Patent ID: 11879480
Assignee: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A compressor assembly for a gas turbine engine, the compressor assembly comprising
an outer band that extends at least partway circumferentially around a central axis to define an outer boundary of a gas path of the compressor assembly,
a plurality of variable pitch vanes configured to vary a direction of a gas flowing through the gas path of the compressor assembly, each of the plurality of variable pitch vanes extends radially inward from the outer band relative to the central axis, and each of the plurality of variable pitch vanes being configured to rotate about a pitch axis that extends radially outward from the central axis and through the corresponding variable pitch vane included in the plurality of variable pitch vanes, and
an inner band that extends circumferentially at least partway about the central axis to define an inner boundary of the gas path, the inner band formed to define a plurality of bearing apertures that each receive a portion of one of the plurality of variable pitch vanes, and the inner band includes a forward ring segment that extends partway circumferentially about the axis, an aft ring segment that extends partway circumferentially about the axis, and a rivet that extends axially entirely through the forward ring segment and the aft ring segment and wherein at least one of a forward end and an aft end of the rivet is plastically deformed to couple the forward ring segment with the aft ring segment,
wherein a layer of abradable material is coupled to a radial inner surface of the forward ring segment and a radial inner surface of the aft ring segment.