| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide an airfoil, made of a ceramic composite material, for a gas turbine engine. <P>SOLUTION: Each CMC airfoil 66 made of a ceramic composite material has an airfoil portion 68 defined between a leading edge 70 and a trailing edge 72, and fillets 74, 76 forming a transition to inner and outer platform segments 78, 80 on each side of the airfoil portion 68. A CMC ply 88 used for manufacturing the CMC airfoil 66 forms an I-shaped fiber structure. The pressure side 82, the suction side 84, and the platform segments 78, 80 are continuously and integrally formed. A first portion of the CMC ply 88 defines the airfoil portion 68, the pressure side 82, and the suction side 84. Transverse portions of the CMC ply 88 defines the platform segments 78, 80. The platform section 78, 80 are chevron-shaped to provide a complementary geometry with respect to each adjacent platform section. <P>COPYRIGHT: (C)2013,JPO&INPIT |
