Patent ID: 8245513

Claim:
A combustion chamber for a gas turbine, comprising: a combustion chamber wall; a liner formed from a plurality of heat shields on an inside of the combustion chamber wall; an inner space formed between the heat shield elements and the combustion chamber wall and exposed to a cooling medium, wherein said liner is made from a leak-free material such that the inner space is configured to direct the cooling medium along a cold-side of the liner and within the inner space, and to a burner for combustion in the burner upon exiting the inner space; and a flow element arranged in the inner space for selective adjustment of a cooling medium stream, the flow element arranged on the combustion chamber wall, wherein a longer side of the flow element is adjacent and in contact with the combustion chamber wall such that the longer side is defined by a plane that is substantially parallel to and encompasses the combustion chamber wall; wherein each respective heat shield has a surface region with a surface contour curved along a longitudinal axis in a flow direction of the cooling medium and a transverse axis perpendicular to the longitudinal axis; and wherein the flow element has a wedge-shaped profile such that a flow cross-sectional area for the cooling medium within the inner space between an outer surface of the flow element and the heat shield elements is configured to continually decrease for at least a portion of the profile.