LASER-IGNITION COMBUSTOR FOR GAS TURBINE ENGINE

摘要

The combustor has a laser ignitor mounted to the casing, remotely from the liner of the combustion chamber. The laser ignitor has an igniter beam path for igniting the fuel and air mixture in the combustion chamber, the igniter beam path extending at least partially across the air plenum surrounding the liner and into the combustion chamber through a corresponding beam path aperture provided in the liner.

主权项

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 beam path aperture, 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; at least one laser ignitor mounted to the casing, remotely from the liner, 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 beam path apertures in the liner.