Abstract: A seal (1) includes a first component (7) and second component (9), the first component including a first material having a high thermal and oxidation and wear resistance, and the second component (9) including a second material that is different from the first material and has a high spring load maintenance. The seal (1) is applied to a combustion chamber for a gas turbine, where the first component (7) extends between the casing wall of the combustion chamber and adjacent liner segments (4). The spring load of the second component (9) provides a seal also in the case of vibrations in a combustion chamber. The lifetime of the seal (1) is increased due to the individual materials, which are optimally chosen for the functions of high thermal and wear resistance and spring load maintenance respectively. The seal is further applied to the sealing between adjacent stationary blade platforms in gas turbines.

Abstract: The present invention relates to a sealing body (1) for sealing an outer component (2) with respect to an inner component (3), in particular for a combustion chamber of a gas turbine. The outer component (2) has a passage opening (4), through which the inner component (3) projects out of the outer component (2). In the installed state, the sealing body (1) is arranged in the region of the passage opening (4), surrounds the inner component (3) in a circumferentially continuous manner, bears in a circumferentially continuous manner, by means of an inner sealing zone (7), against an outer sealing surface (6) of the inner component (3) and bears in a circumferentially continuous manner, by means of an outer sealing zone (8), against an inner sealing surface (5) of the outer component (2). The sealing body (1) is produced by deformation from at least one metal sheet that is in strip form and is circumferentially continuous.