Combustor for gas turbine engine

A combustor comprising:

• an inner liner;
• an outer liner spaced apart from the inner liner;
• an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis;
• fuel nozzles in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented axially to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber;
• nozzle air inlets in fluid communication with the annular combustor chamber to inject nozzle air in the annular combustor chamber, the nozzle air inlets configured for high pressure air to be injected from an exterior of the liners through the nozzle air inlets into the annular combustor chamber and impinge on the injected fuel so as to encourage mixing of injected fuel and injected air, a central axis of each of a plurality of the nozzle air inlets having a tangential component and an axial component relative to the central axis of the annular combustion chamber, the tangential component of the central axes of the nozzle air inlets being oriented in a same common direction;
• a plurality of dilution air holes defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes into the combustor chamber, a central axis of each of a plurality of the dilution air holes having a tangential component relative to the annular combustor chamber, the tangential component of the central axes of the dilution air holes being oriented in a same common direction opposite to that of the tangential component of the nozzle air inlets;
• and
• a plurality of cooling air inlets defined through the inner and outer liner at least downstream of the dilution air holes, the cooling air inlets being substantially smaller than the dilution air holes.