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Research Papers

Numerical and Experimental Evaluation of a Dual-Fuel Dry-Low-NOx Micromix Combustor for Industrial Gas Turbine Applications

[+] Author and Article Information
Harald H. W. Funke

Department of Aerospace Engineering,
Aachen University of Applied Sciences,
Hohenstaufenallee 6,
Aachen 52064, Germany
e-mail: funke@fh-aachen.de

Nils Beckmann

Department of Aerospace Engineering,
Aachen University of Applied Sciences,
Hohenstaufenallee 6,
Aachen 52064, Germany
e-mail: n.beckmann@fh-aachen.de

Jan Keinz

Department of Aerospace Engineering,
Aachen University of Applied Sciences,
Hohenstaufenallee 6,
Aachen 52064, Germany
e-mail: keinz@fh-aachen.de

Sylvester Abanteriba

RMIT University School of Engineering,
124 La Trobe Street,
Melbourne 3000, Victoria, Australia
e-mail: sylvester.abanteriba@rmit.edu.au

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received October 20, 2017; final manuscript received September 13, 2018; published online October 23, 2018. Assoc. Editor: Ting Wang.

J. Thermal Sci. Eng. Appl 11(1), 011015 (Oct 23, 2018) (9 pages) Paper No: TSEA-17-1402; doi: 10.1115/1.4041495 History: Received October 20, 2017; Revised September 13, 2018

The dry-low-NOx (DLN) micromix combustion technology has been developed originally as a low emission alternative for industrial gas turbine combustors fueled with hydrogen. Currently, the ongoing research process targets flexible fuel operation with hydrogen and syngas fuel. The nonpremixed combustion process features jet-in-crossflow-mixing of fuel and oxidizer and combustion through multiple miniaturized flames. The miniaturization of the flames leads to a significant reduction of NOx emissions due to the very short residence time of reactants in the flame. The paper presents the results of a numerical and experimental combustor test campaign. It is conducted as part of an integration study for a dual-fuel (H2 and H2/CO 90/10 vol %) micromix (MMX) combustion chamber prototype for application under full scale, pressurized gas turbine conditions in the auxiliary power unit Honeywell Garrett GTCP 36-300. In the presented experimental studies, the integration-optimized dual-fuel MMX combustor geometry is tested at atmospheric pressure over a range of gas turbine operating conditions with hydrogen and syngas fuel. The experimental investigations are supported by numerical combustion and flow simulations. For validation, the results of experimental exhaust gas analyses are applied. Despite the significantly differing fuel characteristics between pure hydrogen and hydrogen-rich syngas, the evaluated dual-fuel MMX prototype shows a significant low NOx performance and high combustion efficiency. The combustor features an increased energy density that benefits manufacturing complexity and costs.

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Figures

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Fig. 1

Section view of a micromix combustor

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Fig. 2

Geometry of a typical micromix combustor

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Fig. 3

Schematics of the micromix combustor geometry, detailing the recirculation zones and aerodynamic flame stabilization

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Fig. 4

Computational domain of the derived slice model

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Fig. 5

Schematics of the atmospheric test rig

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Fig. 6

Sketch of a DLN micromix test-burner, detailing the measurement grid and coordinate system

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Fig. 7

Flame images of hydrogen (left) and syngas (right) micromix flames at Φ = 0.4

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Fig. 8

Simulated temperature distribution on the central symmetry plane for hydrogen (top) and syngas combustion (bottom) at Φ = 0.4

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Fig. 9

Spatial development of the simulated combustion efficiency η as function of the sampling position z for hydrogen (gray) and syngas combustion (black) at Φ = 0.4

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Fig. 10

Simulated flow path of hydrogen and syngas fuel jets in air crossflow at Φ = 0.4

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Fig. 11

Numerical and experimental results of exhaust O2 volume fractions for H2 and syngas combustion

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Fig. 12

Numerical and experimental results of unburned fuel emissions (mole fractions) for H2 and syngas combustion

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Fig. 13

Numerical and experimental results of overall combustion efficiencies η for H2 and syngas combustion

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Fig. 14

Numerical and experimental results of NO/NOx emissions corrected to 15 vol % O2 for H2 and syngas combustion

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Fig. 15

Spatial distribution of the molecular production rate of NO on the central symmetry plane for hydrogen (top) and syngas combustion (bottom) at Φ = 0.4

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