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

Impact of Precessing Vortex Core Dynamics on Shear Layer Response in a Swirling Jet

[+] Author and Article Information
Mark Frederick

Mechanical Engineering,
The Pennsylvania State University,
University Park, PA 16802
e-mail: mdf5282@psu.edu

Kiran Manoharan

Indian Institute of Science,
Bangalore 560012, India
e-mail: kiranm@aero.iisc.ernet.in

Joshua Dudash

Mechanical Engineering,
The Pennsylvania State University,
University Park, PA 16802

Brian Brubaker

Mechanical Engineering,
Texas A&M University,
College Station, TX 77843

Santosh Hemchandra

Indian Institute of Science,
Bangalore 560012, India
e-mail: hsantosh@aero.iisc.ernet.in

Jacqueline O'Connor

Mechanical Engineering,
The Pennsylvania State University,
University Park, PA 16802
e-mail: jxo22@engr.psu.edu

1Corresponding author.

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received August 2, 2017; final manuscript received August 22, 2017; published online January 17, 2018. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(6), 061503 (Jan 17, 2018) (10 pages) Paper No: GTP-17-1429; doi: 10.1115/1.4038324 History: Received August 02, 2017; Revised August 22, 2017

Combustion instability, the coupling between flame heat release rate oscillations and combustor acoustics, is a significant issue in the operation of gas turbine combustors. This coupling is often driven by oscillations in the flow field. Shear layer roll-up, in particular, has been shown to drive longitudinal combustion instability in a number of systems, including both laboratory and industrial combustors. One method for suppressing combustion instability would be to suppress the receptivity of the shear layer to acoustic oscillations, severing the coupling mechanism between the acoustics and the flame. Previous work suggested that the existence of a precessing vortex core (PVC) may suppress the receptivity of the shear layer, and the goal of this study is to first, confirm that this suppression is occurring, and second, understand the mechanism by which the PVC suppresses the shear layer receptivity. In this paper, we couple experiment with linear stability analysis to determine whether a PVC can suppress shear layer receptivity to longitudinal acoustic modes in a nonreacting swirling flow at a range of swirl numbers. The shear layer response to the longitudinal acoustic forcing manifests as an m = 0 mode since the acoustic field is axisymmetric. The PVC has been shown both in experiment and linear stability analysis to have m = 1 and m = −1 modal content. By comparing the relative magnitude of the m = 0 and m = −1,1 modes, we quantify the impact that the PVC has on the shear layer response. The mechanism for shear layer response is determined using companion forced response analysis, where the shear layer disturbance growth rates mirror the experimental results. Differences in shear layer thickness and azimuthal velocity profiles drive the suppression of the shear layer receptivity to acoustic forcing.

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Figures

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Fig. 1

Experimental facility

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Fig. 2

Interpolated points in cylindrical coordinates (white dots) on velocity magnitude in r–θ plane

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Fig. 3

Variation of time-averaged flow field (base flow) with swirl number in r–x (top) and r–θ (bottom) planes

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Fig. 4

Energies of POD modes 1–20 for all swirl numbers

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Fig. 5

POD reconstruction and frequency spectrum of swirl numbers that cause a PVC to be formed

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Fig. 6

Strength of PVC modes m = 1 and m = −1 for three swirl numbers as a function of radius

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Fig. 7

Distribution of modes at the PVC frequency for three swirl numbers and r/D = 0.7

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Fig. 8

Strength of the m = 0 mode for a range of swirl numbers at the forcing frequency, 600 Hz

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Fig. 9

Distribution of modes at 600 Hz for six swirl numbers and r/D = 0.5 (a) and distribution of modes at 600 Hz and the PVC frequency for the three highest swirl numbers and r/D = 0.5(b)

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Fig. 10

Strength of the m = 0 mode for S = 0.38 and S = 1.43 at a range of forcing frequencies

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Fig. 11

Response of flow at swirl number of S = 0.38 to acoustic forcing as seen by pressure transducer and POD modes at various forcing frequencies. Forcing at 400 Hz (a), 500 Hz (b), 600 Hz (c), and 700 Hz (d).

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Fig. 12

Response of flow at swirl number of S = 1.43 to acoustic forcing as seen by PT and POD modes at various forcing frequencies. Forcing at 400 Hz (a), 500 Hz (b), 600 Hz (c), and 700 Hz (d).

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Fig. 13

Spatial Amplification envelope of flow response to forcing at 700 Hz

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Fig. 14

Variation of peak value of envelope as a function of nondimensional excitation frequencies at various swirl numbers

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Fig. 15

Radial profiles at various swirl numbers, S, of time-averaged base flow velocity components (a) U¯x and (b) U¯θ, at x/D = 0.3

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