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Propulsion controls and diagnostics research in support of NASA aeronautics and exploration mission programs
U.S. Government
Paperback. Books LLC, Reference Series 2011-09-27.
ISBN 9781234038557
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Förlagets beskrivning
Original publisher: Cleveland, Ohio : National Aeronautics and Space Administration, Glenn Research Center, [2011] OCLC Number: (OCoLC)743073308 Excerpt: ... Active Combustion Control - Combustion Instability Dynamics Simulation Previously, GRC, working in collaboration with industry and academia developed and demonstrated several key technologies for the active suppression of thermo-acoustic instability. These technologies included a high frequency fuel modulation valve, an actuator characterization rig, fuel delivery system dynamic models, combustion instability dynamic models, and control methods. A significant reduction in instability magnitude was demonstrated for both a high frequency ( ~ 500 Hz ) engine-like instability and a lower frequency ( ~ 300 Hz ) large amplitude instability. This was the first time such instability suppression had been demonstrated in an aero engine-like environment. Current research is investigating the application of these instability suppression technologies to advanced ultra-low emissions combustors being designed by NASA and the aerospace industry. Key to the success of this effort are simulations that can capture the instability behavior of these advanced combustors. A simulation has been developed which captures the thermo-acoustic instability behavior of an advanced, low-emissions combustor prototype as installed in the GRC CE5B flame tube. The simulation layout captures the relevant physical features of the combustor / rig. The physics-based simulation uses a Sectored 1-D approach, includes ( simplified ) reaction equations ( as opposed to just an energy source term ), and provides time-accurate results. A computationally efficient method is used for area transitions, which decreases run times. Dynamic pressure " transducers " are at two different locations downstream of the fuel injector in both the rig and the simulation to allow the approximate mode shape to be captured and compared. Reference: DeLaat, J.C., Chang, C
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Propulsion controls and diagnostics research in support of NASA aeronautics and exploration mission programs
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