| Popis: |
An un-cooled fiber-optic sensor has been developed for the purpose of gas turbine engine health monitoring. These sensors were developed over the course of 2 SBIR and 1 STTR Phase II’s, each contributing to an advancement in the sensor’s development. Real time direct monitoring of combustion pressure within aircraft turbines will enable more efficient, lower emission designs, through active control of the fuel supply. Sensor prototypes have been demonstrated to operate at greater than 1922°F (1050°C) and 500psig in laboratory experimentation. A co-located measurement system enabled the team to calibrate an alpha prototype sensor over a range of 70°F to 1840°F (20–1000°C) and 0-500psig with an error less than 0.37% Full Scale (FS) over the entire sensor calibration envelope. Previous iterations of this sensor were prototyped and installed into an operating, specially modified, aerospace gas turbine engine immediately after the 1st stage turbine. In this engine the alpha fiber-optic sensor measured dynamic pressures of +/- 0.5 psi while exposed to a maximum temperature of 932.9°F (500.5°C) and a maximum static pressure of 15.4 psig during operation. Finally, another alpha prototype was demonstrated in field trials at a customer facility in two combustors. During these trials the sensor usefully captured hum and rumble oscillations while measuring pressures reasonably accurately at temperatures up to 1652°F (900°C).Copyright © 2007 by ASME |
