A rich-quench-lean combustor assembly for a gas turbine engine defining an axial direction and a circumferential direction, the combustor assembly comprising: a fuel nozzle; a dome, the fuel nozzle attached to the dome; and a liner (102, 108) attached to or formed integrally with the dome, the liner (102, 108) and the dome together defining at least in part a combustion chamber, the liner (102, 108) extending between a forward end (106, 110) and an aft end (104, 112), the liner (102, 108) comprising an annular forward section (182, 184) disposed adjacent the forward end, an annular aft section disposed adjacent the aft end, and an annular convergence section interconnecting the annular forward section and the annular aft section, the liner (102, 108) further comprising a plurality of quench air jets positioned at the convergence section approximately halfway along a length of the liner (102, 108) between the forward end (106, 110) and aft end (104, 112), wherein the dome and the forward section (182, 184) of the liner (102, 108) are each free of cooling holes and are configured to prevent cooling air from entering the combustion chamber and defining a forward section (182, 184) extending from the quench air jets to the dome, the dome and the forward section (182, 184) of the liner (102, 108) configured to be cooled substantially by one or both of impingement cooling or convective cooling; wherein the quench air jets comprise a plurality of primary stage air jets and a plurality of secondary stage air jets, wherein the plurality of primary stage air jets are positioned at a forward end of the convergence section, and are oriented substantially perpendicularly to the axial direction, and the plurality of secondary stage air jets are positioned at an aft end of the convergence section, and are oriented oblique relative to the axial direction such that air is injected in an upstream direction relative to a flow through the combustion chamber; and a flow sleeve extending around the liner (102, 108) and the dome, the flow sleeve defining a plurality of impingement cooling holes sized and oriented to direct an airflow directly onto an outer surface of the forward section (182, 184) of the liner (102, 108) and the dome; wherein the combustor assembly defines a forward height within the combustion chamber between the outer liner and the inner liner at a location forward of the plurality of quench air jets; wherein the combustor assembly further defines an aft height within the combustion chamber between the outer liner and the inner liner at a location aft of the plurality of quench air jets; and wherein a ratio of the forward height to the aft height is at least 1.75:1. a fuel nozzle; a dome, the fuel nozzle attached to the dome; and a liner (102, 108) attached to or formed integrally with the dome, the liner (102, 108) and the dome together defining at least in part a combustion chamber, the liner (102, 108) extending between a forward end (106, 110) and an aft end (104, 112), the liner (102, 108) comprising an annular forward section (182, 184) disposed adjacent the forward end, an annular aft section disposed adjacent the aft end, and an annular convergence section interconnecting the annular forward section and the annular aft section, the liner (102, 108) further comprising a plurality of quench air jets positioned at the convergence section approximately halfway along a length of the liner (102, 108) between the forward end (106, 110) and aft end (104, 112), wherein the dome and the forward section (182, 184) of the liner (102, 108) are each free of cooling holes and are configured to prevent cooling air from entering the combustion chamber and defining a forward section (182, 184) extending from the quench air jets to the dome, the dome and the forward section (182, 184) of the liner (102, 108) configured to be cooled substantially by one or both of impingement cooling or convective cooling; wherein the quench air jets comprise a plurality of primary stage air jets and a plurality of secondary stage air jets, wherein the plurality of primary stage air jets are positioned at a forward end of the convergence section, and are oriented substantially perpendicularly to the axial direction, and the plurality of secondary stage air jets are positioned at an aft end of the convergence section, and are oriented oblique relative to the axial direction such that air is injected in an upstream direction relative to a flow through the combustion chamber; and a flow sleeve extending around the liner (102, 108) and the dome, the flow sleeve defining a plurality of impingement cooling holes sized and oriented to direct an airflow directly onto an outer surface of the forward section (182, 184) of the liner (102, 108) and the dome; wherein the combustor assembly defines a forward height within the combustion chamber between the outer liner and the inner liner at a location forward of the plurality of quench air jets; wherein the combustor assembly further defines an aft height within the combustion chamber between the outer liner and the inner liner at a location aft of the plurality of quench air jets; and wherein a ratio of the forward height to the aft height is at least 1.75:1.