TECHNICAL PAPERS: Gas Turbines: Controls, Diagnostics, and Instrumentation

Active Combustion Instability Control With Spinning Valve Actuator

[+] Author and Article Information
P. Barooah, T. J. Anderson, J. M. Cohen

United Technologies Research Center, East Hartford, CT 06108

J. Eng. Gas Turbines Power 125(4), 925-932 (Nov 18, 2003) (8 pages) doi:10.1115/1.1582495 History: Received December 01, 2001; Revised March 01, 2002; Online November 18, 2003
Copyright © 2003 by ASME
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Kiel, B., 2001, “Review of Advances in Combustion Control, Actuation, Sensing, Modeling and Related Technologies for Air Breathing Gas Turbines,” AIAA Paper No. AIAA 2001-0481.
Cohen, J. M. et al., 2000, “Longitudinal-Mode Combustion Instabilities: Modeling and Experiments,” presented at the “NATO RTO Symposium on Active Control Technology for Enhanced Performance Operational Capabilities of Military Aircraft, Land Vehicles and Sea Vehicles,” Braunschweig, Germany, May 8–11.
Anderson, T. J., Proscia, W., and Cohen, J. M., 2001, “Control of a Liquid-Fuel Jet in an Unsteady Cross-Flow,” ASME Paper No. 2001-GT-0048.
Cohen, J. M., Rey, N. M., Jacobson, C. A., and Anderson, T., 1998, “Active Control of Combustion Instability in a Liquid Fueled Low-NOx Combustor,” ASME/IGTI Gas Turbine Expo and Congress, Stockholm, June.
LaScala, B., 1994, “Approaches to Frequency Tracking and Vibration Control,” Ph.D. Thesis, Department of Systems Engineering, The Australian National University, Dec.
Banaszuk, A., Mehta, P., Jacobson, C. A., and Khibnik, A., 2003, “Limits of Achievable Performance of Controlled Combustion Processes,” IEEE Trans. Autom. Control, submitted for publication.
Muruguppan, S., Park, S., Annaswamy, A. M., Ghoniem, A. F., Acharya, S., and Allgood, D. C., 2001, “Optimal Control of a Swirl Stabilized Spray Combustor Using System Identification Approach,” Paper No. AIAA 2001-0779.
Paschereit, C. O., Schuermans, B., and Campos-Delgado, D., 2001, “Active Combustion Control Using an Evolution Algorithm,” Paper No. AIAA 2001-0783.


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Comparison of combustion pressure amplitude spectra for uncontrolled and the best controlled point
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Instantaneous phase difference between Pfuel and Pcomb during closed-loop control
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Single-nozzle combustor assembly, showing choked inlet (left) and outlet (right) boundaries, fuel injector and combustor liner. Unsteady pressure measurement (PLA1C1) located at 1.865 in. downstream of combustor bulkhead. Dimensions shown are in inches.
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Schematic of the spinning valve concept, using a rotating drum with multiple holes, which align with exit holes in the case. A close tolerance was maintained to produce the maximum level of modulation and to minimize leakage. An even number of exit holes provided a pressure balance.
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Schematic of the cold flow test facility. A cooling system maintained a constant temperature despite heat added from pump work at high-pressure differentials. A high-pressure nitrogen system was used to pressurize the fuel system to realistic operating pressures.
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Time traces showing response of fuel pressure (measured downstream of the valve and upstream of fuel nozzle orifice) to 500 Hz flow modulation command (cold flow test) to the spinning valve
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Valve flow modulation capacity as a function of frequency
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Modulated fuel pressure response curves for the spinning valve as the base pressure was changed between atmospheric and combustor pressure (flow bench tests)
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Block diagram of the spinning valve controller
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Schematic of change of shaft position during several cycles of rotation. This behavior led to an ambiguity in deciding which branch to track.
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Stacking of combustor pressure phase to create a single trajectory for the spinning valve motor shaft to follow
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Response of the spinning valve in a step-input test
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Bode plot (magnitude and phase) of the identified valve transfer function and loop transfer function (product of valve and controller transfer functions Gloop=Gv*Gc)
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Time trace, amplitude spectrum and PDF of fluctuating combustor pressure in the 280 Hz instability condition (mid-power)
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Peak amplitude near 280 Hz and r.m.s. value of combustor pressure as a function of control phase, showing discrepancy between amplitude and r.m.s. attenuation
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Instantaneous difference between the phase of fuel pressure and 12* (motor shaft position) from during closed-loop control, showing “phase drift” of spinning valve control




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