Non-metallic engine case inlet compression seal for a gas turbine engine

1. A J-shaped 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 the gas turbine engine, said non-metallic longitudinal leg section comprises a radially inwardly projecting stepped surface configured for positioning immediately axially adjacent to a forward circumferential edge of said outer case structure, said non-metallic longitudinal leg section configured for positioning on top of the outer case structure; and

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.

2. 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.

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 mount flange section.

4. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein said non-metallic longitudinal leg section has a durometer hardness different than a durometer hardness of said of said non-metallic mount flange section.

5. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein each of said non-metallic arcuate interface section, said non-metallic longitudinal leg section, and said non-metallic mount flange section have a different durometer hardness.

6. The non-metallic engine case inlet compression seal as recited in claim 5 , wherein each of said non-metallic arcuate interface section, said non-metallic longitudinal leg section, and said non-metallic mount flange section are integral.

7. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein each of said non-metallic arcuate interface section, said non-metallic longitudinal leg section, and said non-metallic mount flange section are integral.

8. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein each of said non-metallic arcuate interface section, said non-metallic longitudinal leg section, and said non-metallic mount flange section are manufactured of a silicone rubber.

9. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein at least one of said non-metallic arcuate interface section, said non-metallic longitudinal leg section, and said non-metallic mount flange section includes fiber reinforcement.

10. The non-metallic engine case inlet compression seal as recited in claim 9 , wherein said fiber reinforcement includes an aramid material.

11. The non-metallic engine case inlet compression seal as recited in claim 1 , further comprising a fiber reinforcement that impregnates at least one of said non-metallic arcuate interface section, said non-metallic longitudinal leg section, and said non-metallic mount flange section.

12. The non-metallic engine case inlet compression seal as recited in claim 1 , further comprising 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.

13. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein said non-metallic engine case inlet compression seal is configured to be positioned forward of a fan section of said gas turbine engine.

14. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein said non-metallic engine case inlet compression seal is configured to extend from the outer case structure and from a forward circumferential edge of a fan section forward of an engine mount of the gas turbine engine.

15. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein said non-metallic arcuate interface section is configured to be positioned around an engine axis of the gas turbine engine.

16. The non-metallic engine case inlet compression seal as recited in claim 1 , wherein said non-metallic arcuate interface section is circular.

17. The non-metallic engine case inlet compression seal as recited in claim 1 , further comprising a fiber reinforcement bonded to an outer surface of said non-metallic longitudinal leg section to sandwich said non-metallic leg section between said outer case structure and said fiber reinforcement.