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

A sealing assembly for a gas turbine engine, comprising:

• an outer case structure of the gas turbine engine;
• a non-metallic longitudinal leg section that comprises a stepped surface that abuts a forward edge of the outer case structure of the gas turbine engine;
• non-metallic arcuate interface section that extends from said non-metallic longitudinal leg section, said non-metallic arcuate interface section forms a bulb;
• and
• an interface to said bulb to receive air sourced from a secondary airflow path of the gas turbine engine to pressurize a pressurization region formed by said bulb such that the pressurization region formed by said bulb is cantilevered from the forward edge of the outer case structure of the gas turbine engine defined along an engine longitudinal axis of the gas turbine engine to extend generally axially with respect to the engine longitudinal axis.