Patent ID: 7954326

Claim:
A gas turbine engine assembly, comprising: a combustor configured to combust an air-fuel mixture to produce combustion gases in a first direction; a transition liner coupled to the combustor and adapted to receive the combustion gases from the combustor and to redirect the combustion gases in a second direction, the transition liner having a plurality of effusion holes that include a first group that extend at least partially in a tangential direction and a second group; and a turbine coupled to the transition liner and adapted to receive the combustion gases from the transition liner, wherein the transition liner has a first edge coupled to the combustor and a second edge coupled to the turbine, the first group being positioned adjacent the first edge, and wherein the effusion holes of the first group have a first angle in the radial-axial plane adjacent the first edge and the effusion holes of the second group have a second angle in the radial-axial plane adjacent the second edge, the first angle being greater than the second angle.