A computer program product contains computer-readable instructions, which, when operated on by a computer, performs the following method. A combination is determined of relative circumferential positions of the individual rotor components associated to a bow shape configuration of the centers of mass along the axially-extending sequence based on geometrical reference values concerning individual rotor components each having a center of mass and configured to be assembled to one another in an axial sequence to form a rotor assembly, the geometrical reference values being stored in a computer readable memory accessible to the computer.

A machine has: an outer member; an inner member mounted for rotation about an axis relative to the outer member; and a seal system. The seal system has: a seal housing mounted to the outer member; one or more seal rings held by the seal housing and having an inner diameter surface; and a seal runner mounted to the inner member and having a first outer diameter surface portion contacting or facing the inner diameter surface of the one or more seal rings. The seal runner has a circumferential array of mounting features. One or more weights are mounted to one or more of the mounting features.

A rotor shaft cap for a gas turbine has a disk-shaped body defining a first axial face, a second axial face, and an outer radial face. The disk-shaped body has a first annular jaw provided on the first axial face. The first annular jaw includes a plurality of teeth projecting from the first axial face. A plurality of apertures are defined by the disk-shaped body, each aperture of the plurality of apertures extends through the disk-shaped body along an axial direction.

A method for simulating the distribution of blades on a turbomachine disc includes: providing blade configurations, each being associated with a blade and including at least one measurement of a balancing parameter measured on the associated blade; and searching for and selecting a bladed-disc distribution combining the configurations of blades supplied with positions on the disc, the bladed disc distribution encouraging the attainment of at least one criterion defined according to a predetermined cost function dependent on the balancing parameter measurements, and the searching and selecting being performed by successive iterations.

A balancing system and method for an engine of an aircraft includes a housing retaining a magnetorheological fluid including magnetic particles within a carrier fluid. Electromagnets are coupled to the housing. The electromagnets are associated with fan blades of the engine. A balancing control unit is in communication with the electromagnets and sensors of the fan blades.

The invention includes a disc-shaped disc section (30) that is attached to a rotating shaft (6), and blade sections (40) that are provided on a front surface (31) that is one side in an axial direction of the disc section (30). Balance holes (33) for attaching weight-adjusting weight members W thereto are provided at positions where the blade sections (40) are provided in a radial direction, in a rear surface (51) that is the other side in the axial direction of the disc section (30).

A rotor for a turbomachine includes a rim defining a base of a rotor, an airfoil shaped blade extending from said rim and defining a chord line and a bore extending from said rim opposite said airfoil shaped blade. The rim further includes at least one rail extending away from said airfoil shaped blade.

A spool for a gas turbine engine includes at least one rotor disk defined along an axis of rotation and at least one rotor ring defined along the axis of rotation, with the rotor ring being in contact with the rotor disk. The rotor disk and rotor ring are contoured to define a smooth rotor stack load path.

A method is provided of processing one or more blades of a row of blades which forms part of a rotor for a gas turbine engine. The method includes: providing a rotor disc having a slot for mounting one or more blades; applying tape at one or both sides of the slot such that when the blades are loaded in the slot the tape reduces a range of tilt angles which can be adopted by the blades; loading the blades in the slot; and performing a processing operation on the loaded blades.

A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface and respective flanges extending along the radial interface radially outward from the teeth. The first and second portions define a trough axially between and separating the teeth of the first portion from the teeth of the second portion. The first and second portions include facing recesses that form an internal annular cavity along the radial interface.