Gas Turbine Engine Exhaust Jet Shear-layer Pressure Measurement System Navy SBIR FY2011.2 Sol No.: Navy SBIR FY2011.2 Topic No.: N112-098 Topic Title: Gas Turbine Engine Exhaust Jet Shear-layer Pressure Measurement System Proposal No.: N112-098-0714 Firm: ATA Engineering, Inc 11995 El Camino Real Suite 200 San Diego, California 92130-2566 Contact: Parthiv Shah Phone: (858) 480-2101 Web Site: www.ata-e.com Abstract: ATA Engineering proposes an SBIR program to design, develop, and demonstrate a jet shear-layer hydrodynamic pressure measurement system capable of detecting large-scale organized turbulence structures in full-scale military/commercial engine exhaust plumes. The ability to detect such structures at full-scale on an engine test stand is the necessary precursor to the ultimate goal of full-scale noise reduction through models that can be used for prediction and control of the spatio-temporal evolution of the jet shear-layer turbulence. ATA and its partners will leverage a breadth of expertise in the modeling of jet noise and the measurement, interpretation, and far-field projection of aeroacoustic noise sources using a high-resolution continuous-scan array technology developed under F-35 program SBIR funding and demonstrated at model-scale. Acquisition of fluctuating pressure data with a continuously moving array maximizes the efficiency of the data sampling in terms of sensor count, acquisition time (hence, engine run time), and measurement accuracy. The objective of the Phase I SBIR effort will be to determine the feasibility of the design of a near-field measurement system and propose a candidate mechanical and software design that can be built and demonstrated post-Phase I in an engine test stand environment. Benefits: The end product of this technology development effort will be a gas turbine engine exhaust jet shear-layer pressure measurement system that will enable detection and quantitative measurement of instability waves caused by convecting large-scale turbulence structures which may ultimately be used in source modeling and empirical confirmation of the effectiveness of proposed engine noise reduction technologies at full-scale. This technology will initially be tailored specifically for military jet engines but can also be modified to characterize noise sources for a wide variety of engine exhausts. There are significant commercial applications and opportunities for this measurement system including military and commercial jet noise reduction, measurement of lift-off acoustic loads for launch vehicles, and improved design of hearing protection for people exposed to exhaust noise. Return