Patent ID: 8561409

Claim:
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, wherein each quarl section includes a configuration of a conical shell of a truncated cone, and wherein the quart sections are distributed consecutively one after the other in a downstream direction of the burner, and wherein a part of the second quarl section surrounds a part of the first quarl section, and wherein the main flame is formed as a conical rotational symmetric shear layer around a recirculation zone, 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, wherein the stagnation point is located within the quad and at an exit of the pilot combustor, 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.