Patent ID: 7308794

Claim:
A gas turbine engine combustor comprising a liner defining an annular reverse-flow configuration, the liner extending from an annular upstream dome to a downstream exit, the liner reversing direction thereinbetween, the liner including an inner liner and an outer liner, the dome being substantially planar and substantially perpendicular to an upstream end portion of at least the inner liner, the dome being connected to at least the inner liner through a continuously rounded transition portion extending from the planar dome to the upstream end portion of the inner liner, the dome having a plurality of fuel nozzles mounted therein, the dome having an interior directly exposed to a combustion region of the combustor, the dome further including a plurality of effusion cooling holes provided non-perpendicularly to an entry surface of the holes, the effusion cooling holes in use cooling the dome to relieve heat transferred from the combustion region.