A rich-quench-lean combustor assembly for a gas turbine engine defining an axial direction (A) and a circumferential direction (C), the combustor assembly comprising: a fuel nozzle ; a dome , the fuel nozzle attached to the dome ; and a liner attached to or formed integrally with the dome , the liner comprising an inner liner and an outer liner , the liner and the dome together defining at least in part a combustion chamber , the liner extending between a forward end and an aft end, the liner comprising a plurality of quench air jets positioned between the forward end and aft end, the quench air jets comprising a plurality of primary stage air jets and a plurality of secondary stage air jets , the plurality of primary stage air jets each spaced from the plurality of secondary stage air jets along the axial direction (A); characterised in that : the combustion chamber includes a primary combustion zone and a secondary combustion zone , wherein the combustion chamber converges aft of the primary combustion zone ; wherein the quench air jets of the inner liner and the outer liner are positioned at the convergence of the combustion chamber about halfway along a length of the inner liner and outer liner ; wherein the plurality of primary stage air jets is positioned at a forward end of the convergence, and the plurality of secondary stage air jets is positioned at an aft end of the convergence; wherein each of the plurality of primary stage air jets is oriented substantially perpendicularly to an axial centerline of the combustion chamber and each of the plurality of secondary stage air jets is oriented oblique relative to the centerline of the combustion chamber ; and wherein a curved inlet transition is provided immediately forward of each of the plurality of primary stage air jets . a fuel nozzle ; a dome , the fuel nozzle attached to the dome ; and a liner attached to or formed integrally with the dome , the liner comprising an inner liner and an outer liner , the liner and the dome together defining at least in part a combustion chamber , the liner extending between a forward end and an aft end, the liner comprising a plurality of quench air jets positioned between the forward end and aft end, the quench air jets comprising a plurality of primary stage air jets and a plurality of secondary stage air jets , the plurality of primary stage air jets each spaced from the plurality of secondary stage air jets along the axial direction (A); characterised in that : the combustion chamber includes a primary combustion zone and a secondary combustion zone , wherein the combustion chamber converges aft of the primary combustion zone ; wherein the quench air jets of the inner liner and the outer liner are positioned at the convergence of the combustion chamber about halfway along a length of the inner liner and outer liner ; wherein the plurality of primary stage air jets is positioned at a forward end of the convergence, and the plurality of secondary stage air jets is positioned at an aft end of the convergence; wherein each of the plurality of primary stage air jets is oriented substantially perpendicularly to an axial centerline of the combustion chamber and each of the plurality of secondary stage air jets is oriented oblique relative to the centerline of the combustion chamber ; and wherein a curved inlet transition is provided immediately forward of each of the plurality of primary stage air jets . <EOS>