Addressing the issues of slow dynamic response and poor measurement accuracy of airflow temperature sensors used in aero-engines

an analysis and real-time compensation of steady-state and dynamic errors were conducted for a certain type of turbo-exhaust temperature sensor selected for aero-engines. Based on the physical model of the airflow temperature sensor

a numerical simulation of thermal-flow coupling was performed. A dynamic real-time compensation model based on a second-order compensation system was proposed and validated through experiments in a calibrated hot-wind tunnel. The results showed that the simulation results were basically consistent with the sensor time constants obtained from the calibrated hot-wind tunnel tests

verifying the accuracy of the simulation model. Meanwhile

after realtime compensation

the steady-state and dynamic errors were significantly reduced

suppressing the overshoot phenomenon of dynamic response. At an incoming total temperature of 772.95 K and an incoming Mach number of 0.400

the minimum reduction in steady-state error was 0.1 ℃

with a decrease of 98.6%. At an incoming step temperature of 403–594 ℃ and an incoming Mach number of 0.402

the maximum reduction in dynamic error was 63.9%.