Abstract: A burner construction especially for gas turbine engines in which the combustion takes place in a plurality of small porous ceramic burner cans that are mounted on a flame tube and extend substantially at right angles to the tube with fuel nozzles at the end remote from the flame tube.

Abstract: An igniter for the main burner of a gas turbine engine has an air chamber with a discharge passage and the fuel nozzle or tip is positioned within and in spaced relation to the walls of the passage. The tube has a helical member around the portion of the tube within the passage in order to impart a swirl to the air and the member itself is spaced from the passage walls to produce less swirl at the periphery of the air flow through the passage. The size of the device is such that it may operate continuously utilizing fuel from the main burner supply and air from the engine compressor.