| 摘要 |
<p>A fluid flow engine (1), in particular a turbo engine, has at least one guide vane row (5) with a plurality of guide vanes (6) and at least one rotor blade row (7) with a plurality of rotor blades (8). One guide vane row (5) and one rotor blade row (7) that follows the former directly downstream with respect to a working gas flow (11), together form a stage (10) of the fluid flow engine (1). To reduce the load on the rotor blades (8), the guide vanes (6) and the rotor blades (8) are coordinated at least in one stage (10) so that in a reference relative position between the respective guide vane (6) and the respective rotor blade (8), there is an axial distance (B) and a circumferential distance (C) between the outgoing flow edge (16) of the respective guide vane (6) and the oncoming flow edge (17) of the respective rotor blade (8) that is measured in the axial direction and is varied along a height (H) of a gas path (12) running axially between the blade rows (5, 7) of this stage (10), said height being measured radially.</p> |
