Gas turbine moving blade
AssigneeMTU Aero Engines AG
InventorsFrank Stiehler, Lars Schellhorn
Life of this patent
Estimating the term…
Abstract
A moving blade for a turbine or compressor stage of a gas turbine is provided, including a vane (10) and a radially outer shroud (20), for at least one contour point (PK) of an outer contour of a profile cross section (P) of the vane at a radial outer gas channel boundary, the wall thickness of the shroud at at least one edge point (PR) of the shroud, whose connecting line (V), including the contour point with a normal (N), which is perpendicular to the outer contour of the profile cross section in the contour point, encloses an angle (σ), which is no more than 5°, is less than a wall thickness of the shroud at the contour point, the wall thickness of the shroud decreasing strictly monotonously along the connecting line.
Claims16
A moving blade for a turbine or compressor stage of a gas turbine, comprising:
- a blade;
- and
- a radially outer shroud,
- for at least one contour point (PK) of an outer contour of a profile cross section of the blade at a radially outer gas channel boundary, a wall thickness of the shroud at at least one edge point (PR) of the shroud is less than a wall thickness of the shroud at the at least one contour point, wherein a connecting line (V), which connects the at least one contour point with the at least one edge point, intersects the at least one contour point and encloses an angle (σ) of no more than 5° with a normal (N) perpendicular to the outer contour of the profile cross section at the at least one contour point, and wherein the wall thickness of the shroud decreases strictly monotonically along the connecting line, wherein the at least one contour point (PK) is located at a junction between the blade and the shroud;
- and
- the shroud having two opposing end faces in a circumferential direction, at least one of the end faces of the shroud in the circumferential direction having a cam having an uppermost cam point (O) in the circumferential direction and a groove having a lowermost groove point (U) in the circumferential direction forming an end face surface, wherein the wall thickness of the shroud at at least one edge point between the cam and the groove, the wall thickness of the shroud at at least one edge point on a side of the cam facing away from the groove and the wall thickness of the shroud at at least one edge point on a side of the groove facing away from the cam is smaller than the wall thickness of the shroud at the uppermost cam point and/or the lowermost groove point.
Dependencies are inferred from the claim text.