Abstract: A multi-vane structure for incorporation in an aircraft gas turbine engine has vanes of complex geometry made of braided fibers which are continuous about the cavities defined by the vanes. These complex geometry parts are prepared by providing a plurality of removable mandrels, stacking the mandrels along a horizontal axis in a cavity end to cavity end configuration, braiding about the mandrels, cutting the mandrels adjacent the cavity end faces, side stacking the mandrels so the faces are placed in a parallel orientation and molding. Utilizing braided fibers instead of hand lay-up woven fibers eliminates seams and produces cavities having continuous fibers about the periphery thereof which substantially increases the strength and dimensional reproducibly of the part.

Abstract: A multi-vane structure for incorporation in an aircraft gas turbine engine has vanes of complex geometry made of braided fibers which are continuous about the cavities defined by the vanes. These complex geometry parts are prepared by providing a plurality of removable mandrels, stacking the mandrels along a horizontal axis in a cavity end to cavity end configuration, braiding about the mandrels, cutting the mandrels adjacent the cavity end faces, side stacking the mandrels so the faces are placed in a parallel orientation and molding. Utilizing braided fibers instead of hand lay-up woven fibers eliminates seams and produces cavities having continuous fibers about the periphery thereof which substantially increases the strength and dimensional reproducibly of the part.

Abstract: A multi-vane structure for incorporation in an aircraft gas turbine engine has vanes of complex geometry made of braided fibers which are continuous about the cavities defined by the vanes. These complex geometry parts are prepared by providing a plurality of removable mandrels, stacking the mandrels along a horizontal axis in a cavity end to cavity end configuration, braiding about the mandrels, cutting the mandrels adjacent the cavity end faces, side stacking the mandrels so the faces are placed in a parallel orientation and molding. Utilizing braided fibers instead of hand lay-up woven fibers eliminates seams and produces cavities having continuous fibers about the periphery thereof which substantially increases the strength and dimensional reproducibly of the part.

Abstract: A method for fabricating and stabilizing three dimensional composite fabric preforms. The method comprises disposing a plurality of fabric plies between upper and lower templates that have substantially the desired preform shape and openings in at least two planes. The fabric plies are joined through the template openings and the templates are removed from the preform. These stabilized preforms maintain tighter tolerances.