Cooling scheme for an increased gas turbine efficiency

A burner for a combustion chamber of a turbine, comprising:

• an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device includes:
• at least one body which is arranged in the burner, the at least one body being a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner, wherein the body has an outer wall including two lateral surfaces substantially parallel to the main flow direction joined at their upstream side by a leading edge portion of the body and joined at their downstream side forming a trailing edge defining the streamlined cross-sectional profile, wherein within the outer wall, there is provided a longitudinal inner carrier air plenum with a wall distanced from the outer wall leaving an interspace therebetween for the introduction of carrier air into the injection device, wherein the carrier air plenum is provided with holes such that carrier air exiting through these holes impinges on an inner side of the leading edge portion of the body of the outer wall;
• and
• at least two nozzles for introducing the at least one fuel into the burner, the at least two nozzles being distributed along the trailing edge of the streamlined body.