Contouring a blade/vane cascade stage
AssigneeMTU Aero Engines AG
InventorsMarkus Brettschneider, Inga Mahle
Life of this patent
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Abstract
Disclosed is a blade/vane cascade segment of a blade/vane cascade of a turbomachine, which comprises at least two blade/vane elements defining an axial cascade width, and a stage with a stage surface, as well as a stage edge on the inflow side. The stage surface has an elevation extending up to the pressure side of a first blade/vane element and a depression extending up to the suction side of the other blade/vane. At least one highest point of the elevation and at least one lowest point of the depression each lie at least 30% and at most 60% of the axial cascade width downstream of the inflow edges of the blade/vane elements. In this case, the elevation and the depression each come close to the stage edge on the inflow side.
Claims13
A blade/vane cascade segment of a blade/vane cascade of a turbomachine, comprising:
- at least two blade/vane elements, each defining an axial cascade width by their inflow and outflow edges;
- a stage having a stage surface and a stage edge, the stage edge being the leading edge on the inflow side;
- wherein the stage surface has an elevation extending up to the pressure side of a first blade/vane element and a depression extending up to the suction side of the other blade/vane element;
- wherein at least one highest point of the elevation and at least one lowest point of the depression each lie at least 30% and at most 60% of the axial cascade width downstream of the inflow edges of the blade/vane elements;
- and
- wherein the elevation and the depression each extend directly from the stage edge on the inflow side.
Dependencies are inferred from the claim text.