Gas turbine combustor

The present invention relates to a burner for a combustion chamber of a gas turbine with a mixing and injection device (43), wherein the mixing and injection device (43) is comprising a limiting wall (44) that defines a gas-flow channel (440) and at least two streamlined bodies (22), each extending in a first transverse direction (49) into the gas-flow channel (440). Each streamlined body (22) has two lateral surfaces that are arranged essentially parallel to the main-flow direction (14), the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body (22). Each streamlined body (22) has a cross-section perpendicular to the first transverse direction (49) that is shaped as a streamlined profile. At least one of said streamlined bodies (22) is provided with a mixing structure and with at least one fuel nozzle (15) located at its trailing edge for introducing at least one fuel essentially parallel to the main-flow direction (14) into the flow channel (440), wherein at least two of the streamlined bodies (22) have different lengths along the first transverse direction (49) such that they may be used for a can combustor.