Accession Number : AD0163622


Title :   Supersonic Jet Engine Inlet Flueric Bypass Control.


Descriptive Note : Patent,


Corporate Author : OFFICE OF THE SECRETARY OF THE ARMY WASHINGTON D C


Personal Author(s) : Warren,Raymond W. ; Holmes,Allen B.


Report Date : 09 MAR 1971


Pagination or Media Count : 4


Abstract : The patent relates to a flueric system for controlling the position of the normal shock wave in a turbojet diffuser is disclosed. Control is accomplished without the use of mechanically moving parts by providing an exhaust tube for reducing the pressure downstream of the normal shock. A fluid feedback path which is responsive to a pressure differential on opposing sides of the shock wave produces a fluid control signal which is capable of deflecting fluid away from the exhaust tube and thereby effectively closing off the exhaust tube whenever the shock wave has relocated itself in a stable position.


Descriptors :   (*FLUID AMPLIFIERS, *PATENTS), SUPERSONIC AIRCRAFT, TURBOJET ENGINES, DIFFUSERS, SHOCK WAVES


Subject Categories : FLUIDICS AND FLUERICS


Distribution Statement : APPROVED FOR PUBLIC RELEASE