Thermal Math Model Development for a Resonant Cavity Temperature Sensor.
Final rept. 28 Jun-31 Dec 73,
HONEYWELL INC MINNEAPOLIS MINN GOVERNMENT AND AERONAUTICAL PRODUCTS DIV
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The use of fluidic, resonant cavity temperature sensors has shown some promise for measuring ramjet engine combustor temperatures ranging up to 4000R. This program was established to develop a thermal math model of the temperature sensor through testing and analysis. With a thermal math model, approaches can be evaluated for reducing heat transfer losses and for evaluating techniques to compensate for sensor errors. Test variables for the sensor were insulator material and mass flow through the sensor. The insulator materials used were Hastelloy X, magnesium oxide and zirconium oxide. These materials had a thermal conductivity range of about 10 to 1. The test data was used to adjust the math model and validate its performance. The general heat transfer approach used for developing the math model is described. Techniques are also evaluated for compensating sensor errors. Lastly, sensor performance is evaluated over a large range of ramjet combustor pressure and temperature conditions. Modified author abstract
- Test Facilities, Equipment and Methods
- Combustion and Ignition
- Jet and Gas Turbine Engines