Turbine or compressor stage assembly

The assembly addresses turbine and compressor stage vibrations in turbomachines by using components with optimized contact surfaces and contours to transfer vibrational energy into other modes, thereby reducing undesirable vibrations and improving stability.

EP4764155A1Pending Publication Date: 2026-06-24MTU AERO ENGINES GMBH
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Patent Information

Application Number
EP2025223428
Authority / Receiving Office
EP · EP
Patent Type
Applications
Current Assignee / Owner
Priority Date
2024-12-17
Filing Date
2025-12-15
Publication Date
2026-06-24

AI Technical Summary

Technical Problem

Turbine and compressor stages in turbomachines experience undesirable vibrations due to aerodynamic, mechanical, and thermal loads, which existing technologies have not effectively mitigated.

Method used

An assembly comprising two components with specific contact surfaces and contours that reduce vibrations by transferring vibrational energy into other modes, utilizing contact areas and contours that are free of protrusions and depressions, or form point, line, or surface contact points to manage vibration propagation.

Benefits of technology

The assembly effectively reduces vibrations by transferring vibrational energy into other modes, particularly reducing pronounced vibrations without such contact contours, enhancing stability and performance.

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Abstract

The present invention relates to an assembly comprising a first component (110; 210; 310) and a second component (120; 220; 320; 420) for arrangement in the same turbine or compressor stage of a turbomachine, in particular an aircraft engine, wherein the first component has a first surface (111) and the second component has a second surface (121; 221; 321) opposite the first surface, wherein the first surface has a first contact area (112) for contacting the second surface and the second surface has a first contact contour (122; 222; 322) opposite this first contact area for contacting this first contact area, which has a recess (227; 327; 427; 428) or a convex edge (123; 223; 323) or a convex tip (124). The invention also relates to an assembly arrangement, a turbine and compressor stage and a turbomachine.
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Citation Information

Patent Citations

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    EP1970535A1

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    EP2888450B1

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    EP3382144A1

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    JP1979125307A