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TECHNICAL PAPERS: Gas Turbines: Combustion and Fuels

Liquid Fuel Combustion Using Heat Recirculation Through Annular Porous Media

[+] Author and Article Information
E. Ryan Newburn1

School of Aerospace and Mechanical Engineering, University of Oklahoma, Norman, OK 73019

Ajay K. Agrawal2

Department of Mechanical Engineering, University of Alabama, Tuscaloosa, AL 35487

1

Presently at General Electric Company, GE Aviation, Evandale, OH.

2

Corresponding author.

J. Eng. Gas Turbines Power 129(4), 914-919 (Jan 21, 2007) (6 pages) doi:10.1115/1.2719259 History: Received October 26, 2005; Revised January 21, 2007

A counter-flow annular heat recirculating burner was designed for lean prevaporized, premixed combustion. Prior to entering the combustor, the reactants are passed through a porous media-filled preheating annulus surrounding the combustor. Kerosene is dripped by gravity onto the porous media and vaporized by the heat conducted through the combustor wall. Experiments were conducted to evaluate heat transfer and combustion performance at various equivalence ratios, heat release rates, and inlet air temperatures. Results show low CO emissions over a range of equivalence ratios. NOx emissions were high at high heat release rates, indicating inadequate prevaporization and premixing of fuel with air. Heat recirculation and heat loss characteristics are presented at various operating conditions.

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Copyright © 2007 by American Society of Mechanical Engineers
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Figures

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Figure 2

Exterior surface temperature profiles at steady state for ϕ=0.57.

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Figure 1

System configuration: overall system (Left), combustor details (Right)

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Figure 9

Effect of air temperature on (a) Pre-heat temperature, (b) percent heat loss, (c) percent heat recirculation

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Figure 8

Effect of inlet air temperature: (a) CO (top) and (b) NOx (bottom)

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Figure 7

(a) Preheat temperature, (b) percent heat loss, and (c) percent heat recirculation

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Figure 6

Emissions versus equivalence ratio in the center point at the combustor exit plane: (a) CO (top) and (b) NOx (bottom)

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Figure 5

Emissions profiles at the combustor exit plane: (a) CO (top) and (b) NOx (bottom)

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Figure 4

Emissions in the streamwise direction at r=0.0cm: (a) CO (top) and (b) NOx (bottom)

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Figure 3

Radial temperature profile at the combustor exit (z=27.2cm)

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