A combustor of a gas turbine engine, the combustor comprising a wall assembly comprising: a support shell (68,70) arranged around an engine central longitudinal axis; and a multiple of liner panels (72,74) and mounted to the support shell (68,70), the multiple of liner panels (72,74) defining a multiple of liner panel gaps (120,122) around the engine central longitudinal axis wherein each of the multiple of liner panel gaps (120,122) are swept with respect to the engine central longitudinal axis; a first liner panel side edge between a liner panel aft edge and a liner panel forward edge; and a second liner panel side edge between the liner panel aft edge and the liner panel forward edge, the first and second liner panel side edges (134,136) non-perpendicular to the liner panel forward and aft edge edges (130,132); wherein the first liner panel side edge, the second liner panel side edge, the liner panel forward edge and the liner panel aft edge generally define a parallelogram, characterised in that the wall assembly further comprises: a multiple of swirlers configured to provide swirl flow; wherein the multiple of liner panel gaps (120,122) include a multiple of outer liner panel gaps and a multiple of inner liner panel gaps, the outer liner panel gaps swept in a direction opposite that of the multiple of inner liner panel gaps, and wherein the multiple of outer liner panel gaps and the multiple of inner liner panel gaps are swept transverse to a flow direction of the swirl flow. a support shell (68,70) arranged around an engine central longitudinal axis; and a multiple of liner panels (72,74) and mounted to the support shell (68,70), the multiple of liner panels (72,74) defining a multiple of liner panel gaps (120,122) around the engine central longitudinal axis wherein each of the multiple of liner panel gaps (120,122) are swept with respect to the engine central longitudinal axis; a first liner panel side edge between a liner panel aft edge and a liner panel forward edge; and a second liner panel side edge between the liner panel aft edge and the liner panel forward edge, the first and second liner panel side edges (134,136) non-perpendicular to the liner panel forward and aft edge edges (130,132); wherein the first liner panel side edge, the second liner panel side edge, the liner panel forward edge and the liner panel aft edge generally define a parallelogram, characterised in that the wall assembly further comprises: a multiple of swirlers configured to provide swirl flow; wherein the multiple of liner panel gaps (120,122) include a multiple of outer liner panel gaps and a multiple of inner liner panel gaps, the outer liner panel gaps swept in a direction opposite that of the multiple of inner liner panel gaps, and wherein the multiple of outer liner panel gaps and the multiple of inner liner panel gaps are swept transverse to a flow direction of the swirl flow. a multiple of swirlers configured to provide swirl flow; wherein the multiple of liner panel gaps (120,122) include a multiple of outer liner panel gaps and a multiple of inner liner panel gaps, the outer liner panel gaps swept in a direction opposite that of the multiple of inner liner panel gaps, and wherein the multiple of outer liner panel gaps and the multiple of inner liner panel gaps are swept transverse to a flow direction of the swirl flow.