Numerical analysis on hydrogen swirl combustion and flow characteristics of a micro gas turbine combustor with axial air/fuel staged technology

Liu, Hong; Zeng, Zhuoxiong; Guo, Kaifang

doi:10.1016/j.applthermaleng.2022.119460

Cited by 19 publications

(9 citation statements)

References 25 publications

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“…The geometric structure of the combustion chamber in this paper is shown in Figure 1, and it is based on a prototype with two-stage swirling combustion from an industrial micro gas turbine. 20 The combustion chamber outlet has a diameter of 109 mm and a total length of 451.75 mm. There are two inlets in the combustion chamber, of which the swirl inlet has an inner diameter D 0 of 10 mm and an outer diameter of 38 mm, the annular direct injection inlet has an inner diameter D d, inner of 42 mm and an outer diameter D d, outer of 104 mm.…”

Section: Geometric Modelmentioning

confidence: 99%

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Analysis of vortex combustion flow in a chamber of guide ring coupling with swirl flow

Sun,

Zeng,

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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To investigate the impact of different vortex structure on the combustion stability in a chamber, this paper evaluates the performance of a vortex combustion chamber coupled with a swirler and a guide ring. The simulated cases include different guide ring angles of 95°, 105°, 115°, 125° and 135°, in addition to a control case without coupling the guide ring. The distributions of velocity, vorticity, temperature, outlet temperature distribution factor ( OTDF), reaction rate, turbulent kinetic energy ( k), synergy angle ( β), and NO emission are numerically analyzed. Results show that the coupling of the swirler and guide ring changes the vortex structure and significantly influences the chamber performance. The increase of the guide ring angles ( α) enhances the interaction between the swirl flow and the direct jet, which intensifies heat and mass transfer, as well as turbulence. The application of the guide ring induces external entrainment of the jet, leading to the formation of a large central recirculation zone compared to that without a guide ring. With increasing the α from 95° to 135°, both average outlet velocity and tangential velocity ( Vt) at the coaxial line position decrease, while the flame length decreases by 286 mm. And the OTDF variation among all cases is less than 0.065. The β of the central section decreases from 76.18° to 70.17°. Furthermore, combustion chamber without the guide ring exhibits higher temperature and OTDF.

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Section: Geometric Modelmentioning

confidence: 99%

“…Thermodynamic NO model is chosen to predict NOx emissions. 20 The fuel is hydrogen and a one-step reaction between hydrogen and air is used.…”

Section: Modeling and Solutionmentioning

confidence: 99%

Analysis of vortex combustion flow in a chamber of guide ring coupling with swirl flow

Sun,

Zeng,

2023

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…The optimal relationship between the axial liner length and fuel hole diameter is proposed 23,24 . Liu et al analyzed the effects of the two staging techniques on combustion characteristics and emissions, fuel staging has a more significant effect on reducing NO emission than air staging 25 …”

Section: Introductionmentioning

confidence: 99%

“…23,24 Liu et al analyzed the effects of the two staging techniques on combustion characteristics and emissions, fuel staging has a more significant effect on reducing NO emission than air staging. 25 Microgas turbine has the characteristics of compact structure, strong fuel versatility, and flexible use, but it also faces the problem of reducing pollutant emission. Due to size and space constraints, the formation of full premixed fuel and air in the combustor of microgas turbine becomes the key to the research of low-emission combustion technology of microgas turbine.…”

Section: Introductionmentioning

confidence: 99%

Study on combustion performance of microgas turbine combustor with different fuels

Liu

Xinci

et al. 2023

Energy Science & Engineering

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A low‐pollution single‐tube microgas turbine combustor using different gas fuels was studied. The combustion performance of two kinds of landfill gas and natural gas was tested in a single‐head combustor. The effects of fuel nozzle position, and the fuel distribution ratio between pilot and main combustion stage on pollutant emission were investigated under rated load condition. The flow field, temperature field, and pollutant generation characteristics with different fuel nozzle diameters and nozzle positions were analyzed by numerical simulation. The results show that: the combustor can form an obvious central recirculation zone, which is convenient for ignition and stable flame propagation; in the case of limited premixed length, the influence of fuel nozzle position on fuel–air mixing uniformity is less obvious than that of fuel nozzle diameter. The fuel–air mixing uniformity plays a decisive role in the temperature field and the generation of pollutants in the combustor. The combustor has good pollutant emission characteristics, and the NOx emission can be reduced to about 10 ppmv (15% O2 concentration) under the appropriate combination of fuel nozzle diameter and position, which provides a reference for the further optimization of low‐emission combustor.

