The flow structure for the compressor of especially a gas turbine has at least one toroidal chamber (18) installed concentrically to an axis (17) of the compressor in the region of the free blade ends of a blade ring (15,16). An opening (30) is located in ...

The part (30) has a base plate that forms, in common with an associated control plate (38,44,52), a flow channel (36) for a coolant that extends in cross-section essentially over the entire width in relation to the axial direction of the guide rings. The c...

The thermically-loaded wall (2), acted on by a hot gas (17), has 2 directly adjacent wall segments (33,35) separated by a gap (55) which is sealed by the thermic expansion of a flexure element (45) attached to one wall segment (33), cooperating with a pres...