US 12,473,840 B2
Containment ring for gas turbine engine
Nathan Tomes, Hamilton (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on May 10, 2024, as Appl. No. 18/661,372.
Prior Publication US 2025/0347230 A1, Nov. 13, 2025
Int. Cl. F01D 21/04 (2006.01); F01D 5/28 (2006.01); F01D 25/24 (2006.01)
CPC F01D 21/045 (2013.01) [F01D 5/282 (2013.01); F01D 25/24 (2013.01); F01D 25/243 (2013.01); F05D 2240/14 (2013.01); F05D 2250/283 (2013.01); F05D 2300/603 (2013.01); F05D 2300/6034 (2013.01); F05D 2300/612 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A casing for a gas turbine engine, comprising:
an inner ring portion;
an intermediate layer of honeycomb and/or foam secured to a radially outward surface of the inner ring portion;
an outer ring portion secured to a radially outward surface of the layer of honeycomb and/or foam; and
a composite containment belt secured to a radially outward surface of the outer ring portion, the composite containment belt having a central portion integrally formed with a forward ring portion and an aft ring portion, the composite containment belt formed from at least one single woven belt wound about the outer ring portion, the at least one single woven belt including a plurality of continuous fibers, wherein a first portion of the plurality of continuous fibers are at arranged at an angle of 45/−45 degrees or greater with respect to a circumferential direction of the composite containment belt in the central portion and a second portion of the plurality of continuous fibers are at arranged at an angle of less than 45/−45 degrees with respect to the circumferential direction of the composite containment belt in the forward ring portion and the aft ring portion.