We will demonstrate the feasibility of a piezoluminecent sensor for making measurements of the distribution of pressures on turbine vanes and blades in low temperature (up to 500 F or 260 C) aeropropulsion research facilities. The research will address three critical issues; 1) we will select which of three potential design approaches for piezolminescent sensors is best-suited to this application, with special emphasis on achieving spatial resolution better than 0.25 mm over an area at least as large as 100mm by 100mm; 2) we will identify structuraland electrical components consistent with operation at 260 c; and 3) we will demonstrate electroluminescent phosphors for operation at 260 C In addition, 4) we will build a piezoluminescent sensor and test it at 260 C, and we will determine what issues remain to be addressed to provide a sensor system for measurements in research facilities in Phase II and later.
Keywords: Sensor, Turbine, Vanes, Blades
