Patent ID: 9134028
Filing Date: 2015-09-15
Classification: F23R

Abstract:
1. A combustor for a gas turbine engine, the combustor comprising: a liner having first and second concentric annular walls with interconnected upstream ends; an annular combustion chamber defined between inner surfaces of the walls, the combustion chamber having a primary zone adjacent the interconnected upstream ends and a dilution zone downstream of the primary zone; with wherein the at least one heat shield of each of the walls extends over the dilution holes thereof and includes a dilution hole defined therethrough in alignment with each of the dilution holes of a respective one of the walls, and each of the walls includes cumferential row of starter holes defined therethrou downstream of the dilution holes and under a downstream end of each heat shield extending adjacent the dilution zone, and the downstream end of each heat shield extending adjacent the dilution zone is angled away from the inner surface of the primary zone to direct a flow from the starter holes along the inner surface of the dilution zone.