Turbine engines with ceramic vanes and methods for manufacturing the same

摘要

A vane assembly includes first and second annular metal rings (31,48) configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion (38). The assembly further includes a ceramic matrix composite vane (30) configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member (33) disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.