47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011
JUL 31-AUG 03, 2011
San Diego, CA, United states
In this paper, an integrated water-cooled sensor has been developed to simultaneously measure the heat flux and temperature at the wall of a scramjet combustor. The sensor was designed based on the principle of Gardon heat-flux gauge. Numerical simulation of the heat conduction processes inside the sensor has been carried out to obtain the time responses of the sensor. Calibration processes using radiative and conductive heating sources were carried out and calibration curves such as heat flux vs. output voltage and wall temperature vs. heat flux were obtained. The effects of structural material and dimensions on the sensor's responses have also been examined. Several wall heat flux/temperature sensors have been built and tested in a Mach 2.5 supersonic combustor at stagnation temperatures up to 1920 K and the results demonstrat satisfactory time response and stability of the sensor.
American Institute for Aeronautics and Astronautics (AIAA)