Abstract: A continuous-flow machine (1), in particular a turbine or a compressor, includes at least one stator blade section (2) which has a plurality of stator blades (3) which project into a gas path (10) of a working gas, and at least one adjacent section (6), which has a plurality of adjacent elements (7), which bound the working gas path (10) at the side. A gap (11), through which a cooling gas can be introduced into the working gas path (10), is formed between the stator blades (3) of the stator blade section (2) and the adjacent elements (7) of the adjacent section (6). In order to improve the efficiency of the continuous-flow machine (1), lateral seals (14) are formed in the gap (11) and prevent or at least impede pressure equalization and/or a gas flow in the gap (11) in the lateral direction (5).

Abstract: A continuous-flow machine (1), in particular a turbine or a compressor, includes at least one stator blade section (2) which has a plurality of stator blades (3) which project into a gas path (10) of a working gas, and at least one adjacent section (6), which has a plurality of adjacent elements (7), which bound the working gas path (10) at the side. A gap (11), through which a cooling gas can be introduced into the working gas path (10), is formed between the stator blades (3) of the stator blade section (2) and the adjacent elements (7) of the adjacent section (6). In order to improve the efficiency of the continuous-flow machine (1), lateral seals (14) are formed in the gap (11) and prevent or at least impede pressure equalization and/or a gas flow in the gap (11) in the lateral direction (5).

Abstract: A turbine casing for an axial-throughflow gas turbine surrounds at least one hot-gas space between a compressor stage and a turbine stage and has an outer shell as an external boundary and also an inner shell which is provided separately from the outer shell and which separates the hot-gas space from the outer shell via an annular space. The inner shell is connected to the outer shell via two axial interfaces, in such a way that the annular space is sealed off relative to the hot-gas space. The turbine casing withstands higher compressor final pressures and temperatures and can be produced cost-effectively.

Abstract: The present invention relates to a turbine casing for an axial-throughflow gas turbine. The turbine casing surrounds at least one hot-gas space (5) between a compressor stage (7) and a turbine stage (6) and has an outer shell (1) as an external boundary and also an inner component (2) which is provided separately from the outer shell and which separates the hot-gas space from the outer shell via an annular space (3). The inner component (2) is connected to the outer shell (1) via two axial interfaces (4), in such a way that the annular space (3) is sealed off relative to the hot-gas space (5).