Multiplexed Spectroscopy Sensor for Assessing Combustion Instabilities in Jet Engine Augmenters

This Phase II proposal outlines a research, development, and field test plan to complete a novel diagnostic sensor for gas turbine/augmented aircraft engines, the ZoloTASS, based on wavelength multiplexed tunable diode laser spectroscopy (WM-TDLAS). The sensor's attributes include that it is totally fiber-coupled, non-contact, and non-invasive. The proposed sensor will aid in the design, development, and testing of augmented gas turbine engines by enabling the user to monitor combustion instabilities that can occur producing lean blow-off or intense combustion-driven dynamics both of which can be catastrophic. The sensor will find immediate use in the development of the F135/F136 engine for the Joint Strike Fighter (JSF) program that has experienced unexpected difficulties with augmenter performance. The sensor can be used as a diagnostic during engine ground tests and to perform measurements to validate CFD calculations. Both functions should reduce JSF engine development time and cost as well as helping to insure a successful outcome. In addition, the proposed sensor can be used to monitor emissions from gas turbine engines such as CO, CO2, H2O, and NO2. It can simultaneously monitor exhaust temperature.