United Technologies Corporation

Sikorsky Aircraft Corporation

Richard S Barnard

Armand F Amelio

Robert C Frawley

Scott A Chasen

Thomas Perrotta

Jon C Peters

James J Manzolli

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.

Integrated engine air particle filter assembly

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. The exhaust gas suppression system is preferably disposed in the tail section of a helicopter aircraft, having nozzles pointing in an essentially downward direction to reduce the threat from an over flying aircraft while minimizing the ability of ground based systems to acquire a direct line of sight on any hot surfaces or to detect the exhaust cavity using radar.

Suppression system for a gas turbine engine

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.sub.O) thereof is disposed internally of the lower fuel filtering portion (42) and such that the coarse apertures (44.sub.O) of the upper bypass portion (44) are distally spaced from the inlet orifice (18.sub.O). The fuel intake device is further characterized by a shroud member (50) disposed about the filter assembly (40), which shroud member (50) includes an upper end portion (52) disposed in sealed combination with an external peripheral surface (18.sub.P) of the internal fuel feed line (18) and a lower end portion (54) which extends into the sump region (26) of the fuel tank (14). The lower end portion (54), furthermore, defines an opening for facilitating fuel flow to the filter assembly (40).

Fuel intake device for fuel systems

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.

Low observable engine inlet system

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.

Growing community of inventors

Monroe, CT, United States of America

Richard S Barnard