Patent ID: 8561409
Filing Date: 2013-10-22
Classification: F23R

Abstract:
1. A burner of a gas turbine engine, comprising: axially opposed upstream and downstream end portions arranged to receive mixed fuel and air to be burnt in a main flame of the burner, a quarl arranged to house the main flame, wherein the quarl comprises a plurality of quarl sections, a pilot combustor supplying a high concentration of free radicals directly to a forward stagnation point and to the main flame formed as the conical rotational symmetric shear layer around the recirculation zone, an annular premixing channel for premixed air and fuel arranged between walls of the first and second quarl sections, wherein air is provided at an air inlet of the annular premixing channel, and wherein fuel is introduced through a tube located at the air inlet, whereby the fuel is distributed into the air flow as a spray and mixed with the air flow.