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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Assessment of Different Actuator Concepts for Acoustic Boundary Control of a Premixed Combustor

[+] Author and Article Information
Mirko R. Bothien, Jonas P. Moeck

Institut für Strömungsmechanik und Technische Akustik, Technische Universität Berlin, 10623 Berlin, Germany

Christian Oliver Paschereit

Institut für Strömungsmechanik und Technische Akustik, Technische Universität Berlin, 10623 Berlin, Germanymirko.bothien@tu-berlin.de

J. Eng. Gas Turbines Power 131(2), 021502 (Dec 24, 2008) (10 pages) doi:10.1115/1.2969088 History: Received March 31, 2008; Revised April 21, 2008; Published December 24, 2008

In the design process, new burners are generally tested in combustion test rigs. With these experiments, computational fluid dynamics, and finite element calculations, the burners’ performance in the full-scale engine is sought to be predicted. Especially, information about the thermoacoustic behavior and the emissions is very important. As the thermoacoustics strongly depend on the acoustic boundary conditions of the system, it is obvious that test rig conditions should match or be close to those of the full-scale engine. This is, however, generally not the case. Hence, if the combustion process in the test rig is stable at certain operating conditions, it may show unfavorable dynamics at the same conditions in the engine. In previous works, the authors introduced an active control scheme, which is able to mimic almost arbitrary acoustic boundary conditions. Thus, the test rig properties can be tuned to correspond to those of the full-scale engine. The acoustic boundary conditions were manipulated using woofers. In the present study, proportional valves are investigated regarding their capabilities of being used in the control scheme. It is found that the test rig impedance can be tuned equally well. In contrast to the woofers, however, the valves could be used in industrial applications, as they are more robust and exhibit more control authority. Additionally, the control scheme is further developed and used to tune the test rig at discrete frequencies. This exhibits certain advantages compared with the case of control over a broad frequency band.

Copyright © 2009 by American Society of Mechanical Engineers
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Figures

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Figure 1

System with different acoustic boundary conditions induced by a change in geometry or by implementation of a liner

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Figure 2

Schematical setup of the control concept for manipulation of the acoustic boundary condition of a duct

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Figure 3

Control schematic for impedance tuning at discrete frequencies

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Figure 4

Network representation of the test rig

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Figure 5

Setup for online wave identification with multiple microphones

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Figure 6

Block diagram mapping n measured pressures to the downstream traveling wave f

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Figure 7

Schematic setup of the atmospheric test rig

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Figure 8

Setup of the DDV mounted at the downstream end of the test rig

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Figure 11

Top: spectra of acoustic pressure; bottom: spectra of OH-chemiluminescence. Without control (◻); |Rcl|=1—with different additional lengths (○ and ×). Downstream reflection coefficient is tuned for frequency range.

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Figure 12

Downstream reflection coefficient. Without control (◻); |Rcl|=1—with different additional lengths (○ and ×).

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Figure 13

Upstream reflection coefficient Rus comprising the flame response

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Figure 14

Top: spectra of acoustic pressure; bottom: spectra of OH-chemiluminescence. Without control (◻); |Rcl|=1−85 Hz (○) and 70 Hz (×). Downstream reflection coefficient is tuned at discrete frequencies.

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Figure 15

Top: spectra of acoustic pressure; bottom: spectra of OH-chemiluminescence. Without control (◻); |Rcl|=1−185 Hz (○) and 175 Hz (×). Downstream reflection coefficient is tuned at discrete frequencies.

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Figure 16

Influence of limitation of control signal on closed-loop reflection coefficient (|Rcl| solid; φcl dashed). The system is tuned to generate an instability at 85 Hz.

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Figure 17

Influence of the limitation of control signal on closed-loop reflection coefficient (|Rcl| solid; φcl dashed). The system is tuned to generate an instability at 175 Hz.

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Figure 10

Top: spectra of acoustic pressure; bottom: spectra of OH-chemiluminescence. Without control (◻—with orifice and ◇—without orifice); |Rcl|=1—with different additional lengths (Δl=0 m, ○; Δl=0.5 m, ×; and Δl=2 m▽). Downstream reflection coefficient is tuned for frequency range.

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Figure 9

Downstream reflection coefficient. Without control (◻—with orifice and ◇—without orifice); |Rcl|=1—with different additional lengths (Δl=0 m, ○; Δl=0.5 m, ×; and Δl=2 m, ▽).

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