Flowfield study of LDI combustor with discrete jet swirlers using re-stress model

Teo, CS; Siow, Yeow; Yang, Shiyou

doi:10.2514/6.2001-3424

Cited by 4 publications

(2 citation statements)

References 4 publications

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“…Aerodynamic characteristics of the non-reacting, swirling flow field in a lean direct injection (LDI) combustor were investigated by using Particle Image Velocimetry (PIV) (Fu et al 2007) and computational fluid dynamics (CFD) code (Teo et al 2001) respectively. The turbulent flow and flame dynamics within a lean direct fuel injection (LDI) multi-swirler gas turbine combustor were studied by using laser Doppler velocimetry (LDV), particle imaging velocimetry (PIV) and large eddy simulation (LES) (Fureby et al 2007) .…”

Section: Introductionmentioning

confidence: 99%

Investigations of Combustion Performance in LPP Combustor

Yan¹,

Liu²,

Li³

et al. 2017

JAFM

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A Lean Premixed Prevaporized (LPP) low-emission combustor which is applied with the combustion technology of staged lean fuel is developed. To study the cold flow dynamics and the combustion performance of the LPP combustor, both experimental tests using the Particle Image Velocimetry (PIV) to quantify the flow dynamics and numerical simulation using the Fluent software are conducted respectively. To investigate the emissions of the LPP combustor, four kinds of inlet conditions (viz. 7%, 30%, 85% and 100% F ∞ (Thrust Force)) were conducted using numerical simulation. Numerical results are in good agreement with the experimental data. Results show that:1) a Primary recirculation zone (PRZ), a Corner recirculation zone (CRZ) and a Lip recirculation zone (LRZ) exist in the LPP combustor, and the velocity gradients between pilot swirling flow and primary swirling flow have contributed to the exchanges of mass, momentum and energy. 2) With the decrease of thrust force, NO mass fraction, CO2 mass fraction and total pressure losses at the exit of LPP combustor fall gradually. 3) Thermal NO formation rate closely relate to the zone area where gas temperature overruns 1900K and the maximum temperature in LPP combustor. 4) The combustion performance of the LPP combustor proposed in this paper is very well, and through comparative analysis with four kins of typical gas tubine combustor, the NO emission is very low and is equivalent to the CAEP6 43.87%.

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Section: Introductionmentioning

confidence: 99%

Investigations of Combustion Performance in LPP Combustor

Yan¹,

Liu²,

Li³

et al. 2017

JAFM

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“…Flow dynamics is foundational for researching fuel spray and combustion in low-emission combustors. Aerodynamic characteristics of the non-reacting, swirling flow field in an LDI combustor were investigated by using Particle Image Velocimetry (PIV) (7) and Computational Fluid Dynamics (CFD) code, (9) respectively. The turbulent flow and flame dynamics within an LDI multi-swirler gas turbine combustor were studied by using LASER DOPPLER June 2017 The Aeronautical Journal VELOCIMETRY (LDV), Particle Imaging Velocimetry (PIV) and Large Eddy Simulation (LES) (10) .…”

Section: Introductionmentioning

confidence: 99%

Experimental and computational investigations of flow dynamics in LPP combustor

Yan

Liu

et al. 2017

Aeronaut. j.

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A Lean Premixed Prevaporised (LPP) low-emission combustor with a staged lean combustion technology was developed. In order to study cold-flow dynamics in the LPP combustor, both experimental tests using the particle image velocimetry (PIV) to quantify the flow dynamics and numerical simulation using the commercial software (FLUENT) were conducted, respectively. Numerical results were in good agreement with the experimental data. It is shown from the observation of the results that: there is a Primary Recirculation Zone (PRZ), a Corner Recirculation Zone (CRZ) and a Lip Recirculation Zone (LRZ) in the LPP combustor, and the exchanges of mass, momentum and energy between pilot swirling flow and primary swirling flow are contributed by the velocity gradients, and the shear flow is transformed into a mixing layer exhibiting the higher Reynolds stresses, which suggests the mixing process is strictly affected by the Reynolds stresses.

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Numerical Study of Nonreacting Gas Turbine Combustor Swirl Flow Using Reynolds Stress Model

Yang

Siow

Peschke

et al. 2003

Journal of Engineering for Gas Turbines and Power

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This paper presents recent research on the use of a Reynolds stress turbulence model (RSTM) for three-dimensional flowfield simulation inside gas turbine combustors. It intends to show the motivations for using the RSTM in engine flow simulation, to present a further validation of the RSTM implementation in the KIVA code using the available experimental data, and to provide comparisons between RSTM and k-ε turbulence model results for chemically nonreacting swirling flows. The results show that, for high-degree swirl flow, the RSTM can provide predictions in favorable agreement with the experimental data, and that the RSTM predicts recirculations and high velocity gradients better than does the k-ε turbulence model. The results also indicate that the choice of swirler has a significant influence on the structure of the combustor flowfield.

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Flowfield study of LDI combustor with discrete jet swirlers using re-stress model

Cited by 4 publications

References 4 publications

Investigations of Combustion Performance in LPP Combustor

Investigations of Combustion Performance in LPP Combustor

Experimental and computational investigations of flow dynamics in LPP combustor

Numerical Study of Nonreacting Gas Turbine Combustor Swirl Flow Using Reynolds Stress Model

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