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):

Report Date:

1971-03-09

Pagination or Media Count:

4.0

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.

Subject Categories:

  • Fluidics and Fluerics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE