Method for machining a blade and a blade for a turbomachine
AssigneeMTU Aero Engines AG
InventorsKrzysztof Skura, Martin Pernleitner, Christian Eichler, Lutz Friedrich
Life of this patent
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Abstract
A method for machining a blade and a blade for a turbomachine comprising a shroud which is positioned on a tip side of the blade. The shroud has an outer surface with at least one circumferential fin arranged thereon, whereby at least one section of the outer surface beside the at least one fin is processed in at least two manufacturing steps. At least one first section of the outer surface is processed to have a first shape and at least one second section of the outer surface is processed to have a second shape.
Claims4
A blade for a turbomachine having a rotation axis, comprising a shroud which is positioned on a tip side of the blade having an outer surface with at least one circumferential fin arranged thereon, comprising:
- a rib structure having a top surface;
- the top surface having a first section and a second section;
- the first section of the top surface being cylindrical in shape and extending circumferentially about the rotation axis of the turbomachine;
- at the first section, the shroud having a constant radial thickness;
- and
- the second section of the top surface being entirely linear in shape;
- at the second section, the shroud having a varying radial thickness, and
- wherein the first section extends from a first shroud edge and transitions to the second section, wherein the second section extends to a second shroud edge.
A blade for a turbomachine, comprising a shroud which is positioned on a tip side of the blade having an outer surface with at least one circumferential fin arranged thereon, comprising:
- a rib structure having a top surface;
- the top surface having a first section and a second section;
- the first section of the top surface being linear in shape and oriented at a first angle relative to a plane arranged perpendicular to a center line of the blade;
- at the first section, the shroud having a varying radial thickness;
- and
- the second section of the top surface being linear in shape and oriented at a second angle relative to the plane arranged perpendicular to the center line of the blade and with a recess circumferentially between the first section and the second section of the top surface of the rib structure;
- at the second section, the shroud having a varying radial thickness;
- the second angle being different than the first angle.
Dependencies are inferred from the claim text.