Patent ID: 7856830

Claim:
A combustor for a gas turbine engine, the combustor comprising inner and outer liners defining an annular combustion chamber therebetween and joined by a combustor dome, the combustion chamber having a primary section adapted to receive a plurality of fuel nozzles and a secondary section defined downstream of the primary section, the inner and outer liners having a plurality of angled effusion holes defined therethrough in the primary and secondary sections, at least some of the effusion holes in the primary section being located between the fuel nozzles and the combustor dome, wherein a diameter of the effusion holes defined in the primary section is smaller than a diameter of all the effusion holes defined in the secondary section, each of the effusion holes being defined through a corresponding one of the liners at a first non-zero angle with respect to a surface of the corresponding one of the liners and at a second non-zero angle with respect to a corresponding radial plane extending radially from a central axis of the combustor, a density of the effusion holes defined in the primary section being greater than a density of the effusion holes defined in the secondary section.