Patent ID: 8387397

Claim:
A gas turbine component in which combustion occurs, comprising: a liner, including a first surface facing a first space and a second surface facing a second space, the liner being interposed between the first and second spaces and having a through-hole defined therein extending from the first to the second surface by which incoming flows proceed from the first space and to the second space, wherein at least the first surface is formed to condition the incoming flows to resist separating from sidewalls of the through-hole, a central portion of the through-hole has a substantially uniform diameter, an edge of the through-hole is radiused at the second surface such that a portion of the through-hole proximate to the second surface has an exponentially increasing diameter receding from the central portion and approaching the second surface, an edge of the through-hole is chamfered at the first surface such that a portion of the through-hole proximate to the first surface has a linearly increasing diameter receding from an angular end of the central portion and approaching the first surface, and wherein the chamfered edge of the through-hole is raised.