Robust Pressure Transducer for Propulsion Control Systems

Pressure measurements in gas turbine engines are unacceptably constrained by the limited operating temperatures of commercially available sensors. In engine hot sections, electronic semiconductor material-based sensors must be cooled or remotely located and connected using a pneumatic tube. Dispersion of pressure waves in the tubes degrade frequency response needed for the measurement of transient pressure phenomena. Because of size, weight and geometrical constraints, in situ cooling of electronic pressure sensors is also impractical for many test applications and unacceptable for most flight applications. Today, important needs for dynamic pressure measurements in gas turbine hot sections are currently unmet. In this Phase II program, Prime Photonics will build upon the successful Phase I demonstration of an optically excited, optically interrogated resonant beam sensor (RBS) to develop a low-cost, practical sensor for measurement of dynamic pressures at frequencies of at least 5 kHz and at temperatures up to 2200 degrees F. RBS technology combines the high operating temperature and EMI immunity of optical sensors with the simple, low cost signal processing afforded by digital phase lock loops. The Phase II technology development will culminate with testing on a gas turbine engine, and will parallel commercialization activities directed towards product transition.