US 12,345,169 B2
Thermally compliant forward outer-diameter ring for a gas turbine engine
Alex J. Simpson, Tolland, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Aug. 9, 2023, as Appl. No. 18/447,167.
Prior Publication US 2025/0052173 A1, Feb. 13, 2025
Int. Cl. F01D 25/14 (2006.01); F01D 9/04 (2006.01); F01D 11/00 (2006.01); F01D 25/24 (2006.01)
CPC F01D 25/14 (2013.01) [F01D 11/003 (2013.01); F01D 11/005 (2013.01); F01D 25/24 (2013.01); F01D 25/246 (2013.01); F01D 9/04 (2013.01); F05D 2240/14 (2013.01); F05D 2260/202 (2013.01)] 19 Claims
OG exemplary drawing
 
19. A cooled turbine exhaust case assembly for a gas turbine engine, the assembly comprising:
a forward outer diameter ring, the forward outer diameter ring comprising:
a flowpath ring extending circumferentially about a central axis and extending axially from a first end to a second end relative to the central axis, wherein the second end is axially aft of the first end;
a hoop stiffener connected to the second end of the flowpath ring and extending circumferentially around the second end of the flowpath ring, and wherein the hoop stiffener comprises:
a first stiffener end connected to the second end of the flowpath ring;
a second stiffener end axially aft of the first stiffener end; and
tabs formed in the second stiffener end, and wherein the tabs are circumferentially spaced apart from one another;
case segments connected to the second stiffener end by the tabs, and wherein the case segments are circumferentially spaced about the central axis from one another;
a slot between each pair of the case segments; and
a seal extending axially along the slot, wherein the seal is connected to two of the case segments;
a turbine case located radially outward of the forward outer diameter ring;
a turbine exhaust case axially aft the turbine case and connected to the turbine case via a forward outer turbine exhaust case;
a plenum defined by the forward outer diameter ring, the turbine case, the turbine exhaust case, and the forward outer turbine exhaust case;
an inlet opening in the turbine case for introducing cooling air to the plenum; and
one or more film cooling openings in a fore region of the forward outer diameter ring configured to allow cooling air to exit the plenum to a hot gas path of the gas turbine engine to provide film cooling to the forward outer diameter ring.