US 12,234,744 B2
Flow guides for internal cooling of a CMC airfoil
Howard J. Liles, Newington, CT (US); and Tyler G. Vincent, Portland, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Jun. 17, 2022, as Appl. No. 17/843,518.
Prior Publication US 2023/0407753 A1, Dec. 21, 2023
Int. Cl. F01D 5/18 (2006.01); F01D 5/28 (2006.01); F01D 9/06 (2006.01); F23R 3/00 (2006.01)
CPC F01D 5/189 (2013.01) [F01D 5/282 (2013.01); F01D 5/284 (2013.01); F01D 9/065 (2013.01); F05D 2240/126 (2013.01); F05D 2260/201 (2013.01); F05D 2260/22141 (2013.01); F05D 2260/232 (2013.01); F05D 2300/6033 (2013.01); F23R 3/007 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A component for a gas turbine engine comprising:
a ceramic matrix composite (“CMC”) component having a radially outer end and a radially inner end, said CMC component having an internal cavity;
a spar received within the internal cavity, and spaced from an inner surface of the CMC component defining a chamber with the inner surface;
flow guides formed on one of an outer surface of said spar and said inner surface of said CMC component, said flow guides directing airflow towards a portion of the inner surface;
an air inlet chamber being formed at one radial end of said spar and an air outlet chamber formed at an opposed radial end of said spar, and said air inlet chamber being defined such that air will flow into the air inlet chamber, along the outer side of the spar, and inwardly of the inner surface of the CMC component; and
a portion of the flow guides on the one of the outer surface and the inner surface contacts the other of the outer surface and the inner surface.