A combustor section for a gas turbine engine comprising: an array of fuel injector nozzles arranged about a longitudinal axis; a combustor liner including an array of liner segments (68; 168) arranged about the longitudinal axis to define a combustion chamber, wherein each one of the fuel injector nozzles defines a nozzle axis, a projection of the nozzle axis extending through the combustion chamber, and each one of the liner segments (68; 168) comprises an external wall extending axially between leading and trailing edges (68LE, 68TE; 168LE, 168TE) and extending circumferentially between opposed mate faces (68M; 168M) with respect to the longitudinal axis, wherein a cooling circuit (70; 170) is defined by the external wall, and a plurality of heat transfer features (72; 172) are distributed in the cooling circuit (70; 170) to define first and second prioritized flow regions (74-1, 74-2; 174-1, 174-2) on opposed sides of a first restricted flow region (74-3; 174-3), each of the first and second prioritized flow regions (74-1, 74-2; 174-1, 174-2) extending axially along the projection of the nozzle axis of respective ones of the fuel injector nozzles from the leading edge (68LE; 168LE) to the trailing edge (68TE; 168TE) such that the first restricted flow region (74-3; 174-3) tapers from the leading edge (68LE; 168LE) to the trailing edge (68TE; 168TE), each of the first and second prioritized flow regions (74-1, 74-2; 174-1, 174-2) having a relatively greater average flow path volume than the first restricted flow region (74-3; 174-3), and wherein the first and second prioritized flow regions (74-1, 74-2; 174-1, 174-2) has a lesser concentration of the plurality of heat transfer features (72; 172) than the first restricted flow region (74-3; 174-3). an array of fuel injector nozzles arranged about a longitudinal axis; a combustor liner including an array of liner segments (68; 168) arranged about the longitudinal axis to define a combustion chamber, wherein each one of the fuel injector nozzles defines a nozzle axis, a projection of the nozzle axis extending through the combustion chamber, and each one of the liner segments (68; 168) comprises an external wall extending axially between leading and trailing edges (68LE, 68TE; 168LE, 168TE) and extending circumferentially between opposed mate faces (68M; 168M) with respect to the longitudinal axis, wherein a cooling circuit (70; 170) is defined by the external wall, and a plurality of heat transfer features (72; 172) are distributed in the cooling circuit (70; 170) to define first and second prioritized flow regions (74-1, 74-2; 174-1, 174-2) on opposed sides of a first restricted flow region (74-3; 174-3), each of the first and second prioritized flow regions (74-1, 74-2; 174-1, 174-2) extending axially along the projection of the nozzle axis of respective ones of the fuel injector nozzles from the leading edge (68LE; 168LE) to the trailing edge (68TE; 168TE) such that the first restricted flow region (74-3; 174-3) tapers from the leading edge (68LE; 168LE) to the trailing edge (68TE; 168TE), each of the first and second prioritized flow regions (74-1, 74-2; 174-1, 174-2) having a relatively greater average flow path volume than the first restricted flow region (74-3; 174-3), and wherein the first and second prioritized flow regions (74-1, 74-2; 174-1, 174-2) has a lesser concentration of the plurality of heat transfer features (72; 172) than the first restricted flow region (74-3; 174-3).