Turbine ring assembly, turbine, and turbine engine
By employing ceramic matrix composite ring sections and ring support structures in the turbine ring assembly, mechanical stress and leakage issues were resolved, improving the mechanical strength and sealing performance of the turbine ring and enhancing the efficiency of the turbine engine.
CN122122372APending Publication Date: 2026-05-29SAFRAN AIRCRAFT ENGINES SAS
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2024-10-23
- Publication Date
- 2026-05-29
AI Technical Summary
Technical Problem
Existing turbine ring assemblies using ceramic matrix composites suffer from insufficient mechanical stress strength and leakage problems caused by dimensional deviations, affecting turbine efficiency and performance.
Method used
The ring section, made of multiple ceramic matrix composites, combined with the ring support structure, forms a sealed structure by machining adjustment parts on the downstream radial clamp and inserting folded metal sheets, thereby reducing shear stress and leakage at the joint between sections.
Benefits of technology
Without affecting the chamber pressure, the load on the inter-section joint is reduced, the mechanical strength and sealing effect of the turbine ring are improved, and the efficiency and performance of the turbine engine are enhanced.
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Smart Images
Figure CN122122372A_ABST
Abstract
The invention relates to a turbine ring assembly equipped with a segmented ceramic matrix composite turbine ring and a ring support structure (6); each ring segment (10) comprises a base (12) from which axially spaced upstream and downstream hook lugs (16, 14) extend radially outwards, the ring support structure (6) comprises an upstream radial clamp (62) and a downstream radial clamp (64), the hook lugs (14, 16) being clamped between the two clamps. In a corresponding position of each intersegment joint (100) between two adjacent ring segments (10) in a circumferential direction (D C ), the downstream radial clamp (64) comprises an adjustment (70) machined from an upstream face (642) thereof to an inner thickness thereof, the adjustment extending radially from a radially inner end (643) of the downstream radial clamp (64); the thickness of the downstream radial clamp (64) is measured in an axial direction (D A ) and the adjustment of the downstream radial clamp (64) and its opposite intersegment joint (100) are kept at a distance in the axial direction.
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