Patent ID: 7726936

Claim:
A turbine engine ring seal segment comprising: a first channel having a radially inwardly concave surface, the first channel being shaped so as to form an extension transitioning into a forward span and an aft span, the forward and aft spans being opposite each other and extending at an angle from the extension in a radially outward direction, wherein the extension of the first channel includes an outer surface that is exposed to turbine blades in use; a separate second channel having a radially inwardly concave surface, the second channel being shaped so as to form an extension transitioning into a forward span and an aft span, the forward and aft spans being opposite each other and extending at an angle from the extension in a radially outward direction, wherein the extension of the second channel includes an outer surface that is exposed to turbine blades in use, the first and second channels being detachably coupled such that the aft span of the first channel substantially abuts the forward span of the second channel so as to define an axial interface and the extensions for the first and second channels form a uninterrupted planar surface across the entirety of the extensions; and at least one of a seal and a bonding material operatively engaging the aft span of the first channel and the forward span of the second channel.