| CPC F02C 7/25 (2013.01) [B64D 27/10 (2013.01); F01D 25/18 (2013.01); F02C 7/14 (2013.01); F02C 7/185 (2013.01); F02C 7/22 (2013.01); F02C 7/222 (2013.01); F02C 7/232 (2013.01); F02C 7/36 (2013.01); F02C 9/263 (2013.01)] | 20 Claims |

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1. A reservoir system for a heat exchanger of an aircraft engine, comprising:
a reservoir of the heat exchanger having an inner chamber that contains a flammable fluid;
an inlet to the inner chamber, the inlet fluidly connected to a source of the flammable fluid which pressurizes the flammable fluid to a pressure during an operational condition of the aircraft engine;
an outlet to the inner chamber;
an air source that operates at a pressure that is lower than the pressure of the flammable fluid during the operational condition of the aircraft engine; and
a valve selectively fluidly connecting the inner chamber to the air source, the valve being movable between a closed position, in which the pressure of the flammable fluid in the inner chamber acting on the valve exceeds the pressure of air from the air source acting on the valve such that the valve blocks the air from entering the inner chamber, and an open position, in which the pressure of the flammable fluid in the inner chamber acting on the valve is lower than the pressure of the air from the air source acting on the valve such that the valve allows the air to flow into the inner chamber and evacuate the flammable fluid from the inner chamber through the outlet.
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