A damper seal for a turbomachine includes an annular body having an inner circumferential surface and an outer circumferential surface separated by a thickness. As such, the inner circumferential surface may define a plurality of cavities arranged into a plurality of circumferential rows and at least one partition positioned between at least two of the plurality of cavities. In addition, the inner circumferential surface may further define at least one plenum arranged between two of the plurality of circumferential rows.

A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.

A turbine engine assembly includes: a fan assembly; a turbine coupled to the fan assembly through a gearbox; a stationary component; and an assembly extending between the gearbox and the stationary component to couple the gearbox to the stationary component, wherein the assembly includes at least one vibration-reducing mechanism configured to isolate a vibratory response of the gearbox from the stationary component.

An acoustic attenuator comprises a first attenuation unit, a second attenuation unit, a welded section, and a communication part. A first acoustic damper is provided on an outer surface of a first acoustic liner, which faces toward a side opposite from an object, to form a first damper space that communicates with an internal space of the object. The second attenuation unit is attached to an outer surface of the object. The welded section is provided at least between the first acoustic damper and a second acoustic damper. The welded section secures the second attenuation unit to the first acoustic liner. The communication part is disposed in a position farther from an outer surface of the object than the welded section, allowing communication between the first damper space and a second damper space.

A balance adjustment method for a rotor includes an imbalance acquisition step of acquiring imbalance position and amount of the rotor after a first balance correction step of correcting balance of the rotor by cutting a compressor wheel side, an excision target section determination step of determining, based on the imbalance position and amount of the rotor, an excision target range including an imbalance correction position of the turbine wheel and a removal amount in the excision target range, and a second balance correction step of correcting the balance of the rotor by repeatedly irradiating the excision target range determined in the excision target section determination step with laser light from a laser marker device to remove by the removal amount from the turbine wheel.

The method of assembling the rotor assembly can include obtaining geometrical reference values about the individual rotor components, based on the geometrical reference values, determining a combination 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; and assembling the rotor components to one another in said determined combination of relative circumferential positions, into the rotor assembly.

Methods, apparatus, systems and articles of manufacture are disclosed. A split shroud for an inner shroud of a gas turbine engine includes: at least one forward shroud segment and at least one aft shroud segment to couple to the at least one forward shroud segment, the at least one forward shroud segment and the at least one aft shroud segment forming a split line.

Methods, apparatus, systems and articles of manufacture are disclosed. A split shroud for an inner shroud of a gas turbine engine includes: at least one forward shroud segment and at least one aft shroud segment to couple to the at least one forward shroud segment, the at least one forward shroud segment and the at least one aft shroud segment forming a split line.

An annular parts assembly for mounting onto a shaft of an aircraft engine is provided. The assembly comprises a first annular body having a surface defining a plurality of pulling features extending from a remainder of the surface, the pulling features circumferentially spaced apart on the surface. The assembly comprises a second annular body defining a balancing ring, the balancing ring concentric with the first annular body, the balancing ring having a plurality of protrusions and circumferential spaces between adjacent ones of the plurality of protrusions, the circumferential spaces accommodating the pulling features such that the pulling features of the first annular body and the protrusions intercalate.

An annular parts assembly for mounting onto a shaft of an aircraft engine is provided. The assembly comprises a first annular body having a surface defining a plurality of pulling features extending from a remainder of the surface, the pulling features circumferentially spaced apart on the surface. The assembly comprises a second annular body defining a balancing ring, the balancing ring concentric with the first annular body, the balancing ring having a plurality of protrusions and circumferential spaces between adjacent ones of the plurality of protrusions, the circumferential spaces accommodating the pulling features such that the pulling features of the first annular body and the protrusions intercalate.