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US 2007/0177979 A1Published application
Vane comprising a transition zone
AssigneeMTU Aero Engines AG
InventorMartin Hoeger
Life of this patent
Estimating the term…
Abstract
A vane of a guide vane or impeller blade of a turbo machine, particularly a gas turbine. The profile of the vane includes at least one thickening that is advantageous for flow purposes in a radially inward final region and/or a radially outward final region of the vane. The thickening is cut in the area of a forward edge of the vane so as to form a mirror surface or a basal plane.
Claims22
1-14. (canceled)
A blade of a guide vane or of a rotor blade of a fluid flow machine comprising:
- at least one thickened portion of the blade profile beneficial from a standpoint of fluid mechanics on a radially inside end region and/or on a radially outside end region of the blade,
- the thickened portion having a cut in an area of a leading edge of the blade forming a mirror surface or a basal plane.
A fluid flow machine comprising:
- at least one guide vane ring having a plurality of guide vanes and at least one rotor blade ring having a plurality of rotor blades, the guide vanes and the rotor blades each having blades that extend in the radial direction of a flow channel, and, at a radially inside end region and/or at a radially outside end region of the blade, the blades exhibiting a thickened portion of the blade profile that is beneficial from a standpoint of fluid mechanics,
- the thickened portion having a cut in an area of a leading edge of the blade forming a mirror surface or a basal plane.
Dependencies are inferred from the claim text.