Annular combustor with scoop ring for gas turbine engine

A gas turbine engine comprising:

• a combustor comprising:
• an annular liner defining a portion of a combustion chamber;
• at least an annular scoop ring on the annular liner, the annular scoop ring surrounding the annular liner, the annular scoop ring including a solid radial inner portion provided with bores defined therein and communicating with the combustion chamber to form air dilution inlets, the annular scoop ring having a radial outer portion to define a C-shaped scoop open to receive annular air flow, the bores of the air dilution inlets communicating with the C-shaped scoop to direct an air flow into the combustion chamber, the bores of the air dilution inlets being oriented to generate air jet penetration and direction within the combustion chamber, the solid radial inner portion having a radial thickness greater than that of a surrounding surface of the annular liner to project from the surrounding surface of the annular liner, the bores being formed directly into the solid radial inner portion, the radial thickness of the solid radial inner portion of the scoop ring having a ratio of at least L/D=1 where L is the axial length of the bore and D is the diameter of the bore.