US 12,448,708 B2
Extended inner profile for mandrel for use in forming braided CMC structures
Jonathan L. Chin, Morrisville, NC (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Feb. 15, 2024, as Appl. No. 18/442,870.
Prior Publication US 2025/0263872 A1, Aug. 21, 2025
Int. Cl. D04C 3/48 (2006.01); D04C 1/02 (2006.01); D04C 3/40 (2006.01); C04B 35/80 (2006.01)
CPC D04C 3/48 (2013.01) [D04C 1/02 (2013.01); D04C 3/40 (2013.01); C04B 35/80 (2013.01); C04B 2235/5252 (2013.01); C04B 2237/38 (2013.01); D10B 2505/02 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A method of forming a gas turbine engine component having an airfoil comprising 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 braiding machine, the mandrel extending 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 having a width in a direction between the leading edge and the trailing edge that transitions into the inner tang beyond an outer location that will serve as a base for the braided material, and a location to mount the inner tang into the braiding machine, and the mandrel body transitions smoothly into the inner tang, with the width of the inner tang between the leading edge and the trailing edge and the width of the mandrel body radially outwardly of the outer location being equal; and
braiding ceramic matrix composite (“CMCs”) yarn about a portion of the mandrel which serves as the base for the braided yarn to form a shear tube.