<p>The combustion chamber (4) for a gas turbine has its wall (24) on the inner side provided with a lining formed from a number of heat shield elements (26). Each heat shield element forms with the combustion chamber wall an inner chamber (27) chargeable with a cooling medium (K) and in which is fitted a flow element (49) for the directed adjustment of a cooling medium flow. By the flow element is formed a cooling medium flow passage in which the flow speed is increased in relation to the flow speed upstream of the flow element. An independent claim is included for a gas turbine equipped with the aforesaid combustion chamber.</p>
