Abstract: A flammability reduction system and method for controlling air pressure and allowing an air separation module (ASM) to consume less pressurized air includes a pressure limiting valve that is dynamically controlled based upon a defined pressure setpoint. A flammability reduction system and method for predictively monitoring the ASM's health and its remaining useful life includes a flow and/or oxygen sensor that are used to detect trends in ASM flow rate and/or oxygen content in the inert gas produced by the ASM. A flammability reduction system and method for controlling heat load includes flow and temperature sensors for calculating heat load of a component, and controls one or more valves to adjust temperature and/or flow rate to control the heat load based upon a heat load setpoint.

Abstract: A venting system (10) in an aircraft (12), where the aircraft (12) is substantially symmetrical about a midline (14), has a pair of wings (16 and 18) extending outwardly on respective sides of the midline (14), a center fuel tank (20), a surge tank (22 and 24) at outer ends of each wing (16 and 18), and optionally one or more wing fuel tanks (26 and 28) interposed between the center fuel tank (20) and the respective surge tank (22 or 24). The venting system (10) for the center fuel tank (20) includes a main vent line (30) that extends across the midline (14) to vent openings (32 and 34) communicating with respective surge tanks (22 and 24). The main vent line (30) forms a linear flow path for fluid, generally air, flowing between opposite ends of the vent line (30). The venting system (10) also includes a branch vent line (36 and 38) extending from the main vent line (30) and opening on the center fuel tank (20). The branch line has at least one fuel tank opening (40 and 42) on each side of the midline (14).

Abstract: A flammability-reducing gas distribution system (10) for an aircraft includes a conduit (20) for distributing flammability-reducing gas within the fuel tank (12) while preventing or minimizing the potential for the buildup of a column of liquid against a separating valve (24) that prevents the exit of liquid fuel from the fuel tank (12). The conduit (20) includes a trap (26) in which liquid that enters the conduit (20) will accumulate. The trap (26) includes a drain (30), such as a float drain valve, to drain liquid from the trap (26) back into the fuel tank (12). The trap (26) includes a section of the conduit (20) at a local minimum elevation between sections of conduit (20) with relatively higher elevations. Consequently, any liquid that enters the distribution conduit (20) can be captured in the trap (26), minimizing or eliminating the opportunity for a liquid column to form against the separating valve (24).

Abstract: A venting system (10) in an aircraft (12), where the aircraft (12) is substantially symmetrical about a midline (14), has a pair of wings (16 and 18) extending outwardly on respective sides of the midline (14), a center fuel tank (20), a surge tank (22 and 24) at outer ends of each wing (16 and 18), and optionally one or more wing fuel tanks (26 and 28) interposed between the center fuel tank (20) and the respective surge tank (22 or 24). The venting system (10) for the center fuel tank (20) includes a main vent line (30) that extends across the midline (14) to vent openings (32 and 34) communicating with respective surge tanks (22 and 24). The main vent line (30) forms a linear flow path for fluid, generally air, flowing between opposite ends of the vent line (30). The venting system (10) also includes a branch vent line (36 and 38) extending from the main vent line (30) and opening on the center fuel tank (20). The branch line has at least one fuel tank opening (40 and 42) on each side of the midline (14).