Abstract
Feasibility for application of a counterrotating intershaft carbon seal to high thrust-to-weight military gasturbine engines was demonstrated through a series of rig tests. The noncontacting high-speed (800 ft/s) seal incorporating hydrodynamic lift geometry with spiral grooves in the seal plates similar to the one designed by NASA-Lewis Research Center. Seal air leakage and carbon wear rates were determined for each of two configurations in rig screening evaluations of 10-h duration. One seal assembly was subjected to an additional 50-h endurance testing. For both configurations, seal air leakage was approximately one-third the leakage that would occur with a conventional labyrinth seal. The wear rate was low for the configuration tested a total of 60 h.
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