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