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: An IR Suppressor (20) operative to suppress the infrared signature radiated from the high-temperature exhaust of an engine (12) and comprising a primary exhaust manifold (22), first and second mixing ducts (24a, 24b), and a secondary flow shroud (26). More specifically, the primary exhaust manifold (22) includes an elongate duct (28) adapted for receiving a primary flow of the high-temperature engine exhaust from the engine and at least two high aspect ratio nozzles (30a, 30b) integrated in combination with the elongate duct (28). The high aspect ratio nozzles (30a, 30b) are positioned so as to define at least two outlets at the same axial station along the length of the elongate duct (28). The first and second mixing ducts (24a, 24b) are disposed over the high aspect ratio nozzles (30a, 30b) so as to form a mixer/ejector defining at least two ejector inlets (44).

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.