Patent ID: 9441546
Filing Date: 2016-09-13
CPC Classification: F02C,F02P,F23Q,F23R

Claim Text:
1. A combustor for a gas turbine engine, the combustor comprising: a casing forming a pressure vessel and having an inlet for receiving compressed air; a liner held inside the casing and delimiting a subchamber of the pressure vessel from a plenum extending between the liner and the casing, the liner having a plurality of apertures formed therethrough and allowing controlled fluid flow communication of the compressed air from the plenum into the subchamber, with at least one of the plurality of apertures being a dilution hole, and an outlet leading to a turbine stage of the gas turbine engine; at least one fuel nozzle mounted to the liner, for injecting fuel into the subchamber, the liner having a combustion flow path extending from the fuel nozzle to the outlet; at least one laser ignitor having a beam outlet, the at least one laser ignitor mounted to the casing remotely from the liner and wherein the beam outlet is positioned aft of the dilution hole in an axial direction, the at least one laser ignitor having an igniter beam path for igniting the fuel and air mixture in the subchamber, the igniter beam path extending at least partially across the plenum and into the subchamber through a corresponding one of the at least one dilution hole in the liner; wherein the laser ignitor is on one side of the corresponding dilution hole and the laser beam path extends into the subchamber on another side of the corresponding dilution hole relative to the combustion flow path, the igniter beam path extending obliquely across the corresponding dilution hole relative to the combustion flow path.