US 11,808,154 B2
CMC component flow discourager flanges
San Quach, Southington, CT (US); Bryan P. Dube, Columbia, CT (US); Erik R. Granstand, West Hartford, CT (US); Michael G. McCaffrey, Windsor, CT (US); and Stephen G. Pixton, South Windsor, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Sep. 26, 2022, as Appl. No. 17/952,693.
Application 17/952,693 is a continuation of application No. 17/221,036, filed on Apr. 2, 2021, granted, now 11,454,129.
Prior Publication US 2023/0036836 A1, Feb. 2, 2023
Int. Cl. F01D 11/00 (2006.01); F01D 5/14 (2006.01); F01D 9/04 (2006.01)
CPC F01D 11/005 (2013.01) [F01D 5/147 (2013.01); F01D 9/042 (2013.01); F05D 2240/12 (2013.01); F05D 2300/6033 (2013.01)] 19 Claims
OG exemplary drawing
 
1. An airfoil assembly for a gas turbine engine, comprising:
an outer portion including an airfoil section extending in a radial direction from a first platform section, the airfoil section including an internal cavity, and the outer portion comprising a ceramic material;
a support structure having a radial portion extending in the radial direction from an axial portion, and the radial portion received in the internal cavity such that a gap is established between the outer portion and the axial portion of the support structure, and the gap extending from the internal cavity; and
a flange extending in the radial direction from the first platform section of the outer portion such that the flange bounds the gap at a distance from the internal cavity;
wherein the gap includes an axial segment extending in an axial direction between the radial portion of the support structure and the first platform section, the flange is a raised protrusion extending outwardly from the first platform section at an intermediate position along the axial segment of the gap to establish a tortuous path, and the tortuous path has a lesser height along the raised protrusion than on either side of the raised protrusion.