Combustor panel arrangement

A combustor module (18) for a gas turbine engine is provided that includes a first annular liner assembly (26) extending along a longitudinal axis of the engine. The first annular liner assembly (26) includes a first annular support shell (52) and a plurality of first heat shield panels (48,50) coupled to the first annular support shell (52). The first heat shield panels (48,50) form a segmented ring defining a plurality of first axial seams (54) therebetween. The combustor module (18) further includes a bulkhead (30) coupled to the first annular liner assembly (26). The bulkhead (30) provides a plurality of fuel nozzles (38) for passing a first mass flow comprising fuel and air. The combustor module (18) further includes a second annular liner assembly (28) coupled to the bulkhead (30). The second annular liner assembly (28) is in spaced-apart generally coaxial relationship from the first annular liner assembly (26) by a channel height H. The second annular liner assembly (28) includes an air admittance hole (78) having a mean diameter D extending along a hole axis (80). The hole axis (80) is offset from the first axial seam (54) defined by the first heat shield panels (48,50).