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

Swirler Effects on Passive Control of Combustion Noise and Instability in a Swirl-Stabilized Combustor

[+] Author and Article Information
Alex Borsuk

The State University of New York at Buffalo,
Buffalo, NY 14260

Justin Williams

University of Alabama,
Tuscaloosa, AL 35487
e-mail: ljwilliams@crimson.ua.edu

Joseph Meadows

University of Alabama,
Tuscaloosa, AL 35487
e-mail: jwm3320@bellsouth.net

Ajay K. Agrawal

University of Alabama,
Tuscaloosa, AL 35487
e-mail: aagrawal@eng.ua.edu

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received April 28, 2014; final manuscript received May 8, 2014; published online November 11, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(4), 041504 (Apr 01, 2015) (7 pages) Paper No: GTP-14-1213; doi: 10.1115/1.4028613 History: Received April 28, 2014; Revised May 08, 2014; Online November 11, 2014

High strength porous inert media (PIM) placed in the reaction zone of a swirl-stabilized lean-premixed combustor is a passive method of controlling combustion noise and instabilities. In this study, the effect of swirler location and swirl number on combustion without and with PIM has been investigated experimentally, using a methane-fueled quartz combustor at atmospheric pressure. Three axial swirlers were designed with eight vanes, a solid centerbody, and vane angles of 30, 45, and 55 deg to yield calculated swirl numbers of 0.45, 0.78, and 1.10, respectively. Swirler location was varied to obtain recess depth in the premixer tube of 0.0 cm, 2.5 cm, and 5.0 cm. A downstream bluff body was used with the recessed swirlers to stabilize the flame at the dump plane. Experiments were conducted at constant air flow rate of 300 SLPM and equivalence ratios of 0.70, 0.75, and 0.80. PIM annular rings with increasing and decreasing cross-sectional area in the flow direction were tested, referred to as diverging and converging PIM. The performance of each test case is compared by observing the flame behavior and measuring sound pressure level (SPL) with a microphone probe. Results include total SPL and SPL in one-third octave bands. PIM proved effective in mitigating combustion noise and instability for all flush-mounted swirlers with total SPL reductions of up to 7.6 dBA. The effectiveness of the PIM generally improved with increasing equivalence ratio. Combustion instability that occurred within the frequency band centered about 630 Hz was suppressed with both PIM configurations. These results confirm that PIM is an effective method to control combustion noise and instabilities in swirl-stabilized LPM combustion.

Copyright © 2015 by ASME
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References

Figures

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Fig. 3

Schematic (top) and photograph (bottom) of swirlers with α = 30, 45, and 55 deg from left to right

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Fig. 4

PIM geometry (top) and photograph (bottom)

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Fig. 5

Features of swirl-stabilized combustor flow field at high S, with diverging PIM insert

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Fig. 6

Flushed swirler, z = 0.0 mm, α = 30 deg, and φ = 0.7

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Fig. 11

Recessed swirler, z = −50.8 mm, α = 30 deg, (a) φ = 0.70, (b) φ = 0.75, and (c) φ = 0.80

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Fig. 10

Recessed swirler, z = −25.4 mm, α = 30 deg, (a) φ = 0.70, (b) φ = 0.75, and (c) φ = 0.80

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Fig. 9

Flushed swirler, α = 30 deg, (a) φ = 0.70, (b) φ = 0.75, and (c) φ = 0.80

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Fig. 8

Recessed swirler; z = −50.8 mm, α = 55 deg, and φ = 0.8

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Fig. 7

Recessed swirler; z = −25.4 mm, α = 30 deg, and φ = 0.8

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Fig. 2

Model combustor showing inlet section, quartz chamber, PIM, and placement of swirler

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Fig. 1

Features of swirl-stabilized combustor flow field at high swirl number

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Fig. 12

Recessed swirler, (a) z = −25.4 mm, α = 30 deg, φ = 0.8 and (b) z = −50.8 mm, α = 55 deg, φ = 0.8

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Fig. 13

Flushed swirler, (a) α = 30 deg, (b) α = 45 deg, and (c) α = 55 deg

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Fig. 14

Recessed swirler, z = −25.4 mm, (a) α = 30 deg, (b) α = 45 deg, and (c) α = 55 deg

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Fig. 15

Recessed swirler, z = −50.8 mm, (a) α = 30 deg, (b) α = 45 deg, and (c) α = 55 deg

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