Non-metallic engine case inlet compression seal for a gas turbine engine
A non-metallic engine case inlet compression seal for a gas turbine engine includes a non-metallic longitudinal leg section that extends from the non-metallic arcuate interface section and a non-metallic mount flange section that extends from the longitudinal leg section.
1. A non-metallic engine case inlet compression seal for a gas turbine engine to form a compression interface with an airframe bulkhead, comprising:
a non-metallic arcuate interface section;
a non-metallic longitudinal leg section that extends from said non-metallic arcuate interface section, said non-metallic longitudinal leg section configured to be at least partially radially supported on an outer case structure of said gas turbine engine, said non-metallic longitudinal leg section comprises a stepped surface adjacent to a forward circumferential edge of said outer case structure;
a non-metallic mount flange section that extends transversely from said longitudinal leg section, said non-metallic mount flange having a multitude of apertures to mount said non-metallic engine case inlet compression seal to said outer case structure of said gas turbine engine; and
a fiber reinforcement bonded to an outer surface of at least one of said non-metallic arcuate interface section, said non-metallic longitudinal leg section, and said non-metallic mount flange section.
2. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein said fiber reinforcement includes an aramid material.
3. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein said non-metallic arcuate interface section has a durometer hardness different than a durometer hardness of said non-metallic longitudinal leg section.
4. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein said non-metallic longitudinal leg section is circular.