US 12,281,702 B2
Non-metallic engine case inlet compression seal for a gas turbine engine
Anthony R. Bifulco, Ellington, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Jan. 30, 2024, as Appl. No. 18/427,070.
Application 18/427,070 is a division of application No. 17/496,288, filed on Oct. 7, 2021, granted, now 11,988,283.
Application 17/496,288 is a division of application No. 16/108,758, filed on Aug. 22, 2018, granted, now 11,143,303, issued on Oct. 12, 2021.
Application 16/108,758 is a division of application No. 14/948,657, filed on Nov. 23, 2015, granted, now 10,077,669, issued on Sep. 18, 2018.
Claims priority of provisional application 62/084,603, filed on Nov. 26, 2014.
Prior Publication US 2024/0255056 A1, Aug. 1, 2024
Int. Cl. F16J 15/02 (2006.01); F16J 15/10 (2006.01); F16J 15/06 (2006.01); F16J 15/46 (2006.01)
CPC F16J 15/027 (2013.01) [F16J 15/104 (2013.01); F05D 2240/55 (2013.01); F16J 15/025 (2013.01); F16J 15/062 (2013.01); F16J 15/46 (2013.01)] 4 Claims
OG exemplary drawing
 
1. A gas turbine engine, comprising:
an outer case structure defined along an engine axis;
a non-metallic mount flange section having a multitude of apertures to mount said non-metallic mount flange section to said outer case structure forward of a fan section of said gas turbine engine;
a non-metallic longitudinal leg section that extends transversely from said non-metallic mount flange section, said non-metallic longitudinal leg section at least partially radially supported on said outer case structure; and
a non-metallic arcuate interface section that extends from said non-metallic longitudinal leg section, said non-metallic arcuate interface section defined around said engine axis, wherein said non-metallic arcuate interface section has a durometer hardness different than a durometer hardness of said non-metallic longitudinal leg section.