Accession Number : AD0692292

Title :   FLUERIC NORMAL SHOCK SENSOR,

Corporate Author : HARRY DIAMOND LABS WASHINGTON D C

Personal Author(s) : Holmes,Allen B. ; Gehman,Stacy E. ; Egolf,David ; Lewellen,Michael

Report Date : APR 1969

Pagination or Media Count : 26

Abstract : A circuit for measuring shock location in the divergent section of a jet-engine inlet diffuser was designed and tested. The circuit consists of 12 bistable sensing elements and a fluid logic network. Control signals to the sensors are obtained from static pressure taps located along the diffuser wall. Fluid logic is employed to prevent erroneous signals from affecting the computed shock position. The circuit was bench-tested over a wide range of pressures to simulate actual operation on an experimental inlet between Mach numbers 1.75 and 3.0. These tests were conducted to establish the static response of the circuit to variations in wall pressure, supply pressure, and ambient pressure. (Author)

Descriptors :   (*DETECTORS, *FLUID AMPLIFIERS), (*SHOCK WAVES, DETECTORS), (*SUPERSONIC DIFFUSERS, TEST EQUIPMENT), JET ENGINES, LOGIC CIRCUITS, PRESSURE, FLUID AMPLIFIERS

Subject Categories : Fluidics and Fluerics
      Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE