CMC airfoil and method of forming same

By alternately inserting fiber belts and setting cooling holes, the problems of large trailing edge thickness and rotation radius of CMC turbine blades are solved, aerodynamic performance and strength performance are improved, and cooling efficiency is enhanced.

CN119686812AActive Publication Date: 2025-03-25AECC COMML AIRCRAFT ENGINE CO LTD
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Patent Information

Application Number
CN202311235539.0
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2023-09-22
Publication Date
2025-03-25
Estimated Expiration
2043-09-22

AI Technical Summary

Technical Problem

The existing CMC turbine blades have large thickness and slewing radius at the tail edge, resulting in poor aerodynamic performance and weak local strength.

Method used

By using the method of alternating interspersing and laying, the fiber continuity and strength properties in the tail edge region are formed by alternate arrangement of the first and second fiber strips, the tail edge thickness and rotation radius are reduced, and cooling holes are provided in the inner and outer layers of the fiber frame to improve cooling efficiency.

Benefits of technology

It significantly improves the aerodynamic and strength properties of the tail edge of the CMC airfoil, reduces the tail edge thickness and slewing radius, and improves the cooling efficiency to prevent overtemperature problems.

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Abstract

A CMC airfoil combines trailing edge aerodynamic performance and strength performance. In the blade height direction of the CMC airfoil, first sections formed by laying multiple layers of first fiber belts and second sections formed by laying multiple layers of second fiber belts are alternately arranged, so that the first sections and the second sections are alternately arranged in the trailing edge area of the CMC airfoil. Projections of the fibers continuously extending along the airfoil pressure surface side and the airfoil suction surface side respectively in a projection plane perpendicular to the blade height direction are mutually staggered and overlapped. The forming method of the CMC airfoil is used for manufacturing the CMC airfoil.
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