GAS TURBINE EXIT TEMPERATURE MEASUREMENT

THE AIR FORCE NEEDS RELIABLE AND ACCURATE GAS TEMPERATURE MEASURING CAPABILITY AT HIGH TEMPERATURES. A SPECIFIC APPLICATION IS IN MEASURING GAS TURBINE COMBUSTOR EXIT TEMPERATURES, WHERE CURRENT NEEDS EXCEED THE CAPABILITY OF EXISTING TEMPERATURE MEASUREMENT SYSTEMS. THIS PROGRAM WILL DETERMINE THE FEASIBILITY OF A THERMAL PROBE SYSTEM CAPABLE OF 15 DEG F ACCURACY AT 2000 TO 3000 F FOR THE GAS TURBINE APPLICATION. THE PROPOSED METHOD CAN BE EXTENDED TO OTHER TEMPERATURE RANGES AND ENVIRONMENTS, GREATLY INCREASING ACCURACY AND TIME RESPONSE WITHOUT SACRIFICING PROBE DURABILITY. THE TECHNIQUE DESCRIBED USES COMMERCIALLY AVAILABLE PROBE MATERIALS AND SIGNAL CONDITIONING HARDWARE TO ACHIEVE THIS PERFORMANCE IN A SYSTEM THAT IS SIMPLER AND MORE RELIABLE THAN RADIATION PRYOMETRY OR LASER-BASED THERMOMETRY.