Abstract: In a jet engine with compressor air circulation provided for stabilizing the flow conditions, the compressed hot compressor air tapped from the flow path of the compressor (1) is first cooled in the bypass duct (3) and then resupplied to the upstream compressor via line (12). This reduces the thermal load of the blades and improves efficiency.

Abstract: The course of the leading edges of turbomachine components, such as rotor blades and stator vanes is defined mathematically exactly and repeatedly as well as aerodynamically advantageously by the respective axial coordinate in the direction of the machine axis in relation to the blade height in percent, extending from the blade tip as per equation (1): axial ? ? coordinate ? [ % ? ? blade ? ? height ] = 1 5 ? ? extension ? [ % ? ? blade ? ? height ] ? ? tan ? ? sweep tip ( 1 - ? - 5 ? ( 100 ? % - blade ? ? height ? [ % ] ) extention ? [ % ? ? blade ? ? height ] ) and extending from the blade hub as per equation (2): axial ? ? coordinate ? [ % ? ? blade ? ? height ] = 1 5 ? ? extension ? [ % ? ? blade ? ? height ] ? ? tan ? ? sweep hub ( 1 - ? - 5 ? ? blade ? ? height ? [ % ] extention ? [ % ? ? blade ? ? height ] ) where sweept