US 12,404,780 B2
Containment ring for gas turbine engine
Jocelyn Bisson, Québec (CA); Jagdeep Singh Jhinger, Québec (CA); and Guy Lefebvre, Québec (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Québec (CA)
Filed by Pratt & Whitney Canada Corp., Québec (CA)
Filed on Jan. 29, 2024, as Appl. No. 18/425,993.
Prior Publication US 2025/0243778 A1, Jul. 31, 2025
Int. Cl. F01D 21/04 (2006.01); F01D 25/24 (2006.01); F02C 7/00 (2006.01)
CPC F01D 21/045 (2013.01) [F01D 25/243 (2013.01); F02C 7/00 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A containment ring for a turbine casing assembly, comprising:
a main body portion, the main body portion having an outer periphery and an inner periphery and a forward end and an aft end each extending between the outer periphery and the inner periphery, the main body portion having a center axis and also including an outer containment zone and an inner containment zone, the inner containment zone is integrally formed with the outer containment zone in order to provide a single unitary structure and the inner containment zone being radially inward from the outer containment zone, the inner containment zone extending radially outward from the inner periphery and having a plurality of ribs, each of the plurality of ribs extending continuously from the forward end and the aft end and each of the plurality of ribs being substantially parallel to the center axis, wherein the plurality of ribs are each separated by an opening extending into the inner periphery, the opening does not extend to the outer periphery or the forward end or the aft end and each of the plurality of ribs have opposing surfaces that are anularly offset in the same direction with respect to the inner periphery of the containment ring and to a plane extending radially from the center axis.