Abstract: A secondary oil system for a flight propulsion gas turbine engine includes an oil reservoir rotatable as a unit with a rotor shaft of the engine, means conducting a portion of the primary oil flow of the engine to the rotating reservoir, a discharge orifice on the reservoir limiting centrifugal force induced oil discharge from the reservoir to a secondary oil flow rate substantially less than the primary oil flow rate to a bearing supporting the rotor on a case of the engine, and means for conducting the secondary oil flow to the bearing. The secondary oil flow persists for on the order of ten minutes after primary oil flow stops.