US 12,241,374 B2
Ceramic matrix composite endwall sealing around vane airfoil of gas turbine engine
David J. Thomas, Indianapolis, IN (US); and Thomas Nixon, Indianapolis, IN (US)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on May 10, 2023, as Appl. No. 18/195,700.
Prior Publication US 2024/0376831 A1, Nov. 14, 2024
Int. Cl. F01D 11/00 (2006.01); F01D 9/04 (2006.01); F01D 25/14 (2006.01)
CPC F01D 11/003 (2013.01) [F01D 9/041 (2013.01); F01D 25/145 (2013.01); F05D 2240/15 (2013.01); F05D 2240/56 (2013.01); F05D 2300/6033 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A turbine vane assembly adapted for use in a gas turbine engine, the assembly comprising:
a flow path ring made of ceramic matrix composite materials that extends at least part way around a central axis and that is formed to include an airfoil aperture extending radially through the flow path ring,
an airfoil heat shield made of ceramic matrix composite materials that extends through the airfoil aperture of the flow path ring, the airfoil heat shield mounted to allow for movement through the airfoil aperture to accommodate thermal growth of components associated with the turbine vane assembly during use of the turbine vane assembly in the gas turbine engine, and
a seal configured to resist passage of gases through a gap formed between the flow path ring and the airfoil heat shield along an interface at the airfoil aperture, the seal including a plurality of ceramic bristles that extend from the flow path ring toward the airfoil heat shield to engage an outer surface of the airfoil heat shield thereby establishing a brush seal element,
wherein the flow path ring is shaped to include a radially-outwardly facing surface, a radially-inwardly facing surface opposite the radially-outwardly facing surface that defines an outer boundary of a primary gas path, an aperture surface that extends from the radially-inwardly facing surface to define the airfoil aperture, and a chamfer surface that extends between the radially-outwardly facing surface and the aperture surface and cooperates with the outer surface of the airfoil heat shield to define a groove, and wherein the seal further includes a compressible rope located in the groove between the flow path ring and the airfoil heat shield.