US 12,312,979 B1
Retainer rings for vane assemblies used in gas turbine engines
David L. Sutterfield, Indianapolis, IN (US); and Aric Acius, Indianapolis, IN (US)
Assigned to Rolls-Royce North American Technologies Inc., Indianapolis, IN (US)
Filed by Rolls-Royce North American Technologies, Inc., Indianapolis, IN (US)
Filed on Feb. 21, 2024, as Appl. No. 18/583,829.
Int. Cl. F01D 9/04 (2006.01)
CPC F01D 9/041 (2013.01) [F01D 9/042 (2013.01); F05D 2230/60 (2013.01); F05D 2240/12 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A vane assembly adapted for use in a gas turbine engine, the vane assembly comprising
an outer case arranged around a central axis to define an outer boundary of a flow path of the vane assembly,
a plurality of vanes that extend radially inward from the outer case to direct air through the flow path, and
an inner body assembly arranged around the central axis to define an inner boundary of the flow path of the vane assembly and configured to secure the plurality of vanes radially relative to the central axis, the inner body assembly including an inner body and a retainer ring,
wherein the inner body includes a band and an inner case arranged circumferentially about the central axis and having an outer surface that provides the inner boundary of the flow path of the vane assembly and an inner surface opposite the outer surface, the band is coupled with the inner surface of the inner case and the retainer ring extends into the band of the inner body and into each of the plurality of vanes so that the band radially locates the retainer ring relative to the central axis and the retainer ring radially locates each of the plurality of vanes relative to the central axis,
wherein the band and each of the plurality of vanes cooperate to form a continuous retainer ring receiver having an axially-facing opening that receives a portion of the retainer ring therein such that the retainer ring is removably coupled to the band and each of the plurality of vanes.