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US 2026/0235034 A1Published application
Turbine or compressor stage assembly
OwnerAndreas HARTUNG, Markus SCHLEMMERinventors
Life of this patent
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Abstract
An assembly including a first component and a second component configured for arrangement in a same turbine or compressor stage of an aircraft engine. The first component has a first surface and the second component has a second surface opposite the first surface. The first surface has a first contact area configured for contacting the second surface. The second surface has a first contact contour opposite the first contact area configured for contacting the first contact area, the first contact contour area having a recess or a convex edge or a convex tip.
Claims13
An assembly comprising:
- a first component and a second component configured for arrangement in a same turbine or compressor stage of an aircraft engine,
- wherein the first component has a first surface and the second component has a second surface opposite the first surface,
- wherein the first surface has a first contact area configured for contacting the second surface, and
- wherein the second surface has a first contact contour opposite the first contact area configured for contacting the first contact area, the first contact contour having a recess or a convex edge or a convex tip.
1 more element
Dependencies are inferred from the claim text.