Ultrasonic Transmission Investigations for Turbine Inlet Gas Temperature Measurement.
Final rept. Jan 71-Jun 72,
BENDIX CORP SOUTH BEND IND ENERGY CONTROLS DIV
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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 transmitterreceiver 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
- Safety Engineering
- Jet and Gas Turbine Engines