EVALUATION OF THE CONDUCTRON FLAMEOUT SENSOR FOR GAS TURBINE AUTOMATIC RESTART SYSTEM.
Final technical rept.,
NAVAL AIR PROPULSION TEST CENTER TRENTON N J AERONAUTICAL TURBINE DEPT
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The Conductron Model 66A001 Flameout Sensor was evaluated under flameout conditions induced by fuel derichment and simulated missile exhaust gas ingestion at sea level, Mach 0.0, 0.5 and 0.8. The Conductron Flameout Sensor satisfactorily observed the presence and absence of flame when the sensor was mounted in the engine spark ignitor opening. The sensor responded rapidly 0.05 seconds to observed loss of flame and did not give false responses during rapid engine transients. Author
- Jet and Gas Turbine Engines