Research Papers: Fuel Combustion

Numerical Study of the Effect of Nozzle Configurations on Characteristics of MILD Combustion for Gas Turbine Application

[+] Author and Article Information
Xiaowen Deng, Hong Yin, Qingshui Gao

Electric Power Research Institute of
Guangdong Power Grid Corporation,
Guangzhou, Guangdong 510080, China

Yan Xiong

Research Center for Clean Energy and Power,
Chinese Academy of Sciences,
Lianyungang, Jiangsu 222069, China

Contributed by the Advanced Energy Systems Division of ASME for publication in the JOURNAL OF ENERGY RESOURCES TECHNOLOGY. Manuscript received October 12, 2015; final manuscript received March 22, 2016; published online April 19, 2016. Assoc. Editor: Ashwani K. Gupta.

J. Energy Resour. Technol 138(4), 042212 (Apr 19, 2016) (8 pages) Paper No: JERT-15-1381; doi: 10.1115/1.4033141 History: Received October 12, 2015; Revised March 22, 2016

The MILD (moderate or intense low-oxygen dilution) combustion is characterized by low emission, stable combustion, and low noise for various kinds of fuel. This paper reports a numerical investigation of the effect of different nozzle configurations, such as nozzle number N, reactants jet velocity V, premixed and nonpremixed modes, on the characteristics of MILD combustion applied to one F class gas turbine combustor. An operating point is selected considering the pressure p = 1.63 MPa, heat intensity Pintensity = 20.5 MW/m3 atm, air preheated temperature Ta = 723 K, equivalence ratio φ = 0.625. Methane (CH4) is adopted as the fuel for combustion. Results show that low-temperature zone shrinks while the peak temperature rises as the nozzle number increases. Higher jet velocity will lead to larger recirculation ratio and the reaction time will be prolonged consequently. It is helpful to keep high combustion efficiency but can increase the NO emission obviously. It is also found that N = 12 and V = 110 m/s may be the best combination of configuration and operating point. The premixed combustion mode will achieve more uniform reaction zone, lower peak temperature, and pollutant emissions compared with the nonpremixed mode.

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Fig. 1

Schematic diagram of the gas turbine combustor

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Fig. 2

Three-dimensional computational domain and meshes of the combustor

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Fig. 4

Comparison of FOUR numerical simulation and experimental measurements: (a) temperature distribution of central plane and (b) Z direction velocity

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Fig. 5

Grid independence check for the case 6

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Fig. 6

Flowfield of combustor: (a) path lines of the combustor and (b) vectors near the nozzle

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Fig. 7

Pressure contours of X-Z plane

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Fig. 8

Flowfield and temperature contours of different nozzle number cases

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Fig. 9

Recirculation ratio at different height of combustor

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Fig. 10

Pollutant emissions and pressure loss of the combustor

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Fig. 11

Velocity decay along the centerline of jet nozzle

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Fig. 12

Recirculation ratio of different jet velocity

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Fig. 13

Pollutant emissions and pressure loss of the combustor

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Fig. 14

Contours of mass fraction of CH4 (YCH4) of case 8: (a) contours of YCH4, (b) contours of YCH4 near nozzle

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Fig. 15

Comparison of nonpremixed and premixed modes




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