Combustion Instability Suppression in Liquid-fueled Combustors PDF Download
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Author: Keith R. McManus
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Category :
Languages : en
Pages :
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Author: Keith R. McManus
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
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Category :
Languages : en
Pages : 2
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Author: J.-Y. Lee
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Languages : en
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721527069
Category :
Languages : en
Pages : 30
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An adaptive control algorithm has been developed for the suppression of combustion thermo-acoustic instabilities. This technique involves modulating the fuel flow in the combustor with a control phase that continuously slides within the stable phase region, in a back and forth motion. The control method is referred to as Adaptive Sliding Phasor Averaged Control (ASPAC). The control method is evaluated against a simplified simulation of the combustion instability. Plans are to validate the control approach against a more physics-based model and an actual experimental combustor rig. Kopasakis, George and DeLaat, John C. Glenn Research Center NASA/TM-2002-211805, NAS 1.15:211805, E-13500, AIAA Paper 2002-4075
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721591268
Category :
Languages : en
Pages : 30
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This effort extends into high frequency (>500 Hz), an earlier developed adaptive control algorithm for the suppression of thermo-acoustic instabilities in a liquidfueled combustor. The earlier work covered the development of a controls algorithm for the suppression of a low frequency (280 Hz) combustion instability based on simulations, with no hardware testing involved. The work described here includes changes to the simulation and controller design necessary to control the high frequency instability, augmentations to the control algorithm to improve its performance, and finally hardware testing and results with an experimental combustor rig developed for the high frequency case. The Adaptive Sliding Phasor Averaged Control (ASPAC) algorithm modulates the fuel flow in the combustor with a control phase that continuously slides back and forth within the phase region that reduces the amplitude of the instability. The results demonstrate the power of the method - that it can identify and suppress the instability even when the instability amplitude is buried in the noise of the combustor pressure. The successful testing of the ASPAC approach helped complete an important NASA milestone to demonstrate advanced technologies for low-emission combustors. Kopasakis, George Glenn Research Center NASA/TM-2003-212535, E-14099, NAS 1.15:212535, AIAA Paper 2003-4491
Author: George Kopasakis
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Author: C. E. Johnson
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Category :
Languages : en
Pages :
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Author: Anil Gulati
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Category : Combustion engineering
Languages : en
Pages :
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Author: George Kopasakis
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Category :
Languages : en
Pages :
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Author: Daniel Gregory Doleiden
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Category :
Languages : en
Pages : 0
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Combustion instabilities in gas turbines are associated with increased pollutant emissions, inconsistent power or thrust output, and premature wear and failure of components. Combustion instabilities arise from a feedback loop between resonant combustor acoustics and flame heat release rate oscillations and are especially of concern in modern lean-premixed combustor systems. This thesis considers the suppression mechanisms and efficacy limits of two techniques used to mitigate combustion instability: fuel staging and central piloting. Fuel staging, a technique in which the equivalence ratio of a multi-nozzle combustor is unevenly distributed between the nozzles, has been shown to mitigate the intensity of self-excited combustion instabilities in multiple nozzle combustors. Foundational work to this thesis explored the suppression mechanism of a combustor stabilized by fuel staging via an edge-tracking algorithm applied to high-speed planar video of adjacent flame edges, revealing that fuel staging de-phased adjacent flame edges, breaking the instability feedback loop. A nozzle for which fuel staging exhibited relatively lower efficacy in comparison to the other nozzles of the combustor was also investigated; this differences in efficacy was attributed to a minor variation in nozzle hardware. Central piloting suppresses combustion instability via the addition of a central torch-shaped pilot flame along the central axis of a larger main flame. The pilot flame has previously been shown to improve the static stability of the main flame by providing a source of heat and radical chemical species near the main flame base. However, the presence of the pilot flame may also enhance an instability in certain cases. This thesis studies the mechanisms and flame dynamics associated with central piloting both in cases where piloting was effective at stabilizing the combustor and in cases where the stability outcome was worsened by piloting. By studying the efficacy limits of instability suppression techniques, this thesis aims to contribute to improved thermoacoustic design tools and injector designs.
