The objective of this program is to continue the development of an advanced bristle seal concept for use in the primary flowpath and secondary air systems of gas turbine engines, both turbofan/jet and turboshaft/prop. The extension of bristle seal technology into seal applications requiring 1450f and 1450 feet per second tip speed is the goal of this development. The proposed concept will also allow engine rotor excursions without permanently increasing the leakage of the engine seals. The analysis, manufacture of a test article, and static performance testing of the advanced seal will be performed in phase i. Dynamic testing of the seal concept under advanced gas turbine engine conditions, as well as the development of the design methodology required to apply the advanced seal concept to demonstrator and production engines, will be performed in phase ii of the program.
