Advanced Large Diameter Air Seals

During Phase I testing, flow factors less than 0.02 for the candidate non-contacting compliant surface axial face seal were measured demonstrating the feasibility of this technology for advanced turbine engines. Under Phase II, the concept design will be enhanced to reduce flow factor to less than .01 and permit axial motions of approximately 0.150 inches. The seal design will then be fabricated and tested under realistic operating conditions of temperature, differential pressure, surface velocity and axial motions to demonstrate performance substantially better than brush, labyrinth and conventional carbon face seals. Initial testing will be conducted with seals sized for smaller engines, but under large-scale engine dynamic conditions. Finally testing of a segment of the complete full-scale seal will be tested statically. To ensure realistic engine test conditions and a path for technology transition to product in both military and commercial engines a major gas turbine engine manufacturer has been enlisted to support the effort with the necessary engine and test requirements as well as design reviews.