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CERAMIC MATRIX COMPOSITE AIRFOIL SEGMENT FOR GAS TURBINE ENGINE, CERAMIC MATRIX COMPOSITE STRUCTURE, AND METHOD FOR ASSEMBLING THE CERAMIC MATRIX COMPOSITE STRUCTURE
CERAMIC MATRIX COMPOSITE AIRFOIL SEGMENT FOR GAS TURBINE ENGINE, CERAMIC MATRIX COMPOSITE STRUCTURE, AND METHOD FOR ASSEMBLING THE CERAMIC MATRIX COMPOSITE STRUCTURE
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机译:燃气轮机的陶瓷基复合材料翼型段,陶瓷基复合材料结构以及陶瓷基复合材料的组装方法
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摘要
PROBLEM TO BE SOLVED: To provide a geometry that provides continuity to fibers of a ceramic matrix composite material, and to maximize the strength per weight.SOLUTION: In each structure of the air foil segments 82, the box-shape ceramic-matrix-composite-fiber geometry 98 is used. Each of the ceramic matrix composite airfoil segments 82 defines a rectilinear pressure side bond line 100P and a rectilinear suction side bond line 100S on a circumferential segment of the ceramic matrix composite airfoil segments 82 to maintain aerodynamic performance and provide a strong bonding part. The rectilinear pressure side bond line 100P and the rectilinear suction side bond line 100S approximately align with a front edge 84L, a rear edge 84T, and respective platforms 90, 92.
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