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 (20,30), 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 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 (22,32) in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber, wherein the nozzle air inlets (22,32) are holes made through the inner liner and the outer liner and disposed adjacent to and downstream of the fuel nozzles, the inlets configured for high pressure air to be injected from the exterior of the liners (20,30) through the nozzle air holes (22,32) into the annular combustor chamber; a plurality of dilution air holes (26,36) defined through the inner and outer liners (20,30) downstream of the nozzle air inlets (22,32), the dilution holes (26,36) configured for high pressure air to be injected from an exterior of the liners (20,30) through the dilution air holes (26,36) generally radially into the combustor chamber; and characterised by a central axis of the dilution air holes (26,36) having a tangential component relative to the central axis of the annular combustor chamber, a central axis of at least one of the nozzle air holes (22,32) having a tangential component relative to the central axis of the annular combustor chamber, and the tangential component of the nozzle air holes (22,32) being in an opposite direction to the tangential component of the dilution air holes (26,36). an inner liner; an outer liner spaced apart from the inner liner; an annular combustor chamber formed between the inner and outer liners (20,30), 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 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 (22,32) in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber, wherein the nozzle air inlets (22,32) are holes made through the inner liner and the outer liner and disposed adjacent to and downstream of the fuel nozzles, the inlets configured for high pressure air to be injected from the exterior of the liners (20,30) through the nozzle air holes (22,32) into the annular combustor chamber; a plurality of dilution air holes (26,36) defined through the inner and outer liners (20,30) downstream of the nozzle air inlets (22,32), the dilution holes (26,36) configured for high pressure air to be injected from an exterior of the liners (20,30) through the dilution air holes (26,36) generally radially into the combustor chamber; and characterised by a central axis of the dilution air holes (26,36) having a tangential component relative to the central axis of the annular combustor chamber, a central axis of at least one of the nozzle air holes (22,32) having a tangential component relative to the central axis of the annular combustor chamber, and the tangential component of the nozzle air holes (22,32) being in an opposite direction to the tangential component of the dilution air holes (26,36).