Exhaust Plume Reduction and Cooling System.
DEPARTMENT OF THE NAVY WASHINGTON D C
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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
- Jet and Gas Turbine Engines