Accession Number : AD0752602
Title : Ultrasonic Transmission Investigations for Turbine Inlet Gas Temperature Measurement.
Descriptive Note : Final rept. Jan 71-Jun 72,
Corporate Author : BENDIX CORP SOUTH BEND IND ENERGY CONTROLS DIV
Personal Author(s) : Ahern,C. J. ; Longstreet,C. S. ; Teitelbaum,B. R. ; Werts,W. E.
Report Date : SEP 1972
Pagination or Media Count : 288
Abstract : For advanced turbine engine propulsion systems, the need for an accurate, fast response turbine inlet gas temperature measurement is becoming more acute. One of the potentially promising techniques is the ultrasonic gas gap approach which utilizes the transit time of a high-frequency acoustic pulse to determine the average gas temperature along a path through the sound supporting medium. The objective of this Air Force sponsored research and development effort was to ascertain the potential and limitations of such an approach. Based on engine noise tests conducted on a J85-7 turbojet engine and both bench and burner rig evaluations of candidate transmission approaches, a matched piezoelectric transmitter/receiver pair operating in a gated RF mode within the carrier frequency range of 200 to 500 kHz was selected as a prototype engine sensor. (Author)
Descriptors : (*TURBOJET ENGINES, *TEMPERATURE WARNING SYSTEMS), PIEZOELECTRIC TRANSDUCERS, ACOUSTIC EQUIPMENT, ULTRASONIC RADIATION, JET ENGINE NOISE, IMPEDANCE MATCHING, SIGNAL GENERATORS, TEST METHODS, DETECTORS
Subject Categories : Safety Engineering
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE