The present application provides a compressive stress system for a gas turbine engine. The compressive stress system may include a first bucket attached to a rotor, a second bucket attached to the rotor, the first and the second buckets defining a shank pocket therebetween, and a compressive stress spring positioned within the shank pocket.
FEDERAL RESEARCH STATEMENT
This invention was made with Government support under Contract No. DE-FC26-05NT42643, awarded by the U.S. Department of Energy (DOE). The Government has certain rights in this invention.