US 12,442,311 B1
Turbine case structure for an aircraft propulsion system engine
Philippe Savard, Terrebonne (CA); Guy Lefebvre, St-Bruno (CA); Remy Synnott, St-Jean-sur-Richelieu (CA); and Ruoxin Huang, Montreal (CA)
Assigned to Pratt & Whitney Canada Corp., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Dec. 20, 2024, as Appl. No. 18/990,597.
Int. Cl. F01D 11/00 (2006.01); F01D 25/24 (2006.01)
CPC F01D 11/003 (2013.01) [F01D 25/24 (2013.01); F05D 2220/323 (2013.01); F05D 2240/57 (2013.01); F05D 2250/711 (2013.01); F05D 2250/712 (2013.01); F05D 2260/96 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine for an aircraft, the gas turbine engine comprising:
a turbine section extending along a rotational axis of the gas turbine engine;
a turbine case including a cantilevered inner wall disposed downstream of the turbine section, the cantilevered inner wall extending circumferentially about the rotational axis, the cantilevered inner wall extending between and to an upstream axial end and a downstream axial end, the upstream axial end disposed at and downstream of the turbine section, the cantilevered inner wall forming a first sealing surface and a second sealing surface axially spaced from the first sealing surface;
an inner case extending circumferentially about the rotational axis, the inner case disposed radially inward of the upstream axial end; and
a damping seal baffle extending circumferentially about the rotational axis, the damping seal baffle mounted to the inner case, the damping seal baffle disposed in contact with one or both of the first sealing surface or the second sealing surface and configured to move relative to the first sealing surface and the second sealing surface.