A blade (1) for a turbomachine, including an impact chamber (2), a single impulse body (3) being situated in the impact chamber, a clearance (S1+S2) between the impulse body and the impact chamber being at least 10 μm and/or at most 1.5 mm in at least one direction.

Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a platform surrounding the main body, the platform comprising a slash face. The rotor blade further includes a damper stack disposed at the slash face and extending generally along an axial direction. The damper stack includes a plurality of damper pins, each of the plurality of damper pins being in contact with a neighboring damper pin.

Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a platform surrounding the main body, the platform comprising a slash face. The rotor blade further includes a damper stack disposed at the slash face and extending generally along an axial direction. The damper stack includes a plurality of damper pins, each of the plurality of damper pins being in contact with a neighboring damper pin.

Identifying effects of geometric variations of physical parts may include measuring one or more surfaces of a physical part in three-dimensions, analyzing measurements of the physical part to determine a geometric variation from a baseline model, modifying an existing computational fluid dynamics (CFD) mesh for the baseline model based on the geometric variation using a mesh metamorphosis algorithm to create a target mesh for the physical part, and analyzing the target mesh using a CFD analysis to determine an effect (e.g., an effect on unsteadiness) in a system caused by the geometric variation.

Identifying effects of geometric variations of physical parts may include measuring one or more surfaces of a physical part in three-dimensions, analyzing measurements of the physical part to determine a geometric variation from a baseline model, modifying an existing computational fluid dynamics (CFD) mesh for the baseline model based on the geometric variation using a mesh metamorphosis algorithm to create a target mesh for the physical part, and analyzing the target mesh using a CFD analysis to determine an effect (e.g., an effect on unsteadiness) in a system caused by the geometric variation.

A method for operating a machine plant having a shaft train, including: a) determining the harmonic frequency of a torsional vibration mode of the shaft train and determining mechanical stresses arising during a vibration period of the torsional vibration mode; b) determining a correlation for each torsional vibration mode between a first stress amplitude, at a position of the shaft train that carries risk of stress damage, and a second stress amplitude, at a measurement location of the shaft train, using stresses determined for the respective torsional vibration mode; c) establishing a maximum first stress amplitude for the position; d) establishing a maximum second stress amplitude, corresponding to the maximum first stress amplitude, for the measurement location; e) measuring the stress of the shaft train while rotating; f) determining a stress amplitude at each harmonic frequency; g) emitting a signal when the stress amplitude reaches the maximum second stress amplitude.

A compressor, in particular, of a turbomachine. The compressor comprises at least one blade ring and at least two ring segments, wherein the blade ring has at least two equally large ring segments. The compressor also comprises blades, which are arranged in the ring segments of the blade ring in such a way that a first number of blades is arranged in a first ring segment and a second number of blades is arranged in a second ring segment. The first number of blades is not equal to the second number of blades.

A compressor, in particular, of a turbomachine. The compressor comprises at least one blade ring and at least two ring segments, wherein the blade ring has at least two equally large ring segments. The compressor also comprises blades, which are arranged in the ring segments of the blade ring in such a way that a first number of blades is arranged in a first ring segment and a second number of blades is arranged in a second ring segment. The first number of blades is not equal to the second number of blades.

The present invention reltues to an assembly Ru a turbomachine, comprising: a first rotor; a second rotor, and, a damper (2) configured to damp a displacement of the first rotor relative to the second rotor, the damper comprising: a first portion (21) bearing against the first rotor and having a first thickness, a second portion (22) bearing against the second rotor and having a second radial thickness, and a third portion (23) connecting the first portion (21) to the second portion (22) and having a third radial thickness, wherein the third radial thickness is greater than at least one of the first radial thickness and the second radial thickness.

The present invention reltues to an assembly Ru a turbomachine, comprising: a first rotor; a second rotor, and, a damper (2) configured to damp a displacement of the first rotor relative to the second rotor, the damper comprising: a first portion (21) bearing against the first rotor and having a first thickness, a second portion (22) bearing against the second rotor and having a second radial thickness, and a third portion (23) connecting the first portion (21) to the second portion (22) and having a third radial thickness, wherein the third radial thickness is greater than at least one of the first radial thickness and the second radial thickness.