Accession Number : ADD005358

Title :   Exhaust Plume Reduction and Cooling System.

Descriptive Note : Patent,

Corporate Author : DEPARTMENT OF THE NAVY WASHINGTON D C

Personal Author(s) : Inglee,Clinton F

Report Date : 11 Jul 1978

Pagination or Media Count : 8

Abstract : A radiation suppressor for exhaust turbine or other engines which significantly reduces the lock-on range in infrared seeking missiles is provided. Engine exhaust gases are the sole power source for driving an exhaust turbine which includes a self-contained turbo-fan assembly and a surrounding plenum-shroud assembly both of which are structurally supported by the aircraft or other vehicle-cooling air duct assembly. The turbo-fan assembly comprises a turbine wheel having a top or outer fan for providing both hot metal and plume cooling air and a central centrifugal blower to partially cool the hollow turbine blades. The duct assembly is combined with ambient air passages to distribute plume cooling air, while a plenum-shroud assembly which surrounds these assemblies includes internally cooled radial vanes disposed in a turbine shroud as well as an outer fairing having flow passages for cooling air. (Author)

Descriptors :   *Patents, *Exhaust plumes, *Infrared signatures, *Suppressors, Cooling, Air cooled, Gas turbines, Turbofan engines, Turbojet engines

Subject Categories : Countermeasures
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE