Burner for a gas turbine engine

A burner for a gas turbine engine, comprising:

• a radial swirler to create a swirling fuel/air mix, the radial swirler, comprising
• a plurality of vanes arranged in a circle,
• a plurality of radially inwardly extending flow slots defined between adjacent vanes in the circle;
• a combustion chamber in which combustion of the swirling fuel/air mix occurs;
• and
• a pre-chamber located between the radial swirler and the combustion chamber,
• wherein each flow slot includes a radially outer inlet end, a radially inner outlet end, first and second generally radially inwardly extending sides provided by adjacent vanes, a base and a top,
• wherein air travels along the plurality of flow slots from the inlet ends to the outlet ends and combines with gas fuel and creates the swirling fuel/air mix adjacent to the outlet ends,
• wherein each flow slot comprises a first gas fuel injection hole in the base and a second gas fuel injection hole in the first side,
• wherein an amount of gas fuel injected via the first and second gas fuel injection holes are independently variable,
• wherein a circular pilot face is located within the circle of the plurality of vanes,
• wherein a plurality of pilot gas fuel injection holes are spaced around a circumference of the circular pilot face,
• wherein the first gas fuel injection holes are supplied with gas fuel from a first gas fuel supply gallery,
• wherein the second gas fuel injection holes are supplied with gas fuel from a second gas fuel supply gallery independent of the first gas fuel supply gallery,
• wherein the burner further comprises an annular shaped gas fuel supply manifold which comprises the first and second gas fuel supply galleries,
• wherein the first gas fuel supply gallery supplies gas fuel to the first gas fuel injection holes by way of first passages within the gas fuel supply manifold that communicates with the first gas fuel injection holes, and
• wherein the second gas fuel supply gallery supplies gas fuel to the second gas fuel injection holes by way of second passages within the gas fuel supply manifold that communicate with the second gas fuel injection holes via third passages within the vanes of the radial swirler, the second passages being separate from the first passages.