imbalance of the rotor and extends in the radial direction in the rotor outer space, at least in sections.

A turbofan engine has a fan drivingly engaged by a shaft for rotation about a rotation axis and having: fan blades circumferentially distributed about the rotation axis and drivingly engaged by the shaft; an ice-accruing feature located on a surface of the fan exposed to an air flow flowing between the fan blades, the ice-accruing feature having a shape providing a non-axisymmetric ice accumulation on the fan to create a rotational imbalance; a balancing feature secured to the fan or to the shaft to counteract the ice-accruing feature such that the fan is rotationally balanced when the fan is free of ice, the balancing feature being located such as to be outside the air flow; an aircraft controller; and a sensor operatively connected to the fan and operable to send a signal to the aircraft controller, the signal indicative of the rotational imbalance caused by the ice-accruing feature.

A method of forming a balanced rotor blade assembly includes measuring a weight of a plurality of sub-components of the rotor blade assembly excluding a core. A configuration of a core of the rotor blade assembly is determined. In combination, the core and the plurality of sub-components achieve a target weight distribution and moment. The core is then fabricated and assembled with the plurality of sub-components to form a rotor blade sub-assembly.

A system and method for reducing the vibration response of a rotating system are provided. In one aspect, an optimized balance shot or solution that indicates one or more physical locations at which one or more balancing weights are to be added or removed from the rotating system is generated. The balance shot is generated based on a transfer function that is customized specifically for the rotating system. The transfer function is generated by applying one or more machine-learned models to parameter values for parameters that are associated with the rotating system. The machine-learned models can generate main effects plots, and from the plots, an effective set of parameter values can be determined. The transfer function can be generated using the effective set of parameter values so that the transfer function used to generate the balance shot is optimized specifically for the rotating system undergoing the balancing process.

A turbofan engine has a fan drivingly engaged by a shaft for rotation about a rotation axis and having: fan blades circumferentially distributed about the rotation axis and drivingly engaged by the shaft; an ice-accruing feature located on a surface of the fan exposed to an air flow flowing between the fan blades, the ice-accruing feature having a shape providing a non-axisymmetric ice accumulation on the fan to create a rotational imbalance; a balancing feature secured to the fan or to the shaft to counteract the ice-accruing feature such that the fan is rotationally balanced when the fan is free of ice, the balancing feature being located such as to be outside the air flow; an aircraft controller; and a sensor operatively connected to the fan and operable to send a signal to the aircraft controller, the signal indicative of the rotational imbalance caused by the ice-accruing feature.

A rotor balancing method for a gas turbine on a balancing machine, includes performing a base run by running the rotor at an intended balance speed and measuring the vibrations at a first pedestal; carrying out partial balancing; performing a first influence run by fitting a first balancing weight to a first correction plane in order to reduce vibrations at the first pedestal; performing a second influence run by fitting a first calibration weight to a second correction plane, running the rotor at the intended balance speed and measuring the vibrations at the first pedestal and the second pedestal, and removing the first calibration weight; and carrying out final balancing of the rotor by fitting a final balancing weight to the first correction plane and a second balancing weight to the second correction plane dependent on vibrations measured as part of the first influence run and the second influence run.

A method of forming a balanced rotor blade assembly includes measuring a weight of a plurality of sub-components of the rotor blade assembly excluding a core. A configuration of a core of the rotor blade assembly is determined. In combination, the core and the plurality of sub-components achieve a target weight distribution and moment. The core is then fabricated and assembled with the plurality of sub-components to form a rotor blade sub-assembly.

The present invention relates to a shaft for a propulsion system configured to rotate a reducing mechanism about a rotational axis, the shaft comprising: —a first end configured to engage with an input gear of the reducing mechanism, —a first bellows and a second bellows, the first bellows and the second bellows being rotationally symmetrical about the rotational axis, the first bellows extending between the first end and the second bellows, and —a frustoconical body mechanically connecting the first bellows and the second bellows.

A rotor balancing method for a gas turbine having a rotor with a first correction plane and a second correction plane, wherein a first balancing weight is attached to the first correction plane. The method includes performing a first influence run wherein first balancing weight remains fitted for the subsequent second influence run; fitting a first calibration weight to the second correction plane using a reference influence vector; performing a second influence run; removing the first calibration weight from the rotor and calculating an influence vector of the second correction plane using a first set of vibration measurements and a second set of vibration measurements taken during the first influence run and the second influence run, respectively; and carrying out balancing of the rotor by fitting a final balancing weight to the first correction plane and a second balancing weight to the second correction plane using the calculated influence vectors.