the sealing grooves 41 and additionally the inserting of the sealing segments 35 35 u2032 into the flange 28 which is provided for them can prove to be exceptionally awkward and it is directly dependent upon the geometric design of the sealing segment foot 44 fig5 7 and also upon the design of the outer shell flange 28 the cross sectional profiles and the geometry of the two parts are evident for example from fig9 the feet 44 of the sealing segments 35 35 u2032 must be designed so that these fit accurately into the respective flange geometry of the flange 28 and during operation despite the thermal deformation of the shells 23 33 and of the flange 28 are furthermore u201c able to support u201d the flange 28 and consequently the combustor and allow a mass flow of cooling air from fig8 13 which refer to different operating states of the gas turbine and are correspondingly characterized by different axial and radial distances b c and a between combustor 15 25 and turbine vane carrier 47 b c or sealing segment 35 35 u2032 and turbine vane carrier 47 a the associated positions of the sealing segments 35 35 u2032 are apparent in the operating states according to fig9 and 10 the axial distance b between flange 28 and turbine vane carrier 47.