Development of pressure sensor for the instrumentation of experimental aerodynamic facilities has traditionally concentrated on electrical techniques. Such transducers have temporal and spatial resolutions that are currently insufficient to provide the accurate measurement of turbulent flows behind turbine rotor stages, for example. We present result obtained in a turbine test rig form a simple fiber optic pressure sensor based upon the interferometric response of an extrinsic cavity formed between the interrogation fiber and a reflective diaphragm. We discuss the design trade-offs, optical interrogation and temperature sensitivity of such a configuration, and demonstrate the success of the design in small-scale shock tube experiments. We then describe the application of the sensor in a full scale turbine test facility.
|Number of pages||10|
|Journal||Proceedings of SPIE - the International Society for Optical Engineering|
|Publication status||Published - 1998|
|Event||Laser Interferometry IX: Techniques and Analysis - San Diego, CA, United States|
Duration: 20 Jul 1998 → 20 Jul 1998