US 12,410,728 B2
Hybrid composite components
Nicholas Joseph Kray, Mason, OH (US); and Nitesh Jain, Bangalore (IN)
Assigned to General Electric Company, Evandale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Jun. 7, 2023, as Appl. No. 18/330,841.
Application 18/330,841 is a division of application No. 17/210,845, filed on Mar. 24, 2021, abandoned.
Prior Publication US 2024/0076997 A1, Mar. 7, 2024
Int. Cl. F01D 21/04 (2006.01); F01D 25/24 (2006.01); F02K 3/06 (2006.01)
CPC F01D 21/045 (2013.01) [F01D 25/24 (2013.01); F02K 3/06 (2013.01); F05D 2220/36 (2013.01); F05D 2240/14 (2013.01); F05D 2300/603 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A containment assembly of a gas turbine engine, the gas turbine engine having a fan section including a plurality of fan blades, the containment assembly comprising:
a containment case located within the fan section and at least partially encasing the plurality of fan blades, the containment case extending along an axial direction about a longitudinal centerline of the gas turbine engine, the containment case having an inner surface confronting the plurality of fan blades and an outer surface, opposite the inner surface, defining a radially outermost surface of the containment case, the containment case comprising:
a first composite shell defining a first portion of the outer surface, and
a metallic shell defining a second portion of the outer surface, the metallic shell being at least partially axially aligned with the plurality of fan blades;
wherein the metallic shell interlocks with the first composite shell.