Abstract: An engine air particle filter system configured to selectively receive one of at least a first tray which supports a first filter media and a second tray which supports a second filter media different than the first filter media.

Abstract: An engine air particle filter system configured to selectively receive one of at least a first tray which supports a first filter media and a second tray which supports a second filter media different than the first media.

Abstract: A suppression system for a gas turbine engine uses a tapered exhaust manifold with a plurality of exhaust nozzles acting in conjunction with a plurality of mixing cells to produce cooling of an exhaust gas stream upon exit from an aircraft. The cooling air is supplied to the mixing cells in such a way that the walls of the cells are inherently maintained at a desired temperature without the use of dedicated cooling apparatus such as finned head exchangers, film cooling slots, etc. This approach allows the typically conflicting requirements of low IR signature and low radar cross section to be simultaneously satisfied in an efficient, light weight and low cost manner.

Abstract: A fuel intake device (20) for a fuel system (10) having a fuel tank (14) for containing a supply of fuel (16) and an internal fuel feed line (18) which is disposed internally of the fuel tank (14) and which extends into a sump region (26) thereof. The fuel intake device (20) is characterized by a filter assembly (40) which envelopes an end portion (18.sub.E) of the internal fuel feed line (18) and which includes a lower fuel filtering portion (42) and an upper fuel bypass portion (44). The lower fuel filtering portion (42) has a plurality of fine apertures (42.sub.O) therein for facilitating a primary flow (P.sub.F) of fuel (16) therethrough and for filtering debris from the supply of fuel (16) in a normal operating mode. The upper fuel bypass portion (44) has a plurality of coarse apertures (44.sub.O) for facilitating a secondary flow (S.sub.F) of fuel therethrough in a bypass operating mode. Furthermore, the filter assembly (40) is situated about the end portion (18.sub.E) such that the inlet orifice (18.

Abstract: A turbine engine inlet system includes a curved duct 14 to deliver air to the engine, an inlet lip 16 to smooth the entry of air flowing into the duct, a forward inlet section 18 submerged within the aircraft skin contour to provide a degree of ram recovery to the duct, and a movable air deflector 20 which is flush with the forward inlet section 18 during normal flight conditions and extended to slightly above the inlet lip 16 during icing conditions.

Abstract: A compact, lightweight integrated environmental control (IEC) system for a helicopter incorporates in operative combination an environmental control system (ECS) and a nuclear/biological/chemical life support system (NBC LSS). The IEC system includes a refrigerant subsystem, a regenerative heat exchange apparatus, a decontamination subsystem, and an airflow distribution network, and is operative to provide super-cooled, super-dry, decontaminated airflow, in seriatim, directly to left and right mission equipment package bays and the cockpit for cooling of avionics/electronic modules and crew comfort. The IEC system is further operative to directly provide cooled, super-dry, decontaminated airflow for cooling of avionics/electronic modules of the mid mission equipment package bay and for over pressurizing the left and right mission equipment package bays to preclude contaminant infiltration thereof.