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“…In addition, the highly complex reaction kinetics associated with NH 3 make the characteristics of a three-dimensional turbulence flame still unknown for certain industrial combustors. Therefore, based on a multiple direct-injection combustor developed from the combustor of an industrial micro gas turbine, 26 the mixing characteristics of fuel−air in the mixing-nozzle are first analyzed. Subsequently, the new San Diego mechanism is used, which involves 40 reaction steps and 19 species, 27 and the flame and emission characteristics of NH 3 /H 2 /Air premixed combustion are further investigated at different equivalence ratios and hydrogen mixing ratios.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on NH₃/H₂/Air Combustion Flow in a Multiple Direct-Injection Combustor

Wu,

Zeng,

Liu

et al. 2023

Energy Fuels

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To investigate the turbulence combustion characteristics of NH 3 /H 2 /Air in a multiple direct-injection combustor, the effects of equivalence ratio and hydrogen mixing ratio on the mixing characteristics of fuel−air in the mixing-nozzles as well as the flame and emission characteristics in the combustor are analyzed numerically. The results show that the spatial mixing deficiency of fuel−air mixture at the mixing-nozzle outlet is below 1% under all circumstances, which indicates that the mixing-nozzle exhibits satisfactory mixing performance and is capable of achieving the premixed combustion. Furthermore, the intensity of gas turbulence at the mixing-nozzle outlet (inlet of the combustor) is primarily affected by the gas flow within the fuel collision zone. Regarding the flame characteristics, the larger equivalence ratio increases the NH 3 concentration (reducing combustion rate), and the larger hydrogen mixing ratio increases the gas turbulence intensity at the mixing-nozzle outlet (increasing gas flow velocity), which disrupts the stabilized combustion. Moreover, the reaction R18, NH 3 + M ⇔ NH 2 + H + M, inhibits NH 3 consumption and the reactions R20, NH 3 + O ⇔ NH 2 + OH, and R21, NH 3 + OH ⇔ NH 2 + H 2 O, promote NH 3 consumption, while R19, NH 3 + H ⇔ NH 2 + H 2 , initially inhibits and later promotes NH 3 consumption, but primarily plays an inhibitory role. Furthermore, reactions R4, NH + H ⇔ N + H 2 , R11, NH 2 + H ⇔ NH + H 2 , and R28, HNO + H ⇔ NO + H 2 , promote the H 2 formation, and R19, NH 3 + H ⇔ NH 2 + H 2 , inhibits the H 2 formation. As for the emission characteristics, R16, NH 2 + NO ⇔ N 2 + H 2 O, and R28, HNO + H ⇔ NO + H 2 , inhibit and promote NO generation in the upstream region of the combustor, respectively, while R36, NO 2 + H ⇔ NO + OH, promotes NO generation in the whole area.

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Numerical analysis on hydrogen swirl combustion and flow characteristics of a micro gas turbine combustor with axial air/fuel staged technology

Cited by 19 publications

References 25 publications

Analysis of vortex combustion flow in a chamber of guide ring coupling with swirl flow

Analysis of vortex combustion flow in a chamber of guide ring coupling with swirl flow

Study on combustion performance of microgas turbine combustor with different fuels

Numerical Investigation on NH₃/H₂/Air Combustion Flow in a Multiple Direct-Injection Combustor

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Numerical analysis on hydrogen swirl combustion and flow characteristics of a micro gas turbine combustor with axial air/fuel staged technology

Cited by 19 publications

References 25 publications

Analysis of vortex combustion flow in a chamber of guide ring coupling with swirl flow

Analysis of vortex combustion flow in a chamber of guide ring coupling with swirl flow

Study on combustion performance of microgas turbine combustor with different fuels

Numerical Investigation on NH3/H2/Air Combustion Flow in a Multiple Direct-Injection Combustor

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Product

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Numerical Investigation on NH₃/H₂/Air Combustion Flow in a Multiple Direct-Injection Combustor