Extended inner profile for mandrel for use in forming braided cmc structures

Abstract

A method of forming a gas turbine engine component having an airfoil includes the steps of placing a mandrel into a braiding machine, with the mandrel having a mandrel body, a radially outer tang and a radially inner tang for holding the mandrel relative to the knitting machine. The mandrel extends between a leading edge and a trailing edge and the radially outer tang with a width in a direction between the leading edge and the trailing edge that is smaller than a distance between the leading edge and trailing edge of the mandrel such that there is a ledge leading into the outer tang. The mandrel body has a width in a direction between the leading edge and the trailing edge that transitions into the inner tang beyond a location that will serve as a base for the braided material, and the mandrel body transitions smoothly into the inner tang. Ceramic matrix composite (“CMCs”) yarn is braided about a portion of the mandrel which serves as the base for the braided yarn to form a shear tube. A mandrel is also disclosed.

Dependencies are inferred from the claim text.