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

Time-Resolved Particle Image Velocimetry Measurements of Nonreacting Flow Field in a Swirl-Stabilized Combustor Without and With Porous Inserts for Acoustic Control

[+] Author and Article Information
Joseph Meadows, Ajay K. Agrawal

University of Alabama,
Tuscaloosa, AL 35487

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 9, 2014; final manuscript received July 17, 2014; published online October 28, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(4), 041501 (Oct 28, 2014) (10 pages) Paper No: GTP-14-1344; doi: 10.1115/1.4028381 History: Received July 09, 2014; Revised July 17, 2014

Combustion noise and thermo-acoustic instabilities are of primary importance in highly critical applications such as rocket propulsion systems, power generation, and jet propulsion engines. Mechanisms for combustion instabilities are extremely complex because they often involve interactions among several different physical phenomena such as unsteady flame propagation leading to unsteady flow field, acoustic wave propagation, natural and forced hydrodynamic instabilities, etc. In the past, we have utilized porous inert media (PIM) to mitigate combustion noise and thermo-acoustic instabilities in both lean premixed (LPM) and lean direct injection (LDI) combustion systems. While these studies demonstrated the efficacy of the PIM concept to mitigate noise and thermo-acoustic instabilities, the actual mechanisms involved have not been understood. The present study utilizes time-resolved particle image velocimetry (PIV) to measure the turbulent flow field in a nonreacting swirl-stabilized combustor without and with PIM. Although the flow field inside the annulus of the PIM cannot be observed, measurements immediately downstream of the PIM provide insight into the turbulent structures. Results are analyzed using the proper orthogonal decomposition (POD) method and show that the PIM alters the flow field in an advantageous manner by modifying the turbulence structures and eliminating the corner recirculation zones and precessing vortex core (PVC), which would ultimately affect the acoustic behavior in a favorable manner.

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Figures

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Fig. 1

Typical flow structures present in a gas turbine combustor with a coaxial injector

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Fig. 2

(a) Schematic diagram and (b) photograph illustrating flame stabilization with PIM

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Fig. 3

Schematic of combustor setup

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Fig. 4

Normalized vorticity contour plots (a) without PIM and (b) with PIM

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Fig. 5

Radial profiles of the normalized axial velocity at different axial locations (a) without PIM and (b) with PIM

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Fig. 6

Turbulent intensity (a) without PIM and (b) with PIM

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Fig. 7

Cumulative energy contribution

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Fig. 8

Flow field and normalized velocity magnitudes without PIM for (a) instantaneous velocity field and (b) reconstructed velocity field

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Fig. 9

Flow field and normalized velocity magnitude with PIM for (a) instantaneous velocity field and (b) reconstructed velocity field

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Fig. 10

POD modes 0–5 without PIM

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Fig. 11

POD modes 0–5 with PIM

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