Abstract: A ring segment for a gas turbine engine includes a forward mate face with respect to a circumferential flow component of a working fluid of the gas turbine engine, an aft mate face opposite to the forward mate face, an arcuate body extending between the forward mate face and the aft mate face, the arcuate body having a first surface facing to the working fluid and a second surface opposite to the first surface. The first surface includes an arcuate surface extending from the aft mate face toward the forward mate face, the arcuate surface having an arcuate cross section taken in a section plane that is normal to a central axis of the gas turbine engine, and a chamfered surface extending from the forward mate face toward the aft mate face, the chamfered surface having a non-arcuate cross section taken in the section plane.

Abstract: A ring segment assembly includes a ring segment including an impingement pocket having an impingement surface, a plurality of pins extending from the impingement surface, and an impingement plate spaced a non-zero distance from the impingement surface. The plurality of pins are arranged to define a plurality of pinless impingement areas. The impingement plate has a plurality of bumps and a plurality of valleys. The impingement plate defines a plurality of impingement holes. Each impingement hole of the plurality of impingement holes is formed in one of the valleys of the plurality of valleys and positioned opposite one of the plurality of pinless impingement areas.