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):

Report Date:

1978-07-11

Pagination or Media Count:

8.0

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

Subject Categories:

  • Countermeasures
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE