Novel Laser-Based Diagnostics and 3D Numerical Modeling for Quantitative Characterization of Burning Phenomenon in the Turbine
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5100 Springfield Street, Suite 301, Dayton, OH, -
AbstractABSTRACT: The objectives of the proposed research effort is to provide a comprehensive measurements and modeling tools to understand the physics and chemistry associated with burning phenomenon near the turbine surface for various cooling hole configurations. Current state-of-the-art measurements and modeling tools are inadequate in addressing the issues related to burning phenomenon near the turbine surface. The measurements, modeling, and new cooling configurations are geared toward addressing the following issues: 1. Quantify the conditions that result in"burning in the turbine."2. Quantitatively determining the effects of various cooling-hole configurations in preventing or reducing the heat release related to the secondary combustion near the turbine blade. 3. Identifying the areas that needed to be cooled based on a 2D measurement of temperature and heat-release rates near the turbine blade. 4. Identifying coolant delivery methods to the needed areas as guided by quantitative measurements of temperature and species concentrations. 5. Validating that coolant maintains vane at acceptable temperatures without burning. Successful demonstration of these measurements and the 3D modeling during the Phase-II research effort will allow us to address the issues related to"burning phenomenon in the turbine"in great detail. The goal of the research program is to establish a sufficient understanding for the development of turbine-cooling schemes that enable the application of the UCC/ITB or the development of advanced cooling systems for future war-fighter systems. BENEFIT: The proposed research effort will provide new diagnostic and modeling capabilities that will enable the Air Force and gas-turbine-system manufacturers to address the challenges associated with the development of compact combustors and their integration with turbines. These tools are critical for the development and long-term health of propulsion systems for high-performance military as well as for commercial systems. The proposed research will also help to advance the state-of-the-art turbine-cooling technology by quantitatively identifying various factors that lead to burning in the turbine and then by designing innovative cooling configurations for preventing burning near the turbine blades. Quantitative measurements are critical for validating numerical models of reacting and non-equilibrium phenomena affecting modern gas-turbine and hypersonic propulsion systems. The proposed experimental and numerical tools will enable analysis of military and commercial gas-turbine combustors, as well as of applications with limited optical access such as internal combustion engines and stationary power-generation systems.
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