Flammable fluid reservoir
An aircraft engine reservoir system includes a reservoir inner chamber containing a flammable fluid. A chamber inlet is fluidly connectable to a flammable fluid source pressurizing the fluid. The chamber includes an outlet. An air source operates at a pressure that is lower that a flammable fluid pressure during an engine operational condition. A valve selectively fluidly connecting the chamber to the air source is movable between a closed position, in which the chamber flammable fluid pressure acting on the valve exceeds the air source pressure acting on the valve such that the valve blocks the air from entering the chamber, and an open position, in which the chamber flammable fluid pressure acting on the valve is lower than the air source pressure acting on the valve such that the valve allows the air to flow into the chamber and evacuate the flammable fluid from the chamber through the outlet.
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.
2. The reservoir system as defined in claim 1 , wherein the valve includes an air inlet in fluid communication with the air source, an air outlet in fluid communication with the inner chamber, and a stopper floatable by the flammable fluid to selectively fluidly couple and uncouple the air inlet and the air outlet.
3. The reservoir system as defined in claim 2 , further comprising a spring operatively coupled to the stopper and operable to compress in the closed position of the valve and extend in the open position of the valve.
4. The reservoir system as defined in claim 1 , wherein the inlet and the outlet are disposed in a lower portion of the inner chamber.
5. The reservoir system as defined in claim 1 , wherein the valve is disposed in an upper portion of the inner chamber.
6. The reservoir system as defined in claim 1 , wherein the valve includes a stopper that is buoyant in the flammable fluid.
7. The reservoir system as defined in claim 1 , wherein the valve, in the open position, allows the air to flow into the inner chamber and evacuate the flammable fluid from the inner chamber both through the outlet and through the inlet.
8. An aircraft engine, comprising:
a source of a flammable fluid which pressurizes the flammable fluid to a pressure during an operational condition of the aircraft engine;
an air source that operates at a pressure that is lower that the pressure of the flammable fluid during the operational condition of the aircraft engine; and
a heat exchanger comprising a reservoir, the reservoir containing the flammable fluid, the reservoir including;
a wall circumscribing an inner chamber containing the flammable fluid;
an inlet to the inner chamber, the inlet fluidly connected to the source of the flammable fluid and flowing the flammable fluid into the inner chamber;
an outlet from the inner chamber, the outlet flowing the flammable fluid out of the inner chamber; and
a valve selectively fluidly connecting the inner chamber to the air source, the valve being movable between a closed position in which the valve blocks air from the air source from entering the inner chamber during an operational state of the aircraft engine 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, and an open position in which the valve allows the air to flow into the inner chamber and evacuate the flammable fluid from the inner chamber through the outlet during a shutdown state of the aircraft engine 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.
9. The aircraft engine as defined in claim 8 , wherein the valve includes an air inlet in fluid communication with the air source, an air outlet in fluid communication with the inner chamber, and a stopper floatable by the flammable fluid to selectively fluidly couple and uncouple the air inlet and the air outlet.
10. The aircraft engine as defined in claim 9 , further comprising a spring operatively coupled to the stopper and operable to compress in the closed position of the valve and extend in the open position of the valve.
11. The aircraft engine as defined in claim 8 , wherein the inlet and the outlet are disposed in a lower portion of the wall.
12. The aircraft engine as defined in claim 8 , wherein the valve is disposed in an upper portion of the wall.
13. The aircraft engine as defined in claim 8 , wherein the valve includes a stopper that is buoyant in the flammable fluid.
14. The aircraft engine as defined in claim 8 , wherein the heat exchanger comprising the reservoir is an air-cooled oil cooler.
15. The aircraft engine as defined in claim 8 , wherein the valve, in the open position, allows the air to flow into the inner chamber and evacuate the flammable fluid from the inner chamber both through the outlet and through the inlet.
16. The aircraft engine as defined in claim 8 , wherein the air source is one of a gearbox, an oil tank, or a scavenge tube of the aircraft engine.
17. A method for evacuating a flammable fluid from a reservoir of a heat exchanger of an aircraft engine, comprising:
flowing a flow of the flammable fluid into the reservoir via an inlet and out of the reservoir via an outlet, the flow of the flammable fluid maintaining a valve to the reservoir in a closed position in which the valve blocks air from an air source from entering the reservoir; and
ceasing the flow of the flammable fluid into the reservoir via the inlet, the ceasing of the flow of the flammable fluid allowing the valve to the reservoir to movie into an open position in which the valve allows the air to flow into the reservoir and evacuate the flammable fluid from the reservoir through the outlet.
18. The method as defined in claim 17 , wherein flowing the flow of the flammable fluid into the reservoir further includes flowing a flow of oil into an oil reservoir in an air-cooled oil cooler for the aircraft engine.
19. The method as defined in claim 17 , wherein flowing the flow of the flammable fluid into the reservoir further comprises the flow of the flammable fluid compressing a spring operatively coupled to a stopper disposed in the valve to block the air from entering the reservoir.
20. The method as defined in claim 17 , wherein ceasing the flow of the flammable fluid into the reservoir via the inlet further includes evacuating the flammable fluid from the reservoir both through the outlet and through the inlet.