Oil leakage recovery system for gas turbine engine

A gas turbine engine comprising:

• at least one internal combustion engine;
• an oil system including an oil reservoir fluidly connected to the internal combustion engine for lubricating the internal combustion engine;
• and
• an oil leakage recovery system fluidly connected to the oil system for recovering leaked oil in the oil system, the oil leakage recovery system including:
• a collecting reservoir extending from an upper portion to a lower portion relative to a horizontal placement of the gas turbine engine relative to the ground in a parked aircraft, the upper portion having an inlet opening and the lower portion being close ended and configured to collect and hold the leaked oil therein by gravity through a first flow path between the inlet opening and the lower portion, the collecting reservoir having an outlet opening disposed between the inlet opening and lower portion, the outlet opening providing access to a second flow path separate from the first flow path, the inlet opening and the outlet opening communicating with the oil system;
• a piston operatively mounted with the collecting reservoir between the upper portion and the lower portion, the piston movable to a first position in which the piston is disposed away from the outlet opening to allow oil to leak from the collecting reservoir to the oil system through the second flow path and a second position in which the piston blocks second flow path to impede oil leaking from the collecting reservoir to the oil system;
• and
• a pressure-controlled actuator system configured to move the piston to the first position when a pressure of the oil system is below a threshold pressure value and to the second position when the pressure of the oil system is above the threshold pressure value.